N O T I C E This Document Has Been Reproduced From

N O T I C E

THIS DOCUMENT HAS BEEN REPRODUCED FROM MICROFICHE. ALTHOUGH IT IS RECOGNIZED THAT CERTAIN PORTIONS ARE ILLEGIBLE, IT IS BEING RELEASED IN THE INTEREST OF MAKING AVAILABLE AS MUCH INFORMATION AS POSSIBLE KSC Historical Report No. 1 (KHR-1, Revised 1979) Eastern Test Range (ETR) July 1980 Western Test Range (WTR)

A Summary of Major NASA Launches October 1,1958 - December 31,1979

1 A (NASA-TI-81 106) ). SUIIIARY 01 IAJOR NASA N80- 28386 LAUIVICRXS, 1 OCTOBER 1958 - 31 JECEIBEB 1979 (NASA) 201 p HC AlO/BF A01 CSCL 22A TJocl as

, THOR MERCURY DELTA MERCURY ATLAS ATLAS GEMINI TlTANIll-E SATURN SATURN ACOLLO DELTA REOSTONE ATLAS AGENA CENTAc ,- TITAN II CENTAUR I I8 SATURN V SKYACOLLO LA8 SPACE SHUTTLE FORE WORU

With the publ ication of this edition, "A Slmary of Major NASA Launches" nw spans more than twenty-one years in the launch history of the Nationa: Aeroriautics and Space Administrat.~on, frorn October 1, 1958, through Decanber 31, 1979. The initial brief sumnary of NASA Atlantic Missile Range (AMR) launches was prepared in 1962 as a reference tool for internal use within the Launch Operations Center Historical Branch. Repeated requests for infor~natioriconcerning f4ASA launch activities warranted the presentation of this information in handy form for broeder distribution. The Summary now includes major NASA launches conducted under the direction of the John F. Kennedy Space Center (or its precursors) from the Eastern and Western Test Ranges. It does not include launches of non-mi 1itary, non-NASA spacecraft by the U.S. Air Force or launches of the small NASA Scout vehicle. This edition supersedes 811 previous issues of this Historical R~port.

The rnateri a1 contai ned in this report was compi 1ed from several different sour'ces. Docunents consulted include: Operations Sumnaries, post-launch Flash ~lisht Reports, Final Field Reports, Mission Operations Reports (both pre-launch and post-launch), and Satellite Situation Repor&. Other major references were publications of the NASA Historical Office, such as: Aeronautics and Astronautics 1916-1960; Aeronautical and Astronautical E vents of 1961-1962 ; Aeronautics and Astronautics (yearly editions since f96T,mgs Pocket Statistics (published monthly). The writer is indebted to Mr. Marven R. Whipple, USAF ETR Historian, now retired, for providing data not otherwise available, and to Mr. William A. Lockyer, who prepared the previous edition of this report. Ms. Donna A. Clement, Mr. Joseph L. Green, and Mr. Hubert E. Griggs, McGregor-Werner Information Services Unit, provided valuable editorial assistance.

The report is divided into projects within broad mission categories. Individual launches are listed In chronological order vif5in the categories. Mission results have been categorized as: successful (S); unsuccessful (U) ; or, pdrtially successful (P). A successful launch, fol lowed by a spacecraft fai lure, is designated (P). These are arbitrary classifications, made after a comparison of objectives and actual resul ts.

A similar document, prepared in chart form, is available up011 request. Comnents, criticismns, and suggest ions for the ilnprove~nentof this publ ication are sol icited. Correspondence should be addressed to KSC Historical Services (SI-SRV- 1) , John F. Kennedy Space Center, tIASA, Kennedy Space Center, Florida 32899. Francis E. Jarrett KX Historian ...... a*.*...... a*...... me...... a.m...... mn. om a*. .. :zme :... : : il...... na.....J ... z %%: :H =I- .W z 32 . .I- W JY. L uu. .m.- -1JCYLIC 9 eor -00 0 WWW* WWWW a Lza>% OO=rQ?L 2 --u==) naemJ or I 3 A ...... 0...... h.. ... :::i#::...... 0.0 ...... C...... Is...... V). . ... ::::%:: ...... u.. ... n... .. V)...Wr. ... .C ...... Oh. =:..n.. n***d*. .V) . C...-l.. .O u. . OW" . .W 0. .+V) . . 0- :s W .u 3 : c, :d, :*- : -w. . -I .O .A V)t A .L .UW 0'- .CC WA :U .zn -u-ad : i#ii CV) m-Y) .OC ess ZUO :zgi : ZzS z3z AUA CkJY *L-J.> :. >-au :ws. ewu- CYCU .A- sOe wmr .u(1 An V) 0 .LO mcnn e0-l 2si OOC .uO * nzw CU .CP: CWC 0-a *ua . Z U w u maw : -mum a-1n .WC Qca uuo .nu az .or OZZ LOV) . I%T -+aL-0 .** . CWS meem +z 51m03*C-o w * a: W0OCPOV)V)L' OQW AOCQZOOC 00- w-r-WWW * wwe Cb-Zaa3E m '3aJ

TABLE OF COHTENTS (Continued)

PAGE

MANNED SPACE FLIGHT MERCURY

GEMINI

APOLLO

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APPENDICES

A: SUMMARY OF LAUNCHES PRIOR TO OCTOBER 1958 IN SPACE PROJECTS LATER TRANSFERRED TO MSA VANGUARD**aa*aa*...aaaaa~aca~~aaaa~aaaaaaaaaaaaaaaaaaaaaaaaaaaaaaaaaaaaaaaaaaA02 EXPLORERaaaaa*a*aaaaaaaaa~aaaaaaa~aaa~a~aaaaaaaaaaaaaaa*aaaaaaaaaaa*aaaaaaaaaaaaA-6 PIONEERa*.a.aao.aa*aa**aaaaaa*aeaaa~*aaaa a.aaaaaa.aaaa*aaaaa*aaaaaa*aa*aa~aa*aaaaaa*aaa A09 8: CHRONOLOGICAL IfiDEX OF LAUNCHES~~.a*.*.a~aaaaa*a~~~a~aa*aaa*aaaaa**a*a**a*aaaaaaaaaaaaa8-1 C: ALPHABETICAL INDEX OF LAUNCHESaa~~aa.....~..a~~aaa*oaaaaa**~aaaaaaaaaaaaaaaaC-1 a, 9 9 5?8 rC) c-* 4s %a- -- m SF+@ r a* a @4Q)O'II -"Ps *r. U- OS'SaO~*~Z rw- &e t! g$ s""> 4 C'rU' 4zms= L ow- Y) -@- as VL su- -0)OY)~gl*gte taB=I6 vDz'E@ 2s9 '3 z L@C na~umo m* urL I ameg ~NS0 04 n uuwB 0 - - I P (nhr 0 cn COW Po@mw 0)dOIOU 3-n @ '~~'5 mu, 0) c u, 0)m 1 ce, a, Et &rI wgscll$Zi L--EWY) 0- u,rcn- C worn% --BOcrPLE 0) ULO P"P g x zc cz 8=5 cll r,c.aiiCU 3 -2%C &

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A h u LL 7 -w rJ ZS urn 4 urn 'Qrn ,a 4 2.2 or: C,dv 0 1 or: 3s Flal aQ) 5s 53 > 3- m= 3-59 3- PHYSICS AND ASTRONOMY (continued)

Mission Launch Launch NASA Sitc/ Name Date/Time Vehicle -Code -Pad Renarks/Resul ts Explorer 12 15 Aug 61 Delta S-3 ETR 37.64-kg (83-lb) spacecraft designed to provide 2221 EST DM-19 17A data on magnetic fields, energetic partfcles, and (Del ta-6) solar wind. Data received from all utperiaents; transmitted until 6 December 1961; re-entered in Septenber 1963. (S)

Explorer 14 2 Oct 62 Delta S-3a ETR 36.28-kg (80-1 b) spacecraft injected into highly I 1711 EST DSV-3A 170 elliptical orbit--98,476 x 280 km (61,190 x 974 I (Del ta-13) sm), inclination 33O, period 36.4 hours. Energetic particles experiment. Sti11 in orbit, but orbital elements no longer maintained. Data transmission continued until 10 August 1963. (S) Explorer 15 27 Oct 62 Delta S-3b ETR A 44.45-kg (98-lb) satellite to stu4y artificial 1815 EST DSV -3A 178 radiation belt. High spin rate, still in orbit, (Del ta-14) but orbital elements no longer maintained. (S)

Explorer 17 2 Apr 63 Del ta S-6 ETR A 183.7-kg (405-lb) satellite studied density, 2100 EST DSV-3B 17A pressure, composition, and temperature of the (Del ta-17) Earth's upper atmosphere. Re-entered on 24 November 1966. (S)

Explorer 18 26 Nov 63 Del ta IMP-A ETR Successful launching of an Interplanetary hi tor- 2130 EST DSV- X (S-74) 170 ing Probe; its mission was to measure the f~jor (Del ta-21) magnetic field phenomena in space, incfudijcg the interplanetary magnetic field, interactiws of the streaming solar plasma, and the qeomagnetic field, galactic and solar radiation. Rz-entered in Decelllber 1965. (S) \ we k-h Ecno Wrc

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-e- CU Q) I Sr- W UV (Om@ C-r @I- =Is FWQ) 'waJ acne A> no- PHYSICS AND ASTRONOMY (continued)

Mission Launch Launch NASA Site/ Name .Date/Time Vehicle -C ode -Pad Remarks/Resul t s Explorer 31 28 Nov 65 Thor-Agena DME-A WTR Dual launch of 98.88-kg (218-lb) spacecraft with 2349 EST (Thrust- SLC-2E Alouette 2 (total pa: load 245 kg--541 lb). Com (2049 PST ) Augmented) plemented A1 ouette by taking measurements of iono- (Thor- spheric characteristics with a companion Agena-5) spacecraft as part of ISIS-X program. Sti11 in orbit ; sti11 transmitting. Orbital parameters are: 2,939 x 505 krn (1,826 x 314 sm), period 121 mins, inclination 79.s0. (S)

E~plorer32 25 May 66 Dei ta AE-B ETR Atmosphere Explorer; the 224.5-kg 1495-lb) payload 0900 EST DSV-3C (S-6 a) 178 was desi gned to col 1ect temperat composition, (Del ta-38) density, and pressure data to perlnlt the study of the physics of the atmosphere on a global basis. Still in orbit--1,664 x 255 km (1,034 x 158 sm), period 104 mins, inclination 64.6'. (S)

Explorer 33 1 Jul 66 Delta IMP-D ETR Anchored Interplanetary Wni toring Pl a+.form 1102 EST DSV-3E 17A (AIMP), designed to become the nation's first Moon (Del ta-39) sate1 1 ite. However, the second stage of the Delta booster accelerated too rapidly for the retro-rac- ket compensation necessary to achieve lunar orbit. The 56.7-kg (125-1 b) spacecraft went into a looping Earth orbit and sent back information on radiation, magnetic fields, and solar winds. It is still in , rbit, but orbital elements are not mai ntained. (S)

Explorer 34 24 May 67 Delta IMP-F W TR Interplanetary Monitoring Platform (IMP), satel- I - 1006 EDT DSV-3: SLC-2E lite to study solar and galactic cosmic radiation, 1 (0706 PDT) (Del ta-49) sol ar plasma, and re1ated phenomena. Highly elliptical polar orbit. All eleven experiments 3 functioned. Re-entered 3 May 1969. (S) PHYSICS AND ASTRONOMY (continued)

Mission Launch Launch NASA Site/ Name DateITime Veilicle -Code -Pad Expl orer 19 Jul 67 Delta IMP-E ETR Explorer 35 was the 50th Delta launch for NASA, of 1019 EST DSV-3E 178 which only three failed, a 94% success. The (be1 ta-50) 106.5-kg (235-1 b) sate1 1i te, an Interplanetary Monitoring Platform, studied interplanetary space phenomera vi:h emphasi s on study of solar wind and rnagrietic iield at lunar distances. Explorer 35 is in a selenocentric orbit around the Moon. (S)

Explorer 38 4 Jul 68 Del ta RAE --k The 190.5-kg (420-1 b) spacecraft, a Radio 1326 EDT DSV-3J Astronomy Explorer, was injected into a near- (1026 PDT) (Del ta-57) circular orbit. Mission int~ndedto investigate sporadic radio bursts from Jupiter, Earth, and the Sun; radio emission from discrete cosmic sources; plasma oscillations and background radio mission from galactic sources. Still in orbit--5,865 x 5,830 km (3,644 x 3,623 sm), period 224 mins, incl ination 123.9". (S)

Explorer 41 21 Jun 69 Del td IMP-G The 79-kg (174-lb) spacecraft was launched into a 0448 EDT DSV- 3E highly elliptical , 129,912 x 343 km (80,723 x 213 (0148 PDT) (Del ta-69) sm) orbit with a 3-day, 9-hour, 46-minute period. This was the seventh of 10 missions, beginning with the launch of Explorer 18 (IMP-A) 26 Nov 63. Twelve experiments were aboard the spacecraft to measure cos~icrays, sol ar plasmas, and magnetic fields in interplanetary space. Solar proton data acquired by this spacecraft supported the Apol lo missions. Re-entered atmosphere 23 December 1972. (S) PHYSICS AND ASTRONOMY (continued)

Mission Launch Launch NASA Site/ Name Date/Ti me Vehicle -Code P& -RemarksIResul ts Explorer 43 13 Mar 71 Del ta IMP- I ETR After first launch attempt on 12 Mar was scrubbed 1115 EST D SV- 3M-6 17A due to problem in second stage, Delta-83 success- (Del ta-83) ful ly launched 288- kg (635-1 b) spacecraft into highly el1 iptical orbit with 206,049-kin (128,039-sm) apogee, 241-km (150-sm) perigee, 28.6' inclination and 6,012-min period. Eighth of ten approved IMP spacecraft, Explorer 43 was designed to provide a detailed understanding of regions broadly surveyed by previous seven. First launch from ETR of Delta wi;h six solid motors strapped to first stage and second stage restart capabi 1i ty. Spacecraft re-entered 2 Oct 1974. (s

Explorer 47 22 Sep 72 Delta IMP-H ETR Ninth of current ly-approved IMP series, the 376-kg 2i20 EDT DSV - 3N- 11A 178 (829-1 b) spacecraft was successfully launched on (Del t a-90) schedule into elliptical transfer orbit. On 25 Sept, satellite kick motor was fired to inject spacecraft into near-ci rcular 235,639 km (146,427 sm) by 201,599 km (124,274 sm) orbit about halfway between Earth and Moon, and changing its inclination (to 17-21') to provide the optimum science. Period was 12.3 days. Mc--2 than six months after launch, 12 of 13 scientific instruments aboard sate11 i te were sti11 operational, providing detai led data on the solar-lunar-terrestrial re1ationship. Sti 11 in orbit at 253,505 x 180,415 km (157,520 x 112,105 sm) with a period of 12 days, 3 hrs, 36 mins and incl ination of 43.8'. Sti11 transmitting. (S) PHYSICS AND ASTRONOMY (continued)

Mission Launch Launch NASA Site/ Name DateITime Vehicle -Code -Pad Remarks/Results Explorer 49 10 Jun 73 Del ta RAE-B ETR After a 24-hour delay due to spacecraft problems, 1013 EDT DSV-3 P- 11 178 the 330-kg (728-1 b) RAE payload was launched on (Del ta-95) time for its lunar trajectory. Launch trajectory was so accurate that only one of two planned mid-course corrections was required. At 0321 EDT 15 June, the spacecraft's lunar insertion motor - was fired to place it in a lunar orbit with an apocynthion of 1,334 km (829 sm) and a pericynthion of 1,123 km (698 sm) at an inclination of 61.3O prograde to the lunar equator. On 18 June the lunar Insertion motor was jettisoned and the spacecraft's Velocity Control Propulsion System was fired in the first of a series of maneuvers to circularize the orbit. With its antenna array measuring 458 meters (1,503 feet) tip-to-tip, Explorer 49 was, in physical dimensions, the largest man-made c3ject to circle the Moon. Its instrwnents studied low-frequency radio emissions from the solar system and other gal act ic and extragal act ic sources. In sel enocentric orbit. (S) PHYSICS AND ASTRONWY (continued)

Mission Launch Launch NASA Site/ Name Date/Time Vehicle Code -Pad Remarks/Resul ts Explorer 50 25 Oct 73 Del ta IW-3 ETR This 398-kg (877-lb) satellite was injected into a 2226 EDT DSV- 3N 178 highly elliptical orbit--286,125 x 155,975 km (Del ta-97) (177,795 x 96,921 sm); incl ination 27.8'; 12-day, ll-hour, 45-min period. Launch was delayed because an operator flipped the wrong switch at T-10 seconds in the countdown. Engine ignition did not occur on time an3 the count was recycled to T-3 minutes. Second attempt was successful. Interplanetary fbnitoring Platform-3 (IMP-J) per- f owned detai led studies of energetic and charged particles in the near-Earth interplanetary envf - ronment and explored the Earth's magnetosphere. One of the 2 electronic field antennas failed, reducing some of the scientific return of the mission. Still transmitting; in orbit 240,845 x 191,302 km (149,654 x 118,869 sm). (S) Explorer 51 16 Dec 73 Delta AE-C WTR Atmosphere Explorer-C was the first spacecraft in 0100 EST DSV- 3N- 1A SLC-2W a series of Atmosphere Explorers equipped with un- (15 Dec 73) (Del ta-99) usually powerful on-board propulsion systems, to (2218 PST) a1 low them to make large orbital corrections. AE-C was bui 1t to withstand atmospheric friction. It "dipped" into the atmosphere and then out again on each orbit. Its highly elliptical orbit measured 4,199 x 156 km (2,672 x 97 sm), with an inclination of 68.1° and a period of 2 hours, 12 minutes, 30 seconds. Purpose of this orbit was to a1 1ow the spacecraft to invest igate photo-chemical processes and energy transfer mechanisms accompanying the absorption of solar ultraviolet radiation in the low a1 t itude regions. Re-entered 12 Dec 1978. (S) PHYSICS AND ASTRONOMY (continued) Mission Launch Launch NASA Site/ fi am Date/Time Vehicle -Code -Pad Expl orer 54 6 Oct 75 Delta AE-D WTR AE-D was nearly identical to AE-C. Its mission 0500 EDT 2910 SLC- 2W also involved taking atmspheric measurements at (0200 PDT) (Del ta-115) a1 titudes as low as 120 krn (75 sm). A€-D's initial orbit was 3,810 x 158 kin (2,367 x 97 sm), I with an inclinatisn of 90.1° and a perid of 2 hours, 7 minutes. The satell ite re-entered 12 - March 1976. (S)

Explorer 55 19 Nov 75 Del ta AE -E ETR Like its predecessors AE-C and AE-D, this Atmo- 2107 EST DSV-3P-11D 178 sphere Explorer a1 so circled the Earth, "dipping" (Del ta-117) through the atmosphere and pulling back out on each orbit. The 737-kg (1,625-1 b) spacecraft was injected into an orbit (3,026 x 158 km) (1,880 x 98 sm); inclination 19.7'; and period 1 hour, 50 minutes. Sti11 transmitting; sti11 in orbit--449 x 447 km (279 x 278 sm), period 94 minutes, and inci ination 19.6". (S) PHYSICS AND ASTRONOMY (continued)

INTERNATIONAL SUN-EARTH EXPLORER ( ISEE)

Missi on Launch Launch NASA Site/ Name DateITime Vehicle -Code -Pad Remarks/Resul ts ISEE 1/ 22 Oct 77 Del ta ISEE-A & -9 ETR ISEE 1 and 2 were the first two International Sun- ISEE 2 0953 EDT 2914 179 Earth Explorers in a three spacecraft series. The (Del ta-135) ISEE sate11 i tes were a joint project of NASA and the European Space Agency and contributed to the four-year International Magnetospheric Study (1976-1979). ISEE 1 and 2 were launched simultaneously with ISEC 2 "riding piggyback" atop ISEE 1. Once in orbit , ISEE 2 moved a known distance from ISEE 1, so that scientists could determine changes occurring in the near-Earth space environment. The two ISEEs carried several identical instrunents, which returned data on the Earth's magnetosphere, its boundaries , and the movements of radiation trapped within it. However, ISEE 1's sol id state telescope projected a reflection, and its data was questionable. Both still in orbit; transmitting on comnand only. ISEE 1's orbit measures 154,998 x 3,261 km (83,884 x 2,026 sm); ISEE 2's is 134,997 x 3,261 km (83,883 x 2,026 sm). The two spacecraft have identical periods--3,442 minutes--and incl inati0n--51.9~. (S)

12 Aug 78 Delta ISEE-C ETR ISEE 3 was the third of the three International 1112 EDT 29 14 17B Sun-Earth Expl orers. It was successfully 1aunched (Del ta-144) and placed at Libration Point 1 (Ll), the point in space between the Earth and the Sun where their gravitational forces are exactly counterbalanced. Placed exactly at L1, on the Sun-Earth line, the Sun' s radiation ~ouldinterfere with comnunications. ISEE was placed in a "halo orbit" around L1 to prevent this. In heliocentric orbit. (S) PHYSICS AND ASTRONOMY (cont inued)

INTERNATIONAL ULTRAVIOLET EXPLORER (IUE)

Mission Launch Launch NASA Site/ Name DatelTime Vehicle -Code -Pad IUE 26 Jan 78 Delta IUE E TR IUE (the International Ultraviolet Explorer) was a 1236 EST 2914 17A cooperative undertaking by NASA, the British (Delta- 138) Science Cdunci 1, and the European Space Agency. This orbiting observatory furnished astronomers with spectrograms in the ultraviolet wavelengths, which cannot penetrate the Earth' s atmosphere and reach ground- based observat cries. IUE discovered a corona of hot gas surrounding our Milb Uqy galaxy. Before launch the spacecraft weighed 671 kg (1,480 lb); over 227 kg (500 lb) of that weight was the apogee motor and its sol id propellant. Orbiting at 45,756 x 25,820 km (28,431 x 16,044 sm) , incl ination 28.2', and period 1,436 minutes. Transmitting on comnand only. (S) PHYSICS AND ASTRONOMY (continued)

ORB ITI NG SOLAR OBSERVATORY (OSO )

Missi on Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Resul ts OSO 1 7 Mar 62 Delta OSO-A ETR Measured sol ar f 1ares and subf 1ares ; transmitted 1106 EST DM-19 (S-16) 17A data on Sun's radiation in ultraviolet, X-ray, and i (Del ta-8) gamna ray regions, plus other solar phenomena. Prior to 199.58-kg (440-lb) OSO 1, less than an i hour of solar 2henmena data had been collected from above :he Earth's atmosphere. Sti11 in orbit--6;L x 471 km (306 x 293 sm), inclination I 32.g0 and period 94 minutes. (S) 1 OSO 2 3 Feb 65 Del ta OSO-0-2 ETR Sol ar physics; 247.2- kg (545-1 b) spacecraft for i 1136 EST DSV - 3C (S-17) 178 continuation of OSO 1 studies with added ability (Del ta-29) to scan the solar disc and part of the corona. Sti11 in orbit--572 x 516 km (355 x 321 sm), inclination 32.g0, and period 96 minutes. (S) OSO 25 Aug 65 Delta OSO- C ETR Solar physics; spacecraft was similar- to OSO 1 and 1017 EST D SV- 3C 17B OSO 2. Failed to orbit due to premature ignition (Del ta-33) of the third stage. (U)

OSO 3 8 Mar 67 Del ta OSO-E- 1 ETR Identical to the unsuccessful OSO-C. The 284.4-kg 1112 EST DSV-3C 17A (627-1 b) spacecraft carried nine separate experi- (Del ta-46) ments to provide data on solar disturbances and radiation in space. In Earth orbit--485 x 471 km (302 x 293 sm), incl ination 32.g0, and period 94 minutes. (S)

OSO 4 18 Oct 67 Del ta OSO-D E TR Solar physics. Launched into extremely good cir- 1158 EST DSV- 3C 178 cular orbit. A1 1 systems on 274.42-kg (605-1 b) (Del ta-53) spacecraft operated normal ly. Experiments conducted by Harvard Col lege Observatory; herican Science and Engineering Inc.; University College, London; Naval Research Laboratory; and Lawrence Radiation Laboratory. Still in orbit--497 x 478 km (309 x 297 sm) , incl ination 33O, and period 95 minutes. PHYSICS AND ASTRONOMY (cont inued)

Mi ssion Launch Launch NASA Site/ Name Date/Ti me Vehicle -Code -Pad Remarks/Resul ts OSO 5 22 Jan 69 Del ta OSO- F ETR Launched into an orbit with an apogee of 586.21 1148 EST DSV- 3C 178 and a perigee of 543.59 km (353.07 x 337.77 sm). (Del ta-64) The 290.75-kg (641-1 b) spacecraft contained 120.2 kg (265 1b) of scientific instruments to stu@ solar radiation in the X-ray, ganma ray, and ultraviolet regions of the solar spectrun. The first experiment was turned on during the 11th orbit and the eighth and last was activated during orbit 102 on 29 January. All instruments and spacecraft systems functioned normally. Launch vehicle was last of 30 Del ta vehicles of this con- f iguration, all of which performed successfully. Sti11 orbiting at 515 x 496 km (320 x 308 sm), incl ination 33', and period 95 minutes. (S)

OSO 6 9 Aug 69 Oel ta OSO-G ETR The 293.47-kg (647-1 b) spacecraft was successful ly 0352 EDT DSV- 3N 17A injected into a 488 x 444 km (303 x 276 sm) orbit, (Delta- 72) at an inclination of 33'. OSO-G was first in the OSO series to contain an offset pointing and offset rastering capabil ity, enabl ing investi- gators to make detailed studies of ultraviolet and X-ray spectra at any point on the solar disk and within a few arc mixtes above the limb. The two-stage launch vehicle a1 so carried a Package Attitude Control (PAC) spacecraft, rigidly attached to the second stage, into a 563.6 x 498.9 km (344 x 310 sm) orbit. PAC experiment f 1i ght tested a long-1 ife, low-power , 3-axis, Earth-sta- bi1 i zed control system designed to convert the Delta second stage into a stabilized platform for a wide variety of piggy-back payloads. Still in orbit--448 x 417 km (278 x 259 sm), incl ination 33O, and period 93 minutes. (S) PHYSICS AND ASTRONOMY (continued)

Missi on Launch Launch NASA Sit e/ Name Date/Time Vehdcle -Code -Pad R&s/Resul ts OSO 7 29 Sep 71 Delta OSO-H ETR Launch vehicle also carried MSFN training satel- 0545 EDT DSV-3L 17A 1i te TETR-D as a secondary pay1oad. Count dorm and (Del ta-85) liftoff were normal, but a launch vehicle anomaly during coast phase between first and second burns of second stage affected second burn performance, causing the 637-kg (1,404-1 b) observatory to be injected into an elliptical, rather than the planned circular orbit, and at a pitch angle outside normal Sun acquisition limits. Ground controllers were able to stabilize the spacecraft and adjust its pitch angle to permit it to lock-on to the Sun. By 29 Nov OSO 7 completed over 850 orbits of the Earth, returning high resolution data from the solar corona in the extreme ultraviolet and visible regions, and the mission was deemed successful. OSQ 7 re-entered 9 July 1974. TETR-0 re-entered 21 September 1978. (S)

OSO 8 21 Jun 75 Del ta OSO-I ETR Thi s 1,052-kg (2,319-1 b) spacecraft was the eighth 0743 ED1 DSV-3P-11D 178 and last spacecraft in the OSO series. Like its (Del ta-112) predecessors, it studied sol ar radiation that does rut penetrate to the Earth' s surf ace and prsv ided long-ten observation of the Sun. OSO 8 was an improved and en1 arged version of the 01 der ones. It carried eight experiments in a circular low-Earth ortit. Orbital parameters are 530 x 519 km (329 x 322 sm) , incli nation 33O, and period 95 minutes. (S) PHYSICS AND ASTRONOMY (continued) ORBITING GEOPHYSICAL OBSERVATORY (0601

Missi on Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Resul ts OGO 1 4 Sep 64 Atlas- OGO-A ETR First Orbiting Geophysical Observatory, designed 2023 EST Agena 12 to conduct nunerous space experiments simulta- SLV-3 neously. The 486.7-kg (1,073-lb) 060-A carried 20 (At 1as- tests. Failure to lock into place resulted in Agena- 10) sol ar panel s generating insufficient power to complete a1 1 experiments. Consi &red successful since 75% of planned data acqui sf tion was obtained. Stil; in orbit; orbital elements not maintained. (S)

OGO 2 14 Oct 65 Thor- Agena 060-C WTR Launched into a low-altitude, nearly polar orbit 0911 EST (Thrust- SLC- 2E to a1 low observation of near-Earth phenomena. (0611 PST) Augmented) 521.63-kg (1,150-1 b) spacecraft planned for at- (Thor- spheric and Earth magnetic survey; 19 of 20 Agena-4) experiments worked but horizon scanners bifted, causing depletion of stabi 1i zation gas supply, which caused loss of electrical power. Ceased transmitting on 24 October 1965. Still in orbit --916 x 380 km (569 x 236 sm), incl ination 87.3O, and period 98 minutes. (P)

OGO 3 6 Jun 66 At1 as-Agena 060-B ETR Interdiscipl inary studies. Earth-Sun space inter- 2148 EST SLV-3 12 re1ationshi ps using a highly el1 iptical orbit to (At 1as- correlate studies of particles and f ields, atmo- Agena-16) spheric physics, solar, and other emissions. Development and operation OF a standardized, observatory type oriented spacecraft. Demonstrated capabi! ity of a three-axis stabil ired observatory. 514.82-kg (1,135-1 b) spacecraft sti11 in orbit--105,798 x 16,529 km (65,740 x 10,271 sm), incl ination 76.3", and period 2,911 minutes. (S) PHYSICS AND ASTRONOMY (continued)

Mission Launch Launch iiASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Hesul ts OGO 4 28 Jul 67 Thor-Agena OGO-D WTR 562.45-kg (1,240-1 b) satel 1 ite put into nearly 0921 EST (Thrust- SLC- 2E polar orbit. Mission to study the effects of (0621 PDT) Augmented) solar activity on the Earth's environment during a (Thor- period of increased sol ar activity. Re-entered Agena-8) atmosphere 16 August 1972. (S)

OGO 5 4 Mar 68 At1 as-Agena OGO-E ETR Fifth of six approved inissions in the OGO program. 0806 EST SLV-3A 13 Successfully launched into a parking orbit. After (At1as- a 32-minute coast period, Agena stage was re- Agena-26) started, injecting the €10.98-kg (1,347-1 b) spacecraft into a highly ell iptical equatorial orbit. This orbit permits the spacecraft to pass in and out of Earth's magnetosphere, sweeping the forward leading quadrant and the geomagnetic tail, as it acquires data on magnetic fields , energetic particles, and plasma. Last NASA launch from Launch Complex 13, Cape Canaveral. Still in orbit-- 120,027 x 27,008 km (74,581 x 16,782 sm), inclination 54", period 3,746 minutes. (S) OGO 6 5 Jun 69 Thor- Agena OGO-F WTR The 632.3-kg (1,394-lb) OGO 6 spacecraft, last in 1042 ED1 (Thrust- SLC- 2E the currently programed OGO series, carried 25 (0742 PDT) Augmented) experiments for detailed studies during solar maxi- ( Thor- mum activity in the near-Earth envirorment. All Agena-11 ) spacecraft subsystems functioned and experiment performance was satisfactory. OGO spacecraft have carried 130 axperirnents into orbit and results obtained from over 1.2 mi11 ion hours of experiment operation to date have been disseminated in Inore than 300 reports and papers. Still in orb't--448 x 417 km (278 x 259 sm), inclination 33", and period 93 minutes. (S) PHYSICS AND ASTRONOMY (continued)

ORB ITI ffi ASTRONOMICAL OBSERVATORY (OAO 1 Mission Launch Launch NASA Sitel Name Date/Time Vehicle -Code -Pad RemarksIResults OAO 1 8 Apr 66 At1 as-Agena OAO-A1 ETH Orbiting Astronomical Observatory. Capable of 1435 EST SLV-3 12 accurate, 1ong-duration pointing for ultraviolet, (At 1 as- X-ray, and gamna ray observations and mapping any- Agena-15) where in the celestial sphere. 1,769-kg (3,900-1 b) spacecraft stopped operating after two days due to battery failure ending comnunications. However, it is still in orbit. (U)

OAO 2 7 Dec 68 At1 as/ OAO-A2 ETR The launch vehicle successfully injected the 0340 EST Centaur 36B 1,995.8-kg (4,400-1 b) spacecraft into a near-ci r- (AC-16 ) cul ar orbit. A total of 11 telescopes were carried on the spacecraft, divided among two experiment packages provided by the Uni versity of Wisconsin and the Smithsonian Astrophysical Observatory. The objective was to make precision observations from above the Earth's atmosphere in the re1ati vely unexplored ultraviolet region of the spectrum. Both experiment pack ages performed successfully. Still in orbit--775 x 765 km (482 x 475 sm), incl ination 3S0, 100-minute period. (S)

30 Nov 70 At1 as/ OAO-B ETR Countdown and 1iftoff were normal, with a minor 1740 EST Centaur 36B 10-minute hold to check spacecraft GSE. However, (AC-21) a1 though the At1 as and Centaur propul sion systems functioned properly, the launch vehicle failed to achieve sufficient velocity to inject the 2,132-kg (4,700-lb) spacecraft into orbit. Telemetry indicated that, although the sequence was initiated on time, the spacecraft shroud panels failed to separate properly. (U) PHYSICS AND ASTRONOMY (continued)

Missi on Launch Launch NASA Site! Name Date/Time Vehicle -Code -Pad Remarks/Resul t s OAO 3 21 Aug 72 Atlas/ OAO- C ETR Terminal countdown proceeded to 1if toff with no (Coperni cus) 0628 EDT Centaur 368 unscheduled holds. Launch vehicle injected the (AC-22) 2,200-kg (4,900-1 b) observatory into a near-per- f ect circular orbit: 745 x 740 km (463 x 460 sm); 35" incl ination; 100-minute period. Fol lowing spacecraft checkout, experiment operation began on 29 Aug. By 12 Jan 1973 Copernicus had completed over 2,000 orbits of the Earth with all systems operating satisfactorily, and both primary and secondary mission objectives had been accom pli shed. Observatory operation was continued. Current orbital parameters are: 742 x 731 km (461 , x 454 sm) , incl ination 35", and period 100 minutes. (S) PHYSICS AND ASTRONOMY (continued)

HIGH ENERGY ASTRONWY OBSERVATORY (HEAOL

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Resul ts HEAO 1 12 Aug 77 At1 as HEAO-A E TR This was the first of three spacecraft launched to 0239 EDT Centaur 368 detect high energy radiation-- X-rays, gamna rays, (AC-45) and cosmic rays. HEAO 1 mapped X-ray sources in the skies; it found more than 1,200. HEAO 1 a1 so located a new black hole candidate. The spacecraft weighed 2,566 kg (5,665 lb) and completed a 17-month mission. Orbit decayt ' 15 March 1979. (S) HEAO 2 13 Nov 78 Atlas/ HEAO-B ETR HEAO 2, nicknamed "Einstein," was designed to (Einstein) 0024 EST Centaur 36B focus on precise points of high energy radiation, (AC-52) rather than to scan the sky as did its predecessor, MA0 1. HEAO 2 weighed 3,145 kg (6,936 Ib) before launch and carried the largest X-ray telescope ever bui 1t. The telescope achieved the first photograph of an X-ray burster. Sti 11 in orbit--514 x 496 km (319 x 308 sm), incl ination 23.5O, period 95 minutes. (S)

HEAO 3 20 Sep 79 At1 as/ HE AO- C ETR Third in the series of three orbiting observa- 0128 EDT Centaur 36B tories, HEAO 3 was launched into the planned (AC-53) orbit: 507.4 x 494.8 km (315.3 x 307.5 sm), inclination 43.6", period 94 minutes. The spacecraft had a weight at liftoff of 2,915 kg (6,412 1 b) . HEAO 3 perforrned an a1 1-sky survey of cosmic rays and gamna rays, in a manner simi 1 ar to the X-ray survey performed by HEAO 1, except HEAO 3 operated at a higher orbital inclination. The higher incl ination of HEAO 3 took advantage of the greater cosmic ray flux near the Earth's magnetic poles. Still in orbit: 492 x 477 km (306 x 296 sm) , 43.6" incl ination, 94-minute period. (S) PHYSICS AND ASTRONOMY (continued)

SPACECRAFT CHARGING AT HIGH ALTITUDES (SCATHAL

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Resul ts SCATHA 36 Jan 79 Delta SCATA ETR SCATHA (Spacecraft Charging at High A1 titudes) was 1642 EST 29 14 17B the first spacecraft devoted primarily to studying (Del ta-148) the tendency of the near-Earth environment to cre- ate a build-up of static charges on sate1 lites at geosynchronous orbit a1 t itudes. This accumulation can cause electrical arcing and can damage the spacecraft or some of its components. SCATHA's apogee motor fired on 2 Feb and put the spacecraft into its planned near-geosynchronous drift orbit. SCATHA was a joint project of NASA and the U. S. Air Force; it was operated in orbit by the Air Force. Still orbiting in a path 43,549 x 27,245 km (27,060 x 16,929 sm), with a 7.6' inclination and a 1,416-minute period. (S) SPACE SCIENCE INTERNATIONAL SPACE SCIENCE -AR IEL Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Resul ts Ariel 1 26 Apr 62 Delta S-51 ETR First international satellite, joint U. So-U. K. 1300 EST DM-19 (UK-1) 17A venture. The 59.87-kg (132-lb) spacecraft per- (Del ta-9) formed ionospheric and solar radiation studies. L Transmitted unti1 Novenber 1964; decayed 24 May ! 1976. (S) INTERNATIONAL SPACE SCIENCE (continued) ALOUETTE

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Resul ts Alouette 1 30 Sep 62 Thor-Agena S-27 WTR First NASA launch from WTR, first use by NASA of 0200 EST Thor-Agena B SLC-2E the Thor-Agena. Canadi an-bui 1t 145-kg (320-1 b) (29 Sep 62) (Thor- sate1 1ite, put into polar orbit. Investigated (2300 PST) (Agena-1) upper levels of ionosphere and aspects of space noise, and measured electron Gensi ty. Experiments revealed that effective radio frequency reflecting surfaces in the polar regions were very rough, and that temperatures 480 km (300 sin) above ;he Earth varied greatly and increased with latitude. Sti11 in orbit--1,028 x 992 km (639 x 616 sm), inclination 80.5", period 105 minutes. (S) Alouette 2 28 Nov 65 Thor- A1 ouette B WTR Dual launch with Explorer 31. Initiated a NASA- 2349 EST Agena-5 DME-A SLC-2E Canadian program called International Sate11 ites (2049 PST) for Ionospheric Studies (ISIS). Sate11 ites were placed in near-dupl icate orbits. Eight experi - ments of Explorer 31 were correlated with five of 146-kg (323-1b) Alouette 2. Extended to polar regions ionospheric soundings begun by Alouette 1. Still in orbit--2,889 x 504 kin (1,795 x 313 sm), inclination 79.8", period 120 minutes. (S) 'I- I In 0 68 C, w I 'a Q) d, t 1I *r CW IC 'C I cn- L 0-r gO c Q gcs .r C, E 8 w-0 8.r~) gx8 2iIroca.. oacrre-.r--- LzEQ)%*U)Ind X.r.r~ULm.rC:c .rC aJpE Xno,".Z 0 0 N Q) bjr 0 01OC, 2"'E WOCC,QQ~ m.r a *r E r. CQ)O &- E .r 30 .rW U) 0 C- m- CV)V u)?) JQ V) L%r 0 vru, o Em- 3...I,3Q",g.2!';;; 3...I,3Q",g.2!';;; rm Q *.r 0Q.r 3 JVL OC,1II ttC,"o osU**.r WCO 8 ~SLLLvaoc C I"U)II~.CLQ):! n 00 PL C'r-rC C OC, tuC, 0- 0 8= 5.z gsE Q)= x kz'+w E m'3.r-r Em rgsC)zw$ Q)LQenQ L C,o -'"!!CU .r Q)CU C encco 3 L 0 C, .r Or aQ)CV)Q C 000 E Qh.r=m*S 5-0.a C CLnCc,QW 0)- 0- *; 0 C C 0- PLZ Q) Q Q 4 I IQ)- V I ooroc, norr Q E L aC,\U)U)NC,C,C" 0 agV)y)Gb&E~.r - E~-Qwc .-or- * E.r Ul @ € 2 ==3 %*II a L U) 0 I aJcgmn a Q) 0.c ,A 42.4 Qf-8QLOhV) C a am C Q) 0 *- *- .r Eu.~FLLU)CL Q) QLU 9. m *LX ,ta mE N;pgw(;r aarmco -la cow Q) U) .r\LQ)f-Q)U IQO =u m u=Q)-fw .r *r 3u*C, XWL~EWQ)L Car EN w U) Q) Q) Q) Q) L L-3 I C, ON I muQ) La Us- C Jm-w J U) LCWt'P a t C,r 3 0 can 0 0.v-v- Q) 0 E'r * =*%s Q) noL PL.r 4mfX'B E U) cnf-LLPY E REgdccrcn cn= nmocc INTERNATIONAL SPACE SCIENCE (continued)

EUROPEAN SPACE AGENCY (ESA)

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Resul ts HEOS 1 5 Dec 68 Delta HEOS-A ETR NASA 1aunch; non-NASA mission. HEOS (Hi ghly 1355 EST DSV-3E 17B Eccentric Orbit Satellits), the first satellite (Del ta-61) produced by the European Space Technology Center for the European Space Research Organi rati on (ESRO), carried eight experiments to obtain information on magnetic fields, cosmic radiation, and solar winds from an area beyond the magnetosphere and the shock wave of the Earth. The 107.5-kg (237-1 b) , 16-si ded spacecraft was succes~ful1y injected imto an elliptical orbit: 222,264 x 422 km (138,108 x 262 sm); inclination 28"; 4-day, 15-hour, 40-minute period. Fol lowing verification of orbit, spacecraft control was turned over to the ESRO Operations Center. Re-entered 28 Oct 1975. (S)

HEOS 2 31 Jan 72 Delta HEOS-A2 WTR HEOS 2 was the second Highly Eccentric Orbit 1 1220 EST DSV-3L SLC-2E Satellite launched by NASA for the European Space (0920 PST) (Del ta-87) Agency. Its mission was to investigate the high- I latitude magnetosphere and search for neutral 1 points at the boundary of the magnetosphere.

1 Duri ng prelaunch preparations, the second stage i was shipped back to its manufacturer for a modifi- cation, and the third stage motor to its manufacturer for an X-ray. HEOS 2 was successfully ;': ced into the planned orbit. Initial orbital ,:meters were: 240,160 x 406 km (149,233 x 252 S:til, inclination 89.g0, and period 5 days, 4 hours, 34 minutes. Re-entered 2 Aug 1974. (S) INTERNATIONAL SPACE SCIENCE (continued)

Mission Launch Launch NASA Site/ .- Name Date/Time Vehicle -Code -Pad Remarks/Resul ts 11 Mar 72 Delta TD-1/A WTR Launch vehicle was two-stage Delta wfth three 2055 EST DSV-3N SLC-2E strap-on sol id-propel 1ant motors on first stage; (1755 PST) (Del ta-88) second stage had restart capabi 1i ty. Total thrust at 1iftoff (including sol ids) was 1,460,000 newtons (328,500 lb). First launch attempt on 9 Mar was scrubbed due to problems in second stage ve- 1oci ty control system. Second terminal countdown proceeded normally to 1i ftoff. 472-kg (1,038-lb) spacecraft was successfully injected into near- circular orbit of 542 x 523 km (337 x 325 sm); 98O inclination; %-minute period. Largest and most advanced European spacecraft, TO 1 was built by consortium of five firms headed by Matra of France; carried seven experiments provided by six European uni versities and scientific organiza- tions. Launched by NASA for ESRO on a reimbursable basis. Sti11 in orbit--265 x 257 km (165 x 160 sm) , 97.4O inclination, 90-minute period. (S) Cosmic 1 8 Aug 75 Del ta COS-B WTR Developed and owned by the European Space Agency, 2148 EDT DSV-3P- 1A SLC-2W COS-B studies gamna radiation in the 25 MV to one (1848 PDT) (Del ta-113) GV range. Launch was delayed two days by failure of a hydraulic valve in an ARIA aircraft assigned to provide teleriry coverage. COS-B was successfully launched into orbit at 99,834 x 343 km (62,067 x 213 sm) with a 90.1° inclination. The spacecraft weighed 278 kg (612 lb). Sti11 in orbit--89,407 x 9,985 km (55,555 x 6,115 sm), inclination 96.5OS 2,203ninute period. (S) INTERNATIONAL SPACE SCIENCE (continuedJ

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad RemarksfResul ts Geos 20 Apr 77 Delta ESRO/Geos ETR Geos was designed to study the propagation path of 0515 EST 2914 178 high-energy particles from the Sun and to give an (Del ta-130) estimate of the number bombarding the atmosphere. Geos was the first geosynchronous scientific satel 1ite owned and developed by the European Space Agency; it was also the first purely scien- t ific spacecraft scheduled for geosynchronous orbit. However, Geos never reached proper orbit. Its spin table failed to spin up the 3rd stage/ spacecraft combination; consequently, the 3rd stage fired in an improper orientation without effective spin stabi 1ization. The satell ite's apogee kick motor was successful ly fired 27 Apr 77 to put Geos in the most desirable orbit that was achievable--70,365 x 1,215 km (43,723 x 755 sm), with an inclination of 26O. Geos operated properly but could only fulfill a portion of its scientific objectives. (P)

Geos 2 14 Jul 78 Delta ETR Geos 2 was the replacement for the original Geos, 0643 EDT 2914 17A which did not achieve the proper crbit. Built as (Del ta-143) a qua1 ification model, it was identical to Geos 1 atd was upgraded to flight status. Geos 2 weighed 574 kg (1,265 lb) prior to launch and 268 kg (591 lb) after burning its apogee motor propellant. It went into the correct orbit, and is now at 35,793 x 35,775 km (22,241 x 22,230 sm), inclination O.ZO, period 1,432 minutes. (S) INTERNATIONAL SPACE SCIENCE (continued)

HELIOS Mission Launch Launch NASA Site/ Name Date/Tirne Vehicle -Code -Pad Remarks/Resul ts Helios 1 10 Dec 74 Titan/ He1 ios-A ETR This was the first of two launches in a joint 0211 EST Centaur 41 project of the United States and West Germany, in (Titan III- which the United States supplied two launch vehi- Centaur 2) cles and West Germany two spacecraft. Helios was initially controlled after liftoff by the United States, then turned over to a West German team in Oberpfaffenhofen, West Germany. He1 ios 1 approached to within 47 mil1 ion km (29 mil1 ion sm) of the solar surface and penetrated the outer fringes of the solar corona. The spacecraft reached perihelion on 5 March 1975, where it experienced approximately 11 times more heat than that at the Earth's orbit. Its heat dissipation system worked we1 1 , and the spacecraft survived to return a wealth of new data on the Sun, the solar wind, the outer solar corona, and the Sun's magnetic and electric fields. In heliocentric orbit. (S)

Helios 2 15 Jan 76 Titan/ He1 i0s-B ETR Launched into a he1 iocentric orbit toward the Sun, 0034 EST Centaur 41 the spacecraft achieved man's closest approach to (Titan III- the Sun on 2 Apri 1 1976. A cooperative project by Centaur 5) the United States and West Germany, the spacecraft provided data on solar plasma, solar wind, cosmic rays and cosmic dust, and performed magnetic and electrical field experiments. In he1 iocentric orbit. (S) rm CW WCU BIOSCIENCE (continued) I BIOSATELLITE (BIOLOGICAL SATELLITES) Mission Launch Launch NASA Site/ Name DateITime Vehicle -Code -Pad Remarks/Resul ts / Biosatell ite 14 Dec 66 Del ta BIOS-A ETR Objective of satell ite was to test the effect of 1 1420 EST DSV-3G 17A weightlessness and space radiation on growth of (Del ta-43) plants and animals. The 425-kg (937-1b) space craft contained millions of animal and plant cells. The retrorocket failed to fire when triggered on the 48th orbit, and no useful data was acqui red. Sate11 i te and capsule re-entered 15 February 1967, landing near Australia. A search was performed but they could not be located. (P)

F i Biosatellite 7 Sep 67 Delta BIOS-B ETR Objecti ves were similar to those of BIOS-A. The I 2 1804 EDT DSV-3G 17B 433-1 b (955-1 b) sate11 its worked we1 1, except for : (Del ta-51) a slight difficulty in accepting ground comnands. I Because of concern with the comnand reception and weather in the recovery area, it was decided to de-orbit on orbit 30, rather than continue the 3-day mission. A1 1 de-orbit events occurred normally, and capsule was recovered by aircraft over the Pacific within 24 km (15 sm) of predicted impact point on 9 September 1967. Remainder of sate1 1i te re-entered atmosphere on 4 October 1967. (S) BIOSCIENCE Vd)

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Resul ts Biosatellite 28 Jun 69 Del t a BIOS-D ETR lhird spacecraft desi gned for bi01 ogical expri- 3 2316 EDT DSV-3N 17A mentation in space and subsequent recovery of spe- (Del ta-70) cimens. The 677-kg (1,493-lb), 2.4-meter (8-foot) long spacecraft consisted of a re-entry section containing an instrumented 6.8-kg (15-lb) pigtail monkey and an adapter section containing most spacecraft systems. The spacecraft was launched into a 394 x 360 km (245 x 224 sc) orbit with an inclination of about 34'. Although planned for 30 days, the mission was terminated on 7 July when the primate developed an irregular heartbeat and lowered metabolic state. The capsule was recovered but the primate died 12 hours afterward. Re- mai nder of the spacecraft re-entered 20 January 1970. (P) SPACE SCIENCE LUNAR AND PLANETARY

PIONEER (LUNAR)

Mission Launch Launch NASA Site/ Name DateITime Vehicle -Code - Pad Remarks/Resul ts Pioneer 1 11 Oct 58 Thor- -- ETR Lunar probe. Uneven separation of second and 0342 EST Abl e-1 17A third stages; reached altitude of 113,808 km (70,717 sm). Verified Van Allen Belt and returned other useful data before payload re-entered after 43 hours. (U)

Pioneer 2 8 Nov 58 Thor- ETR Lunar probe. Third stage failed to ignite; 0230 EST Abl e-2 17A reached 1,550 km (963 im). Brief data indicated that Earth's equatorial region has higher flux and energy level s than previously be1 ieved. Suggested micrometeoroid density higher near Earth than in space. (U)

Pioneer 3 6 Dec 58 Juno 11 ETR Lunar probe. Premature cutoff of first stage, 0045 EST (AM-1 1) 5 failed to produce required velocity for lunar probe. Reached a1 titude of 102,322 km (63,580 sm) to contribute major scientific discovery of dual bands of radiation around the Earth. Re-entered after 38 hours, 6 minutes. (U) Pioneer 4 3 Mar 59 Juno I1 ETR Lunar probe. Instrumented for space radiation 0011 EST [AM-14) 5 measurements on Earth-Moon trajectory; carried photoelectric scanner for use in vicinity of Moon. Trajectory caused it to pass within 59,545 km (37,000 sm) of Moon; not close enough for scanner to function. Yielded excellent data on radiation in space. Was tracked for 82 hours to a distance of 655,000 km (407,000 sm) (greatest tracking distance for human-made object to date) before going into permanent he1 iocentric (solar) orbit. 6) LUNAR AND PLANETARY (continued)

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Resul ts Pioneer 26 Nov 59 At1 as- -- ETR Lunar probe. Payload shroud broke away 45 seconds 0226 EST Abl e-1 14 after 1 iftoff; satellite tom off. (U)

Pioneer 25 Sep 60 At1 as- P- 30 ETR Lunar orbit attempt ; failed to achieve trajectory 1013 EST Abl e-2 12 due to second stage ma1 function. (U)

Pioneer 15 Dec 60 At1 as- P-31 ETR Lunar orbit attempt; exploded 70 seconds after 0410 EST Abl e-3 12 1iftoff due to first stage malfunction. (U) LUNAR AND PLANETARY (continued) -P IONEIER (INTERPLANETARY) Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Resul ts P ; s;;c?r 5 11 Mar 60 Thor- P- 2 ETR Highly successful expl orat ion cf interpl anetary 0800 EST Abl e-4 17A space between orbits of Earth and Venus; produced f irst data on nature of interplanetary space; establ ished comnication record of 36.2 mil1 ion km (22.5 million sm) on 26 June 1960, a record un- matched until Mariner 2. First radio comnunication at interplanetary distances. In solar orbit. 6) Pioneer 6 16 Dec 65 Delta Pioneer-A ETR Study of interplanetary phenomena in space. Pro- 0231 EST DSV-3E 17A vided simultaneous scientific masurements at I (Del ta-35) widely separated points in he1 iocentric orbit in interplanetary space to provide data on interplanetary environment for U.S. advanced space program. In he1 iocentric orbit. ($)

Pioneer 7 17 Auy 66 Delta Pioneer-B ETR He1 iocentric orbit, measuring sol ar magnetic 1020 EST DSV -3E 17A field, solar wind, and coslnic rays. Like Pioneer iDel ta-40) 6, continued measurements of solar activity at widely separated points in interplanetary space. Orbit of 403 days. [S) LUNAR AND PLANETARY (continued) , Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Res~its Pioneer 8 13 Dec 67 Delta Pioneer-C ETR Third mission in current Pioneer Program of scien- 0908 EST DSV-3E 178 tific interplanetary exploration on a continuing (Del ta-55) basis. Spacecraft was similar in appearance to Pioneers 6 and 7 but contained different experiments. Launch vehicle also carried TTS-1 as a piggyback payload. Intended to collect data including magnetic field, plasma, and cosmic ray measurements in a he1 iocentric (Sun-centered) orbit for a period covering two or more passages of solar activity centers. Also aided in providing a synoptic study of sol ar-interplanetary relations by (a) long-term observations using the Pioneer series, and (b) correlat ive measurements between these spacecraft. Was launched in a path ahead of Earth to give spacecraft added velocity in solar orbit to move out beyond the orbit of Earth. All experiments working properly following orbital inject ion. Reached Earth's magnetospheric boundary at approximately 14CO EST, 15 December 1967. On 18 January 1968 Sun, Earth and spacecraft were a1 igned, with spacecraft about 3.2 mil1 ion km (two mi11 ion sm) from Earth, thus providing opportunity for further investigation of Earth's magnetic tail (first performed by Pioneer 7 in September 1966). In he1 iocentric orbit. (S) LUNAR AND PLANETARY (continued)

I Mission Launch Launch NASA Site/ N am DateITime Vehicle -Code -Pad Remarks/Results Pioneer 9 8 Nov 68 Delta Pioneer-D ETR Pioneer 9 was injected into a solar orbit with an 0446 EST DSV-3E 17B aphelion of 148,207,998 km (92,091,837 sm) and a (Del ta-60) perihelion of 112,752,970 km (70,061,186 sm), and a 297.5-day period. The 66.7-kg (147-1 b) , cyl indrical , spi n-stabi 1i zed spacecraft carried seven scientific experiments, provided by universities, industry and NASA, to obtain data on the proper- ties of the solar wind, cosmic rdys, and interplanetary magnetic fields. The launch vehicle also carried a 20-kg (44-lb) secondary payload, a MSFN Test and Training Sate1 1ite (TETR-B), which was injected into Earth orbit. In heliocentric orbit. (S)

Pioneer 27 Aug 59 Del ta Pioneer-E ETR A problem developed in the first stage hydraulics 1759 EDT DSV-3L 17A system during the flight, causing it to fail com- (Del ta-73) pletely. The second stage recovered from the vio- lent maneuvering this failure caused at separation, but at an incorrect attitude. The vehicle was destroyed 484 seconds into the flight. (U) LUNAR AND PLANETARY (continued) '1 I~lission Launch Launch NASA Site/ Name DatefTi me Vehicle -Code -Pad Pioneer 10 2 Mar 72 At1 as/ Pioneer F ETR Pioneer 10's launch vehicle consisted of an Atlas 2049 EST Centaur 36A SLV-3 first stage, a Centaur D second stage, and a TE-14-364-4 new, spin-stabil ized third stage incorporating a (AC-27) TE-M-364-4 sol id propel 1ant motor. For several I weeks after launch, sun1 ight hit Pioneer 11 from the side, causing heating problems. Leaving some Pioneer 10 Firsts experiments cnenergi zed, shielding others with screens, and pointing the spacecraft away from Pioneer 10 was the first spacecraft to fly beyond Earth helped to protect the instruments. On 15 the orbit of Mars; to penetrate and cross the aster- July 1972 Pioneer 10 entered the asteroid belt; in oid belt; to provide "in situ" measurements of Jupi- February 1973 it emerged unscathed after a 435 ter's environment; and to take close-up pictures of mi11 ion-km (270 mi11 ion-sm) passage. It counted Jupiter. It was also the first NASA spacecraft to asteroid penetration and measured the intensity of use all-nuclear electrical power and be capable of the Zodiacal Light in interplanetary space. In operating beyond the influence of the Sun. Pioneer August 1972, Pioneer 10 measured the solar wind, 10 will become the first htlman-made object to leave its data to be correlated with those from earlier this solar system. Pioneers in sol ar orbit near the' Earth's distance from the Sun. On 3 December 1973, Pioneer 10 made its closest approach to within 130,354 km (81,000 sm) of Jupiter's cloud tops--at a sped of 132,000 Interstel1 ar Stel a km (82,000 sm) per hour. During encounter, Pioneer 10 missed only one objective because of I ! Attached to Pioneer 10 is a plaque with a message fa1se comnands tri ggered by Jupiter ' s intense ra- 1 for extraterrestrial intelligences, should the diation. Pioneer 10 discovered plasma in Jupi- 1 spacecraft ever be found by them. The message, deter's magnetic field; and returned images of the planet in red and blue, which were later processed I signed by Drs. Carl Sagan and Frank Drake, pictures t~)humans, male and female, and tells when and into nearly true-color pictures. The 258-kg k where the species lived. The design is etched into (569-1b) Pioneer 10 will cross Pluto's orbit in i 1983 and continue at 40,000 km (25,000 sm) per I a gold anodized aluminun plate, which measures 15.25 L x 22.8 x 0.127 cm (6 x 9 x 0.050 inches). hour into interstellar space. (S)

i LUNAR AND PLANETARY (continued)

Missi on Launch Launch NASA Site/ Name Date/Time Veh icl e -Code -Pad RemarksIResults Pioneer 11 5 Apr 73 At1 as/ Pioneer-G ETR The 259-kg (571-1 b) Pioneer 11 followed Pioneer 10 2111 EST Centaur 36B to rendezvous with Jupiter. Pioneer 11's closest TE-M-364-4 approach occurred on 2 December 1974. It pene- (AC-30) trated deeper into the radiation be1 ts than the preceding spacecraft, to within 42,760 km (26,570 sm) of the cloud tops--3 times closer than Pioneer 10. Although it took a closer path to Jupiter, it writ straight up through the radiation be1 ts and thus reduced exposure time. Its total radiation dose was Pioneer 11 Firsts not as great as Pioneer 10's. Approaching Jupiter, Pioneer 11 repeatedly crossed the bow shock, showing Pioneer 11 was the first spacecraft to fly to Saturn that the Jovian magnetosphere changed its boundaries and take close-up pictures of the pl anet. It a1 so as it was buffeted by the solar wind. Pioneer 11 returned the first pictures of the polar regions of found Jupiter's poles to be covered by a thicker but Jupiter. transparent atmosphere and to have lower cloud tops than the rest of the planet. Pioneer 11 used Jupiter's massive gravitational field to swing back across the solar system to encounter Saturn. Spu- rious commands began interfering with the operations of the asteroid/meteoroid detector, and the instrument had to be turned off in 1975. Closest approach to Saturn occurred on 1 September 1979. Pioneer 11 crossed the ring plane beyond the outer ring, then swung underneath the rings, passing a few thousand kilometers (statute miles) from them. The spacecraft came within 21,400 km (13,300 sm) of Saturn's cloud tops, at a speed of 114,100 kph (71,900 mph) at the point of closest approach. After 1eaving Saturn, Pioneer 11 began a course for interstellar space in a direction nearly opposite from Pioneer 10. Like Pioneer 10, Pioneer 11 also carried a pl aque with a message for extraterrestrial intel 1 igences. (S ) LUNAR AND PLANETARY (continued)

Mission Launch Launch NASA Site/ Name Date/Ti me Vehicle -Code -Pad Remarks/Resul ts Pioneer 20 May 78 At1 as/ Pioneer ETR The Orbiter was the first spacecraft placed in Venus 1 2113 EDT Centaur Venus 36A orbit around Venus. It achieved orbit on 5 Dec (AC-50) Orbiter 1978. The Orbiter supplied data for a radar map of the Venusian surface. Mountains were discovered, some higher than those on Earth. The maps exposed the largest canyon yet discovered in the solar system--a giant rift valley 4,572 meters (15,000 feet) deep, 1,448 km (900 sm) long, and up to 282 km (175 sm) wide. Observations in the infrared revealed a clearing in the planet's cloud layers over the north pole; photos in the ultraviolet showed dark markings, that spanned the visible hemisphere, in the clouds. Cameras also detected almost continuous 1i ghtni ng activity on Venus$ (S)

Pioneer 8 August 78 Atlas/ Pioneer ETR Launched over two months after the Pioneer Venus Venus 2 0333 EDT Centaur Venus 36A Orbiter, the Multiprobe arrived at the planet only (AC-51) Mu1 t iprobe five days later because of its shorter trajectory. The Multiprobe consisted of a bus (or main body) and four probes. On 9 Dec 1978, all five components entered the upper atmosphere independently. Three weeks earlier the probes had been released, to continue traveling separately. Thw fell through the Venusian atmosphere, radioing information on the structure and composition of the atmosphere, incl udi ng temperature and pressure profiles, heat received from sunlight, and cloud structure and motion. The bus entered the atmosphere 1-1/2 hours later than the probes, in order to perform radio tracking on them as they fell. Horizontal motions of the probes, measured by tracking, provided scientific data on the Venusian winds. (S) LUNAR AND PLANETARY (continued)

RANGER

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Ranger 1 23 Aug 61 At1 as- P-32 ETR Lunar probe. Injected into low-Earth orbit rather 0504 EST Agena-1 12 than planned deep-space orbit due to failure of Agena stage to restart. Served as useful engineering test. Returned scant scientific data before re-entry on 30 August 1961. (U) Ranger 2 18 Nov 61 At 1as- P-33 ETR Lunar probe. Placed in low-Earth orbit rather C312 EST Agena-2 12 than programed deep space orbit. Test of spacecraft achieved. Re-entered 30 Nov 1961. (U)

26 Jan 62 At1 as- P-34 ETR United States ' first attempt to rough-1 and separa- 1530 EST Agena-3 12 ble instrunented capsule on 1 unar surface. Space- craft injected into lunar transfer path at excessive velocity due to ma1 function in Atlas guidance equipment. Arrived in area of the Moon approximately 14 hours early, missing it by 36,793 km (22,862 sm). Provided first measurement of interplanetary gamna ray f 1iix. Entered soi ar orbit. (U)

23 Apr 62 At1 as- P-35 ETR First lunar impact for a U.S. payload. Put into 1550 EST Agena-4 12 proper 1 unar impact trajectory by Agena restart, but failure of timer prevented controlled descent onto Moon's surface and precl c4ed accompl ishment of engineering and scientific experiments. No mid-course corrrection. Crashed onto backside of Moon on 26 April 1962. While full flight objectives were not achieved, a high order of performance in the At1 as-Agena/Ranger combination was demonstrated. (P) a LUNAR AND PLANETARY (continued) Mission Launch Launch NASA Site/ I Name DateITime Vehicle -Code -Pad Remarks/Resul t s Ranger 5 18 Oct 62 Atlas- P-36 ETR Spacecraft launched into proper lunar impact tra- 1159 EST Agena-7 12 jectory; after 15 minutes of normal operation, ma1 function caused spacecraft to transfer from solar to battery power-. Normal operation never rcsumed; battery power supply ran down after 8 hours, rendering spacecraft systems and experi - ments useless. Passed within 724 km (450 sm) of Moon and on into solar orbit; was tracked to distance of 1,271,381 km (790,000 sm). (P) Ranger 6 30 Jan 64 At1 as- Ranger-A ETR Successful launch but mission not accompl ished due 1049 EST Agena (P-53) 12 to failure of TV cameras which were to transmit SLV-3 3,000 pictures of the Moon at altitudes ranging (At1 as- from 1,448 to 6.4 km (900 to 4 sm). Ranger im- Agena-8) pacted in the Sea of Tranquility at 0424 EST on 2 February, precisely on schedule. (P) I

Ranger 7 28 Jul 64 At1 as- Ranger-B ETR The 365.6-kg (806-1 b) spacecraft, which carried i 0050 EDT Agena (P-54) 12 six TV cameras, was successfully placed into park- SLV-3 ing orbit, and later injected into lunar trajecto- (At1as- ry by restarting the Agena motor. During the last Agena-9) 15 minutes of flight, the cameras sent back 4,316 I high-qua1 ity photographs of the Moon's surface. The final pictures were transmitted 2.3 seconds I before impact on 31 July 1964. All aspects of the test were successful. (S)

Ranger 8 17 Feb 65 At1 as- Ranger-C ETR Lunar photography. 7,137 pictures obtained ; im- 0005 EST Agena 12 pact occurred about 24 km (15 sm) from target in SLV-3 Sea of Tranqui 1ity on 20 February 1965. (S) (Atlas- Agena-13) ,"A* UQC 0 U) -r Z*LL=P aJ'L 0, 03 OQOW C, V-U* 0 h* .- C E'ECnF OL Q L a *.- QCCWV) U C O U)w L 3 4 QOI A Pad LUNAR AND PLANETARY (cont inued)

SURVEY OR

Mission Launch Launch NASA Site/ Name Date/Time Vehic'l e -Code -Pad Remarks/Resul ts Surveyor 1 30 May 66 At1 as/ Surveyor-A ETR Soft-landed on Moon in the Ocean of Storms 2 June, 0941 EST Centaur 36A proving capabi 1i ty of 1aunch vehicle and space- LV -3C craft. Returned thousands of high-qua1 ity pic- (AC-10) tures. Selenological data obtained in morphology and lunar origin. Completed mission 13 July but spacecraft remained operable for 8 months. (S)

Surveyor 2 20 Sep 66 At1 as/ Surveyor-B ETR Intended to demonstrate soft 1unar 1anding and 0732 EST Centaur 36A provide data for Apollo program. Flight success- LV-3C ful until midcourse maneuver, when one of three ( AC-7 ) vernier engines failed to ignite, causing spin, Data obtained on spacecraft performance until it crdshed on Moon 23 September, (P)

Surveyor 3 17 Apr 67 At1 as/ Surveyor-C ETR Soft-landed on Moon 20 April , within Apol lo land- 0205 EST Centaur 368 ing area. Returned TV pictures and obtained data LV -3C on lunar surface by digging up a sample with a (AC-12) claw. On basis of data, scientists concluded that lunar soil had consistency similar to wet sand, with a bearing strength of 10 psi, f inn enough for Apollo LM landing. Experiments stopped 2 May rrhen 1unar night began. Surveyor 3 was visited by Apollo 12 astronauts on 20 November 1969. Some of - its parts were removed and returned to Earth. (S)

Surveyor 4 14 Jul 67 At1 as/ Surveyor-D ETR Carried a surface claw similar to Surveyor 3, with 0753 EDT Centaur 36A a magnet in the claw to measure ferrous elements LV-3C in lunar soil. Flight was successful until all (AC-11) communications with Surveyor 4 were lost 2 seconds before retrorocket burnout on 17 July 1967, 2-1/2 minutes before landing. Scientists theori ze that Surveyor 4 spacecraft exploded. (P) LUNAR AND PLANETARY (continued)

Mission Launch Launch NASA Site/ Name DatelTime Vehicle -Code -Pad RemarksIResults Surveyor5 8Sep67 At1 as/ Surveyor-E ETR Soft-landed on Moon in Sea of Tranqui 1i ty an 11 0357 EDT Centaur 36B September. Spacecraft landed on inner slope of SLV-3C ma11 crater, about 9 meters (30 feet) in diameter (AC-13) and 1.37 meters (4-112 feet) deep, with the TV camera about 50.8 centimeters (20 inches) above crater's rim. Returned TV pictures of surface, some converted to color. Conducted a vernier engine experiment to investigate erosion from rcxk- et ' s flame. Obtained touchdown dynamics, thermal and radar reflectivity data on lunar surface. Performed a1 pha scattering experiments to determine re1at i ve abundance of elements in 1unar soi 1. Shut down for lunar night on 24 September. Restarted at a later date, but subsequent data was of lower qua1 ity. Loss of signal on 16 December 1967. (S)

Surveyor 6 7 Pdov 67 At1 as/ Su rveyor-F ETR Soft-landed in Sinus Medii near later Apoilo Site I 0239 EST Centaur 368 2 P-8 (3) 9 November after 53-hour, 22-minute I SLV-3C flight from Earth. Transmitted over 30 thousand pictures to Earth during first lunar day of operations. Besides surveying lunar surface, also photographed Earth, Jupiter, and the stars Canopus, Capella, Sirius and Vega. Obtained data on touchdown dynamics, thermal and radar reflectivity of lunar surface, and relative abundance of chemical elements in lunar soil. On 17 November spacecraft ' s three vernier engi nes were restarted and Surveyor 6 was 1ifted about 4 meters (13 feet) off the lunar surface and translated a horizontal distance of about 3 meters (10 feet). Shut dorm for lunar night on 24 November 1967. (S) WNAR AND PLANETARY (continued)

Mission Launch Launch NASA Site/ Name Date/T ime Vehicle -Code -Pad Remarks/Resul ts Surveyor 7 7 Jan 68 At1 as/ Surveyor4 ETR Last spacecraft of Surveyor series. Successfully 0130 EST Centaur 36A launched from Cape Canaveral (within one second of SLV-3C the desired liftoff time) into a direct ascent (AC-15) lunar trajectory, which required only a single midcourse correction maneuver. Soft-1 anded near crater Tycho at 2005 EST. 9 January 1968, after a flight of 66 hours, 34 minutes. Landing site (40.8g0 south latitude, 11.44O west longitude) was about 2.4 km (1.5 sm) from aiming point. Returned over 21,000 television pictures, including some in stereo, of lunar surface and lunar rocks of speci a1 geological interest duri ng first ls:.rar day operations. On two different occasions, Nrveyor camera detected laser beams directed from Earth towards the spacecraft. A1 so, photographed Earth and Jupiter. Returned telemetry data on 1unar surface, similar to Surveyors 1, 3, 5, and 6. Spacecraft was shut down for its first lunar night on 22 January 1968. (S) o I 3 L HO 3 NU 0 u, rth " V) rt-0)- L N Lez 5- *z -ao-*Yo a ulw Rc,k$Sul C't 0 -- o oco8 baJLL .C mc, nnF * g,p -*f- aJC V) ELV) E 4 PLcSaJ 02 YL dL 0 CCUU C ooi 2 3.2 oua3 >A L ow 'tLU V) 0 a E CC," "SZ L V) a 0 CV) ma" 't .r P:g !?!w.-c,2!- &a Fc-.-I=rhS-~ a "C (DE.5 ".r f&; C 40 E'*Ls-J =I-C: ubQ).rC, *E 0 E 4H:: 0)- v bcnO"aJC3 P-00)Q)rt n't-r LooEzo o'to 0 aJ o-0) m~ -V) munuI aJ gV)so3* U aon E& E L EZ 2; C,'thV)J 0 'to OaJQLO'g .-OW3 c, 10 aJ"UU 't'&*z gt: -0 LmCUaO OgpF En0 0 - h In-. t! 5 E zor .Fm~.o uu L 3- 0)*f- Xwau 0)N ,$, 4c,noC,aJ LACao EU V)tU .r.r 4 .)cerc 34 > 3.r't a0Q LL. L-rte- OC, C Q d 9.0 0'4-

L -,-- turn C L 30 LUNAR AND PLANETARY (continued)

Mission Launch Launch NASA Site/ Name DateITime Vehicle -Code -Pad Remarks/Results Lunar 1 Aug 67 At1 as- LO-E ETR Lunar orbit at 100-km (62-sm) perilune. Photo- Orbiter 5 1833 EDT Agena 13 graphed Apol lo target sites, areas of scientific SLV-3 interest, and backside areas not previously (At 1as- covered. Photo readout completed 28 August. Agena-24) Crashed on lunar surface 30 January 1968. (S)

e.. u LUNAR AND PLANETAR" (continued)

MAR INER

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Resul ts Mariner 1 22 Jul 62 At1 as- P-37 ETR Attempted Venus probe, the booster deviated from 0421 EST Agena-5 12 course and was destroyed by the range safety officer 290 seconds after launch. (U) Mariner 2 27 Aug 62 At las- P- 38 ETR First spacecraft to scan another planet; passed 0153 EST Agena-6 12 within 34,762 km (21,600 sm) of planet Venus on 14 Decer.s;;cr an: made a 42-minute instrument scan of Venusian atmosphere and surface before cont inuf ng into heliocentric orbit. Transmissions from interplanetary experiments received unti1 4 January 1963 from 87.4 million km (54.3 million sm) distance, establishing a new comnunications record. (S) Marifler 3 5 Nov 64 At1 as- Mari ner-64C ETR Planetary exploration to the vicinity of Mars. 1422 EST Agena 13 The shroud fai led to jettison; battery power SLV-3 dropped and there was no svidence to indicate that (At 1as- the solar panels opened to replenish the power Agena-l 1) supply; communications were lost. In permanent he1 iocentric orbit. (U)

Mariner 4 28 Nov 64 At1 as- Mariner-64D ETR Planetary and interplanetary exploration. Mars 0922 EST Agena 12 trajectory. Fly-by occurred 14 July 1965 with SLV-3 closest approach between 8,000 and 9,660 km (five (Atlas- and six thousand sm). 22 pictures were taken; Agena-12) first Mars flyby pictures. In heliocentric orbit. During its 3.06 years of useful life Mariner 4 travelled more than 2.4 billion km (1.5 bi11 ion sm) and returned excellent data. (S) LUNAR AND PLANETARY (continued)

Mission Launch Launch NASA Site/ Name DateITime Vehicle -Code -Pad Remarks/Resul ts Mari ner 5 14 Jun 67 At1 as- Mari ner-67E ETR Purpose was to conduct a single fly-by mission to 0201 EDT Agena 12 Venus in 1967 to complement and extend results of SLV-3 Mariner 2. The 245-kg (540-lb) spacecraft passed (At1as- within 4,023 km (2,500 sm) of Venus on 19 October Ag ena-23) 1967. Measured the planet' s magnetic field, ionosphere, and radiation be1 ts and teniperature. In heliocentric orbit. (S)

Mariner 6 24 Feb 69 Atlas/ Mari ner-69F ETR This was the first Mariner launch with the Atlas/ 2029 EST Centaur 36B Centaur vehicle. This spacecraft was one of a SLV- 3C pair (with Mariner 7) launched to perform a Mars ( AC-20) fly-by almost together, and acquire data on the planet. Instrunents included a Visual Imager, U1- travi01 et Spectrometer, Infrared Spectrometer, temperature sensors, and others. The fly-by was successful and, with Mariner 7 fly-by data, obtained the most detailed data on Mars to date. In he1 iocentric orbit. (S)

Mariner 7 27 Mar 69 Atlas/ Mari ner-69G ETR This was the second Mariner launch with the Atlas/ 1722 EST Centaur 36A Centaur vehicle, and formed the second of a pair SL v- 3C of Mariner spacecraft launched to fly by Mars al- (AC-19) most together. The instrunentation was virtually the same as that on Mariner 6 and the spacecraft performed with equal success, flying by Mars at a different angle from its companion and obtaining data at fly-by from other areas of the planet. Both spacecraft entered heliocentric orbits after passing Mars. (S) LUNAR AND PLANETARY (continued)

Mission Launch Launch NASA Site/ Name -.-DateITi me Vehicle -Code -Pad Remarks/Resul ts Mari ner 8 8 May 71 At1 as/ Mari ner-71H ETR Mariner-H was first of two 998-kg (2,200-lb) 2111 EDT Centaur 36A spacecraft intended to explore, during the 1971 (AC-24) opportunity, the physical and dynamic characteristics of the planet Mars from Martian orbit. Countdown of the AC-24 launch vehicle began at the scheduled time and proceeded smoothly to 1iftoff. Powered fl ight was normal unti1 shortly after separation and igni tion of the Centaur second stage, when a malfunction occurred in the Centaur flight control system. Loss of pitch control resulted in an end-over-end tumbling, causing an abnormal shutdown of the Centaur engines. The Centaur stage and the Mariner-H spacecraft re- entered the atmosphere about 1,500 km (932 sm) downrange. (U)

Mariner 9 30 May 71 Atlas/ Mariner-?!: ETR Second of two planned Mariner Mars 71 missions. 1823 EDT Centaur 36B First launch attempt on 29 May was scrubbed *en (AC-23) special flight control system checks indicated an apparent probl em. Second countdown co~mencedon time and proceeded to 1iftoff after a six-minute delay caused by a faulty instrumentation ground 1i ne. Direct ascent powered f 1i ght placed spacecraft into desired he1 iocentric trans-Hars trajectory. On 13 Nov Mariner 9 was inserted into Mar- tian orbit. It arrived during the middle of a planet-wide dust storm, which made surface photography impossible for several weeks. When the storm cleared Mariner-9 went to work, providing an almost complete photographic record of the entire surface of Mars. The high-resolution photographs disclosed features such as the giant mountain Olympus Mohs and the huge Valles Marineris canyon system, as well as enabling cartographers to pre- pare the first detailed maps of Mars. The 90-day rnission was extended until 1831 EDT 27 Oct 72, ending when depletion of spacecraft attitude control gas made it impossible to continue (S). 1-52 LUNAR AND PLANETARY (continued)

Mission Launch Launch NASA Site/ Name DateITime Vehicle -Code -Pad Remarks/Resul ts Mariner 10 3 Nov 73 At1 as/ Mariner-733 ETR Primary objective of this 502.6-kg (1,108-lb) 0045 EST Centaur 366 spacecraft was to explore the atmosphere, surface, ( AC-34) and physical characteristics of the planet Mercury. Secondary objective was to perform a fly-by of Venus. Mariner 10 flew by Venus on 13 Feb 1974 with perapsis at 1301 EDT at a distance of 5,769.5 km (3,585 sm). On 29 March 1974, Mar! ner 10 Firsts Mariner 10 passed within 805 km (500 sm) of Mercury, reveal ing a barren, heavily cratered First launch of any spacecraft to the planet planet which resembl ed Earth's moon. However, un- Mercury. First mission to program one spacecraft 1ike the Moon, Mercury was found to have a small to explore two planets; to use the gravity of one magnetic field and traces of a thin atmosphere. planet to slow a spacecraft and change its flight Mariner 10 went into solar orbit and encountered path to an encounter with a second planet; to Mercury again on 21 Sept 1974, passing by at return to its second target twice after the initial 48,066 km (29,867 sm). Mariner 10's hydrazine encounter; and to use the solar wind as a major control gas ran low, so the spacecraft was maneu- means of spacecraft orientation duri ng f 1i ght . vered using the pressure of the solar wind on its solar arrays and disk-shaped high gain antenna. Third fly-by of Mercury took place 16 March 1975, with an approach to 327 km (203 sm). Control gas exhausted, on 24 March 1975, Mariner 10's trans- mitter was turned off and the mission concluded. In he1 iocentric orbit. (S) LUNAR AND PLANETARY

VIKING

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pa; Remarks/Resul ts Viking 1 20 Aug 75 Ti tan/ Viki ng-A E TR This was the first of the twin Vikiny spacecraft 1722 EDT Centaur 41 to reach Mars. Designed primarily to collect evi- (Titan 111- dence for life--or the lack of it--an Mars, the Centaur-4) spacecraft had two major parts: an Orbiter, which circled the planet, and a Lander, which descended to the surface. Both Vikings were sterilized in 1arge ovens at KSC. A valve failure caused the Viking 1 Weights first launch attempt to be scrubbed. While the appointed spacecraft awaited launch, its batteries Total weight (combined spacecraft): 3,527 kg (7,775 lb) discharged. The second spacecraft was substituted Orbiter: 2,339 kg (5,157 Ib) fully fueled on the vehicle while the first was checked for Lander: 978 kg (2,157 1b) fully fueled damage--a reversal in the planned order of launch. Viking 1 entered Martian orbit on 19 June 1976. Under camera exa~ninat ion of the planned 1andi ng site, the location proved too rough and a new site was chosen. Orbiter 1 proceeded to map water vapor in the atmosphere, build up thermal maps, spot clouds and dust storms, and report seasonal changes. Lander 1 descended to the Martian surface on 20 July, taking air samples as it went. Once down, it surveyed its surrocndings, taking high-qua1 ity photographs in three colors. The sei smometer ma1 functioned, but soil property and weather instruments functioned well. Earth received dai ly weather reports, incl udi ng temperatures and wind direction and speed. The mission's major experiment was a miniature biological 1abo- ratory, which analyzed the Nartian soil. Some data indicated the presence of life, but a major test for organic cornpounds proved negat ive. The puzzle remains unsolved. Lander 1 continues to transmit to Earth once a week. Orbiter 1 is taking high-resolution pictures of the surface of Mars. (S) LUNAR AND PLANETARY (continued)

Mission Launch Launch NASA Site/ Name DateITime Vehicle -Code -Pad RemarksIResul ts Viking 2 9 Sept 75 Ti tan/ Viki ng-B ETR This was the second of the twin Viking spacecraft 1439 EDT Centaur 41 to reach Mars. It was scheduled to be launched (Titan III- first, but due to a battery discharge problem it Cent aur-3) had to be checked for damage and was replaced with the spacecraft slated for the second mission. Each Viking had tw major parts: an Orbiter, which circled the planet, and a Lander, hich de- Viking 2 Weights scended to the surface. On 7 August 1976, Viking 2 entered Martian orbit and joined the Viking 1 Total weight (combined spacecraft) : 3,527 kg (7,775 1b) Orbiter in its search for a landing site for Land- Orbiter: 2,339 kg (5,157 lb) fully fueled er 2. A site was chosen on the edge of the polar Lander: 978 kg (2,157 lb) fully fueled ice-cap, where water was located and a better chance for finding life expected. Lander 2 descended to the surface on 3 Sept. Results of the biology tests performed in the robot laboratory of Lander 2 were similar to those of Lander 1--;:don- clusive on the question of whether life exists or has ever existed on Mars. Martian soil could contain reactants produced by bombardment of the soil by ultraviolet rays--which produce characteristics of Earth soil containing living organisms. (Earth's denser atmosphere absorbs such rays before they reach ground.) Orbiter 2 was shut down 24 July 1978, after it ran out of attitude-control gas. Lander 2 was turned off early in 1980. (S) LUNAR AND PLANETARY Tontinued)

VOYAGER

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Resul ts Voyager 2 20 Aug 77 Tit3n/ Voyager-2 ETR Voyager 2 arrived at Jupiter on 9 July 1979, fol- 1029 EDT Csntaur 41 lowing a different path from Voyager 1 (see (Titan III- following page) that enabled it to photograph the Centaur-7) same fi ve moons as its predecessor from the opposite side, and at other positions in their orbits. Voyager 2 took several new photos of the ring discovered by Voyager 1, acquired new data on the clouds and their circulation patterns in the Jovi an atmosphere, and obtained much riew coverage of the four largest moons and tiny halthea. (Later analysis of photos proved a new moon exists inside the orbit of halthea, one not spotted by telescopes on Earth.) The photos of the four largest moons were largely of areas not covered by Voyager 1. The volcanoes on 10 were still erupting, though one of the largest had stopped. Present theory is that these are primarily sulfur volcanoes, throwing up material from a layer of liquid sulfur under pressure beneath the surface. The vast amount of data accumulated by both Voyagers wi11 require years of analysis by planetary astronomers and other scientists. Voyager 2 is scheduled to arrive at Saturn in August 1981. If Voyager 1 has been successful, Voyassr 2 will be aimed to fly-by Saturn on a path that will take it to Uranus in January 1986, and possi bly Neptune in September 1989. The Voyagers have already become one of the most successful unmanned planetary exploration programs conducted by NASA. (S) LUNAR AND PLANETARY (continued)

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Resul ts Voyager 1 5 Sept 77 Ti tan/ Voyager-1 ETR Voyager 1 was launched 16 days behind Voyager 2, 0856 EDT Centaur 41 but followed a flight path that enabled it to (Ti tan III- arrive at Jupiter first, on 5 March 1979. During Centaur-6) the approach and fly-by Voyager 1 studied the moons Amalthea, 10, Europa, Call isto, and Gany- mede, and Jupiter itself. 10 proved to have live volcanoes erupting, the only known ones outside Earth. Europa has many mysterious long dark streaks crossing its surface, and few craters. Ganymede presents evidence of geologic faulting. Call isto is the most heavily cratered, and apparently has the oldest surface, of any known moon. Europa, Ganymede, and Call isto appear to have crusts that are partially ice, and may be composed of ice over a sol id core. The spacecraft had a single opportunity to photograph the area where some scientists suspected a ring might be fo~!nc!, and it was discovered there. The atmosphere of Jupiter was intensely photographed and studied by a variety of instrments. The Great Red Spct appears to be a semi- permanent anticyclone. Mate- rial moves back and forth between the giant colored bands that ring Jupiter, in incredibly complex circulation patterns. Jupiter a1 so dis- plays northern lights (auro; ') activity, and fre- quent lightning strikes. Voj 3er 1 studied Jupiter' s huge magnetic field, the interaction between this field and the solar wind, planetary heat balance (Jupiter radiates more heat than it receives from the Sun), radio emissions, energetic ions and electrons in the magnetosphere, ultraviolet and infrared emissions, the famous "plasma torus" created by the passage of 10 through the planet's magnetic field, and much more. Overall , Voyager 1 returned far more information than the two earlier Pioneers. It was then sent on its way to Saturn for a November 1980 encounter. (S) EARTH OBSERVATIONS

METEOROLOGY

TELEVISION INFRARED OBSERVATION SATELLITE (TIROSI

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Resul fs TIROS 1 1 Apr 60 Thor- A- 1 ETR First true meteor01 ogical sate1 1 ite, weighing 122 0640 EST Abl e-5 17A kg (270 1b) . Photographed cloud cover and transmitted over 22,000 photographs between 1 April and 17 June 1960. Demonstrated that satellites can be used to survey other surface features from space. Still in orbit--729 x 686 km (453 x 426 sm), inclination 48.4', period 99 minutes. (S)

1 TIROS 2 23 Nov 60 Delta TIROS-B ETR The 122-kg (270-lb) spacecraft combined infrared 0613 EST DM-19 A-2 17A measurements with photography. Wide-angle photos (Del ta-3) were substandard, but useful cloud pictures and radiation data were transmitted. Spacecraft was still transmitting usable pictures a year after launch; still in orbit--700 x 603 km (429 x 375 sm) , incl ination 48.6", period 98 minutes. (S) TIROS 3 12 Jul 61 Del ta TIROS-C E TR The 129- kg (285-1 b) spacecraft was 1aunched during 0525 EST DM-19 A- 3 17A hurricane season; one camera system failed by the (Del t a- 5) end of July, the other was used unti 1 December 1962. Weather Bureau reported TIROS 3 spotted 50 tropical storms during the sumner of 1961. Still in orbit--807 x 735 km (501 x 457 sm), incl ination 47.g0, period 100 minutes. (S)

TIKOS 4 8 Feb 62 Delta TIROS-D ETR All systems on the 129-kg (285-lb) spacecraft pro- f 0744 EST DM-19 A-9 17A vided good data. Clarity of pictures from the new i (Del ta-7) wide-angle lens was outstanding. Photos unclear after 14 June 1962. Still in orbit--834 x 704 km (518 x 437 SIII), inclination 48.3O, and period 100 minutes. (S) Mission Launch Launch NASA Sitej Name Date/Ti me Vehicle -Code -Pad TIROS 5 19 Jun 62 Delta TIROS-E ETR The 129-kg (285-lb) spacecraft entered an orbit 0719 EST DM-19 A- 50 17A more el1 iptical than planned. First to spot five (Del ta-10) of the ten major tropical storms around the world in August. Still in orbit-937 x 591 km (582 x 367 sm) , incl ination 58.1°, period 100 minutes. (S) TIROS 6 18 Sept 62 Delta TIROS-F ETR Launch moved up from November to cover storrn sea- 0353 EST DM-19 A-51 17A son. The 127-kg (281-1 b) spacecraft performed as (Del ta-12) planned. One camera failed 1 December 1962. Still in orbit--695 x 669 kin (432 x 416 sm), inclination 58.3", period 98 minutes. (S) TIROS 7 19 Jun 63 Del ta TIROS-G This 135-kg (297-1 b) TIROS was the first to carry 0450 EST DSV- 3B A-52 an el ectron temperature and densi t.y probe. St i1 1 (Del ta-19) in orbit--616 x 588 km (383 x 365 sm) , incl inat ion 58.2O, period 97 minutes. (S)

1 TIROS 8 21 Dec 63 Del ta TIROS-H Eighth successful TIROS launch; the primary mis- 0430 EST DSV - 3B A- 53 sion of the 120-kg (265-lb) spacecraft was to test (Del t 3-22) a new experimental camera subsystem, cal led Auto- matic Picture Transmission (APT); a1 so carried a TV camera similar to the one carried on previous TIROS sate1 1 ites. Operated satisfactorily for more than 36 months. Still in orbit--735 x 695 km (457 x 432 sm), inclination 58.5", period 99 minutes. (S)

TIROS 9 22 Jan 65 Delta TIHOS- I ETR First 138-kg (305-1 b) TIROS cartwheel conf igura- 0252 EST DSV-3C A- 54 17A tion, for increased coverage of world cloud cover; (Del ta-28) elliptical polar orbit. Still in orbit--2,572 x 702 km (1,598 x 436 sm) incl ination 96.4O, period 119 minutes. (S) aJ 0 eo 10 C ,.c f I V)w UC, V) V) 't I W3i2 LV)OO-* 0) WuQ, 10~33- 0 mdf0.r C- o ~'t0-Q) u o C6X 0 Ewx2

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nw LaoQ, ln 0000(Uo Mission Launch Launch NASA Site/ I;ar,le DateITime Vehicle -Code -Pad ESSA 4 26 Jan 67 Del ta TOS-B WTR The 134-kg (295-1b) spacecraft was launched into a 1231 EST DSV- 3E SLC- 2E retrograde, Sun-synchronous polar orbit. Advanced (0931 PST) (Del ta-45) cartwheel type. Two Automatic Picture Transmis- sion camera systems, one became inoperable on the third day because of shutter problems. Replaced ESSA 2, whose usefulness was limited by orbital drift. Still in orbit at 1,439 x 1,323 km (894 x 822 sm), inclination 102O, period 113 minutes. (S)

ESSA 5 20 Apr 67 Del ta TOS-C W TR The 147-kg (325-1 b) spacecraft was successfully 0621 EST DSV-3E SLC-2E launched into a near-pol ar Sun-synchronous orbit. (032 1 PST) ( Del t a-48) It carried two Advanced Vidicon Camera Systems to provide 24-hour global weather coverage. Turned over to ESSA 8 May. Still in orbit--1,420 x 1,352 km (882 x 840 sm), incl ination 10ZO, period 114 minutes. (S)

ESSA 6 10 Nov 67 Delta TOS-D WTR This 135.6-kg (299-1b) operational cloud mapping 1253 EST DSV- 3E SLC-2E spacecraft was launched into an Earth-oriented, (0953 PST) (Del ta-54) near-polar orbit to provide real-time data for weather analysis and forecasting. Launch vehicle successfully injected spacecraft into desired orbit. A1 1 spacecraft subsystems performed we1 1. Still in orbit--1,483 x 1,406 km (921 x 874 sm), incl ination 102.Z0, period 115 minutes. (S)

ESSA 7 16 Aug 68 Delta TOS-E WTR Seventh spacecraft in the TIROS Operational System 0725 EDT DSV-3N SLC-2E (TOS) series and seventeenth in the TIROS series. (0425 PDT) (Del ta-58) ESSA 7 was successfully launched into the desired orbit. The 154-kg (340-1 b) polyhedral spacecraft carried two Advanced Vidicon Camera Systems (AVCS to obtain daily global cloud photos and a flat plate radiometer to measure the heat balance of the atmosphere. Still in orbit--1,471 x 1,429 km (914 x 888 sn), inclination 101.9°, period 115 minutes. (S) Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Resul ts ESSA 8 15 Dec 68 Delta TOS-F WTR This was the eighth spacecraft in the TIROS Opera- 1221 EST DSV- 3N SLC-2E t ional Sate11 ite (TOS) series. The two-stage (0921 PST) (Del ta-62) launch vehicle first injected the second stage and spacecraft into a transfer orbit. After a coast period the second stage was restarted, and placed the spacecraft into the desired retrograde, Sun- synchronous, near-pol ar orbit. This provided maximum coverage of the illuminated Earth. The 18-sided, 136-kg (300-lb), spin-stabil ized spacecraft carried two Automatic Picture Transmission (APT) camera systems to transmit real-time television pictures of Earth's cloud cover. Still in orbit--1,462 x 1,411 km (908 x 877 sm), inclination 101.3O, period 115 minutes. (S) ESSA 9 26 Feb 69 Del ta TOS-G ETR The 112-kg (247-lb) spacecraft was launched into a 0247 EST DSV- 3E 17B near-pol ar , Sun-synchronous orbit. A1 though re- (Delta-67) quired to perform three precise "dogleg" maneuvers to reach the orbital injection point over the Pacific Ocean, some 3,219 km (2,000 sm) southwest of Cdpe Canaveral, the launch vehicle performed exceptionally we1 1. The spacecraft's orbit is so nearly Sun-synchronous that it will take over 30 years for the satellite's equator crossing time to change by one hour. The spacecraft carried two Advanced Vidicon Camera Systems (AVCS) to obtain daily global cloud photos, and a radiometer to measure the heat balance of the atmosphere. Still in orbit--1,503 x 1,423 km (934 x 884 sm), inclination 102.1°, period 115 minutes. (S) METEOROLOGY (continued)

IMPROVED TIROS OPERATIONAL SATELLITE ( ITOS and NOAA)

Mission Launch Launch NASA Site/ Name L)ate/Time Vehicle -Code -Pad i i'OS 1 & 23 Jan 70 Del t a TIROS-M/ W TR Dual launch of the prototype in a new series of OSCAR 5 0631 EST DSV-3L-11 OSCAR- A SLC-2W operational meteorological sate1 1 ites and ac ama- (0331 PST) (Del ta-76) teur radio operators communications satellize. First launch of Delta rocket using 6 strap-on solid motors on first stage. The Improved TIROS wi11 provide, on a daily basis, global coverage of weather conditions; OSCAR, with a two-month operational life, was designed to provide data on communications tests between amateur radio operators. Spacecraft systems performed normally in orbit. TIROS orbital parameters are: apogee 1,476 km (917 sm), perigee 1,432 km (890 sm), inclination 101.gO, period 115 minutes. (S) METEOROLOGY lconti nued r Mission Launch Launch NASA Site/ 14 ame DateITirne Vehicle -Code -Pad Remarks/Resul ts NOAA 1 11 Dec 70 Delta ITOS-A WTR 309-kg (682-1 b) spacecraft, first operational 0635 EST DSV- 3L SLC- 2W (after prototype ITOS 1) second-generat ion (0335 PST) (Del ta-81) meteorological sate11 ite with three-axis stabi 1izat ion and nighttime viewing capabil ity for 24-hour global coverage- Funded by Dept. of Comnerce; developed by NASA; operated by National Oceanic and Atmospheric Admin. NOAA 1 was successfully injected into 1,472 x 1,423 km (915 x 884 sm) orbit with 102' inclination and 115-minute period. Launch vehicle was two-stage Delta with six sol id-propellant mators strapped to first stage and second-stage restart capability. Three of solid motors ignited at liftoff to give total thrust of 1,467,440 newtons (330,000 1b). Remaining three solids ignited 31 seconds later to extend thrust augmentation. First 1aunch attempt terminated on 8 Nov due to second stage control system problems. Second launck attempt on 9 Dec scrubbed due to hi gh-a1 titude wind conditions. Countdown resumed on 10 Dec and proceeded to 1 iftoff. Launch vehicle a1 so carried into orbit a Cy- 1 indrical Electrostatic Probe Experiment (CEPE) as a secondary payload attached to second stage. In near-circular orbit with apogee 1,471 km (914 sm), perigee 1,422 km (884 sm), incl ination 101.9", and period 115 minutes. (S) Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Results ITOS B 21 Oct 71 Delta ITOS-B WTR Second operational spacecraft of second-generat ion 0732 EDT DSV-3L SLC-2E Improved TIROS Operational Sate11 ite (110s) (0432 PDT) (Del ta-86) series . Countdown proceeded normal ly to 1iftoff . Flight appeared normal through the first burn of the second stage, but at start of one-hour coast period a force resulting from a leak in the second stage oxidizer system tended to tumble the vehicle. Pitch-and-yaw jets were able to maintain proper vehicle attitude until the control gas was expended and vehicle began to tumble. Remaining vehicle functions, including second-stage second burn and spacecraft separation, occurred on schedule but orbit was not achieved. Spacecraft and Delta second stage impacted above the Arctic Circle. (U) METEOROLOGY lconti nued)

Mission Launch Launch NASA Site/ Name DateITime Vehicle -Code -Pad Remarks/Resul ts NOAA 2 15 Oct 72 Delta ITOS-D WTR Delta-91, a two-stage launch vehicle with first & 1319 EDT DSV-3N SLC-2W stage liftoff thrust augmented by three strapped- OSCAR 6 (1019 PDT) (Del ta-91) on Castor I1 solid propellant motors, was originally assigned to the ITOS-C mission and had completed prelaunch checkout when a decision was made to launch ITOS-D instead of ITOS-C. Due to a con- flict in priorities with the ERTS-A mission, the launch vehicle was demated from SLC-2W in late May and placed in storage until re-erection began near the end of July. Launch vehicle and spacecraft assembly and checkout proceeded normal 1y , a1 though the original countdown was scrubbed on 13 Oct due to an unacceptable predicted debris fa1lout pat- tern resulting from the upper level winds. The 345-kg (760-1 b) NOAA-2 spacecraft was successfully placed in the desired near-polar circular orbit of 1,454 x 1,448 km (903 x 900 sm) with an inclination of 102O, a 115-minute period, and equator crossing times of 0848 and 2048 local time. The 18-kg (40-lb) OSCAR 6 amateur radio satellite, carried as a secondary payload, was injected into a similar orbit. Both spacecraft functioned normally. Both now in orbit of 1,453 x 1,447 km (903 x 899 sm), inclination 101.4", period 115 minutes. (S) METEOROLOGY (continued)

Mission Launch Launch NASA Site/ Name DateITime Vehicle -Code -Pad Remarks/Resul ts I ITOS 16 Jul 73 Delta ITOS-E WTR Countdown began on schedule and 1iftoff occurred 1310 EDT DSV-3N SLC-2W within the launch window. Early stages of powered (1010 PDT) (Del ta-96) flight appeared normal, but tracking stations at Tananarive and Johannesburg failed to pick up sig- 6 nal s at the programned time, indicating the 345-kg (760-lb) satell ite failed to reach orbit. Early flight data revealed that at approximately 270 seconds after second-stage ignition the hydraul ic I pump abruptly ceased output, resulting in loss of I hydraul ic pressure and thrust vector control. Because of this loss of control, the vehicle tum- I bled and did not achieve orbital velocity. (U) NOAA 3 6 Nov 73 Del ta ITOS-F WTR This ITOS (Improved TIROS Operational Satellite) 1202 EST DSV-3N-11 SLC-2W joined the network of weather-report ing sate11 ites (0902 PST) (Del ta-98) operated by the National Oceanic and Atmospheric Administration. Damage to the comon bulkhead of the second stage propellant tanks caused a delay in the launch from 18 October 1973 tc 6 November 1973 while the second stage was replaced. NOAA was then launched into an initial orbit of 1,509 x 1,499 km (937 x 932 sm); inclination 102,8O; and period 1 hour, 56 minutes, 5 seconds. Current orbit is at the same altitude, with an inclination of 101.8O and a period of 116.1 minutes. (S) METEOROLOGY (continuedr

Mission Launch Launch NASA Site/ Name DateITime Vehicle -Code -Pad RemarksiResul ts NOAA 4, 15 Nov 74 Del ta ITOS-G WTR This was the third NOAA spacecraft rhich obtained OSCAR 7 d 1211 EST DSV-?N-11 SLC-2W quant itati ve measurements of the Earth's atmo- Int asat (0911 PST) (Del ta-104) spheric structure, and provided informat ion for daily weather forecasting. During prelaunch prep- arat ions, a VE 1 actuator, both first-stage actua- tors, and the second-stage hydraulic pump had to be removed and rep1aced. Rodent contamination found in the guidance section was a1 so removed. Besides NOAA 4, the Delta vehicle a1 so carried in- to orbit an amateur radio operator's satellite, OSCAR 7, and a small Spanish sate1 lite, called Intasat. Initial orbital parameters for NOAA 4 were: orbit 1,464 x 1,454 km (909 x 904 sm); incl ination 101.7O; and period 1 hour, 55 minutes. Current orbit is 1,457 x 1,444 km (905 x 897 sm), with a 101.5O inclination and a 115-minute period. 6) NOAA 5 29 Jul 76 Delta ITOS-E2 WTR The 339.3-kg (748-lb) NOAA 5 was successfully in- 1307 EDT 2310 SLC-2W jected into an orbit with an apogee of 1,522 km (1007 PDT) (Del ta-126) (946 sm) and a perigee of 1,509 km (936 sm) ; incl ination 101.9O; and period 1 hr, 56 mins, 12 secs. NOAA 5 fulfilled two af the three objectives of t he National Operational Meteor01ogical Sate1 1 ite System (NOMSS). It obtained global cloud-cover data both day and night, and also obtained global -scal e quantitative measurements of the Earth's atmospheric structure to apply to numerical weather predict ion. The other objective of NOMSS, continuous viewi ng of weather features from synchronous a1 titude, was fu1 f i1 1ed by sate1- 1ites in the SMS/GOES series. In orbit at 1,523 x 1,506 km (946 x 936 sm), inclination 101.9O, period 116 minutes. (S)

METEOROLOGY (conti nued j

Mission Launch Launch NASA Site/ Name Date/Time Vehicle Code -Pad 18 May 68 Th or- Nimbus -8 WTR First NASA 1aunc h usi ng long-tank Thorad-Agena. 0423 EDT Agena SLC- 2E Spacecraft incl uded a radioi sotope thermoelectric (0123 PDT) (Thrust- generator (SNAP-19) , augnenti ng the sol ar conver- Augmented) sion power supply, to assess operational capabi 1 i- (Thor- ty of radioisotope power for long-life weather Agena-9) sate11 ites. A1 so carried as a "pi ggybac k" pay1oad was a U.S. Arqy SECOR (Sequential Collation of Range) geodetic sate1 1i te. A1 though the so1 id- propel 1ant strap-on boosters performed normal ly, the Thor engi ne began an undamped osci 11at ion about two seconds after liftoff. The launch vehicle was destroyed by the Range Safety Officer after 121 seconds of flight when it veered beyond limits. (U)

Nimbus 3 14 Apr 69 Thor- Nimbus-B2/ WTR The fourth of seven spacecraft in the Nimbus and 0254 EST Agena SECOR SLC- 2E series was essentially a repeat of the EGRS 13 (13 Apr 69) (Thrust- unsuccessful Nimbus-B mission. The 617- kg (2354 PST) Augmented) (1,360-1 b) spacecraft was injected into a Sun-syn- (Thor- chronous , near-ci rcular, pol ar retrograde orbit . Agena-10) A1 1 spacecraft systems functioned successfully, including the SNAP-19 radioisotope thermoelectric generator. An Arqy SECOR (Sequenti a1 Col 1at ion of Range) sate1 1 ite was carried as a secondary payload on the Agena stage and was also injected into orbit. SECOR was later renamed EGRS 13. Both spacecraft are still in orbit. Ninbus 3 is at 1,130 x 1,070 km (702 x 665 sm), with an incl ination of 99.6', and a period of 107 minutes. (S) METEOROLOGY Tcont inued 1

Mission Launch Launch NASA Site/ frame Date/Time Vehicle -Code -Pad Remarks/Resul ts Nimbus 4 8 Apr 70 Thor- Nimbus-D/ WTR This was a dual launch of a NIMBUS meteorological & TOP0 1 0318 EST Agena TOP0 SLC- 2E satellite, with a U.S. Army Topographic Comnand (0018 PST) (Thrust- TOPO-A as a secondary payload. TOPO-A performed Augmented) we1 1. The l4IMBUS was designed to take measure- (Thor- ments to provide selected vertical profiles of Agena- 13) temperature, water vapor, and ozone content of the atmosphere from ground level upward. ;he spacecraft operated satisfactorily in a nearly circular orbit. Still in orbit, with an apogee of 1,102 km (685 sm), a perigee of 1,091 km (678 sm) , 99.6O inclination, and a 107-minute period. (S) ! 1 Nirilbus 5 11 Dec 72 Del ta Nimbus-E WTR Delta-93 was a two-stage launch vehicle with i 0256 EST DSV - 3N SLC- 2W first-stage liftoff thrust augmented by nine 1 (10 Dec 72) (Del ta-93) strapped-on Castor I1 solid propellant motors. (7356 PST) The second stage was programed for three starts to demonstrate its mu1 t iple restart capabi 1ity. Although range scheduling moved the launch date from 11 to 10 Dec (local time), no problems were encountered during countdown and 1i ftoff occurred on schedule at the opening of the launch window. The 772-kg (1,702-lb) Nimbus 5, sixth in the series of seven research and development spacecraft desi gned to f 1i ght -test a variety of meteor01ogical and other Earth observations experiments, was successfully injected into the desired Sun-synchronous, near-ci rcul ar polar orbit of 1,101 x 1,089 km (684 x 676 sm) at an incl ination of 100" amd a 107-minute period. Still in an orbit of 1,105 x 1,092 km (687 x 679 sm), incl ination 99.8" and period 107 minutes. (S) METEOROLOGY (continued)

Mission Launch Launch NASA Site/ N am Date/Time Vehicle -Code -Pad Nimbus 6 12 Jun 75 Del ta Nimbus-F WTR Mission of Nimbus 6 was to gather data on Earth's 0412 EDT DSV-3N-1 iB SLC-2W atmosphere and its dynamics and provide better (0112 PDT) (Del ta-111) means of weather forecasting. The spacecraft participated in the Global Atmospheric Research Program (GARP) conducted during the sumner of 1975. GARP was an international effort to gather data on the upper South Atlantic ocean region, where many hurricanes originate. Nimbus 6 was placed into the planned near-Earth orbit of 1,108 x 1,106 km (688 x 687 sm) with an incl ination of 99.6O and a period of 1 hour, 47 minutes, and 12 seconds. Nimbus 6's current orbital status is: apogee 1,116 krn (693 sm) , perigee 1,105 km (687 sm), inclination 99.g0, and period 107 minutes. (S) Nimbus 7 24 Oct 78 Delta Nimbus 7 was successfully launched into an orbit 0414 EDT 2910 954.6 x 953.6 km (593.2 x 592.5 sm); with a period (0114 PDT) (Del ta-145) of 1 hour, 44 minutes, and 8 seconds; and an incl ination of 99.28O. It was the last satel 1ite in the series which flight-tested new instrlments for pol 1ut ion, oceanographic, and meteorological appl ications. The Nimbus series contributed significant ly to observation techniques incorporated in operational satellites such as GOES and TIROS. Nimbus 7, which weighed 987 kg (2,176 Ib) at launch, was sent into orbit with an 89-kg (196-lb) experiment attached to the second stage of the Delta vehicle. Called CAMEO (for Chemically Active Material Ejected in Orbit), this experiment consisted of one 1ithiun and four barium gas can- isters. It released the gases at orbital altitudes, in order to study the boundary between the polar cap and the auroral belt, and to evaluate orbital velocit effects on neutral and ion clouds. current orbit is 958 x 945 km (595 x 587 sm), inclination 99.3O, period 104 minutes. (S) METEOROLOGY (cont inueo GEOSTATIONARY OPERATIONAL ENVIRONMENTAL SATELLITES (SMS and GOES

:lission Launch Launch NASA Site/ Name DateITime Vehicle -Code --Pad RemarksIResul ts SMS 1 17 May 74 Delta SMS-A ETR SMS 1 (Synchronous Meteorological Satellite 1) was 0531 EDT DSV-3P-11B 17B the f irst of two prototype geosynchronous orbit (Del ta-102) weather satellites. It was designed to (1) photograph the complete disk of the Earth every half-hour in both visible light and infrared, (2) serve as a relqy for up to 10,000 unmanned environmental monitoring platforms on the ground and in the oceans, and (3) monitor solar radiation and warn of solar disturbances such as flares. Too little pressure in the liquid oxygen tank caused Delta-102's first stage to achieve lower than the planned velocity. The guidance system added 14.7 seconds end time to the first burn to compensate for the low velocity achieved by the first stage, but correct orbft was not achieved. SMS 1 was injected into a highly elliptical transfer orbit close to the predicted in prigee and inclination, but about 3,336 km (2,073 sm) be1ow the planned apogee. Goddard control 1ers uti 1 i zed part of the on-board attitude control system fuel, in conjunction with the usual apogee motor burn, to move the spacecraft into the proper geosynchronous orbit. SMS 1 was first stationed at 45' west longitude to participate in the Global Atmospheric Research Program, then moved to 75O west 1ongi tude to provide weather observations of the United States and adjacent ocean area. SMS 1 provided continuous day and night images of cloud cover over the United States and the Atlantic Ocean for the first time. The satellite weighed 628 kg (1,385 Ib) at launch. Still orbiting at 35,790 x 35,779 km (22,239 x 22,232 sm), inclination 4. lo,and period 1,436 minutes. (S) METEOROLOGY (continued)

Mission Launch Launch NASA Site/ Name DateITime Vehicle -Code -Pad Remarks/Resul ts SMS 2 6 Feb 75 Del ta SMS- B ETR This spacecraft was the second of the two 1704 EST DSV-3F-11B 178 prototype Synchronous Meteor01 ogical Sate11 i tes, (Del ta-108) which were desi gned to operate in geosynchronous orbit. These satellites were prototypes of the GOES (Geostationary Operational Environmental Satellite) spacecraft operated by the National Oceanic and Atmospheric Admini stration (NOAA) . SMS 1 and 2 were also operated and controlled by NOAA after being checked out by NASA. SMS beamed weather photographs and other information directly to local weathermen at widely scattered data utilization stations and to the operations center, where it was analyzed by meteorologists there, then sent to the smaller receiver stations using the SMS as a relay. SMS tracked hurricanes, typhoons, and blizzards by the hour, providing imnediate information on their location and probable path of travel. Orbiting at 35,814 x 35,757 km (22,254 x 22,218 sm), inclination O.lO, period 1,436 minutes. (S)

GOES 1 16 Oct 75 Delta GOES-A ETR This was the first Geostationary Operational Envi- 1840 EST DSV-3P-11B 17B ronmental Sate11 i te. The spacecraft in this (Del ta-116) series are physically identical to the two earlier Synchronous Meteorol ogical Sate1 1i tes, which were funded and developed by NASA. The GOESs are the operational version, funded by NOAA. GOES 1 was placed in a near-geosynchronous orbit , then turned over to NOAA and drifted to its final location, where it entered normal service. Orbiting at 35,591 x 35,566 km (22,115 x 22,100 sm), inclination O.OO, period 1,425 minutes. (S) METEOROLOGY (continued)

Mission Launch Launch NASA Site/ Name DateITime Vehicle -Code -Pad GOES 2 16 Jun 77 Delta GOES-B ETR Second operational geosynchronous we:. ther 0651 EDT 2914 178 observer. Del ta vehicle perfonnance was normal , (Del ta-131) and placed the spacecraft in the desired transfer orbit. The apogee motor firing circularized the orbit , and the satel 1 ite entered operations under NOAA control after a 30-day checkout by NASA. Now in orbit at 35,799 x 35,780 km (22,244 x 22,233 sm), inclination 0.4O, period 1,436 minutes. (5) 16 Jun 78 Delta GOES-C ETR This third wither observer (96-1 was no longer 0650 EDT 2914 179 operational ) operating from geosynchronous orbit (Del ta-142) enabled the USA to free GOES 1 to become part of the five-satell ite Worl d-wi de Weather Watch system, replacing a planned U. S.S.R. satel 1ite which was not launched. In conjunction with GOES 2, GOES 3 provides full weather coverage of the entire western hemi sphere, greatly improving weather forecasting and the tracking of dangerous storms and hurricanes. In geosynchrono~~sorbit at 35,804 x 35,775 km (22,248 x 22,230 sm), inclination 0.0". period 1,436 mins. (S) METEOROLOGY lconti nued)'

Mission Launch Launch NASA Site/ Name Date/Time --Vehicle -Code -Pad Remarks/Resul ts GMS 14 Jul 77 Delta GMS ETR This geosynchronous weather sate1 1i te, bui 1t and 0639 EDT 2914 17B operated by Japan, fulfilled that nation's comnit- (Del ta-132) ment to provide one of five World-wide Weather Watch satel 1i tes for global weather reporting. Functionally similar to the GOES and SMS series, its data can be integrated with the other WWW sate1 1ites for global -scale weather reporting and analysis. Japan assumed charge in the transfer orbit and fired the apogee motor; GMS entered the correct orbit. It is now on station over Asia. Current orbit measures 35,858 x 35,715 km (22,281 x 22,192 sm), inclination 0.7', period 1,436 minutes. (S)

EARTH OBSERVATIONS

GEODETIC EARTH ORBITING SATELLITE (GEOS)

Mission Launch Launch NASA Site/ Vehicle Code Pad Name Date/T ime - 7 GEOS 1 6 Nov 65 Del ta GEOS-A ETR First launch of a Geodetic Earth Orbiting (Expl or- 1339 EST DSV-3E 17A Satellite and an improved thrust-augmented Delta; er 29) (Del ta-34) first gravity-gradient stabilized satellite, 174.6 kg (385 lb), launched by NASA. Purpose was to investigate Earth's gravitationa: field, to improve world-wide geodetic accuracies, and to improve positional accuracies of sate1 1ite tracking sites. Still in orbit at 2,269 x 1,119 km (1,410 x 695 sm), inclination 59.4O, period 98 minutes. (S

PAGEOS 1 23 Jun 66 Thor- PAGEOS A WTR Passive Geodetic Earth Orbiting Sate1 1ite. Near- 2021 EDT Agena SLC-2E circular polar orbit. Similar to Echo 1, alumi- (1721 PDT) (Thrust- num-covered ql ar balloon , 30.48-met er (100-foot ) Augmented) dianeter, 56.7 kg (125 lb). No instruments, (Thor- world-wide triangulation network by optical sight- Agena-7 ) ing~allows very accurat? mapping. Still in orbit at 4,280 x 4,172 km (2,659 x 2,592 sm), inclination 86.g0, period 181 minutes. (S)

I GEOS 2 11 Jan 68 Delta GEOS-B Second spacecraft of the GEOS series and fifth (Expl or- 1116 EST DSV -3E satellite to be launched in the National Geodetic er 36) (0816 PST) (Del ta-56) Satell ite Program (NGSP). Successfully injected into an orbit very close to that planned: 1,575 x 1,085 km (979 x 674 sm), inclination 106O, 112- minute period. Spacecraft was checked out and declared operational on 20 February 1968. GEOS 2 extended the investigations associated with the NGSP. Current orbit measures 1,573 x 1,080 km (997 x 671 sm), inclination 105.8O, period 112 minutes. (S) GEODESY ( cont inued)

GEODY NAMICS EXPERIhENTAL OCEAN SATELLITE (GEOS)-.

Missi on Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remrks/Resul t s GEOS 3 9 Apr 75 Delta GEOS-C WTR GEOS 3, the Geodynamics Explerimental Ocean Satel- 1950 EDT 1410 SLC-2W 1ite, continued the Earth studies performed by (1650 PDT) (Del ta-109) GEOS 1 and 2, the Geodetic Earth Orbiting Satel- 1ites. GEOS 3 concentrated on the oceans, providing ocean wave heights, wind speeds at the air-sea interface, ocean current boundaries and vel oci- ties, and sea ice locat ions. GEOS 3 a1 so demonstrated that Earth terrain contouring could be done with radar a1 timeter measurements from a satell ite. GEOS 3 was placed in an almost perfect circular orbit, 849 x 849 I-I (527 x 527 sm) with an 115' inclination and a ' our, 42-minute period. Still in orbit; still transmitting. Orbit now measures 863 x 821 km (536 x 510 sm), incl ination 114.g0, period 102 minutes. (S) GEODESY (cont inued)

LASER GEODYNAMIC SATELLITE (LAGEOS ) I Missi on Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Resul ts I LAGEOS 1 4 May 76 Delta LAGEOS WTR Designed to be a reference point in space for 0400 EDT 2913 SLC-2W ground lasers, this 411 -kg (906-1 b) sate1 1ite had (0100 PDT) (Del ta-123) a surface covered with 426 corner cube reflectors. LAGEOS 1 was used to measure (1) the movement of the Earth's tectonic plates, (2) motion of the Earth's polar axis and the Earth's rotation, (3) the Earth's gravity field, and (4) satellite orbital perturbations. Understanding t:lo=c processes could lead to ways to predict earthquakes and locate mineral resources. LAGEOS is now orbiting at 5,946 x 5,837 km (3,695 x 3,627 sm), inclination 109.8", period 225 minutes. (S) EARTH OBSERVATIONS

EARTH RESOURCES TECHNOLOGY

LANDSAT (EARTH RESOURCES TECHNOLOGY SATELLITES)

Mission Launch Launch NASA Site/ Name DateITime Vehicle -Code -Pad Remarks/Resul ts LANDSAT 1 23 Jul 72 Delta ERTS-A W TR Two-stage Del ta configuration ; first use of new (for~nerly 1406 EDT DSV-3N-11 SLC-2W Delta Inertial Guidance System; first use of nine ERTS 1) (1106 PDT) (Del ta-89) strap-on sol id-propel1 ant motors on first stage. Six sol ids ignite: at liftoff to give total sea- level thrust of 2,152,832 newtons (484,000 lb); remaining three sol ids programed to ignite 39 seconds after 1 iftoff to pro1ong thrust augnenta- tion. New second stage propulsion system had two- restart capabil ity. Liftoff occurred 12 minutes into launch window due to a hold to investigate first stage anomaly. 941-kg (2,075-i b) spacecraft, based on the Nirnbus design, was injected into a near-circul ar orbit: 907 x 900 km (564 x 558 sm); 99' inclination; 103-minute period. On 24 Oct ERTS 1 was deemed to have achieved its primary objective of repetitively acquiring synoptic multispectral images for a period of three months, providing useful data for investigations of agri- culture and forestry resources, mineral and land resources mapping and charting, and the environment. LANOSAT 1 was retired in early 1978. It is still in orbit--912 x 899 km (567 x 559 sm), incl ination 98.8", 103 minutes. (S) EARTH RESOURCES TECHNOLOGY (conti nued)

Mission Launch Launch NASA Site/ Name --Date/Time Vehicl e -Code -Pad Remarks/Resul ts LANDSAT 2 22 Jan 75 Delta ERTS-8 WTR Original ly scheduled for launch ten days earl ier, 1256 EST 2410 SLC-2W the mission was delayed for rep1acement and re- (0956 PST) (Del ta-107) qua1 ification of Stage 1 and 2 electronics packages. Designed to scan atmospheric and surface features in both infrared and visual spectrms, incl udi ng water, atmosphere, forests and pollu- tion, the spacecraft was successfully placed in an orbit of 919 x 904 km (572 x 561 sm). LANDSAT 2 was retired from operation in Jan 1980, because of a wear-induced failure of its primary flight control n~chanism. The spacecraft surpassed its design lifetime of one year and provided environmental data for five years. As of 31 Dec 1979, its orbit measured 919 x 914 km (571 x 568 sm), incl ination 99.1°, period 103 minutes. (S) LANDSAT 3 5 Mar 78 Delta LANDSAT-C WTR Carrying a 25.8-kg (56.8-lb) AMSAT/OSCAR 8 and a 1254 EST 2911) SLC-2W 33.8-kg (74.6-1b) PIX satellite in addition to its (0954 PST) (D2l ta-139) own package dupl icating the LANDSAT 2 mission, the spacecraft was successfully placed in an orbit of 917 x 899 km (571 x 508 sm). Now orbiting at 921 x 902 km (572 x 560 sm), inclination 9g0, period 103 minutes. OSCAR 8 was bui 1t by radio amateurs in the United States, Canada, West Germany, and Japan. It was developed under the auspices of the non-profit Radio Amateur Satellite Corp. in cooperat ion with the American Radio Re1 ay League, Inc. OSCAR 8 carried two transponders, both of which shared the same uplink frequency of 145.9 MHz but employed different down1 ink frequencies of 29.4 MHz and 435.1 MHz. PIX, the Plasma Interaction Experiment, was attached to the second stage of the Delta launch vehicle, which remained in orbit. Its purpose was to develop a means for control 1ing detrimental interactions between high voltage systems and the space plasma environment. (S) COMMUNICATIONS

TECHNOLOGY DEVELOPMENT

ECHO

Mission Launch Launch NASA Site/ Name Date/Ti me Vehicle -Code -Pad Echo 13 May 60 Del ta First use of the Delta launch vehicle; attempt to 4 0416 EST DM-19 orbit a 30-meter (100-foot) diameter, 60-kg .-3 (Del ta-1) (132-1 b) passive ref 1ector sphere. Second-stage 2 autopi lot fai led during coast phase; third-stage engine did not fire; spacecraft did not separate $ from launch vehicle. (U) C- ", Echo 1 12 Aug 60 Del ta A- 11 ETR First passive comnunications sate1 1ite; the 0440 EST DM-19 17A 30-meter (100-foot) diameter, 75-kg (166-lb) alu- (Del ,ta-2) minized plastic sphere, used as a reflecting relay for global communications experiments, was 1argest and most visible sate1 1ite to that time. Initial orbit parameters were 1,942 km (1,207 sm) apogee and 1,753 km (I ,089 sm) perigee. Slowly lost its spherical shape due to meteoroid punctures and escape of internal gases. Re-entered atmosphere 24 May 1968. (S)

Echo 15 Jan 62 Thor AVT- 1 E TR "Project Big Shot" Applications Vertical Test No. (Test) 0607 EST DSV - 2D (A-12) 17A 1, a suborbital inflation test of 243-kg (535-lb), (Thor-337) 41-meter (135-foot) diameter sphere. Canister ejection successful, but too rapid inflation ripped balloon apart at 400 km (250 sm) a1 titude. All test objectives were d~cornplished, dnd cdrsule with rnovie film re-entered and was recovered. (P)

Echo 18 Jul 62 Thor AVT- ;' E TR Inflation test of 13-story balloon, second "Proj- (Test) 0430 PST USV- 2D (A-12) 17A ect Big Shot ," was successful. The 243-kg (Tilor-338) (535-1b) sphere wc; visible for 10 minutes fro111 Cape Canaveral. It was the largest human-made object sent into space, the previous record being held by Echc 1. Not interlded as an orbital shot, AVT-2 rz-entered 27 July i962. (S) I I I QdL Q L CCU 0 C OaJ Ira c

TECHNOLOGY DEVELOPMENT (continued)

RELAY

Mission Launch Launch ~JASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Resul ts Relay 1 3 Dec 62 Del ta A-15 E TR This octagonal 78-kg (172-1 b) spacecraft was the ,830 EST DSV -3B 17A first active repeater comnunications satel 1 ite. fDel ta-15) Power supply voltage originally too low for comnu- nicat ion experiments ; vol tage bui 1t up, and early in January 1963 transatlantic TV transmissions began. Still in orbit--7,438 x 1,321 km (4,622 x 821 sm), inclination 47.5', period 185 minutes. (S) Relay 2 21 Jan 64 Del ta A-16 E TR Simi 1ar to Relay 1, but had longer expected oper- 1615 EST DSV - 2B 176 ating time, more efficient orbit, and internal (Del ta-23) changes designed to improve operation over earlier version. The 83.3-kg (183.6-1 b) spacecraft successful ly transmitted television test patterns at the end of its first orbit, and performed successfully when tested on subsequent orbits. Still in orbit--7,477 x 2,024 km (4,646 x 1,258 sm), inclination 46.4, period 195 minutes. (S) TECHNOLOGY DEY ELOPMENT (continued)

SY NCOM

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Results Syncom 1 14 Feb 63 Del ta Syncom-A ETR First NASA attempt for near-synchronous, 24-hour 0035 EST DSV-3B A-25 178 orbit successful. The 39-kg (86-lb) cylindrical (Del ta-16) sate11 ite transrni tted data during 1aunch, then went silent. Was lost until location in desired orbit was confirmed by photoyraphs 1 March 1963. Still in orbit, but current elements not maintained. (P)

26 Jul 63 Del ta Syncom-B ETR World's first satellite to achieve synchronous 0933 EST DSV-3B A-26 17A 24- hour orbit. Entered def irlite synchronous orbit over Brazil and the South Atlantic Ocean on 15 August. Reached an a1 titude of 35,880 bn (22,300 sm) and a speed of 10,943 kph (6,800 mph) , match- ing the Earth's rotation speed of 1,634 kph (1,040 mph) at the equator to keep it on station. Still in orbit, but current elements not maintained. (S)

Syncom 3 19 Auy 64 Delta Syncom-C f TR First launch of a Delta using strap-on solid

0715 EST DSV-3D A-27 ' j$* motors (3) to increase first stage thrust. Sync0111 (Del ta-25) 3 was 1aunched into prel iminary orbit and 1ater maneuvered into synchronous orbit psition over the Pacific above the Equator and the Interna- tional Date1 ine. Live TV pictures of the Olyn~pic Games in T~kyowere trans~r~itted to the U. S. by Syncom 3. Still in orbit, 35,883 x 35,759 kn~ (22,297 x 22,220 sin), inclination 5.5", period 1,437 minutes. (S) TECHNOLOGY UEIELOPMENT (continued)

Mission Launch Launch NASA Site/ Name Date/T ime Vehicle -Code -Pad Remarks/Resul ts Symphonie 1 18 Dec 74 Delta Symphoni e-A ETR This experimental domestic co~r~nunicationssatel- 2139 EST DSV-3P-11B 178 1 ite was owned by France and West Germany. Launch (Del ta-106 ) was slipped one day due to a drain val ve being accidentally opened at the wrong time, allowing bubbles to enter the vehicle's fuel storage tank. Consequently, the tank had to be refilled. At the same time, a quick-disconnect sprang a leak and sprayed the vehicle's skin with kerosene. No damage resulted , and the quick-disconnect was rep1aced. Symphonie 1 entered a highly el 1i pt ical transfer orbit . The German Space Operat ions Center then took control and fired the apogee boost motor to insert the spacecraft into geosynchronous orbit. Sympkdnie had two transponders, each designed to provide a capability ot relaying one color TV channel or 600 two-way telephone con- versat ions. When the sate1 1i te entered service, it was found that its estimated TV capacity could be doubled. Each transponder could relay two color TV programs, for a total of four on the spacecraft. Current orbit measures 35,804 x 35,773 km (22,248 x 22,228 sm), inclination O.gO, period 1,436 minutes. (S) d~l~~phonieL 26 Aug 7 5 Delta Symphoni e-B ETR The second of the two Symphonie spacecraft owned 2142 EDT DSV-3P-11B 17A by France and Germany, which provided the first (Del ta-114) domestic satel 1ite comnunications capability for those nations. Like its predecessor, Symphonie 2 a1 so operated in a geosynchronous orbit. Now orbiting at 35,834 x 35,738 km (22,266 x 22,207 sm), inclination l.SO, period 1,436 minutes. (S) U Q) am -0 r 3 cnm E tno" g,CO," TECHNOLOGY DEVELOPMENT (continued)

SIRIO

Mission Launch Launch NASA Site/ N awe Date/Time Vehicle -Code -Pad

SIR10 25 Aug 77 Del ta SIR10 ETR SIRIO was the first comnunications satell ite owned 1950 EDT 2313 17B and operated by Italy to be placed in a geosyn-

I (Del ta-133) chronous orbit. SIRIO perforned propagation experiments to determine the feasibility of using a superhi gh frequency range for comnerci a1 comnuni - cations. It received signals at 18 GHz and retransmitted them at 12 GHz. (SIRIO was similar to the U.S.-Canadian CTS, which received at 14 GHz and retransn;.;ted at 12 GHz.) SIRIO a1 so gathered data on the ;dss of signal strength due to adverse weather cond ; :f ons such as snow, rain, or heavy fog. Curren~orbit: 37,049 x 34,582 km (23,021 x 21,488 srn), inclination 1.6", period 1,438 minutes. (S) TECHNOLOGY DEVELOPMENT (continued)

GRB ITAL TEST SATELLITE (OTSL

Mission Launch Launch NASA Site/ Narne Date/Time Vehicle Code -Pad Remarks/Resul ts OTS 1 13 Sept 77 Del t a OTS E TR The Orbital Test Sate11 ite (OTS) was built by the 1931 EDT 3914 17A European Space Agency (ESA) as a pre-operational (Del ta-134) version of follow-on satellites that wo~ldprovide co~nnunicat ions 1 inks between cities in ESA member nations. OTS never reached orbit; a motor in one of Delta-134's solid boosters malfunctioned and the vehicle exploded 54 seconds into the mission. (U 1 OTS 2 11 May 78 Oel ta OTS-2 ETR OTS 2 was the backup to the Orbital Test Satellite 1859 EOT 3914 17A lost when Delta-134 failed (OTS 1). The primary (Del ta-141) purpose cf this pre-operat ional spacecraft was to receive and transmit telephone and television signal s whi le performing propagation measurements. OTS 2 carried six transponders (together with a redundant beacon) that operated at a higher than normal frequency range, receiving at 14 GHz and retransmitting at 11 GHz. OTS 2 weighed 865 kg (1,900 1b) at launch and 460 kg (1,014 lb) after burning its apogee motor propellantso It was positioned at 10' east longitude above the equator, in geosynchronous orbit. Current orbit lneasures 35,788 x 35,774 km (22,238 x 22,229 sm), incl ination 0.4', period 1,436 minutes. (S) TECHNOLOGY DEVELOPMENT (continued)

i I Mission Launch Launch NASA site7 i Nam? Date/Time Vehicle --Code -Pad Remarks/Results-- 14 Dec 77 Delta 2s ETR Japan/CS, the Medium-Capacity Cmunications 1947 EST 2914 17B Sate1 1ite for Experinrental Purposes, was funded ~j (Dei :a-137) NASDA (National Space Development Agency of Japan). Its purpose was to explore the utilization of the higher frequency ranges, which were not crowded with commercial radio traffic. Oper- ating in a geosynchronous orbit, Japan/CS carried six K-band transponders, which received ground transmissions at 30 GHz and retransmitted them at 20 GHz, and two C-band traqs~o~der5,whjch received at 6 GHz and retransnittet at 4 &,. The satell ite's antenna horn featured a new design which directed signals to the assigned territory without impinging on neighboring countries. This spacecraft weicjhed 676 kg (1,590 I b) at launch, and 339 kg (747 lb) after burning the apogee motor propellants. It was stationed at 135O east longitude. Orbital parameters: 35,839 x 35,750 km (22,269 x 22,214 sm), inclination O.lO, period 1,437 minutes. (S) TECHNOLOGY DEVELOPMENT (continued)

J APAN/BSE

Mission Launch Launch lJASA Sitel Name DateITime Vehicl e -Code Pad Remarks/Results JapanIBSE 7 Apr 78 Del ta B SE E TR The Japanese Medi um-Scale Broadcasting Satell ite 1701 EST 2914 178 for Experimental Purposes (BSE) was designed to (Del ta-140) develop the higher K-band frequencies not in commercial use. Its three K-band channels received at 14 GHz and retransmitted at 12 GHz. BSE conducted experiments in relaying color television signals on K-band directly to home receiving sets in Japan. Owned and operated by Japan's National Space Development Agency, BSE was stationed in a geosynchronous orbit at 110" east longitude. Orbit measures 35,788 x 35,774 km :22,238 x 22,229 sm), incl ination O.lO, period 1,436 minutes. (S) L. crrh 0 nu L '4-3 0-x v (II '*aJ S w W.r-.ram <.r Q 2, ",,9",3 crr IF-ONd ,,n1:.r n cnc, -v aJ .r v) 0 -0-C dlE.r a~n uat L .E~L*= Urn0 aJC)ln a E L Pv-b ==cocnlO " 'UDOLC -0 7 E .r .r w,'p"Z? aJ aJ.P u +J L wv+-'xr( " atm F- 5- a0 c aJ 380 -(UC+J(II .r C) 0 UO MC) (II mm (II V) C V) L or. aJdC3.rC %Z2SN ..z 'l- (IIC u L a= v L.?- L 0re.r (II Cr) ~J~UL+J 0 C V)h OUU r-am. U 'l-CWC, V) I- 0 aJe aJh aJ +<>a Em* mv, 3LW-43 LEOWaJL *C 'l-Od aJ > aN*r LUrtD 0 CTN E

I u a am-P ->-P If- a aJ VI 0 a=-- OPERATIONAL SYSTEMS (continued)

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Resul ts Intelsat I1 27 Sep 67 Delta F-4 ET.9 Fifth comercial comunications satel 1 ite. 2045 EST D SV- 3E 178 Launched by NASA for COMSAT to supplement and (Del ta-52) back-up Intelsat I1 F-2. Still Sn near. geostationary orbit over Pacific at about 176" east longitude. Orbital parameters are: 35,783 x 35,740 km (22,224 x 22,208 sm), inclination 2.5", period 1,435 minutes. (S)

Intelsat 111 18 Sep 68 Del ta -A E TR First oi several spacecraft planned to improve 2009 EDT DSV- 3M 17A global comnunication network. Intel sat I1 15 were (Del ta-59) designed to more than double telecommunication service to all areas of the world via active sate11 ite. Liftoff was normal, but at 102 seconds into the flight a malfunctior? developed in the pitch rate system in the first stage autopilot. The space vehicle was destroyed by the Range Safe- ty Officer 108 seconds into the flight. The trou- ble was diagnosed ds a,. intermittent electrical signal in the autopilot system. This was the first of the long tank Delta configuration to be launched from the ETR. (U) OPERATIONAL SYSTEMS (continued)

Mission Launch Launch NASA Site/ Fiame Date/Time Vehicle -Code -Pad Remarks/Resul ts

Intelsat I11 18 Dec 68 Delta F-2 ETR Successfully launched for COMSAT Corporation into 1932 EST DSV-XI 17A a temporary el 1 iptical orbit with an apogee of (Del ta-63) 36,725 krn (22,820 sm) and perigee of 262 km (163 sm), at an inclination to the equator of 30". Its apogee kick motor was fired on 20 December and maneuvered it into a synchronous orbit over the Atlantic equator, at 31' west longitude and an altitude of 35,727 km (22,200 smj. All systems functioned normally. The second of the Intelsat 111 series (the first to be successfully orbited!, the 287-kg (632-1 b) cyl indrical spacecraft had the capability of handling 1,200 twc-wqy voice chan-

nel s or four television channel 5 a Began commercial use on Christmas Eve witti scenes of Pope Pa21 VI celebrating midnight mass in Italy. Relayed comnercial TV coverage of the Apollo 8 mission. Still in orbit--35,823 x 35,775 km (22,259 x 22,230 sm), inclination 1.4", period 1,437 minutes. IS') 1 I Intelsat 111 5 Feb 69 Del :a F-3 Successfully launched for COMSAT Corporation into 1939 EST DSV-31 an elliptical orbit, with an apogee of 36,104 km I (Delta -66) (22,434 sm), a perigee of 266 km (165 sm), incl ;- I nation of 2g0, and a period of 538 minutes. The kick motor was later fired to place the spacecrdft in a near-synchronous orbit over the Pacific Ocean. The second Intelsat I1I to be successfully orbited, the 291-kg (642-1 b) spacecraft had the capabil ity of hand1 ing 1,200 two-way voice circuits, or television, teletype, facsimile, and di- gital transmission. Repositioned over Indian Ocean at 62.5" east longitude and began service there on 1 July 1969. Current orbital parameters are: 35,804 x 35,768 km (22,248 x 22,225 sm), inclination 6", period 1,436 minutes. (S) OPERATIONAL SYSTEMS (continued) 1. I Mission Launch Launch NASA Site/ Name Date/Ti me Vehicle -Code -Pad Rernarks/Resul ts Intelsat 21 May 69 Delta F-4 ETR Successfully launched for COMSAT Corporation into I i II I 2200 EST DSV- 3M 17A an elliptical orbit, with an apogee of 36,896 km (Del ta-68) (22,926 sm), a perigee of 280 km (174 sm), inclination of 29", and a period of 656 minutes. The kick motor was fired on 23 May and placed the spacecraft in a near-synchronous orbit over the Pacific Ocean. After it was on station the F-3 satellite was moved until it assumed a new position over the Indian Ocean. This spacecraft had the capability of handling 1,200 two-way voice circuits, or television, teletype, facsimiis, and dig?tal transmission. Sti11 in orbit--35,794 x 35,791 km (22,241 x 22,239 sm), incl ination l.ZO, period 1,436 minutes. (S)

Intelsat 25 3ul 69 Delta F-5 ETR This was the fifth Intslsat spacecraft launched 111-E 2206 EDT DSV-3M 1 7A for the COMSAT Corporation. Vehicle performance (Del ta-71) was normal during the burn of the first two stages. Nc data was acquired during the third stage burn because the spacecraft was not radiat- ing and the third stage was not instrumented. The spacecraft war temporarily lost to ground stations, and when found, both the third stage and spacecraft were in unplanned low orbits. Still in orbit--3,508 x 267 km (2,180 x 166'sm), incl ination 30*3", period 128 minutes. (U) OPERATIONAL SYSTEMS (continued)

Mission Launch Launch NASA Site/ ::am DatejTime Vehicle Code -Pad Remarks/Resul ts Intelsat 14 Jan 70 Delta F-6 ETR This was the sixth Intel sat II1 1 3unched for the 111 1916 EST DSV-3M 17A COMSAT Corporation. Vehicle performance was nor- (Del ta-75) mal and tke spacecraft was injected into a temporary orbit, with an appgee of 35,872 krn (22,290 sm), a perigee of 290 kn~i180 sm), incl ination of 28", and a period of 634 ~ninlites. The 293-kg (647-1b) spacecraft was placed in a near-synchronous orbit by a burn of its apogee kick motor on 16 Januari 1970, and besan operating. Similar in capabil lty to all preceding Intelsat I11 spacecraft, this was the first launch insured against failure by a comnercial company. Sti11 in orbit--35,793 x 35,787 km (22,241 x 22,237 srn) , incl ination 0.2", period 1,436 minutes. (S)

Intelsat 22 Apr 70 Delta F-7 ETR This was the seventh In:fl sat I11 1 aunched for the 111 1946 EST DSV- 3M 17A COMSAT Corporation. The 2%-kg (647-lb) space- (Del ta-78) craft was placed in a sli,ht ty low temporary orbit, with an apogee of ?1,939 km (19,646 sm), a perigee of 260 krn (162 se!, and an incl ination of 27". The on-board positlwning motor was used to increase the apogee and ;Align the spacecraft for firing of the apogee motor. It was fired on 24 April, and placed the spacecraft in a near-synchronous orbit, which :.as further improved by the positioning motor. The spacecraft was simil ar in capabil ity to previous Intel sats. Sti11 in orbit; current elerlrents not inai ntained. (S) OPERATIONAL SYSTEMS (continued)

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Resul ts Intelsat 23 Jul 70 Delta F-8 ETR This was the last of the series I11 Intelsats to I11 1923 EDT DSV- 3M 17A be launched for the COMSAT Corporation. The (Del ta-79) 293-kg (647-1b) .pacecraft had the same capabilities as previous ones in the 111 series. The vehicle placed the spacecraft in an orbit with an apogee of 30,260 km (22,531 sm), a perigee of 261 km (162 sm), at an incl ination of 28'. The apogee motor was fired on 24 July, to position the satellite in a near-synchronous orbit, and contact wirh the spacecraft was lost after the motor had burned for 14.5 seconds of a programed 2? seconds. All spacecraft systems were working well up until the time the signal was lost. Still in orbit; current elements not maintained. (S) OPERATIONAL SYSTEMS (continued)

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Results Intelsat IV 25 Jan 71 At1 as/ ETR AC-25 was the first flight of an uprated Atlas F -2 1936 EST Centaur 36A SLV-3C first stage with an increased liftoff (AC-25) thrust cf 1,794,248 newtons (403,383 lb) and a longer burning time. After three earlier launch attempts (on 22, 23 and 24 Jan) were scrubbed due to upper level winds being unacceptable in shear, a fourth launch &tempt was initiated on 25 Jan. During the countdown a rsnge sequencer problem caused countdown clocks to become erratic and ren- dered Cape radar useless for Range Safety Comnand tracking. Evaluation of the problem and the decision to use Centaur telemetry to satisfy Range Safety requirements caused a planned 10-minute hold at T-5 minutes to be extended an additional 35 minutes; countdown then proceeded to 1iftoff. Intelsat IV F-2, first of a new ser?es, was the largest com~ercialcommunications satel 1 ite ever launcited both in weigkt--1,387 kg (3,058 1b)--and in communications capabil ity (ova- four times the capacity of the Intelsat II I series). Successful ly inserted into elliptical transfer orbit; later positioned in synchronous orbit of 36,410 x 35,940 km (22,625 x 22,108 sm) over Atlantic at 25.5' west 1ongitude. Current orbital parameters are : 35,797 x 35,777 km (22,243 x 22,231 sm), inclination 2.1°, ?eriod 1,436 minutes. (S) OPERATIONAL SYSTEMS (continued)

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Resul ts Intelsat IV 19 Dec 71 At 1as/ F- 3 ETR First launch attempt failed on 18 Jan, due to sur- F- 3 2010 EST Centaur 3 6A face winds exceeding launch 1 imitations. During (AC-26) 19 Jan countdown, a problem with the Atlas LOX tank pressure red1i ne val ues, apparently caused by faulty ground instrumentation, caused unplanned holds and required count to be recycled twice to T-5 minutes. Liftoff occurred at the opening of the second launch window. Spacecraft was placed into a highly el 1ipt ical synchronous transfer arbit, successfully compl et ing NASA mission objectives. COMSAT later fired apogee kick motor to position spacecraft in synchronous orbit over Atlantic at 29.5' west longitude. The spacecraft was identical to the high-capacity Intelsat IV F-2 which preceded it in Jan 71. Still in orbit-- 35,797 x 35,779 km (22,248 x 22,232 sm), inclination 0.3", period 1,436 minutes. (S) OPERATIONAL SYSTEMS (continued)

Mission Launch tau nci~ NASA Site/ --h '~e Date/Time Vehicle -Code -Pad Remarks/Resul ts fntelsat IV 22 ;an 72 At1 as/ F-4 ETR Launch was rescheduled from 19 to 22 Jan to allow F -4 1912 'ST Centax 368 COMSAT to e51aluate the RF systems aboard Intelsst (AC-28) IV F-2 to determf ne if a generic problem existed, Count proceeded until planned hold at T-10 minutes when it became necessary to reconfirm upper level wind shear data. Ahso, surface wind gusts began to exceed allowable launch parameters and lightning was forecast for the area at T-0. After 11- minute hold, count was picked up and proceeded until LOX tanking securing, when surface wind gusts again approached redlines. It w?s decided that time to lmnch was much shorter t .an time neces- 53ry to d2tank and count was continued to liftoff. ' .lasecraft placed into desired ?ighly el :i p- tical :r ansfer orbit. COMSAT 1 ate~.sutcessful ly fired apogee motor to maneuver satellite into synchronous orbit on station over Pacific ~t 174" east longitude. Still in orbit--35,53u x 35,776 km (22,245 x 22,226 srn), inclination 0.3", yri~c! 1,436 minutes. (S)

Inteasat IV 13 Jun 7: At: as/ E TR Terminal countdown comnenced on time am? proceeded F-9 i753 EDT Centaur 36 8 without incidcnt to a liftoff at the qening ,tf (AC-29) the launch window. Spacecraft was placed intc *;? elliptical 42,281 x 6,918 km (26,273 x 4,298 si-1 transfer orbit, successfully con,, ? eti ng NASfi. E:s-- sion objective. COMSAT fired the kick mator a5 the spacecraft reached its th~rdapogee, to pizce the sate1 1ite into geosynchronous orbit over the Indian Ocean at 6Z0 east longitude. Still in orhit at 35,736 x 35,731 km (22,243 x 22,233 sm), inclination O.OO, period 1,436 minutes. (5) OPERATIONAL SYSTEMS (continued)

Mission Launch Launch NASA Site/ Name Date/Time --- Vehicle Code -Pad Remarks/Resul ts Intelsat IV 23 Aug 73 At1 as/ F- 7 ETR Count down began on schedule and proceeded normal 1y F-7 1757 EDT Centaur 3SA until tower removal, which was delayed due to an (AC-31) anticipated thunderstorm in the launch area. Count was picked up when the thunderstorm Fd i led to appear and contitiued to liftoff. All flight events occurred as expected and the 1,406-kg (3,100-lb) spacecraft was injected into a 42,334 x 6,928 km (26,308 x 4,304 sm) transfer orbit, cchieving the NASA mission objective. Spacecraft's apogee kick motor was fired by LOMSAT Corp. on 25 Pugust and geosynchronous orbit wzs achieved. Satellite is positioned over Atlantic at 30" west longitude. Still in orbit--35,794 x 35,779 km (22,241 x 22,232 sm), inclination O.OO, period 1,436 minutes. (S) I Intelsat IV 21 Nov 74 Atlas/ F-8 Intended as a backup and replacement unit in the I F-8 1844 EST Centaur existing television, telephone and data transmission satellite system, Intelsat IV was launched without significant problems or delays, achieved initial orbit and was transferred to its final orbit of 35,802 x 35,772 km (22,246 x 22,228 sm) over the Pacific Ocean. Current orbit is 35,804 x 35,775 km (22,248 x 22,228 sm, inclination O.OO, period 1,436 minutes. (5)

Inte!sat IV 20 Feb 75 At 'as/ i-6 ETR Intended to provide an expansion of the in-orbit F-6 1835 EST Centaur 3 6A capacity of the Intelsat comunications sate1 1 ite (AC-33) system, the spacecraft and Cent-ur stage were de- stroy?d by the Range Safety Officer 414 seconds after launch. Fl ight was uneventful unti 1 booster staging, when failure of an Atlas booster staging connector to disconnect set off a series of problems sausing the vehicle to go effectively out of control. The Centaur second- stage ignition and burn were as planned, but failed to achieve planned velocity and course. (U) OPERATIONAL SYSTEMS (continued)

Mission Lairnc h Launch 14ASA Site/ --Name Date/Ti ine Vehicle Code --Pad Rernarks/Resul t.s Intzlsat IV 22 May 75 At 1as/ F- 1 ETR The last of the Intelsat IV series, and originally F- 1 1804 EDT Centaur 3 6A intended as a ground spare, the spacecraft was (AC-35) launched after the failure of AC-33 with the Intelsat IV (F-6). The telecomnunications satel- 1 ite was orbited as backup to the six Intelsat5 in service. A second burn of the Centaur stage placed the spacecraft in a hi ghly el 1 iptical transfer orbit. Firing of the kick motor Injected the satellite into near-geosynchronous orbit of 35,796 x 35,778 km (22,243 x 22,231 sin' 87 of 30 Apri 1 1975. Current orbit is 35,798 x ?' '76 krn (22,244 x 22,230 sm), inclinatic;~O.Oq, arra period of 1,436 minutes. (S)

Intrl?sat E TR This was the first Intelsat IV-A, desiyned to in- 1'1-A 36 6 crease the capacity of the orbitins co munications .i -11 satellite network, whieh was fast becuming satu- rated. Seven meters (23 feet) tall and weighing 792 kg (1,745 lb) afttr burnout of the apogee motor, it was the largest cofimunications spacecraft ever built, with nearly double the capacity of an Intel sat IV. The satellite was injecd.ed into an elliptical transfer orbit, after which its ,3pogee rnotor was fired to transfer it into a near-synchroi-:3us orbit. It then drifted to its assigned station of 25" west longitude. Its current orbit is 35,801 x 35,775 krn (22,246 x 22,230 srn), inclination O.lO, period 1,436 i:iinutes. (S)

Intelsat 29 Jan 75 At 1as/ E TR Second in the series of second generation Intel sat IY-11 1856 EST Centaur 36 8 connercial comnunications sate1 1 it:es, the space- F-2 (AC-3") craft dds launched inib orbit, then moved to final position at 330.5" esst longitude on 8 April, add- ing 2Q television chznnels or 6,030 two-way telephone circuits t3 the system. Orbit .neasures 35,195 x 35,176 km (22,244 x 22,230 sm), incl ination O.lO, period 1,436 minutes. (S) m w- r cum 0 YO o H T -maLn LLgJh"C aJ 3ln 0 z~P3.r C, 'C C, cnu 5 cnr m r C 0 '--UP '- v ?V) L- .--a0 a m aJ c- ro w E a0 V) ZW .m- c, owt+')m .rm C).rn NhV eu LN OaJ ON P > V) OCXaJ C,Enr C, V) N 7 aJe c d L Nr.rg a o o acu mumcuw 10 -m rCa~Ea maV)Ycc L 5 4 u ;k! aJoO 0 a U >h.r a*': arL U PaJLn a 0 V) Inm Q OPERATIONAL SYSTEMS (continued)

Launch Launch NASA Site/ Date/Time Vehicle Code -Pad 13 Apr 74 Delta Westar-A E TR Owned and operated in orbit by Yestern Union, 1933 EDT DSV-3P-116 178 Westar 1 became the first satellite for domestic (Del ta-101) communications in the United States. It achieved geosynchronous orbit, despite one of the nine sol id rocket boosters fail ing to separate from the first stage when ejectcd. The second stage burned 23.7 seconds longer to compensate for the extra weight of the burned-out booster she1 1 , and the third stage injected the spacecraft into its planned orbit. Westar 1 had 12 channels for commercial operation. Each relayed a mixture of vari- ous types of comnunications, which could total either over 1000 one-way mice circliits, or one color TV program, or up to 60 rnillio~bits of data per second. Westar 1 we~zhed572 kg (i,265 Ib) fully fueled prior to launch. (5)

It) Oct 73 Del ta Mestar-B E TR Westar 2 became the second of Western 3nion': 1853 EDT DSV-3P-118 178 spacecraft in a domestic U.S. comunicdt~onssys- (Gel ta-103) tem. A haman error in a computer caused the launch vehicle to deviate from its predicted pzth, but the 572-kg (1,265-1 h) spacecraft was placed into its proper geosynchronous orbit. (S) OPERATIONAL SYSTEMS (continued)

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code --Pad Remar ..;/Resul ts I 'rlestar 3 9 Aug 79 Del ta Westar-C ETR Built at the same time as Westars 1 and 2, Westar 2020 EDT 2914 17A 3 began its career as an on-the-ground spare. But (Del ta-149) when Western Union needed to expand its system capacity, Yestar 3 was sent to orbital duty. It was placed in a stationary orbit 35,807 km (22,250 sin) zbove the equator south of New Orleans. (S) OPERATIONAL SYSTEMS (continued) --RCA SATCOM Mission tau nch Launch NASA Site/ Name Date/T i me Vehicle -Code -Pad -Remarks/Resul ts ITCUM I 12 Dec 75 Delta SATCOM-A ETR This satellite's launch marked the first flight of 2056 tST DSV-3P-11C 17A the Model 3914 Delta vehicle, a more powerful ver- (Del ta-118) sion financed by RCA in contract with McDonnell Doug1 as Astronautics Co. Countdown was stopped at T-7 minutes and held for nine minutes, 12 seconds for a catamaran sailboat to move out of the launch danger area. Launch was successful and the 86349 (1,915-1 b) satel 1 ite achieved geosynchronous orbit--35,789 x 35,782 km (22,239 x 22,234 sm) at a 0.0' incl ination (over the equator) with a 24-hour perioa. Current orbit is 35,793 x 35,779 krn (22,241 x 22,232 sm), inclination O.OO, period 1,436 minutes. (5)

~~~TULJM2 26 %r 76 Liel ta SATCOM-B ETR Originally scheduled for 25 March, launch was 1747 EST DSV -3P - i lC 17A slipped to permit changeout of the spacecraft yaw (Del ta-171) gyro which had exhibited an erratic drift rdte. All launch vehicle and spacecraft systems performed as expected, and the RCA sate1 1 ite, designed to provide comnercial comnunications capabilities to the 50 states, was bcosted to transfer orbit, then moved to synchronous equatorial Earth orbit. Current orbit is 35,797 x 35,784 km (22,243 x 22,235 sm), inclination O.OO, period 1,436 minutes. (S) OPERATIONAL SYSTEMS (continued)

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Resul ts

SFiTCOM 3 6 Dec 79 Delta SATCOM-C ETR Planned as the third spacecraft in RCA's satellite 2035 EST 3914 1?A system for comnercial comunications, SATCOM 3 was (Del ta-150) 1ost whi 1e RCA spacecraft contro?'~rs were changing its orbit. The Delta vehicle placed the 907-kg (one-ton) spacecraft into a transfer orbit with an apogee 35,808 km (22,300 sm) above the equator. RCA controllers lost contact with SATCOM 3 during firing of its apogee kick motor to achieve geosynchronous orbit. Neither RCA nor the North American Air Defense Comand were able to locate the missing satellite. (P) OPERATIONAL SYSTEMS (continued)

/ U .S. FMRITIME COWNICATIONS SATELLITE (MARISAQ I i I hission Launch Launch NASA Site/ !i arne Date/Time Vehicle -Code -Pad

Eari sat 1 19 Feb 76 Delta Mari sat-A ETK This launch placed the first U .S. Maritime Communi 1732 EST DSV -3P - 11B 178 cations Satell ite in geosynchronous orbit over the (Del ta-120) Atlantic at 15O west longitude. The initial transfer orbit was circularized at 35,900 km (22,300 sm) when ihe on-board kick motor was fired on seventh apogee. Current orbital parameters are: 35,809 x 35,764 km (22,251 x 22,223 sm), in- c7 ination 0.7', period 1,435 minutes. (S)

,4.3r.i s;: 2 9 Jun 76 Gel ta Marisdt-B ETR Following a hold that lasted thrcggh the first 2009 EDT 2914 17A launch window, to allow evaluation of lightning (Del t a-124) hazards, the second maritime comiunicati ons satel - iite was launched into transfer orbit during the second window and, subsequently, was ?laced in geosync?ronous orbit at 176.5" east ioncjicude, over the Pacific basin, providing liitra-high frequency co~nniunications for the U .S. Navy, comner- cia1 shipping and offshore facilities in the Pacific. Current orbit measures: 35,815 x 35,759 km (22,254 x 22,220 sm), inclination 1.6O, period 1,436 minutes. (S)

tkri sdt 3 14 Oct 75 Delta Karisat-C ETR Originally designated as a ground spare, the 1844 EDT 2914 17A spacecraft was launched to provide UHF maritime (Del ta-127 ) cornrnunications in the Indian Ocean, and to serve I as a spare in orbit in the event of failure of Marisat 1 or 2. The spacecraft was placed in geosynchronous orbit of 35,793 km (22,240 sm) at approximately 73O east longitude. Current orbit is: 35,798 x 35,771 kin (22,244 x 22,227 sm), in- ! clination O.lO, period 1,436 minutes. (S) OPERATIONAL SYSTEMS (cont inued)

U.S. FLEET SATELLITE COMMUNICATIONS SPACECRAFT (FLTSATCOM)

/.ti ssion Launch Launch NASA Site/ Name Date/Time --Vehicle Code - Pad Remarks/Resul ts FLTsATC~1 9 Feb 78 At 1as/ FLTSATCOM- ETR First in a series of military satellites designed 1617 EST Centaur A 3 6A to provide world-wide comnunications for the U.S. (AC-44) Navy, Air Force and Department of Defense (incl ud- ing the Presidential Comnand Network), the spacecraft was launched despite a hydraulics leak in the Atlas engine system. The 1,864-kg (4,132-1b) spacecraft was successful 1y placed in geosynchronous orbit, which now measures 35,816 x 35,756 km (22,255 x 22,218 sm) with a 9.7" inclination, and a 1,436-minute period. (S)

FLTSATCOM 2 4 May 79 Atlas/ FLTSATCOM- ETR Second in the series of military satellites link- 1456 EDT Centaur B 36A ing the Comnand Network with the Strategic Air (AC-47) Comnand, the spacecraft did not 1 ift off until the second day of launch opportunity, due to a possible short-circuit in the apogee motor system. With a p:anned life of five or more years, the satellite took its station in geosynchronous orbit. (S) OPERATIONAL SYSTEMS (continued)

Mission Launch Launch NASA Site/ P4 am e Date/Time Vehicle Code Pad

At 1as/ COMSTAR D-1 ETR First of three domestic comnunications satel 1ites Centaur 36A designed for lease to American Telephone and Tele- (AC-38) graph Corporation, the spacecraft was launched after two holds due to adverse weather and a hish LOX temperature reading. Placed in geosynchronous orbit, on a trajectory identical to Intelsat IV-A, the spacecraft provided 24 simu1 taneous color television channels or 14,000 two-way telephone c~nversations. Current orbital status is: 35,794 x 35,783 km (22,241 x 22,234 sm). inclination O.OO, period 1,436 minutes. (S)

22 Jul '5 Ati as! COMYTAR D-2 ETR Boosted by an Atlas StV-3D, with G Centaur D-lAR, 1804 EP; Centaur 36B the Hughes Aircraft-bui 1t spacecra rL, ,rei ghing 'AC-40) 1,513 kg (3,347 lb) at launch, was Inft.-4 into transfer orbit, moved into near-geosynchronous orbit, and drifted to its station at 95' west longitude. %bit is now 35,800 x 35,776 kin :L2,245 A 22,230 sm), inclination O.OO, period 1,43b inutes. (S)

,-jt; 5 s/ COTISTAR U-3 ETR Launched as 3n in-orbit backup to COMhTAR 0-i zt Centaur 36 B 128" west longitude and COMSTAR D-2 at 119" west !AC-41) longitude, D-3 was positioned at 131.8" ~est longitude, so that no more than one of the three would be in Earth's shadow or crossing the face of the Sun at once. Intended primarily for long-distance telephone service, the COMSTAR sateiiites weigh 811 kg (1,440 lb) in orbit. Orbit is 35,800 x 35,778 km (22,245 x 22,231 sm), incl inat ion 0.O0, period 1,436 minutes. (S) OPERATIONAL SYSTEMS (cont inued)

SKYNET

Mission Launch Launch NASA Site/ Name Date/Ti me Vehicle -Code -Pad Remarks/Results Skynet 1 21 Nov 69 Delta Skynet-A ETR This spacecraft, the first United Kingdom comnuni- 1937 EST DSV-XI 17A cations sate1 1ite, was successfully launched into (Del ta-74) a highly elliptical transfer orbit as planned. This launch was conducted by NASA for the U.S. Air Force, acting as agent for the United Kingdom. The apogee motor was fired on the fifth orbit by U. S. Air Force ground controllers, and placed the spacecraft in a near-synchronous orbit, with an apogee of 33,688 km (22,797 sm) , perigee of 34,702 km (21,563 sm), and inclination of 26". The spacecraft was then turned over to the United Kingdan for operation. Still in orbit, but current elements are not maintained. (S) Skynet 2 19 Aug 70 Delta SKynet-B ETR This second comnunications satellite of the two 0811 EDT DSV-3M 17A launched for the United Kingdom, with the U.S. Air (Del ta-80) Force acting as agent, was successfully injected into a highly elliptical transfer orbit, with an apogee of 37,441 km (23,265 sm) and a perigee cf 266 km (165 sm). The apogee motor was fired on the seventh orbit by U.S. Air Force ground controllers, to place the satellite in synchronous orbit. A1 1 comuni cat ions with the spacecraft, both tracking and telemetry, were lost halfway through the apogee motor burn. Still in orbit, but current elements are not maintained. (S) .c aJLL I C, c<-r Q- I +'rn+' .r c a =a '4-4.- 0 Q) .r d r4 E Lr- ln aJNW X aJ2 r UG WO+-'NrnN0 w'4- E (V ,--I*- 9mhOCu *=+' F L 0 '.. am aJH.EC EEV)C C,u mUQY V)W-r v- .r C aJ !-+'-A= hLN* :CU V)~~orWGC -aJ c a O+P.N-FV- ",3Elll24-E *me amso=-- *-Q-m '4- clll C aJaJ0E.r OCC,CC y On 0 .raJ .-my) +' mcnQ,cr,-Nv 5@U c0cO.r m UIUaJOaJOhc,Cy .r L LC, c L CW ammcncu~ 3au.r~m xu E O'Z* ZQ-o'cr,C: OlhC'V-n OOIInC U- an 1 C *N.r ELLC.r aJ4 mE ?~poOaaJC, tnCCcu~, (V a mln#-- aJC,.r 0-C3 t'CLmrmL .r.c a,.,-,- a, r E% +'oao~d 'r p -r .r ETIOC aeY,v aJLSr+'+' ah0 V) C, C, 're?.I C h .r .r .r Ct- an--r m L rCOaLLE,-*cu I-~UUOOW~~~ aJ E cut- ="- hv, Ek > W 3aJ 0- ac, Zd cFI 0 n 0I-J 4 OPERATIONAL SYSTEMS (continued) iilission Launch Launch NASA Site/ Name Date/Time Vehicle Code Pad Rernarks/Resul ts

Anik A F-2 20 Apr 73 Delta Tel esat-5 ETK Second 1aunch on a reimbursable basis for Tel esat , (Telesat 2) 1847 EST DSV-3P 178 Canada, of a dornest ic cornmunications sate11 ite. (Del ta-94) First countdown on 19 Apr was scrubbed, after a 29-minute hold at T-7 minutes, to allow for inspection of the vehicle for a missing piece of holding tape for a spacecraft connector dust cover. Second terminal count on 20 Apr proceeded to b3ilt-in hold at T-7 minutes, despite operational problems requiring personnel to be dis- patched to pad area during cnunt. Built-in hold was extended to permit a1 i3;lirlent of countdown iterns with countdown clock, the:) extended further to permit shower to clear the launch area. Count- down then proceeded to 1 iftoff. 566-kg (1,247-1 b) spacecraft was injected into a transfer orbit of 36,480 x 212 km (22,653 x 12sslii). On 23 Apt- apogee motor was fired to place ;;!acecraft in synchronous orbit at 109' west longitude. Sztel- 1 ite expands Canadian television, radio, and tale- phone coverage initiated by Ani k I. Curre~t orbital parameters: 35,790 x 35,754 kin (22,239 x 22,235 sm), inclination O.lO, ~eriod1,436 minutes. (S) WERATIONAL SYSTEMS (continued)

Mission Launch Launch NASA Site/ Name Date/Tirne Vehicle -Code -Pad Rernarks/Resul ts Anik AF-3 7May75 Delta Tel esat-C ETR During launch of this domestic communications (Telesat 3) ,1935 EDT DSV-3P-11B 17B satellite, identical with AJk 1 and 2, two holds (Oel ta-110) (totaling 6 minutes, 24 seconds) were necessary due to the presence first of bcats, then an aircraft low on fuel in the launch danger area. Placed initially in a highly elliptical geosynchronous transfer orbit, the spacecraft was injected into a near-geosynchronous orbit, with 35,795 km (22,243 sm) apogee and perigee of 35,778 km (22,231 sm) when Telesat controllers in Canada fired the on-board engine on the seventh apogee. The spacecraft entered comnercial service as part of Canada's telecommunications network. Current orbital status is 35,794 x 35,781 km (22,241 x 22,233 sm), inclination O.OO, period 1,436 minutes. (S)

Anik B 15 Eec 78 Delta Tel esat -D ETR A hybrid satellite designed for interspal use with- (Telesat 4) 1921 EST 3914 17A in Canada, Anik B differs substantially frorn its three predecessors. It offers 12 channels in the 614 GHz range, and two channel s, with two backups, in the 14/12 GHz range. The lower frequencies are to supplement the existing network and/or rep1 ace older Aniks, the higher are to perfonn pilct projects for later 14/12 GHz satellites. Anik B is three-axis stabilized, unlike the spin-stabilized Anik 1 satellites, and mch heavier at 922 kg (2,032 lb). This payload weight required the use of the 3914 Delta vehicle. Current orbital status is 35,794 x 35,782 km (22,241 x 22,234 sm), inclination O.OO, period 1,435 minutes. (S) I c WO w wl r +.J C 1 WSr W OaJLW EPUL '-UWL aJ-CL + .rfUC,Q)QJ mar-'4- my) v oam c*ro 'P Uv,v-V)v,m+ C Q'rrO .I- 3 =rc,~arc,a~cn I-n. WbUL E *rL.rmLO 0 F-0,-LO%+ O .cUc VLLSr.r OaJOaJaJ f-n mt- EwvLmLn a? w XWwwu C 4-I 'r +t 0 mm . aJ rv) ro U+.JO,-c,rr2 C, +ttaa.~c,v)c 02.1-a m 0 L *c, 6.L 4J--0 aJ+J on m 0 E V) wc .r L a,++aJvlc,*c,,J 'rDU aJ23+aO '4- aJucno0.r-LC 0'T)C 0 C F w wwtrC( cL0u.r- aa, I: 'r WLWWOL +V) n C-YrU m aJ mC,c w UU- C V)W W.-4 C(U .r y) la-? 30+3r- +J 5- L.rV)WovE: ?-@Ole I Law v) a)+ La+ V E ?+5LW5LC5W r fu L wcw a, OFF- +- m u%+)t 30 aa,

. - .P GI- c \ =w mu -J ro C3 OPERATIONAL SYSTEMS (continued)

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Resul ts- NAiOIII-A 22Apr76 Del ta NATO 111-A ETR Using 9 strap-on Castor I1 sol id-propel 1ant boost- 1546 EST 2914 17B er motors, the Delta vehicle boosted the 701-kg (Del ta-122) (1,543- 1b) sate1 1 ite into transfer orbit , where the on-board kick motor placed it in near-synchrc- ncus Earth orbit over the equator. First in a new SF:-ies for NATO, the satellite was designed to replace HATO XI sat\?lites, to improve free world mili tary comnunications. Current orbit measures 35,794 x 35,781 km (22,241 x 22,233 sm) , r ncl ination 1.4", period 1,436 minutes. (S)

NATO 111-B 27 Jan 77 Del ta NATO I1I-B ETR Lifting off in the opening of the launch window, 1950 EST 2914 17A the Delta vehicle placed the spacecraft in a high- (Del ta-128) ly elliptical transfer orbit that later was modified by firing the on-board kick motor into a near-Earth synchronous orbit of 35,798 x 35,775 km (22,244 x 22,230 sm). Orbit now measures 35,791 x 35,787 krn (22,239 x 22,237 sm), inclination 2.1°, period 1,436 minutes. (S)

NATO 111-C 18 NOV 78 Del ta NATO I1I-C ETR Last in the series of three improved military CWI- 1946 EST 2914 176 munications sate11 i tes for NATO, the sate1 1ite was (Del ta-146) boosted into transfer orbit, then moved into Earth-synchronous orbit over the equator. Current orbital parameters are: 35,793 x 35,486 km (22,239 x 22,050 s~n), inclination 4.Z0, 1,429 rninutes. (S 1 OPERATIONAL SYSTEMS (continued)

Launch Launch NASA Site/ --Date/Tine Vehicle -Code -Pad RemarkslResul ts 8 Jul 76 Del ta Pa1 apa-A E TR The first of two domestic communications satel- 1931 EOT 2914 17A lites launched to serve Indonesia's 3,000 islands (Del ta-125) and 120 millian people, Palapa 1 was launched into transfer orbit by the three-stage Delta vehicle, then was boosted into near-synchronous orbit. Drifted to its permanent position at 83' east longitude at an altitude of 35,785 km (22,231 sm), the satellite entered service on 17 Aug. Current orbit is: 35,834 x 35,732 km (22,266 x 22,202 sm) , inclination 6.2', period i,436 minutes. (S) i Pal apa 2 10 Mar 77 Eel ta Pal apa-B ETR Designed for expansion of remote site communica- i 1817 EST 2914 17A tions, the sate1 lite completed Indonesia's comnu- (Del ta-129) nications system when it was successfully launched and the spacecraft was placed in sy!~chronous Earth orbit at 77' east longitude. Current orbital status is: 35,799 x 35,781 km (22,244 x 22,233 sm) , inclination O.OO, period 1,436 minute:. (S) SPACE APPLICATION3 AND TECHNOLOGY

LAUNCH AND SPACE VEHICLE DEVELOPMENT

f4i ssion Launch Launch NASA Site/ :iame Date/Ti me Vehicle -Code -Pad Remarks/Resul ts Saturn 27 Oct 61 Saturn C-1 SA-1 ETR Successful initial flight test of first stage. 1006 EST 34 Take-off thrust achieved was 5,764,508 newtons (1,296,000 1b). Hurled two water-fil led, dumny upper stages, carried as ballast, to peak altitude of 136.5 km (84.8 sm) and distance of 345.5 km (214.7 sm) downrange. Reached maximum velocity of 5,804 kph (3,607 mph) before plunging into ocean 8 minutes after launch. (S)

Saturn 25 Apr 62 Saturn C-1 SA-2 ETR Like first Saturn, fired only first-stage engines, 0901 EST 34 generating 5.8 million newtons (1.3 million lb of thrust). Dummy upper stages filled with water were detonated at 104.6-km (65-sm) a1 titude (Proj- ect Highwater) and formed artificial cloud. All test objectives achieved. (S)

Sat urn 16 Nov 62 Saturn C-1 SA-3 ETR First stage only; coasted to 167.4-km (104-sm) al- 1245 EST 34 titude where it was destroyed to release 86,184 kilograms (95 tons) of water ballast into the atmosphere, forming a huge ice cloud (Project Highwater). All test objectives achieved. IS)

Saturn 28 Mar 63 Saturn I SA-4 E TR First stage only. One engine purposely shut off 1511 EST 34 after 100 seconds to determine "engine-out" capability. Last of four first stage tests. (Launch vehicle officially designated Saturn I, on 7 February 1963.) (S) v- kiJw O 'e5 - mr -DY ODW ? L a 0-mu ooa 0.- 04-P z u,W u 0 r CO m Lrcs- *hOOL rmo= OAC n Qu 3, wcnr ?&'LS * raoa aJO mL ULUL mrN.r 0 C 00 CrnUaJE 3 0.c 0 .r (d meCLaJ c,a~cn C U 13Y& aJ> m J, mcI- CL C *r V) " 32 .yl- CI) .%Boar7 ca, LC .C mmo a s 3 ?-I- u m Lr:V)*U reOL 0 a z,CZ w L TJOaJO LW>13 OW7.r > =Lee2 aJ X .r e.f-L L m Ot' aJf- aJ r *o > 2OZ C7 -- a m 3 u cr~as? e 3 .r C '- 9I.n 3 -6.4 cu 'C L aa V) CLA K L+-"-Z V)c,u.r bS'trnID V) C OOC 5 L 3maJ a*.- a CL V)C tnUOa3 r C '4- a.1 .r 3 O3EaJaJ V) *r aaJm aJnu 'f- 0 a,= w Q)Ccn+ =I- 3°E=:," C m a- t'rc 3 U L aJ 0'4-I- n -r Pu 01 m 3aJo UCO m 3 t'c >a 3 V)'r V) 6 I av CULre cn OW Oa v, a, m3- . m t'o K ar w w fun UO ow V) c uww m a aJm U U m .ca CaJZ L - *WaJ rc0'Jl1WA- HIE00 07-vr 41117 0 C I OaJL L- 5 a a L- u c ., ~~V-0manzv, LAUNCH AND SPACE VEHICLE DEVELOPMENT (Continued)

CENTAUR

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Results Centaur 8 May 62 At 1as/ F- 1 E TR Exploded 55 seconds after 1aunch, apparently due 1449 EST Centaur 36 A to a structural failure which resulted in a fuel LV-3c tank rupture. Vehicle destroyed before separa- (AC-1) tion. (U)

Centaur 27 Nov 63 Atlas/ AC-2 First successful launch of Centaur; first known 1403 EST Centaur ignition of 1iqui d hydrogen-fuel ed rocket engines LV-3c in spdce. Centaur did not carry an inst~umented (AC-2) payload on this space flight. Still in orbit-- 1,667 x 476 km (1,036 x 296 sm), inclination 30.4", period 107 minutes. (S)

Centaur 30 Jun 64 Atlas/ AC-3 Failure of engine actuator hydraulic system per- 0904 EST Centaur mitted Centaur to roll, forcing propellants to LV- 3C sides of tanks and uncovering feed-line outlets. ( AC-3) The two 66,720-newton (15,000-lb) thrust RL-10 engines shut down 127 seconds before programed burning time of 380 seconds elapsed. Fl iyht objectives which were attained included successful jettison of insulation panels and nose fairings, separation of the At1 as and Centaur stages, and demonstration of guidance system operations. AC-3 achieved maximum velocity 18,387 kph (11,425 mph) and an a1 titude of 555 km (345 sm). (P) 11 Dec 64 Atlas/ AC-4 Carried model of Surveyor spacecraft. A1 1 primary 0925 EST Centaur miss ion object ives met ; however, secondary test of LV-X second burn not accompl ished. Re-entered atmo- ( AC-4) sphere 12 December 1964. (S)

Centaur 2 Mar 65 Atlas/ AC-5 First attempt to place a Sgrveyor dynamic model 0825 EST Centaur into a simulated lunar transfer trajectory. I ! LV- 3c Seconds after liftoff the Atlas booster failed due ( AC-5) to the closing of a fuel-line valve. (U) .m.r L E: - 3 3 L At' L +o~m ma -3 C,ut'D- 2 3: Cm'r O) Q)>U aJ-9-OQ VLaJFi U3LCO U 3'- aJ 1 EOOE 7V) m+, V) .r U V) Lln mww3aJln ma Cmm- 3 -C, .a" .c fa 3 *C,L 4 WY- E- - > L m L 3 m am 3 CLC UW r.?m r L 0 3c C,c, a.r 0 CU m WLL LL2-G . aJ aJ mo aJw u muQI aJu.rC, >'TJt-Z>m E n C, aJ 3.7 wn.r L4 3 LE C,ma ma mom 3 WOLmaJ CLm L 3;" 2 ln30r> aJ 2l-y. 0 L w -30 V) EU30 30=-,car 0 WFZ au~o C, -7 L W VWW 0 Kl .r 2,.r lr\IFIOU am =ISrLUlO ln0.L aJx 4-' ulu WL3W - .r C, ummaJ W"-wW .J .aV) 5 L 2 2 m F cm: a, OL aJ U 'r CJ t' *'VC,r- a.J Qy W u C on(J cc,mu*r ?a 3= ZJG (6 3 ~JTL~JKI~or EQ Wach+ E mo La v) UC, 0-r ul VF.F m c a.r .r U wcng U Un 0-LD 2 ca c C .r L F -'tar .C, rer o mi3 r 3 wuc Q) 't.rvm ln .r m W mua'- >QV) w .rV)(PO occ= >u 42 aJ ult'u wsg%.mUWrnCaJaJ m-.r C aJ LC, ELL-r L rn0E.F L LaJ .r Q, OVU C,- w a4-, 3r ar Y- I 'r v).Q -0 nut' U~--OC, nErL 0-L l cac aJ aJ m aJ C C,mmoo .-am0 aJ > > CC, CJ lnc E E r7cEw1 0 OUI LO'? aJ aJ aJQ *a,? aJaJ3C,oaJ CdUQ >my= tee a+ t' *r,a-

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V'J-I LAUNCH AND SPACE VEHICLE DEVELOPMENT (Continued)

SPACE ELECTRIC ROCKET TEST (SERT)

Mission Launch Launch NASA Site/ Idarne Date/Time Vehicle Code -Pad Remarks/Resul ts SERT 2 3 Feb 70 Thor- SERT 2 W TR The 1,391-kg (3,067-1 b) Space Electric Rocket Test 2200 EST Agena-D SLC- 2E 2 (SERT 2) was successfully launched into a near- (1900 PST) (Thrust- circular Sun-synchronous twilight orbit. The pur- Augmented) pose was to verify ground test results of ion (Thor- propulsion systems, determine electric propul sion Agena-12) engine operating characteristics in space, and develop and veri fy ion thruster engi ne operational procedures. All systems were turned on and operated normally, but ion thruster stopped operating one month short of 6-month goal and was deemed unsuccessful. Sti11 in orbit--apogee 1,047 km (650 sm), perigee 1,039 km (646 sm), 99.1" inclination, 106-minute period. (S) LAUNCH AND SPACE VEHICLE DEVELOPMENT (Continued)

TITAN 111-CENTAUR

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Results Titan- 11 Feb 74 Titan-111-E TC-1 ETR This was the first launch of the Titan/Centaur Centaur 0848 EST Centaur D 41 vehicle, a new combination of the Air Force- Proof developed Ti tan 111-E vehicle and the Fl ight NASA-developed Centaur upper stage. Primary purpose of this launch was to fl ight test the new vehicle, but it also carried two payloads. The Viking Dynamic Simulator was designed to measure the launch and flight stresses the vehicle would place on Viking spacecraft (planned for two missions to Mars in 1975). The second payload was called the Space Pl asma High Voltage Interaction Experiment (SPHINX). Its objective was to investigate the effect of charged particles in space on high-vol tage systems. TC-1 's Centaur engines did not ignite in two attempts, because a pump failed to del iver liquid oxygen to the engines. The Range Safety Officer destructed the vehicle at T+750 seconds. (U) SPACE APPLICATIONS AND TECHNOLOGY--

APPLICATIONS TECHNOLOGY

APPLICATIONS TECHNOLOGY SATELLITE (ATS)

Mission Launch Launch NASA Site/ Name Date/Time Vehicl e --Code Pad Remarks/Resul ts ATS 1 6 Dec 66 Atlas- ATS-B E TR First sate1 1 ite in Appl ications Techno1 ogy Sate1- 2112 EST Agena 12 1i te Program. The 351.53-kg (775-1 b) sate1 1 ite SLV-3 was placed in circular, equatori a1 synchronous or- (At 1as- bit. Used for 15 separate experiments related to Agena-19) communications and meteor01ogy and control technology. Still in orbit; still transmitting. Orbital parameters are: 35,798 x 35,777 km (22,244 x 22,231 sin), inclination 9.6", period 1,436 minutes. (S)

ATS 2 5 Apr 67 At 1 as- ATS- (1 ETR Purpose of 370-kg (815-lb) satellite was to 2223 EST Agena 12 eval uate gravity-gradient system for spacecraft SLV-3 stabil ization. Entered el 1 iptical transfer orbit, (At1as- but failed to go into circular orbit when 2nd- Agena-21) stage Agena engine failed to re-ignite. Sonre eu- periments were carried out, but NASA ruled the satellite unsuccessful. Re-entered 2 September 1968. (P) APPLICATIONS TECHNOLOGY (Continued)

Mission Launch Launch NASA Site/ N2me Date/Time Vehicle -Code -Pad Remarks/Resul ts ATS 3 5 Nov 67 At1 as- ATS-C ETR Third in a series of Applications Technology 1837 EST Agena 12 Sate1 1 ites. Contained 14 appl ications techno1 ogy SLV-3 experiments concerned with comnunications , meteo- (At1as- rology, stabil ization and pointing technology, Agena-25) orbital technol ogy, and space environmental degra- dat ion. Launch vehicle injected 714.95-kg (1,574-1 b) spacecraft into highly el 1 iptical orbit. Then, at apogee of second orbit, apogee kick motor was fired on ground comand to transfer spacecraft into near-stat ionary equatori a1 orbit at approximately 35,700'km (22,200 sm) and about 47' west 1ongi tude. Transmitted excel 1ent qua1 ity high-resolution photos of entire visible disk of Earth. Still in orbit; still transmitting. Cur- rent orbit measures: 35,863 x 35,713 km (22,284 x 22,191 sm), inclination 8.1°, period 1,436 minutes. (S)

ATS 4 10 Aug 68 At1 as/ ATS-D ETR Liftoff was normal and within the desired launch 1833 EDT Centaur 36A window. The Centaur first burn injected the vehi- (AC-17) cle artd ATS-D into a parking orbit. However, the Centaur second ignition did not occur, and attempt; to separate the ATS-D from the Centaur were unsuccessful. Although the mission was a failure, the satellite attained orbit and was therefore designated ATS 4. Two cesium-propel 1ant ion engines, developing a total thrust of 20 micro-pounds and designed for satellite positioning and station-keeping, successfully performed five separate tests totaling 23 hours firing time. Satellite and Centaur stage re- entered the atmosphere on 17 October 1968. (P) APPL ICATIONS TECHNOLOGY (Continued)

Mission Launch Launch NASA Site/ Name --Da+,e/Time Vehicle -Code -Pad Remarks/Resul ts ATS 5 12 !lug 59 At 1as/ ATS- E ETR After rninor delays total 1 ing 7 minutes, success- 0701 EDT Centaur 3 6A fully 1aunched spacecraft into a nominal transfer (AC-18) orbit. Because of unexpected large spacecraft fuel expenditure to maintain a stable spin condition, apogee kick motor was fired at first apogee rather than second one as planned. Maneuver resul ted in a near-synchronous orbit with a westward drift of about 7O per day, but spacecraft began a fiat spin about its yaw axis rather than pre- scribed rotation about its roll axis. GSFC scientists waited until spacecraft drifted into lirie- of-sight with ATS ground stations in U.S. on 5 September, then comnanded ejection of spent apogee kick motor. Kick motor ejected but spin rate remained about 70-80 rpm, reducing usefulness of some primary experiments. Sti11 it1 orbit--35,791 x 35,783 km (22,239 x 22,234 sm), inclination 5.7O, period 1,436 minutes. (S) m V) A! 0 IT] I-* (Ow &* mil (UC, UULU V) L 00haJ 0 ,L .t- q) .r L 0 -3 0- L 3z P: maJ u> m rreC,aJ9) 3 C >C,'t- 0 *aJL .4 IUre t aJ 0.r U >V) Q aJ-u 1 .t- aJ 0 IA~LOCOC, C, (J'C,C, w .r u *r (O C, (O f ores L: QW re KG- aJ U Lmo C, L c 0 0 C, 3 aL aJC,moo .r Q) 'r uu mC, 't- C r st- V) mc aJ CC, 8% (O - amva C'aJ E4m- awl- ar- w L aJ u0aJm SIC C~JL T] C, w LC. av, LQ, R1 C, (O Cam C,m WaJ 0 LACm mt'w V)N+ WC, C'r V) aJ .r U mw3aJm V)C, 0 t' s3(O U>*>O Y~~U~I-V) * 0 U U 'r u .I- 0 -rV) 0 -C,C,n E mcr m wV)- Kt3 m C 7 0 OK1 T] OC, OC, w V) Pi m UC, L aJ 0-0 aJ L'r U V) E C a r na-wc, E .r C PID x-u-t- iGi5 Z 0 m L-? .C 4 3 C, Q)O'? L: - V) m w L .r C a>=> V) QCtJ 4aJ .r 4 0 aJ .c< . av, aJ L aJ .I- rexc LOQ)~~ d-' OaJO aJus C, .t- .c C,w C I C E mv, +J am cl- 0 L L.r re OaJ C =Jar C 4J.r aJ 0 %LH3 > 3-43-u MANNED SPACE FLIGHT

MERCURY

SUBORBITAL

Mission Launch Launch NASA Site/ Name DateITime Vehicle -Code Pad

Big Joe 9 Sep 59 At1 as-1OD Mercury-BP ETR Full-scale instrumented boilerplate model of 0319 EST 14 Mercury capsule reached an altitude of 161 km (100 sm) in re-entry test. Capsule recovered after surviving re-entry heat of more than 5,537OC (lO,OOO°F). (S)

29 Jul 60 Mercury- Mercury 4 ETR Launch of Mercury production capsule by an Atlas 0913 EST At1 as-50D 14 ended in failure when malfunction occurred one minute after 1iftoff, resulting in destruction of launch vehicle. (U)

21 Nov 60 Mercury- Mercury 2 ETR Generally not considered a launch, FlR-1 rose 2.5 0900 EST Redstone-1 5 centimeters (one inch), stopped firing, and (MR-1) settled back on pad. Premature booster cutoff, ,- triggered by faulty ground slipport circuitry, resulted in engine shutdown i:..!odiately after igni- - tion, and ignition of ~SLJ;)~tower rockets. Capsule was used again in RR-1A launch on 19 December 1960 with a different booster. (U)

19 Dec 60 Mercury- Mercury 2A ETR Repeat of MR-1 flight mission was successful and 1115 EST Redstone-3 - 5 all major objectives fulfilled. Capsule re- (MR-3) entered and landed in target srea 378 km (235 sm) - downrange after reaching an altitude of 217 km - (135 smj and speed up to 6,920 kph (4,300 mph). Capsule recovered in excel lent condition 48 min- - utes after launch. (S) =.- MERCURY (Continued)

Mission Launch Launch NASA Site/ Name Date/Tirne Vehicle -Code -Pad RemarksIResul ts MR-2 31 Jan 61 Merc~iry- Mercury 5 ETR Successfully launched fully equipped, operational 1155 EST Redstone-2 5 Mercury capsule containing 16.8-kg (37-1 b) chin- (MR-2) panzee named "Ham" on 16-minute suborbital fl ight to altitude of 251 km (156 sm) and over a dista,,ce of 676 k.2: (420 sm). Excessive booster velocity carried spacecraft higher and farther than programed, but mission objecti ves--fl ight tes; of capsule and its life-support system--was achieved when spacecraft and passenger were recovered in satisfactory condition. (S)

21 Feb 61 Mercury- Mercury 6 ETR Successful 2,293-km (1,425-sm) f 1i ght test of 0912 EST Atlas-67D 14 blercury capsule. At1 as shutdown prematurely to simulate an abort. After separation, capsule coasted to altitude of 172 km (107 sm); automatic stabil izdtion and control system oriented capsule for steep entry. Attained maximum velocity of 20,680 kph (12,850 nph). Landed in Atlantic Ocean 18 minutes after liftoff, sighted by search aircraft 4 minutes after landing, and recovered in excel 1ent condi tion shortly thereafter. Mercury- Atlas combination functioned smoothly during severe test, which was an essential step before manned orbital flights could be attempted. {S)

MR-BD 24 Mar 61 klercury- Me~sury-BP ETR Booster develop~enttest flight tc verify modifi- 1230 EST Redstone-5 5 cations necessitated by MR-2 f 1ight . Modified (MR- 5) Redstone carried boi 1erpl ate Mercury capsule to an altitude of 185 km (115 sm) and distance of 500 km (311 sm) downrange; test did not call for separation or recovery of capsule. Completely successful fl ight qua1 if ied Redstone for manned suborbital flights. (S) c,c-~ Fcc"005 I mCF " Col,u=z.: .rOaJ mm 0 gZ'L V), Q LC, V) 0 9- L maa'r 0 aJOC C V) wz +'$" CUU . ma5 C, U ?C- 3 m L.rC,aJ C C,C,CV) .rE CmmL E I aJLeraJ E lUaJ> m.r aJ cn 3% \ XLC C,m om rEr co aJ O5.rC ZBhTI5L aJUU *vaJ U CSrTI Q- CQ)>aJaJrc 3.- m CF3 L L mv V, U Q) 'r ~n cnru rnXF-V)aJC CaJmluZrn MERCURY IContinued)

ORB ITAL

Mission Launch Launch NASA Site/ Narne Date/Time Vehicle -Code -Pad Remarks/Resul ts MA- 3 25 Apr 61 Mercury- Fiercury 8 ETR Attempted orbital capsule test. Atlas did not 1115 EST At1 as- 14 fol 1ow programed fli ght path irrmediately after 100 -D 1iftoff and was destroyed by range safety action at approximately 5,000 meters (16,400 feet). Mer- cury capsule boosted clear of Atlas by escape tower rockets and was recovered intact. Provided thorough test of abort and recovery systems. (U)

13 Sep 61 Mercury- Mercury 8A ETR Successfully completed one orbit. Capsule was 0904 EST At 1as-88D 14 recovered. Checked Mercury world-wide tracking network. (S)

MS- 1 1 Nov 61 Mercury- hercury-NA ETR Destroyed by range safety action 30 seconds after 1032 EST Scout 18B 1iftoff. Air Force-launched: had been intended as test of global Mercury tracking network. (U) MA- 5 29 Nov 61 Mercury- Mercury 9 ETR Scheduled three-orbi t fli ght to test a1 1 Mercury 1008 EST At1 as-93D 14 systems. Spacecraft, carrying chimpanzee, completed two orbits when re-entry was cormnanded due to development of abnormal roll rate. Capsule was r2covered 1 hour and 25 minutes after water landing, and we1 l-performi ng "Enos" was recovered in excel lent condition. (S)

MA- 6 20 Feb 62 Mercury- Mercury 13 ETR First U.S. orbital manned space flight. Mercury 0947 EST At las-1090 (Friend- 14 spacecraft, manned by John H. Glenn, Jr., com- ship 7) pleted three orbits in 130,357-km (81,000-srn) flight lasting 4 hours, 56 minutes. Splashdown in Atlantic Ocean 267 km (166 sm) east of Grand Turk Island. Astronaut wmai ned inside capsule unti 1 on deck of recovery vessel. Flight provided significant aerospace medical data durins 285 minutes of weightlessness. Astronaut pi1 oted spacecraft during second and third orbits due to automatic pilot difficulties. (S) I I aJbW C WHQ) .r Q) > OL ln earn- ln L LQaJ EZ+'a r -0 - 0 YaJcaO>~ln LLO r 0-rln a aN OLt UFaJ -8 5 0 EQrn ELL- 2% -La C, aJ WaJU r Z OL >O **Skr 630 z a'." :I? &.z' m.r- 0 U U NC, onrn,E aJ Q-wmo 3 u P u ewe aJLme"C" C am+' U -ucm m-8 mL '4-m aJ aJer Q) -7 gl EM.: "a > U c Ul- L m"LOaJL0 * UC LP1 +-a- L ln-aJ- +'lnrvm+'o aJ+'EU Q).rmQ- L ln m c m*L+ ma on n3 L 'r 0 LV) ln 0 L 2-0 U lnrc U 0 3UC"laJO %u2 L "a UC, CN *cln ON- " rcl ;k?!lnc3c+'==* urn- L +' .r " .r -I- LUC7:') a L E-r r- Er- a-3 w .r .r n +' .r 8+' m x LCLbP aJECL U-0.- am- 0-Y 0 aJ mE Oc, ln- -I= L+' ln.5 arc c mm Ern+'+ m-r aJ- +' ow ln m Sowu ru- a Uh4 0 aJln+' m *ln LO he a'? C V) aJ aJ *-.r +' 3% aJ OQV) .+' +'OLE3 >u L'4-rn ln 3 CCD m L CC0 m +'a Q)C m.-l aJ aJ-r aJ L a cn L &+'- 3-c~E ln aln =x ul- 3 E 3biiUK6 1 THL

Pii ssion Launch ~aunch i4ASA Site/ hame Late/Ti ne Vehicle -Code -Pau Kenrarks/Hesul ts benri ni 2 19 Jan 65 Tith I1 GT-2 ETK Space vehicle devel op~i~ent. Suborbital , unmanned 0904 tST 6LV-2 19 re-cnt ry test at maxi mu~iiheat ing rate ; de~r~on- (GT-2) strated structural inteyri ty and systems performance of the spacecraft throughout the flight ; re-entry and parachute water 1andi ng. Recovery in downrange At1 antic. (S) OK6 ITAL hi ssi on Launch Launch NASA hite/ iJan~e Uate/Tirie Vehicle -Code -Pad Remarks/Hesul ts Gel~~ini 1 8 Hpr 64 Titan I1 GT- 1 ETH First Project Gemini flight, which tested the 11OO tST GLV-1 19 Titan 11 1aunch vehicle, (ien~inispacecraft struc- (tiT-1) tural integrity, and spacecraft-launch vehicle compati bili ty. Spacecraft placed into orbit of 328-km (204-snl) apogee, 160-kn~ (99.6-sm) perigee and 89.27-~iiinute period. 140 separation between the 3,175-kg (7,000-lb) spacecraft and the spent rocket casi ng was planned; orbiting assernbly re- entered the atmosphere and disintegrated about 3-112 days later. Test objectives achievea. (S)

23 Mar 65 Titan I1 tiT-3 First r~~annedGemini. Virgi 1 I. Grissoir~, Comnand 0924 tST GLV-3 Pilot and John W. Young, Pilot. Three orbits, 4 (tiT-3 j hours and 53 minutes in space. First use of (;;*i ltal Attitude Maneuver System. First control ~'ire-entry flight path using maneuverable spacecraft. Spacecraft unofficially called "holly Grown." (S)

3 Jun 65 Titan I1 tiT-4 CTK James A. hcbivitt, Comianu Pilot, tdward H. White, 1016 E3T GLV-4 19 11, Pilot. 62 orbits, a total of 97 hours and 59 (GT-4) minutes in space. First extravehicular acti vity (EVA) for 22 ~i~inutes,and the first use of person- al propulsion unit (both by White). A prograiil of eleven scientific experiments was successfully conductea. Uenaezvous with booster was not achieved due to excess fuel consumption. First rilission control fro111MSC. Recovery by bSS Wasp. (3)

G~PIIIJI (continued)

Launch Launch It ASA Site/ Uate/Ti iile Vehicle -Code -Pad Hen~arks/Kesults

16 Mar b6 Titan I1 tiT-8 ETk Nei l k. An~~strong,Corrn~anrt Pi lot, and bavid 'k. 1141 EST GLV-8 19 Scott, Pi lot. 7 rev01 utions, 10 hours and 42 min- (GT-8) utes in space. First dual launch and docking with the Agena target vehicle. hission curtai 1ed by short circuit in the Orbital Attitude Pineuvering System depleting fuel through thruster #8. Unex- pected yaw and roll rr~otioncaused astronauts to undock, use their re-entry control SyStai to stabilize the spacecraft, and re-enter on the 7th revol ution instead of going the planned 44. Land- ing was in stipulated eiilergency area in the hestern Pacific, 3 ~i~iles from USS Mason. Planned tVk for one orbit not achieved. (P) Gen~ini 9 At1 as UTL tTk Target vehicle for GT-9. The nunber two At1 as Tarset TLV-5303 14 engine nialfunctioned, and the number one engine Vehicle ny ena was unable to con~pensatefor the pitch aown atti- TV-5004 tude. The missile fell into the Atlar~tic. (Ir)

1 Jun 66 ATUA ETH Sent up in lieu of the unsuccessful tiATV for GT-9. 1000 EST 14 The HTLP. was to be used for rendezvous and docking rrianeuvers. However, due to the faulty instal- lation of separation devices, the protecti ve shroud failed to separate from the satellite. Rendezvous 1ater accornpl ished with the shroud sti11 in place. Re-entered dtn~osphere11 June 1966. (P) (continued)

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Gemini 9A 3 Jun 66 Titan I1 Thomas P. Stafford, Command Pilot, and Eugene A. 0840 EST GLV-9 Cernan, Pilot, were in orbit for 44 revolutions. (GT-9 ) The primary purpose was to rendezvous and dock with the GATV and ta evaluate EVA. The ATDA sent up in place of the unsuccessful GATV kept its protective shroud, making docking impossible, although rendezvous was accomplished. Splashdown on 6 June, 966 km (600 sn) fro? Cape Canaveral, 50 km (31 sm) from the USS Wasp. (P)

Gemini 10 18 Jul 66 At1 as GATV + E TR Rendezvous vehicle for GT-10. Launched 100 min- Target 1540 EST TLV-5305 14 utes before launch of GT-10. Placed in near-cir- Vehicle Agena- cular orbit of 296 km (184 sm). Re-entered TV-5005 atmosphere 29 December 1966. (S)

Gemini 10 18 Jul 66 Titan I1 GT- 10 E TR John W. Young, Comnand Pilot, with Michael 1540 EST GLV-10 19 Col 1 ins , Pi1 ot . Primary purpose was to rendezvous (GT-10) and dock with Agena test vehicle. Secondary objectives included rendezvous with the GT-7 target vehicle. More fuel used in docking than was planned. Docking accompl ished on fourth rev01 u- tion, Mated spacecraft reached apogee of 766 km (476 sm) , 1ater rendezvoused with GATV of GT-8. Stand-up EVA by Collins terminated due to irrita- tion in eyes. hbilical EVA terminated to save fuel. Rr-entered on 21 July after 43 revolutions. (S)

Gernini 11 12 Sep 66 At1 as GATV E TR Launched 97 minutes before GT-11. Near-circul ar Target 0805 EST TLV-5306 14 orbit of 298 km (185 sm). Docking vehicle for Vehicle Agena GT-11. Re-entered atmosphere 30 December 1966. TV-5006 (S) 0 V)aa aJ = *L xi2 V) UW U aJ aJ CNC U L 3h 0 a aJ a.w.r n* -I V)WC '3.7 PJ am 3 aJ I I-N amaJ .rfUL5U O'FY .K 1L h 0) 0 . ir) >e,rOh- Cc,c,E MSFN TRAINING SATELLITES

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Resul ts TTS 1 13 Dec 67 Del ta TTS-A E TR Launched as a piggyback payload attached to rear 0908 EST DSV-3E 17B of second stage of Delta vehicle that successfully (Del ta-55) injected Pioneer 8 intc solar orbit. Timer aboard Delta second stage ejected TTS one minute after third stage ignition. 18-kg (40-lb), eight-sided (35.6 centimeters, or 14 inches/side) sate1 1 ite with solar cells on external surfaces. Contained a power supply, command receiver, telemetry trans- mitter, passive magnetic stabilization system, and a transponder conpat ibl e wit h un if ied S-Band (USB) system. Transponder was designed to transmit and receive S-Band data characteristics of the Apoll o spacecraft and its mission. During 3-month 1 ife- time satellite afforded each shift of every Manned Space Fl ight Network (MSFC) station amp1 e opportu- nities to check out equipment and train personnel. 483-km (300-sm) apogee; 292-km (182-sm) perigee; 33O inclination; 92-minute period. Re- entered atmosphere 28 April 1968. (S)

TETR 2 8 Nov 68 Del ta TETR-B E TR The second of three training satellites launched 0446 EST DSV-3E 178 to test the Manned Space Flight Network, TETR-2 (Eel t a-60) was injected into Earth orbit from the Delta second stage after it had pi aced the third stage and primary Pioneer-D spacecraft in a parking orbit. The 18-kg (40-lb) spacecraft provided an economi- cal and dynamic medium for exercising the unified S-band systems of the PSFN. Re-entered 19 Septem- ber 1979. (S)

TETR 27 Aug 69 Delta TETR-C E TR This was the third spacecraft in the MSFN training 1759 EDT DSV-3L 17A series. The Delta first stage hydraulics system (Del ta-73) failed before main engine cutoff, throwing the second stage into an incorrect attitude aftzr separation. Range Safety destructed the vehicle after 483 st conds of flight . (U)

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Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code Pad Remarks/Resul ts Apol 1 o- 25 Aug 66 Uprated AS-202 ETR Second fli ght test of major spacecraft systems and Saturn 1316 EDT Saturn I CSM-011 34 second performance check of comnand module (CM) (AS-202) heat-shielding; first use of spacecraft fuel cell power system. Liftoff was normal. Launch vehicle developed 7,116,800-newton (1,600,000-lb) thrust during first (S-IB) stage powered flight. After separation of Apoll o spacecraft (011) , service module (SM) engine was burned once to raise spacecraft to 1,136-km (706-sm) a1 titude, then was ignited and cut off three more times to test rapid restart capability. CM separated from SM and re-entered atmosphere at more than 32,026 kph (19,900 mph). maxi mu^ re-entry temperature of CM's outer surface was calculated to be about 1482°C (2700°F) ; interior temperature was 21°C (70°F). CM landed in Pacific 805 km (500 sm) southwest of Wake Island after 93-minute fl ight, and was recovered by USS Hornet. (S)

NOTE

The Saturn I9 vehicle was renamed the Uprated Saturn I on 9 June 1966. On 15 January 1968, the name was changed back to Saturn 19. APOLLO (cs nti nued)

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Results Sat urn 28 May 64 Saturn I SA-6 ETR First major flight test in Project Apollo, with 1207 EST (SA-6) CSM-BP-13 375 successful orbiting of first boilerplate Apol lo spacecraft. The payload consisted of the boilerplate and the S-IV second stage; re-en2ered atmosphere and disintegrated over the western Pacific during its 50th orbit of the Earth on 1 June 1964. One mission highlight was the perfect performance of the ST-124 guidance platform, which control led the second stage during flight . One first-stage engine shut down 24 seconds early, but deviation from the planned trajectory was cor- rected by the SA-6 guidance system. Test considered highly successful. (S)

Saturn 18 Sep 64 Saturn I SA-7 ETR First demonstration of Launch Escape System (LES) 1122 EST (SA-7) CSM-BP-15 37B design, by successful jettison during powered fl ight. Boi ierplate Apol lo spacecraft comnand and service modules, instrument unit and S-IV stage, were placed in orbit. All major test objectives were met. Motion picture cameras and a TV camera mounted on the S-I stage recorded flight events. However, the motion pictures were ejected near a hurricane area and recovery was not attempted. Re-entered atmosphere on 22 September 1964. (S) APOLLO (cont inued)'

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Pegasus 1 16 Feb 65 Saturn I SA- 9 E TR Spacecraft used to detect micrometeoroids, the 0937 EST (SA-9) CSM-BP-16 37B first primary use of capacitor-type penetration detector. Carried into orbit insiae 9l half of boilerplate CSM. Sensor area 185 square meters (2,000 square feet). Re-entered 17 September 1978. (S)

Pegasus 2 25 May 65 Saturn I SA-8 ETR Spacecraft used to obtain data on micrometeoroids 0235 EST (SA-8) CSM-BP-26 378 in near-Earth environment. Carried into orbit inside SM half of boilerplate CSM. Test of Saturn launch vehicle. Ninth successful test in nine flights for Saturn I. Re-entered 3 November 1979. (S)

Pegasus 3 30 Jul 65 Saturn I SA-10 ETR Last of current Pegasus program. Carried into 0800 EST (SA-10) CSM-BP-9A 37B orbit inside SM half of boilerplate CSM. Contin- ued study of distribution, size, and velocity cf meteoroids in near-Earth orbit, and continued development of Saturn I vehicle. Re-entered Earth atmosphere 4 August 1.969. (S)

...... -NOTE Following a review of the results of prior suborbital and Earth-orbital missions, the Saturn IB launch vehicle and the Apollo spacecraft (comand and service modules) were deemed qua1 ified for Earth-orbi tal s-znned missions. Preparations began for the first manned Apollo flight.. On 27 J?ns&r-y 1967, at 1831 EST, fire broke out in the command module during a pre-launch test on Launch Complex 34. The crew was on board and the spacecraft's 100% oxygen atmosphere pressurized to 16.7 psia. The fire resulted in the deaths of astronauts Virgil I. (Gus) Grissom; Edward H. White, 11; and Roger B. Chaffee.

APOLLO (continued)

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Resul ts Apol lo 5 22 Jan 68 Saturn IB AS-204 ETR First Earth-orbi tal test (unmanned) of Apol 1o 1748 EST (AS-204) LM-1 3 7B spacecraft Lunar Module (LM). (On this flight Apollo Command and Service Modules were replaced by a dumrly nosecone.) Launched after extended holds caused by spacecraft equipment and ground instrumentation problems, the LM and second (S-IVB) stage of Saturn IB were successfully injected into desired orbit, then separated. A1 though LM descent stage propulsion system did not sustain combustion following first ignition, 1ater attempts were successful (including restart). LM ascent stage propulsion system operation and staging of ascent and descent stages were also performed successfully. All mission objectives were achieved. S-IVB stage re-entered Earth's atmosphere on 23 January, LM ascent stage re-entered on 24 January, and descent stage re-entered on 12 February 1968. No attempts at recovery were planned, or made. (S) APOLLO (continued)

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Results

Apol lo 6 4 Apr 68 Saturn V AS-502 KSC LC-39 This fl ight was pi anned as a mission similar to 0700 EST (AS-502) CSM-020 Pad A Apoll o 4 (9 November 1967), but in-fl ight problems prevented achievement of primary mission objectives. Liftoff was normal and on schedule. How- ever, severe up-and-down ("pogo" ) vibrations of the entire space vehicle during first (S-IC) stage thrust, early shutdown of two second (S-11) stage engines, and failure of the third (S-IVB) stage engine to restart following orbital coast, required that Mission Control perform an a1 ternate mission. Spacecraft separation was commanded, and the Service Module (SM) engine was started and burned for 445 seconds, to raise spacecraft apogee to 19,312 km (12,000 sm). This utilized most of the propellants and resulted in a Comnand Module (CM) re-entry of 1,919 meters per second (4,000 feet per second) less than planned. CM was recovered in Pacific near Hawaii , about 370 km (230 sm) from the target area, 9 hours, 58 minutes after liftoff. (U) APOLLO (continued)

Mission Launch Launch NASA Site/ Name Date/Ti me Vehicle -Code -Pad

Apol 1o 7 11 Oct 68 Saturn IB AS-205 ETR Liftoff was two minutes, 45 seconds later than 1103 EST (AS-205) CSM-101 34 planned, due to a brief hold to check second stage engine chilldown. The second (S-IVB) stage, IU, SLA,and CSM were injected into Earth orbit. After a brief coast period the S-IVB stage was restarted, placing the attached spacecraft into a higher orbit. Later the CSM was separated and performed rendezvous and station-keeping maneuvers, approaching within 21 nreters (70 feet) of the spent S-IVB. Extensive checkout of spacecraft Apol lo 7 Astronauts systems was performed during the course of the mission. A total of eight service propulsion Walter M. Schirra, Jr., Corrunander; Donn F. Eisele, system (SPS) firings were accomplished, and sev- CSM Pilot; Walter Cunningham, LM Pilot eral changes in orbital path were made. The final SPS burn was a deorbit retrofire. The command module separated from the service module prior to re-entry, landing in the Atlantic about 11 km (7 Apol 1o 7 Weights sm) from the target point at 0711 EST on 22 October, after a flight of 260 hours, 9 minutes Weight in Earth orbit--S-IVB stage, Instrument (10.8 dzys). Seven television transmissions from Unit , Spacecraft Lunar Modul e Adapter (SLA) , and the spacecraft were broadcast 1ive over commercial CSM--30,323 kg (66,850 Ib) television, both in the U.S. and abroad. While in orbit a1 1 three astronauts developed colds, without any apparent aftereffects. (S)

I Apollo 7 Firsts i First manned Apol lo fl ight ; manned Saturn IB 1 fl ight ; manned launch from Launch Complex 34; C3M 1 operated by astronauts in flight; CSM performed ! rendezvous and st ation-keepi ng maneuvers ; extensive checkout of CSM systems performed during mission; eight Service Propulsion System firings performed; tel evision broadcasts by astronauts in CM; and manned CM landing in ocean. Ciission Launch Laurlch NASA Site/ Name L)ate/Time Vehicle -Code -Pad Apollo 9 3 Mar 69 Saturn V AS-504 KSC LC-39 After a three-day delay due to a minor viral in- 1100 tST (AS-504) CSM- 104 Pad A fection of all three cremen, the AS-504 vehicle (Gunldrop) was launched on time and without unplanned holds. Lh-3 The S-IVB stage and spacecraft were inserted into (Spi der ) a low-tarth orbit. The spacecraft separated from the vehicle, turned around, docked to the Lh, and removed it from the SLA. The S-IVB was then reignited and placed in an Earth-escape trajectory, but propellant dumps could not be performed. The npollo 9 Astronauts C9i SPS rocket was fired four times with the LM and CSM docked. The Liq descent engine was fired James 14. Ivrclii vi tt , (;orislander; David H. Scott, Cbh with the two vehicles still docked. The SPS en- Pilot; Russell L. Schweickart, LM Pilot y ine was fi red ayai n. The Conmander and Lh pi1 ot undocked the Lh from the CSM and manuevered away fro111and back to the CSH, using both the aescent and ascent engines. The Lh flew independently of Hpol 1o 9 Weights the CSlvl for over six hours. After redocking the crewinen returned to the CSM and the ascent stage 1 Total weiyht--space vehicle on paa--2,893,618 kg was jettisoned; its engine was fired by remote 1 (6,379,335 lb) control to send the stage into a high el 1iptical height in tarth orbit (S-IVU stage, IU, CSM, and orbit. The SPS engine was fired twice more for i LPI)--131,528 kg (289,970 Ib) maneuvers, a multispectral photography experiment I was conducted, and the SPS engine fired a final i I ti~ilefor re-entry. The USS Guaaalcanal had the crew aboard one hour after splashdown on 13 march, pol lo Y Firsts completing a flight of 241 hours, 1 minute (10 days, 1 !lour, 1 minute). Lh descent stage re-en- First 1aunch of coriipl ete Pj01lo configuration tered 22 )\arch; ascent stage still in orbit. (S) (Saturn V vehicle, CSM, and Lh); docking in space I I of 6S.i and LM; firing of LEI ascent and descent engines in space; transfer by b.5. astronaut from one space vehicle to another; separation, rendezvous, ana redockiny of two spacecrdft; 57 hours ana 47 11;inutes of fl iqht with docked spacecraft; and first LVH by an astronaut completely free of spaceship life support equipment. APOLLO ?continued j

LUNAR ORBITAL

Mission Launch Launch NASA Site/ N arne Date/Time Vehicle -Code -Pad Remarks/Resul ts Apollo 8 21 Dec 68 Saturn V AS-503 KSC LC-39 The S-IVB third stage and spacecraft were launched 0741 EST (AS-503) CSM-103 Pad A into a low-Earth parking orbit, to check space- LTA-B craft and ground systems. During second orbit the S-IVB stage engine was reignited, boosting the space vehicle to an initial trans-lunar coast velocity of 39,579 kph (24,593 mph). The spacecraft A~ollo8 Astronauts a~dthe S-IVB then separated, and the S-IVB was sent on a path away from the spacecraft and into Frank Borman, Commander; James A. Love1 1, Jr., CSM sol ar orbit . The spacecraft ' s 1unar trajectory Pilot; William A. Anders, LM Pilot required only minor rnidcourse corrections. Apol lo 8 passed ahead of the Moon at an alt'tude of about 114 krn (71 sm) and a speed of about 9,205 kph @llo 8 Weights (5,720 rnph) , and at 0459 24 Dec, while on the far side, the spacecraft's engine was fired to insert Total weight--space vehicle on pad--2,821,236 kg it into lunar orbit. During 10 1unar rev01 uti2ns (5,219,760 lb) the astrcnauts took star sightings to pinpoint h'right in Earth orbi t--spacecraft , IU, S-IVB-- 1andmarks, surveyed 1anding sites, took both st?11 121,913 kg (282,000 lb) and notion pictures, and made two televisio:! '$!eight fol lowing translunar injection--28,871 kg transmissions to Earth. At 0110 25 Dec, again on (63,650 lb) the far side of the Moon, the spacecraft's engine was ignited to accelerate it out of lunar orbit. Initial transearth coast velocity was about 3,712 Aoolio 2 Firsts kph (6,035 mph), and onlj one midcourse correctior! was needed. At about 16,668 km (10,357 sm) from :,,or-ld's first manned flight to Moon; first manned Earth the command and service modul es separated, flight to orbit the Moon; first manned flight to and fifteen minutes later the comand module re- escd?e rhe influence of Earth's gravity; fastest entered Earth's atmosphere at a speed of 36,015 and fut.:hest humans travelled in space to that kph (24,243 rnph). On 27 Dec, Apollo 8 1anded in date; first audio-video comunication by astro- the Pacific 508 meters (5,000 yards) from the re- nauts from lunar distance (6 TV transmissions: 2 covery ship USS Essex, after a flight of 147 enroute, 2 in lunar orbit, 2 during return); first hours. (S) iii~nnedSaturn V fl ight; first manned launch from I Launch Conplex 39, KSC; first manned spacecraft 1 anding in darkness. /\POLL0 (continued)

Iqission Launch Launch NASA Site/ Name DateITin~e Vehicle -Code -Pad Kemarks/Hesul ts hpollo 10 18 May 69 Saturn V AS-505 KSC LC-39 AS-505 was the fifth successive on-time launch of 1249 tbT ( AS-505) CSM-106 Pad B the Saturn V vehicle. All three stages ?erfomeci (Char1 ie norn~ally. The S-IVB stage was reignited in orbit brown) and placed itself and spacecraft in a lunar tra- LN-4 jectory. The CSM separated, turned, and docked to (Snoopy the LM; this docking was shown 1ive on comnercial television. The S-IUB propellants were dumped and the staye reached tarth-escape velocity. Only one k,jollo 10 Astronauts spacecraft trajectory firing was utilized. fit the Noon the spacecraft fired its enyine twice to en- Thomas P. Stafford, Corrrnander; John k. Young, CStl ter a low-circular orbit. The lunar surface was Pilot; tugene A. Cernan, Lh Pilot shown to Earth in a 29-minute color TV transmission. The Cormlander and LM Pi 1ot undocked the LM and flew within 15.6 km (9.7 sm) of the lunar sur- hpollo 10 Firsts face. When the Lbi descent stage was jetti sioned, an incorrectly placed switch caused the ascent Lemonstrated rendezvous in lunar orbit, including stage to change attitude, requiring the Comnander i to assure manual control. Rendezvous with the CSh i burning LM descent staye enyine in the lunar landing 111i ssi on configuration and environment; eval u- was then accomplished. After jettisoning the LM i ated Lk steerable antenna at 1unar distances; flew ascent stage the CSM fired its engine to return to i ii4 within 15,240 meters (50,000 feet) of lunar sur- Earth. (In the trip ho111ethe crew made six more TU face; eval uation of Lh omrli antennas at 1unar dis- broadcasts. Splashdown 26 May occurred in mid- tances; in-flight test of the abort guidance Pacific, with the crew picked up shortly after- Systeni, in-fl iyht use of VHF ranging; landing radar wards. The fliyht lasted 192 hours, 3 minutes (8 t test in near-1 unar envi ron~nent; demonstration of days, 3 minutes). (S) iiestinyhouse color TV carrlera in flirjht; manned nav- isational , visual, and photographic eval uations; 1aryest payload placed in Earth ana 1 unar orbit at tirr~e. 1 APOLLO (conti nued)

LUNAR LANDING

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Remarks/Resul ts Apollo 11 16 Jul 69 Saturn V AS-506 KSC LC-39 Apollo 11 had the historic mission of landing a 0932 EDT (AS - 506 ) CSM-107 Pad A human on the Moon. Liftoff and insertion into (Col umbi a) Earth orbit were normal. The S-IVB stage was re- LM-5 ignited and inserted itself and spacecraft into a (Eagl e) lunar trajectory. The CSM then docked to the LM. Only one of the four planned trajectory correction firings was utilized. At 55 flight hours the crew Apol lo 11 Astronauts transmitted TV for 96 minutes, showing themselves "1 ive" on comnercial TV. Two burns of the :SM en- Neil A. Armstrong, Commander; Michael Collins, CSM gine placed them in a low-lunar orbit. The LM un- Pilot; Edwin E. Aldrin, Jr., LM Pilot docked and dropped toward the lunar surface. The area where the automatic systems would have 1anded the LM was too rocky, and the Comnander took manu- Apollo 11 Firsts al control and 1anded the craft, at 1617:43 EDT on 20 July. The tw men donned spacesuits and went First manned 1unar 1anding and return; 1unar sur- EVA 6-1/2 hours 1ater, Comnander Armstrong being face EVA; seismometer deployed on Moon; 1aser re- the first man to set foot or the Noon at 2255: 15 flector deployed on Moon; solar wind experiment EDT. He deployed a TV camera on the way down the deployed on Moon; lunar soil and rock samples re- ladder, and the event was seen "live" by an esti- turned to Earth; largest payload placed in lunar mated haif-billion people on Earth. The two men orbit at time; first test of landing radar and set up a flag and scientific experiments, gathered other landing systems on the LM under operational rock samples, talked to President Nixon "1 ivn," conditions; use of mobile quarantine facil ity and and many other firsts. They then re-entered the Lurlar Receiving I-aboratory at MSC. LM, 1i fted off, rendezvoused with the CSM, and returned sdfely to Earth 24 July after a flight lasting 195 hours, 18 minutes (8 days, 3 hours, 18 minutes). Rock samples were turned over to scientists for analysis, which continues. (S) APOLLO Iconti nued)

Mission Launch . Launch NASA Site/ hame DateITime Vehicle -C ode -Pad Remarks/Resul ts Apol lo 12 14 Nov 69 Saturn V AS- 507 KSC LC-39 Apol lo 12 was the second lunar landing mission. 1122 EST (AS-507) CSM- 108 Pad A Liftoff was normal, but while passing through a (Yankee low cloud the vehicle apparently caused an elec- Cli ppe r) trical discharge through the Saturn to the LM-6 ground. Safety devices turned off most power sup- (Intrepid) plies in the CSM, but the astronauts restored them and the flight continued. After a check of all kpol 1o 12 Astronauts systems whiie in Earth orbit the S-IVB stage was reignited and injected itsel f and spacecraft into Charles Conrad, Jr., Comnander; Richard F. Gordon, a lunar trajectory. The CSM then docked with the Jr., CSM Pilot; Alan L. Bean, LM Pilot LM. The LM Has entered and checked to be certain the electrical discharge had not affected its systems. The CSM engine was fired tkice to achieve Apollu 12 Firsts the correct lunar orbit, and the LM separated and descended to the surface. The landins was at First use of S-IVB stage to perform an evasive ma- 0154:35 EST on 19 Nov, within 183 meters (600 neuver; use of a hybrid trajectory; largest payload feet) of the Surveyor 3 spacecraft. r'he crew went ;laced in lunar orbit to that date; demonstration of EVA and set up the scientific experiments and a point landing capability; use of two lunar surface color TV camera but direct sun1 ight entered the EVA periods; first Apollo Lunar Surface Experiments lens and it became inoperative. During a second Package (ALSEP) deployed on the Moon; deployment of EVA the astronauts walked more than a mile. They the erectable S-Band antenna; use of geologist to also collected samples and parts off Surveyor 3. plan lunar surface traverse in real time; documenta- After a time of 31 hours, 31 minutes on the lunar tion of samples as they were taken on the Moon; surface the LM ascent stage lifted off and double-core tube sample taken; return of spacecraft rendezvoused with the CSM. It fired its engine to parts (Surveyor 3) that had been on Moon 2-1/2 return to Earth in the established manner, landing years; longest distance traveled on 1unar surface, in the mid-Pacific 24 Nov after a flight of 244 and largest payload returned from lunar surface, to hours, 36 minutes (10 days, 4 hours, 36 minutes). date; first mu1 tispectral terrain photography from The samples were distributed to the scientific lunar orbit. community. (S) APULLO (continued)

Fri ss ion Launch Launch iJASA bite/ Narne irate/Time Vehicle -Code -Pad Hemarks/Hesul ts i Ago1 lo 13 11 Apr 70 Saturn V A3-508 KSC LC-39 kpol lo 13 was planned as the third lunar landing 1413 EST (AS-508) C3M-109 Pad A mission. First staye perfomlance was nominal, but (Odyssey the S-I1 second staye center engine cut off 132 LM- 7 seconds ear-ly. The remaining four engines burned (Aquarius) an extra 34 seconds, and tile S-IVB nine seconds, to compensate. Lunar trajectory insert i on occurred on schedule. The CSM then turned and I! A~ollo13 Astronauts docked with the LM. The spent S-IVB stage was I i fired to yuide it to an impact point on the Moon 2 '; ~art~esIr. Love11 , ~r.,Corrunanaer; John L. Swiyert, 15 April, 137 km (85 sin) from the seismometer i: 12. ' dr., CSM Pilot; Fred W. Haise, Jr., Lh Pilot established by Apollo The CSM flight was nor- I ri~al until almost 56 hours after liftoff, at which point a fire occurred in the No. 2 oxygen tank in pol 1 o 13 Firsts the 91. This led to loss of all fuel cell power , as we1 1 as other CSEl failures. The mission was First use of Lh as 'lifeboat" when CSM was powered aborted and the task of getting the astronauts down; operational firing of LM descent engine in safely home began. The CSN was powered down and I 1 unar environrner~t to change veioci ty of CSM!LM the astronauts entered the LM. The LM descent ~hiledocked; attitude positioning of CSM/LM with engine was fired twice to establish a faster re- ti4 guiaance systems; demonstrated feasi bi1 i ty of turn path after circling the Moon, and twice for conserving consumables by powering down CSM; opera- trajectory correction. The SM and then the Li3 :i onal probl eni-sol viny on real-tirile basis by both were jettisoned as the astronauts neared Earth, I astronauts and ground-support personnel ; and safe and re-entry occurred in the usual nlanner in the recovery of astronauts from aiszbled CXI. LSM, powered by its batteries. The astronauts were recovered from the mid-Pacif ic within an hour after landins 17 April, after a flight of 142 hours, 54 n~inutes(5 days, 22 hours, 5 minutes). (PI APOLLO (continued]

Mission Launch Launch NASA Site/ Name Date/Time Vehicle -Code -Pad Apol lo 14 31 Jan 71 Saturn V AS-509 KSC LC-39 Spacecraft modifications to improve mission scien- 1603 EST (AS-509) CSM-110 Pad A tific capabilities, plus changes in flight plan (Ki t ty and flight hardware for greater safety margins (as Hawk) result of Apollo 13 problems), caused launch date LM-8 to be moved from Oct to Nov 70; then to 31 Jan 71 (Ant ares) (13th anniversary of Explorer 1). Cocntdown was normal until T-8 minutes, when weather restric- tions (imposed after Apol lo 12) caused an un- pl anned 40-minute hold. Delayed 1i ftoff necessitated revised launch-to-orbit azimuth and a mod- Apol lo 14 Astronauts ified trans1unar trajectory so spacecraft would reach Moog on schedule. CSM-LM docking, following A1 an 0. Shepard, Commander; Stuart A* Roosa, CSM translunar injection, achieved on sixth try. Pilot; Edgar D. Mitchell, LM Pilot Spacecraft entered initial 1unar orbit on 4 Feb. Orbital path later lowered to minimum of 15,240 m (50,000 ft) to permit a shorter, s:eeper LM Apollo 14 Achievements descent path. "Antares" landed on Moon at 0418 EST 5 Feb, 27 m (87 ft) frai target point in Fra Third manned lunar landing mission and return. Mauro highlands. During two excursions on lunar First use of mobile equipment transporter (a small, surface (totaling 9 hrs, 24 mins) Shepard and two-wheeled handcart) on lunar surface. Lunar sur- Mitchell covered 3.3 km (2 sm) , while Roosa con- face stay time, distance traversed on lunar sur- ducted scientific experiments from CSM in lunar face, and payload returned from lunar surface were orbit. Lunar 1iftoff occurred 5 Feb after 33-hr, considerably greater than previous missions. F;rst 32-min stay ; rendezvous, docking, and transfer use of shortened descent and rendezvous technique. were normal ly achieved. "Kitty Hawk" departed First extensive orbital science period conducted 1unar orbit after 34.5 rev01 utions. CYit 1anded in during CSM solo operations. mid-Pacific at 1605 EST 9 Feb within 1.6 kilometers (one mile) of planned landing point, com- pleti ng 9-day, 2-minute mission. (S) APOLLO (continued)

Mission Launch Launch NASA Site/ Name Date/Time Vehicle Code Pad Remarks/Resul ts

Apollo 15 26 Jul 71 Saturn V AS-510 KSC LC-39 Prelaunch checkout and final countdokn mved 0934 EDT (AS-510) CSM- 112 Pad A steadily to an on-time 1iftoff for the first of (Endeavour j the Apol lo missions with lengthened stay-t ime and LM-10 improved mobi 1i ty for extensive 1unar surface op- (Fa1con) erations. Spacecraft entered initial lunar orbf t LRV-1 on 29 February. Despite 25-minute delqy in CY!=tM undocki ng, "Falcon" landed on Moon at 1816 ED1 30 July. Shortly after touchdown Scott stood in LM upper hatch to observe and photograph landing area. Lunar surface activity began the following Apollo 15 Astronauts norning. A1 though some minor difficulty was experienced with deployment of the lunar roving vehi- David R. Scott, Comander ; A1 f red i4. Worden, CSM cle, and with its steering mechanism, it later Pilot; James B. Irwin, iM Pilot functioned perfectly. Yhile Scott and Irwin explored the edge of the Hadley Rille and the base of the 1unar Apenni nes, Worden conducted experi - Apol 1o 15 Achievements ments from lunar orbit. LM lifted off 66 hours, 55 minutes after touchdown. Following crew and Fourth manned lunar landing and return; first ex- cargo transfer to CSM, subsatc-llite was injected tended 1unar exploration mission. First 1unar into 141 x 101-km (87 x 62-sm) lunar orbit. orbital science payload carried in Service Module "Endeavour" departed Moon after 74 revolutions and bay and operated by CSM Pilot. First use of manned 1anded in mid-Pacif ic, c~pieti ng 12-day, 7-hour, lunar roving vehicle (traveled 27.9 km--17.25 sm-- 12-minute mission* (S) over 1unar surface). First ground-control 1ed remote operation of TV camera on the Moon (observed LM lu~ar1iftoff). First subsatell ite launched from CSM in lunar orbit. First spacewalk from CM during return flight to Earth. \

.r a an. APOLLO (continued)

1 ,J- s jion Launch Launch NASA Si te/ 1 -,zm Date/Ti me Vehicle -Code -Pad i --*,loI --1 17 7 Dec 72 Saturn V AS-512 KSC LC-39 Launch countdown proceeded smoothly unti1 the fi- 0033 EST (AS-512) CMS- 114 Pad A nal minutes when the automatic Terminal Countdown 1 (Arneri ca) Sequencer fai 1ed to comnand pressuri zat ion of the LM-12 Sat~rnV second-stage LOX tank. Llthough tank (Chdl ienger) pressuri zat ion was cor~nandedmanual 1y, the failed fcnction prevented actuation of an interlock in the ready-to-launch logic train and the sequencer comnanded an automatic shutdoun. It was determined that the interlock could be bypassed by a A;:: 1 o 17 Astronauts jumper. The work-around was analyzed and checked 1 out on a breadboard sequencer at MSFC, and the de- :,gene A. Cernan, Commander; Ronald E. Evans, CSM cision made to proceed with the countdown. The 1 ;-:~t;Harrison H. Sctunitt, LM Pilot final Apollo miss?on lifted off 2 hrs, 40 mins I late. Flight to the Moon was near-routine, and "Challenger" landed at Taurus-tittrow at 1455 EST I L;2l lo 17 Achievements 11 Dec. During three traverses with the LRV on 1 the lunar surface, astronauts Cernan and Schmitt I i :-~hsuccessful manned lunar landing and return stopped at numerous pre-planned points to conduct I I' ?st in Apol lo Program); first geologist astronaut geol cgical observations and col 1ect samples, whi 1e (lchmi tt) on lunar surface; longest lunar surface astronaut Evans operated scientific equipment in s'3y time (74 hrs, 59 mins, 38 secs); longest single the CSM "herlca" in lunar orbit. Lunar liftoff I !>gar surface excursion (7 hrs, 37 mins, 22 secs); occurred at 1745 EST, 14 Dec. After 75 revolu- 1 ;.yest total lunar surface excursion (22 hrs, 5 tions about the Moon, "America" departed for I :-C~S, 4 secs); longest lunar distance travelled by Earth. During the return flight, astronaut Evans Lji qn one traverse (19 km--11.8 sm); longest total exited the spacecraft to retrieve fi 1:#1 from cam- 4i;tance traversed with LRV (35 km--21.75 sm); most eras located in the service module. 3n 19 Dec the 1 Jndr samples returned to Earth (115 kg--250 1b); cormiand module landed in the mid-Pacific 12 days, 24 hrs after 1i ftoff bringing the Apol lo manned I longest time in lunar orbit (147 hrs, 48 mins--75 , i ~TS). lunar landings to a close. (S) SKY LAB

ShL LAB

hi ss ion Launch Launch MSG Site/ 14 ame Date/Tirne Vehicle -Code -Pad Kemarks/Kesults- 3kyl ab 1 14 kay 73 Saturn V SL-1 KSC LC-39 Prelaunch countdown was con~pletedwith no unsched- 1330 EDT (AS-513) AS-513 Fad A uled holds, despite problems within the ML corn- ULJ S puter during the final two hours. The unmanned Nq-MDA Orbital Workshop (OWS) was inserted into the de- i I ATM sired orbit of 440 x 424 kin (273 x 263 sn~)with an r irtcl ination of 50' and a period of 93 minutes. The payload shroud was jettisoned and the Apollo Telescope hunt (ATM) and its solar arrays depl oyed normally. However, inspection and analysis of telemetry records verified that about 63 see- onds after liftoff the GWS meteoroid shield (which ti1 so provided protection from solar heating) had Largest habitable structure ever placed in orbit, prematurely deployed and was torn off, taking one with 3b0 cubic meters (12,700 cubic feet) of work of the OMS solar array wings with it. A piece of ana 1ivi ng space. Sky1 ab was 35.7 meters (117 the shroud had wrapped around the other solar feet) long, 27.4 meters (90 feet) wide across its array wing , keepi ng it from depl oyi ng and generat- i solar panels, and had a mass of 90,605 kg (139,750 ing electrical power. Temperatures inside the OWS I b) 1 1 with the CSM attached. The HTM performed the rose to 5Z°C (125°F). The manned SL-2 mission was i rilost thorough manned proyranl of observation of postponed while solutions to the OWS heat and pow- i solar flares to date, obtaininy some of the best er loss prob?ems were devised, equipment 9 coveraye avail able. kore men (nine) 1ived in Sky- constructed, and the crew trained in its installa- I lao than in any other space vehicle. The program tion. Three therrrial shields were prepared for t returned a wealth of scientific and phjsiol oyical possible use: The Skylab Parasol that could be ddta. Three crews traveled a total of 113.5 mil- deployed throuyh the Oh5 scientific airlock; a lion-kill (70.5 mill ion-sm), lived in space for 171.5 "twin-pole" shield that could be deployed by the days, and cornpl eted 2,476 n~annedorbits of the crew working outside the OMS; and a "sail" that iarth. Skylab returned han~~lesslyto Earth on 11 could be deployed by crew members standing in the July 1979, after coi~tpletiny34,181 orbits. open hatch of the SL-2 CSM. Meanwhile, ground I control lers combatted sritical internal temperatures by changing the attitude of the UWS in relation to the Sun by varying the systems configuration, while three con~pleteyurying/repressuri- zation cycles were performed to eliminate any toxic gases emanating froin material s within the OMS aue to the high temperatures. (S) SKY LAB (continued)

!" ssion Launch Launch NASA Site/ :;me Date/Ti me Vehicle Code -Pad RemarksIResul ts S~jlab 2 25 May 73 Saturn IB SL- 2 KSC LC-39 Due to the OMS problems, launch of SL-2 was post- 0900 EDT (AS-206) AS-206 Pad B poned f;-om 15 May to 20 May; then to 25 May. On CSM-116 the evening of 24 May, lightning struck the Mobile Service Structure surrounding the space vehicle, but tests showed no damage. The countdown began on time and progressed to lift-off with no un- Skylab 2 Astronauts scheduled holds. Stowage of the three thermal shields and their associated tools in the CM was Charles Conrad, Jr., Comnander performed during the countdown. Rendezvous of the ?sse?h P. Kerwi n, Science Pilot CSM with the OMS was accomplished on the fifth Patil J. Weitz, Pilot orbit. Prior to docking a flyaround of the OWS verified that one solar array wing was missing and the second was only partially deployed. An Skylab 2 Achievements attempt to dislodge the debris restraining the I wing while standing in the open CM hatch was un- First three-man crew to stay in space for 28 days. successful. Docking of the CSM with the Multiple First major repairs to an orbiting space station, Docking Adapter (MDA) was completed on the fifth p~vingthat men can accomplish more than pro- attempt. On Mission Day 2 (MD-2) the crew entered grammed machines in space. First occupancy of a the OWS and deployed the parasol thermal shield U.S. space station, and operation of its scientific through the scientific airlock. Temperatures instrlments and 1ife support systems (including ob- irrunediately began dropping. On MD-3 the crew I started activating the OWS. Experiments began on I taining extensive physiological measurement data). MD-5 and continued through MD-25. On MD-14 astronauts Conrad and Kerwin opened the Airlock Module hatch and, standing on the outside of the ON, succeeded in dislodging the debris and extending the wing, restoring electrical power to the OWS. On the 28th day, the crew re-entered the CM, undocked, and returned to Earth, landing in the Pacific southwest of California. Based on their success in overcoming the OWS problems and general mission performance, the SL-1/SL-2 missions were desi gnated as successful. (S) SKY LAB (ci- Mission Launch Launch NASA Si te/ Name DatefTime Vehicle -Code -Pad Remarks/Resul ts Sky1 ab 3 28 Jul 73 Saturn IB SL-3 KSC LC-39 Prel aunc h checkcut and countdowri proceeded nor- 0711 EDT (AS- 20 7 ) AS-207 Pad B mally to an on-time liftoff. Shortly after dock- CSM-117 ing and entering the OWS all three crew members experienced motion sickness, causing a delay in activating the OMS equipment. On 2 Aug apparent Skvlab 3 Astronauts failure of two of four thruster quadrants of the service module reaction ccntrol system raised the Alan L. Bean, Commander possibility of an early end to the mission, or of Owen K. Garriott, Science Pilot inability of CSM to safely deorbit. KSC launch Jack R. Lousma, Pilot crews were placed on a 24-hour seven-day-week schedule to ready SL-4 space vehicle for rescue, but a decision was made to continue the mission. Skyl ab 3 Achievements Working outside Workshop, astronauts extended "twi n-pol e" thermal shield to rep1 ace "parasol " 1 Established new record for manned space flight, deployed by SL-2 crew. Skylab 3 crew then contin- I more than double the 28 days of Skylab 2 crew. ued extensive series of experiments, particularly I Proved that signs of physical deterioration experi- of unanticipated solar activity, and mission was 1 enced by first Sky1 ab crew reversed themselves over extended to 59 days to make up time lost earlier. i I a longer period, except for bone calcium loss. As- Although SL-4 vellicle had been brought to launch I I tronauts obtained excellent scientific results readiness if needed, CSM-117 systems functioned i using ATM, EREP, and other instruments. Proved duri ng deorbit maneuvers and comnand module 1anded i long-term viability of both space station and as- in Pacific Ocean off southern California. (5) tronauts. Ii SKY LAB (continued)

Mission Launch Launch NASA Name Date/Time Vehicle -Code -Pad Remarks/Resul ts Skylab 4 16 Nov 73 Saturn IB SL-4 KSC LC-39 The SL-4 checkout revealed hair1ine cracks on the 0901 EST (AS-208) AS-208 Pad B tailfins of the S-IB rocket. They were changed (SM-119) out on the pad, delaying the launch by several days. Some other internal cracks were ruled not serious. Food bars were added to the food supply to permit a long mission if advisable. The actual Skylab 4 Astronauts launch operation went smoothly, and rendezvous occurred on time. Some replacement parts were in- Gerald P. Carr, Comnander stalled in Skylab, then the crew settled down to Edward D. Gibson, Science Pilot establish a manned space flight record for the William R. Pogue, Pilot U.S. and at that time for the world. The astronauts were given so much work to do by ground controllers they had little time to rest, and at Skylab 4 Achievements first made mistakes. When the workpace was slowed their efficiency improved, and in the end they did Proved man can survive and function indefinitely even more work than was programned. They traveled in space, if the bone calcium loss problem can be 55.5 mil1 ion-km (34.5 mil1 ion-sm) , during a mis- solved. Establ ished the value of 1ong-term manned sion lasting 84 days, one hour, and 16 minutes. scientific instriin~entsoperating above the atmo- This crew achieved one of the most desired scien- sphere. Paved the way for permanent manned space tific objectives, full photographic coverage of a stations in orbit around the Earth, or other long- solar flare from its beginning to its full size. duration space missions. They a1 so studied the comet Kohoutek fran above the atmosphere for 156 hours, obtaining the best record of its type to date. They performed scientific experiments for 1,563.2 hours, more than the first two crews combined. The astronauts were a1 so in better physics1 conditioo afterward, except for bone calcium loss, icdicating long duration flights are practical. This flight set many records for the U. S. which wi11 probably last for years to come. (S) APOLLO-SOYUZ TEST PROJECT

ASTP

Missi on Launch Launch NASA Site/ Name DateITime Vehicle -Code -Pad RemarksJResul ts Apol 1o- 15 July 75 Saturn IB ASTP KSC LC-39 First international manned space flight. This Soyuz Test 1550 EDT (AS-210) AS-210 Pad B five-year program was conducted to establish space Project CSM-111 rescue techniques for the U.S.A. and U.S.S.R., conduct scientific experiments, and study the feasibility of more ambitious joint programs in the future. The Soyuz lifted off first, at 0820, and ASTP Astronauts entered orbit. The countdown went smoothly at KSC, and liftoff was on time. The astronauts Thomas P. Stafford, Commander turned the Apollo spacecraft around in space and Donald K. Sl ayton, Docking Module Pilot docked with the docking module attached to the Vacce D. Brand, Command Module Pilot SIV-B stage. The Apollo then "chased" the Soyuz in orbit, docking with it at rendezvous July 17 at E (U. S. S. R. Cosmonauts 1210 EDT. The two spacecraft remained attached, [ A1 eksey A. Leonov, Commander conducting joint experiments in space, sharing 1 Val eriy N. Kubasov, Fl ight Engineer) each other's accommodations and meal s, and hol ding 1 press conferences with the news media of the I world, until undocking at 0812 on July 19. The L iI ASTP Achievements spacecraft then docked again, for practice, at 0834 and separated at 1127 for the last time. F irst major cooperation between only two nations Soyuz landed in Russia at 1848 EDT July 21. The engaged in manned space flight. First meeting of Americans stayed aloft for three more days, con- I two manned spacecraft of different nations in ducting a series of experiments. They landed in i space, first docking, and first visits by astro- the Pacific Ocean at 1718 EDT. The astronauts nauts and cosmonauts into the others' spacecraft. failed to turn on the Earth Landing System at the Established workable joint docking mechanisms, correct time, resulting in some gas entering the taking first steps toward mutual rescue capability spacecraft, but the crew were not hurt. The ASTP of both Russian and American manned missions in proved that American and Russian space programs i space. could cooperate and perform joint missions in space. All major objectives were achieved. (S) APPENDIX A

SUMMARY OF LAUNCHES PRIOR TO OCTOBER 1958 IN SPACE PROJECTS LATER TRANSFERRED TO NASA

On 1 October 1958, coincidental with the official activation of the National Aeronautics and Space Administra- tion, President Eisenhower issued Executive Order 10783. This order transferred jurisdiction to NASA, fran the Department of Defense' s Advanced Research Projects Agency, over several space programs that were a1 ready we1 1 under way. Included among these were: the Naval Research Laboratory's International Geophysical Year sate11 i te program (Vanguard), initiated 9 September 1955; the Army Ball istic Missi 1e Agency's sate1 lite launching project (Explorer), authorized to proceed on 8 November 1957; and certain lunardprobes under the direction of the Air Force Ballistic Misc'le Division (forerunner of the Pioneer space probes), officially announced on 27 March 1958.

This Appendix lists the launching attempts in these programs that occurred prior to 1 October 1958. Launching attempts made subsequent to 1 October 1958, as a part of these and other space programs transferred to NASA by Exec- utive Order 10783, are contained in the main portion of this report. SUMMARY OF LAUNCHES PRIOR TO OCTOBER 1958 IN SPACE PROJECTS LATER THANSFERRED TO NASA (A1 1 launches were from Cape Canaveral)

?Ii ssion Launch Launch Intntl. Site/ Name Date/Time Vehicle Desi g. Pad Remarks/Resul ts

Vanauard 6 Dec 57 Vanguard - - 18A The first attempt by the Naval Research Laboratory Test 1145 EST TV-3 (NRL) to orbit a test sate1 1 ite using a Vanguard Vehicle rocket with all three stages powered was unsuc- ! cessful when a mechanical failure in the propulsion system caused it to burst into flarnes two seconds after it was fired, after lifting about 15 cent irneters (six inches) off the pad. (Previous Vanguard project launches at Cape Canaveral were launch vehicle development tests, not orbital attempts.) (U)

Vanguard 5 Feb 58 Vanguard - - The second trial firing of a Vanguard test satel- Test 0233 EST TV-3BU lite failed as defects in the first stage engine Vehicle control system caused the rocket to veer to the (Backup) right and break in two about 50 seconds after launch, 4.5 km (4 sm) up. The rocket was destroyed by the range safety officer. (U) SUMMARY OF LAUNCHES PRIOR TO OCTOBER 1958 IN SPACE PROJECTS LATER TRANSFERRED TO NASA (All launches were from Cape Canaveral) (cont inued) i Mission Launch Launch Intntl. Site/ Name Dat e/T ime Vehicle Desig. -Pad Remarks/Reswl ts Vanguard 1 17 #ar 58 Vanguard 1458 18A Vanguard 1, the second U.S. satellite, an a1 uminum 0725 EST TV-4 Beta 1 test sphere 16.25 centimeters (6.4 inches) in di- (casing) ameter and weighing 1.47 kg (3.25 lb), was suc- 1958 cessful ly launched into orbit, together with its Beta 2 22.6-kg (50-lb) carrier rocket casing, just "two (sate11 ite) years, six months and eight days after initiation of the project from scratch," as pointed out by John P. Hagen, NL program director. Initial perigee was 358 km (409 sm), and apogee was 3,948 km (2.453 sm), at an inclination to the equator of 34-26". Geodetic observations of its stable orbit determined that Earth is sl ightly pear-shaped. Although not actually instrumented, two transmitters were carried and temperatures could be de- duced from changes in their radio frequencies. Satellite transmitted data until May 1964 and is still in orbit. Current orbital parameters are: 3,917 x 666 km (2,534 x 414 sm), incl ination 34.3", period 134 minutes. (S)

I Vanyuard 28 Apr 58 Vanguard -- Attempt to orbit an instrumented satellite 50.8 Test 2150 EST TV -5 centimeters (20 inches) in diameter and weighing i Vehicle 9.75 kg (21.5 lb), using a Vanguard test vehicle. i Satell ite instruments were i ntended to record X-rays, temperatures, and meteor data. Fai 1ure of the third stage engine to ignite due to faulty wiring in the ignition circuit resulted in the launch vehicle being unable to attain orbital speed. Sate1 lite burned up on re-entry; launch vehicle impacted 2,414 km (1,500 sm) downrange. (U c, CT, '0 our. Q)d V)C *Q)ul3, 3.rd aJ L.r aJ+J L L wx .)a+ .r tA- aJ Q)., Q) UN 1.r LL. 3 U,c,Y- L a-m~ SUMMARY OF LAUNCHES PRIOR TO OCTOBER 1958 IN SPACE PROJECTS LATER TRANSFERRED TO NASA (A11 1aunches were from Cape Canaveral ) (cont inued)

Mission Launch Launch Intntl. Site/ Name DatelTime Vehicle Desig. -Pad RemarksIResul ts Vanguard 26 Sep 58 Vanguard - - 18A An abortive attempt occurred on 17 September, in Sate1 1 ite 1038 EST SLV-3 which the vehicle 1 ifted about 2.5 centimeters Launch (one inch) off the launch pedestal, +hen settled Vehicle back into position when uneven release of ground- disconnect plugs transmitted a spurious shutdown signal to the first stage engine. Liftoff was normal on 26 Sep, and all stages of the Vanguard SLV-3 fired. However, second stage low performance, possibly due to corrosive particles partially clogging fuel tank piping, resulted in the satellite not attaining sufficient speed to maintain an orbit. Although not verified by tracking data, the sate1 1ite may have made at least one complete orbit at an a1 titude 426 km (265 sm) before falling into the Indian Ocean, approximately 14,806 km (9,200 sm) from the launching site. The satellite contained instruments to measure cloud cover, and carried a tape recorder to store data for a later release on comnand fran a ground station. (U) SUMMARY OF LAUNCHES PRIOR TO OCTOBER 1958 IN SPACE PROJECTS LATER TRANSFERRED TO NASA (A1 1 1aunches were from Cape Canaveral ) (continued)

I EXPLORER Mission Launch Launch Intntl . Site/ Name Date/Time Vehicle Decig. -Pad Rernarks/Resul ts Explorer 1 31 Jan 58 Juno 1 1958 26A Explorer 1, the first A-nerican satellite, was suc- 2207 EST (Jupiter C) Alpha cessfully launched into an orbit with an apogee of RTV-4 2,531 km (1,573 sm) and a perigee of 360 km (224 srn). The satell i te, 203 centimeters (80 inches) long and 15 cm (6 inches) in diameter, was an in- tegral part of the launch vehicle's fourth stage motor case, and weighed 14 kg (30.8 lb). Its payload, weighing 8.22 kg (18.13 Ib) (including two radio transmitters and their mercury batteries), was developed by Iowa State University under the direction of James A. Van A1 len, and contained in- stt-uments to measure cosmic rays, micrometeor im pact , and internal and external temperatures. Analysis of data returned by Explorer 1 resulted in the discovery of belts of radiation surrounding the Earth (the Van Allen belts). The satellite transmitted data until 23 May 1958, and re-entered Earth's atmosphere 31 March 1970. The Juno I 1aunch vehicle, developed by the Army Ball istic Missile Agency with the assistance of the Jet Pro- pulsion Laboratory, consisted of a three-stage Jupiter C Composi te Re-entry Test Vehicle modi f ied by the addition of a live, solid propellant fourth stage. (Of the six Juno Is constructed, three successfully orbited satel 1ites.) (S) SUMMARY OF LAUNCHES PRIOR TO OCTOBER 1958 IN SPACE PROJECTS LATER TRANSFERRED TO NASA [All launches were from Cape Canaveral) (continued)

Mission Launch Launch Intntl. Site/ Name Date/Time Vehicle Desi g. -Pad Remarks/Resul ts Explorer 2 5 Mar 58 Juno I -- 26A An attempt to orbit the Explorer 2 satellite was 1327 EST (Jupiter C) unsuccessful when the fourth stage of ?he Juno I KTV-5 launch vehicle failed to ignite, resulting in insufficient speed to attain orbital velocit). The satellite probably burned up on re-entering the atmosphere, before falling into the Atlantic near Trinidad, 3,058 km (1,900 sm) frm the launch site. (U)

Expl orer 3 26 Mar 58 Juno I 1958 Explorer 3, the third U.S. IGY satellite, was suc- 1230 EST (Jupiter C) Gamma cessfully launched into an orbit with an apogee of RTV -6 2,810 km (1,746 sm) and a perigee of 195 krn (121 sin). The satellite instrumentation was similar to that of Explorer 1, with the addition of a tape recorder feature. On 1 May 1958, Dr. James A. Van Allen announced that scientific findings from Ex- plorers 1 and 3 disclosed an unexpected band ~f high-intensity radiation extending from 966 km (600 sm) above Earth to possibly an 12,875 kn (8,000 sm) altitude. The Explorers a1 so showed that the atmosphere at 354 km (220 sm) was denser than predicted, that satellite temperatures would not be too great for humans, and that cosmic dust was only a small hazard to space travel. Explorer 3 transmitted data until 16 June 1958 and re- entered the atmosphere 28 June 1458. (S) SUPMARY OF LAUNCHES Pdidk -i! :;,~t:.cR 1958 IN SPACE PROJECTS LATER TRANSFERRED TO NASA (All lau~cneswere from Cape Canaveral ) (con~inued)

Mission Laurtch Launch intntl. Site/ Fi ame DatelTime Vehicle -Desi g. -Pad RemarksIResul ts Explorer 4 26 Jul 55 Juno I 1958 5 The fourth U.S. IGY satell ite was successfully 1000 EST (Jupiter C) Epsilon launched by a Juno I into an orbit with an aGeqee RTV -7 of 2,221 km (1,380 sm) and a perigee of 262 km (163 sni). Instrume~tationwas designed to nieh3rare corpuscular radiation and consisted of two Geiyer- ihel ler counters and two scintillator counters. Two radios, powered b2 mercury batteries, transmitted informaticn simultaneously and continuous- ly, utilizing the satellite's stainless steel skin as antennas. Explorer 4 transmitted data until 6 October 1958 and re-entered the atniosphere on 23 October 1959. (S)

Explorer 5 24 Aug 58 Juno I Ttie fifth orbital attempt by the Aw Ballistic 0017 EST (Jupiter C) Missile Agency, using the Juno 1 launch vehicle, RTV -8 was unsuccessful. Liftoff was normal , but after separation of the first stage, its residual fuel carried it forward to bump and deflect fran course the remaining three stages. They fired nomially, but failed to carry the satellite into orbit. The flight lasted 659 seconds, on a path northeast from Cape Canaveral . The sate11 i te carried i nstru- ~~ientationdesigned to measure the Van Allen radiation belts. (U)

A-a SUMMARY OF LAUNCHES PRIOR TO OCTORER 2958 IN SPACE PROJECTS LATER TRANSFERRED TO NASA (All 1auncr~es were from Cape Canaveral ) (continued)

P IONEER Mission Launch Launcil Intntl. Site/ Name Date/Time Vehicle Desi g. -Pad Remarks/Resul ts Pioneer 17 Aug 58 Thor-Abl e- -- 17A The first attempt by the Air Force Ballistic Mis- 0718 EST 1 sile Division to launch a lunar probe, using the three-stage Thor-Able launch vehicle, was unsuccessful due to a failure in the first-stage engine. Liftoff was normal, but an explosion ripped the vehicle apart after 77 seconds of flight, at an a1 titude of about 16 km (10 sm). The mission had been designed to put 18 km (40 lb) of instru- i~~entsin an orbit around the Moon, to take pictures of the backside. In addition to the scan- ning devices, the probe contained a magnetometer,

a meteoroid co ' tr, and thermometers. Had the mission been ,,:cessful, the probe wuld have been given the designation of Pioneer. (II) APPENDIX B

Ct4KONOLOGICAL INDEX OF LAUNCHES

-Date Page Mission -Date

1960 (continued)

THOR/ABLE-1 Pioneer 1 ETR 10-11-58 JUNO 1-49 Bsacon ETR 10-22-58 THOR/ABLE-2 Pioneer 2 ETR 11-08-58 JUNO 11-11 Pioneer 3 ETR 12-06-58 JUPITER-13 Bioflight 1 ETR 12-13-58 MERCURY/REGSTONE-2 Mt-2 ETR 01-31-61 JUNO 11-19F Explorer ETR 02-24-61 MERCURY/ATLAS-67D MA-2 ETR 02-21-61 MERCURY/REDSTONE-5 MR-BD ETR 03-24-61 VANGUAkD-4 Vanguard 2 ETR 02-1 7-59 DELTA-4 Explorer I0 ETR 03-25-61 JUNO 11-14 Pioneer 4 ETR 03-03-59 MEIJCURY/ATLAS-100D MA-3 ETR 04-25-31 VANGUARD-5 Vanguard ETR 04-13-59 JUNO ll-19E Explorer 11 f3R 04-27-61 JUPITER-18 Bioflight 2 ETR 35-28-59 MEFCURY/REDSTONE-7 MR-3 ETR 05-05-61 VANGUARD-6 Vanguard ETR 06-22-59 JUNO l I-19G Explorer ETR 05-24-61 JUNO 11-16 Explorer ETR 07-16-59 DELTA-5 TI ROS-3 ETR 07-12-61 THOR/ABLE-3 Explorer 6 ETR 08-07-59 *RCURY/REDSTONE-8 MR-4 ETR 07-21-61 JUNO 11-198 Beacon ETR 08-14-59 DELTA-6 Explorer 12 ETR 08-15-61 ATLAS-IOD Big Joe ETR 04-09-59 ATLAS/AGENA-1 Ranger 1 l3R 08-23-61 VANGUARD-7 Vanguard 3 ETR 09-18-59 MEFCURY/ATLAS-880 MA4 ETR 09-13-61 JUNO 11-194 Explorer 7 ETR 10-13-59 SATURN SA-1 ETR 10-27-61 ATLAS/ABLE-I Pioneer ETR 11-26-59 MERCURY/SCOUT MS-I ETR 11-01-61 ATLAS/AGENA-2 Ranger 2 ETR 11-18-61 MERCURY/ATLAS-93D MA-5 ETR 11-29-61

I THOR/ABLE-4 Pioneer 5 ETR 03-1 1-60 I JUFK) 11-19C Explorer ET2 03-23-60 1 THOR/ABLE-5 TIROS 1 ETR 04 -0 1-60 AVT-I Big Shot 1 ETR 01 -15-62 DELTA-1 Echo ETR 05-13-60 ATLAS/AGENA-3 Ranger 3 ETR 01-26-62 MERCURY/ATLAS-50D MA-1 ETR 07-29-60 DELTA-7 TIROS 4 ETR 02-08-62 I1 I DELTA-2 Echo 1 ETR 06-12-60 MERCURY/ATL AS- 109D MA6 ETR 02-20-62 I ATLAS/ABLE-2 Pioneer ETR 09-25-60 DELTA-8 'JSO 1 ETR 03-07-62 JUNO 11-190 Explorer 8 ETR 1 1-03-60 ATLAS/AGENA-4 Ranger 4 ETR 04-23-62 MERCURY/REDSTONE-I .*-I It ETR 11-2160 SATURN 9-2 ETR 04-25-62 DELTA-3 TIROS 2 ETR 11-23-60 DELTA-9 Ariel 1 ETR 04-26-62 ATLAWABLE-3 Pioneer ETR 12-15-60 CENTAUR 1 ETR 05-98-62 APPENDIX B

CHRONOLOGICAL INDEX OF LAUNCHES Mission -Date Page Mission -Date

1964 (continued)

MERCURY/ATLAS-107D MA-7 ETR 05-24-62 DELTA-24 BE-A ETR 03-19-64 DELTA-I0 TIROS 5 ETR 06-19-62 TITAN II GLV-1 Gemini 1 ETR 04-1,-64 DELTA-I1 Telstar 1 ETR 07-10-62 ATLAS-2630 FIRE 1 ETR 04-14-64 4VT-2 Big Shot 2 ETR 07-18-62 SATURN I SA-6 ETR 05-28-64 ATLAS/AGEhJA-5 Mar iner 1 ETR 07-22-62 CENTAUR-3 ETR 06-30-64 ATLAS/A;ENA-6 Mariner 2 ETR 08-27-62 ATLAS/AGENA-9 Ranger 7 ETR 07-28-64 DELTA-12 TlROS 6 ETR 09-18-62 DELTA-25 Syncom 3 ETR 08-19-64 ;+OR/A;ENA-1 A l ouette 1 hTiT;i 10-29-62 MOR/AGENA-3 Nimbus 1 WTT? 08-28-64 PELTA-13 Explorer 12 ETR 10-02-62 ATLAS/AGENA-10 OGO I ETR 09-04-64 '-!rRCURY/ATLAS-I13D MA-6 ETR 10-03-52 SATilRN I SA-7 ETR 09- 16-64 ATLAS/PSSERA-7 Ranger 5 ETR 10-18-62 DELTA-26 Explorer 21 Em 10-03-64 DELTA-14 Explorer 15 OR 10-27-62 ATLAS/AGENA-11 Mariner 3 EFR 1 1-05-64 SATURN SA-3 ETR 11-16-62 ATLP.S/AGENA- 12 Mar iner 4 ETR 11-28-64 DELTA-15 Relay 1 ETP 12-13-62 CENTAUR-4 Surv. Mass tbdel ETR 12-11-64 DELTA-27 Explorer 26 Em 12 '1-64

DELT4-16 Syncm : ETg 02-14 -43 sAT~~PNSA4 ETR 03-28-63 TITAN 11 GLV-2 Gemini 2 ETR 01-1 9-65 aKLih-: 7 Cxp lorer : 7 ETR 04-02-63 2CLTA-28 TlROS 9 ETR 01-22-65 DL t-13 els star-2 FTk 22-07-63 ':ELTA-29 OSO 2 ETR 0243-65 MtfiCURY 'A ' -6-1 33D '4.4-3 EiR 35-15-63 ATURN I SA-9 (Pegasus 1) ETR 02-16-65 DELTe4-i9 TlROS 7 ETR 06-19-63 ATLAS/AGENA-13 Rznger 8 ETR 02-1 7-65 DELTA-20 Syncom 2 FTR 07-26-63 CENTAUR-5 Surv. Dynamic Mod. ETR 03-02-65 7ELiA-2 1 Explorer 19 ETR 11-26-63 ATLAS/ASENA-I4 Ranger 9 ETR 03-21-65 ;Ehli4Uk-2 ETR 1' -27-63 TIT4N II GLV-3 Gemini 3 ETR 05-23-65 Di-TA-22 TIRrS 8 ETR :2-21-63 DELTA-30 Early 6i-d 1 ETR 04-06-65 ATLAS-264D FIRE 2 ETR 05-22-65 SATUfW I S4-8 (Pegasus 2) ETR 95-25-65 CELT:-31 Exp'xer 28 ETR 05-29-65 TITAN II GLV-4 Gemini 4 ETR 06-03-65 DELTA-23 Relay 2 ET9 01-21-64 DELTA-32 T14Z 10 EN07-01-65 SATURN SA-5 ETR 01 -29-64 SAT.!QN I SA-I0 Pegas~s3) ETR 07-30-65 TtiWAGENA-2 FC~Q2 dTR 01-25-64 C,\T4'JR-6 Surv. Dynamic Mod. ETH 03- 11-65 ATLAS/AGEN4-8 ?anger 6 ET9 01-30-64 TITAN !I XV-5 :mini 5 ETR 08-21-65 APPENDIX B

CHRONOLOGICAL INDEX OF LAUNCHES

Mission Date Page Mission Date - Page

1%5 (continued) 1966 (conTinued)

DELTA-33 OSO-C ETR 08-25-65 TITANIIGLV-10 Gemini10 ETR07-18-66 THOWAGENA-4 OGO 2 KIT? 10-14-65 ATLAS/AGENA-17 Lun. (kb. 1 ETR 08-10-66 ATLAS TLV-5301 Gemini 6 ETR 10-25-65 DELTA-40 Pioneer 7 ETR 08- 17-66 Target Veh ic l e ATLAS TLV-5306 Gem in i 11 ETR 09-12-66 DELTA-34 Explorer 29 (GEOS 1) ElR 11-06-65 Target Vehicie TWAGENA-5 Alouette 2 6 WTR 11-28-65 TITAN II GLV-11 Gemini 11 ETR 09-12-66 Explorer 31 SATUW IB AS-202 ETR 08-25-66 TITAN 1.1 GLV-7 Gemini 7 ETR 12-04-65 CENTAUR-7 Surveyor 2 ETR 09-20-66 TITAN II SLV-6 Gemini 6A ETR 12-15-65 DELTA-41 ESSA 3 WTR 10-02-66 DELTA-35 Pioneer 6 ETR 12-16-65 CENTPUR-9 Surv. Mass Me1 ETR 10-26-66 DELTA-42 lntelsat II F-1 ETR 10-26-66 ATLAS/AGENA-18 Lun. (Xb. 2 ETR 11-06-66 ATLAS TLV-5307 Gemini 12 ETR 11-11-66 Target Vehicle DELTA-36 ESSA 1 ETP. 02-03-66 TITAN I1 GLV-12 Gemini 12 ElR 11-11-66 SATURN IB AS-201 ETR 02-26-66 ATLAS/AGENA-19 ATS 1 ETR 12-06-66 DELTA-37 ESSA 2 ETR 02-28-66 DELTA-43 Blosatell ite 1 Em 12-14-66 ATLAS TLV-5302 Gemini 8 ETR 03-16-66 Target Veh ic le TITAN I1 GLV-8 Geminl 8 ETR 03-1 6-66 C ,. AUR-8 Surv. Mass bbdel ETR 04-07-66 ATLAS/AGENA-15 OAO 1 ETR 04-08-66 DELTA-44 lntelsat II F-2 ETR 01-11-67 THOWAGENA-6 Nimbus 2 WTR 05-15-66 DELTA-45 ESSA 4 bdTR 01 -26-67 ATLAS TLV-5303 Gemini 9 ETR 05-17-66 ATLAS/AGENA-20 Lun. Orb. 3 ETR 02-04-67 Target Vehicle DELTA-46 OSO 3 ETR 03-08-67 DELTA-38 Explorer 32 ETR 05-25-66 DELTA-47 I ntelsat I I F-3 ETR 03-22-67 CENTAUR-I0 Surveyor 1 ETR 05-30-66 ATLASIAGENA-21 ATS 2 ETR 04-05-67 4TLAS TLV-5304 Gemini 9A ETR 06-01-66 CENTAUR-12 Surveyor 3 ElR 04-1 7-67 Augmented Target DELTA-48 ESSA 5 WTR 04-20-67 TITAN II SLY-9 Gemini 9A ETR 06-03-66 ATLAS/AGENA-22 Lun. Orb. 4 ETR 05-04-67 ATLAS/AGENA-16 OGO 3 ETR 06-06-66 DELTA-49 Explorer 34 UTR 05-24-67 THOS/AGENA-7 PAGEOS 1 WTR 06-23-66 ATLAS/AGENA-23 Mariner 5 En 06- 14 -67 DELTA-39 Explorer 33 ETR 07-01-66 CENTAUR-11 Surveyor 4 ETR 07-14-67 SATURN 18 SA-203 ETR 07-05-66 DELTA-50 Explorer 35 ETR 07-19-67 ATLAS TLV-5305 Gemini 10 ETR 07-18-66 MOR/AGENA-8 OGO 4 07-28-67 Target Vehicle ATLAS/AGENA-24 Lun. Orb. 5 ETR 08-01 -67 APPENDIX C

CHRONOLOGICAL INDEX OF LAUNCHES

% Mission -Date Pagc Mission Date hd!?

1%7 (continued) 1969 (continued)

DELTA-51 Biosatellite 2 ETR 39-07-67 DELTA-65 lSlS 1 WTR 01-28-69 CENTAUR-13 Surveyor 5 ETR 09-08-67 DELTA-66 lntelsat Ill F-3 ETR 02-05-69 DELTA-52 lntelsat I I F-4 ETR 09-27-67 CENTAUR-20 Mariner 6 ETR 02-24-69 DELTA-53 359 4 ETR 10-18-67 DELTA67 ESSA 9 ETR 02-26-69 ATLAS/ASENA-25 ATS 3 ER 11-05-67 SATUW V AS-504 Apo l l o 9 E?R 03-03-69 CENTAUR-14 Surveyor 6 tTR 11-07-67 CENTAUR-19 Mariner 7 ETR 03-27-69 S4TURN V AS-501 Apollo 4 ETR 11-09-67 THOR/AGENA-10 Nimbus 3 13 WTR 04-13-69 DELTA-54 ESSA 6 WiR 11-10-67 EGRS 13 7ELTA-55 Pioneer C 5 TT2 1 ETR 12-13-67 SATURN V AS-505 Apollo 10 ETR 05-18-69 DELTA-68 Inte! sat l I l F-4 ETR 05-21 -69 THOR/AGENA-11 OGO 6 WTR 06-05-69 DELTA-69 Explorer 41 WlT7 06-21-69 DELTA-70 Biosatellite 3 ETR 06-28-69 I CENTAUR-15 Surveyor 7 ETR 01 -07-68 SATURN V AS-506 Apol lo 1 1 ETR 07- 16-69 i DELTA-56 GEGS 2 WTR 01-11-68 DELTA-71 lntelsat l1l-E ETR 07-25-69 I SATIIRN IB 6-294 Fpol 13 5 ETR 01-22-68 DELTA-72 OSC 6 ETR 08-09-69 t ! P.TLtS/AGENA-2i CG0 5 ETf? OWN-68 CENTAUR-18 ATS 5 ETR 08-12-69 08-27-69 1 iATVRN V A,-5'2 Apo! lo 6 ETR 04 -04-68 DELTA-73 Piweer-E 6 ETR I THOR/AGE?JA-9 N imbus B WTR 05-18-68 TETRC I 1 DE1 TA-57 Exp I orsr 38 'rlrR 07-04-68 SATURN V AS-507 Apol lo 12 ETR 08-10-68 DELTA-74 Skynet 1 i CEYTAUH-17 ATS 4 I DELTA-53 ESSA 7 WR 38-16-68 UELTA-59 ' r tb. l sat I I I -A ETR 09-1 8-68 SAT'jRN It3 G-205 Apollo 7 FTR 10-1 1-68 UELTA-60 Pioneer 9 & ET'? 11-08-61! TETIi 2 DELTA-75 l ntel sat I 1 1 F-6 ETR 01-14-70 DELTA-61 HEOS 1 ETR 12-05-68 DELTA-76 ITOS 1 5 WTR 01-23-70 I SENTAUR-16 3h3 2 ETH 12-07-68 OSCAR 5 3EtTA-62 ESSA 8 dTR 12-15-68 Tki!IR/AGENA-12 SERT 2 WTR 02-03-70 3EifA-63 l nte l sat I I I F-2 ETR 12-18-68 MLTA-77 tiATOSAT 1 -EiR 03-20-70 SATURN V AS-503 Apolio 8 ETR 12-21-68 THOR/AGENA-13 Nimbus 4 6 WTR 04-08-70 TOP0 1 SATURN il 95-508 4pollo 13 ETR 04- 11-70 ELTA-79 Intelsat l I1 F-7 ETR 04-22-70 DELTA-79 lntel sat l i l F-8 ETR 07-23-70 3ELTA-64 OSC 5 XLTA-80 Skynet 2 35 08- 19-70 APPENDIX B

CHRONOLOGICAL INDEX OF LAUNCHES

Mission -Date Page Mission -Date

1970 (continued) 1973

CENTAUR-21 OAO-B ETR 11-30-70 CENTAUR-30 Pioneer 11 ETR 04-05-73 DELTA-81 NOAA 1 WTR 12-11-70 DELTA-94 An ik 2 ETR 04-20-73 SAT.'.% V AS-513 Skylab 1 ETR 0514-73 SATURN 18 6-206 Sky lab 2 ETR OS2573 DELTA-95 Explorer 49 ETR 06-10-73 DELTA-% ITOS-E WTR 07- 16-73 CENTAUR-25 lntelsat IV F-2 ETR 0 1-25-7 1 SATURN IB 6-207 Sky lab 3 ETR 07-28-73 SATURN V AS--509 Apol 10 I4 ETi? 01-31-71 CENTAUR-31 Intelsat IV F-7 ETR 08-23-73 DELTA-82 NATOSAT 2 EIR 02-02-71 DELTA-97 Explorer 50 ETR 10-25-73 DELTA-83 Explorer 43 ETR 03-13-71 CENTAUR-34 Mariner 10 ETR 11-03-73 DELTA-84 lSlS 2 UlR 03-31 -7 1 DELTA-98 NOM 3 UTR 11-06-75 CENTAUR-24 Mariner 8 ETR 05-08-71 SATURN IB 6-208 Sky lab 4 ETR 11-16-73 CENTAUR-23 Mariner 9 ETR 05-30-71 DELTA-99 Explorer 51 WTR 12-15-13 SATURN V AS-510 Apollo 15 ETR 07-26-71 DELTA-85 OSO 7 d TETR 4 ETR 09-29-71 DELTA-86 ITOS-B UlR 10-21-71 CENTAUR-26 l ntelsat IV F-3 ETR 12-19-71 DELTA- 100 Sky net l l-A ETR 01-18-74 i/C-1 Proof Flight ETR 02- 11-74 .DELTA-IOI Westtr 1 ETR 04- 13-74 DELTA-102 SMS 1 ETR 05- 17-74 CENTAUR-28 lntelsat IV F-4 ETR 01-22-72 TITAN Ill< ATS 6 ETR 05-30-74 DELTA-87 HEOS 2 WTR 01-31-72 DELTA-I03 Westar 2 ETR 10- 10-76 CENTAUR-27 Pioneer 19 OR 03-02-72 DELTA- 104 NOM 4, OSCAR 7 d WlR 11-15-74 DELTA-88 TD 1 WTR 03-11-72 Intasat SATURN V AS-511 Apollo I6 ETR 04-1&32 CENTAUR-32 lntelsat IV F-8 ETR 11-21-74 CENTAUR-29 lntelsat iV F-5 ETR 06-13-72 DELTA-I05 Skynet 3 ETR 11-22-74 DELTA-89 UWDSAT I UTR 07-23-72 T/C-2 tie 1 ios 1 ETR 12-10-74 CENTAUR-22 OAO 3 ETR 06-21-72 DELTA-106 Symphonic 1 Ell'? 12-1 8-74 DELTA-90 Exp lorer 47 ETR 09-22-72 DELTA-91 NOM 2 d OSCAR 6 Kt73 10-15-72 DELTA-92 An i k l ETR 11-99-72 SATURN V AS-5 12 Apo l lo 17 ETR 12-07-72 DELTA-93 Nimbus 5 WTR 12-10-72 DELTA-107 LAMISAT 2 WTR 01 -22-75 DELTA- 108 2 ETR 02-06-75 CENTAUR-33 Intelsat IV F-6 ETR 02-20-75 APPENDIX B

CHRONOLOGICAL INDEX OF LAUNCHES

Mission -Date Miss ion -Date

1975 (continued)

DELTA-109 GEOS 3 WTR 04-09-75 DELTA- 128 NATO 1 1 1-8 ETR 01-27-77 DELTA-I10 Anlk 3 ETR 05-07-75 DELTA-129 Palapa 2 ETR 03-10-77 CENTAUR-35 lntelsat IV F-l ETR 05-22-75 DELTA-I30 ESRO/Geos ETR 04-20-77 DELTA-1 11 Nimbus 6 WiR 06-12-75 CENTAUR-39 lntelsat IV-A F-4 ETR 05-26-77 DELTA-112 OSO 8 ETR 06-21-75 DELTA-131 GOES 2 ETR 06-16-77 SATURN 10 AS-210 Apol10-Soyuz ETR 07-15-75 DELTA-132 GMS ETR 07-14-77 Test Project CENTAUR-45 HEN) 1 ETR 38-12-77 DELTA- 1 13 COS-B WTR 08-08-75 T/C-7 Voyager 2 ETR 08-20-77 J/C-4 Viking 1 ETR 08-20-75 DELTA-133 S lRlO ETR 08-25-77 DELTA-114 Symphonic 2 ETR 08-26-75 TK-6 Voyager 1 ETR 09-05-77 T/C-3 Viking 2 ETR 03-09-75 DELTA-134 OTS 1 ETR 09-13-77 CENTAUR-36 intelsat IV-P. F-1 ETR 09-25-75 CENTAUR43 Intelsat IV-A F-5 ETR 09-29-77 DELIA-115 Exp1orr.r 54 WR 10-06-75 DELTA-135 l SEE 1 6 2 ETR 10-22-77 DELTA-I 16 GOES i ETR 10-16-75 DELTA- 136 METEOSAT ETR 11-22-77 DELTA-117 Explorsr 55 ETR 11-19-75 DELTA-137 Japan CS ElR 12-14-77 DELTA-118 RC9 SATCOM 1 ETR 12-12-75

1 L 1976 CENTAUR-46 l ntelsat IV-A F-3 ETR 01 -36-78 I T/C-5 Hel 10s 2 ETR 01-15-76 DELTA-138 IUE ETR 01-26-78 DELTA- 1 19 CTS ETR 01-17-76 CENTAUR-44 FLTSATCOM I ETR 02-09-79 I CENTAUR-37 i nte l sar I '4-I, F-2 ETP 01 -29-76 DELTA-139 LAWSAT 3 WTR 03-05-78 ! DELTA-120 Marlsat 1 ETR 02-19-76 CENTAUR-48 lntelsat IV-A F-6 ETR 03-31-78 1 DELT.9- 121 RCA SATCOM ?. ETii 03-25-76 DELTA-140 Japan BSE Ell? 04-07-78 DELTA-122 NATO Ill-A ETR 04-22-76 DELTA-141 OTS 2 ETQ 05- 1 1-78 CIELTA-123 LAGEOS KTR 05-04-76 CENTAUR-50 Pioneer Venus OR 05-20-78 CENTALTI-38 CWSTAR D- 1 ETR 05-13-76 Orbiter DELTA-124 Marisat 2 KlR 06-09-76 DELTA-142 GOES 3 ETR 06- 16-78 DELTA-125 Palapa I ETR 07-08-76 CENTAUR41 COMSTM 0-3 ETR 36-29-78 CENTAUR-40 COMSTAR D.2 ETR 07-22-76 DELTA-143 Geos 2 ETR 07-14-78 OELTA-126 NOAA 5 WTR 07-29-76 CEYTAUR-51 Pioneer Venus ETR 08-08-78 DELTA-127 Marisat 3 €TR 10-14-76 Hal t iprobe DELTA- 144 l SEE 3 ETR 08-12-78 DELTA-145 Hlmbus 7 ClTR 10-24-78 CENTAUR-52 HEN) 2 ETR 11-13-78 I- C1 CO~O\VIO Z$S1L2a

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-g :: t-. . OW.. 2% :: APPENDIX C

ALPHABETICAL INDEX OF LAUNCHES

Mission Page Mission

GEOS. See Geodetic Earth Orbiting SatellJte 6 B...... =...... bodynamTcs Exper imenta l Ocean Sate l- c...... I lte

Geostationary Y~teorolagicalSatellite (GMS).... lntelsat I (Early Bird)...... Geostationary Operational Environmental Satel l lte (GOES) lntelsat I I l...... F-1 (Lani Bird)......

MS. See Geostationary Veteorologlcal Satellite lntelsat !;I GOES. See Gwsta?ionary Operational Envlron- F-2...... --..* ...... mental Satellite F-3.me...... t1 ...... F-4...... -...... Sordo, See Bi.-i l igh; : F-6...... --* F-7...... IiEAO, Set! High Ener2v .%tronomy Observatory F-8...... -*

lntelsat IV F-I..."...... F-I..."...... HEOS. See Highly Eccentric Orbit Satellite F-2.m...e...... F-3...... e*. H igh Energy Astronomy Observatory (HEAO) F-4...... I...... ,...... F-5...... -- ...... 2...... -.... F-6...... **...... 3...... 1...... F-7...... *.. F-8...... Highly Eccentric Orbit SaT~ilite(HEOS) l...... *.*...... lntelsat IV-A z...... F-l...... F-2...... Improved TlROS Clperatlonal Sateillte (ITOS? F-3...... -. l...... e...... F--4...... *. ... a...V)...... - L.. : -z - (u

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