Apollo 8, Will Be the Second Manned Flight in the Apollo Program and the First Manned Flight on the Saturn V Rocket, the United States' Largest Launch Vehicle

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WO 2-4155 WASHINGTON,D .C .20546 TELS* WO 3-6925 FOR RELEASE: SUNDAY December 15, 1968 RELEASE NO: 68-208

: APOUO 8 P *'

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_-- a- I ' 7 . ... ^. (ACCESSIONNUMBER1 E ITHRUJ ? (CODE1 : / 3s (NASA CR OR TMX OR AD NUMBER) (CATEGORY8 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WO 2-4155 TELS* WO NEWS WASHINGTON,D .C. 20546 3-6525 FOR RELEASE: SUNDAY December 15, 1968 RELEASE NO: 68-208

FIRST MANNED LUNAR ORBIT MISSION

The United States has scheduled its first mission designed to orbit men around the Moon for launch Dec, 21 at 7:51 a.m. EST from the National Aeronautics and Space Administration's John F. Kennedy Space Center, Florida,

The mission, designated Apollo 8, will be the second manned flight in the Apollo program and the first manned flight on the Saturn V rocket, the United States' largest launch vehicle .

Crewmen for Apollo 8 are Spacecraft Commander Frank Borman, Command Module Pilot James A. Lovell, Jr. and Lunar Module Pilot William A. Anders. Backup crew is Commander Neil A. Armstrong, Command Module Pilot Edwin E. Aldrin, Jr. and Lunar Module Pilot Fred W. Haise, Jr.

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d lnisslon with the objective

nces. A lunar

t to a lunar

1 be carried out on a step-by-step "commit mean8 that deelarlons whether to continue Earth or to to an alternate mlsslon will b status of the spacecraft systems and crew.

A full duration lunar orbit mjlssion would Include ljP orbits around the Moon. Earth laadZng would take place some 147 hours after I * EST, D~C,27.

Earlier devel 61 Ap0110 Earth-orbital unmanned flight8 have qualifled all the spacecraft syaLema --it~clt~diWthe C nd module heat shield at lunar peturn speeds-and the Apollo 7 ten-day failurn-free October demonstrated that the spacecraft can opersrte for the lunar-misslon dumtion. -3-

Apollo 8 will g r? data to be used in early development of training, ground lation and crew inflight procedures for later 1

is at the beginning of the December ts, Therse windows hinge upon the face lighting conditions at the Moon and upon launch and December ooindow sloses Dec. 27. pens Jan. 18 and closes Jan. 24.

The misoJion will be launched from Complex 39A at the Kennedy Space Center on an azimuth varying from 72 to 108 degrees depending on the launch date and time of day of the launsh. The first opportunity aalh far liftoff at 7:51 a.m. EST Dec. 21 on an ~i~uthof 72 degresa. Launch of Apollo 8 will mark the first nned use of the Moonport. 1

The Saturn V launch vehicle with the Apollo spacec'raft on top stands 363 feet tall. The five first-stage engines of Saturn V develop a combined thrust of 7,500,000 pounds at liftoff. At igintion the space vehicle welghs 6,218,558 pounds .

Apollo 8 wlll be inserted into a 103 nautical mile (119 statute miles, 191 kilometers) Earth orbit.

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econd or third Earth orbit, the Saturn V in@will restart to place the space vehicle on a path to the Moon. The command anU service modules will stage and begin the translunar coast period of about 66 hours, A lunar orbit insertion burn Poith rvice propulsion engine! will place the apace- 60 x 170 nm (69 x 196 sm, 111 x 314.8 km) s1lipz;Ical lunar orbit which later ulll be circularized at

60 (69 sm, 111 km) a

8r injection burn of the third stage will place the ~~ac~crafton a free-return trajectory, so that if for aom mason no further maneuvers are made, Apollo 8 would sweep around the Moon and make a direct entry into the Earth's atmosphere at about 136 hours after liftoff and land in the Atlantic off the west coast of Africa. During the free-return trajectory, corrections may be mads using the spacecraft Reaction Control System.

Ten orbits will be3 made around the Moon while the cmw vigation and photography investigations. A tran earth in~~ctionburn with the service propulsion ngine will bring the spacecraft back to Earth With a direct atmospheric entry In the mtd-Paclflc about 147 hours after a Dec. 21 launch. Missions beginning later in the wlndow would be of longer duration, 8- mason the, orbit, a high-

"wobblea" In the Sp ft orbit. In network coupled onboa ehargen the arccuraoy of lunar orbit lunar nttssi

Another faclst of' o th a at lunar distanors will be t ft Ifled S-band ante ut f

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The high-gain antenna relays onboard television and high bit-rate telemetry data, but should it become inopera- tive, the command module S-band ormi antennas can relay voice cormnunications, low bit-rate telemetry and spacecraft commands from the ground ..

Apollo 8 will gather data on techniques for stabilizing spacecraft temperatures In deep-space operations by invssti- gating the effects of rolling the spaoecraft at a slow, fixed rate about Ita three axes to achieve thennal balance. The __/- Apollo 8 naission ~Illbe the first opportunity for in-depth testing of these techniques in long periods of sunlight a from the reflective influence of the Earth.

Any solar flares occurring during the mission will be monitored by Solar Pa~ticleAlert Network (SPA#) st around the worlU. Solar radiation and radiation in the Allen belt around *he Earth present no hazard,to the c Apollo 8 in the thlck-Aclnned commnd module. The anticipated dosages are less than one rad per BoELn, well below that of a thorough chest X-ray series.

Although Apollo 8's entry will be the first from a lunar flight, it will not be the first command module entry at lunar-return velocity.

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The unmanned Apollo 4 mission in November 1967 provided a strenuous test of the spacecraft heatshield when the command module was driven back into the atmosphere from a 9,769 nautical mile apogee at 36,545 feet-per-second. By comparison, Apollo 8 entry velocity Is expected to be 36,219 feet-per- second. Heatshield maximum char depth on Apollo 4 was three- quarters of an inch, and heat loads were measured at 620 33TUs per square foot per second as compared to the 4-80 BTUs anticl- pated in a lunar-return entry.

Apollo 8 entry will be flown with a nominal entry range of 1,350 nautical miles in either the primary or backup control modes. Adverse weather in the primary recovery area can be avoided by a service propulsion system burn prior to one day before entry to shift the landing point. Less than one day out, the landing point can be shifted to avoid bad weather by using the spacecraftls 2,500 mils entry ranging capability.

The crew will wear the inflight coveralls during entry- pressure suits having been doffed an8 stowed since one hour after tmnslunar injection. Bcpsrlence in Apollo 7, when the crew flew thaP entry phase without pressure suit, helmets or &loves, prompeed the decision not to wear suits once the spacecraft's presarure integrity was detarrmlned.

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The decision to fly Apollo as a lunar orbit mlssion was made after thorough evaluation of spacecraft performance in the ten-day Earth-orbital Apollo 7 lsrission in October and an assessment of risk factors involved in a lunar orbit mission. These risks are? the total dependency upon the service propulsion engine for leaving lunar orbit and an Earth-return tlm as long as three days compared to one-half to three hours in Earth orbit.

Evaluated along with the risks of a lunar orbit mission was the value of the flight in furthering the ApolPo program toward a manned lunar landing before the end of 1969, Princi- pal gains from Apollo I; will be experience in deep space navigation, communlcatiors and trackfng, greater knowledge of spacecraft them1 response to deep space, and crew operational experience--all directly applicable to lunar landing missions.

As many as seven lltve television transmissions mybe made from Apollo 8 as it is on Its path to the Moon, in orbit about the Moon and on the way back to Earth. The television signals will be received at ground stations and transmitted to the NASA Mlssion Control Center In Houston where they will be released live to comaaercirnl networks, -9-

However, because of the great distances involved and the relatively low transmlssion power of the signals from the spacecraft to ground, the TV pictures are not expected to be of as high quality as the conventional commercial broadcast pictures .

Apollo 8 also will carry still and motion picture cameras and a variety of different film for black and white and color photography of the Moon and other Items of interest. These include photographs of an Apollo landing site under lighting conditions similar to those during a lunar landing mission.

The Apollo 8 Saturn V launch vehicle is different from the two unmanned rockets that habe preceded it in the following major aspects:

The uprated 5-2 engine capable of reaching a thrust of 230,OOO pounds is being flown for the first time, on the third (S-IVB) stage.

The new helium pmvalve cavity pressurization system will be flying on the first stage (5-IC) for the first time. In this Bystem, four liquid oxygen prevalves have cavities filled with helium to create accumulators "shock absorbers" that will damp outthe "pogo" effeat.

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The liquid hydrogen engine feed line for each 3-2 engine has been redesigned, and the auxiliary spark igniter lines have been replaced with lines without flex jointa.

A helium heater will be used a8 a repressurization system on the S-IVB.

The center F-1 engine on the S-IC will be cut off early to keep the acceleration forces from building up past the four

"0" leve 1.

Software changes In the instrument unit wlll give a new cant capability to the outboard F-1 engines. After clearing the tower, the outboard engines will cant outward two degrees to reduce the load on the spacecraft in the event of a premature cutoff of an F-1 engine.

Film cameras will not be carried on the S-I1 stage to record the first and second plane separsrtions.

The forward bulkhead of the 5-11 ntel tank is a lightweight type that will be used on future Saturn V vehicles.

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AS-503 CONFIGURATION (APOLLO 8) -11-

MISSION OBJECTIVES FOR APOLU) 8

* Demonstrate crew/space vehicle/mission support facilities performance during a manned Saturn V mission with command and service module. * Demonstrate performanee of nominal and selected mlssion activities including (1) translunar inJection; (2) command service mojlule navigation, communications and midcourse correotions; and (3) command service module consumablgs assesment and passive thermal control. In addition, detailed test obJectives have been designed to thoroughly wring out systems and procedure@ that have a direct bearing on future lunar landings and space operations in the vicinity of the Moon.

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MOMINAL MISSION

Time from Lift-off Event (Hr: in: Sec ) 00 :00 :00 Ll ft-of f 00:01:17 Igaxlmum dynastic pressure 00o02r06 S-IC Center Engine Cutoff 00 z 02: 31 S-IC Outboard Engine Cutoff 00:02: 32 S-IC/S-II Separation 00 :02: 33 8-11 Ignition 00:02:55 Camera Capsule EJectlon 00 :03 :07 Launch EePcape Tower Jettison Mode I/ Mode I1 Abort Changeover 00 :08: 40 23-11 Glatoff 00 :08: 41 S-II/S-IVB Separation 00 :08: 44 S-IVB Ignition 00:10:06 Mode XV Capability begins 00:10:18 Mode II/kode I11 Abort Changeover 00:11:32 Insertion Into Earth Parking Orbit 02:50:31 Trans lunar In3 ec tion Igni tIon 02: 55 :43 Translunar Injection Cutoff Translunar CoarPt Beglns 03:Og:ldC S-IVB/CSM Saga ra t ion 04 :44: 54 %gin Maneuver to Slingshot Attitude 05 :07 :54 LOX Duarg Begins 05;12: 54 I;oT Ends

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Event

TLI+ 6 Hrs. MidaQupS@Correction 1 TLI+ 25 Hr8, Midcourse Correction 2 WI- 22 Hrs. Miduour~~Correctlon 3 LOI- 8 Hrs, Correction 4 Lunar Orbit Insertion (LOI~) Initiation 69: 11: 35 rblt Insertlsn (LOI1) nation 73 :30 :53 Orbit Inamtion (LQI2)

Lunar Orbit Insertion (~012) Temlnation 89: 15:07 Transearth InJection Initiate 89 r 18: 33 Traneerrth InJeotion Telllainate !CEI+ 15 HPS, Midcouree Correction 5 TEI+ 30 Hrs. Corrsotion 6 ET- 2 Wra. ~d~o~~~Cormctlon 7 146: 49 :00 Entry Interface 147 :00: 09 SPUS w -13a -

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n6 Apollo 8 Window

Pre-Launch Apoll~8 is unched from Launch Lex 39, pad medy, Florida I on December 21, e The launc at 7:51 a,m. EST and closes 2:32 p.m. ES ds in the launch countdown or weather require a scrub, there a arix days remaining In December during which the mission could be launched.

December Launch Days for Apollo 8

21 7251 a.m. l2:32 p,m, 22 9:26 a.m. 2:05 p.m. 23 10258 a,m. 3:35 p*m* 24 12:21 p.m. 4:58 p.m, 25 1:52 p.m. 6220 p.m. 26 3:16 p,m. 6:20 p.m. 27 4245 p.m. 6:20 p.m.

A variable launch azimuth of 72 degrees to 108 degrees capability will be available to assure a launch on time. This is the first Apollo mission which has employed the variable launch azimuth concept. The concept fa necessary to compensate for the relative positioned relationship of the Earth at launch ti- a

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MISSION DESCRIPTION

-NOTE: Information presented in this press ki, is based on a nomlnal mission. Plans may be altered prior to or during flight to met changing conditions.

Launch Phase Apollo 8 will be launched from Itsnnedy Space Center Launch Complex 39A on a launch azimuth that can vary from 72 degrees to 108 degrees, depending upon the time of day of launch. The azimuth changes wlth time of day to permit a fuel optimum inJection from Earth parung o~bitonto a free return circum- lunar tradectory. Other factors influencing the launch windows are a daylight launch (sunrise -30 mln, to sunset +3O rnin.) , and proper Bun angles on lunar landmarks in the Apollo landing zone * The planned Apollo 8 launch date of Deceinbsr 21 will call for liftoff time at 7:51 a.m, EST on a launch azimuth of 72 degrees. Insertion into Earth parking orbit Will occur at 11 an. 32 sec. ground elapsed time (GET) at an altitude of 103 nm (119 sm, 191.3 la). The orbit resulting from this launch azimuth will have an Inclination of 32.5 degrees to the equator.

Earth Parking Orbit (EPO) Apollo 8 will rewin in Earth parking orbit after insertion and Will hold a local horizontal attitude during the entire period, The crew will perform spacecraft systems checks in preparation for the Translunar Injection burn.

Translunar InjectSon (TLI) In the second or third revolution in Earth parking orbit, the S-NB third stage engine will reignite over the Pacific to inject Apollo 8 toward the Moon. The vsalocit will increase to 35,582 feat per second l0,gOO meters/sac. 7 Injection will begin at an altitude of 10 nm (122 sm, 197 while the vehicle is in darkness. Kidway through the translunar injection burn, Apollo 8 will enter sunlight. Translunar Coast Following the t slunar injection bum, Apollo 8 will 66 hr. 11 aka. translunar coast, The spacecraft will te fmm the S-IVB stage about 20 minutas after the start tmnslunar inje on Control Syrste about 50 to 70 f atlon keeping. Th9 spacecraf nutes later in an 'e ed to dump peas1 In@ bell abwt 1 hr. rcl stige auxili to depletion. Tha LOX d city of' about 90 fp8 to contact with the spaos 8hot" trajscitory passing behi nd on Into solar orbit. Four mldcourse, oormctioa burner alp6 po&mibl translu~rcoast phase, depQnding upon the accu ectory. The first burn, at translunar InJcaotion +6 hra., 1 be done if the needed veloulty chaw@ is gre ps; the second at TLI +25 hrs.; the third at 1 (LOX) -22 hrs., ad the fourth at LO1 - burns will be made only If the needed velocity is greater than 1 fpra,

The first of two lunar orbit lnrs@,rtionburns will be :29 ClET at on altitude above he Moon 69 rn (79 sm, ). Lo1 No. 1 wl.1 nal retrograd f 2,991 fP8 (912 11 insert Apo m (69 x 196 s 8 km) elliptical lunar rbit. At ?3:30:53, LO1 Burn 140. 2 1 ciroulariz parking orbit at 6Q nm 69 sm, 111 ) with a ret ocity charnge Qf 138 fps t 42.2 ds$c The lunar ng orbit wlll have an inolinmtlon of 12 degrees to the lunar equator.

ring the 10 revolutions of lunar parki~orbit, the 8 crew will perform lunar landmrk tracWRg and Agoll~ site tracMng and photographic tasks, anci stereo phy of' that lunar surface from termainator to temainator. The last two lunar revolutions will be spent in preparation for the transearth injection burn. LUNAR ORBIT ACTIVITIES

Revolutlon Activitx 1 2 Housekeeping, Systems Checks, and Landmarks sightings 3 LO1 , System Checks and Trafning Photography

495,697 General landmark sightings, Stereo photography, and general landmark photography 8 Qeneral photography, Landmark alghtings, Solar corona, Dim Sky, and Earth Shine photography 9 Prepare for TEI and perform gblique stereo strip photography 10 Perform TEI

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-more- corrections are possible during the transearth coast phase, and their values will be computed in real time. The midcourse cor ctions, if ne@ded, will be made at transearth injection +l5 hr., TEI +3O hr,, and entry interface -2 hr. (400,000 ft, altitude) .

Apollo 8 co dule will be pyrotechnically separated from the service module approximately 15 minutes prior to reaching 400,000 ft, altitude, Entry will begin at 146:49:00 GET at a spacecrafe elocity of 36,219 fps (11005 m/sec) . The crew will fly t entry phase with the GdcN system to produce a constant celeration (averaq 4 Os) far a direct entry, rather than the dual-pulse "skip entry technique considered earlier in Apol o program planning. Splashdown i8 taxg&tad for the PacifZ Oosan at 165 degree8 West longitude by 4 degrees 55 mln. North latilude. The landing foot- print will extend some 1350 nm (1560 sm, 2497 km) from its entry point. Splashdown wAll be at 13 min. 46 sec. after entry,

CM END-OF-MISSION E RY AND LANDING POIwTS+

21 Dec 14'42 N 174930 'E 4'55 N 165OOO W 22 Dec 5O35 ' 173O50 'E 1Ooo ' s 165'00 'W 23 D 1°20 N 174'35 'E 8°10'S 165*00 W 24 Dec 1Oo15'S 172'15'E 12O50 S 165°00 W

25 Dec 18O55 ' S 171°25'E 18OOO S 165OOO? W DeC 25'00 ' S 170°45 'E 22O10 ' s 165OOO 'W Dec 'S 17Oo55'E 25'25 ' S 165OOO W These points are for a 72 degree launch azimuth, Other launch azimuths will change the data slightly. -more- c-0 a drc

-more- FLIGHT PLAN Crew Activities

The Apollo 8 Plight plan call8 for at least one crewman to be awake at all times. The nom1 work/rest cycle will be 17 hours of work followed by 8even hours of rest. The command module pilot and lunar module pilot sleep periods are scheduled slm'ultaneously. Following the translunar injeution bum, the crew will take off their space suits and put on the inflight coveralls for the duration of the mission. The Apollo 8 spacecraft normally will remain f'ully powtared up throughout the entire mission, with the stabilization and control system and navigation sextant and scanning telescope turned on as needed. The inertial measurilyri unit and command module computer will stay in the "operate mode. Changes of lithium hydroxide eanisters for absorbing cabin carbon dioxide are scheduled at times when all crewmen me awake, an& all scheduled maneuver8 will be made when all crewmen are awake. Flight plan upUatea will "be relayed to the Ago110 8 mew over S-Band frequencies each day for the uonring day's activities, Following is a brief summary of tasks to be aCC0t?1pli8hedl in Apoll~8 on a day-to-day schedule. The tasks are subject bo changes to suit opportunity.. or operational factors: Launch Day (0-24 hours): * CSM systems oheckout,foPlowing Earth orbit insertion * Translunar injeation burn, separation from S-IVB and transposition snaneuver * Monitor S-NB LOX blowdown and "slingshot" mneuver * Fivetsets of translunar coast star-Earth horizon navigation 8igIr'tings * Perform first midcourse correction burn if required * Star-Earth landaark navigation sighting8 Seoond Day (24-48 hours): * Midcourse correction burns Nos. 2 and 3 if required -more- -21-

* Star-Earth horizon, star-lunar horizon navigation sightings Third Day (48-72 hours): * .Star-lunar horleon navigation sighting8 * Maidcourse corrmtlon burn No. 4 If required * Lunar orbit insertion burn Into initial 60 x 170 nm (69 x 196 sm, 111 x 314.8 km) orbit * General lunar landmark obsewation, photography, onboard television * Preparations for lunar orbit circularization burn * Align IfW once during each lunar orbit dark period FouPth Day ( 72-96 hours).: * circularize lunar orblt to 60 nrn (69 sa, 111 k~) * Vertical stereo, convergent ratereo navigation photogmphy * Solar oorow photography * Landmark and landlng site tracking and photography * Star-lunar landmark navigation sightfngs * Transearth Injection burn Fifth Day (96-120 hours): * Star-lunar horizon, star-h&ax?thhorizon navigation sightings * Midcourse coPreation burns Nos. 5 and 6 if required Sixth Day (120-144 hours): * Star-Ebsrth horizon and star-lunar horieon navigation sightings * Midcourse oarreation burn No. 7 If mqulred Seventh Day (144 hours to splaarhdown) : Star-Earth hor9zon and starmEarth landmark navigation sightings * CM/SN separation, entry and splashdown.

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Recovery Operatlonrs

The primary recovery line for Apollo 8 is in the mid- Pacific along bhe 165th west meridian of PongieUde where the primary pecov ry vessel, the aircraft carrier USS Yorktown will be on station. Nonrinerl splashdbwn for a Pullxration lunar orbit mission launched -on^iXme-lkcea'ber 21.will be at 4 degrees 55 minutes'north x 165 degrees west at a ground elapsed pime of 147 hours, Other plannett recovery lines for a deep-space mission are %he East Pacriflb line extending parallel to the coast- line of North and South America, the Atlantic Ocean line running along the 30th West meridian in the northern hemisphere and along the 25th West meridian In the southern hemisphere, the Indian Ocean line extending along the 65th East meridian, and the West Pkcific line along the 150th East meridian In the nQr?thel?n healsphere and jogging to the 170th East meridian in the southe6Y*5knlsphere. Secondary landing area8 for a possible Earth orbital alternate mission have been established in two zones in $he Pacific and two in the Atlantic. Ships on station in the.launoh abort area stretching 3,400 miles eastward from Cape Kennedy inalude the Helicopter landing platform -08s Quadaleanal, one of whose duties will be retrieval of omera oassettelcs froar the S-IC stage; the transport US$ Rankln, the tracking ship USNS lch will be re=sM moovery duty aftems Earth parking orbit, and the oibr U%S Chuckawan. In addition to surfaoe vecnsele deployed In the launch abort area and the prlaary moovery vessel in the Pacific, 16 HC-130 aircraft will be on standby at eight staging bases around the Earth: Tachikawa, Japan; Pago Pago, Samoa; Hawaii; Bermuda; Lajes, Azores; Aercension Island; Mauritius, and Panama Canal zone, Apollo 8 reaovew operations will be dlreotcsd from the Reoovery Operation@Control Room in the Mission Control Center and will be supported by the Atlantlc Recovery Control Center, Norfolk, Va.; Paoific Recovery Control Center, Kunia, Hawaii; and control centers at Ramstein, Germany; and Albrook APB, Canal Zone.

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The &pollo 8 crew will be flown from the primarry recovery vessel to Manned Spacecraft Center after relrovery. The spacecraft will receive a prellmlnary mination, saflng and power-down aboard the Yorktown prior to offloading at Ford Island, Hawaii, where the spacecraft will undergo a more complete deactivation, It is anticipated that %he spacecraft will be flown from Ford Island to Long Beach, Calif., within 72 hours, and thence trucke to the North American Rockwell plant In Downey, Calef., f r poertflight analysis.

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-more- ALTERNATE NISSIOMS

Several alternate mission plans have been prepared for the Apollo 8 mission, and the soope of the alternate is dependent upon when in the mission timellne it becomes necessary to swiech to the alternate, For example, if there is an early shutdown of the S-IVB stage during the, Earth parking orbit insertion burn, the aervice propulsion system engine would be Ignited for a contingency orbit insertion (COX), and again Inglted later in the mission to boost the spacecraft to a 4,000 nm (4,610 sm, 7,400 km) apogee. The rsecond burn into the high elllppre would be done only if the COI burn required less than 900 Fps (274,5 ra/sec) velooity Inorease, The COI-high apogee mission is Alternate 1, and would have a duration of up to 10 days, Alternate mission 2 would be followed if the S-M3 failed to restart for the translunar InJectIon burn aut of Earth parking orbit, This alternatei Cklls for the SPS engine to boost the spacecraft to the 4,000-ntu (4,610 si, 7,400 kn) apogee for two to four revolutionB. A deboost maneuver later would lower apogee and the tulssion would aontinue In low Earth orbit for LO days, Alternate lnPss1on 3 Is split into three subalternates, each depending upon the apogee that can be reached after early S-TVB cutoff during the translunar injection burn. In the 3a alternate where apogee would be between 100 to 1,000 nm, (115-1,352 185-1,853 km) the orbit would be tuned up with an’SPS burn to permit la rk sighting; and the mission would follow the alternate 2 tlnoellne, If apogee en 1,000 nm (1,152 ern, 1853 ka) and 25,000 nm 46,250 lan)$ 8 phasing maneuver would be paad@ at first perlgee to shift a later perigee over a network station, where a deboost burn would lower apogee to 400 nm (461 sm, 740 km) and the raission would continue in low Earth orbit for the 3b alternate,, Alternate 3c would be followe f apogee wa@ between 25 000 nm (28,800 stu, 46,250) .and 000 ~1 (69,100 ljdllp, 111,000 km). his alternate calls for a p ing iiaiwuver at first perigee to shift later perigee to the recpovery area. A seaond maneuver at the later perigee would ardjuert the elliptical orbit to one with a seml-syn&uxmxw period of about 12 hours-- tha-t; is, there would be two daily perigee Beorbit pe&ods, one over the Pacific an8 one over he Atlantic. The entire misslon would be flown in this typ orbit, Inalu8ing direct entry from the high ellipse ,

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rly TLI outoff' whleh would prqduce an ogee greater (69,loo am, l11,O ) would fall Into the tegorye !Phis alt 8 calls for a .(zlrcum- lunar flyby using, the Semrloe Pro~18l~~Sgstgsn to oor- re& the fll@t-yflle Wok-to- -a_Pr$e-ratup?ntz%i ecto-e, In somd &&Ses a unar orbit miselon may be posszb1- e. A11 alternat islrion plains along the nololnarl ifX-6- recove and In general fo thra lunar orb *try veloeltles any of the a1 &6,000 fps and 3 PPS (7,930-1 Ago110 8 alternate mission ar table belowt Ap0110 8 Alternate Mtlsslonra Conditlm surrvaury Al.t;ernate Plan % - 1, S-IVB early eutotf on EPO If COI takes less than 900 fps burn, 001 with SPS (274,5 op/sec), use SPS to mi80 apogee to 4,000 run (4,610 sm, 7,200 h);if COI takes more than 900 fpa (274.5 m/sec) remain in Earth orbit up to 10 1. days 2, Xn EPO.but;S-m fall0 Uae SPS to raise apogee to to reratart for TLI 4,000 M? (4,610 ern, 7,400 km). remain In high ellipse for 2-4 revolutions, then deboost to low Earth orbit for remainder of 10 days,

producing apoge a* 100-1,000 m Barn bo 4,000 nm (4,610 mn, 2 ma, 185- 7,400 h)apogee, p

tlons, lower apogee and continue low Earth orbit mission,

be 1~000~2~~000ll~a Make phalsing mamv~rat flret (1,15248 800 1,853= perigee to shift later perigee 46,250 km) over network station; at that to 400 ;Lowers_-apogee further and mission 6on.l;inucess in low Earth orbit, d, More than 60,OOO nm Comect t;rerjee.f;oryto lunar (69,100 sm, ~J,J,Q~&.) f1yVy and rth free-return with SPS, direct entry, The Apollo an be aborted at anytime during the launch phase 0 e8 after a auocessful insertion Into e Abort mo rized as iollowe: Launch phase-

tower propels CQ cle, This mode 11 LES Jettison nt @anrange from sm, 964 h) downrangee S is JettisoneU and runs to tes from launah vehiole landing between ) downrange. Mode IPS: - n e”u1l-llft; landing point reacrhes 3200 NI~(3680 B tends through orbital insertion, The CSM would separate fr the launoh vehicle, and if neaessary, 833. SPS retrogmds rn would be made, and the oommEkDd module would be flown half-lift to entry and landing between 3000 and 3350 lllg @&073850 sgh, 5560.6200 ky) downrange_. , k - Begins after the point the SPS CSM into an earth parking orbit ---from about 1 t3er liftoff. The. SPS burn into Orbit would be tea af.t;er rseparatlon from the s-NB and the aontlnue as an earth orbit alternate, or if‘ other ~~~~~ti~~swarranted, to landing in the West Atlantic or Cent 3.0 after one revolution, Mode is preferred ov A variation of Mode IV is the Apogee Xi@ PS wmlU be Ignited at first apogee to raiss ereby set up a mitable orbit for a low earth-o %e mission. Earth Parking Aborts f~ t would be flown similar to tha nom1 t; was flown on Apollo 7: SPS deorbit burn followed by CM@4 Beparation and guided entry, aft8r init i applied.

y translunar CQUB 90-minute TLX abort.

force8 an abort

earth Lunar Orbit Inam?% It insertion

I11 omurs near om in lunar orbit, -29- Lunar Orbit Pha If during lunar g rking or!bit it b nWeSSal?y to abort, the transearth ln3ecdion would be made early and would target spacsc landing to the mid-Paclf 3.0 r line. Transearth In3

z?t and a SPS r perioynthlon. I TEI burn t would call for a osalble for ea&h-rsturn t e mid-Paolflc recovery lints the antipode at the time of'

aervlcm modulg rs, but in general, these are covered in the of transearth raidcourse correm4 %ions. No abort burns will be made later than 20 hours prior to entry to avoid !affects upon CM enLry velocity and flight path angle.

- mora - -30-

ortant a rol

h2ah heretofore have

In the course

ai 8 eo~uiartsof two 7-

inslade lena

Phstographio t Sk8 have beea divided into three $enera1 oategories: lunar telvibo tatrip photography, engineering photography and item of Apollo ~~oto~~~~i~a - __ 8 taaka -31-

to the publie.

-more- -32-

me. NASA endt4t&IOn18 large antem and aenaitlve recaiver%--'m-&6\lp fOF moat of this dltferencm, but the Apollo piotums are no6 expeated to be a8 high quality as nom1 broadaaat program8 . -33-

Apollo spaaecraft No. 103 for the Apollo 8 mission ils aomprised of a launch e ystem, crommrand module, service module rand a ~pa~~~raft-lu~rmo&tle adapter, The latter serves as a mating struoturs to the lnartrument unit atop the %.I'VE stage of the Saturn V for thlm mIss1on, lunar module test artide B (LTA-B) will be housed In the adapter. -Propels c nd module It Is made UP of an open- frame tower atruc ounted to the command module by-four fraqgibls bolts, ree solid-propellant rocket motorst a 155,000-pound-thmet launch esaape systmh motor, a 3,000- pound-thrust pltoh control motor that bends *he cromand module traje y froln the launoh vehlole and pad area. Two canard v r the top detgloy to turn the module aerrod fy to an attitude with the forward, At he base of the Escape Syatsm Is a boost protectgve c3 ed of glass, 010th and honeycomb, that proteala %he from rocrket exhaust gasres from the main and the ;let%isanmotor. The aystem is 33 feet tall four feet in diameter at the base and weighs 8,900 pounds (4040 kg). -The baralc etructure of the c esel encased In heat-shields, cone-shaped 12 feet h , baa@ dlmetsr of 12 feet 10 inch@8, and launch weight 12, pounds (5626 kg), oonslats of the forward ecnnpartment oh rmotion control engine8 and systea; the Grew compartment, 1, contal~ and spacec

r layer of phs- eat -shield thlck- froar 0.7 lnchea, e8 on the aft side. -34-

-The servltm module la a tsr by 22 feet long. B 51,258 pounda (23,271 8 one lmh thick form la1 beams separate the In- service propulsion system and ge, Pucal cselle and onboard

-The ecruait- tape from 260 inches dlamet am to 154 inches at the forward end at the %cl;mcio ting line. AlutuAnusn honeyoomb 1.75 Inches thick s~~d-~kinstruoture, f" the spacecraft adapter, !Bm 4,150 pounda (1,884

auidance,maeion and Control Systq/( QNCS )--Measlures and cbnwais dtjmeoraft attitude and velocitlp, caloulates traJectory, uo&rols spaeecmft propulsion system thrust vecttor

-Controls apaue- r and providear the guidance, mttit;ude mf'erence, attitude

=inore- -35-

-?!hie Indudera two

23%~'of' two independent six One Is aetivated

se prcepellanto are hypergolic, aot wlthmt need fer an

4eneiet;o of' three, 31- P plants In the three 28-voit ets in the Corntuand ent bay, two pyrotechnic batteries in the hree 115-200-volt d by the main 28-voit n the lower equipment oxygen react in the r, potable water and be switched to fire rger builds the

Environmental Control System/(ECS)--Controls spaoecraft atmoephere, pressure and temperature and manages water. In addition to re oabin and malt gas pre6sur6, temperature em removes carbon dioxide, odors and lates the crabin after landing. It collects gotable water for 'crew uw,' supplies water tors for cooling, and dumpi su~2itswater urine dump valve. Excess heat generated and cfrew is routed by this system to rs, to the space radiators, to the glycol evaporators, or It vents the heat to space.

-more- s of pulse code ed Space Flight stems and crew condition, sponder, air-to-ground lsion, and a VHF recovery o the spaceoraft rsuuh cornputel? and central for certain onboard funct ions , The Apollo h~~~gainsteerable S-Band antenna will be flown for the first tim on the Ap~llo8 mission. Deployed shortly afeer CSM sepamti n from the S-NB stage, the high- gain antenna will be tested in the two-way mode between the spacecraft and the nnsd Space Plight Network stations during translunar coast, lunar orbit and Farth return, The high-gain S- d antenna consists of four, 31-inch- diameter parabolic di s mounted on a folding boom rt.t the. aft end of the se dula Nested alongside the service, propul81oQ syaQerm noz'zlTF until d@gloment, the antenna swinge ,out at righ Cab to the spacearaft longitudinal axis, witWt2lie boom psialring 52 8egrees below the heaUs-up horizontal. [email protected] ground stations oan be, traoked either raatieallg or manually with the antenna*s gimballing ays All nom1 S-Band voioe and.uplink/ ounlinkl communications will be handled by the high-gain an€ennmrr- -1nt~rfa~~~with other spaaswaft systems ate crltiaal funationa during launch, orbital aborts and entry portions of a 80 controls routine spaotecraft se separa.t;ion and deployment of the landing system. teats and displays

-more- -37- *

-MenUm% aigmew?aPt sjsrtems for and alerts.qrew by visual and audible alarms BO that crewmen may trouble-shoot the problem. Conl;rols am4 ~8glay?8--PPOVldetrcraradmtrs and control funation8 of all other sgaeeerraft Ipystemls In $he c nd and semrlcdt modules. All aontrol8 ere dealgned to be operated by crewmen In presrsvlrleed auits, DlapLays ape groupad according to the fregueaoy the oreu eefers to them. LAUHCH ESCAPE MOTOR STRUCTURAt SKIRT

LAUNCH ESCAPE TOWER

COMMAND MIDULE

SERVICE MODULE

SPS ENGINE EXPANSION NQZZ

SLA PANEL JUNCTION (BWEEN WD AND AR

INSTRUMENT UNIT (SHOWN AS .REFERENCE)

SPACECRAFT COPJFIGURATION -more-

-37c - e

-MOP€?- -37d- ULE K II ECS RADIATOR

n LIGHTS CM/SM HIGH-GAIN FAIRING ANTENNA SAT IC

Plrst Stage

stages at Mar8 The first flight of the AS-503 The static test -39-

our of' the Q

Zy in the c

Second Stage 11 ana 33 f ,035,463 PO pounds. The 14,774 ~~~~d at sQpar~ti~ninclude section, 2,164 pounds Items on board.

burnout It will be mov

-41-

Propulsion

sollda

t 10 tonlg, is mo

0.6 .___8emnd;, The =in prop from 175,000 to 225 a total mean thrust

Designed to 8 3,fjoO-pound J-2 Is burns the Ugh-e on the intsrat liquid propella attain a "c1m drop away with -42-

ma variow functions on the

t ~IU)la a cyllnd

rain" of the Saturn

he SIXmajor s nt umlt are swing an8 t control of t network d1;ts

If 8uch air currantar the! vehicle, fro optimum trajectoq In cll Mole derives 8 jectory. Calculations are out once eaclh throughout the flight. The 1 hlcle dlgi and launerh vehicle data adapt rm the nay guidance computations. reference coon31 three ntutually pergenUlcular axe8 of the coordinate system. for moovery .

Both tsl@vl 11 d Inside the thrust structure, of the flrsrt stage. -44-

fixed center

scrmpcsra will r from the two ob

PB paultiplexed tram try link. T unsc ation . ontarin 28-voit vidicon cmmmm, pre -ampllPlera ep circuits for 30 fra second scanning . ~~InuQusly f r before llftof n first ert

Ejection and Recovery ldhen the camera capsules am eJected, stabilization flaps open for the initial part of the descent. When the capsules descend-to about 15,000 feet above gmund a para- balloon ail 5iflate automatically, causing flags to fall away. A recovery radio transmitter and flashing light beacon are turned on about 6 seconds after para-balloon Inflation, After touchdown, the capsule effuses a dye marker to aid sighting, and It releases a shark repellent to protect the capsules, parEt-ballOQn (whlch keeps the capsule afloat) and the recovery team,

-mom- -45-

A Navy ship wlth helicQptera and frog n aboard all be cruising In the aplaahdown area For the camra capsules. The capsule8 all be picked up and flown by helicopter to Kennedy Space Center. The capsule8 will then be transferred to a data plane at Patrick Air Force Base, Fla,, for immediate transfer to the Marshall Center at Huntsville where the fila will be processed. Sequence of Events

NOTE: Information presented in this press kit is on a nominal mission. Plans may be altered prior to or during flight to meet changing conditions.

Launch !Fhe first stage of the SaturnV will carry the vehicle and Apollo spacecraft to an altitude of 36,3 nautical miles (41.9 sm, 67 km) and 47.4 nautical miles (54.6 sm, 88 km downrange, building up rspeed to 5,267.3 knots (6,068 mph in two minutes 31 seconds of powered flight. After separation from the second stage, the first stage will continue a ballistic tra3ectory endin in the Atlantic Ocean some 357.6 nautical miles ( t 12 sm, 665 km) downrange from Cape Kennedy (latitude 30.24 degrees N and longitude 74.016 degrees W) about nine minutes after liftoff. Second Stage 'Phe second stage, with engines running 6 minutes and 7 seconds will propel the vehicle to an altitude of about 105,8 sm, 197 kaa) some 805 nautical miles downrange, building up to 13,245 epace fixed velocity. The spent second stage will land in the Atlantic Ocean about 19 minutes after lift-off some 2,190 nautical miles (2,527 sm, 407 km) from the launch site, at latitude 31.79 degrees H and longitude 38.24 degrees W. First Third-Stage Bwn The third stage, in ita 1~2-SSOQndinitial burn, will glace itself and the Ago110 spacecraft in a circular orbit 103 nautical laileza (119 sm, 191.3 km) above the Earth. Its inclination will be 32.5 degrees and orbital period 88.2 minutes, Ago110 8 will enter orbit at about 47.08 degrees W l.oq@tude and 26.33 degrees N latitude cat a veloclty of 25,592 feet-per-second (17,433 sta€utce mph or 15,132 knota] . -47-

Parking Orbit While in the two revolutions in Earth parking orbit, the Saturn V third stage and spacecraft systems wlPl be checked out in preparation for the aecond S-nrS burn. Second Third-Stage Burn Near the end of the second revolution, the J-2 engine of the third stage will be reigni'ced for 5 minutes 12 seconds, This will inject the vehicle and spacecraft into a translunar trajectory. About 20 minutes later the CSM separates from the S-NB/IU. Following separation, the S-IVB performs an attitude maneuver in preparation for dumping LOX rwiduals and a burn to depletion of the S-NB auxiliary propulsion system (APS) . Dumping of S-IVl3 LOX residuals and APS Burn on Apollo lunar missions may be done to alter the velocity and trajectory of the spent S-TpB-IU to place it in a 'slingshot" trajectory passing behind the Moon's trailing edge into solar orbit. Differences In Apollo 6 and Ago110 8 Launch Vehicles

The new helium prevalve cavity pressurization system will be flying on the S-IC for the first time. In this system, cavltiea in the liquid oxygen prevalves are filled with helium to oreat;e accumulators or 'shock abaorbers" to damp out oscillations, Thia system was installed to prevent excessive longitudinal oscillations experienced in the Apollo 6 flight. The center eagincr of the S4C stage will be cut off ea~iy(126 seconds after liftoff) In the boost phase. This is being done to keep acceleration forces from passing the four "g" level. Software eh9tngea in the instrument unit will give a new cant capability to the outboard F-1 engines of the first stage. The engines will be in the normal position until the vehicle clears the launch tower. The engines will then cant outward two degrees to reduce the load on the spacecraft in the event one of the F-1 engines cut off prematurely.

- more - -48-

The 5-IC stage will also be carrying added inrstru- mentation on this flight, The addla3 inatruinents will monitor the actions of the fir& &age in connection with the accluirrulstors installed to reduae longitudinal oscillations. On the 3-11 st e, the propellant utilization system will have M open loop eapability for Itnprov& reliability, Commands from the instrument unit will keep the propellants close to the planned levels. The liquid hydrogen engine feed line for each 5-2 engine has been redesigned, and the auxiliary spark igniter lines have been replaced, Leak8 developed iB the Augmented Spark Igniter (MI) lines of two J-2 engines on the second Saturn V launched. The new lines, without flex joints, were tested on the Apollo 7 flight and verified as satisfactory. Film cameras wi3.1 not be oapried on the seoond atage of Apollo 8, On Apollo 6 two recoverable cameras recorded the first and rsecond plane’separations of the first and second #tagas. - 1 A lightweight forward bulkhe& in the liquid hydrogen tank is being used in this vehicle. The original bulkhead was damaged durdng production of the S-SI stage about two years ago. The new bulkhead is the same type which will be used in S-II stages of all future SaturnV vehicles. Added i~~t~~~~~~~io~~3.11alao be flown on the 5-IX stage. The added qquipmpnt will monitor the actions of the new AST lines and further verify their suitability for future fllghta. The thruat of ,$he J-2 @nglnes on this S-II rstage will reach rtrlaost 230,000 pounds at one point, (Average engine thrust will be 228,290.7 pounder for a total stage Ghrust of 1,141,453.7 pounds.) The engines will ignite at a mixture Patlo of 5.0 to 1 and then shift to 5.5 to 1 for the first portion of the bum. The high thrust occurs during $he high mixture ratio bum phase. The mixture ratio then shifts at84&3seconds after liftoff back to 4.5 to 1 for the rema3-F of the powered flight. (Average engine thrulst is 180,168.7 pounds for a stage total thrust of 900,843 .7 pounds .) - more - -49-

!Fhe propellant utilization system for the S-TPB stage will also have the open loop capability, The 5-2 engine of the third e is an uprated version with a top thrust of 230, pounds at the mixture ratio of 5.5 to 1. However, the ne will not reach 230,000 pounds thrust on thirs fli because the 5.5 to 1 mixture ratio is not plz%zmxL It is the firat uprated J-2 engine to be flown. A helium he&Cer will be used as a repressurization system on the S-IW for the first time on this flight. In this system, cold helium from the storage bottles are heated to pPovide pressurization for the fuel tank. The capabiliey to reignite the S-IVB stage engine after separation from the spacecraft has been added to this vehicle, The prime mission plan calls for the stage to be reignited in Earth parking orbit with the spacecraft attached. The added capability will permlt stage reignition even if some unforeseen trouble requires separation of the spacecraft from the stage while in Earth parking orbit. For example, losa of an B-1 engine during S-IC powered flight might require the use of too muoh S-DIE propellant in reaching Earth parking orbit. This would leave a shortage of propellant for the tPtmslunar injection bum. Also, a condition might be discovered during parking opbit which would pose a risk to the astronauts if the S-XWB was restarted while the spacecraft wa6 attached. In any event of separation, the S-ZVB will still be rerstartsd, if possible, so that test data can be obtained from the stage even though it will be UntnaMed. The redesZgnet3 ASI l%newill alao be flown on this flight. It will be monitored again to vepify satisfactory findlngs on the AS-205 flight, Instrumentation for checking out the new line has also been added, while research and development instrumentation no longer needed in some other parts of the vehicle has been removed. Launch Vehlc-le Instrumentation and Communications

A total of 2,608 measurements will be taken in flight on the Saturn V launch vehicle, - more - -50-

This Includes 893 in the first stage, 78 in the second stage, 359 in the third stage and 37 i!i in the instrument unit. The Saturn V will carry 20 telemetry Byitems, six on the first stage, six on the second stage, three on the third stage and five on the instrument unit. The vehicle will carry a radar tracking syertem on the first stage and a C-Band erystsm and command syatem on the instrument unit. Each propulsive stags will carry a range safety system as on previous flights. Four motion picture cameras in recoverable capsules and two television cameras will alero be on the first stage.

- more - -51-

APOUO 8 CH OP

NASA's John F, K er is responsible for preflight checkou h of the Apollo 8 space vehicle. A ta~~ust~team of about 450 will conduct the f ntdown from Firing Room 1 of the Launch Control Center (LCC) , is back^ up by more than 5,000 in launch operations at KSC--from the time the vehicle t stages arrive at the center until the Two major d light hardware for Apollo 8 was at ad a pronounced affect on the sc nd launch operations at KSC, The first was the decision in April of this year to fly Apollo 8 as the first mamd SaEurnV fllght. At that time, the launch vehicle had been erected on its mobile launche bay number 1 of the Vehicle Assembly Buildi

As 8 result of this decision, It was necesaarg to disassemble th second stage (&XI) could be returned to t Center's Mississippi Test Facility rwent modifications to prepare It to ensure that the problem which own of two engine8 on the previous f

IPiaat;t on kit8 launch vehicle the failure of the In orbit, Both of these problems occurred on the second unmanned Saturn V flight, Apollo 6,

The S@tEOnd to KSC In late June and erected on bay number 1 in July. The third stwe and instrument unit were erected the following month, - more - -52-

In AUgu8t the decierlon was made not to ly a lunar module on Apollo 8. Lunar Module 3, which had been scheduled for the mission, had en at KSC since June, and was carried a$ part of the 0110 8 spacecraft checkout schedule, As a result of this decision, M-3 was dropped from the spaceoraft schedule and a lunar module test article wals inserted. Assembly a,nd oheckout of Agollo 8 has baen carried out while launch teams at KSC prepared and launched the Apollo 7 mission and began preparation for the Apollo 9 and Apollo 10 missions, scheduled for Che first and second quarter of next year. On Oct, 9, when the Apollo 8 space vehicle was moved from the Vehicle Assembly Building to Pad A, the launch team for Agollo 7 was conducting the final countdown to launch for the first manned Apollo mission. The Apollo 9 launch vehlcle was already erected in the Vehicle Assembly Building and its command, aervice, and lunar modules were undergoing checkout in the Manned Spacecraft Operations Building (MSOB) in the industrial area. Lunar Module 4, the first flight hardware for Apollo 10 to arrive at KSC, was also undergoing checkout in the MSOB, The! Apollo 8 cman8 service modulers arrived at KSC in mid-August and were taken to the Manned Spacecraft Operations Building for checkout and altitude chamber runs. The prime surd backup crews each participated in altitude chamber tests during which spacecraft and crew systems were checked out at simulated altitudes in excesa of 200,000 feet . At the comple%ion of testing in the altitude chamber, the CSW was mated to the spacecraft lunar module adapter (SLA) and moved to the VAB where it was mechanically mated to the launch vehicle. The move to the VAB akrd erection on the launch vehicle was completed Oct. 7. Following installation of certain ordnance items and the launch escape system, the space vehicle was moved to Pad A by the crawler transporter. Integrated systems testing was conducted at the pad and the space vehicle was electrically mated in early November. - more - -53-

e first overall t st of the space vehicle, called the Opererll Test, Plugs In, v@rified the compatibility of the space vehicle systems, ground support equipment, and off-site support facilities by demonstrating the ability of the systems to proceed through a simulat down, launch, and flight. During the simul portion of the test, the systems were requi to both emergency and normal flight conditi The space vehicle Plight Readiness Test was conducted in mid-November. This was the last overall t before the countdown d stration. Both the prime backup crews participate in portions of the FEET, which is a final overall test of the vehicle systems &kt associated ground support equipment when all systems are as near as possible to a launch configuration. After. hygepgolic fuels were loaded aboard the space vehicle and RP-1, the launah vehicle first stage :fie1 Was brought aboard, .an&.6h9 .ff&?xQ-wjor test .of the s .as vehicle began. This was the counfdown demonstration eees (CDD!!!), a dress rehearsal for the final countdown to launch. The CDMl for Apollo 8 %vasdivided into a "wet" and a "dry" portion. During the first, or "wet" portion, the entire countdown, Including propellant loading, was carried out down to-zy8-. seconds. The ahltronaut crews did not partictipa in t&6 wet CDDT. At the completion of the wet CIIDT, @ cryogenic propellants (liquid oxygen and liquid hydrogen) were off-loaded, and the final portion of the countdown was re-run, this time simulating the fueling and with the grime astronaut crew participating as they will on launch day. Because of the complexity involved in the aheckout of the 363-foot-tall Apollo/SeLturn V configuration, the se of extensive automation in their on is one of the major differences in 0110 compared to the 'procedures used

in the Mercury and Qemini programs.__ _I_--. --- . - ROA JlOA czhpjters, -.&tgtd&a la -aa.-. digital data teahnlques are used wo automatic checkout from the time the launch vehicle is erected in the VAB through liftoff, 'A similar, but separate computer operation called ACE (Acceptance Checkout Fquipment) is used to verify the flight readiness of the spacecraft, Spacecraft checkout is controlled from separate firing rooms located in the lylanned Spacecraft Operations Building. - more - -54.1

HPS: Min: S@css T - 28: 00: 00 Start launch vehicle and spacecraft countdown activities - 24: 30: 00 S-IS power-up - 24: 00: 00 S-IVB power-up - 09: 00: 00 Six-hour bu ilt -in hold - 09: 00: 00 Egd _.of _bujlt--ln hold olose ConanaM Module and boost protective cover hatch - 08: 59: 00 Clear gad fop launoh vehicle cry0 loading - 07: 28: 00 Start S-WB LOX loading .. 07: 04: 00 s-IVB mx loading oromplete; start S-I1 LOX loading - 06: 27: 00 84-11 LOX loading complete; start S-IC LOX loading - 04: 57: 00 S-IC LOX loading complete - 04: 54: 00 Start S-1% liquid hydrogen loading - 04: 11: 00 S-If liquid hydrogen loading complete; start S-IVB liquid hydrogen loading - 03: 30: 00 Flight crew d8paX”tS MWIXked Spacecraft; Operations building - 03: 28: 00 S-IVB liquid hydrogen loading complete - 03: 13: 00 Closeout crew on station; start ingress preps - 02: 40: 00 Start flight Grew ingress - 02: 10: 00 Flight crew ingress complete - more - T - 01: 40: 00 spacecraft hatch - Of: QOt 00 st RP-1 level adjust - OO: 42: 00 neh Escape System pyro buses - 00: 35: 00 el adjust complete - 00: 15: 00 craft on internal power - 00: 05: 30 and Amdeviaes - __.- - 00: 03: 07 1 Count Sequence (WS) start - 00: 00: 17.2 GCU e reference release CQ - 00: 00: 08.9 s-IC i KSC Launch Complex 39

Launch Complex 39 facilities at the K Center were planned and built specifically for the Saturn V program, the space vehicle that will be used to carry astronauts to the Moon. Caraplex 39 irrtrdiaced the mobile concept of launch operationlj, a departure from the fixed launch pad techniques used previously at Cape Kennedy and other launch sites. Since the early 1950's when the first ballistic missiles were launched, the fixed launch concept had been used on NASA missions. This method called for assembly, checkout and launch of a rocket at one site--the launch pad. In addltion to tying up the pad, this method also often left %he flight equipment exposed to the outside influences of the weather for extended periods. Using the mobile concept, the space vehicle is thoroughly checked in an enclosed building before It is moved to the launch pad for final preparations, This affords greai;er protection, a more systematic checkout process using computer techniques, and a high launch rate for the future, since the pad time is minimal, Saturn V st;ages are shipped to the Kennedy Space Center by ocean-going vessels and specially designed aircraft, such as the Guppy, Apollo spacecraft modules are transported by alr. The *spacscrraft components are first taken to the Manned Spacec-BWt Operations Building for preliminary checkout, SatUrnV stages are brought immediately to the Vehicle Assembly Building after arrival at the nearby turning basin, Apollo 8 is the thin3 Saturn V to be launc Pad A, Compldtx 39. The historic first lamh of the Saturn V, designated Apollo 4, took place Wove 9, 1967 after a perfeat countdown and on-time liftoff at 7 a.m. EST. The second Saturn V mission--Apollo 6--was conducted last April 4.

- more - The major 39 inelude: (1) the Vehicle where the Apollo 8 was Launch Control Center, where the launch team conducts the preliminary checkout and countdown; (3) the mobile launcher, upon which the Apollo 8 was erected for checkout and from where It will be launched; (4) the mobile service struc$ure, which provides external acces8 to the space vehicle at th6 pgb; (5) the transporter, which carries the spam vehicXe and mobile launcher, as well as the mobile service stmature to the pad; (6) the arawlerway per which the space vehicle travels from the, VAB to the launch pad; and (7) the launoh pad itself. !Fhe Vehicle Aacsmbly Building

The Vehicle Assembly Building is the heart of Launch Complex 39. Covering eight aares, 3.t is where the 363-footn tall space-veflfsle is assembled and tested, The VAB contains 129,482,000 cubic feet of spaae, It is 716 feet long, and 518 feet wide and it covers 343,500 square feet of floor space. The faundation of tfie VAB reats on 4,225 steel pilings, each 16 inches in diameter, driven from 150 to 170 feet to bedrock. IF placed end to end, these piles would extend a distance of 123 miles. The skeletal rstructure of the buildiw contains approxilnately 60,000 tons of structural steel. The exterior is covered by more than a million square feet of insulated aluminum siding. !Phe building is divided Into a high bay &rea 525 feet high and a low bay area 210 feet high, with both areas serviced by a transfer aisle for movement of vehicle stages. The low bay work area, approximately 442 feet wide and 274 feet long, aontainsJeight stage-preparation and checkout cells, These cells are etqulppGd with systems to simulate stage ineerface and operation with other stages and the instrument unit of the Saturn launah vehi'cle. After the Ap0110 8 launch vehicle upper tages arrived at the Kennedy Spaae Center, they were moved o the low bay of the VAB. Here, the seaond and third stages underwent scuep- tance and checkout testing; prior to mating with the S-IC first e atop mobile launcher No. 1 An the high bay area. The high bay provlcfes t;h@ Facilities for aS8@mbly and chsokout of both the launch vehicle and spaceoraft, It oontains four separate bag8 for vertical assembly and checkout, At present, three bay8 are equippetU, and the fourth will be reserved for possible changes In vehicle configuration. -more- Work ~latfo~s-- ome as hlgh as three-story bull in the high bays pro acmm by aurroundlng the laun at varying lev high bay ha8 five platforms. Each platform consists of two biAparting sections that move in from opposite sides and mate, providing a 360-degree access to the section of the space vehicle being uhecked, A 10,000-ton-capacity air conditioning system, sufficient to coo$ about 3,000 homes# helps eo control the environment wIfih€n the entire office, laboratory, and workshop compPex located inside the low bay am16 of the VAB. Air conditioning is also fed to individual platform levels located around the VehiCle,- There are 141 lifting devices in the VAB, ranging from one-ton hoists to two 250-ton high-lift bridge manes. The mobile launchers, camied by tmnraporter vehicles, move in and out of the VA33 thsmgh four doors in the high bay area, one In eaah of the bays, Fach door Is shaped 1Ue an inverted T, They are 152 feet wlde and 114 feet high at the basea narrowing to 76 feet in width, Total door.height Is 456 feet , The lower seetion of eaeh door is of the aireraft hangar type that s12dea3 horizontally on tiraaks. Above this are 8evm tela coping vertlgal lift panels stacked one above the other, each 50 feet high and driven by an Individual motor. Each panel slide8 over the next to oratate an opening large enough to pertnlt paacsage of the Mobile Launcher.' The Launeh Control Center

Adjacent to the VAB is the bunoh Control Center (LCC). This fm3?-PtQ3?y tructure is a radieal departure from the dome-shaped blodfhoue s at other launah sites. Ponlc .."braA$n"of nah Complex 39, the LCC hec~o~tand teat operatlone while Apollo 8 wac3 d inside the VAB. The WC oontaims display, d contmol equipment used for both cheekout and launch operatlonls Wild $F OWekWt StatiQnS On It8 seco loora rooal~~,0n83 for each high bay of the VAB, On floor? Three firing rooms will contain identical ~lat;s l--&E& monitoring equipment, so that launch of a vehiole and aheekout of others my take place simltantmusly, A ground computer facility is associated with each firftng FO~. -59-

The high speed aotlaput@rdata link is provided between the LCC and the mobile launcher for checkout of the launcrk vehicle. !Phis link can be connected to the mobile launcher at either the VAB or at the pard, The three eQuipped fir% rooms have aome 450 conaoles which contaln control8 and dI8playe requlrd for the cheekout proce8s. The digital data llnkt, connecting with the high bay am88 of the VAB and the launcrh padsparry vast amount8 of data required daring checkout and launcrh, . There are 15 ~ispl8ysgstemrs in eaoh LCC firing room, with each system sapable of provlding digital Information Instantaneously, Sixty televi8~0~c~me~~s are poeltioned around the Agollo/Sa turn ltting pictures on 10 modulated uhannels, The ing room also contain8 112 operational intercommunication channels used by the crew$ In the checkout and launch countdown. Mobile Launcher

The mobile launcher 18 a transportable launch base and umbilical tower for the space vehicle, Three launchers are used at Compl@x 39. The launcher ere is a two-story steel strueture, 25 feet high, 160 feet long, and 135 feet wide. It Is positioned on six steel pedestals 22 feet high when in the VAB or at the nah pad, in addition to the six eteel le oolums also are used to atiffebn the rebound loade, if the engine cuts off. 398 feet above the launrrh the Zaunpher 'base, A ham- ook height of*??6 feet above of 85 feet from the oenter of the tower. -1 ~~~~Qun~mobile launaher stands 445 feet on if%pedestals.- The base, ooverlng about a compartmented structture built of 25-foot

The launuh &oh sI$S OV a 45-f oot-raquare opening , wkrloh orllow0 an let for engi exhausts into 8 trsnoh @on- talnilng a flame leetor. This opening is lined wlth a replaceable $%eel blast shield, Independent Of the atructure, @riaw3S.Tbs Booled by I water eureain initiated two seoonda after liftoff, -60-

re are nine eraCed service a on the umbilical arms lines for the vehicle umbil vide for psPSOM@l to the stages as well a8 the aslatronaut craw to the spacecraft. On Apollo 8 two of the erritice ana (includlng t spaclecraft accle re retracted e8rly in the oount. A third is releas 0 seconds, and a fourth at abaut T-15 seconds. The five amis are set to vehicle first”motionafter T-0. The swing system in case The Apollo aclee 32O-foot level above the spacecraft cabin crews. Astronaute Bo spacrecraft start The acaess arm will be moved to a parked position, 12 degrees Prom the spaaec!T&ft, at about T-42 minutes.

This IS 8 8iShncte Of about three feet, which permits a rapid reconneetion ~f the am to the spaceuraft in the event of an emergenay condition. The arm is filly retraoted at th T-5 minute mark in t The Apollo 8 vehicle is ~ecur~dto the mobile launch by four cotpbination eupport an4 Id-down arms mounted on the launcher deek. !Phe hold-down a one pieas, about 6 by 9 feet at the base %.nd 10 ing more than 20 tonfa. -per struts 88cure the ~.vehicle near Its top. After the engines ignite, the am hold Apollo 8 for about six seconds unL 6 build Up $0 95 p thrust and other moni inUlcate they are properly. The ams r eipt of a launch c at the zero mark in the eount. The Transporter

The sixdillion-pound tmnaporters, the largest tracked vehioles &-*,move mobile launchers into the V*3 and mobile launcher6 wXth asrslsrabled Apollo apace vehlcrlets to the launoh pad. They also ir yFed >to transfer the mobile service etruoture to and from the launch pads. ’Pwo transporters are In use at Complex 39

-more- Transpoz?&er1s 131 f cle IILOV~Son four double igh and 40 feet long. en feet six inchea in length and weighs about a ton. s powemd by four 1,OOO-kil , whiah In turn am driven by two 2,750-kgg% ower for the trans 1,045+9rsep , lighting, v

!burn speed OF the transporter lq-.zibbut onedaile- F loaded arid about two-iniles-p6rohour unloaded. A a mobile launoher, e at less 8 approximately seven h . ellng syst designed to keep ertlcal wl in plus-or-minus t the d%tk18n8lOnS of a basketball. ing opcarrationa required cent nuup which leads to the vel when It is raised and lo ad and within the VAB. er ovsrall height of the transporter is 20 feet from d level to the top deck on whieh the mob118 launcher Is for tranaportsrtlon The deck Is flat and abaut the size of a baseball diamond (96 by 90 feet). QP eonlmol cabs, one at eauh end of the c lly opposite each other, provide totally sEa5cons fsoaa which all opera%ing and oontrol functions are coordinated. e transgor2;er tncmes on a roadway 131 feet wlde, by a median strip. This is alrnoet a8 broad as an me turnpike and $s designed to acoonnrrodate a combined t of about 18 million pands.

B roadway id, built In three layetre wI*h en feet. The roadway base layer la two e-half feet xlaullc fill crompacted to 95 per cant de nsiets of three feet of crushed rock paraked to ~rraxlmrn ollowe4 by a layer of one fool4 of selected hyareLulla bed is topped and sealed with an asphalt prime coat. -e-

On top of $hu three Xayers Is a cover of rl elght Inches deep on the curves and six i straightway, This layer reduces the fric and helps distribute the load on the tra

A ,402-foot-t;iall, 9.8-ml11i~n-pound tower Is used to -+- &3&b%o-&~~hv&x&&b-~- sgase-;.a8 ---pad, The 40-story ste@l-trus~edtower, aalled a nroblle service - structure, provides 360-degree platform aecess to the Saturn vehicle and the Apollo spacecraft. The, IPBIPB~~G~)struoture ha five platform -- two self- propelled and thpee flxed,Lbut movable. Two @levators carry personnel and equipment between work platforms. The platforms can open and crlose around the 363-foot spaoe vehicle. After deposrlltiag the mobile launoher with Its #pace vehicle on the pad, the transporter returns to a parking area about 7,000 feet from the pad. There it plcka up the mobile service structure and moves It to the launch pad, At the pad, the hugs tower 1s lowered and secured to four mount lnechanlsma. I The top three work platforms are .located In fixed posltlonar which serve the Apollo spacecraft. The two lower movable platforms rsemre the Saturn V. The mobile service structure rarmalns In poaltlon until about T-11 hours when it Is removed from ita mounts and returned to the parking area. Water Deluge System

A water deluge reystsm will provide a mlllion gallons of Industrial water for cool1 and fire prevention during launch of Apollo 8. Once th omrloe arms are retracted at llftofP, a spray system will come on to cool tchese am61 frola the heat of the five Saturn F-1 engines during liftoff. the mobile launcher are 29 water nozzles. 11 start immediately after liftoff and wlll pour ~LCPOSS the faoe of the launcher for 30 seconds at the rate of 50,000 galloner-per-ainute. Mter 30 seconds, the Plow will be reduced to 20,000 gallona-per-minute. Positi on both sP re a aeries of n s which wi 8,000 llons-perdninute, 10 (880 liftoff, This water will directed over the flame deflector, r ~lu~h~~~te~nqtzle8, posits d around the pad, aG---fiii&fspill as a protection against fire

Water spray B alao are available along the egress rcnaee that onauts and eloseout crews wwld follow In case an y evaouation was required, B1 !Pmnch and loctor

‘phe flme ereneb ir 58 feet wide t above maan sea level a ch and deflaetor Is app The flame derlector welghacaboug 1.3 alllion pounds and is stored outside the flame erench on mils. When it is moved beneath the launaher, it is raised liaally into goeitian, The detlector is covered nZth a fou -one+alf-incfi l2i’iZE= ness of refractory csoncrete consist Ia volcanic ash aggregate and a calcuim aluminate binder, The heat and blast of the engines are axpsoteU to weaf about.thrm-quarters of an incrh from this refraetory suz%i5tTe-during the Apollo 8 launoh. Pad Areas

Both Pad A and Pad B of Launcrh Corsnplex 39 are roughly 0ct;agonal in shape and oov0r about one fourth of a square mile of twrraln.

The center of the) gad is 8 hardstand conkltruotsd of heavily reinfaroaa conwete. In addition to supporting tho t of the mobile launcher and the Saturn V vehicle, it also mst support3 th4 g;84Bi1 ion-pound mobile aerviae structure and 6-million-pc&nd transport T, all at th top of the pad srtands sane 4 feet above s &%urn v pmp ll+nCs -- liquid oxyfgew, liquid hydrogen, and RF-1 -0 are art e4 near the pad perlmter, t;lrz_nrttBs@&~ vaauuar plpes carry the l%tqui$_’ oxygen (LOX) amTi liquid hydr the storage tanka €0 the pad, up the mobile launcher, an8 finally into the launcrh v@hic\l@propellant tanka.

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00-~mllona-per-plinute. Llquld hydrcqpm, used In t aeaond and third 8tage8, is stored in an 8~0,000-galZ~n &, and is sent through 1,500 fe& of 310-lncz?T~-v~cuum-joketed %nvw pipe, A v @P presevurlzes the torage tank to 60 psi’f s-per-minute flow The RP-.l fuel, a high gmde of keroraene la atorotd In three tanks-each with a capaoity of 86,000 gallona. St is pumped at a rate of 2,000 gallons-per-minute at 175 pslg, The. Compltsx 139 pnevlmatlc rrystenn intlludes a _.gonverter- capraseor fiicXL~ty, a pa8 high-preasure gas etorage bmtEery, a high-presssure storage battery in the WB, low and hlgh- pressure, cross-country supply linea, high-pressure hydrogen storage am3 ’convm?slon caqulpment, and pad distribution piping to pneumatic control panels. The various purgtng systems require 187,000 pQUndf!i of liquid ni%rogen“and 21,000 gallons Of hQliUtIi, 1

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The Taission Control Center at the Hamsd spacecraft Center, Houston, 1s the focal point for all Apollo flight control activities. !&e Center will receive tracking and telemetry data from the Manned Space Plight Network. These data will be processed through the Misalon Control Center Real-Time Computer Complex and used to drive displays for the flight controllers and engineers in the Mission Operations Control Room and staff support rooma. The Mannd Space Flight Network tracking md data. acquisition stations link the flight controllers at the Center to the spacecraft,

For Apollo 8, all stations will be rmo$B..Bites- without glight control teams. All uplirik commands and voice communications will originate from Houston, aad telemetry data will be sent back to Houston at high speed (2,400 bits per ~econd),on two separate data lines. They can be either real time or playback information. Signal flow for voice oircuita between Houston and the remote sites is via commercial carrler, usually satellite, whsPever possible using leased lines which ore part of the NASA Communications Network. C~nemand~are aent from Houston to MSAfs Ooddard Spaoe Flight Center, Greenbelt, Md,, lines whiclh link computers at the two points, The Qoddard computers provide automatic switching facilities and speed buffering for the command data, Data arcs transferred from Qoddard to remote sites on high speed (2,400 bits per sectond) lines. Command loada also can be sent by teletype from Houston to the smote sitetit at 100 wordla per minute. Again, ffoddard computers pqovlde storage and switching functions. Telemetry data at the rsrnote site are received by the RF reeeivera, processed by the Pulse Code Modulation ground stations, and traasfermd to the 64a remote-site telemetry computer for storage. Depending on the format selected by the telemetry controller at Houston, the 642B will output the desired format through a 2010 data transmission unit which provides parallel to serial conversion, and drivers a 2,400 bit-per-second modem. - mare - The data &ern converts the digital serial data to phazre-shifted keyed tones which are fed to the high speed data lines of the Communications Metwork. Telemetry summary messages can aleo be output by the 642B computer, but them messages are sent to Houston on 100-word-per-minute teletype lines rather than on the hIgh-aEeed llneq., Tracking data are output from the sites in a low speed (100 words) teletype foraiat and a 2W-bit block high speed (2,400 bits) format, Data rates are 1 sample-6 seconds for teletype and 10 samples (frames) per second for high speed data, All high-speed data, whether tracking or telemetry, which opiginate af a remote site are sent to Qoddard on high-speed lines, aoddard reformats the data when and sends them to HourJton In 600-bit blocks necBssa3at a 40, 00 bits-per-second rate, Of the 600-bit block, 480 bits are reererved for data, the other 120 bit8 for address, syno, intercomputer instructions, and poly- nomirial error encoding. All wideband 40,800 bits-per-second data originating at Houstan are converted to high speed (2,400 bits-per- second) data at aoddslrd before being transferred to the designated remote site. .-

- more - at wlth the?

craft from li~to~f

neoualy tpan~~tte~ ta will be run flight controllers .,

at Merritt 11 Bsnauda , the Xsland, Later, Carnarvon, A

drid, Spain;

Earth 80 at

a and corn- ... Data is constantly relayed back through the huge antennas and transmitted via the NASA Communications Network--a half million miles of land and underseas cables and radio circuits, including those through communications satellites--to MCC. This data is fed into computers for visual display in Mlsslon Control. For example, a display would show on a large map, the exact position of the spacecraft, Or returning data could indicate a drop in power or some other difficulty which would result in a red light going on to alert a Flight Controller to make a decision and take action, Returning data flowing through the Earth stations give the necessary information for command2 mid-course maneuvers to keep the Apollo in a proper trajectory for orbiting the Moon. On reaching the vicinity of the Moon the data indicate the amount of burn necessary for the service module engine to place the spacecraft in lunar orbit. And so it goes, continuous tracking and acquisition of data between Earth and Apolloare used to fire the spacecraft's engine to return home and place It on the precise traJectory for reentering the Earth's atmosphere . As the spacecraft comes toward Earth at about 25,000 files per hour, it must reenter at the proper angle. Calculations based on data eomlng in at the various tracking stations and ships are fed into the computers at MCC where flight controllers make decisions that will provide the returning spacecraft with the necessary information to make accurate reentry. Appropriate MSFN stations, including tracking ships and aircraft repositioned in the Pacific for this event, are on hand to provide support during reentry. An A/RIA aircraft will relay astronaut voice communications to MCC and antennas on reen%ry ships will follow the spacecraft. During the journey to the Moon and back, television will be received from the spacecraft at the various 85-foot antennas around the world: Spain, Goldstone, and Australia. Scan converters at Madrid and Goldstone permit immediate transmission via NASCOM to Mission Control where it will be released to TV networks,

NASA Communications Network - Goddard

This network consists of several systems of diversely routed communications channels leased on communications satellites, common carrier systems and high frequency radio facilities where necessary to provide the access links.

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with a wide range do not extend over- rovided for added

switching and ntralized facility

intermediate a Guam;’ and Cape

various stations acecraft circles the Earth.

atstion, the Atlantic Ocean ship and the Canary Is The mo cationa satellite, over the mid-Pacific a won, AuBtralia VSS site and the Pacific these stations will b transmit simult satellite to Housto Brewster Flat, the Goddrrrd Spaoe Flight Center. In the case of compaters refep to t before! transmitting the required data to the

nformatlon from these , as well as from remote

The comptlter systems perlt'Qrm many other functions, ln- e ludlng : the quallty of the transmisr~lonlines by continually exerclslng data paths,

Verifying accuraey of the messages by ~e operations , Constantly u atlng the f llght stattzs.

For "down" Uata, sensor8 bullt into the spacarcraft 0 tinually sample cabin temperature, pressure, physical lnf " tion on the astronauts such as heartbeat an8 relapiration, among other item, These data are tranermltted to the ground stations at 51.2 kilobits (12,800 binary digits) per second. At MGC the coaputerso Rete& and seleert changes or deviations, compape with their stoma progpams, and Indicate thea problem amas or pertinent data to the flight controllers, Provide diaplays to mtsslon garsonnel , Assemble output data in proper formats. Log data on magnetic tape for =play. st~~~efor 'an-ctall'' display for the fllght controllers, -71-

Network Configuration for Ago110 8

Canberra (Cm) Atmtmlia Cioldetone (QDS), C (Frise) drld (MAD) Spain (Prl *Canberra (DSS-42 Apollo (-chP) Wold8toae (DSS-11 Agollo Wine) Backu ) dribd rD3S-61 Apollo Wing) O-kUP)

Tananarfve (TA public (STA~A~station In support role only,)

@Wings have, been B c8 Network site operations buiidings * TWS~ onal Unified S-Band equipment as backup to

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The Ap0110 Shipa

The 1nlSS10n will be supportd by four Apollo instrumentation ships operating as ral stations of the Ma~edSpace Flight Network ( to provide coverage in areas beyond the range of land stations, rd, Redstone, Mercury, and Huntsville will perform t eoPnrPunication functions for t orbit insertion, translunar inje ry at the end of the mission. Vanguard will be station@d aboutLLOQOmiles tyqu$heagjt._ of Bersa\da (25ON, 49%) to bridge the Bermuda-Antigua gap during Earth orbit insertion. Vanguard also function8 as part of the Atlantic recovery fleet in the event of a launch phase Pacific, north near Wake of mobile stations between the MSlPN stations at Camarvon and Hawaii for ooveragar of the burn Internal for translunar InJection. In $he event the launch date @lips from December 21, ehe'ships will all move generally southwestward to cover the changing flight window patterns. Mercury and EYunt%rvillewill be repositioned along the reentry corrkdor for trwklng;, telemetry, CaCnB comunications functions during reentry and laxicling. The Ago110 ship#! were developed Jointly by MASA &nd the Department of Def?nse. The DOD operates the ships in support of Ap~lloBnB other NASA and DOD ~aissionson a non-interference basis with Apollo requirements. The overall ~~~m~~tof the Apollo ships is the responsibility of the' CQBupBnder, Air Force Western Test Range (APWTR) The Military Sea Transport Service provides the maritime crews and the Federal Electric Corporation of Irat ionmrl Telephone and Telegraph, under contract to , provides the technical inatm- mentation crews. -73-

The technical crews operate in accordance with Joint ?JASA/DOD standards and specifications which are compatible with WFN operational procedures. Apollo/Rang e Iwtrumentation Aircraft ( AmA) The Apollo/Range Instrumentation Aircraft (A/lUA) will support the mission by filling gaps in both land and ship station coverage where important and significant coverage requirements exist. During Apollo 8, the A/RIA will be used primarily to fill coverage gaps of the land and ship stations in the Pacific during the translunar injection interval (TLI). Prior to and during the TLI burn, the A/RIA pecord telemetry data from Apoll~and provide a real-time voice cammunicatlon between the astronauts and the flight director at Houston. Six aircraft will participate in this mission flying from Pacific air bases to positions under the orbital track of the spacecraft and booster. !!?he A/RIA will fly, Initially, out of Hawaii, Cham, and the Philippines, a8 well a8 three bases in Australia: Townsville, D.aywln, and Perth. The aircraft, like the tracking ships, will also be redeployed in a southwest direction in the event of launch day slips. The total A/FkIA fleet for Apollo missions consist of eight W-135-A (Boeing 707) jet aircraft equipped specifically to meet mission needs. Seven-foot parabolic antennas have been installed in the nose section of the aircraft giving them a large, bulbous look. They are under the overall rsupemrislon of the Qffice of Tracking and Data AcquiBition with direct supervision the responsibility of Qoddard. 911.18 aircraft, as well as flight and instrumentafion crews, are provided by the Air Force and they are equipped through joint Air Force- NASA contract action.

- more - Y . .. -73a- NETWORK CONFIWRATION FOR APOIIW) 8 MISSION

*SubJoct to avdlabtllty. i -more- I 08c

hours of formal crew orbit mimion's six-d most 1,100 hours of training we training syllabus over and above t rations for the mission-- technical briefi , pilot meetings and study. In spacecraft an Rockwell ch testing at valuable operational omplex vehicle. Highlights of specialized Apollo 8 crew training topics are: * Detalled series of bri fings on spacecraft systems, operation * Saturn 1 s on countdown, range safety, fli modes and abort conditions, The icle briefings were updated periodically. idance and avigation system briefings ts Institute of Technology Instrumentation Laboratory. * Briefingrs continuous training on mission photographic objectives and use of camera equipment, * Extensive pilot participation In reviews of all flight procedures for normal as well as emergency situations. * Stowage reviews and practice in training sessions in the spacecraft, mockups, Command Module simulators allowed the crewmen to @valuatespaoecraft stowage of crew-associated equipment.

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* More than 200 hours of training per man in Command Module sirnulators at MSC and KSC, including closed-loop simulations with flight controllers in the Mission Control Center. Other Apollo simulators at various locations were used extensively for specialized crew training. rridar deceleration profiles at lunar- .in the MSC Plight Acceleration Facility manned centrifuge. * Water egress training conducted in indoor tanks as well as in the Gulf of Mexico, included uprighting from the Stable I1 position (apex down) to the Stable I position (apex up), egress onto rafts and helicopter pickup . * Launch pad egreas training from moekups ad from the actual spacecraft on the launch pad for possible emergencies such a8 fire, Contaminants and power failurers. * The training covered use of Apollo spacecraft fire suppression equipment in the cockpit. * Planetarium reviews at Morehead Planetarium, Chapel Hill, 1. C., and at Griffith Planetarium, Los Angeles, Calif,, of the celestial sphere with special emphasis on the 37 navigational stars used by the Command Module Computer. Agollo 8 ,Spacesuits Ago110 8 crewmen, until one hour after tmnslunar injection, wgll wear the intravehicular pressure garment assembly-a multi-layer spacesuit consisting of a helmet, torso and gloves whluh can be pressurized Independently of the spacecraft. The spacesuit outer layer is Teflon-coated Beta fabric woven of fiberglass strands with a restraint layer, a pressure bladder and an inner high-temperature nylon liner. Oxygen connection, communications and biomedical data lines attach to fittings on the front of the torso. - more - ipper access to shoulder discon Et ec tr ical connector

UCT and biomedical injection flap patch

Data list pocket (detachable)

Intravehicular configuration of the PGA.

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A one-piece constat wear g to "long johns," is worn as an unde e spacesuit and for the in-flight garment is porous- tton with a waist-to-neck zipper for donning. Attach points for the biomedical harness also are provided. After taking off the spacesuits, the crew will wear Teflon fabric inflight coveralls over the constant wear garment. The tw-piece coveralls provide wamth in addition to pockets for personal items. The crew will wear the inflight coveralls during entry. The soles of the garment have been fitted with a special metal heel clip which fits in the couch heel restraint. Additionally, fitted fluors1 foam pads on couch headrests will provide head restraint during entry, These pads will be stowed until just prior to entry. The crewman will wear communications carriers Inside the pressure helmet, The communications carriers provide redundancy in that each has two microphones and two earphones, A lightweight headset is won with the inflight coveralls,

Agollo 8 Crew Meals

The Apollo 8 crew had a wide range of food items from which to select their daAly mission space menu, More than 60 items comprise the sel@&ion list of freeze- dried bite-size rehydratable foods. Average daily value of three meals will be 2,500 calories per man. Unlike aemini crewmen who prepared their meals with cold water, Apollo crewmen have running water for hot meals and cold drinks, Water is obtained from three sources--a dispenser for drinking water and two water spigots at the food preparation station, one supplying water at about 155 degrees F., the other at about 55 degrees F, The potable water dispenser emits half-ounce spurts with each squeeze and the ,f garation spigots dispense water in one-ounce inc . - more - Spacecraft potable water is supplied from service module fuel cell by-product water. The day-by-day, meal-by-meal Apollo 8 menu for each crewman is listed on the following page.

Personal Hygiene Crew personal hygiene equipment aboard Apollo 8 ihcludes body cleanliness items, the waste ~n~g~ment system and two medical kits, Packaged with the food are a toothbrush and a, two- ounce tube of toothpaste for each crewman. Each man-meal package contains a 3.5 by 4-inch wet-wipe cleansing towel. Additionally, three packages of 12 by l24nch dry towels are stowed beneath the command module pilot's couch. Each package contains seven towels, Also stowed under the command module pilot's couch are seven tissue dispensers containing 53 3-ply tissues each, Solid body wastes are collected in Gemini-type plastic defecation bags which contain a germicide to prevent bacteria and gas formation. The bags are sealed after use and stowed in empty food containers for post- flight analysis, Urine collect3.m devices are provided for use either while wearing the pressure suit or in the infllght coveralls, The urine is dumped overboard through the spacecraft urine dump valve, The two m@&€,cal ac3csfasory kits, 6 by 4,5 by 4 inches, are stowed on tkb spacecraft back wall at the fe the command module pilot, The medical kits contain three motion 810 injectors, three pain suppression injectors, o bottle first aid ointment, two 1-02 bottle eye drops, three nasal sprays, two compress bandages, 12 adhesive bandages, one oral thermometer and two spare c biomedical harnesses. Pllls in the medical kits are 60 antibiotic, 12 sea, 12 stimulant, 18 pain killer, 60 decongestant 4 diarrhea, 72 aspirin and 21 sleeping.

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At least on@ orew member will be awake at all times, The nom1 cycle will be 17 howrs of’ work followed by seven hours of rest, Simultaneous rest periods are scheduled for the cotamand module pilot and the lunar module pilot. When possible, all three crewmen will eat together, with one hour allocated for eacrh meal period, Sleeping positions in the a module am under the left and right cwohes, with heads toward-the crew hatch, Two lightweight Beta fabric sleeping bags, are each supported by two longitudinal straps attaching to lithium hydroxide storage boxes at one end and to the spaceoraft pressure vessel

inner structure- “1 at the other end, Additlonal transverse reertraint; strapis have been added to the sleeping bags since the Apollo.7 mission to provide greater sleeping eomfort and body restraint in zero-g, The sleeping bags have also been perforated for improved ventila- tion, fiurvlval War

The rsurvival kit is stowed in two rucksacks in the right-hand Forward equipment bay above the lunar module pilot, Contents of rucrksack No, 1 arm two combination survival lights, one desalter kit, three pair sunglasses, one radio beaoon, one spare radio beacon battery and spacecraft connector cable, one nqaohetta in sheath, three water ContaInWS and two:containera of’Sun lotlon, Rucksack No, 2: one three- maiilife raft with CO inflater, one sea anchox?, two sea dye markers, three aunbohfiets, one mooring 1an-d; three manlines and two attach-brackets. The gj_ygyivaljki~la designed to provide a 48-hour postlanding (water or land) survival Gapability for three crewmen between 40 degrees North and South Iatitudes, -1 BSomediaal Inflight Monitoring

The Apollo 8 Grew inf12ght biomediaal telemetry data

.reciived___I by the ManncEad Space Flight Network will be relayed for instantaneous display at Mission Control Center. Heart rate and breathing rate data will be displayed on the flight sgrgeOPs console, Heart rate and respiration rate average, range and deviation are computed and displayed on the digztal W screens. -__- Y I ILMI ION HOLES 1 IN. OIA

-more- -more- -80-

In addition, the instantaneous heart rate, real time and delayed EXCt and respiration are reczorded on stfip charts for each man. Biom8diCal data observed by the flight surgeon and his team in the Life Support Systems Staff Support Room will be correlated with spacecraft and spacesuit environmental data displays, Blood pressure an8 body temperature are no longer taken as they were In earlier manned flight programs, The Crew on Launch DFlx

Following Is BL timetable of Apollo 8 mew activities on launch day, (All times are shown in hours and minutes before liftoff .1 T-9:OO - Backup crew alerted

T-8:30 = Backup crew to LC-39A for spacecraft pre-launch checkouts T-5:QO - Flight crew alerted T-4:45 - Medical examhations T-4:15 - Breakfast

T-3:45 Don prsssulcae.I suits - , T-3:30 - tsave Manned Spacecraft Operations Building for W:-39A via Crew Transfer Van T-2:3O - Arrive at EC-39A T-2:37 { Enter elevator to spacecraft level T-2:40 - Begin spacecraft ingress

Radiation Monitor$-%- I

Apollo 8 crew radiation dosage8 will be closely monitored by onboard dosimeters which either provide crew readouts or telemeter radiation msasurements to hnned Space Flight Network stations.

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-more- rt Network (SPAN) tivity during the misalon y increase in radiation. evlces are carried ndard passive film area which provide Each marn also has k r@adfor cumulative dosage at any t right thigh of the the shoulder or the pressure suiter have been dorfed. Radiation d ate w~t~lnthe pacecraft cabin Is measured by the tlon survey mat r, a one-and-a-half pound device rnwn lower equipment bay near the navigation azxtant. A Van Allen bel% doarimeter rnounW.4 on the aptweeraft gireh frame near the lunar module pilot's head measures and telemeters onboard radlra.l;ion skin dose rates and depth dose. rates to network stations. Proton and alpha partlale rates an8 energies ex4serior to the spacecraft are measured and te1emetered;by the nuclear particle deteation system mounted on the service module forward bulkhead in the area covered by the fairing around the CM-SM mating line, SPAN sritsa keeping tabs on solar flare activity during Apollo 8 will be NASA-operated sltgtions at Manned Spaoecmft Center, Cirnarvon, Australia, and Canary Islands; and Environ- mental Saleneeas Services Adminiatration (ESSA) sites at Boulder, Colo. , and Culgoora, Australia. COVERALLS

6ONS~A~T-WEAR

/ WADI ATION SURVEY METER -82-

NAME: Frank Bo Coaunande

PknYSXCAL DESCR

e from the int in 1950 tical Engineering gy, Pasadena,

gbee of Tucson, bee, resides in Tucson, '

CHILDREN: Fredrick, Oatobsr 4, 1951; Edwin, July 20, 1953. OTHER AGTmITbS: He ~n~Qyshunti ORGAN XZ ATIOMS : te of Aeronautics erimental Test Pilots . SPECXAL HONORS t

Trophy; and rec Teahnology Dist EXPERIENCE: Bo 1, red the Air Poi nd received his pilot training at W~ll~amsAir Force Base, Ari From 1951 to 1956, d to various fighter squadrons in th and the Philippines.. -He"became an in mo-dynamics and fluid mechanics at th in 1957 and subsequently attended the US School from which he gradua instructor until 3962. -03-

~e has aacuaulated over 5B5M hours flying time, lncludlng 4,500 hours In Jet airerait, CURRENT A§SIGNMI@W: COlOnS1 Bonamrn was trelected as an astronaut by NASA In September 1962, He has performed a variety of rspecial duties, Including an assignment as backup conunand pilot for the Oemlnl 4 flight and as a .member - .. - of!- - _' the Apollo 204 Review Board. AB cloartaarnd pilot of the history-making Gemini 7 misalon, launched on Dec. 4, 1965, be participated In estab- liishlng a number of space "PIrrsts"--mong whlah are tiha longest manned space, flight (330 hour8 and 35 minutes) and the first rendezvous of two manned maneuverable spacecraft as Gemini 7 was joined In orbit by Gemini 6.

-end- NAME: James A. Lovell, Jr, (Captain, USH) Command Module Pilot BIR'PHPLACE AND DATE: Born March 25, 1928, in Cleveland, Ohio. His mother, Mrs. Blanche I.'ovellJ resides at Edgewater Beach, Fla. mYSICA& l5EB&IPTLOH: Blond hairs; blu eyes; height: 5 feet; 11 inches; weight;: 170 pounds, EDUCATXON: Oraduat d from Juneau High bChOOl, Milwaukee, Wiscr.; attended the University of Wisaonsln for 2 years, then racelvsd a Bachelor of Science degree from the United States Naval Academy in 1952. MARITAL STATUS: Plarried to the former Marilyn Gerlach of Milwaukee, Wiec. Her parents, Wr. and Mrs. Carl Gerlach, are residents of Mllwaukee, CHILDREN: Barbara L.8 0ct;ober 13' 1953. James A., February 15, 1955; Suean K., July 14, 1958; Jeffrey C.# January 14, 1966, OTHER ACTIV3TIES: His hobbies are golf, swirnmln.g, handball, and tennis. ORGANIZATIONS: Member of the Sooisty of Experimental Test Pilots and the Explorers Club . SPECIAL HOHORS: Awarded two NASA Ekcepti~rmlService Medals, [email protected] Astronaut Winga, t;wo Navy Distinguished Flying Crosses, and the 1967 PA1 Gold Space dal (Aehens, Greece) ; and co-re~lpientof the 1966 Araerloan Astronautical Society FXC&t Achievement Award and the Harmon Intsr- national Aviation Trophy in 1966 and 1967.

EXPERIENCE: Lovell, bl, Wavy Captain, rcacreived flight training f ollowlng graduation from Annapolis. He has had ~um~rousnaval aoiato fs including mar as a test pilot at Air Test euxent River, Hd. 'while there he served as wager for the F4H weapon system evaluation. A graduate of the Aviation Safety School of the University of SouthePn'California, he also served as a flight instructor and safety officer with Fighter Squadron 101 at the Naval Air Station, Owana, Va. Of the 4,000 hours flying time he has accumulated, more than 3,000 hours are in jet aipcraft. -more- CURRENT ASSIC)

On' Deg. 4, 1965, he and c wem launched i 7 mission. The during whieh th lashed: lo of two man Joined In orbit space flight. t that numerous technical and medical ex~~r~m~ntswere completed suc- ceaaf'ully, , The Qewini 12 misaion, with Love11 and pilot Edwin 11, 1966. This &-day 5g-revolu- the Oemlni Progralrz to a successful ~ls~~~t~of the 94-hour 35-mlnute -revolution rendezvous with the na (using for the first time ions due to a radar failure);

-I-ex$rclse; -1 retrieval of a package from the spacecraft exterior; ,an eJaluat1 the u88 of body restraints specially designed fo letting work tasks outside of the spacecraft; anta c Ion of' numerous photographic experiments, the hi& of which are the first pictures takth from space qf an eclipse of the Sun. mini 12 ended when retrofire oezcurred at the beginning of th 60th revolut&on, followed by the second oonlseoutive fully atltonstPtlc controlled reentry of a spacecraft, and a landing In the Atlantic? within 23 miles of the prime recrovery $hip USS WASP. As a result of his partlcipallon In this flight, Love11 holds the space endurance record, with 425 hours and 10 rrrlnutes, for total tint@ sp nt; in space. Aldrin d a new'EVA record by completing 5* hours outs de the spacecraft during two standup WAS and one wnlb f! loa1 EVA. SPECLAL Ass1 : In addition to his regular duties as a member of the astronaut group, Captain Love11 was sslected in June 1967 to serve as Special Consultant 60 the President's C ncil on Phyaical Fitne'ss,

-end- -86-

BIRTHPLACE AND : Born Ootober 17, 193 , in Hong Kong; ndsr (USN retired7 and MPS. Arthur F. Anders, now reside in La Mea&, Calif, PHYSICAL DESCRIPTION: Brown hair; blue ey s; height: 5 feet 8 inches; weight: 145 pounds, EDUGATIQMt Rsoel chelor of Science degree from the 1 Aaademy in 1955.and a Master of e In Nuolear Ehgineca irq from $he Air te of Tecthnology at right-Patterson Air Force B88t9, Ohio, in 1962, MARITAL STATUS: Married to the former Valerie E, Hoard of Lemon Grove, Calif,, daughter of Mr, and Mra, Henry G, Hoard, of Oceanside, Calif, CHILDREN: Alan, February 1957; Glen, July 1958; Qayle, December 1960; Gregory, Dectember 1962; Eric, July 1964, OTHER ACTIVITIES: Bie hobbies are fishing, flying, camping, and water skiing; and he also enJoys ~oacer. ORGANIZATIONS: Member of the Amerioan Nuclear Society and Tau Beta Pi, SPECIAL HONORS: Awarded the Air Force Commendation Medal. EXPERIRNCX: Andera, an Air Force Major, was commissioned in the Air Force upon graduation from the Naval Academy, After Air Force flight training, he served as a fighter pilot; in all-weather'interoeptor squadrons of the Air Defense Conupand, After his graduate training, he served as a nuclear engineer and lnsstructor piloe at the Air Force Weapons Laboratory, Kirtland Air Force Base, N.M., where he was relsponhllble for technical management of radiation nuclear power reactor shielding and radiation effects programs. He has logged more than 3,000 hours flying time0

CuRREM"p ASS1 : Major Andem was one of the third group of astrcmaut;s selected by NASA In October 1963. He has airme served as backup pilot for the Gemini 11 mission,

-end- LUNAR DESCRIPTION

Terrain - Mountainous and crater-pltted, the former risivandsof' feet and the latter ranging from a few lnchels to180 rnlleer in diameter. The craters are thought to be Formed by the impact of metiiorites.' The syrf'ace is covered with a layer of fine-grained material rebsslgbllng silt or sand# as well a$ small rocks. air, no wlnd, and nc, moisture, The temperature ranges from 250 degrees In the two-week lunar day- to 280 degrees below zero 3n the two-week lunar night . Qraviey Is one-sixth that of' Earth. MdcrometeoroldbJ pelt the Moon (there is.no atmosphere to burn then up), Radiation might present a problen durlng periods of' unusual solar activity, . Dark Side - The dark or hidden aid@of the Meon no longer Is a complete mystery. It was fir ph~tographs8by a Russian craft and since then has been photographed mkny tlmes, partlcu- larly by NASA's lunar Orbiter spacecraft. Ori ;in - There is aCil1 no agreement among sczientists on the-#T or g n of the MQOn. The three theories: (1) the Moon once was part of Earth and split off Into Its own orbit, (2) it evolved as a s parate body at the same time a0 Earth, and (3) it formed elsewhere In space and wandered until it was captured by Earth s gravitational f ield .

At 1 Surfaas to Surface -Date II mc. 21 5 p.m. EST 220,874 statutb

Dec. 22 6 p.m. EST - -2Zjt+3?!7..sf;af;\z2_e __ Dec. 23 7 p,m. EST 227,182 staCute

Dee. 24 7830 pomo EST 231,238 srtatute Dec. 25 8 p.m. EST 235,186 statute D~C. 26 9 p.m. EST 238,751 rstatute Decr. 2'7 10 pa, EST 241,779 statute 9-80.

Physical Facts

Diameter 2,160 miles (about t that of Earth) C irculllrerenc e 6,790 miles (about that of Earth) Distance from Earth 238,857 miles (mean; 221 ,463 minimum to 252,710 maximum) Surface temperature 250 (Sun at zenith)-280 (night) . -_ Surface gravity 1/6 that of Earth Mass 1/10Qth that of Earth Volume l/50th that of' Earth Lunar dag and night 14 Earth days each Mean velocity in orbit 2,287 miles per hour Eacape velocity 1.48 miles per second Month (period of rot;atlon 27 days, 7 hours, 43 minutes around Earth) -89-

APOLLX) PROGRAM MANAGEMENT/CONTRACToRs

Direction of the Apollo Program, the United States' effort to land men on the Moon and return them safely to Earth before 1970, is the responsibility of the Office of Manned Space Flight (OMSF), National Aeronautics and Space Administration, Washington, D.C. NASA Manned Spacecraft Center (MSC), Houston, is responsible for development of the Apollo spacecraft, flight crew training and flight control. NASA Marshall Space Flight Center (MSFC), Huntsville, Ala., is responsible for development of the Saturn launch vehicles . NASA John F. Kennedy Space Center (KSC), Fla., is responsible for Apollo/Saturn launch operations. NASA Goddard Space Flight Center (GSFC), Greenbelt, Md., manages the Manned Space Flight Network under the direction of the NASA Office of TPacking and Data Acquisition (OTDA). Apollo/Saturn Officials Dr. George E. Mueller Associate Administrator for Manned Space Flight, NASA Headquarters Maj. Gen. Samuel C. Phillips Director, Apollo Program Office, OMSF, NASA Headquarters George H. Hage Deputy Director, Apollo Program Office, OMSF, NASA Headquarters William C. Schneider Apollo Mission Director, OMSF, NASA Headquarters Chester M. Lee Assistant Mission Director, OMSF, NASA Headquarters

- more - Col. Thomaar H. McMullsn Aselhtant Mission Director, OMSF, MASA Headquarters Dr. Robert R. Bilruth Director, Manned Spacecraft Center, Houston George Me Low Managcar, Apollo Spacecraft Program, MSC Kenneth S. Kleinkneoht Manager, Comraand and Service Modules, Apollo spacecraft Program Office, MSC Donald K. Slay-ton Director, Plight Crew Opera- tions, MSC Christopher C. Kraft, Jr. Direator Plight Operations, MSC (3liffbrd E. Charleaworth Apollo 8 Flight Directors, Glynn S. Lunney Flight Operations, MSC M.L. Windler Directtor, Marshall Space Flight Center, Huntsville, Ala. Brig. Wn. Edmund F. O~Conmor D~WW~OP,Industrial Operations, MSPC Lee B. James Hana&ger, Saturn V Program Office, MSFC willim D. Brown X arr, wine Program Office, HSFC Dr, Kurt H. Debus Dirhector, John P. Kennedy Spercre Center, Fla. Miles Ross Deputy Dlrector, Center Operations, KBC Rocco A, Petrone Director, Launch Operations, lcsc Walter 3. Kapryaul Deputy Director, Launch Operations , KSC DP. Hans F. Qrrmene Director, Launch Vehicle Operations, KSC - more " Rear Adm, Roderick 0. Middleton Manager, Apollo Program Office, Ksc John J, Williams Director, Spacecraft Operations, KSC Paul C, Donnelly Launch Operations Manager, KSC GCerald M. Truszynskl AaJsocihste Administrator, Tracking and Data Acquieition, NASA Headquarters H. R. Brockett Deputy Associate Administrator, OTDA, NASA H8adquarters Norman Pozinsky Pirgctor, Network Support Implementation Division, OTDA Br. John F. Clark Director, 8oddard Space Flight, Greenbelt, Md . Ozro M. Covington Aas3iatant Director for Manned Space Flight Tracking, QSFC Henry F. Thompson Deputy Aersistsmt Director for I'utanned Space Flight Support, GSFC PI. William Wood Chief, Manned Plight Operations Division, GSFC Tecwyn Roberts Ohief, MmdPlight Engineering Division, QSFC L. R. Stelter Chief, NASA Communications ~ivi~ion,QSFC Maj, Qen. Vincent 0. Huston WAF, DOD Manager of Manned Spaoar Plight Support Operations Mail. Wn. David M. Jones UMP, Deputy DOD Manager of P!mned Space Flight Support Operations, Commander USAF Eastern Test Range Rear Adm, F. E, &hatis UslQ, Commander Combined Task Force 130 Pacific Recovery Area (Primary) - more - -92-

The Boeing Co. First Stages (SIC) of Saturn New Orleans V Flight Vehicles, Saturn V Systems Engineering and Integration Ground Support Equipment North American Rockwell Cow. Development and Production Space Division of Saturn V Second Stage Seal Beach, Calif. (sa) McDonnell Douglas Astronautics Development and Production co. of SaturnV Third Stage Huntington Beach, Calif. (s-m) International Busineas Machines Instrument Unit (Prime Federal Systems Division contractor) Huntsville, Ala. Bendix Cow., Wldance Components for Navigation and Control Div. Instrument Unit (Including Teterboro, N. J. ST-12M Stabilized Platform) Trans World Alrlinea, Inc, Installation Support, KSC Federal Electric Corp. Communications and Instru- mentation Support, KSC Bendix Field Engineering Corp, Launch Operations/Complex Support, KSC Catalytic-Dow Facilities Engineering and Modificationer, KSC ILC Industries Space Suits Dover, Del. Radio Corporation of America 1lQA Computer - Saturn Van Nup, Calif. Checkout Sanders Associatea Qger@tional Display Systems Nashua, New Hampshire Saturn Brown Engineering Discrete Controls Huntaville, Alabama Ingalls Iron Work@ Mobile Launchers Birmingham, Alabama (stntcttmal work)

- more = -93-

Rear ABm. P. 5. WcManus USH, Comm&er Combined Task Force 140 Atlantic Recovery Area Col. Royce Q. Olrson USAP, Director, DOD Manned Space Flight Office Brig. @en. Allison C. Brooks USAF, Commander Aerospace Rescue and Recovery Service

Major Apollo/Saturn V Contractors Contractor -Item Bellcom Apollo Systems Engineering Washington, D. C. The Boeing Co. Technical Integration and Washington, D. C. Evaluation General Electric-Apollo Apollo Checkout and Support Department, Rsllabillty Daytona Beach, Pla. Morth American Roche11 Corp. Spacecraft Command and Space Division, Downey, Calif. Service Modules Grumman Aircraft Engineering Lunar Module Corp e , Bethpage, N.P. Massachuaetts Ipstltute of Midance & Navigation Technology, Cambridge, Mass (Technical Management) General Motors Corp., AC Qluidmce &I Havigation Electronics Division, (Banufacturing) Milwaukee TRW Systems IqcL Trajectory Analysis Redondo Beach, Calif . Avco Corp., Space System Heat Shield Ablative Division, Lowell, Mass . Material North A@erican Rockwell Corp. 5-2 Engines, F-1 Engines Rocketdyne Division Canoga Park, Calif. Ehnlth/Ernst (Joint Venture) Electfical Mechanical Tampa, Florida Portion of MLer Washington, D.C. Power Shovel, Inc. Crawler-Transporter Marion, Ohio Hayes International Swing Am Birmingham, Alabama

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etly 180 degreeas op- %ne projected through lslnW.pods refers to a ugh the center of eurface on the the mId-Faolf lc an of longitude once each 24 hotam,

ApolWe--Poin t d the Moon Into mar orb r c8. &.go Ascent tage of taglng Into lunar orbit following lunar landing. AttItude--The POaitiQn Of an 188PO8 8 as determined by the incl2naflon of it of reference; for Apollo, an Inertial, 018 is wed, 88 Zn a rseket engine, nt affixmi to an alr- er stability. hiale by reference to ft before

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Qlmballed 1; i.e., on a Goratrivance orular axes of rotation, BO awlng correc tlon mmentB. and evaluates f'llght arget data, eonverts ssa~yt~ caorhleve the s this data In the

orbltt @rether aativity whlcrh ha@ the Sun as its aenter, Inertla1 Qu rlgsrtion Byat kf-blpeed vehicles. Pltch--’Pke IIPO pace vehiols abmt an axla (2’) that is perpendiaular to Ita l~ng~~dl~laxis. of a spaeeoraf3 that re-enter8 the a~~s~~ereafter flight above It, t that give8 a direcatlm direction of cl*ts motion, @sr of a apace vehicle about Its longl- tudinsll (x) axis. 6 Band--A r~lo-,t”pequeneyband of 3.550 to 5200 m~~ac~cls~ per seaond,

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(Note: 'Phi# list t to Inelude all Ap0110 program a are reeveral aoronynaa that are snwuntered fer the first tlme in the Apollo 8 mlrmlon,)

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