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S P A C E DOCUMENTATION BRANCH 7 5 :; D S 4 2 2 8 DIVISION CODE 256 ^^ 15 AUGUST 1975
LANDSAT- 1 AND LANDSAT-2 EVALUATION REPORT 23 JANUARY 1975 TO 23 APRIL 1975
Prepared By GE LANDSAT OPERATIONS CONTROL CENTER
For NATIONAL AERONAUTICS AND SPACE ADMINISS RATION Goddard Space Flight Center Greenbelt, Maryland 20771 1516177 Ln M U cv '^ ; ,q ry cv in rn 1975 r, 1 ^^ CL .^ ^ rC x! H ry to 1 u C ^ r RECEIVED torA; .0 n U^ G4L^` CYD to U ... m NASA STI FACILiTy u F N ^ ^ INPUT s titi
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SPACE SYSTEM'S GENERAL ELECTRIC COMPANY . . OR.GAN'IZAT!!C)N z (MAIL: 5030 HERZEL .PLACE. BELTSVILLE, MARYLAND 20705); Phone (301) 346-6.000 October 2.0, 1975 :;. TO: Distribution FROM: D. Wise T,4
' Errata for Document 75SDS1228, Landsat-.1 and Landsat-4..Eva.lua;ti.on Report, 23 January 1975 to ; 3 April 1975, dated 15 August 1975.
Landsa.t-1 Page 4-:1, fifth paragraph, delete "currents".. Text should read, "So lar Array Drive Voltages, Temperatures, and....".. .5. Page 4-5, Table 4 -2, Function 1092, title should read '"RMP2 A1TR Current". Page 15-1, Figure 15-1 vertical scale should read "Dumber of Head-to -Tape Contacts (X103).'? d- Landsat-2 P age. 4-1, fourth paragraph, second sentence, delete "currents". Text should x, read "All motor voltages and temperatures were normal".; Page 11-1, third paragraph, first sentence, should read "....on Landwsat -2 s has ranged between 30 - 35 00 during,..". ^i Page 16-.1, fourthparagraph, first sentence,. should read "In Appendix D a scene...".. Fourthpnza...gra.ph, last sentence should read.-;. "Band 1 (Figure D-1) is...".. Page C-10,, Table 2, Figure 2, obliterated function numbers a-re'13032 and 13033.
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Dia C : ^.. c:.,^ : Q I , r .f f <} One pear 75DS42.2'8 Report Daniel G.. Wise, Supe.'rvisor : Off.-Line Engineering DGW/k€m:
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N TABLE OF CONTENTS
Y. se ction Page
INTRODUCTION ...... vii s
1 SUMMARY - LANDSAT-1 OPERATIONS . . . .
2 ORBITAL PARAMETERS ...... 2-1
3 POWER SUBSYSTEM n . . . . , . . . 434
4 ATTITUDE CONTROL SUBSYSTEM ...... 4-1 y. 5 COMMAND/CLOCK SUBSYSTEM ...... S-1 A ; ^ B TELEMETRY SUBSYSTEM ...... 6-1
7 ORBIT ADkTUST SUBSYSTEM ...... 7-1
8 MAGNETIC MOMENT COMPENSATING ASSEMBLY ...... 8=1
9 UNIFIED S-BAND/PREMODULATION PROCESSOR ...... 9-1
10 ELECTRICAL INTERFACE SUBSYSTEM ...... LO'-1
11 THERMAL SUBSYSTEM. 11-1.
12 NARROWrBAND'TAPE RECORDERS . . ..12-1 1 # 13 WIDEBAND TELEMETRY SUBSYSTEM ...... 13-1
14 ATTITUDE MEASUREMENT SENSOR ...... 14-1 i 151,5 WIDEBAND VIDEO TAPE RECORDERS 4: ...... 15-1
1'6 RETURN BEAM VIDICON ...... 16-1 r r..^ I! MU`LTISPECTRAL SCANNER SUBSYSTEM 1T-I
18 DATA COLLECTION SUBSYSTEM ...... 18-1
APPENDIX A - LANDSAT=1 ANOMALY ITT . ..• .. .. . A-1
APPENDIX B - LANDSAT-1 SPACECRAFT ORBIT REFERENCE TABLES ...... B-1
APPENDIX .0 - LANDSAT-4 PIR-U°-1N23.-ERTS-131, BIT :ERROR: 'RISE ON :NBR-2 . .. . C-1
TRG PAGE fLliNlC Ndr FIB L5-1 PR iR
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p LIST OF ILLUSTRATIONS
F`. Figure Page 2.-1 Typical Subsatellite Plot of the LANDSAT-1 Spacecraft ...... 2-3 w 2-2 Effects of Orbit Adjust on Ground Track ( LANDSAT-1) .. .2-5 2-3 I ANDSAT-1 Local Sun Time Equator Crossing-Descending Node ...... 2-7 - -
3-1 LANDSAT-1 Predicted Midday :tolar Current ...... -...... 3-2 j 3-2 1A (Midday) Degradation vs.. Days (LANDSAT..:1) ...... 3-3 :V i 3-3 Actual and (Paddle) Sun Angles (LANDSAT-1) ...... 3 3-4 Predicted Beta Angles ...... 3-5 ,t 3-8 Seasonal Solar Intensity Variations . .3-7 W
€ 4!4 LANDSAT-1 Gating Frequency vs. Time ...... 4-3
5-1 LANDSAT-1 Spacecraft Clock Drift History ...... :5-2 i E 5-2 LANDSAT-1 Spacecraft Clock Drift Rate ...... 5-3 6-1 Power Received at Alaska from VHF Transmitter A (0.3 Watts) - LANDSAT -1 .6-2 9-1 USB Power Output History (LANDSAT-1) ...... 9- 9-2 USB (Link 4) AGG Readings :at Goldstone with 30-Foot . Antennaf ...... x k 11-1 LANDSAT- 1 Sensory Ring Thermal Profile ...... 114 i 134 LANDSAT-1 AGC Readings at .Goldstone with 30-Foot Antenna: Wide . Band; R•:,t Pur Amp-2 (Link. 3) . . . 13-3 -J ,N 15-1 VMVTR-1 Tape Usage by Footage (LANDSAT-1) ...... 15-1
17-.1 Number of Scenes Taken for U. S. at Each Geographical Location, LANDSAT-1 . . . 17-3 .17-2 Scenes Taken This Reporting. Period (LANDSAT-1) . .17-5 17-3 1 Quantum vs. Orbit (LANDSAT-1.} ...... 174 17-4 Quantum vs. Orbit (LANDSAT--4) .` . . 17=9 _ _-
17-5 Quantum vs. Orbit (LANDS:AT-1) . .. . . 17-1I x+ I 17-6 Quantum vs. Orbit (LANDSAT-1) ...... - .. .1743 f 17-7 LANDSAT-1 Line Length vs. Orbit ...... 17-15
^ ` 18-1 DCS Messagege Receipt :History (LANDSAT-1) . .
^f
iV
. II: ..:... 'F 4: ,-^- • f , x LIST OF TABLES 's Table Page V SN 1-1 LANDSA,T-1 Brouwer Mean Orbital Parameters . 2-2 3-1 LE1NDSi4T-1 Mayor Power Subsystems Parameters . . . . . 3-8 ^ ti 3-2 LANDSAT-1 Power Subsystem Analog Telemetry (Average Value for Data Received in NBTR Playback) ...... 3-9 4-1 LANDSAT-1 ACS Temperature and Pressure Telemetry Summary ...... 4-5 4-2 LANDSAT-1 ACS Voltages and Currents ...... 4-5 4-3 LANDSAT-1 ACS Attitude Errors and Driver Duty Cycles , ...... 4-6 g 5-:1 Command Clock Telemetry Summary ...... 5-4 6-1 TLNI Telemetry Summary . . , ...... 7-1 LANDSAT--1 Orbit Adjust Summary ...... ; . 7-2 7-2 LANDSAT-1 OAS Telemetry Values . . . . • • • . r 7-3 8-1 MMCA Telemetry Summary (LANDSAT-1) . . . . . 8-1 9-1 LANDSAT-1 II$P/PMP Telemetry Values . . . . . 9-2 10-1 LAND5AT-1 APU Telemetry Functions . . .10-1 b 11-1 LANDSAT-1 Thermal Subsystem Analog Telemetry (Average Value of Frames for Data Received in NBTR Playback) ...... 114 ? 11-2 LANDSATCompensation-1. Load History,: ...... 11-4 X•2-1 NBR Operating Hours by Modes (LANDSAT-1) ...... 12-1 324 Narrowband Tape Recorder Telemetry Values .: 124 12-3 LANDSAT- L Narrowband Recorder Subsystem Performance . . , ...... 124 13-1 Wideband Modulator Telemetry 'Values, LAI3DSAT-1, .. . 136-2 5y 14-1 LANDSAT-1 AMS Temperature Telemetry ...... 144 15-1 WBVTR Telemetry Values (LAND5AT-1) ...... 15-2 15-2, WBVTR-^1 Function Values by -Made in Orbit (1ANDSAT-.1) ...... ::. .. I5^-3 16-1 R'BV Telemetry, Values (LANDSAT-1) .. . . 16-1 17-1 LANDSAT-1 MSS: Telemetry Values ^r 17=2 LANDSAT -1 Sun Calibration Orbits ...... , . 17 17 17-3 LANDSAT-1-MSS:Operation Orbits in High Gain Mode, Mux Compressed- , .: 17-17 18-1 DCS :Telemetry Values ...... 18.-1 18-2 D.CS Qualitative Performance {LANDSAT .1} LS.-1 v/vi a>. 7_ u INTRODUCTION This is the tenth report in a continuing series of documents issued quarterly to presed flight perforce analysis of the LANDSAT-1 Spacecraft. Previously issued documents are: 72SD4256 ERTS-1 Launch and Flight Activation 18 October 1972 Evaluation Report 23 to 26 July 1972 728DI262 ERTS-1 Flight Evaluation Report 28 November 1972 23 July 1972 to 23 October 1972 zt.. 72SD4224: ERTS-1 Flight Evaluation Report .27 February 19.73 23 October 1972 to :23 January 1973 73SDI249 ERT0-1 Flight Evaluation Report 29 May 1973 23 January 1973 to 23 April 1973 7304260 ERTS-1 Flight Evaluation Report 10 August 1973 23 April 1973 to 23 July 1973 73SD4274 ERTS-1 Flight Evaluation Report 28 November 1973 F: 23 July 1973 to October .1973 w 74SD4265 ER TS-1 Flight Evahia`ion Report 26 February 1974 23 October 1.973 to 23 January 1974. 74SD4217 ERTS-1 Flight Evaluation Report 18 May 1974 23 January 1,974. to 23 April 197.4 cz: 74SD4236 ERTS 1 Flight Evaluation Report 15 August 1,974 23 April 1974 to 23 July 1974 74SD4256 ERTS-1 Flight Evaluation Report 31 December 1974 t- 23 July 1974 to 23 October 1974 76SD4222. LANDSAT-1 Flight Evaluation Report 30 April 1975 23 October 1975 to 23 January 1975 P This report contains analyses of performance for orbits 12476 to 14000 for L• ANDSAT-1. M > LSFi vii/viii SECTION 1 SUMMARY LANDSAT-1 OPERATIONS The LANDRAT-1 spacecraft was launched from the Western Test Range an 23 July 1972 at 16408:06. 506 orbital The launch and injection phase of the space flight were nominal and deployment of the apacecraft followed predictions. Orbital operations of the spacecraft and payload subsystems were satisfactory through Orbit .147 after which,an Internal short circuit disabled one of the Wideband Video Tape Recorders (WBVTR-2). Operations resumed until Orbit 196 when the Return Beam Vidicon failed to respond when commanded off.. The RSV was commanded off via alternate commands and since that time LANDSAT-1 has performed its mission with the Afthispectral Scanner and the remaining Wideband Video Tape Recorder providing Image data. The remaining Wideband Video Tape Recorder experienced four suspensions of operation, the last In being in Orbit 98. 81 on . 2 July 1974,. and has not been used operationally since: Orbit 4396 .ah. integrated circuit chip in the, TMP failed = disabling four TLM functions. COMSTOR "B" has an. intermittent problem with cell 12, whicL is not being used operationally. The "B" section of the U SB with full power output of 1. 5 watts was subs6ituted for the "All section in Orbit 10068 because of excessive decline of transmitter power. The pitch aywheql stopped for 2 .minutes in Orbit 8040; and for 8 hours, 2 minutes in Orbits 11125 . The RMP was switched to 11130. It has been kept close to zero speed ever since, using pitch-bias control l current from B to A in Orbit 11257 as a precautionary measure after RMP B began showing operating var- iations. The DCS subsystem was turned off after Orbit 12690 and the function assumed by LANDSAT-2. Spacecraft performance has not been degraded by. these anomalies thus Ear, except for the Inability to record remote MSS imagery. ORBITAL PARAMETERS The initial orbit of LANDSAT-1 required some correction at Orbitsit 38, 44,. and 59 to achieve the desired 18-day repeat cycle. During Or-bits 938, 2416, 6.390 and 7826 was necessary to fire the -X thruster of the orbit adjust system to maintain the ground trace in the desired 18-day repeat pattern of + 10 nm. On September 29, 1974, the ACS control system fired gas during the spacecraft emergency (pitch pywheel stoppage) which resulted In an unplanned: orbit change similar to firing the -X thrusters, During orbits 1136t, 11464 and 13611 the +X thruster Was fired to maintain the ground trade in the desired 18-day repeat pattern of + 10 nm. POWER SUBSYSTEM (PWR) U The power subsystem performed well throughout this report period. Solar array current has. been slightly lower than predicted'. Data fi?,om this oeriodshows the array degradation to be X26.1% after 33 months in orbit. The power subsystem will meet LANDSAT-1 power requirements through 1976 with the present payload configuration. ATTITUDE CONTROL SUBSYSTEM (ACS) U10 From initial acquisition, the ACS, performance has been excellent except between Orbits 11125'and 11130 when the Pitch flywheel stopped and restarted approximately 8 hours later. Pitch flywheel speed, after Orbi.t 11136i was maln. tE.Oned between. "20 RPM and .-I.00 Htp%by use of P iaswhich eliminated pitch gating. Similarly. rollmomentum unlading was acc . omplished by eDiffployingtRoll Tach Hi Gain during orbits of non-MSS activity to reduce Roll gating. During a'.3ortion of Orbit 13922, the Single sun ^ ^ Scannermode was exercised successfullyAll in a test designed to eliminate normal night to day trans- tents effecting MRS suncallbration. functions are active and within specifications at the end of this. report period. RMP A is operating normally and the SADS are tracking accurately. The forward IR scanner pressure has decreased slightly from S. 33 PSU (Orbit 12749) to 3. 08 PSTA (Orbit 1.3970). t. tie e-2 COMMAND/CLOCK SUBSYSTEM (CMD) All stored commands and real time commands were executed except for the expected one-in-approximately 10, 000 associated with the logic race conditions. No serious problems have resulted from these few com- mands failing to execute. Use of cell 12 COMSTOR "B" has been discontinued for active commands be- cause of intermittent time delta errors 'of, 266° seconds. Occasionally, stored commands are blocked by real-time sequences which overlap in time. The specific cause has not been determined. The VHF com- mand receiver was switched from side B to side .A at the time of USB subsystem switchover to side B. The PCM regulators occasionally switched, without commands, from Unit 1 to 2 and then back from 2 to 1, and was attributed to VHF input signal transients in the command channel. TELEMETRY SUBSYSTEM (TLM) The telemetry subsystem has consistently performed in an excellent .manner. Memory .Section 0, 0 in use since launch was changed to the 1, 1 mode in Orbit 12565 on 10 January 19.75. All dropouts have been associated with known link or ground problems. Except for the failure of an integrated circuit chip in the TMP (Orbit 4396), which disabled four telemetry functions, all functions have performed in a nominal manner. The VH1F transmitter is fully effective; and shows little power loss since launch. ORBIT. AD UST :SUBSYSTEM (OAS)' The orbit adjust system has been fired ten times; seven times using the -X thruster . and three times using the +.X thruster. Three X firings were for initial orbit corrections and four --X for orbit maintenance. The three +X firings were used for orbit maintenance.. Pressure/temperature parameters continue to be normal.. MAGNETIC MOMENT COMPENSATING: ASSEMBLY (MMCA) The Magnetic Moment Compensating Assembly was not operated during. this report period. There have been a total of eleven operations since .launch. The MM•CA has held the Pole-Cm commanded in prior orbits. Telemetry values continue to be normal. UNIFIED "S" BAND/PRE-MODULATION PROCESSOR (USB) The Unified S-Band Subsystem has operated satisfactorily since launch. In Orbit 1:0068 the B=-Section was substituted for the A-Section because the A-transmitter power output had declined from 1.5 watts at launch to 0. 14 watts with noticeable loss of I)CS coverage. The B =trransmitter with a power output of 1. 5 watts has operated without Power drop. since turn ON, restoring furl DCS .coverage until. DCS. turn off in Orbit 12690. ELECTRICAL INTERFACE SUBSYSTEM (EIS) The Auxiliary Processing Unit (APU), Interface Switching Module (ISM) and Power Switching Module (PSM°) performed normally.during this report period. The RBV switching relay :(within the PSAQ failed in Orbit 196. THERMAL CONTROL SUBSYSTEM. '(Tl The thermal subsystem performed normally throughout this period'. Temperatures decreased slightly due to decreasing sun. intentsity.. 1 ` i Y 4 b i". r e { {kjj NARROWBAND TAPE RECORDER SUBSYSTEM (NBR) sd !^ Narrowband Tape Recorder A (NBR-A) has continued to operate satisfactorily without incident. NBR-B f became noisy and was temporar ily turned OFF in Orbit 13015. NBR-A is handling the entire telemetry Record and Playback functions on a restricted schedule to conserve its life. Total ON Time to 12173 hours F for Recorder A and 11851 hours for Recorder B. W13DEBAND TELEMETRY SUBSYSTEM (WBTS) The Wideband. Telemetry Subsystem has continued to operate satisfactorily. The p^*-,er output has conthned } at 20 watts since switching to that mode in Orbit 30. WPA-2 is currently in use. WPA-1 was used with RBV to Orbit 196 and subsequently with MSS between Orbits 1890 and 2099 during Apollo 17 operations. ATTITUDE MEASUREMENT SENSOR (AMS) The AMS continues to function normally in all aspects. WIDEBAND: VIDEO TAPE RECORDERS (WBVTR) a rv. WBVTR4 .failed aRei: 10 days in orbit. WBVTR-1 had 4 major disruptions in service sin_ ce launch and ) was removed from service after Orbit 9881. RETURN BEAM VIDICON..(RBV) The Return Beam Vidicon has been idle since Orbit 196 when its prime input power switching relay failed. a tt RBV per-formed satisfactorily up to that .point and is available for use.: if needed, by an alternate switching mode. MU LT- WPECTR•AL SCANNER SUBSYSTEM (MSS) a ' The Multispectral Scanner Subsystem continues to operate in a completely satisfactory manner.. It has imaged nearly all of the land masses between the .latitudes of 81.420. All units of the Subsystem are k normaland stable. E now operates in real time only and provides data to Brazil, Canada, and Italy as well as an the USA. DATA COLLECTIbN SYSTEM (DCS) J The Data Collection Subsystem operated satisfactorily thru Orbit 12690. Only Receiver A has been used. y After Orbit 12690 the DCS subsystem was turned off and the DC6 in LANDSAT; 2 assumed this function. P^ -_. iU ' r UPUI t^`c m s I ; IN-ORBIT PAYLOAD SYSTEM PERFORMANCE _ LAUNCH THRU ORBIT 13980 LANDSAT-1 a R:13V Total Scenes Imaged 1890 AVG. Scenes/Day 139 Total -Area Imaged 14.7 i.1 (millions of sq, mi.) a ON TIME 14.0 ON/OFF Cycles 91 i f' % Real Time Images 57 % Recorded Images 43 MSS Total. Scenes Imaged 165,707 ' f, AVG. Scenes/Day 172 Total Area Imaged 1,444.9 (mw.lons of sq. n. mi.,) ON TIME (hr.) 1,748 67 ` SO N/OFF Cycles 139 237 Real Tithe -Images 7:2 ti % Recorded Images 28 C t a DCS Messages at OCC 1,152, 045 7 Non-Perfect MSGS 90; 691 Max, DCP's ACTIVE/DAY 114 Users 44.;' Avg. MSG/Orbit 181 ON TIME (hr.) 23, 820.2 . WPA-1 % Real Time Mode 55 F % Playback Mode 45 ON 'TIME (hr.) 31.9 ON/UFF Cycles 311 t E WPA-2 % Real Time Mode 72 a .. % 'P/B Mode 2.8 014 TIME (hr..) 1, 605.3 ON/OFF Cycles 10,.843 s W.BVTR-1 . °fo. Record Mode 38 % Playback Mode 41 ? i Rewind Mode 20 ? _ % Standby Mode 1 Minor France Sync i I Error Count in P/B 1501 ? Time Head-Tape Contact 13266 (hr') Cycles head-Tape Contact. 11, 954` f ON TIME (hr.:) 927, 6' ^ WBVTR-2 % Record Mode 38 .- % Playback Mode 41 1 '^ % Rewind Mode ,20 w % Standby Mode 1 MFSE Count in P/B Failed Orb. 148 Time Head-Tape Contact 5.1 (hr•) Cycles Head.-Tape Contact 44 re; ON TIME (hr.) 6. 5 t;. 1-4 r:. ... ., .. ^;'i A. .: ^^'-n. •anus. zF.-`^ '-Yi /"'•CK,. , .. 3+t ^i9_tis3a"^.?is ' Fi{^'..^ W^L,dlrt'M7 i'•,.C:^.-ei. S f^ U SECTION .2 j ORBITAL PARAMETERS j^. tl LANnsAT-1 LANDSAT-1 launch and injection was satisfactory and required only a minor orbit adjust to achieve normal parameters. These adjustments were trade in Orbits 38, 44 and 59. After several 18 -day repeat cycles, orbit maintenance burns were trade in Orbit 938, 2416, and 6390, 7826, 11367, 11464 and 13611. An unplanned orbit change occurred due to freon gas expended during the pitch flywheel emergency (Orbits 11125 to 11130). The orbital p arameters are given in Table 2-1. Figure 2 -1 chows the sub-satellite plot and. Figure 2-2 shows the longitude error as a function of time and orbit maintenance burns. The longitude error has been maintained within the + 10 nm average in the east-west direction at the equator as pbumed Figure 2-3 shows the change of sun time at the descending node equator crossing. Appendix C gives ground trace repeat cycle predictions. LS^x '" - '^...., ,£^^: fir.-ls.,k Vitae- . rhti ^••:^•-'w,,nmr-.:.c:, „.:^zr;NG i Table 2=1. LANDSAT-1 Brouwer mean Orbital Parametsrs Element Two Body Nodal Argument Right Mean Apogee Perigee Inclination Semi Major Period Period of Perggee Ascension Anomaly Date (KM') (KM) (Deg.) Axis (IM) Eccentricity. (Min.) (Min.) (Deg.) (Deg,) (Deg.) 25 Oct 1972 912.3 898:1 99.103 7285, 850 0.00132 103.152 103,268 93.721 1.060 86.484 25 Jan 1973 922.3 893.1 99.090 7285.865 .0.00200 103..153 103.268 133.693 91.805 52.797 25 Apr 1973 911.056 888.763 99.073 US& 767 0.00073 103,151 103,.267 168.857 181.411 11.098 25 Jul 1.973 914.:341 9006 81C 99.068 7285.741 0.00093 103.150 103.266 95.602 268.944 84.301 25 Oct 1973: 922.013 893.229 99.056 7285.. 786 0.00198 103.151 103, 266 65,.071 0.291 301.002 -25 Jan 1974 915. 873 899.111 99.041 7285.657 0.00115 103,148 1034 264 160.86(! 88.606 19.049 24. Apr .1974 920.190 . 912.672 99.023 7285..691 0.000802 103.149 103.265 117.631 176.743 62.319 23 Jul 1974 922.363 892.629 99.017 7285.661 0.002041 103.148 103..264 109.225 269.779 70.540 23 Oct 1974 918.657 896.316 99.004 7285.652 0.00153 103.148 103,264 150.750 354.743 29.110 s 24.3an 1975 914.18. 900, 67 98.990 7285.590 0.000928 103.147 103.262 278.848 85.403 261.138 24 Apr 1975 914.74 900. 05 98.972 7285..559 0.001008 103.146 1034:262 37.047 173.043 142.764 i _ -.^ _...• ff' .r,. t.+--'dtm..x :a.^...+.-. .... ^.-x'nYA\: ^ e^H ..u..v :i ns+-i . r.r,..PR•.. -..e>x;^ ^. r.w^eae-e•ew,wusnvw^^.?ww•w.yMi.•• rrFn^a+s+^«..^-r.^^^u.+.+s^v^+N+.ne.w:.ra...e?-+t.a^^ws.twssf.'.vu^w...^.+..a...+ai...'n..'-.r.^s:.n`r+!ren•e•^n^.. ..w-.-..n+^^^.-e'r .. rv-^+.^^- _.^.^...._ W 4.1 18.0 ..166 160 196. IID '107 90 76 60 43.. 30 15 0 1S 30 45 60 ZS 40 106 20. 137 150. 163 ISD es es 1 ad ULJA !aP WNK 46 9A 11 ;EGp FNT 'MA4 WTR - - Rp5 30 CV1 HAW F YR S' Y6 16 _ . a EQ ATOR 14 13' IZ 1:1 70 7 L 7 EO UA7 qR 5 d G M $ Z - j AGN I 't a ' IS - INSERTION IS V f TAN 3 6UR' CRO 7 ' 30 _ - . ,gyp HSK ' AGO i ORR dv s8 ^S I ,^ 60 60 >2 77 75 _ e 05 Ir e 110 . ON 150 133 170 ^f06 >a0,. 76 80 43 30 M 0 15 30 43 60 75 90 103 120 133 130 05 00 w Figure 2--1, Typical Subsatellite Plot of the LANDSAT-1 Spacecraft ,p F1f,"" , - 1-111 - W.r 9 a 7 4 3 z FASTI 0 WEST -1 -4 -5 -6 7 --a, -9 BOUT fRAft Y 'a f 5 a s i a 9 1i ORBET ADJUST NO. 7 +6,85 ORBIT ADJUST NC, 6 ACS GAS DUMP a +6.Z0 +6.53. t v - - N PER IOD OF } h a HIGH ACS W PITCH GATEE a N HISTORY m f Q 1:D18.1 w F m U. o- —257 N ^ § ORBIT ADJUST U fVO: 8 -4.90 iORBIT ADJUST.N0:.9 a I ^. 1.. L. . I I: G, _ [ W1. !. I I'.. 1. i I 1 L . 1 L 1: I _r 1 1__ 1. 41 42 43 44 .45 46 47 48 49 50 X19 20 .21 22 23 24 25 26 27 28 29 30; 31 32 33 34 35 36 37 38 39 46 . : ^ 1 ..I L I i... I I :^. 1 - _ I.. . E t. ..I.:. ... .,1 I, E.. 1 . I -.1 I :.. I . _ 1:. _ 1. ... 'I. ^ ' L I: 1 c 1 p 1: F830 5081 5332 5583.5834 6095 .6336 6587 6838 7089 7340 7591 8344 '8595 8846 90979348 9599 9850 101'DI 1'.0352 10663 11A05 1'4607 12109 lash 1. 7842 8093 s - h yn Figure 2-2. Efrfectsx ' g Ground Time U-1 aw r^ f9lbo _A1kIE ORBIT ADJUST_ 'NO. 7 +5;85 ;4'C5 GAS. DUMP +5.53 v r+v y ^ N 3;IOU OF } a1' GH ACS ITCH GATE .HISTORY m - 1'01'81 _Q4B h ^ Lb _2,57 ORB T ADJUS " NO. u' D, A-4.90 m ^, r ORBIT ADJUST NO.9 +fi:Z9 'ORBIT ADJUST NO 10 q. C-URREAIT REPORT PERIOD . wi 37 ,38 39 40 41 42 43 44 4.5 46 47 48 49 50 51 52 ss 54 55 56 G 28 29 30 31 32 33 34 35 36 :. I . 7089 7340 7591 7842 8093 8344 6595 8846 9097 .9348 9599 9850 10101 1035210603 1;1•105 11607 12i09 12614 43113 13st5 MIT s. Figure 272. Effects of Orbit Adjust on Ground Track (LAND 3AT. 3.) FOLD ^. ... . ;_ _, ,.. , ; .f s3 ., .. _..._.; .., ,:.._ .....^ .ss>sc _ - i '^r r.- . rr , r - cvE': ^ v :^sx; t",;r,^ ^v.+^'? xkxavM'ifE4fs ^^.}{ -> r ^ w^ OEM. mC ! ` [? ^^ r , F+: 0943 09az' 0941= .' . 0940,' a 0939= - D93T 0936: o x '0935; m 's F 0934 0U rz Ts ^^ 75 SECTION 3 POWER SUBSYSTEM (PWR) LANDSAT-1 The solar array continued to provide excess energy for the payload and spacecraft load throughout this report period. Compensation Ioads and auxiliary loads dissipated the excess power above the battery. and load requirements using LANDBAT-i power management procedures. Midday measured solar array current tracked aligbtly below the values predicted earlier due to higher than predicted beta angle varia- tions. Solar array degradation was -26.10 at the end. of 33 months in orbit. The power subsystem is predicted to have adequate power through 1976 . for the present LANDSAT =1 payload configuration, and may etdend to 1977 and 1978 depending on the electro-chemical. degradation of the battery packs for that period. A plot of measured and .predicted midday solar current is shown in Figure 3-1. Figure 3-2 shows actual and predicted solar array current degradation. Figure 3-3. shows . actual sun.angles to the spacecraft and solar panels. Figure 3-4 is a comparison of predicted beta angles (sun angle to orbit plane) for LANDSAT -1 and LANDSAT-2 in 1975. Figure 3-5 shows seasonal solar intensity variation. It is noted .on Figure 3-1 that the high noon solar array current is slightly lower Man predicted. This is due to slightly differ- ent solar panel sun angles and operating point high noon solar array degradation than, initially predicted. Battery papacks avera geda yptypicalical 8.5.to 9% Depth -of Dischargerge (D OD ) during.. this report period. Charge and load shariug.were satisfactory except for Battery .6. The load, sharing of Battery 6 continued to drop, reaching. about 7.7% around Orbit 13300. At the time, the battery had a charge/discharge ratio of 2.:66 and its temperature. had. climbed to 310C. Therefore, the battery was turned off in Orbit 13M for a restoration cycle, expepting a recombination of gases within the. individual cells. The :battery is die- charged through a telemetry load and is scheduled to be turned on when its voltage reaches approximately 26.5x. Due to the Battery 6 anomaly, the temperature spread bettueen .batteries reached as high as 120C during this report period; but, since turn' off and clue to decreasing sun intensity, has dropped, reaching about. 69C at the end of this report .period'. The power system electronics performed well in this report period. with all voltages stable. Table 3-1 shows major power subsystem parameters and Table 3-2 shows power subsystem telemetry for selected orbits:.. Scime .parameters in Table 3.-2 may be slightly different from Table 34, because Table 3-1. uses . a power management time span (night followed by a day); whereas, the time span used in Table 3"2 is the playback period from the N{BR. The Shunt Limiter has not operated since Orbit 3 because the unregulated voltage has been held below cut-in voltage by power management. -1 3= E 12. (PEAK LEVEL) 1 11 MSS+ I WBR +2OW W9`DLK (250 Fmr) RBV + 2OW. WBDLK `14 50 FME) ('AVERAGE LEVEL): MSS + 20W WBDLK (450 FME) m 1.0.. : ; (P EAK .LEVEL) it Q AVEMWE LEVEL 9. MINIMUM S/C WITHOUT PAYLOAD B ON } a Z 7 CURRENT O Z REPORT 6 PERIOD _ - - 1:972 S9T3 11974 1 1:975_ .. 1976 1977 ..... 1978. G 0 200. 4.00 6.00: 800 1,000 1200 1400 1600 11800 2000 LANDSAT .1 DAYS SINCE LAUNCH j ^.(}'^#^Sf{_iYSL. 1^.^?'Ih'w^^b^.7,4^4n'^ "+1i '.rt3+=:YJ:31F' t_Yp'3i^a4}:?.ri SI^t (:vl' H .l Y"e1?'^i%7.".'>3 10 43. 9 4z 4s s 7 u 40 u u 6 39 1U 38. 5. aW' I 4 37. S e 3 a 36 C W, 33 2 E g 1 ^ 0. 34' s F . 1.972 0 p 0 33 Ix s ^,132. Z .0 p F. ..2 } w. z 30 .` -3 L Q -4 z 29 e ur -5"m 28 G -6 27 r -7. 26' :. . 1:00 5 DAYS IN ORBIT F Figure :34. Actual and (Paddle) Sun Angles (LAND$AT-3). xi" 4 .=xys^u. .: fa.. ^...._-.i aw_Aa.v..w....t!.n^_^i^-c^-t^n..r,...^S.1.audl.a^_^'.K4•sir1.,_..S.zinnt_a-rs vL:'-n'F Lad.-.wi3Mf:.u. .u+l p,:vE-.i ^:1: ..r..".G^.S.rS]'Y.a.^r.o-...L..1''.S-^•6..h:#tY.'^!.yS'.ear__ JULY AUGUST JANUAMY FEBRUARY M ARCH APRIL MAY JUNE S. 16 to 20 25 D 10 IA 20 i1! a 40 15 20 to -S 10 17 20 R4 0 iv t5 20 25j 11 10 to Iry A i0 • + ,, L ^ ,1 e ,1,€ t t r - S f+ t ilil 't 1 r + I €- _I ' I 3' a i 1 €. I-u;L 20 If I_ + _ i e , - 1 , I E II I` I y Ai ,il ,. }, 1 13 -r t t - k ^;'i1 i -"-- ; •; ---^- ,r ,, f - i,€ ! , :.., t ; —•{. ,!I i t , • ,,-_. .:^` '+ ,,' 3 k. t r€ 4..-1114. l .^ - _ T 1, I'' I , Mh I ^Tril'.,I. I €-- l I ^} L --- - - N -,^ it "' i i a I , I- _, if f•! '+ t 7 l' tl, i. i f r , ilr i t i ^ 1 , i i t:r .k .1211 p ' 1:...... ^. 30 7. ----,^-- _ fw ! v ^F _, €._^' '^ - I' I. I '^ "k. 1 }f{ . k •€ 1 . 1 L k 1 -1-Y 1 7 '.. I 1-_- i i 1' I k i k I I '' -^ f 6 to 1IS 2b 2S ! 6 16 19 26 25 A iR f i 2A 2 .4 - 6 16 IL 110 '25 _. -t0 is ^O2 A^ 10 IS 2R 7 •S 6 ke] 1% $0 2!1 L 10 fK 1s:. JANUARY F69RUARY_ MARCN.^ - . APRIL MAY JUN E JULY AURUG 19.?5 f LS•-1 s...r, nuke JULV ^UCUST saine iDER dCTC, Blsq . rlavli+. eea ouE1+en11 SIt! 20 25 r W 1tl RO ¢S 'J I17 1-1 20 :IS 4 IA 15 PO 85 4 fta 15 2Q . 25 6 !4 19 âO S!f t}.. 10 11f 7A ¢'1. 6 14. tD 24 27 i , t I^^ I ' Iltt `' t t!I 1^1 : I E I I ^ ^ ^i Ij ' ' I 1,: i't Ft' ! € I s l ( - ^. ll I ^ ..._ _ ^ r1 'it I: ,; i ^ , I t, l I: ^-: ^ _ ^ 1^ 1 , j, T i ^ F 1 ^ J;•: 1 I f j , 1, Y 1 ^- 7 1' { i! T; i V I IA ` I . i , ! I RI I I £1 . ^ 1 Ir ` _ 11 Y '' ' ^ij iSt ' fi l, I i ! ; l RL t ! , iI r + f I I i ' , : 1 I, I { I I _ #c:' I !t €j € _ { _ iY' !. 111 1 1 1 € , , I 1' ^ , t I^rl t , '' = it € I' !'I ^;I 1 1__ - ' TL- 1 T_-^ iL 1 ! t ^ s. •: ° , .t S ^^ , 1 i €^3 I i ''!i I •I -; (+ :^iF t.^i I I^t 1 : ^ t 1 • ` ! r.l - , ^ l,t E. ; ]A _ , 'A.I ! I '1 ^ ..- ..I-.-.T.^ .I .}._. ... _ _ __•. '' J I ji! I 11 = I f _ ! I ^ I , I , 4 , I tf r t},! 1 €_ j -r ._ __..J OF , 1 ^Y I ^ ^ •^ , -1,1 1 J 1 , ....t ' ' 1 ^ (_,I Ic f i, FI= rl• ,i I. ' I ^ - 1 , , _ ' I ^- -1 , i f r jtT i}', i 1 € 1 1 I t I_ i , t ,' t I E ,j ;^, _ :; I' If. IiI :fit r' _ t I '. ; I j '^ ! , '€' '' FWD T H i i^ I t 11 ,'I t 1 - ;. I t - i t 1' I 1 ^ I I I. 1 11 I I'. `t 11 4 1. - 1 II ! i - 1 I I. r l f. - , - . .i. i . »lY .- i. I -,, I ' ,+Ii, :T[ 1! I 1 ' i. 1 ,.€: 1 ^ 4 i ( ( h F L. ^'_ I ^. ate_ ^' - .t.^ t ^ — 1 ^_ 1 ^. -t -, , ^ ^^ :'ft [ `^^ I IS E I ^. II r I ! I YI I e ^ ^ ! ,I .} ^ 1^, 1 I. .^ ^. 1 I ,it t Lt f 11 t' 1 1 ;_ ! ^_ I t i , ^ 1 I ^ 1^ 1 i I : 3 i s 1 ^ i I _, - S - ID f ,l .2A 39 D IS 20 2L ^ 90 -i5 26 45 6 'jug 1!. zo J286 10 IF 20 2S- 6 YO 13 @O 14 1>; 10 16 i^O Z3 , IJ ac"ToaER NOVE/OOER OECEMSFR ..re JUI,YE -^ JULT - AUGUST 6EPTEM BHR 1975 FO UT M Figure 3-4. Predicted Beta: Angles x LS-1 3"5/6 .:. . .S :SF^ ^, [$=" :. .. FYew=,.`^'i kiWM'v^rv7^''~ 'FY -,:., :.;3°1'5,1.^"_'fer':.'ES5 3^i'S- #"ems=..Y^'?S^°^V.<. ^v. K.'Y%.i`e^e<. e^^f . _ f Fsi nt?.°..F. F'"'\^..Y nh v'N.^TH_:^.-Af:_: i yl R'Fis tom i:;hF.. v:(.Rr :: ^ iWuY '.SP.'T ],K. F..Y ) e'n`^°Sia"Si ':'3 U 3..03 M Lo o0 . 1.00 9499 zcn tar 0 98; z V 0.97 W. 0.96 1972, tk973, 1 1974, 19.75, 1,976 CURRENT 0 20 40 60 80 1:00 120 140 160 180 200 220. 240 260 280 300 320 340 360 CALENDAR DAYS OF YEAR co 4 Figure 3-5. Seasonal Solar Tensity Variations 6"sr.Y}ga.:<..L.41.'^l}^w^Pl e:13^4Ar.^2R:$.l^„J'aad G3ckays^ikrs_.:'^ - a_:c'A Ri Table 3-1. LANDSAT-1 Major Power Subsystems Parameters OR147110. aB 0.0.0 4016 run l0117a 13113 Ims 23799 ^^ y 1011771 MAT(. 32.41. 72.83 II.11 U.T3 33:35 37.82 32:88 37.82 2 CHGE - 7I.45: 12.71. 32.91 09.73 33..16 32.92 12.71 32.72 1__1 3 VOLTS 32.40-. 39.91 32.99 - $2.73 33;75 33.82 - 42.02 32.88 { 02.40 12441 32.99 - 39.77 33.35 32.83 22:81 - 32.62 6 7â:9f 07:91 32:83 .. 32.62 33.33 27;61 42.81 32.91 8 52,31 . will 32.21 - 32,73 x3.76 32:62 28:72 27,95 7 21.22' 22191 82,11 32.73 33.25 _ 2 2. 83 37. 04 32.89 6 3234 32. 91 32.81 22:78 33.25 324E 32:67 32.87 AVERAGE - 37.3B 52.92 32:87 0.16 33.25- - 32.82 U.32 32:71 - RAT>' 1 -END_ 28.11 23.12 28.85 at 04 26. 118 28.04 28.81 Ye.64 j 1 0T- 26.61 16.12 26.30 211.04 74.00 28.64 28.61 x6.71 S NIGHT. -28. it 516:04 - 26.5 6601 29.98 M i8:51 25:86 4 VGLis 21:6o 96.12 76.78 16.94 20. 91, 28.86 20.81 20.72 3 5 26. so 26.23 16;24 20.12 29.06 - :5:.72 : 26.80 29.77 20, 9s 6 .26.81 20.514 18. so vi. Is - 76.56 25.66 27:27 7 26.111 26.12 2840 s0: o4 29.91 - 20:64 24.91 85.66 7a. 94 9 28.81 28:32 20 -SO 211.01 24.04 96.91 28,64 AVERAGE 28,84 711.11 21.32 76.0 90.89 10.04 28.06 19.87 ti •: i . 00171' PI•cHat 13..11 18:08 13.88 -13.14 as. 96 13.68 15.15 .19.21 SHARE 12. 83 33. 60 r as. as - oil. j4 -13.90- • 18: 99 4/h.16 - 439.27 1 11,.95 .. i 3 127 11.56: 19.03. 4.1.11 1L" 11 a .13.11 13;90 19.39 17.-13- 11.93 17:92 - 1249 - 1214 14:25 19:10 11.93 16 32.37 12.44 - Ii•9s 17:39 i2.41 13:79 13.28 5 12:90. 12.17 12;35 17,64 SLID 11.61- 8149 *8• 1 21.13 7 12.82 12,18 17.92 12.33 12.29 13:99 13.91 1 12:45' 19.4.5. 12..10 ts.26. '11; 9a 12.44 .. 1340 14,42 RAPT I .LOAD 12.71 12.85 12.4 IS.ss. 12.53 13.36 14.53 14.85 2 SHARE- 12.00 11.43 - 13.84 13;4 13.70 14.07 15.66 161.14 S 11.2 11.43. 12.12. 11,81 u:04 12.43 12.50 1{.15. 14.28 { 12.77 12. @a 11.01 12. a3 12.12 13.43 14.74 14.61 11 #11 6 12.64 12.29 12.42 13.41 L2- 60 1 43 12.70 13.99 6 12.53' 12.29 .1244 12..31 11:30 a1 • * * # i_ 7 12.90 32.17 12.41 12:41 12.50 12.36 13.81 12.84 ti 9 12.37 12012 Ia." 12.09 11.97 12;69 13:10 12. h7 HATT 1 TEMP 21.11 - 25:11' 24.85 25.31 24.16 .24.78 13.86 13.78 2 W 18.74 - 12.33 It. 42 - 7137 20, 99 40.126 - 20.38 20w9B f 3 foci 16.71 26.12 20.29 70.31 20.16 19:07 1s. 72 10.48 4 21:97_ 23.23 23.11 23.28 =3.34 22.99 22.14 22.39 5 21.lI '29.77 ?3. E6 37.62 24.09 28.60 20.311 24.19: a 21.21 20:95 24.37 IT. 61 24.75 38.63 25.74 31,46 7 21,41 2Ti18 23.01 27.87 24,96 37.69 36.04 .x4.79 0 - 11.62 26,60 I5.16 27.01 25.24 -. 29.00 - 25,77 "- , M.26 1 AVERAGE 20.81; 74.87 23:49r- - 25.65 23.53 24.83 I3.01 24;04 505.6 97.90 - 92.96 99.04 B/C REO Bus- PWR M7 576..0 117.3 553 .4 16e.0 29.4 COMP LOADP.WH-5V13 . 49.0 34.8 14.8' 4A 67.9 4119 20.4 (ViO.a/C SITa . Bu8 P55m) 56:6 0, 25 0:.48. - P/L REC, HIM Pp71:'(W) - 16:2' 38.1 13. 7 n:9 1.17 C/D RATIO 1.09 . 1.08 1.13 7.17 1; 21. 1.39 1.10 •181. 49 x•223.11 .-2mn TOTAL CHARGE (A-MI '3984 352. as 790.23 '291.5 194..18 180.26 203.18 ^ ^ TOTAL DISCHARGE (A-M1 ';290.9 327:05 - 736:28- 240.0 :N12 1 942. SOLAWARRAY1 0014 .a. 1038 '966 634- 43, $60 421 q 12.35 . S.A.. PEAK1(ANY 16.E .'.16..1.0 11.60 33.00 12.44 17.4 44. u9 j l 11..70 - 11:52 .11.4.4 ^ MIDDAY AWtAY P(A311R 15.01 -14 : 51. 12. n0 - '4.A. N.A 8.48 6379 1:69 BIIN.ANOLE. 4DE01 •5.33. ; 15.:Ib .3.64 !6;63 .p. w2 - 7 0 65. 9 MAX R PAD TEMP {OL462.0 : ►71 ,00 281:90 63.20 i 0 - -77:32 -30.14 -40.06 3T1N ' R^PAD TEMP^C -06.00 - -511 00 '55.0' - -43.7§ - 87.00 . MAX L PAD TEMP ?: ♦69.00 160.59 *67:0 ad - 89:6057.70 1 -39:16 -41.67 - -41;90 MIN L PAD- TEMP + j°C -60:90 -64;09 - =60:0 47 . 0E i a ( • AOsr tht4demetr7.'hlier* to Orb.It.4"d Battery 2.eharte @4417 wn tWwo egpaF w. SWINT:I eharF - U 8n oppr"Ar6adouLto order to thrive-a eharp aMro tslua.for 96ch-b44fery: * *Nate: 114ncry6 romatnea of. tram Orbit 134461bruugh lh6: end of Ws repo!. period. c. L] : Table 3-2. LANA9AT i Power Subsystem Analog Telemetry (Average Value for Dais, Received in NBTR Piwyba;ckk) CTrelu Fmcitau!. Ducmuon . VIM 444 4 28. 2400 6088, 7660 10182 1DiN. - 166r 14M1 coal '8077 .7 ...851 AldP - 044 123 - . 0.61 L01- - - 0%a 0;91 075-. . 6002 7 0.86 1.20 s s • 8003 3 0.84 I.17 ..76 0.98 0.66 0:64 0,01 0,73 6004 4 0.83 1.21. -0:86 L07 3.86 0,91 0.69 0476 6005 5 0.92 1119 0.87 0.96 0.82 0.64 (1 0.7>t coot - 6 . , 0..91 1.20 0.76 0.96 -0.7` 0:64 • • ... c 6091 1 0.94 . 1..16 4:.62 1.01 0.83 0.62 01 0.72 6008 6 0.91 1,19 0.77 0.97 0.78 0:81 0.64 0:66 C. 6611 'GATT 1 CRG AMP 0.58 0:71 0.56 0.48 O:RB 0.44 0:83 0:69 6012 2 0.57 -0,71 • • • a dais 3 - 050 0.83 0.48 0,44 6.60 - 0.39 a 48 0.88 6014 4 O. SS 0:86 0.51 p,{6 a.60 0,40 0:60 0.58 r•. 6010 6 0,54 0.86 0.50 0,46 0.56- 0.49 0,48 0.55 8016- 6 ++ o.ST - 0:76 0.52 0.48 0..56 0.38 •• ♦♦ 6017 7 0.65 0.70 0.53 0:47 0.60 0.40 0.46 0.66 6018 6 0.55 - 0.69 0.52 0.49' 0,58 0.44 0.49 0.56 8021 - IBATT 1 VOLT VOC .30.67 30.74 31.24 - 31.08 --31.64- -31,19 -31.04 -31.81 6022 - 2 30,07 30.74 31.25 3 L 08 41.66 -IS-30 -31.04 - -91:21 8023 3 30.87 30.74 31.25 31.06 -31.88 -31.16 -81.04 41.21 8024 4 - .30.90 SD.77 31.28 3L 11 .31.70 -31.21 -31607- -31.25 1 6025 5 30.0% 30.62 3I,93 7417 -31.75 '41.28 -31 13 -31.so 6026 6 ++ 30.86 30.72 • 31.24 31.07 -31.65 -31.16 -28.70 -27.92 f 6037 7 - 30,69 30.76 91,27 SL to -31.68 -31.91 -31,96 -31.22 0026 6 - 30.89 30.25- 31.27 31. to --3L68 - -31.21 -31.05 -31.22 6031 IBA'TT 1 TEMP DGC 21.17 25.19 24.4a 25.38 26.09 24.67 24.01 - 22.83 6032 2 16.60- - 22,44 - 21.29 21,51 22.61 20,06 20155 21.03 6033 3 18.16 20.60 - 211.17 20.36 2L26 1 10.08 18,7 19.64 6634 4 21.57 ' 23.20 .23.01 23.30 23.83 23.00 22:1; - 22.42' 603.54 5 21.8 26.86 33 77', 27.68 34.78 28.60 26.41 - 24.24 6036 8 +♦ 21.24 20.99 24.27 21.85 25.78 26.70 25.40 23.52 6037 7 21.49 .27,20 27.74' 26.09 - 27,71_ 26.09 34.63 6038 6 21.86 25.75 r 25..02 - 21.40 26.21 - 26.98 25.81 -26.29 r 0040. 11T PAD TEMP DOC 25. 82 27.88 .{ 27.22 33.78 27. 16 94, 20 32.40 30.95 6041 in PAD' N 'V V13C - 33.40 33.01 { 33,.85 33.00 34.36_ 32.04 38.64 33.45. r; 8042 ' R PAP -V N VDC 33.294332; 33 . 50 37 oR 33.60 92..18 31. 0 32:62 6044 LT -PA6 TEMP. DGC 14.14 15.56 16.61 24.69 19.11 27.46 25.4, 22.57 6045 L PAD V F Di 33.69 33.71 34:16 33.64 34.67 34.00 33.7:- 34.16 6OU L -PAD V G - DVC 33:68 33.73 34.19 $3,89 -34.72 34. @4 33.7.1; 34.20- . 6050 6/C uR RUB V VDC 31.24 31-.03 - 31.65 . 31.50 -32.06 :31.63 - -31-.3t; -31.60 6051 - B/C RG BUS V VDG 24..54. - 24.54 24.55 .24.55 -24.55 -24:54 -24.54 -24.54 9 6052 AD$ REG A V VDC W. 41 U. 45 23.48 23,47 :-23,47 -23, 46 23^.47 423.4S 6053 .AUX REG B V YDC 23,50 2350 23.50 23.30- -23.50 -23:50 23.51, -23.60 6054 AOLAR I AMP 14.67 13, S7 12.69 12.61- 11.60 11.45 11.31 11:22 6055. B/C RG BUS I AMP 7.11 7.45 6.27 6.54 6.90 644 6.56 6.34 6056.. - -871 RG BUS 1_ AMP 7,31 7..46 - 6.27. - 6.53 6.79 - 6..04 6.5, .6.33 6050 - !PC- MOD T 1 OW 21..82 23.53 22.23 -_ 22.65 23.22 21.50 21.4' 21.69 8059 .:PC -MOD T 2 Doc 21. 60 23.08 22.53 .22.72 23, 00 21,65 21.41 21.92 6070 jP/L RG BUS V VDC - 2466 24.67 '24.68: 24',68 -24.61 41.68 -24.6: -24.67- i 6071 WIL Ult BL's' V VOC 31 -03 30. 68 31 . 53 31.35 -3L.92 -31. 47 -31.21 -81.46 6072 + 'P/L 'RC BUS l AStP 0.57 1.47 0.56 0.67 0.36. 0.37 0.3, 0.37 6073 P AUX A V. VDC - 23,31 23.53 23.51 23.51 -23.50 --23.50 -23.51 -23.50- 607{ iP AUX B V VDC 23.51 23.53 13 51 -, 13,51 -21..50 28.60 -Z3.50 -23.60 6075 ;PR -MOD TI .DGC 21.50 - .24.40 23.13 73.36 23.02 22,05 22 5e 23,03 6076-. ' :PR MOD T2 GGC - 20.34. 22.31 .21.45. 21,6; 21, h4 20;64 20.84 21.25 6079. .FUSE BLOW V . VDC - : 24. 56 +• 24.57 mu -24.60 -24.59 -24.55 -24.09 6080 ;SHUNT I. I AMP 0.00 - '0 , 00 o.00 049 0400 - 0,00 0. 9t, 0.00 6061 2 _ 0.00 0.00 0.00 '01 0,00 i 0.00 0.0b 0.00 6082 - - - 3 - 0.00 3.00 . 0.00 O.00 -0.00 0.00 0.00 - 0.00 6063 4 0.00 0.00 0100 01 r 0.00 0100 0.0o 0.00 'r. 6084 S 0.00' 0100 0..00 0.00 - 0.130 0.00 0.011 0.00 608& 6 .. 0.00 - '0100 0400 0.00 0.00 6409 04" 3466 Boss 7 0.00 - 0,00 1 BAD 0,00 6,06 '0 .00 '0.011 0roo 8084 B' 0.00 0.00 0. OD 0.00 O. Oa 0.00 0:00 0.60 -6100P/L.RG BUS A11P. ..0.58 1.47 0.58 0.67 0.36 '0.330.37 ^ 389 0.37 'TOTAL NO. MAJOR FRAMES `. ' CRM '764- - 425 - -.387 384. 786 ^796 . • T^ipeifm6o0z, 6616 [niaelfl6 Qiss resitlteA framdfeYtiled;tflemeiry 'rreultie from IC clitp tallure which . riteeted charge ciirrmt direeUg Ovid disehsrge ' current lttdtrecUY Atibe power computer. program;. }}^^}} 7 ! •• FVoeSim 6678; missing dala,re6Wted irarn W1Re error iw master Information file used l0 computer processing. ♦ FUNC- 6053, 6066, . SDT2 data la dmived3rom Paeudo . FUNC 6155, 5136, 6172 E .. und'After t hacge to'•Moda 11 r ^ ,. BA'kT a ww and nohaad w.f6r ft rest of thIa ORIGINAL PAGE T OF POOR QUALIY^. i 8-9f-141 ' .. xs'S9y sou.:. F^+ax" rw.:^;^Y??5;/ .-C;-nr 1 IF{II 11([ t SECTION 4 ATTITUDE CONTROL SUBSYSTEM (ACS) LANDSAT-1 LANDSAT-I's ACS system performed normally and reliably during this report period. The ACS NORMAL mode has been employed only during the six daily orbits of MSS activity, For the remaining eight .daily orbits of non-MSS activity, the spacecraft is commanded into the Roll DlS Tach High Gain mode and Pitch Position Bias (0.0 and +0. 6) is employed to maintain the Pitch flywheel 's speed be- tween +20 and +100 RPM. i Implementation of this mode of operation became necessary, after a Pitch flywheel problem. developed in 3 Orbit 11125, (29 September 1974). ^^ This mode of operation has proven to be quite successful in keeping the Roll flywheel unloa+d&J. In addition, r pneumatics gating has been almost entire lyeliminated, and the total average +Roll gales per week have been reduced to less than one as shown in Figure .4 1. Consequently, the Freon remaining useable 1=11 9, 31.49 LB - SEC, should be adequate for at least four more years rather than to March of 176, as pre- viously anticipated. LANDBAT-l's Single Scanner 'node was exercised for a portion of Orbit 13922 (18 April 1975) in order to ' ascertain if MSS sun calibration can be more effective ly performed by eliminating transient spacecraft E attitude errors emanating from the normal night-to-day transition. drip charts recorded daring this test demonstrated the transient error could be completely -removed without effect on the ACS system. 4 Solar Array Drive voltages, currents, temperatures and cosine pot signals have alibeen.normal. RMP 1, which replaced AMP 2 in Orbit 11267, is functioning normally. Pressare/temperature ratios have all been satisfactory. The forward scanner pressure decreased from 3, 33 PS1A (Orbit 12749) to 3.08 (Orbit 13970) and is following the leak pattern described in previous re- ports. Tables 44, 4-2 and 4-3 are a summary of LANDSAT-1 Attitude Control Subsystem telemmetry,, Ai E "s F 1 i A_ I j..1 4-1,/2 :: .`•yr..s' l`.e"F".'^" :.m_ :"" _ v .. .,., r. +: tg issTM,s+f^"^'f^:F?t r' Tirs^ ..:y^! " ,ti ° v, as. iT^li'1^^ n'low 1 AVERAGE GATES/OAYa WEEK TOTAL. r 7 - ^'s m .m N - M0i - ^` - INCI'IAL.OR131T . ADIUST NO,.1 ,3 LM - MNICA C.ORRECP'IObl6 w ROLL GATES.NC S1iDWN. (^ 150 TOTAL DURING tST 3LWK ------_ 8:.24_, _..,^ . 8-27 i - - 9-10 9-1T1 `w. 9-24. - 10-1. . - ORBIT ADJUST - NO..4. - .10.8 -, - - - - 10.29E 11-5r 12-3' ^^J 12-101 12-17' 12-31 - y T-7 c^. d i_fd ORBIT ADJUST NO.5 1_21' . 1_20, r:.Jr 2-4 2-1t 3-44 3-25:. 4_7 SI 4-& 1 1.'f I - 4-15 4-22 V A v 5-59. } .^ F OY - 5-13 >7 5-20: ^J . 3-27; it - f-3 1 6:10!1 7_1 `. 7_B J . _ 7-22 - l 8-5 L1 - - - - 8-12 :. r 8.26 1l 9-2 Ly -9-16 9-23 0.30: L . 10.7'' 10-34 . 10_21- L7 ORBIT ADJII5T ND; 6 11. u-1a ^t 11-25: L----r 1z'z rr 12-16 12-25 12-30: rl rJ • ^3 _r^ irueu S+L-n'SSVtS4^.^astG s^.stw':=.^i So-t 1r:%wLWK•kkcw.%^'i cHf: ax?uf_`5'.\(^FYE — b.,u.^.e .,i_. i.rwi^': - t •-V,,.na•+ra3wl.i.M....!^s=^ ^ ^^ . i.. i6..1..:..+f :...«-«,..a., -.^,._ .tr .a._..?.^_.. ..:..ce4... ss..0 wYa ..: _ _ .. .. _ _ _ ^...,. c __.,J- a :' "^:re•.r.^st_.^«.r^•e•:a.-m-.^:rw `,x.',.;'sx'as;.9"';7 ^rs^£;? ^.:;ye '"^z';^^d^a -- 3 Table 4- 1. LANDSAT-1 ACS Temperature and Pressure Telemetry Summary 0e>iit Function Gaits _ 11L 2000 5009 7600, 13198.--. 19660 14001 lOS4.11M31 I Ryrr. Temperature 1)6c 44.5 24.26 - 23.06 25,21 i;. 22. 42;09 ^4 - 4^ L-02 1094116111 2 GyroTomparatute DOC 74, 3 75:47 75610 75,42 4.3.45 24 .22 24. 17 28:83 f -1222 SAD RT-MTR HSLd,O- Tamp DGC .21. 1 23.07 22:00 24.29 20.55- - 22.28 22,92 - 2z 34 1242 HAD LT r,l 'flt HMNG Temp - Doc 27.0 92.27 - 30,38 33.44 29.16 29,88 -29.66 29.29 . 1223 SAD HT AITH WNDNG . Tomp 13GC 23.3 27.39.' 26.54 r 26.26 24;83 26.03 26.11 28.40 :. 1243'SAU LT A1TR WNDNO Temp 1360 28,7 34.99 32.92 ^ 35.87 30. 32 32. 20 32,04 31.:74 f r 1 t 1228•SAII RT- 115G Pmssum Pat 7.6 7.53 7.35 7.28 7. 32 6.97 6.w 6.95 1248 SAD, LT- IIS6 Pressure PSI 710 7,04 - 8.86 - 6,76 61.47 6.31 -6,31 6.26 d toot FWD Scanner AITA Tump pGC 19.9 21.36 19;88 22.26 16.48 19.68 10.93 19.89 C 10161tear'ScannarAITHTerrip DOC 20;5 21.25.E 19:53 21:79 17,86 19,15 '1g.28 19.21 1003 MD Seanner Prussure ^ Psi 4. 6 4.52 4.02 3.84 3.50 3. 17 3.10. S. OP I tit, Haar Scanner Pressure Pal 7.8 -8,05 7..61 7.87 7.44 7.:19 7.2'2 7.19 1 1212 Uus Tank Prassum Pei 1968.0 1849.06 - 17 3.34 1598.59 1454.19 247.82 24L65 339.68 .Tank.TemperdUm Doc 22;6 26. 07 24.30 27. 22: - c 1210 Gas 16: 66 24:21 24.21 24:.07 . 1213 Manifold Pressure PM 56.7 5T, 46 67,44 57.81 58.73 81.26 0I.25 .6L2 } 1211 Mmiifeld Tanlperatum DGC 21,9 25:51 23.62. 26.61 21.77 23.72 23.74. - 23;48 11159 C1,11 Power $upply- CarilTetap D15¢ J7.1 42;22 . 40.54 43.34 36.8,3 40.40 40.47 .'40.34 t .1200 ACS Rsseptate l DOC 25.4 29;7.1 27,93 - 31,01 28.38 26.91 26.72 20.32 1261 ACS-RaseplaW 2 DGC 22.9 26.42 24.73 27;76. .2100 25:08 25.04 24.72 1262 ACS Hasuplate 3 DGC 2;1.4 25.09 23,69' 26.24 2L.97 24;60 24.62 - 24.49 F 1463 TIlOI STS DGC -6 . 6 0.59 - 0.97 3: 97 -3.41 2.99- 2.03 1.16 1204 T11M STS DGC - -14.6 - -8,01 -9,42 -3.85 - _6,27 - -2.75 - -4.00 -4.80 1265 TH0.3SfS DGC .- 3. 1 .9, 32 9.31. .15;52 -. .7.58 16.32 14.75 13.08 i 1866 THO-i STS DGC -12.9 -2.55 2.95 '- 4.40 -1.95 4.00 2.89 1.96 I 1267 THUSSTti DGC 78,9 -0,97 -1.10 6.73 -6,17 5.70 2,99 1,30 1224 SAD It F55T DGC -89.5 - - 52.87 60.21 ---- 61:80-- -- 63;25 63;00 -' - 62.26. - 64.88 ^^ f 1244 SAD L F..SST DOC - 27.1 - 45.64 51.11 - 58 : 46 . -53.21 57.21 65.74 5.6.25 Table 4-2. LANDSAT-1 ACS Voltages and: Currents .. C?rL1t- .. . Fdnctfss 13fdla 2600 ,- 7650 .13569 241101. ;I1- ., 3909 0.....". 13196 P f 2 1057 CLH Power 8dpply Volts TMV - 2. B 2.79 .2.78 2.79 2..78 2;78` 2:.76 .78 t 198I RMp 1-64TR Volts VpC ^- OFF OFF - OFF' OFF OFF -30.14- --30.14 -30.14 i Amps .. O ^ OFF OFF OFF 0;1i 0.11 0;11 4082 A010 I MTR Current. OFF FF. 3 Io80-RMP1• Ik:pplg Vol ts VDC OFF' OFF OFF OFF OFF -23. 79 -23. 76 .=23;78 29;63- OFF OFF OFF X 1081 RMP 2 MTR- Volts - - VDC -29. 7 -29,83 - -29. 0 -29.59 - 1 1002 RNIP 214141 CuwstA - Amps 0,10 - '0.10 0,10- - 0.11 - 0.11 OFF OFF. OFF 1 1090-R51P a Supply Volta . V11c - -23,4 -23.38 -. -23.43 -23.38 .23, 60 OFF OFF OFF '. 1220;SADRT 1STR ' WNDNG`V01ts . - VDC -4: s -1r32 . -4.35 -4. 16' 4..86' -3.71. -3..75. .•3.11.. -3:25 -3::19 =3.27 1240^SAIMT AITR.WNDNG WIN VDC '. -4.8 .-4.12 .4,09 -3,95. ` -7,38 s 1227;BAD`RT. -15 VDC :C., - VDC - - 14.9' -14,96 14.88. 14. as 14. 8D : :14;88 14.88- '14.69 - -VDC. 16,2 -15.15 15.13 . 15.13 15,14 15...-13 16.:14 15,38 d 1247 SA13 LT -IS VDC Corer• 1 ^. low C10,4 6 VDC . TMV '2.4." . 2435 2,95- 2p 35 . 2.36 ' : 2.35 '2.35 2;25 5 '..1055 CL33;+ LO 13C: TMV. .. I .. TMV...... 2;75 2. 75. . 2.75 .. 2.75 , 2.74 . . 2:78 ' .. 2:44' . '2,74. orbits Function Units 13198 13569 14001 1141 Pitch Fine-Error m DEG -0. 40 -0.08 -0.02 1143 Pitch Flywheel Speed RPM -10.49 -26.86 -4.21. k 1038 Pitch MTR DRVR PCT 4.96 5.81 4.55 3 CCW j 1039 Pitch MTR DRVR CW PCT 2.29 2.17 5.10 r } 1030 Roll Fine Error DEG -2.25 -0.20 -0.20 11.27 Roll Rear Flywheel RPM 715; '78 756.92 782.08 k j Speed ^ F F 1126 Roll Fwd Flywheel RPM 641, . 82 674. 47 693.31 ^ Speed fi 1022 Roll Rear MTR DRVR 'PCT 0. . 01 0.68 0; 90 CCW r [ i 1025 Roll Rear MTR DRVR ' PCT 4. 26 5..22' 5. 52 i CW I 1023 Roll Fwd. MTR .DRVR PCT 0.01 0:66 0.72 . 3 CCW 1024 Roll. Fwd MTR DRVR PCT 4.15 .4494 5.3:5: s^ CW F a: 1035 Yaw Tach RPM -206.08 -11C 50 -93.72 1033 Yaw MTR DRVR CW PCT O. 04 1.53 1. 84 1034 Yaw MTR DRVR CCW PCT 0.70 1.60 1.76 1221• SAD Right Tach DEG/MIN. 3.37 3:37' 2.81 1241 SAD Left Tach DEG/3AIN 2.80 2, 81 2.81 NOTE! Tabdiation'o. f'these. Amotions Began after the pitch flycwheel anomaly (stopped), in orbit 13125.. a ^i ri; 5 - 4-6 1- 4 .^. m3 .^„ ^:%i::: ..y}.a.a•sarersxFa:4•°+x.^^, ; - .Y'•vr5^rtr+`4 A.' SECTION 5 COMMAND CLOCK SU MSTEM (CMD) The Command. and Clock Subsystem consists of A and B wits of: Command. Clock, Command Decoders, Comstors, Matrix. Decoders, Matrix Drivers, Time Code and Frequency Generators and VHF Receivers plus a Command' Execute Counter and switching equipment. Command processing for both real time and stored commands has been nondual during this period. Rare command difficulties that have been experienced have been isolated to ground transmission problems. Missed real time commands, attributed to the logic race in the command clock design, are occasionally noted. On rare occasions stored commands are blocked by a real time sequence being transmitted during the stored command time tag. =i The spacecraft time base provided by the tune code geneftior has been well within specifications. The clock has been reset five times in orbit: at the beginning of 1973 during Orbits 2249 and 2274, is August 1973 during Orbit 5578; at the beginning of 1974 during Orbit 7339.; and at the beginning of 1975 d uring Orbit 12429 (Figure 5-1):,: The S% C clock consistently loses time, as shown .by the negative slope in 1 Figure 5-1. The slope decreases with time. 'These slopes are plotted in Figure 5-2;: which shows that the drift rate decreases with time. Table 5-1:gives typical telemetry values, all nominal. I i talk(i I ^^ 3 E ^ r 3 5.L ... wr^xc.c ^S t -f :. i?Kr.a i..^^:v-. tiY'^ .aF'Y y'S YEx, _o,7ao. ; f^ - m -0 8 0 CURRENT REPORT PERIOD W -I: MO. U . i i 3 E. 7 -t,2ao S o 1 i z 3 a s s ^ a ^ 1.o n 11 ,:3 14 15 IS 17 ° 1972 1973 rl - .. i974 1'97!5 ---F „ 3). OR131T (X 10 - - ' w Figure 5-2. 1 ANDSAT-1 Spacecraft Clock Drift. Rate c^::if:vla.r,^-.§.rt^,:aa: „.,.„,, ^tw,s . 3 3 Spam ^az. kTx` La +^-.^.^':: xt^l^-as+i^-,.h . _xr„,Lrtlhn^l:i cU+.w+^'.x^-r'M„fen9a.T-k+, 4^.r S."n- - - -1 Table 5-1. Command Clock Teleme ft Summary art's. 9n . ... . Vtm0 I900Y Nu. %a 4 Kode pwla 35 5093 - 1011113 - i^188' 11001_: .uD: - Pd.P-84.0y T-P °C ii.31 28.37 i6, 60 39;43 3e,/T 3e: ds' POW tt•d. Parer Supply Temp °C 35.73 10.06. 311-31 30..16 37.40 - 37.90 - r007 PH, V., Tamp °C 31.14 31.90 33.18., 31.97 31.13 31.61 Mau Hl d. O•r, Temp °C 30.4T 31-29 3L42 31,40 .30.48. bo" Prl: Orr. Ckdw - Tt'l1V 0:05 0.95 0.07 0.97' 0.86 0.91 ^i 6010 Hrd. urr. Ou1Pd - TM •• •• •• •• '• •• all 100 kill Pt. --Red, '[MV - 3,11- 3,10 3:11 3.11 It-0. 1.11 4013 P) ldlx'. Fri. -.fled. TMV 7:10 - 3,07 3.06 1.08 -i,6e 3:0•- 6013 2,5 Ally Pry, - Red. TMV 3:06 3,05 2,0S- 3.86 2.95 2..95 6014 400 HI Pry. -. Rad. TMV 4:40 4140 4,40. 4,40 4.40 4.49- Am Pry. 44V P-r F.glply Pry. Clk ON VDC 4.10 4 , 10 4.10 4.10 4.16 4. 19' 0016 'fled. MV P-elsupply Re4: elk OTi VLC 3,95 3,.95 3.95 3.95 3.94 3.94. 0917 - Pa. tGV P-r.8apply Ptt. elk ON VAC 6.06 - 6, C7 - 6,07 - 6,01 6.07 6:ff w6 Red. 16V V--rr 8umty Red. CM ON file - 5.00- 5.94 6.94 6.03 0.06 5.01 0019 FD: -GV I--r BU707 Fri. Glk ON VI1C -6.02 -6.02 -6.03 -6.03 _CO3 0430 Y d, -s l' Rod: [ik.ON vDC -5, 99 x600 -0.m -6.09 -6.00 a. 00: •071 PA, .2oV Im•er euppl7' Fri. elk ON VDC -Zi. 06 -42.83 -22,69 -.'.2. as -12:90 -32.911 .027 Rd. -23V VP r fi wll '1104. elk ON V11C -22.96 -23.08 -23.01 •15.00 -13.00 -23.00' 1023 Prl. -29V P0•er supply Pit. elk ON VAC -29.13 -49. le -39.4 •20 -15 -29. IE -29. I6 0024 Hed. -29V Pmwr Beppll- iced. CIk ON VOC -29.07 -79.27- -20.21. 22 -29;21 .39.31 SID1 CIU A -12S- CIA A.ON VAC -12.33 -71.15 ".-12;71 -1_-36' -17.34 -12:34 5102 CiU 'B -12V CRI B-CD VOC -17.20 -12.26 -12. 23 -12,23 -12 AZ -[7.21• 8101 ew A -:\' CAI A'ON VAC -5.37 --5:74 -5.34 -5.34 -5.76 -3.34: 6194 C1U B--6\- COI RON VDC •6,31 -5.31 -5.31 -5.31 - -6.311 0105 CRI A 7rmp CA1 A ON °C 24.47 24.17 25,04 - 15.00 24.37 24.55 0196 C1U D Temp CTU`0 (M °[ 74.96 35.31 15-46 x4.38 24.74 24.94. 0.01 - R9wtwr RY-A Temp - °C •• •° 20.47 26,24 27.51 27.03. d2o2. H.wl-RY-B Temp - °C - 17.96 10,12 I. •• .. •• •n03 - 13ROD AT.mp - °C 25.41 25.73 37, 9a 37.74. 3G. US -3T. {0f 6214 A MUU 11 'Temp °C ..35.03 35.61 26, @ 16.71 24.91 26.3E - 03p5 RewtwrA AGC Ru°41wr XOH OBM •' •• -96,71 -920.03 -91.12 - ad, 50 0:106 Rec[I•es 0 Ar.0 .Reeetwr O ON 0851 -94.74 -04,67. . .• •. .. - 11107 Amp. A Iwltpul Mwlwr: A ON TMV •• " 2.31 2.64 S. W 1.13: I^'uk Amy. B,udpul A-jw.[8013 TMV ,2.01 3,122. •.. .. 4. e^u9 Yreq. shift Key A CUT RowJw"r-A ON TMV •• •• - 6. 10 1.12 1.11 '1.10 -a2t0 Fnq. SKID. NOy`9 OUT Rervlrer B-ON TMV 1.10. t,11 •• •• a• .• . 9ZI1 ADP• A(: ;.A Iu-IwrA'ON TMV '• 1:70. J-12 1-12 !2L" :. A.P. B Output Reeelw ?B ON .TMV .l.t3 1.15 •• •• - 8215 A MCI A -15V - Reuelwr A ON - TMV 5-00. 5.00 - 6,W 5. P0' 8216 111MOD B-15V - - Rerel-11 ON TMV 5.00 5:D6 .. .• •• .. 0317 Rqu1N0r A -70:' Remlwr A ON TMV •• •• 5,40 - 5.40 - 4.70 6.40: Bi4 RcSylNuc N -InV DuwlvO'r-B-4N TMV 6.60' 6.60 •• . d ^e i F pS .,s SECTION 6 f F TELEMETRY SUBSYSTEM (TLM The Telemetry 9&system consists of A and B units of: Memory, Sequencer, Formatter, Multiplexer, F Converter Multiplexer, Preregulators, Transmitter Buffers, and VHF Transmitters, in addition to a single repro unit and switching circuits. The Narrow Band Telemetry Subsystem samples, encodes, formats, and: transmits data from spacecraft service and payload systems to earth receiving stations. The TLM processes and transmits a VHF signal containing this data... R supplies. data to the USB Subsystem for transmittal, and provides timing and synchronizing signals to spacecraft service and payload subsystems. ^ ^ 4 The Telemetry Subsystem has: been operating continuously since launch. Typical telemetry values are given in Table 6-1. Memory Section 0, 0 was used in the telemetry matrix thru Orbit 12565, after which it was switched to the 1:,1 mode. Total performance has been .normal except for one integrated circuit chip failure in Orbit 4396, containing four functions (6012, 1011, 1`2238, 7010): The VHF transmitter unit consists of two redundant Amplifier /Modulator/Output units, A and B, capable of eitner 0.3 watts or 2 watts output, together with Modulator Filters, switching equipment to select real time or playback telemetry modulation, and an omnidirectional vertical stub antenna centrally located on "s top of the spacecraft. The transmitter is ON full time, .normally transmitting real time (1-kilobit) F telemetry data. In an emergency, it can be commanded to the 2.0 watt mode and switched to playback (24 kilobit) data, or to carrier only for use by the Mini-track Stations. /A-AY transmitter unit A has been used since launch.. It has operated flawlessly. Figure 6-1 shows the i ctory of the AGC level in the Alaska ground station for identical spacecraft position and orientation. k _^ Since launch, nearly 3 years ago, its loss in power delivered to the ground, station has been about 1 db. f Referring to 11gure 6-1, a signal of -104 dbm would leave a link margin of 6 dbm is the worst case (24 i kilobit modulation), providing the 85. foot antenna is used. E i L^ Y•. 1 .M1 1 Tabl® 6-1. TLM Telemetry .Summary ^. i _ _ Or4ii 1'uectla0 ea. rts6eW6 Home u6i1 ad xauD 1106 2679 16311 Istpt 11169 l •• w r• ...... no ,Memory Svq&a fDC p6rerter VIY.' •• •. 9003 ,Memory-Squi6eer Temp. - 6C 19.58 21.47 21.06 31.67 - M30 23.24 31.61 - 21.44 9004 •rermtuerACamrrter VDC 5.99 - 6.99 6:99 6.69 5.99 6.62 ;,99 jlu 9005 rFarmalier FtComerLr WE •• •• w. •• .. •. .. 9005 1011. M65 .A C®rener VOC 10.01 to, or 19,04 IDIOT in 10.01. )1,.m 16:67 0004 i111i. MwP Caererter VI1C •• •• a .. .. 9008 -F'orm6tirr/Plj• Mu Ttrmp. 0C 22.50. 21,64 34. t9 :7.97 96.9 29.24 :7.00 U.92 6009 'Antos M-:Ac nver- er - vw Mot. 36. id x1.18 to. 16 25.29 '_6.^-4.: :6.20. °-6:29 9010 Aa41°6.11n D COmtrlar VDC •• •• •• « •• •. •• .. poll A/D Camrtsr A V.ILW YDC 16- 00 10.04 - - lo. u1 19.91 16. In 16.011. 16.07 to. rr,- Satz AM Cgtrerler 11 Vatt4pr - VDC •• •• •• « • ., .• 9011 Ae Wj , lliw1VP C®rerur °e 21:66 77:50. 26.67 . 79.0 x7.49 50-00 21.0 =7:22 9014 Prere401tmr A Valtso VDC - t9.03 19:69 19, 0. ^ t9.19 03:84 20.00 10.96 16:95 pots . Prerepdeur. 0 VeUxp -VDC - •• • - '- 9014 lteprvgr .r Tetrto, °C ..77.00 25:00 32.50 26.05 ?1.53 SR. 9• 34. R1 21.04 poll Memory A , Camgrt- vM 6.06 6100' -. `5:99 0.00 6006. q-.•., 5.9: 'S;a. 9018 '.Memory A Temp. °C !1131 16.66 17.50 19.00 n,so I . eq 17.:3 t6.19. •• •• •• 9619 Me-Y 0Cotlydrter _ - v •• « 9Na Mem9ry a Temp. ^C - 111:66 19.29 17.8 t9. 62 37.51 - 1M.0-1 le..ti i 1«. 15 9160. : Refected. P.-AXmtr 'A; dwn L 1.95 '13.15 12.72. 13. it. '12. 3e .. -IP. 12.:3 1 fYr34 9101 XmtrrA- 20 VDC VDC -15.18 '.'_19.76 -19.76 -ICT8 -19.16 tv..p 0.7: a 18.TT 9102 Xwr 11:20 VPC 'VDC •• •• - -' 0190 XmirA Temp. °C 20,93 24.06 x1.14 -25.24 tl;01 171:6 9101 Xmtrr R. Temp. °C x1.49 76.02 21:93 - 26126 22.16 =r-5151 :5.60 4i "1.95 9105 Xmtr'A. P-ir'Output d&t x6.IS 25.06 25.73 15.14. 56.21 5.M _3.27 i 25.44 - BIDS Xmtr NPoi." AStol dRm •• •• •• q ... - SECTION 7 ORBIT ADJUST SUBSYSTEM (OAS) The Orbit Adjust Subsystem has been fired ten times, seven times using the -X thruster and three times using the+X thruster. Three -X firings were for initial orbit correction and four -X for orbit maintenance. The three +X firings were for orbit maintenance. The only orbit maintenance maneuver in this report per- iod occurred in Orbit 13611 utilizing the +X thruster. The burn lasted for 2.8 seconds and performance was normal in all respects. The ACS pneumatics was not enabled during this maneuver in view of the short duration of the burn and the low availability of freon. The Subsystem pressure/temperature parameters continue to be normal. There is 64.86 pounds of hydrazine fuel remaining from an initial prelaunch load of 67.00 pounds. Figure 2-2 shows spacecraft ground track drift from standard orbit tracks and the effects of orbit adjustment. Table 7-1 is a summary of OAS performance to date, and Table 7-2 gives average tele- metry values for the off quiescent state. LS-1 7-1 ,.rK . . ^,....,,s iu Table 7-1. LUMBAT•-1 Orbit Adjust Summary Orbit, Burn E igine Fual Tank Tank Adjust Ignition: . _ Duration Performance Used Pressure Temperature Axis Orbit No. Epoch' (5 econds:) (Meters) Efficiency (MS.) (PSLA) (°F) Thruster 38 1. 26 Jul 72 4.8 12 60% 540.0 75.0 -X 11:25 0.0 U2 44 2. 26 Jul 72 250.0 1975 103.4% 2.15 U -x- 21-.44:46 58 3. 27 Jul. 72 318.0 2391 101.5.% 6.16.0 73.9 -X 23;34:45 2 938' 4. .29 Sep 72. 11.8 98 110.0°x, 0.039. U U X 00:30: o0 2416 5. 13 JTan 73 20.4 154 .106.0.° 0.071 489.4 75.4 -X 0021:3.0 3 639:0 6. : . :5 Oct. 73 14.8 110 100.0% 0.048 486.8 73.9 -X 00:04,10.8; { 7826 7. 4 Feb 74 14.8 112 101.8% 0.048 490.59 75.4 -X 23327:10.:4 x 11367 8. 16 Oct 74 8. 0 -65 106.0% 0.026 49.0.59 74.0 +X 3' 22:42-10.8: 31464. 9. 23 Oct 74 8.4 -66 102:0% 0.027 490.59 73.9 +X 13611: 10. 26 Mar 75 2.8 -22..6 102.1% 0.01 486.86 70.9 +X 19:3900. 8 (the.••*^ awn rv.w..<^ ^^f.r^ ^ ^.:vms<.e.^ .w^,.v..:. 4 '•^--•..J +.....^+..: ^w,y ^ iw^ ^.w F.^.....,. r. M-.. ^ µ _ , _^.' ^ 4s3^--e.sir.;s ^.::. :^.y:,:,^„ _ ^:^L-`.i6„z.i a^:W si--.r^.W ,.,^u: - ^ ..,:..,^.v,.: , u.'^::y+r: .ne}r, ,,. m^+x^ry s Yps^wZ ,.smp^ 'h?'k^^^»e ^xx._...^',t N,wj.in}.•q. _}^ t Table 7=2. LAND6AT-1 GAS Telemetry Values F^ tupn Orbit No; Name Units 35 2600 5099 7,650 10182 13198 13555: 14001 2001 Prop. Tank Temp. °C 22.03 23.91 22.86 24.53 23.28 24.94 22;65 22.15 2003 Thrust Chamber No. 1 oC 29.57 28.50 29.93 27. 77 .30.55. 27.74 26.36 29:50 (-x) Temp. (1)' 2.004 Thrust Chamber No. 2 oC 38.76 33.74 40.28 39.27. 38.91 38.12 37.56 38.28 (+x') Temp. (1) 2005 Thrust Chamber No. 3 oC 34.55 46.23 34:41 47.52 36.09 51.42 46.87 40.63 (-y) Temp. (1) 2006 I:ine Pressure ps#a 539.29 486.87 486.87 491.10 490.61 497.84 490.07 486.93 ;(I) Wide spread of temperature is due to nozzle locations and satellite day/night transitions relative to data averaged. Typical orbital range is:: from 19 to 59 DGC. wi SECTION 8 MAGNETIC MOMENT COMPENSATING ASSEMBLY :tMdCA) The spacecraft was corrected for unbalanced magnetic moments In Orbits 13, 85, 110., 220, 11181, 11185, and 11186, as reported in early reports. Adjustments were made in the yaw negative dipole in Orbit 1.1186 and the pitch pcnitive dipole in Orbit 220. A short roll . dipole test was Performed in Orbit 11185, with -roll dipole returned to near zero. No adjustments were made in this report period. The current dipcole values are: Pitch +2950 Pole-Cm Roll -500 Pold-Cm. Yaw -3600 Pole-Cm. Telemetry measurement shown in Table 8-1 shows that the dipoles are holding steady without drift.. Table 8-1.- MM CA Telemetry Sumviary (LANDSAIT -1) Orbits Number Name Uhits 35 2600 5099 7650 16182 13198 13569 14001 4001 Al Board Temp 0C 19M 10.37 19.03 19.12 19.11 18.67 17.66 18:13 4062 A2 Board Tamp PC 23.58 24316 23,05 23.. 15 23.,13 22.72 21.$6 22.29 c. 4003 Han current TMV 3.48 3.49 3; 48 & 48 3.48 3.48 3..48 3.48 4004 Yaw Flux Density TWV 3.1.1 3.10 3.11 3.13 3.15 4.01 4.01 4.01 4005 Pitch Flux Density TMV 3413. 2.50 2.51 2.52 2.52 2,62 2.59 4006 F . toll Flux Density TMV 3.19 3.20 3.19 3.19 3.20 . 3.28 3, 28 BECTIO14 9 UNIFIED S-BAND/PRNMODULATION PROCESSOR (USB/PMP) The Unified S-Band Equipment (USBE) consists of two S-Band transmitter/receiver pairs (transponders). Each transmitter/receiver pair normally operates as a separate unit.. Only one of the two is powered at any given time. The USB Receiver receives. the uplink RF sigma, demodulates the command and ranging sub- carriers, and, when possible, provides a phase-locked oscillator signal for the down-link USB transmitter. A ranging (pseudo-random noise-PRN) signal is demodulated and is available for modulation of the downlink upon.ground command. The subcarrier containing command information is sent to the PMP. One of the USB receivers is powered at all times. The USB transmitter uses either the .phase -locked oscillator of the USB receiver or, if sufficient signal for phase-lock .is not present, an auxiliary oscillator for the transmitter RF driver. Back-up modes allow and sometimes require use of the auxiliary oscillator or the receiver oscillator (phase-locked or free--running) at all times.. Modulation of the USB transmitter comes from the PM, P, and may or may not have the Pr_ ranging signal added. Switches permits either transmitter to be ON or OFF, but both transmitters ON simultaneously is not possible. Protection against lengthy inadvertent operation of either transmitter (and/or either of the wide band power amplifiers) is provided by a 32-minute cutoff timer. The. Unified S-Band (USB) Subsystem has operated satisfactorily since launch, .despite repeated and large drops in transmitter power output of the A-section. The B-section of the USB dual installation was substituted during Orbit 10068, restoring full 1. 5 watts output from the 0.14 watts to which the A-section transmitter had declined, as shown In Figure 9-1. TRANSMITTER-B _____4 I,5 '.4 1.3 l.2 I:I US ^: L q 3 h •9 7 .S .7 R 6 .5 ,4 .3 q 1 A ^ . 6 :g 0 2 3 a. 7 g. ..10'^ . ^ '.i1 .. 12. 13 r ORBITS (X 10''} J Figure 94. USB. Power Output. History .(LANDSAT-1) The USB-A Receiver was ON continuously from launch to mid Orbit 10068,, for a total of 17,327 hours. The A-section transmitter was ON only during station passes from launch to mid Orbit 10068 for a total of 2253 hours. It was commanded ON for transmission of real-time telemetry, Playback of stored : .telemetry, ranging data, and for relay of DCS. data. LS-1 9-1 The B-section receiver has been on continuously since mid Orbit 10068 for a total of 9436 hours. The B- section transmitter has been ON for a total of 1227 hours. Table 9-1 lists telemetry values, all normal and typical for this reporting period.. Table 9-1.- LA-NDBAT-1 USP/PMP Telemetry Valu,(:3s Function Orbit NO. Name Units 35 256 ;1; 50.99 10592 13198 13569 1 14001 11 1001 USB Rovr AGC D.BM -122.78 -126.18 -131.99 -129.81 -129.87 -126.38 -128.45 110022 USB Xmtr Pwr WTS 1.60 0.62 0.29 1.54 1. 47 1.47 1.5.1 11003 USB Revr Error KHZ 21.79 -20.87 -21.32 -23.25 -21.46 -20.82 -21.54 11004 USB Xpond Temp DGC 22.92 25.30 22.64 25.64 20.20. 26.93 25 7-0 11005 USB Xpond Press PSI 15.91 16.09 15 . 911 15.92 16.16 16.03 15 94 11007 USB Xjntr A -15V VDC -15.20 .;15 . 20 -15.20 11008 USB Xmtr B -15V VDC -15.20 -15.20 -15.20 -16.20 11009. USB IRAn!tang ges -15V VDC ^14. 76 I -14.76. -14.16 44.58 -14.58 -14.68 -14-58. 11101 PMP Pwr A Volt VDC -15.12 -15.18 -15.18 111.02 PMP Pwr B Volt VDC -15.12 -15.14 -15.09 . -]:5.10 11103 PMP Temp A DGC 30.44 33.70 30.23 26.60 31.74 29.07 26.63 11104 PMP Temp B DGC 31.64 36.0.8 33.83 31.59 Unit turned off. Figure 9-2 shows AGC readings at Goldstone for a constant reference orbit in each cycle since launch. AH data. are taken, thefefore, at the same range, elevation, and azimuth. The AGC difference (8 dB) between the curves is caused by the dual effects of doubling the distance (6 dB) and the USB antenna pattern. The effect of the USB transmitter-A power decline can be seen through 38 cycles, and then the rise caused by substituting the higher powered B-transmitter (10 dB) through cycle 42. 41 -94 REF ORB 178 SLANT RANGE 1.060 KM -86 AZIMUTH 282' -88. ELEV. ANGLE 59' A, -92 co -94 > -100 -102 * SWITCH FROM U SBmA :O. 14 WATTS TO WSB=B 1,49 WATTS - 104 REF ORB 177 SLANT RANGE. 2136 K 106 AZIMUTH 1,76 ELEV. ANGLE 97' -108 CURRENT REPORT PERIOD I 1 -1 A 1 1- 1. 1 1 1 J. .1. 1! 1 1 1.. -1- j 1. 1.- :1 .1 0 4 8 12 18 20 24 28 32 36 40 44 48 2 66 60 64 CYCLE (OF 251 ORBITS EACH) Figure 9.- 2 USB (144k 4) AGC :Readings at Goldstone with 30-Foqt. Antenna 9-2 r. _ ♦ >'1•;,^. '..^.93w'w'^'iytN "Yti1. ,^ ^.t4M^,ICS-.M^%'S'^4rE'LY F } # U1, SECTION 10 t I ELECTRICAL INTERFACE SUBS YSTEM Auxiliary Processing Unit (APU) consists of Search Track Data, Time Code Data, and Back-up Timers which operated satisfactorily throughout this report. .period. Telemetry for the APU is shown in Table 10-1. The APU is in Normal mode. r.. Table 10 -1. LANDSAT-1 APU Telemetry functions Orbit Functions Description Unit 7 2600 5098 7650 .10182. 13198 13569 14001 13200 APU,. -24.5 VDC. -24.90- -24.90 -24.90 -24.91 -24.91 -24.90 -24.91: -24.90. VDC 13201 APU, -12 VDC . -12.08 -12.08 -12..08 -12.07 -12.07 ' -12.06 -12.06 -12.06 Volts 13202 APU Temp. DGC 25.49 28.50 ' 26.05 29.21 27.15 29.99. 28.24 27.45 The Power Switching Module (PSM) contains the switching relays for power to Orbit Adjust, MSS, WBVTR - No. 1 and No, 2, RBV and PRM. The MSS power circuits have been operated on a .regular basis throughout this report .period. The power relay for the RBV remained in a failed closed condition since Orbit 196, but the RBV remained off by relays in the c unera subsystem. 'The. WBVTR No. 2 remained off due to the failure. occurring in Orbit 148. The WBVTR No. 1 operation was suspended in Orbit 10861.due to high minor frame synch errors. The PRM remained on throughout this period to supply switched TLM power. The Interface Switching Module (ISM) performed all switching normally durin this report period. Compen- i? sation Loads changes were exercised in this report period as reported in Table 11-2. 3 ii u u f tS: ^' t Y SECTION 11 THERMAL. SUBSYSTEM x .. The Thermal Subsystem of LANDSAT-1 has maintained spacecraft temperature control over a satisfactory gauge since launch. Table 11-1 shows average analog telemetry values from data recorded on the NBTR. During this report .period, the sun angle varied as shown in Figure 3-3, and the intensity deommwed as shown in Figure 3-4 for day 424 to 113. Figure 11:-1 shows a typical thermal profile for average bay temperatures M of the sensory ring in this report period. The values are consistent with the limits established over two years of orbital operation. t The Compensation Load History is shown in Table 11-2. Compensation load 3, turned on in Orbit 12604. to warm up the wideband electronics unit 1, was turned OFF in Orbit 13206, In the same orbit, compensation load 8 was also turned OFF, since it was located' near Battery ,6 Rr which showed an unhealthy increase in temperature. s: iS8 F .. .. NNW ^ ^w^ h f !, LS..1 i1 . nTY rrn; :_; fr •,3..,^, ^sa^ F?s+.a$rrt.iY'^u.,.».,rs - ^'„Fk>9'^.3:^.k ^!^af!a. Gc?^,r^'ar^^F!,gci. ."t?!^C?[C'}:^ue:zaxr,^ FH A7 °s 7dCg'^$'^ F. u ...E"va u e ^e .^na =S ^_.u. g ^.^^9+.^. ^_ eta_-_e. ^^es ^.A '^.n^'S i^=-mav^ciiu^.^cYn u0.^._^ooW HaW uN^ -i'i -1 y i H i i ij I i i _ 'iii -i •3 'i'i -i -1 •3 .-0 4 i -1 .? . H -4 -1 y •d -4 : -1-^i y KM- K x -1, ^^•i •i'^I-^] .-1 H..dN N.^ r x = x z - s-.x.¢ m 'x z x:z z ^n - m:m:z's.z xx.- .1 ^ 3 ..:>.i.s 4 - ;^-. _ - _ _ --G'r S ^',"L'L-8.^ YiQ Sxz , ^^ ^E F F _^ GGGLGC IVU _ U _1 .s.:-5ii_.,-] i-I y •i ,-1-1 3 .4-i ^i n .+ i i y i . 1:HH,..x ^I ^ i ^l .EEEF - ' ' i-i: - gYY33TT tS.CD^ `: CS>S¢':^',^^ x: ^q :'F k^'1'^HyH < ^- xx CD M. ivi. °m3 ° m u .^X £'K^ ^ ^i'^A i ^-i^^ T. 1 :J J JJ-J t^ ^` -•y.:^y„'^i FF M S.Q .^-I-ice .-ITIPPtL SI'm¢F¢U.0 ^nn 'Nis4 PP¢^..p^^ to ^6i - P 9o: p IcW- .j Z2 = f .^ r S_t'1'C.R.f:.C[ fu is !>RRf GGG CAS;.igeE H CW.m^i_ 47 - ._^'C S.0 = 5 9 m m G.P G,F.x-9 S...'S'.^:C O O p . ^^ Q, `I 0.'.._'':a Z T1'^I f n F i ri ^.5 , 77777.^q Q p1 = E S 8 S $ ^ RZH.usg592rssZ SRgBR89S88S$:8 8 $^RB^ SSS^ ^nnnn.nrr S ^Rnn^^ '^^ Rnn^ ^R n c:^ d^c nficrc" ^ ^^ ^ 1 4 -^i^a ♦ ^m^^i$'o'. $wv^o^. .,_ a^^:'. 'e- 3 Y - v - vwt4NtV. UV. itta13Y P.:o'o^aa3 -oa ^ g E w - Qa, a +xa xs^C, ^ G ENS ' ap m m # _^ d^: $ 3.$-8 .0 o . m . . . ^.... m ...... :r. - z -,. 8 n L^ izm ^w ;^az=^_: a v ci a= 4°mm !i v.IgL°.'n'.Y. -G'' .Fu -mb°'':'mS' €: _ aa^°,'^ . °> mfP> 'f3ioRi...m^oEP.. ...°..m-ws-.. ' ^...g.o'€..^r', ^a..aa,or".,' : ° C^....^^.^^-$3ax^ .^ _ -^EGwmP ' N «.m i".$-Sm-ma U'S''ol w V Z o ^ u a =i.u' rl 6 S'P O. n• p . . r oi- Utz N -^i ^i m -1 la 9^Q T .I II +} X AXIS s sa J +) Y 1X IS AXI L . I i i_ r Table 11-2. LANDSAT-1 CompextsHistoryon Load History Compensation Load Status* Orbits 1 2 3 4 5 6 7 8 Launch 0 0 0 0 0 0 0 0 0 x x x 0 x x 6 x x x x x 0 x x 0 0 118 0 0 0 0 0 ..j 156 x x x x x 0 x x 194 0 0 0 0 0 0 0 0 197 x x x x x 0 x x 701 x x 0 x x 0 x x 1410 x x 0 x x 0 0 x 3484 x x X. x x 0 0 31544 x x 0 x x 0 0 x .3646 x x x x x 0 0 x .0 4177 x x 0 x x 0 x 6872 x X x x x 0 0 x 6966 x 0 x x 0 0 x 829I x x x x x .0 0 x 8348 x x 0 x x 0 0 x 8449 x x x x x 0 0 x 6472 x x x x 0 0 x 8538 x x Y, x x 0 0 x . 8928 x x 0 x x 0 0 9898 x x x x x .0. 0 x 10410 x x 0 x x 0 0 x . 11125 0 0 0 0 I 0 0 0 11126 . x x .0 x 0 0 11197 0 0 0 0 0 0 0 11133 x x 0 x x 0 0 .12604 x x x x x 0 0 13206 x x 0 x x 0 0 0 *Note: x = ON 0 - OFF. I SECTION 12 NARROVIBAND TAPE. RECORDERS LANDSAT-1 The Narrowband Tape Recorder Subsystem (NBR) continued to perform in a completely satisfactory manner until Or'bit 13015. From Orbit I through 12647, the two recorders, A and B, alternated in Record and Playback modes, switching roleb nominally each orbit with a 1-minute overlap in Record for continuity. if After Orbit 12627 on 14 January 1975, the roles of the NBR's were revised to per-form all telemetry recording and playback on NBR-B; and to use NBR-A to accumulate telemetry spanning MSS operations for use in processing MSS data. L. Beginning in Orbit 12837 and during the week ending 8 February 1975, NBR-B exhibited noise "bits" during playback. This condition continued, and NBR-B was rested (OFF) in Orbit 13015, NBR-A assuming the total load of telemetry data Record and Playback. Real time processing was implemented to provide spacecraft attitude information needed. to process MSS images, a function previously provided .by NBR-A. NBR-B has remained in OFF status through the remainder of this reporting period, To conserve the life of NBR-A, telemetry recording operation was restricted only to spacecraft health, and was limited to 7-1/2 hours (2 tapes). daily of data. A detailed discussion of the NBR-B anomaly Is given In Appendix C, PIR-U-1N23-ERTS-131. NBR operating times by modes are shown in Table 12-1. Table 12-1. NBR Operating Hours by Modes (IANDSAT-1) NBR: on Off I Playback Record A 1217.3 11920 488 11685 B 11851 10540 474 11377 Table 12-2 repeats *Idcal telemetry values since launch as shown for the previous reporting period. Due to the anomalous behavior of NBR-B and subsequent reprogramming of NBR-A support activities, telemetry values for this. period are not available at the .present time. Table 12"-o is a significant sample of the data in this reporting period showing the performance parameters of the Narrowband Recorders. It includes data to evaluate the entire link, including the radio downlink trans- mitting: data from the recorders and the effect of ground station processing. The "mean data rate," nominally 24 Idlobits, reflects the motor speed. The slightly slower speed has no effect on fidelity, but only increases operating time by less than one percent. The standard deviation is a measure of effects that would cause 11wovet and "flutter" in a major frame. Occasional high values are attributed to transmission link noise. The performance of NBR-A appears excellent and Is as good asithas been at. any time since launch. i_J 12-1 rl '01@ 12-2, Narrowband. Tape Recorder Telemetry Values r Typical Toternetry Values - Orbits Function 181- 7 0^ - 6. 1 10862 No, Name 1956 3751 :481` 9866 12944 10091 A. - Mator Cur. (ma) Record 190.10 189.4.7 188.20 186,31 186.31 186.31 186.31 P/B 180.00 177.63 17.8.60 172,10 172..10 k80. 60 170.52 10161 B - Mow Cur. (ma) Ree: ,rd 183,26 192,79 193.04 194.19 195.79 198.95 198;95 P/B 188.18 189:47 85.44 186,33 189.47 1 h7,89 189:47 10002 A - Pwr Sup. Cur. .(ma) Record 320.56 939,81 338;29 339.81 339,81 3.49:.81. 343.19 P/B 538.78 563.11 5168.38 569.56 569.56 567.75. 569:58 10102 B - Pwr Sup. Cur. (ma) Record 317.112 333.75 336,05 343.50 346.75 3.,0;00 346.75 P/8 570,18 567.50. 5551.83. .574.00: 567.50 . 567,50 567.50 10003 A - Rec. Temp. (DGC) 25.47 26.,25 24,.40 24.20 22.80 23.60 26.25 .10103 B - Rea. Temp, (DGC) 24.58 25.38 23.41 24.54 24, 7.7 .:3.41 25.38 10004 A - Supply (VDC) -24.47 - 24,56 -24.44 44.82 -24.62 -24.62 .. -24.57 10104 B - Supply ('VDC) -24.44 -24.:57 -24.5.1 -24.57 =24.29 24.29 -24.76 Table 12-3. LANDSAT-1 Narrowband Recorder Subsystem Performauce Orbit Bad Missing MM Devi, Rae. Orbit Bad Missing Mean Bev. Bee. .1-2752. 0.41 0.0.0 -23.84 . 0.02 B 13315 0.00 0.00 23.89 0.03 A 19764 0. 01 0.28 -23.84 0.40 B 13320 0.00 0.00 -23.89 0403 A 12764 000 0. 00 -23.86 0.02 ja 13357 0.00 0.00 -23.88 N. A. A 12771 0.00 0.00 -23.86 0.03 B 13371 0.00 0.00 -23.88 0.05 A 12778 0.00 0.00 -23..87 0.03 B 12834 0.21 0.00 -23.85 0.47 B 13405 0.00 0.13 -23.89 0.49 A 12841 1.61 0.00 -23.86 1.46 B 1-3413 0.00 0.00 -23.88 0.03 A 12847 0.00 0.00 -24.08 0..01 . A 13443 0.00 0.00 -23.89 0.12 A 12848 2.05 0.15: -24.08 1.96 B 13464 0.00 0.12 -23.85 0.02 A 12865 1.24 0.13 -23.86 1.40 B 13475 oil .00 0.00 -23.88 0.03 A 12939 0.34 0. 01. -23.05 0.67 B 135311 0.00 0.00 -23.88 0.02 A 12946 0.00 0.00 -23.87 0.02 A 13539 6.00 0.00 -23.88 0.03 A 12953 0.64 0.00 -23.85 3.08 B 13543 0.00 0.00 -23.88 0.03 A 12959 1.62 0.00 -23.85 1.31 B 13549 0.00 0.00 43. 88 0.03 A 12960 0.00 0.00 -23.86 0.02 A 135611 0.12 . 0.00 -23.88 0.43 A 13043 0.00 0.00 -23.88 0.02 A 13625 0.00 0: 00 -23.88 0,03 A 13050 0.00 0.00 -23.88 0.03 A 13632 0.00 0.00 -23.88 0.02 A 13057 0.00 0.00 -23.88 0.02 A 13639 0.00 0. 00 -23.88 0.03 A 13064 0.01 6.21 -23.87 0.65 A 13646 0.00 0.00 23.88 0.03 A 0.15 -23.88 0. 48 A 13071 0.00 13670 0.00 0:00 -23.88 0.03 A ti 13141 0..00 0.00 -2.3.85 0.02 A 13,723 0.00 0.00 -23.88 0.03 A 13,154 0.00 0.00 -23.88 0.02 A 13729 0.00 0.00 -23..88 0.04 A 13162 0.00 0.010 -23.89 0.03 A 13740 0.00 0.00 -23.89 0.03 -A 13169 0.00 0.00 -23.88 0. 02 A 13751 0.00 0.00 -23.88 0.05 A 13190. 0.V0 0.00 -23.88 0.02 A 13758 0.00 0.00 23.88 0.06 A 13245 0.00 0. .00 -23.88 0.02 A 1384-1 6.01 0i,38 -23.88 0-03 A 13252 0.00 0.06 -23. 88 0.02 A 13854 0.01 0.00 -23.88 0.09 A . 13266 0.-00 0..00 -23.88 0.06 A 13859 0.12 0.00 -23.91 0.04 A L .13273 0.02. 0,00 -23.99 OAS A 13866 0.00 0.00 -23.88 0.02 A 13278 0.00. 0.13 -23.88 1.48 A 13869 0,02 0..25 - 23.89 0.60 A SECTION 13 WIDE BAND TELEMETRY SUBSYSTEM The Wide Band Telemetry Subsystem (WBTd) consists of two 10/20 watt S -Band FM TransmiUars and associated filters, antennas, and signal conditioning equipment. The subsystem is used to transmit Return Beam Vidicon (RBV) video data and Multispectral Scanner (MSS) digital data to LANDSAT ground stations. The RBV and MSS data can be transmitted in real time as it is being generated, or recorded on either of two Video Tape Recorders (or both) andplayed back th=ough the WBTS when in view of a ground station. ^. The Wide Band Telemetry Subsystomm has operated successfully since turn -on in Orbit 12. a WPA No. 1 was used with RBV input until Orbit 196 when the RBV power input circuit failed. WPA-1 was used again, this time with M&S input, between Orbits 1890 and 2099 because its operating frequency was less likely to interfere with the Apollo 17 launch operations. The cumulative ON-time for WPA No. 1 _ is 31 . 9 hours. When used after Orbit 20,- it operated in the 20-watt mode. . WPA No. 2 has been used with MSS input since. its initial turn-ON in the 10 watt mode during Orbit 12. .It was changed to the 20 watt .mode in Orbit 30, and has operated at this power ever since. It was not used r between Orbits 1890 and 2099 The cumulative ON time for WPA No. 2 is 1.695.3 hours. 'fable 13-1 gives the telemetry values for both Wideband Power Amplifier units. All values are normal and show no significant trends. i Figure 13-1 shows the History of AGC levels observed at Goldstone when the spacecraft was at two selected y points in space (identical azimuth, elevation and slant ranges). Variations in ground equipment performance, calibration,procedures, . and readout accuracy are the probable causes of saw-tooth appearance. The Y larger variations in AGC levels have been attributed to equipment substitutions or adjustments. Within the limits of repeatable calibration and equipment adjustment the power delivered to Goldstone appears to tt have been generally constant since launch. The power output of the WPA-2 as measured by telemetry (Table 13-1) has remained level since launch at about 43.5 dBm. During cycles . 4.1 through 45 Goldstone N used their 85400t . antenna instead of the normal 30-foot antenna. r a a a P 2)S G I5-1 w i W Function Orbits Number Name 26 1894 1944 2095 32003 Tmpt TWT Coll. (DgC) 35.7 39.20 39; 90 39.90 12002 Helix Current (Ma) 6.08 0.49 6.5B 6.7.8 QsC 12003 TWT Cath. Cur;. (Ma) 45.89 43.54 43:.48 45.01 12004 Forward Pwr (DBM) 43.18 42.88 42.:51 43.15 *yC7 12005 Reflected Pwr (DBM) 34.95 34.99 34.80 35.21 12227 Loop Str. AFC ConVolt (1) (MHz) -0.39 =1.29 -0.86 -0.67 122.229 Mod Temp VCO (DgC) 21.93 26.31 20.88 20.39 12232 +15 VDC .Pwr Sup A (2) (73V1V) 2..69 2.69 2.65 2.62 12.234 -15 VeDC Pwr Sup A (TMV) 5.98 5.96 5473 5;78 12235 +5 VDC Pwr Sup A (TMV) 3.94 3.94 3.94 3.95 12238 -5 VDC Pwr Sup A (TMV) 5.28 5.26 5..1.8 5.12 12240 -24 VDC Unreg Volt A (TMV) 5.56 5.51 5.42 5.49 12242 Inv. Temp (DgC) 20.60 23.43 24.71 24.04 y .i 1 UMPA-2 Function Number Fume 33 2595 4096 10602 12551, 113569 14001 1210.1 Temp TWT Coll. (Max) (DgC) 35.38 34.80 34.24 35.96 34.80 35.54 .36:54 7.80 12102 Helix Current (Ma) 7.32 7.46 7.70 7.67 7.83 . 7.75 12103 TWT Cath. Cur. (Ma) 44..30 42.52 43.85 42.72 43.22 43.40 42.83 12104 Forward Pwr (DBM) 43.57 43.3.5 43.57 43.47 43.4.8 43.48 43.39 12.105 Reflected Pwr (DBM) 31.59 32.11 32..78 32.62 32.83 32.86 32.66 12228 Loop Str AFC Con Volt (1) (MHz) 1.11 -2.01 -0.78 -1.12 -1.19 -1.17 -1.13 12229 Mod Temp VCO (DgC) 23.70 24.04 20.88 21.50 20.76 22.24 22.38 12232 +15 VDC Pwr Sup A (2) (TMV) 21.68 2.58 2.99 2.69 2.65 2.67 2.67 12234 -15 VDC Pwr Sup A (TMXV 5.90 5.71. 5.98 5.92 5.85 5.89 5.84 12236 +5 VDC Pwr Sup A (TMV) 3.97 3.91 4.01 4.01 3.85 4..00 3.96 12239 -5 VDC Pwr Sup A (TMV) 5.24 5.05 telemetry pclnt "cave 12240 -24..5 VDC Unreg Volt A (TMV) 5.43 5.33 5.52 5.46. 5.471 5.43 5;45 12242- Inv. Temp (DgC) 1 23.0.3 .22.95 22.96 23.66 23.41 22,95 22.97 (1) Satisfactory if not zero or - 7.5 (2) B Tower Supply not. yet used in orbit .....:«m-^rnr...... -.r.....^..^.rr-r.».,...-....-...... ^, ...,.e...... -...nr^ .^... ^...-.....n.,,.-x,....,e^^-..n.,.,-y. ^-..r7.^..,,.m-.-r-.....«^..r. . _,...... +..-.^ _ eF*...:,-..,av^•x..«•...r+.+^s.•-^s*.•.r.r.+e^masw.wr. w -68 REF. ORB 178 . SLANT RANGE 1060 KM —7:0 AZIMUTH. 282° ELEV. ANG. 590 _-72 —74 .01 —76 ^ D^^`• -80 a F -82 REF. ORB 177' SLANT RANGE 2156 KM R -84 AZIMUTH 97' ELEV. ANGLE 17° -86' CURRENT RE PERIOD -88 —90 . 0 4 8 12 16 20 24 28 32 36 40 44 CYCLES (OF 251 ORBITS EACH) X^ rX F{ w, Figure 13-1. LANDSAT-1 AGC Readings at Goldstone with 30-Foot Antemm C4 Wide Band Pwr Amp-2 (Link 3) ... w f--.... r z`^F ^: l^ -;n.^l. -^ wri U s{x x!fyiyej3':ki4:^F^Sjc-a -?a_^C-f .wP*+s f I y SECTION 14 S ATTITUDE MEASUREMENT SENSOR s d Telemetry output of the AMS continues to be normal and in good agreement with the ACS subsystem. 'T'able 14-1 gives typical AMS telemetry values. Table 14-1. LANDSA7-1 ANYS Temperature Telemetry ^i Orbi unction Descriptim units 35 50999 10182 13,198 13689 14001 3004 Case-Temp 1 DGC 18.92 19. 42 19.71 20.0:0 18..93. 19.15 8005 Assembly-Temp 2 DCC 19.15 19.76 19.96 20.28 19.16 19.39 4 SECTION 15 WIDERAND VIDEO TAPE RECORDERS The Wideband Video Tape Recorder Subsystem consists of two components - W-BVTR-1 and WMR4. WBVTR-2 failed in Orbit 148 after '9 hours, 26 minutes and 33 seconds of satisfactory flight, performance. WBVTR-1 operated with RBV through Orbit 196, after which It was re-configared to operate with MSS . . The WBVTR-1 has had 4 major disruptions In its service, generally characterized by high headwheel current (above 0.70 amperes) and! high Minor Frame Sync Error counts (above 300). These disruptions occurred during: Orbit 3469 on 29 March 1973 4 Orbit 8253 on 7 March 1974 Orbit 8845 on 19 April 1974 Orbit 9.881 on 2 July 1974 After Orbit 9881, the tape recorder was temporarily removed from operational service for engineering tests. These tests were suspended. after Or-bit 10861 on 10 September 1974,, The recorders were not used A during this period. The usage of the tape by footage is shown in Figure 15-1. 06 5 YI 4 LAUNCH THRU ORBIT t0174 Z 08 ^..^ w 3 IL it yy LL 0 S i. t Telemetry values for all functions are shown in Table 16-1. Although the WBVTR Ts were not used during this period, the last telemetry Values are included for completeness. Some of the tel.emetered functions. have different values for different operating modes: Playback, Standby, Rewind and Re card. These are 3 shown in Table 15-2, showing stable operations through Orbit 9881 except for the four o ccurrences of anomalies listed above. Table 15-1. WBVTR Telemetry Values (LANDSAT-1) WBVTR-1 Functions Telemetry Value.in Orbits Numbor Name 15 1 2599 029 --TMB 10602 10729 1086Z 13022 Pressure Trans (PSI) 16.12 16. 3.8 16.11 15.98 16.97 15:97 15.96 13023 Temp Trans (Dge) 19.50 25.05 21.84 20.81 20.64 20.39 20.09 13024 Temp Else (DgC) 22.78 25.34 20.44 23.72 16.85 16.84 16,34 13026' Capstan Speed (`b) 100.51. 98..25 101.93 102.84 88.24 101.39: 90:16 13027 HcadwheelSpeed (`b) 95.16 96.84 95.17 93.47 85.04 90.26 90:81. 13628 Capstan Mot I (Amp) 0.25 0.26 0.27 0.28 0.20 0.22 0.24 13029 input P/B Volt. (VPP) 0.72 0:41 0.45 0,33 0.54 0.38 0. 56` 13030 Headwheol Mot I (Amp) 0.55 0.55 0.54 0.55 0.61 0.54 0.53 13031 Rec Input.I (Amp) 3.15 3.31 3.08 2,82 2.64 2.13 2,79 13032 Lim Volt Out (MI) 1.44 1.42 1.45 I.17 1.32 1.32 1.33 13033 Servo Volt M 50.03 50.23 50,74 47.7.1 49.97 48.95 48.98 13034 . iS.6 VDC Conk . (VDC.) _ 5.66 5.71 , ; 5.68 5.65 .. 5.86 6.84 6.78 Wl3VTR-2 hmctiens Orbtt Number Number Name 15 54 103 1.47 13122 Pressures. Trans (i>51) 15.99 16.25 16.25 16,11 13323 Temp Trans (DgC) 18.46 19.19 20.72 21.04 33124 Temp Else (DgC):: 21.50 22.00 24.00 21_92 13126 Capstan Speed al 99.91 160453 100;86 90.38 13127 HeadwheelSpeed 0) 94.16. 95.48. 97.64 98,78 13128 Capstan Idati (Amp) 0,17 0.24 0;24 0, "!B 13129 Input P/B Volt (VPP.) 0.66 0.63 0.62 0.61 Headwheei Mat I (Amp) 0.55. 0.59 0.52 0. ,3 r. r 13130 13131 Roe Input I (Amp) 3.70 3.53 3.07 3.43 13132 Lim Volt Out (VPP) 1.34 1.41 1..41 1.:19 13133 Servo Volt (°.b) 49.:97 45..60 49.80 49„48 13134. .+5.6VDC (VDC)_ 5.47 5,64 5,58 5.59 s. f 1 p j.t Table 15-2. WBVTR-1 Function Values by Mode in Orbit (LANDBAT-1) Orbits Function/Description 913 2379 3781 4876 7385 7953 9866 10862 13029 - Input P/B Voltage Record 0 0 0 0 0 0 0 0 Playback 0.40 0.45 0.58 0.53 0.48 0.48 0.67 0.69 Rewind 0 0 0 0 0 0 0 0 J? Standby 0 0 0 0 0 0 0 0 13028 - Capstan Motor Current, Record 0.23 0,24 0,26 0,23 0.26 0.25 0.25 0,28 i;A Playback 0,25 0,25 0.26 0,26 0.28 0,23 0,28 0.26 Rewind 0,23 0.20 0.20 0,17 0.17 0,18 0,18 0.20 Standby 0 0 0 0 0 0 0 0 13030 - Headwheel Motor Current Record 0,58 0.55 0.58 0,58 0,58 0,58 0.60 0.57 Playback 0,56 0.55 0,62 0,56 0.55 0,58 0,59 0.54 Rewind 0,47 0.44 0,46 0,45 0.43 0,45 0.46 0,43 Standby 0.47 0.44 0.44 0,44 0,44 0.44 0.44 0,44 13031 - Recorder Input Current Record 3.70 3.63 3.46 3,40 3.40 3,30 3.30 3.20 Playback 3.85 3.89 3.74 3.76 3.69 3.56 3,59 3.56 Rewind 2.20 2.18 2.07 1.89 1.94 1,85 1.85 1.85 Standby 1,96 2,08 1,78 1.73 1,88 1,98 1.85 1,85 13033 - Servo Voltage Record 0 0 0 0 0 0 0 0 Plavback 50,30 56.37 50.70 50.78 50.76 50.96 50.86 51,05 Rewind 0 0 0 0 0 0 0 0 Standby 0 0 0 0 0 0 0 0 13026 - Capstan Motor Speed Record 98.50 96.70 102,88 103.41 103.41 105,09 104.53 106.49 Playback 98,40 97.20 101,3 102.40 101.16 104." 103,41 103.96 Rewind 101,70 101,1 99,20 98.90 99,48 9t 98,36 98,36 Standby 0 0 0 0 0 0 0 0 13027 - Headwheel Motor Speed Record 97.10 100.0 94.23 93.64 93.06 91.88 91.88 90.70 Playback 97,10 97,80 93.69 92,93 93,06 90,70 91,29 90.70 Rewind 100,72 100,70 95,10 93.60 93,64 91.88 91,88 41,88 Standby 100.70 102.80 95,41 96.00 95.41 90.12 93.65 1 93.06 ORIGINAL PAGE IS OF POOR QUAL= i is 15-3/4 F y s SECTION 16 1 I RETURN BEAM VIDICON The Return Beam Vidicon (RBV) Subsystem operated normally from turn-on in Orbit 19 to Orbit 196 when J it failed to respond to a :turn-off command because of a probable. failure of a relay in the Power Switching I Module. The RBV .itself was not the cause of the failure, nor was it affected by the failure. The RBV has not been reactivated since Orbit 196, but it is capable of operation through individual component power s switching. An assessment of the RBV performance was given in ERTS-1 Flight Evaluation Report 23 July to 23 October 1972. For completeness and convenience, the telemetry values are repeated in Table 16-1. J ^ Table 16-1. RBV Telemetry Values (LANDSAT-1) i Function Orbits T/V No. Name Value 26 85 349 196 14001 CCC Board Temp. (DgC) (1) 18.61 20.04 19. 30 19.53 14002 CCC Pwr. Sup. Terse. (DgC-) (1) 19.93 21.58 2040 .21.21 14003 + 15 VDC Sup.. (TMV) 3.95 3.69 3.95 3.78 3.95 14004 + 6V-5.25 VDC Sup. (TMV) 3.05 2.84 2.93 2.98 3.05 14106 VID OUT CAM 1 (TMV) 1.06 1. 04 1.15 1..13 1.12 14200 VID OUT CAM 2 (TMV) 1.09 1.05 1. 26 .1.23 1..24 14300 VID OUT CAM 3 (TMV) 1 . 05 .1.03 1.21 1.19 1.20 14102 Comb. Align I Cam 1 (TMV) 3.95 3.67 3.94 3,87 3.94 14202. Comb. Align I Com 2 (TMV) 3.92 3 . 90 3.91 3.89 3,.91 14302 Comb Align . Cam 3'(TMV) 4 . 04 3.75 4.03 3.80 4.:0.3 14103 Cate 1 Elec Temp. (DgC) (1) 20.84 23.37 22..64 25.38 14203 Cam 2 Elec Temp. (DgC) O 18.64 21.06 20.62 22.87 14303 Cam 3 Elec Temp. (DgC) (1) 21.05 23. 61 23.23 25.57 14104 Cam 1 LV Pwr Sup T. (DgC). (1) 2.1.71 23.94 23.49 25.82 14204 Cam 2 LV Pwr Sup T. (DgC) (1).. 18`..38 20.63 19.40 23.30 14304 Cam 3 LV Pwr Sup T. (DgC) (1) 20.75 23.02 22.73 25.67 14105 Cam 1 Def. + 10 VDC (TMV) 4.01 -3,73 4..00 3.77 4.00 14205 Cam 2 Def. + 10 VDC (TMV) 4.00 3.71 3.98 3. 77 3.98 14305 Cam 3 Def. + 10 VDC (TMV) 3. .97 3.95 3 . 95 4.02 3, 95 y 14106 Cam 1 + 6V -6..3' VDC (TMV) 3.73 3.45 3.70 3 . 61 3.70 14206 Cam 2 + 6V -6. 3 VDC ("TMV) 3.69 3.42 3.67 3.49 3,67 14306 Cam 3 +6V -6.3 VAC (TMV) 3.78 3.47 3.72 3. 47 3.72 14107 Cam 1 Telec I (TMV) 2.62 2.50 2.54 2.55 2.64 14207 Cam: 2 Telec 1.(TMV) 2.65 2.53 2656 2.41 2..64 14307 Cam 3 Telec i (TMV) 2.64 2.54 2.51 2.45 2.61 14308 Cam. l Vid ru I (TIM 2. 47 2.30 2.. 36 2.,38 .2.46 14208 Cam 2 Vid Fil I`(TMV) 2.54 2."37 2:52 2.39 2.52 14308 Cam 3 Vid Fil I (TVM). 2.61 2.44 2.60 2.53 2.60- 14110 Cam 1 TARVOLT '(TMV) 3. 43 3.42 3; 42 3.45 3.42 14210 Cam 1 TARVOLT (TMV) 3 . 36 3.13 3.22 3:.26 3.32 14316 Cam 3 TARVOLT (TMV) 3.47 3. 23 3.46 3.45 3.47 14113 Cam 1 Vert Def V (TMV) 2.9.6' 2.75 2.90 2.85 2.97 14213: Cam 2 Vert Def V (TMV) 3.00. 2.86 2..98 . 2.86 3.01. 14313 Vain 3 Vert Def V (TMV) 3646 3 .45 3.4.7 3.31. 3.45 14114 Cam 1 Vid FPT (DgC) (1) k8.15 20.77 17.91 20.99 14214 Cam 2 Vid FPT (DgC) (1) 20.62 20.11 "20.52 20.62 14914 Cam 3 Vid FPT (DgC) (1) 18.54 20:88 19.08 20.20 14115: Cam 1 Foe Coil T (DgC) (1) 17.71 21..67 18.74 19.70 1 . 215 Cam 2 Foc Coil T (DgC) (L) 17.79 21,60 19.25 19:'97 14315 1 Cam 3 Foe Coll T (DgC), (i) 1.8.03 22.09 119.88 120.56 (1) Thermo-Vacuum. temperatures for these functions were not reported. 16-!/2 _ "y, , i.rra.;sz+ua>5"^s. ,.' ,L'nrw+. r•^":;.,hrr^rx -,a•^• I s --; SECTION 17 MULTISPECTRAL SCANNER SUBSYSTEM The Multispectral Scanner (MSS) system consists of spacecraft and ground equipment which permits images of the earth to be obtained simultaneously in 4 or 5 spectral bands. LANDSAT-1 and LANDSAT -2 MSS use a 4-band scanner operating in the solar reflected spectral region from 0.5 to 1 . 1 micrometers (microns) wave length, and scans cross -track swatches of 0.5 km width (at a 496 nm altitude.), imaging six scan lines across in each of the tour spectral bands simultaneously. The object plane is scanned by means of an oscillating flat .mirror between the scene and the double reflector telescope optical chain. The 11..56 ,. degree cross -track field-of-view is scanned as the mirror oscillates approximately +2.89 degrees 13.62 times per second about its nominal position. The instantaneous field.-of-view of each detector subtends an earth-area square of 259 feet on a side from L the nominal orbit altitude. Field steps are formed for each line imaged during a scan, anti for each spectral band, by the square input end of an optical fiber. Six of these fibers in each of four bands are arranged in a 4 x 6 matrix in the focal plane of the telescope. i f_J The Multispectral Scanner Subsystem (MSS) has operated. satisfactorily since initial .turn-on in Oej!.t 20. .. The MSS has imaged nearly all of. the land masses between the latitudes of 81.42 6 N/S. Many of U^ese scenes 1 were repeatedly imaged, some in the United States as many as 45 times. A very large percentage of I,- t every .continent has been imaged. Figure 17-1 is a computer derived map showing how many scenes . were imaged at each geographic location since launch. Along the right -hand edge of the map is listed the ir--ame l { number - frame .1 being at the northern-most extreme, frame 61 centered on &,e equator, and frame 121 at the southernmost extreme, thus giving latitude. Along the top of the map is the number of the reference orbit which fixes longitude. The land masses are distorted to fit this map projection. Figure 17-2 shows how many scenes were acquired during this reporting period. MSS has transmitted real time images to two foreign countries; 20,192 images were transmitted to Canada, and 14,515 to Brazil. Table 17 -1 shows typical, telemetry valued during this quarter. All functions are normal. The maximum MUx. temperature to date has been 33.25 C which occurred in August 1973, when the. MSS was accidentally left ON at LOS, and was turned OFF by the 32-minute back-up timer: The calibration lamp current has ! remained nominally at 1.12 TMV from pre-launch to the present. i Time Code extracted from de-muxed data was found normal. The response history of each sensor to a selected input radiance level is shown in Figure 17-3 thru 17-6. --t Only one radiance level for each sensor has been selected for graph presentation, but the other five levels f selected in the computer program to determine the calibration wedge shape have been analyzed and found j to be consistent with the data .presented. . In general, the graphs show an early gradual decrease in sensor response from launch to Orbit 1000, and essentially unchanged response thereafter. The notable exception is sensor 13. The response of this sensor has gradually increased about 15%, so that it saturates at a lower radiance level than the other sensors. The History of Line .Length Word vs. Orbit Number is shown in Figure 17-7. It is satisfactory and stable. ( Sun calibrations are performed every two weeks and continue to show normal performance. The 94 Sun . I Calibration Orbits are listed in Table 17-2. ^ A record of MSS operations in the Higb Gain and in Linear Mode is shown in Table 17-3. . L8-1 17-1 I - ,._ .-'. CWa^T?YC: .. .'..-. _. ?SSL='YPKYU^ . a - • -- ' 'r i Table 17-1. LANDSAT-1 MSS Telemetry Values Telemetry Values in Orbits Function Name No. 20 2599 5060 1 10597 13330 13569 14001 15044 FOPT 2 T (DGC) 17.46 21.03 19. 84 19.75 19.04 19.11 18.82 15046 ELEC CVR T (DGC) 19.37 23.53 21.83 21.96 20.14 20.28 19.99 15048 SCAN MM REG T (DGC). 16.35 22.84 19.77 20.48 21.05 21.17 20.44 . 15050 SCAN MIR DR. COIL T (DGC) 15.94 21.97 19.30 19.78 20.51 20.57 19.77 15052 ROT SHUT HSG T (DGC) 16.91 20.88 20.07 20.23 19.48 19.62 19..32 15043 FOPT I T (DGC) 17.67 21.17 20.01 19.93 19.26 19.31 19.03 15045 MUX PW'R CASE T (DGC) 21.19 2.6.84 22.03 ". 87 26.44 25.57 24.17 15047 PWR SUP T (DGC) 1.7.41 21.95 20.00 20.21 20.04 .20.23 19.80 15049 SCAN MIR DR. ELC T (DGC) 16.12 22.76 19.41 20.23 20.90 21.10 20.21 15051 SCAN MIR HSG T (DGC) 15.60 21.46 19.05 19.49 20.11 20.07 19.40 15040 MUX-6 VDC (TMV) 4.03 4.03 4.03 3.98 3.99 4.03 3.95 15042 AVE DENS DATA (TMV) 1.67 2.52 2.13 2.05 2.13 2.25 2.37 15054 CAL LAMP CUR A ITMV} 1.12 1.12 1.12 1.12 1.12 1.12 1.12 .15056 BAND 2 + 15 VDC (TMV) 5.10 5.10 5.10 5.04 5.10 5.10 5.10 15058 BAND 4 + 15 VDC ('IWV) 5.10 5.10 5.10 5.04 5.05 5.10 5.10 1506.0 +12 -6 VDC REG (TMV) 4.82 4.92 5.02 4.97 4.93 4.99 5.02 15062 +19 VDC REG OUT ('1'l1IV) 4.80 4.90 4.90 4.97 4.93 4.99 5.20 15064 SAND 1 HV A (TMV) 5.10 5.12 5.16 5.12 5.12 5.13 5.12 15066 BAND 2 HV A (TMV) 4.50 4.52 4.52 4.52 4.51 4. 50 4.52 15068 BAND 3 HV A (TMV) 4.60 4.63 4.62 4..62. 4.62 4.62 4.65 15070 SHUT MOT CON OUT (TMV) 2.43 2.46 2.44 2.47 2.46 2.49 2.46 15041 S/D CONV REFV (TMV) 5.93 5.82 5.93. 5.87 5.82 5.89 5.82 15053 SCAN MIR REG V (TMV) 4.42 4.53 4.51 4.56 4.53 4.58 4.5£ 15055 BAND 1 + 15V (TMV) 4.97 4.97 4.97 4.92 4.98 4.97' 4.97 15057- HAND 3 + 15V . (TMV) 5.00 5.00 5.00 4.94 5.00 5.00 4.91 15059. -15 VDC TEL. (niv) 5.02 5.02 5.02 5.02 5.02 5.02 5.02 .15061 + 5 VDC LOGIC REG (TIVTV) . 4.82 4.80 4.81 4.77.. 4.79 4.76 4.78 15063 -19 VDC. REG OUT (TMV) 3.43 3.50 3.39 3.50 3.51 3.52 3.51 15071 SCAN MIR DR. CLK (TMV) 1.93 1.97 1.97 1.98 1.97 1.99 1.96 `R^2a;^, .. -=cl.' ^ s ^a^ti,: ^if^„ay .^ - _ _ .'^a...^Sk^.`rsY^d.^dst« ^^3`n^l3tili^6d:^2tiltiw mow. ^is,^ ^rx.e#u ^ zc.^za--w.r^ k <>-&. ^ 4 alp i l E-r ♦ E E[ C 22 c 2 I T-2 2 2 2 2 t a 2 C 1l Z 1 2 2 2+ E • ( S . • •• w 4 2] r 2 { I l d[ •. f E F r a f r+ l i S l i l t 2 G: ^_ _ 0 y1V 1'. T 2[ L:S •• S• t t l ^ r C f L - S G•+![ G G[ i [It I+SG l • C 2 2 - T I l Z 9 L< 1{:[ [2 2 t T 1 2 r .. c[ [ T <' E t Z 1! f G 9• 9 9 l[ C E.E E k• ( CIG12:RR • r E I l I S I l( 2 2 .. 2] c f - C (T3 I S I S C.d z 2 21 1 - S L L • r • L V •T0 , E 1':2 L - E' [ E E L E 7 c 1 E e E[ L L F LL • L t 2 t! 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IO re jTOF,vL9¢lC81D6 9L989CS 68198lEdt06vL1f89CiT06SiL96^E8ip"^^- UPS fi4X48^C2 6vivG !EiTO6v;a0!Caia@vi !►8t0avLypqEeTi - I _Z l2[i TITTS1tiTOSl0900000aeauescr.^cvaoyyp •^r^^aooygaoao gage. eeuc^^r t^ llpgfi^ly' RieeaRa»aaaaf^rs T: ^iti p e ^ i1fiT1111^1eT1i1TTS1TUT' a`liYiikv,itia twxu-.; .,.:.p:^tyy^si!st: <:vuhb,^ar: ^.ms.+rM.sw^:ar.,-.i._.•;^,s.:-a.,,^e.^.a:o,.jtii:m^s^.i:.rzz.:^^:h^i^:'.:vrrt^n-x,.^^x:.:.wv...:_iwna^,[ i.--Lim i'a.t:;1:.4.,v,aixv.c.,-,^:w.+asr„r_,iR:wniiR,+ri^zls m a^::^e,-;.....:.i..v....-.;:»_: ._.^.,:H..s ...:..u..e..,:.^^e:,zssa^.^ft+tn, ^^ra.s_s::^[ -.r^.x.G.:uuursu...;-,.s..^,.,,..W,_-,.^.,,....^ B AND Nn, 1 QUANTUM VB.. QMT WORD 110. 100 r µ Cs^ s L, 63 e µ r 31 a 0 K 34 SENSOR S: 4 3s SE.N.50.p:N0: r f 4 SEM^^^ 37 a 1 1 ^. 36 4 100 .100 ^ S00 2700 2400 3100 7300 3300 ]700 MO. 4100 4300 4]03 MM 3700 4400 51M 53001 (ORBIT NO.) 45 f f1 µ BAND NO, I 4.' QUANTUM 115. ORBIT WORD NO. 300 i i F 41 } AO - 0 S.. az 36 r ^. a 4500 3700 4400 5100 - .100 _ 300 500. 700 40 1100 1300 ISOC 1700 1400 2100 2300 Z500 4700. 2400 3100 - 3300 3300 3700 3906. {100. 4l00 (ORBIT NO.) 0 r a.JIJO V a c 3 6 PM ssM Ssoa OM 5260 SIM 6309 65W 6760 MD 7500 TIM 79010 SIM OSM OSCO 103 109 III 1C ti a 5; I . I I I I . j —! a I s *I LL— i I I -L . — I I S7w fim 7100 7700•?m mO B* lum WOO im M 107 109 Aw wo 5 ^00 7500 5700 590; 6160 fi ^l MLDOUM 1. Ls-1 3 I I - t Dow moo sm ow wm ...... ub, ism moo wo sm lim &-165 to IG§ 111: i13 115 1 . 1 18 lil ow tzs, li7 46 131 193 f35 137 lag 14f j Figure 17-3. Quantum vs Orbit (IANDSAT•1): (ORBIT NDJ 49 CL A, FOLDOUT I a i 0 Z. 4706 1706 4900 S100 S506 5500 5700 5900 6100 6304 6500 6700 6WO 7106 7506 7300 7706 7400 6700 4360 ISOO AM 1100 4300 41100 UN 4700 ON 40700 11006 IIIsIII00 14 .7 1 J S x s T S ,_, 4 a F r F F f. 4 ^: i. ^ i I' 1 ^ 1. i ^. ^ r I. 1 I 1 1. i.. 1 k 1. 1 I L ! 1. 1. I i I I 1. f6700 0306 8506 87 CC Y00 9t00 Mo 1960 8700. 9 tOIw 10100 tOM 107 109 111 113 155 117 119 121 123 7TS 1Z7 129 731. 133 135 137 139 141 k "r N A .9- 0. n^J ff (a+srr NM) i a3 n t Vc P"^ 13 e; is OW MQ L igtoo in= 10!5 101 1500 4700 4900 3100 5300 5300 67*0 5900 6100 9300 6500 noo . 6400 1100 7300 7570 7700 ?960 It w 9700 law woo low mw th 17 is 00 9900 45004700 4200 3100 5300 5500 9700 5900 6100 6300 6500 6700 6960 7106 7300 7W0 77 ?900 8100 9700 9706 8700 y. UT 1a 14 f tt ^s is 100 BIM !!6a 6706 MW Moo go&fWW MW MW !slab 10/90 105 107 109 1.1 .1 113 119 - 117 119 121 123 129 127 129 131 133 135 137 139 141 y 1 i too 11G9 85M 1760 0"00 6100' LS- 31 30 29 za z 26 25 24. 23 22 31 3D at 23 24 23 22 ti FOLDO'T Li t Li . ..:,.. ^ ^.,. n ... .:- rp$i r!;,< H:`,nc°JiPol!!F3siF„F. T2ii ^ 1.9 t9 M Z1 20 Y f I- i .^ ^ -^ 1 1 900 Sim 5700 5900 D 1200 V100 9700 om OM 9100 10100 103 105 107 1 L I. 1 I. l ] 1 I t Y s. ^ Y 1 Y l 1 I you 7100 7sao 7700 7900 o1w sim eso0 97oo woo ow SM woe 9700 2100 MOD 103 105 307 109 R31tYs^[S^'HifES='.:JY'^^' 'N'^i_ 2!:ry ^:tN"3p„.. - .. . 1. .. i ... `1a 19 N 21 to 139 141 3226 3ZZ4 3222 N 3220 LL 0 3Zi8 f S7 z a 3216 w z 3214 32't2 3210 ORB-IT NO, - -. ...:. _. -.: `... .:•-...:. ...-. . w : .:.: __ ^\,^..r... .__.:..:, n r --Yf' ra.n hs, C _ ".i_. :-^.!Y_^ic"f,`i%'a^..r^i, ^2PP' t Y.-.. .. ^.. fb.:.^° $C1• LENGTH V5. ORBIT 116 i wa i d8 Table 17-2. LANDSAT-i Hun Calibration Orbits Y, 21 1012 2278 4161 6657 8943 10M 13296 G 47 1207 2375 4370 6852 8999 10561 13685 89 1303 2389 4537 7047 9208 10756 13880 103 1400 2473 4705 7242 9389 10951 131 1497 2585 4900 7437 9585 11161 M!T 214 1595 2668 5095 7633 9724 11331 326 1692 2766 5304 7829 9766 11539 423 1790 2964 5499 8038 9808 11733 521 1877 3159 5861 8220 9850 11928 619 1985 3351 5891 8413 9892 12123 730 2082 3543 6072 8608 9975 12513 814 2166 3742 6268 8803 10171 12918 AR 915 2180 3938 6463 13003 13100 13103 dd Table 17-3. LANDSAT-1 MSS Operation Orbits in high Gain Made, Mux Compressed ef: u 3967 5174 12257 3784 5216 12354 4218 5230 12368 4893 5244 12382 4907 5272 12396 4921 5286 12859 5132 5300 12873 5146 5314 12887 5160 5328 13901 IANDSAT-1 MSS Operation Orbits in High Gain Mode, Mux Linear 13124 .IR 13138 13152 1 r ^ T .S d x ^ 3 JF I~ . Ar 17 -17/18 r sA r4^s SECTION 18 DATA COLLECTION SUBSYSTEM (DCS) The Data Collection System is designed to relay data from randomly distributed Data Collection Platforms (DCP) through the LANDSAT spacecraft to either of two receiving sites at Greenbelt, Md. or Goldstone, California. The DCS system is designed to collect and provide at least one message from each of up to 1000 Data Collection Platforms in the continental United States every 12 hours, with a probability of 0. 95, with a nominal LANDSAT S/C orbit and both ground stations operating. The Data Collection Subsystem (DCS) operated Satisfactorily from turn -ON in Orbit 5 thru Orbit 12690, after which it was turned OFF. The DCS in LANDSAT -2 has assumed this function since that time. For convenience and comparison, the following data is repeated. Only Receiver 1 was used. Since turn -ON this receiver has operated for 19, 704.6 hours continuously, except for an interruption of 11 hours because of ACS problems on September 29, 1974 during Orbits 11125 to 11132, and for the interval between Orbits 12608 and 12659. Since turn-ON in Orbit 5, this subsystem has received 1,155, 065 messages, of which 1, 059, 886 (91.. 8%) have been perfect. Periods of heavy interference have added false messages to both "total" messages and "Imperfect" messages, diluting the apparent "error" rate, and making the "percent perfect" figure an unreliable figure of merit. All telemetry functions have been normal as shown in the typical values of Table 18-1. Table 18--1. DCS Telemetry Values Value in Orbits No. Name Units 15 2599 4811 10592 11587 12078 12565 16001 Revr 1 (DBM) -124.09 -124.39 -123 . 36 -123.52 -123.85 -122 . 59 -124.03 Sig Str 16002 Revr 1 (DGC) 22.72 24.07 23,74 23.65 24.1" 24.71 24.67 Temp 16003 Revr 1 (VDC) 12.02 12.02 12.01 12.02 12.01 12.01 12.01 Inp Volt Figure 18-1 shows the total number of DCS messages received per 1.8-day cycle since launch. The number of active platforms is also plotted on the same time scale. It can be seen that when the number of active platforms reached about 100, the DCS messages received per 18-day cycle reached 28 thousand for about 9 months, decreased with the USB power drop, then rose to about 23 thousand messages per 18 -day cycle. Since then, both the number of messages and active platforms have declined. Table 18-2 shows the qualitative performance of the DCS subsystem and Table 1,8-3 gives statistics of messages received. & LS4 18-1 wzr 30 25 2426 -16— DC5 MESSAGES 22 U>- 2G i6 f 12 qdb— ACTIVE PLATFORMS Wtn 10 M TRANSU05TITUTEP REDUNDANT OUTPUTSMITTER-0 1.5 WATTS POWER1X26 3. —NUU SS POWER CL22 8 10 12 14 16 18CYCLES 20 22 (10 24—DAYS 26 EACH) 28 30 32 34 36 36 40 42 44 46 40 50 Figure 18-1. DCS Message Receipt History (LANDSAT-1) Table 18-2. DCS Qualitative Performance (LANDSAT-1) System Threshold 3500 kni Grazing Angle Effects Not discernible Adjacent DCP Interference Not seen Ground Transmission System Sataifactory Probability of Perfect Reception of any Messages During Window* 98.9% *Window means "at times when the :Jpacecraft is simultaneously within the horizon of the DCP and the grouind receiving station". Table 18-3. DCS Statistics (LANDSAT-1) Through Orbit 12749 DCS Platforms (""P!s) Shipped 224 Maximum DCP's Received per Day 107 Total Mess.ages Received at OCC 1,155,005 Total Messages Rejected at OCC 95.1 i179 Good Messages Maximum Messages per Day (9/31/74). this quarter 1,344 Number of Current Users 44 IANDSAT-1 ANOMALIES AND OBSERVATIONS Date Anumaly/Observation How Observed Comments J 7/24/72 Sun.Seasar Tempernture High Off-Line No Action Required ]For 1ER75 1; ERM B Redesigned 7124/72 SoLar Paddle Temperature Excursions Off-line No Action Required For ERTrI; Greater Than Expected Math Model CorreeW 7/25172 USE Power Out;ut Decreasing off- Line Switched to-StdL 13 In-Orbit I006L on 7/13/74. Under irivestigattoo.fnr EATS-B. Vo:powar drops in USB side B. 8/0/72 WBVTR No. 2 Power Converter Shorted Real Time Turned AR P/L Off During Pus, Formed,NASA/GEIRCAEvaluitilan & Off-une Committee. Disconnected since Anomaly. Redesigned For ERRS.-B 8/03/72 Decrease ln.Salsr Array Current Off-une Evaluate Degradation Effect Due to Solar Flare Activity REV Power Transient PSM Final Time Turned off PRM. MASA/GE, RCA EviduaffanC*mmtti"Formed; Turn-Off Failure Dfacom.tected.Since Anonutly. Redesign PSM For ER49_R 8/10172 DCS Reject Messages Rose to Over OFF-11" External Interference: Located Sourcm No:15cricus, .40(t of.TbW Messages far 25 Days. Interference Since. 0/10/72 mM Cal Wedge L evelB Decreasing Off-Line Leveled Off After Orbit 1000. At OrAbout 51 W Bakm Earlier values $103A2 incorrect Time Tap in Comazor 11111 Ceti .12 Real Time Belo" Comstora and Verify. (Discontinued ALtuvt U .Selof Cell 12) pitch 121U M Motor Drive DatyCyclea Off-Line Evaluate.- Prepared Contingency Plan 321002 Roll Ificreaud1or Short Underinvestiptlab For ERTS- B Taw Period 3/29/73• WBVTR NO- 1: High SER. Real Time Formed NASA/GE/RCA Committee; Lapped He-ads; Now in Operational Use. Temporarily Rearricted,to Lost'.600 Feet (600 Secomb) of Tape 4109/72 Slow Leak In Forward M Scanner Pressure Off-Line Not Expected to Interfere with.Normik] Operations 5/20/72 Defect In Signal of Left Cosine Pat at Off-Fine Not Expected to Interfere with Normal Operations S/C Midmight 8/03/73 Failure of integrated Circuit Chip and Real I Ime Tim Failure only. S/C Operations Nornn6d TLM of Functions 6012. 1011, 12238 and 702C & Off-line 11/5/73. WBVTR-1 Tape Unit Pressure Real Time Defect In Pressure Instrumentation which Causes Drop Occasional Rapid Pressure Drop In TLM - Returns to Normal It/13173 Sotar Array Drive Real Time Slight Pogko.on Drive Voltage Ripple which Picked up Limit Flag - Returned to Normal 11/26/73 High Head Wheel Currea WBVTR-I. Real Time Resumed OpertAlons After tuvestigation During Rewind WBVTR-1 Performed in a Nominal Manner D 12/20%73 Pitch Motor Driver uty Cycle Increased Real Time Similar to Entry 12/4/72 except more Sustained 12/22/71 RMP-1 and RMP-2 Showed Excessive Real Time Condition Lasted.for 5"" Orbits and Noise/Output Returned to Normal 2/20/74 Pitch.Whcel Stopped During-Sun Transient Off-line During a sun•irsovient in orbit 6040-the. pitch flywheel was-changing directions. As it passed thru zero speed, stopped the pitch Flywheel and-did not resume operation until 2 minutes had:elapsed in spite of application of 1009., clockwise pileb motor driver duty cycle during that Interval. 3/5/74 WBTR ♦I High EFR HIGH NW-1 Real Time Limited Usage of Tape Footage 00-Line 3/7/74. VY1BVTR-I-high HWI Rem Time Suspended operation pending study & W-Lino 3/21/74 WBVTR-I4Jgh HW Real Time Suspended operation pending study. aff-Ltne 3/27/74 WBVTn-I-MnE couat high On-line Suspended operation pending study 44/74 WBvTR-1-M FEE count high Off-14nr Suspended operation-peading study WP e "thtu'^Itdeeval'. _ —: •.;-`i•xe_^. rrlr ^.5 '..f'=:.f•.."`yb S/5/74 WBTR *1 High HER HIGH tiW-I Real Time Limited usage of Tape Footage & Off-Line 9/7/74 WBVTR-1-high HWI Real. Time Suspended-operatLon pending study &-t'tf-Line - 3/21/74 Wilmt-I-high. HWI Real Time Suspended operation pending study & Off=Llae 9/17/14 WSVTR=I-MFSE coant.hWb . Off-fine Suspended operation,pendiag study 4/2/74 WRVTA-1 -MFSE count=btgb Off-Lim Suspended operation pending study 1 5/21/74 Piton CCW Motor Driver Duty Cycle mcrssaw I Real Time Stmlliar to 12/4/72 entry. - ..t &UH-.Line ReturoedtanormaL 7/7/74 Pitch CCW Motor Driver DutyCycle locreeset { Real Time Simlllar to 12/4/72 entry. - & Off-Line Remrasdtanarmal. 7/2/74 WSVTR-1 -high HWI and-MFSE Real Time Suspended operation pendtiig:study & off-Line Pitch CCW Motor Driver Duty Cycle Increase Real Time Similar to 12/4/72 entry. Returned yj Normal. & Off-Line 6/2 I/M i Pitch CCW MotorDriver.Duty Cycle Increase Real Time Similar toi2 /4/74 entry. RehMMI .to Normal. & Off-Line - 1.8/28/74 Pitch CCW Motor .Driver_ Duty cycle Increase Real Time Silimar to 12/4/74 entry. Returned to Normal. & Off-Line - Pitch CCW Motor Driver Duty Cycle Increase Real Time SIU=r to 12 /4/72 entry. Returned to Normal & Off-lino 9/9/74 Pitch. CCW:MotorDriver Duty Cycle Increase Real Time Similar to 12/4/72 entry. Returned_to Normal. & Off-Line 9/14/7.4 PSM Power . Regulator -Swttchover From 1 Real Time VHF iuterference .sigoal present.. Occurred at to 2 - 02:4621. Spacecraft was normal. 9/23/74 PSM Power- Regulator Switchover From 2. Real Time VHF.iaterference signal present. Occurred - to 1 - 01:49il7. Spacecraft Is normal - Ron) Time Pitch CCW Motor Driver Duty Cycle Increase. SWmarto 12/4/72 entry. Returned to Normal. 9/25/74 & O8'-IJne - 9/2D/,74 Pitch Flywheel Stopped - .Real Time The pitch CCW motor driver duty cycle began Increasing inarbit 1If20:- Thepitch flywheel stopped.(from 400 RPM) - following a stn transient In orbit 1I125. After a period of approximately 0 hours, and attitude disturbances, the pitch :flywheel restarted. Earth acquisition was obtained and -operations returned W normal in'.orbit 11133. ;0/9/74 RMP B Motor Current Va riations Off-Line As a. precatitionary measure a switch was made to RMP A. & Real Time RMP -B .is still functioning and can be used In the event of RMP A failure. - Switched to Side B i? Orbit 10068 an :7/15/74. .Under investigation for.ERTS-B. No power drops InBSB side B. - t/30/75 Solar Array Current Notch On-Lire - Solar array current drops 500400 ma for f to 14 minutes early in the day then return to normal. Solar panel - temperature_ range is -20 to i f200C. No effect on-S/C Mission, Narrow Band Recorder 2 Bit Error Rise - Real Time Bit Errors be gn build - up IwOrbit 12637 and unit was turned ,aff in &: of1=Line Orbit ^130I5 on 2/12/75.. Unit is. approaching wear out of tape. y^,l :1/7175 Battery G Turned Off Real Time Battery 6 decrease in load share and rose slightly in charge share & Off-Line thereby causing high overcharge. Battery temperature rose and required turnoff of battery. When it discharges to 26.5 wits, it will he returned in-service. - Z F+ LV •f^-aaar; NAV,aY t.X..^'^4x•+C,.?,:i?%:'^Stu`:A'^•r . . k. ^''".'w"Zt'n'^'i^fS .F^ri"!;Y^i k!{x@ .T4}'i' ..':tr.'-,.?/i^,'R^2?If".n!¢?F!'k' ^.."^.: »ti . ^, ... '".!irf f- "?R :^'1'.f°. x(y'e^.:;^FY'u.;ax' . tnvn^,'v.S=+Y?i? ^TTe?7^.+t°4..^U^ti^P^'+tR 1!M K co L LO t• V t^- - z N H M a H c C EA N Lo P4 qIq d Ey E4 pq O . g W h 7 U 0 i s a: i^ k } y . . i ^ r i.._,_..'y : ¥ b' 1'R 1Fy' o-s" 5•'_!?''P F.. ":;H r,A . ^'"A B 'a!r..r9 3,`rw+ i'i !-: ms•^ l`FS'm^+;'k s4r- 4 - t. S :.:.,'^ 1 1^, ..-rl4 "TSB ' aT-mss! —. 3 t7A a ^.., . ^. , ^ . .,., _. ._. -. _ .-- .. ^ ^. ..:.y. "x :....,•^-' u^ x.J' " - tiw"^,w1 ^-.. ., .> rA-x v. ->r-y.$.,.. ,-...... N ^. ..-,. .- ,^K i . ,...... -^ ^ .. f .. _ . .a '^_ni4"+ . f^BJ$ -_^A-tt-kS'{.tJd5at.^^fn.•eLS^aLl°-M-^S`'I:LS^.4^'4"^i^i`k^M^iu vi^ki^i^CS':iYfSl^k^= •_.^•FaI^C^ :S:Fu.:+n:2ira - 4n [¢. 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I,. 0]-17516 1: 7'1 ^ . &4 , .. b 1 7.p I:: "_:. ------I. ------I. -----: ..1. 1256 - 175 ... _ _.. - ' w w.rw -.w-w a r w 4p w r w.a r.w W. w r.wr a 0 w w rw r.w w w:^.w as w w -.--- w w - r-^ - a.a -- - Of 0 a a 0 u ru 4cLAss. LTR. OPERATION PROGRAM 1EQUENCENO. sI:Y. LTR. OENERM0ELECTRICiR SFACE DIVISION PIA ND U — IN23 _ ERTS ---. 133 PRQGRM INFORMATION REQU EST /RELEASE 'USE "6" FOR CLASSIFIED AND "U" FO R UNCLASSIFIED 7M TO K.S. Rfzk T.W. Winchester DATE SENT OATS INFO. REQUIRE1 PROJECT ANO REO, N0. REFERENCE DIR. N0, 4/23/75 SUBJECT WBVTR-1 RE MD ANOMALY, IANDSAT-2 INFORMATION REQUESTED/RELEASED INTRODUCTION During Orbit 1021 on 5 April 1975, WBVTR-1 in 1ANDSAT-2 failed to rew_nd, although it was commanded to do so five times. DISCUSSION On 5 April 1975 during Orbit 1021, WBVTR-1 received a pre-pass ECAM stored command to Rewind at 23:08:45. The Recorder Input Current showed successive 1-second samples of 1.81, 2.30, 2.23 and 1.81 amperes spanning the interval from 1 second before to 2 seconds after the Rewind command. The Rewind Relay contacts closed, verified by telemetry. However, thI next telemetry sample, 16 seconds later showed the Rewind Relay open. Capstan Current, .:npled 10 seconds Fter the command, read zero, and no search track signal resulted, indic9t:zg that there a no take motion. When the real-time pass at Alaska started, Playback was commanded, on the assumption that the stored Rewind Command had executed properly. When it was realized that the tape footage was not at the scheduled place, playback was stopped at 23:16:14, and three real- time commands were given to Rewind at 23:17.16, 23:18:19, 23:19:35. Each of these commands resulted in the same brief rise in Recorder Input Current described above, but as before no Search Track Signal or Capstan Current was detected. After the real-time pass the pre-stored SCAM again commended a Rewind (the fifth attempt) at 23:23:23 with identical results as before. At 23:42:57 ECAM commanded a pre-s tared 'Record Operation, in which WBVTR-1 functioned normally, with Recorder input current of 3.67 amperes, Capstan current of C.28 amperes and Headwheel current of 0.49 to 0.51 amperes. The footage used in the on-pass playback was from 1331 to 1534 €t. The five attempted rewinds :.id not move the tape. The footage used in the final record was from 1534 to 1602.5 ft. The tape has not been moved since. Table la lists the real-time commands transmitted to the spacecraft during the pass. The ECAM stored commands are shown in Table lb. PAGE No. RETENTION REQUMEMENTS Dist: P . L. Smith H. Boys G. Ehrgott COPIE7 FOR MASTER! FOA J. Hayes L. Gonzales F. Putzrath-RCA C. Powell OS 420 F. Lee-RCA n R. Stauffer D. Hay kin-?tQ:.7--T R. Moore-RCA El 3 MOf• — n ° M °' D. Schwartz R. Davidson-312 D. Wise += N° s. B. Phucas J. Lesko-725 K. Rixk (4) ^0f ir00 n n °°°.^°.+,p°°. C-1 IS-2 IRTS R COMMAND UiSTORY KTRANQ FILF OPTAYLFB . COMMAND HISTORY _- _ . NO , 010 _ -- _ . -.- ^# BNB MSG C140 NAME AMT®RETR -.._. EMb _ ^... -_. _ - - -- A9 _. ®0^._.___.SAO... -•-- .--- T4C/ TRC SE0117NCI:' ^3gg98r^+_.. _ A^I1 373 VERIFY T ICM 03111847 n3n Ono . SPARF '--'0A0 -SPARE 03211:4$1 RPARE --73894808 Win - On® b6a Ono µ- SPARR 03811:48 _ 07A 000 _ - _ P3811 i 49 -, nRn — -- Ono SPARF 03814:4q n9n 487 VERIFY TOCK 23811:511 _. -•--- ion 005 SPO - W61a 4 PBOR - i3 11P :.19TT. 11A 702 TNw hATA/RRV FLY B 03112:4n 4 pn Ono SPARE 03112:4n 930 Ono f:PA RF 0311p: 41 14n 6n7 WAVTR I ON IPRTMI 93892:49. Q S n Ono SPARF v1:1p:41 1fn 7no 1NW DATA/MAR FLT B P311?:4p 970 000 —SPARF _ .03i12:4p 18n 000 SPARF 0319p:41 99n 5n5 M59 STANDBY 9 _. 0319P:4^, 911x} Ono SPARE 938 1 p:43 537 TA 9 nATA/MSS FLT R 0:411P:44 _.. Vi99nn . - 000 APARI: P311?:44 03n Ono SPARF 03112:45 p 4n Ono SPARE 03119:45 PAM Ono SP A RF 9311?:45 Phn Ono gPARE: PIS I p:464 p 7n ar,o SPARF a3:1p:46 9fn Ono SPARF 03812:47 P9n GOD SPARF pi 1?:47 q on o m SPARE 9311P:47 39n 147 WBR PIAYBACK g 93812:48 .%pn 006 BOB NRPI 03912:06 2 r, 64b PMP S!r L NSTR I 03313:n7 -_ . ---. -- __ aKn -Ono SPARF s3813i07 'ASn Ono SPARE 23113:OR '^r5n 6p1 NRR RFC 9 P /A MOnE 0311 a: nR 27n 009 5c75 MSS STANDBY 9 93316:01TT 3Rn 50S MSR STANDBY 1 03115i17 aqn 010 505 MSS STANDBY 9 03116:10 .6nn 5175 MSS STANDBY 1 238 4 Ss: 9 ! 1r9A o14 46.5 FACT REWYNn 9 231i7e15 oPR 465 FART REWIND 1 g ; 46 4an o12 81+6 LpAL3 OF'F 93117:54 4k 46 04 7 wPA PR wER RFE: P P3 9 171 SS 4.riin 0 00 SPARF 01:17:55 &AM Otto SPARE 03817:56 47A Ono SPARF 93817:5A rRn Ono SPARF 93:17:56 49m . 5d+1 wPA P8wER HF'F 9 0:919 x:57 FOon Ono SPARF 73117159 -°h Is L, IF 1 a. C-2 U-2 r I -.-., __... - —-.--- .. _ _ - __ - __— -,- —_.---•------.. —_------._.^. --...---__°_ - .. _ _ _- RRTt1 ^ 00MMAND ea - cSTBRv KTRANA -FIL$r M9 o_...Q1A...^__.. ..,--- DFTAILFn, COMMAND 141 STORY 0140 NAME _------aMT / RETR -- ET1ME RPARF .—__ i3117s%A -- non Ono SPARE 03117 : 5A s^4RE .a3t 17, BA __ -.. _ n^^------^.r _.____ 4nd ..----- •— ------'.. ►tl 566 WFM INV A PRWER OFF 03t 17:59 ART REWIND - .0fin. _ .. 013 465 F Pat 1A: t 7 ---- - 06n -_ 465 v FArT REWIND 1 r P —MR-.t 1 _-- n7n--- .----.01 607... WBVTR 1 ON jPRTMt __03HAT-49 HAA 6n7 WBVTR 1 ON T SC R T M 1 P311 A 150 5n5 _ _ MSR STANDBY 1 73119: 07 ^Inn 505 MSc STANDBY 1 03919:09 _. _..9 9 n Oil 465 FACT REWIND 1 P391 ^9 ^,21 IVA 4A5 FACT RFWINn 1 r"-119:3 b _ Inn .. 018 505 MS9 STANDBY 1 1 ^1i 5n5 MSR STA ND BY 1 P312p,^ o kJ 9Rn 019 6c;1 wRVTR 1 OFF P3:?0:,R ihn 6s1 aRVTR 1 OFF P31?nt19 17x1 020 On3 USRF P3t ?1!49 ` 9An 665 RM P m nOUL-ATAR A Or F 031?1:50 9 9n Ono SPARE a31 a1 :5n Rnn Ono SPARF a3 1?it5i p in Ono SPARE 1p3S?1:51 - --- a^n -- - -- 0n0 SPARE os i 2] : 54 33A 757 DIRABI E LISR WMTRS 03121:52 a yn 021 357 AUX LRAD P AN P3: PP: 47 S!sn 357 AUX LAAD P PN 0312e :69 Pf%n 022 ins FCAM RUN A/i 9AD R 231MIR P7n Sn5 FCAM RUN A/i f1A7 8 P31?3::^9 PAM 023 61;1 WBVTR 1 OFF 93:23:.x,9 P9n 6F;i uBVTR 4 OFF P?624: 0n .PSTAP * n % Gv 4F PO ^ PAi-- - x QU^,r^ IBS-2 C-3 i .1 1 ^I i t ^: w^ r D-lN23-ERTS-133 Page 3 23 April 1975 'r TABLE 1b SCAM STORED COMMANDS FOR WBR-1 K LANDSAT-2 ORBIT 1021 PRE PASS TUIE om DESCRIPTION 23:08:38 607 WBR-1 ON :40 505 STBY :45 465 R/W 23:10:38 505 STBY :40 651 OFF i J POST PASG TIME CMD DESCRIPTION 23:23:16 607 WBV-1 ON :18 505 MY :23 465 R/W 23:25:09 505 STBY :11 651 OFF 23:42:50 607 WBR-1 ON :52 505 STBY :57 426 RECORD 23:44:08 505 STBY :10 651 OFF rt^ C-4 18-2 .U-1N23-ERTS-133 Page 4 23 April 1975 Figures I and 2 are the Brush Chart recording of WBVTR-1 telemetry values thru the periods of WBR activity in orbit 1021. The average values shown on these charts are given in Table 2. These values are normal. Temperatures are about record lows for orbital data, but not out of limits. Since launch, the temperature of the transport unit has varied from the low of Orbit 1021 (I6.7 o) to a high of 20.74 0 . The average is about 18.3°. The Electronic Unit has varied from the low of Orbit 1021 (13.10 ) to a high of 25 0 . Average is about 14.60 . Brush charts of the preceding thirty orbits show identical values; the single difference being the sudden rewind failure. An item of interest is the 2-second rise in Recorder Input Current at each Rewind Command, as described in the opening of the Discussion. This rise may also be seen in Figure 1 for each time the Rewind command is given. This is very similar in appearance and magnitude to that seen in LANDSAT-1 when Record was commanded in the Lap Section without being preceded by the Lap Command. In orbit 8646 a Lap operation was planned. The sequence of Commands, however, neglected to precede each tape motion (Record Command) with the Lap command. Of the 9 Lap activities planned, only 4 were preceded with the LAP command. See Table 3 and Figure 3. These resulted in a current increase of 1.45 amperes. The Record Commands without the Lap preceding them resulted in a Lurren't increase of only 0.54 amperes. This value may be compared with the 0.43 amperes which was the average increase of the 5 rewind attempts in Orbit 1021 in LANDSAT-2. Until Orbit 1021, WBVTR-1 had functioned normally in all respects. Tape usage by footage is shown in Figure 4. WBR-1 has operated since Launch for a total of 64.35 hours. The head -to -tape contact time in orbit_ has been 52.8 hours. Canbined with pre-launch head-to-Cape contact time of 522 hours, the total head-to-tape contact time has been 574.8 hours, compared to its expecced life of 1000 hours. In orbit, the number of ON-OFF cycles was 860. rg K.S. Rizk Systems Engineer /pkp i C-5 i IS-2 s 1 F.^T^i„^ ..^^ - , t l t. I ►^^S brnu^ ^tt'1^v^ 1^^aA8N1 ^- 3 ^ ^- 4, ;^^` i `I I ; _._. ^, ocsa -r ^; no L I " "cry 4 sz^ I -I ! I L ^ i . TT -. _ ^— I _— I I , 4t ^r ; 9t ! i i71 —! j I 9i^T i ! ! 91ji~ ! I 9 T — _ ! 9l/l ^ _ h51^ - I ! ! I I ilSf}i I ! I -E Bi7^' I V40 611Sbf7— t I - - I Bs^i91a I i- ^9IFBI +— IS I 1 ^ ^ ^ V I t^ l I , t I k ' + ' ^ ^' ' ^ I illawl ^'$9 4u 3^YiTl uaiI ' a-gsaua In Hari^.T = inaiil a rx ax ^ iartK^— ag n ;^^` 33i a !—.say it ash — zJa Ltiaa—Y uffn I ! I I t I! I j—^— y { I t i I i _ iI -^_^ - I l t l I t I I I I I! l I I I I I I I I n _,^ 1 ._'".."^=—` '7 I 1 ^ I ^ ' — , ! I I ! I , i ^ 'i I I I I I ^ I , I I i -64uET I , pZafi LOOCI3lLi4EI3 SQO£2 '^^I ^760E111900Ci3I I COOCld —i Za LTE:3ri0°E':'— ours , not I ;tuli^lcdvia I I 4ao:a^T j"^9t7c^zia t curi a # I I ra4i ^^ :z;_._ ._ i 3 1 ,:O MI 4a d.L Alo i d[^[ 9 9 d I -(Al 2tl ' fixsA613 Ssm u I v u _T VP^ • L cr Q U1 i ^I fs I I i i, lliffitl^irl3ll^fi(EI(Illliifll t^j +^(t)If^ (J !!11l^ 1111Effii4(f' J I^^^Ulll^q) Elglflll)IIIpI !flJ)11,1 ) I^ i lll ll^l f^ji? ^;t ;l i(f(iiflll!^I^) fl)f'^I(f (fiifli i^lj ffiffilf f^lilllil'iluE^iflrunurnlfi fil(flllilllfif^ilf^^^llifl^f( ^I(f^i^1111111101lllilllffffil fil^iffff^ffffllli^i, ! I J .a^ + ^^. =.. l 1.. I.i^ll•,^ ! i 111 I 1 _ ' I 'III — 77—T—Ft dt r -rht I IT i #I I I f IT,^_ j_I_ i ! _L ^ f--i r 4-- I I I I I ^ ! __ i -'i_ ^I ^^,--} j ^ ! I ; 1 —I 1 E_i_:-_..# I ' , i . I ^ }..- —^-_ I I ^-- I- IT; l i j - 1 ^ I j ^ l i l i ! I} i r r t l I I i k i I i i i i I_ I _ ! ' i l i ' I __- I !_ TT F ^k^ _ I ^ ^ ` I ` # r I • l'1^7s'^f:A^. i k i_I ^'YT ^ _# i I^^_I_i . i i ? C f. I—I,—^_.i_ _Lhj1i^:'^4iµ^ eMl - - _ . ^_ ` I 1 ` -I, _^ I i 1 ' it ^ Yi I I I } ! i I- I ^ Tc (^ ^ " 'I i I ^!^ I I ! ^ ^Ti ^ ^^^ i ;. i- - - -^ - —I -_- - - W6VTR- Pp,rc" L ^Rosp Vs; Luc; ! ( I ^ 1 till } I , I ^ •^ f- ,7 Ilil_'. :ili!,Illll^^llk^.11Il,fll C- LS-2 n tV V by ^^+ jy , r t _.t^^ i- • Rl i mk F rtr - ^i + k CI 1 ! C2R1: CBR leis Cl2RI CISBI R0 I Ct.3l{ _ CiR2 t ; 1 - T_'i^— _i__!___ FF3Rlf 1 { F13C---1.- I36.4F30 ° QI41^F14_^ci §^I ^t^ax w...^ i I ^ I I I I^^- 1k^ 1 T^t^ Bq1 ERV OLtW13R ^I S IA I lgws mg F Spa M .^MAP I p 1pms ` ' a_ f 6T RLG ans 3 VpLF 7 TI L1 ! I ! ! ^i I i ' ^ I I I C--"'[....I ^-^ I I ! I i I ^ I I ^^^ ' I ! !.^..'! i ^ .. ! I ,,^ I Ctte6 ? ^' ..Fin i 42 I I I C1g L'! _: ! tt^ ' I G18 A3_;.T ICi1 2. e y _ 1 i i Lit • 1 _ I! lii ' Ik _ L l fl _^^ -r I _ __ lfi_ i__ T-'1l.If^- I t 15_ I Il/ 1^ ! i 2Z !F13023.. t I + P 13Q2^' I I j^ ' I Pon 6 p FII43Z - ^'^' ^L3[t33 —31742Cr_.__^ - 70 _ t _, I ^ t I i ^ __ I ^-+ ^ I—^iIT i— I ; I I I I i IT I I ^ , .. «^ ^ _.^_1-1— ^–r----^– -.- -- ^ I I! -^ i i^ i' ^' I I-_-- L I L !! I CLLI I C I I l I! — I -^i ^^ I I WBVYR-( Pima 2 BRUitt TO&4 I I t i , N i i J °i I i i 'e f F } 3 I I I I I I E } I I ! I ^ I I rA a f^ r ^i 6- - it t i I ! 1 1 1 1 _- __ i -_ r... 0 MF Fill: i I - L- - - - = I i -^ ! f f = i i - ^-I [ - i FT ' '-i= I i-! t ! -^ i i f I- 4 t - _ I ,I ^i-.i-i ^-- 1 I • -i--' i --f - -; _I _i-^ i _ r J_+_ i! ! _i i i!! I 1 1? ! I I°' 1 I- f ' _; , I I i l ^. I i i ^' I -T t. i II ^^ 1 I j ! i i' I i l' lj-^l.. r _t -; i t i-I I .P i t_ W 9VT12- 1 Ph iof 2 BRUSH[ VhLtJQ -' I I t l l l i l I, i I I i! i I I 1 1 ^ I i 1! i tS' LS-2 C-9 i r U-1N23-ERTS-133 Page 9 23 April 1975 TABIB 2 TELEMETRY VALUES OF BRASH CHARTS FIGURES 1 AND 2 FTf_`11RF 1 VALUE FUNCTION DESCRIPTION UNIT S B R W RxC P B 1,1031 Rec. Input Current Amp 1.78 2.30 3.65 3.79 13030 headwheel Current Amp 0.45 0.44 0.50 0.49 13028 Capstan Current Amp 0.0 0.014 0.28 0.28 13029 Playback Voltage VpP 0.0 0.0 0.0 0.34 13034 +5.6 Volta VDC 5.73 5.73 5.45 5.25 VTMIRI' 7 l"INCTION DESCRIP'T'ION UNIT S B R W REC P B '032 Limiter Voltage VPP 0.0 0.0 0.0 1.50 `_.033 Servo Volts % 0.0 0.0 0.0 50.28 13026 Capstan Motor Speed % 0.0 - 90.9 90.9 13027 Headwheel Mat. Speed % 95.7 96.6 95.6 95.6 13023 Transport Unit Temp. DGC 16.7 16.7 16.7 16.7 13024 Electric Unit Temp. DGC 13.1 13.1 13.1 13.1 13022 Transport Unit Presal. I PSI 16.9 16.9 16.9 16.9 IS--2 C-10 7 l- U-1N23-BETS-133 Pose 11 23 April 1975 TABLE 3 QM*M HISTORY LANDSAT-1 ORBIT 8646 TMM Cho} DESCRIPTION 18:32:24 507 LAP 1 426 WBR REC 1 18:33:2! 505 STBY 18:35:08 426 WBR REC 1 18:35:11 505 STBY 18:35:21 426 WBR REC 1 :24 505 STBY 18:35:35 426 WBR REC 1 :38 505 STBY 18:36:14 507 1AP 1 :51 426 WBR REC 1 :57 505 STBY 18:37:10 426 WBR REC 1 :13 505 STBY 18:37:36 507 UP I :44 426 WBR REC 1 :47 505 3TBY 18:38:11 426 WBR REC 1 :14 505 STBY 18:38:24 426 WBR REC 1 :27 505 STBY 18:38 :45 507 LAP 1 18:39:24 632 WBR OFF LS-2 C-11 _. f L 1 I r.l }1" T mm '^. L1:. LL. ^i :1 1ll'Or a I + ^t^{, r_.-...... --. r`^.^ rj- ^}- 14 gee11 r`\^j ^^ `j fir' J+}\ ,j{ t{ t^1^y4^4`v ' i 41_*j PAP! r .iL. .. i 4 i ' i„ l^-1^ Ll1 i_L !-i1,^71.;.L{ r t ^^ 'T`^ .. t sr ." L^J ^i..t^^ f i ^. •.^ l i ^y r 1^ FallF 4 i m^ r _f t jot ! . . '+`F}— 4 r- r r`; r ^r }^ +^} ^p 1 IF I1-^+t J I ty ^j• L T-t' i F^ . t o . .. ^ ! { t 1 Y j r{TT* i'i "!ri '"rir TAT" I _-__ - '. 'T l _ ^iT`s_.ii 7 _i } i Ei! E. .^ 1 Bat i r --t"t— {- _• ^t " rt e i L r _: Z a. i i -r• f F 1-! ('^""'^^^-Sri-hj"-r"r+" I . 1 L^ ^'t'Yr^'.', -^ ^ ... + A -+1-h--_^_-.."T-•---^i^^-- 1 LE: E i V TR-1. PATr, It ^ANbJ R7 S O'Ztl r r Is-2 C-12 k ,---' r--_ ------' _--- ,--' ------~--- '--- r r r r ------' / mosnGE 4 TAPE USAGH BY F=AGE RZIT Ll If F-4,I vm LE ^_i J. t to jL i I ^ f 1j ( APPENDIX D RBV FLIGHT IMAGERY Representative imagery from the REV is shown in the following figures. Spectral bands are given in Table t D-1. 4 Table D-1. RBV Imagery Wave Length I Figure Band (Micrometers) D-1 1 0.475 - 0 .575 Blue Green D-2 2 0 . 581, - O.680 Yellow-Red D-3 3 0 . 698 - 0.830 Red-IR All photographs show the same ground sf:ene, 185 x 185 square kilometers in area. The scene covers a segment of the California Coast from Oxnard ( right center) to Santa Maria (upper left, obscured by clouds). The suburbs of Bakersfield are visible in the upper right, with the San Rafael Mountains extending from Santa Maria to south of Bakersfield. The Santa Maria River can be seen coursing through the San Rafaels near the top center of the picture. Snow cover is seen over a considerable area of the mountains. Vanoub i familiar landmarks such as Vanderberg AFB, Cachuma Reservoir, and the city of Santa Barbara are located t. . in Figure D-2. The Santa Barbara Islands, while partially obscured by clouds, are easily visible and identi- fiable. Primary traffic arteries are generally visible, and many secondary roads can be seen. The difference in response of the three spectral bands can be observed by comparison of cloud and haze areas,, and by differences in the relative contrast and grey levels of topographical features. 3 - E M-2 D-1 i-_ J ^I 41 N ' III pli • r i N e 4 e e N e a s e •^ WI 38' 4i -88i I '" 9.381 26fE875 C KM-25/1111^^6 N N3^-2Y^I1_^-^7 R9V I ONTO AN EL78 RZ^^i 198^ • G • I- h -{t ^iSR CATS E2Bi -^^^P'^ .^ ORIGINAL PAGE L5 OF POOR QUALITY Figure D-1, LAND.SAT-2 HBV, Band 1 D•-2 IS-2 i C L L . 2d 8G! .+ i 19. 391 H IS au I' 3 h 0 .IL 'PT. A _LO V PT. CON ON A BAR CHA 0 y N i a SAN MIGUEL t SAN SA 2 ^. St ' ' N 2 DOO EL-' a? P2B9 SrJ^^ 17.4:2 a_ E WEM C "- A , _^ K!^•2YW < I : ORIGINAL, PAGE IS OF POOR QUA nYj Y16-urn D-2, L.ANDSAT-2 RBV, Band LS-2 D-3 t m9 OIJ9Z %a,. %A19m ..0 • -1.1 1 mT m f1 4Z NRD f_ ^q J^ NL J' 9 t r V r 1 r^l z '^ :s 1 a c n W :^ L Y V b r I mm bUm2 IOU - bw&2 N1 I him ^ I^ ^ ^^ f ^- — 1 1 y f — —a 1 — - ^ I - ^ 1 - 1 f ^_ — ' 1 1 1 ^ i^^ •^ ^ 1 Z f 1