THE UN I V E R S I T Y OF MICHIGAN COLLEGE OF ENGINEERING Department of Electrical & Computer Engineering Space Physics Research Laboratory Sounding Rocket Flight Report MUMP 9 and MUMP 10 Prepared on behalf of the.project by H. J. Grassl ORA Project 089020 under contract with: NATIONAL AERONAUTICS AND SPACE ADMINISTRATION GEORGE C. MARSHALL SPACE FLIGHT CENTER CONTRACT NO. NAS5-11073 HUNTSVILLE, ALABAMA administered through: OFFICE OF RESEARCH ADMINISTRATION ANN ARBOR November 1971

TABLE OF CONTENTS Page ACKNOWLEDGMENTS iv LIST OF ILLUSTRATIONS v 1. INTRODUCTION 1 2. GENERAL FLIGHT INFORMATION 2 3. LAUNCH VEHICLE4 4. NOSE CONE 8 5. THE THERMOSPHERE PROBE 12 5.1. Omegatron 12 5.2. Electron Temperature and Density Probe 20 5.3. Support Measurements and Instrumentation 23 5.3.1. Aspect determination system 23 5.3.2. Telemetry 26 5.3.3. Housekeeping monitors 27 6. ANALYSIS OF DATA 29 6.1. Trajectory and Aspect 29 6.2. Ambient N2 Density 32 6.3. Neutral Particle Temperature 42 6.4. Electron Temperature and Density 42 6.5. Geophysical Indices 42 7. REFERENCES 49 iii

ACKNOWLEDGMENTS The MUMP launchings were conducted under Contract No. NAS5-11073. Over one hundred persons contributed to the success of MUMP 9 and MUMP 10; some of the personnel with specific responsibilities are listed below. George C. Marshall Space Flight Center Ballance, J. 0 Experiment Physicist Smith, R. E. Project Scientist Youngblood, W. Experiment Engineer Space Physics Research Laboratory Carignan, G. R. Laboratory Director Taeusch, D. R. Associate Laboratory Director Caldwell, J. R. Electronics Engineer Campbell, B. J. Design Draftsman Cittadini, R. J. Data Reduction Supervisor Foust, E. C. Head Programmer Freed, P. L. Head Technician Kartlick, W. G. Omegatron Technician Kimble, R. G. Telemetry Technician Maurer, J. C. Payload Engineer McCormick, D. L. Machinist Phillips, D. C. Electron Temperature Probe Engineer iv

LIST OF ILLUSTRATIONS Table Page I. Table of Events 3 II. Omegatron Data 16 III. N2 Ambient Density Data 40 IV. Charged Particle Results 46 Figure 1. Nike-Tomahawk with thermosphere probe payload. 5 2. Nike-Tomahawk dimensions, MUMP 9. 6 3. Nike-Tomahawk dimensions, MUMP 10. 7 4. MUMP 9 instrumentation design. 9 5. MUMP 10 instrumentation design. 10 6. Assembly drawing, 8-in. nose cone. 11 7. MUMP 9 system block diagram. 13 8. MUMP 10 system block diagram. 14 9. Omegatron and breakoff configuration. 15 10. Final calibration of the MUMP 9 omegatron. 18 11. Final calibration of the MUMP 10 omegatron. 19 12. Electron temperature and density probe. 21 13. ETDP system timing and output format. 22 14. MUMP 9 minimum angle of attack vs. altitude. 24 15. MUMP 10 minimum angle of attack vs. altitude. 25 v

LIST OF ILLUSTRATIONS (Concluded) Figure Page 16. MUMP 9 sequence of events. 30 17. MUMP 10 sequence of events. 51 18. MUMP 9 omegatron current vs. flight time. 33 19. MUMP 10 omegatron current vs. flight time. 34 20. K(S,a) vs. altitude for MUMP 9. 36 21. K(S,A) vs. altitude for MUMP 10. 37 22. MUMP 9 ambient N2 density vs. altitude. 38 23. MUMP 10 ambient N2 density vs. altitude. 39 24. MUMP 9 neutral particle temperature vs. altitude. 43 25. MUMP 10 neutral particle temperature vs. altitude. 44 26. Charged particle results for MUMP 10. 45 27. Solar flux at 10.7 cm wavelength. 47 28. Three-hour geomagnetic activity index (a ). 48 vi

1. INTRODUCTION The results of the launching of two Marshall-University of Michigan Probes (MUMP 9 and MUMP 10), Nike-Tomahawk sounding rocket payloads, are summarized in this report. The MUMP is similar to the Thermosphere Probe (TP), described by Spencer, Brace, Carignan, Taeusch, and Niemann (1965), which was developed jointly by the Space Physics Research Laboratory (SPRL) of The University of Michigan and the Goddard Space Flight Center, Laboratory for Planetary Atmospheres. The MUMPs were developed by SPRL for the Marshall Space Flight Center, Aero-Astrodynamics Laboratory. The TP is an ejectable instrument package designed for the purpose of studying the variability of the earth's atmospheric parameters in the altitude region between 120 and 350 km. Background information for both the neutral particle and charged particle portions of the experiments, along with a full bibliography, is given by Taeusch, Carignan, Nagy, and Niemann (1968). The MUMP 9 payload included an omegatron mass analyzer, a molecular fluorescence densitometer, a "mini-tilty" filter, and a lunar position sensor. This complement of instruments permitted the determination of the molecular nitrogen density and temperature in the altitude range from approximately 143 to 297 km over Wallops Island, Virginia, during January 1971. The MUMP 10 payload included an omegatron mass analyzer, an electron temperature probe (Spencer, Brace, and Carignan, 1962), a cryogenic densitometer, and a solar position sensor. This complement of instruments permitted the determination of the molecular nitrogen density and temperature and the charged particle density and temperature in the altitude range from approximately 145 to 290 km over Wallops Island, Virginia, during the afternoon preceding the MUMP 9 launch in January 1971. A general description of the payload kinematics, orientation analysis, and the technique for the reduction and analysis of the data is given by Taeusch, Carignan, Niemann, and Nagy (1965) and Carter (1968). The results of the cryogenic and fluorescence density and temperature measurements are the subjects of individual reports and are not covered in this document. 1

2. GENERAL FLIGHT INFORMATION The general flight information for MUMP 9 and MUMP 10 is listed below. Table I gives the flight times and altitudes of significant events which occurred during the flights. Some of these were estimated and are so marked. The others were obtained from the telemetry records and radar trajectory information. Flight: MUMP 9 MUMP 10 Launch Date: 16 January 1971 15 January 1971 Launch Time: 00:55:00.117 GMT 20:30:00.127 GMT Location: Wallops Island, Va. Wallops Island, Va. Lat: 37050'14.915"N Lat: 37050'14.915"N Long: 75029'01. 693"W Long: 75~29'01.693"W Apogee Parameters: Altitude: 297.1 km 289.6 km Horizontal Velocity: 336.7 m/sec 380.1 m/sec Flight Time: 269.0 sec 265.5 sec TP Motion: Tumble Period: 3.116 sec 2.120 sec Roll Rate: -12 deg/sec 21 deg/sec 2

TABLE I TABLE OF EVENTS MUMP 9 MUMP 10 Event Flight Time Altitude Flight Time Altitude (sec) ( km) (sec) (km) Lift-off 0 0 O 1st Stage Burnout 3.7 1.6 (est.) 3.6 1.6 (est.) 2nd State Ignition 11.6 6.4 11.8 6.5 2nd Stage Burnout 21.2 19.7 21.3 19.7 Despin 43.4 (est.) 67.9 (est.) 43.7 (est.) 67.6 (est.) TP Ejection 45.4 72.0 45.7 71.6 Omegatron Breakoff 75.5 128.9 79.9 134.6 Omegatron Filament On 76.7 131.0 81.4 137.1 Peak Altitude 269.0 297.1 265.5 289.6 L.O.S. 503.0 -- 501.0 3

3. LAUNCH VEHICLE The launch vehicles for MUMP 9 and MUMP 10 were two-stage, solid propellant Nike-Tomahawk combinations. The first stage of each vehicle, a Hercules M5El Nike motor, had an average thrust of 49,000 lb and burned for approximately 3.6 sec. The Nike booster, plus adapter, was 145.2 in. long and 16.5 in. in diameter. Its weight unburned was approximately 1525 lb. The sustainer stage, Thiokol's TE416 Tomahawk motor, provided an average thrust of 11,000 lb and burned for about 9 sec. The Tomahawk, 141.4 in. long and 9 in. in diameter, weighed 530 lb unburned. The MUMP 9 payload, which was 95.1 in. long and weighed 163 lb including despin and adapter modules, made the total vehicle 379.4 in long with a gross lift-off weight of 2018 lb. The MUMP 10 payload, which was 89.2 in long and weighed 169 lb including despin and adapter modules, made the total vehicle 375.5 in long with a gross lift-off weight of 2024 lb. The vehicles are illustrated in Figures 1, 2, and 3. Both launch vehicles performed flawlessly. MUMP 9 reached a summit altitude of 297.1 km at 269.0 sec of flight time, and MUMP 10 reached a summit altitude of 289.6 km at 265.5 sec of flight time. 4

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ROCKET NO MUMP 9 8.0 DI A.. PAY L OAD g3.1 (W1 - 9^. 3^ ^1 FIRING B DESPIN SECOND SD TAGE TOMAHAWK 141.1 3 9.4 -- 9" DIA. FIRST STAGE NIKE BOOSTER 145.2 OR DNANCE ITEMS 16.5 DIA. O NOSE CONE OPENING PRIMERS O BREAKOFF LINEAR ACTUATORS O DESPIN INITIATION PRIMERS O SECOND STAGE IGNITER — 59.936- - NIKE BOOSTER IGNITER Figure 2. Nike-Tomahawk dimensions, MUMP 9. 6

ROCKET NO MUMP 10 8.0 DI A. ~ PAY L O A O 89.2 2) - FIRING S DESPIN SECOND STAGE TOMAHAWK 141.1 37 5.5 o- 9" DIA. FIRST STAGE NIKE BOOSTER 145.2 ORDNANCE ITEMS 16.5 DIA. " — ) NOSE SONE OPENING PRIMERS O BREAKOFF LINEAR ACTUATORS ~O DESPIN INITIATION PRIMERS O SECOND STAGE IGNITER 59.936 - Q NIKE BOOSTER IGNITER Figure 3. Nike-Tomahawk dimensions, MUMP 10. 7

4. NOSE CONE Figure 4 is a diagram of the payload of MUMP 9 including the nose cone, the despin mechanism, and the adapter section. Figure 5 is the same for MUMP 10. An assembly drawing of the 8-in. nose cone is given in Figure 6. The MUMP 9 payload was despun at 68 km (43 sec after launch), and the ejection began at 72 km (45 sec after launch), resulting in a tumble period of 3.116 sec. The omegatron breakoff device was removed at 129 km (76 sec after launch), and the omegatron filament was turned on approximately 2 sec later. The MUMP 10 payload was despun at 68 km (44 sec after launch), and the ejection began at 72 km (46 sec after launch), resulting in a tumble period of 2.120 sec. The omegatron breakoff device was removed at 135 km (80 sec after launch), and the omegatron filament was turned on approximately 2 sec later. 8

i50 INC. 9.250 FRANGIBLE RING 28.562 CONE ASS'Y T11. s 1..- - \JI NOSE CONE TIMER 8.00 DIA. — _ F_ —-__-. —- 7 t MIINITILTY FILTER -- j —- |- --- -5 t- THERMOSPHERE PROBE PHOTOMULTIPLER _ _ -o- ELECTRON GUN _ OLECULAR FLUORESCENCE DENSITOMETER AMPLIFIER a CONTROL H.V. POWER SUPPLIES 93.096 ~~93.%.09~~6 |_ __ l H VL.V. POWER SUPPLIES 43.208 i! 50.734 4320 TRANSMITTER DECK BATTERY DECK I_ 7 --- __ _COMMUTATOR DEOK ~ I _) —- -— CONTROL DECK....r. r - LOGIC DECK DECK REGULATOR DECK OSCILLATOR DECK OMES. AMP It OMEG. ADAPTOR F-'1 ---- OMEGATRON _ BREAKOFF HOUSING 7.500 - TUBE HOUSING 5 t —-- UMBILICAL PLUG BASE 2.000 5.125 AFT. SECTION. 125 _' —- _ + TOMAHAWK IGNITION AND DESPIN CIRCUITS 6.625 DESPIN - 9DO DIA. — Figure 4. MUMP 9 instrumentation design. 9

I 5~ INC. 9.250 FRANGIBLE RING 28.562 _ CONE ASS'Y IrT'' \ NOSE CONE TIMER L.j. 8.00 DIA. - -1.781' I, -- BREAKOFF -.-.-.^ = z -*- TTHERMOSPHERE PROBE CRYOGENIC DENSITOMETER 89.219 LANOMUIR PROBE S.S......._ E_ TRANSMITTER DECK BATTERY DECK 46.906. E. S.P. DECK S.C.O. DECK L-__ _ — - --— I COMMUTATOR DECK. -- CONTROL DECK 37.625 -"- " -- LOGIC DECK i_.iii _. _- ---- OSCILLATOR CONTROL DECK REOULATOR DECK OSCILLATOR DECK OEO. AMR BX OMEG. ADAPTOR BREAKOFF 7.5000 L i UMBILICAL PLUG 2000 -- BASE 5.125 - - AFT SECTION -^- _TOMAHAWK IGNITION AND DESPIN CIRCUITS 6.625 I I. * DESPIN 9.00 DIA. Figure 5. MUMP 10 instrumentation design. 10

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.J PULL OFF_.... __ 2 r3 4 SPRL CALIBRATOR SCO S CONTROL LEDEX _ OMEATRON SYSTEM SPACE PHYSICS RES. LAB. 0 a 5 CAL 525KhZ INCLTAGE MCONITORS "^_ --- POWER IOUT 100OOMS D 2 O1 40 KhZ FUNCTION CONTROL FILAMENT CONTROL RAYMOND "1' FI L a BO - COMM TIMER VECTOR TYPE MMO-IIS POIWER CONTROL COE U A c MM ANT Fd OWER~ C0-N f RO~L' _MOLECULAR FLUORE- - COMM EXTERNAL/INTERNAL SCENCE DENSITOMETER TM POWER ON/OFF - HV ON 4 70 KhZ MF ~^"~~~~~ ---— ~~~~~~ —-I,, —. —.~~~~- ~TRANSMITTER TM2. COMM. -4b —-- P COMM. — --.-I-|-|. 7 - 5.4 KhZVECTOR PW — I a W- 3.0 KhZ INTERNAL POWER INITILTY FILTER FJ HIGH ALTITUDE ENG. LAB. 5 30 KhZ MIXER AMP 20-HR-3 CELLS PW 22 KhZ MOPW a 3_C1/OMM!RNG CHANGE -~^comM LUNAR ASPECT -4.5KhZ SPRL "STANDARD" DESIGN 14 Kh - COMMUTATOR I RPS 30 SEGMENT - IO. 5KhZ - PW ~I 0 I 2, 3, 4, 5 CAL Fig~e 7. PPW 9 system block diagram. Figure 7. MUMP 9 system block diagram.

PULL OFFS po2 po3 po4 pol OMEGATRON SYSTEM S PRL i VECTOR amplifier S TS-54 >^ amplifier ~~~~~~~~~~~CALIBRATOR sp —--- — * 52.5KHz ledex ^^ oscillator out/d CALIRATOR 40KHz control filament regulator r0&5 50/50nt - 7. 35KHz gage n mass timer CONTROL LEDEX Mitor voltage monitors RAYMOND OM amp control <S TIMER 13 BREAKOFF,control filament control POWER CONTROL COMMUTATOR 10.5KHz COMM ext. power ELECTROSTATIC PROBE SYSTEM 231.4 m Om 30KHz ESP-D INTERNAL VW 22KHz POWER 19-HR-1 *s _ N^ ADCOLE/SPRL SOLAR --'I4..5c ASPECT ASPECT ^N,^-~XTMR POWE R CYROGENIC VECTOR DENSITOMETER ___ 2 WATT ESPlCOMM/ASPECT POWER 24Q.2mc Figure 8. MUMP 10 system block diagram.

FEED THRU PINCH OFF TUBE m.^ —-ORIFICE BREAK OFF ASSEMBLY Oi ACTUATOR CERAMIC ENVELOPE ----— 1 ANTECHAMBER ENVELOPE - VACUUM SEAL OMEGATRON MAGNET OMEGATRON ADAPTER --'" —-- VACUUM SEAL PROBE HOUSING l EL ELCTROMETER AMPLIFIER DECK EMISSION REGULATOR — & BIAS CONTROL OSCILLATOR DECK AUXILIARY DECK —-- - Figure 9. Omegatron and breakoff configuration. 15

TABLE II OMEGATRON DATA (MUMP 9) Calibration Normalized N2 Sensitivity: 1.46 x 10 A/torr Electrometer Amplifier OUT/S Range Indicator Resistor Gain Bias 12 1-1 o.60 V 1.000 x 1012 -1.01 + 3.02 V 1-2 0.90 V 1.000 x 1012 -1.01 - 1.01 V 1-3 1.21 V 1.000 x 10 -1.01 - 5.03 V 1-4 1.51 V 1.000 x 102 -1.00 - 9.05 V 1-5 1.81 V 1.000 x 1012 -1.00 -13.07 V 1-6 2.11 V 1.000 x 101 -1.00 -17.08 V 1-7 2.41 V 1.000 x 10 -1.01 -21.22 V 10 2-1 3.00 V 6.664 x 010 -1.01 + 3.02 V 2-2 3.30 V 6.664 x 1010 -1.01 - 1.01 V 2-3 3.61 v 6.664 x 10 -1.01 - 5.03 V 2-4 3.91 v 6.664 x 10o -1.00 - 9.05 V 2-5 4.21 V 6.664 x 10 -1.00 -13.07 V 2-6 4.51 V 6.664 x 1010 -1.00 -17.08 V 2-7 4.81 V 6.664 x 10o -1.01 -21.22 V OUT/D Range Indicator Resistor Gain Bias 12 1 — 1.000 x 10 -0.2514 0.0089 V 10 2 — 6.664 x 10 -0.2514 0.0089 V 16

Table II (Concluded) (MUMP 10) Calibration Normalized N Sensitivity: 1.35 x 10 A/torr Electrometer Amplifier OUT/S Range Indicator Resistor Gain Bias 12 1-1 0.50 V 1.000 x 1012 -1.00 + 2.99 V 1-2 0.80 V 1.000 x 102 -1.00 - 1.02 V 1-3 1.10 V 1.000 x 102 -1.00 - 4.99 V 1-4 1.40 V 1.000 x 102 -1.00 - 8.97 V 1-5 1.70 V 1.000 x 102 -1.00 -12.97 V 1-6 2.00 V 1.000 x 102 -1.00 -17.00 V 1-7 2.30 V 1.000 x 10 -1.00 -21.02 V 2-1 2.90 V 6.664 x 10 -1.00 + 2.99 V 10 2-2 3.20 V 6.664 x 10 -1.00 - 1.02 V 10 2-3 3.49 V 6.664 x 10 -1.00 - 4.99 V 2-4 3.79 V 6.664 x 10 -1.00 - 8.97 V 10 2-5 4.09 v 6.664 x 10 -1.00 -12.97 V 10 2-6 4.39 V 6.664 x 10 -1.00 -17.00 V 10 2-7 4.68 V 6.664 x 10 -1.00 -21.02 V OUT/D Range Indicator Resistor Gain Bias 12 1 1.000 x 101 -0.2503 0.0039 V 2 6.664 x 10 -0.2503 0.0039 V 17

s: m - / N r rA m rN2 Em V -I10 2 10 " ______2___ —--------- C, t -IC _ _ _ N R D Y ( PANORMALIZED N/ SENSITIVITYC F 2.341X10. PA RT / CC - AMP 0 _ w iC 7 10 ~09 10'~ 1 12 10= NUMBER DENSIT.34x PART/CC-AMPPART / CC DFigure 10. Final calibration of the MUMP 7 9 10 -2 13 Figure 10. Final calibration of the MUMP 9 omegatron.

=_' ~ I 1,1 " i 111' |1I I I II X 11 I - I III n111 | 11 - I I I'n111 I I I I I'1 -10 cr 3 - ~MUMP 10 IO NORMALIZED N2 SENSITIVITY: ~- - /2.52 x 10 PART/CC-AMP bJ ~ -' N2 RUN OF 10-29-70 0 10 7 Id- 10 2 1 10 |10 10 i Ii0 E10 R 10 10A3 NUMBER DENSITY (PART/CC) Figure 11. Final calibration of the MUMP 10 omegatron.

5.2. ELECTRON TEMPERATURE AND DENSITY PROBE The electron temperature and density probe consists of two cylindrical Langmuir probes placed in the plasma, and an electronics unit which measures the current collected by the probes as they are swept through a series of ramp voltages. A typical Langmuir probe is shown in Figure 12. For MUMP 10 probe 1 is stainless steel and probe 2 is rhodium-plated stainless steel. MUMP 9 did not carry the instrument. The electronics unit consisted of a dc-dc converter, a AV ramp generator, a three-range current detector, and associated logic and control circuits. Timing and sequencing of the various functions are shown in Figure 13. The pertinent system parameters follow. (a) Input Power 2.24 W at 28 V (b) Sensitivity Range 1 20 [A full scale (5 V) Range 2 2.0 pA full scale (5 V) Range 3 0.2 MA full scale (5 V) (c) Ramp Voltage (AV) High AV 80.0 V/sec -3 V to +5 V Low AV 26.7 V/sec -1 V to 1.67 V Period 100.0 msec (d) Output Voltage -0.50 V to +5.80 V Resistance 2000 Q Bias Level 0.50 V (e) System Calibration Calibration occurs every 36 sec for a duration of 600 msec. 20

.022 9.000 15.550 5.800 -.0 — - -.065 PROBE FEED THRU AS PER DWG. A-020-183 Figure 12. Electron temperature and density probe. 21

- O 100 M SEC HI AV RANGE (80V/SEC) +5v^ / ^ ^ y ^ ^; i / /////// //////////17 ~~~~~~~~~LO AV RANGE (26.7 V/SEC) /// AV -_ O.ZA - K3ON N - - - - - - - - DETECTOR 2JUA RANGE 20 4A K2 ON CALIBRATION 300 M SEC COMMON MODE CALIBRATION I MEASUREMENT SEQUENCE 5900 IO M SEC - j THIS SEQUENCE OCCURS ONCE EVIERY 36 SECONDS AT BEGINNING OF HI AV 5 10 10 10 -4 —-- -MILLISECONDS! 2% VOLTS I _ST TUI B IS DC I -. -ZERO - iCROSS COMPUTER 4 PULSE THIS FRAME CHANNEL SYNC| - INDICATES 0.2,11A - -- --- - --- OUTPUT I BIIPULSE I B I BIT 2 BIT'3 IRANGE AND HI BT BIT 2 DETECTOR RELAYS ON BIT 3 AV SLOPE AV MAGNITUDE 0 j^ —- — I- -- I AV SAMPLEI MAGNITUDE (MLOPE) -- - V I - - -.- - 4 - S E C ~ 0 5 V 2 O JU A K 0 8 V / S E C - 3 T 0+ 5 < + - -- - - - \ -- - - - -- --- - 100 M SECt 2% ---- -- -----------— _______ _____ R) +3V - ________ - __ ________________________ 5V 5V 2MA NONE 5V 26.7V/SEC -I TO+1.7 AV RETRACE PULSE - OV | 5V 0 O.2UA K3 +I_3V___ —- -----— ________ —------------ CALIBRATION (K2 OR K3 COMPARATOR OUT 0 II0 0 MODE FOR KI. ACCORDING COMPARATOR OUT ALL ^ RANGES',TO RANGE OV MS2 (5MSEC)(SYNC) CONTROL FF - __~~~I____________________________________ CONTROL FF MS 3 (1OMSEC)BITI SAMPLE MS4 (BIT- SAMPLE) MS5 (AV SAMPLE BIT) Figure 15. ETDP system timing and output format.

5.3. SUPPORT MEASUREMENTS AND INSTRUMENTATION 5.3.1. Aspect Determination System The MUMP 9 payload utilized a lunar sensor designed and built by SPRL which was identical to those used on previous nighttime flights. MUMP 10 included a solar aspect sensor built by Adcole Corporation similar to those used on previous daytime flights. A single-eye system (120 deg field of view) was used rather than the triple-eye (360 deg field of view) of previous flights, and the accompanying electronics were modified accordingly. The attitude of each TP was determined by using the method of referencing the solar (lunar) vector and the velocity vector (Carter, 1968). The resulting minimum angle of attack, determined to an estimated accuracy of ~5 deg, is plotted versus altitude in Figures 14 and 15. 23

300 DOWNLEG 280 / UPLEG 260 240 W 220 -r..J MUMP 9 200 16 JANUARY 1971.| ( 00: 55 GMT -| |~ ~ WALLOPS IS., VA. 180 160 0 10 20 30 40 ANGLE OF ATTACK (DEG) Figure 14. MUMP 9 minimum angle of attack vs. altitude. 24

300 MUMP 10 15 JANUARY 1971 280 -20:30 GMT WALLOPS IS., VA. 260 240 _ 220 ~ \'I 00 180 UPLEG DOWNLEG 160 140 -20 -18 -16 -14 -12 -10 -8 -6 -4 -2 0 ANGLE OF ATTACK (DEG) Figure 15. MUMP 10 minimum angle of attack vs. altitude. 25

5.3.2. Telemetry The MUMP 9 payload data were transmitted in real time by a ten-channel PAM/FM/FM telemetry system at 240.2 MHz with a nominal output of 2.5 W. The MUMP 10 data were transmitted in real time by a seven-channel PAM/FM/FM telemetry system at 244.3 MHz, also with a nominal output of 2.5 W. The subcarrier channels are outlined below. MUMP 9 MUMP 10 Transmitter: TR-2125 TRPT-251-RAO1 (Serial No. 981) (Serial No. 2499) Power Amplifier: TRFP-2V (Serial No. 458) Mixer Amplifier: MMA-12 TA-58A (Serial No. 11847) (Serial No. 1162) Subcarrier Channels: MMO-11 TS-54 MUMP 9 IRIG Serial Center Low Pass Band No. Frequency Filter Used 18 16762 70 kHz MFD TM1 790 CD 17 16594 52.5 kHz OM OUT/S 110 CD 16 19165 40 kHz OM OUT/D 110 CD 15 16371 30 kHz MTF 450 CD 14 16300 22 kHz MTF Range 330 CD 13 15285 14.5 kHz Aspect 330 CD 12 18736 10.5 kHz Commutator 160 CD 11 15945 7.35 kHz OM Range 110 CD 10 15844 5.4 kHz MFD TM2 81 CD 8 24375 3 kHz MFD Beam 45 CD 26

MUMP 10 IRIG Serial Center Low Pass Band No. Frequency Filter Used 17 1738-5 52.5 kHz OM OUT/S 110 CD 16 1063-25 40 kHz OM OUT/D 110 CD 15 1890-25 50 kHz ESP-D 450 CD 14 3221-25 22 kHz ESP-F 330 CD 13 3460-25 14.5 kHz Aspect 330 CD 12 1685-5 10.5 kHz Commutator 160 CD 11 1567 7.35 kHz OM Range 110 CD Instrumentation power requirements for MUMP 9 totaled approximately 83 W, supplied by a Yardney HR-3 Silvercell battery pack of a nominal 29 V output. For MUMP 10 the total power requirement was approximately 67 W, supplied by a Yardney HR-1 Silvercell battery pack of a nominal 28 V output. 53.35 Housekeeping Monitors Outputs from various monitors throughout the instrumentation provided information bearing on the operations of the electronic components during the flights. These outputs were fed to thirty segment commutators which ran at one rps. The commutator assignments were as follows: 27

COMMUTATOR FORMAT FOR MUMP 9 COMMUTATOR FORMAT FOR MUMP 10 Segment Segment Segment Assignment Segment Segment Assignment No., No.. 1 1 V Calibration 1 Omegatron Range 2 OUT/D 2 OUT/D 3 Omegatron Range 3 Filament Voltage 4 Open 4 Emission Current Monitor 5 MFD Telemetry 1 (more sensitive) 5 Omegatron Bias Voltage Monitor 6 MFD Telemetry 2 (less sensitive) 6 RF Amplitude 7 MFD Emission Current Monitor 7 CD Regulated Voltage 8 MFD High Voltage Monitor 8 Internal Pressure Monitor 9 MT +15 Voltage Monitor 9 Thermistor - Gauge Temperature 10 MT -15 Voltage Monitor 10 Thermistor - Amplifier Temperature 11 MT + 5 Voltage Monitor 11 Thermistor - Transmitter Temperature 12 MT High Voltage Photomultiplier 12 Thermistor - CD Temperature oo 13 MT High Voltage Monitor 13 Thermistor - Spare 14 Thermistor - Transmitter Temperature 14 Battery Voltage Monitor 15 Thermistor - High Voltage Temperature 15 Open 16 Thermistor - Photomultiplier Temperature 16 Open 17 Open 17 Open 18 Internal Pressure Monitor 18 Open 19 Thermistor - Gauge Temperature 19 Open 20 Thermistor - Amplifier Temperature 20 Open 21 Open 21 Open 22 Open 22 Open 23 Bias Voltage Monitor 23 Open 24 Filament Monitor 24 0 V Calibration 25 RF Voltage Monitor 25 1 V Calibration 26 Emission Current Monitor 26 2 V Calibration 27 Battery Voltage Monitor 27 3 V Calibration 28 0 V Calibration 28 4 V Calibration 29 5 V Calibration 29 5 V Calibration 30 5 V Calibration 50 5 V Calibration

6. ANALYSIS OF DATA The telemetered data were recorded on magnetic tape at the Wallops Island Main Base and the Goddard Space Flight Center Station A ground station facilities. Appropriate paper records were made from the magnetic masters, facilitating "quick look" evaluations. The aspect data were reduced to engineering parameters from paper records. The omegatron and housekeeping data were reduced by computer techniques from the magnetic tapes. 6.1. TRAJECTORY AND ASPECT The position and velocity data used to determine aspect, ambient N2 density, and ambient temperature as a function of time and altitude were obtained by fitting a smooth theoretical trajectory to the radar data (FPQ-6 and FPS-16 for MUMP 9; FPQ-6, FPS-16, and MPS-19 for MUMP 10). The theoretical trajectory is programmed for computer solution similar to that described by Parker (1962). The analysis of minimum angle of attack (%min) as described by Carter (1968) is also incorporated in the program. The output of the computer furnishes CAmin altitude, and velocity as a function of time. Plots of amin versus altitude have already been given in Figures 14 and 15. Figures 16 and 17 show the occurrence of significant events during the flights. 29

ALTITUDE (KM) Cml -0 (it 0 ( 01 o o 0 0 o 0 0 NIKE BURNOUT 3.7 TOMAHAWK IGNITION 11.6 TOMAHAWK BURNOUT 21.2 DESPIN 43.4 ^^^^^: — TP EJECTION 45.4 H OM FILAMENT ON 76.7 ( — $ -1 (D 269.0 00 0 (1D (*D (D O) 0 U)

ALTITUDE (KM) -_- IN) r\) o< oI pe o e o e o eo 0 NIKE BURNOUT 3.6 TOMAHAWK IGNITION 11.8 TOMAHAWK BURNOUT 21.3 DESPIN 43.7 TP EJECTION 45.7 OM BREAKOFF 79.9 _ __ V"B^ OM FILAMENT ON 81.4 -- 0 --- \m o 0 0 ('1) ~T -- 0'rl l l 0.

6.2. AMBIENT N2 DENSITY The neutral molecular nitrogen density was determined from the measured gauge partial pressure as described by Spencer, et al. (1965, 1966), using the basic relationship: An.u. n =....K(S a 2 4 V cos a. where n = ambient N number density a 2 An. = maximum minus minimum gauge number density during one tumble, A x AI, where A is the sensitivity of the gauge ui = V2KT./m, most probable thermal speed of particles inside gauge T. = gauge wall temperature V = vehicle velocity with respect to the earth ca. minimum angle of attack for one tumble min K( S o) = the reciprocal of the normalized transmission probability as defined by Ballance (1967), referred to as the geometry correction factor. AI, the difference between the maximum (peak) omegatron gauge current and the minimum (background) gauge current versus flight time is shown in Figures 18 and 19. The background current is the result of the outgassing of the gauge walls, and the inside density is due to atmospheric particles which have enough translational energy to overtake the payload and enter the gauge. The outgassing component is assumed constant for one tumble and affects both the peak reading and the background reading, and, therefore, does not affect the difference. From calibration data obtained by standard techniques, the inside number density, Ani, is computed for the measured current. By using the measured gauge wall temperature, the most probable thermal speed of the particles inside the gauge, ui, is computed. The uncertainty in this measurement is believed to be about +2% absolute. V, the vehicle velocity with respect to the earth is obtained from the trajectory curve fitting described previously and is believed to be better than +1% absolute. 32

loll l1 —-- I I I~~0It"~~~ MUMP 9 ~* ~ 16 JANUARY 1971 ~* 00:55 GMT *. WALLOP IS.,VA. ^ ~10"~.~ **~0 0 o - * 0 z * z:_ mI10i o.' I I z. (PEAK - BK6) _ / -I- -. * — ~xxx x. X X, {xxXX BKG),X X I0e O 100 200 300 400 500 600 FLIGHT TIME (SEC) Figure 18. MUMP 9 omegatron current vs. flight time. S Figure l8. MUMP 9 megatron current s.fihtme 55

10It MUMP 10 *. 15 JANUARY 1971 _ * 20:30 GMT WALLOPS IS.,VA. * 0 * 0 o10: *. 0* -- S z J = *; -(PEAK-BKO) I"" w _ _C - W.. -,- ( 8K Z: \ 0!* / = V z ~~~10' k / XOm * " XX x0x O 100 200 300 400 500 600 - FLIGHT TIME (SEC) Figure 19. 0MMP 10 omegatron current vs. flight time. FLGH TIME (SEC Fiur 1. UP 0 meato crrntvs lihttie

Cos omin is obtained from the aspect analysis described by Carter (1968). Since the uncertainty in cos onin depends upon amin, for any given uncertainty in Omin, each particular case and altitude range must be considered separately. Figures 14 and 15 show that the minimum angle of attack for the upleg is generally less than 10 degrees, so with an assumed maximum uncertainty in omin of ~5 degrees, the resulting uncertainty in cos omin is less than +2%. The data for low angle of attack were used as control data. K(Soc), the geometry correction factor versus altitude, is shown in Figures 20 and 21. As can be seen, the maximum correction is about 12%, or K(So,a) =.88 at about 145 km altitude for the upleg data. The correction factor, determined from empirical and theoretical studies, is believed known to better than 2%. The resulting ambient N2 number density, obtained from the measured quantities described above, is shown in Figures 22 and 23 and is tabulated in Table III. The uncertainty in the ambient density due to the combined uncertainties in the measured quantities is thought to be 10% relative and 25% absolute. 35

300 MUMP 9 16 JANUARY 1971 280 00:55 GMT WALLOPS IS., VA. 260 240 -220.J -200 // UPLEG DOWNLEG 180 160 140 --.88.90.92.94.96.98 GEOMETRY CORRECTION FACTOR Figure 20. K( So,o) vs. altitude for MUMP 9. 36

300 MUMP 10 15 JANUARY 1971 20:30 GMT 280 WALLOPS IS., VA. 260 240 -220 200/ 180 160 / UPLEG DOWNLEG 140.88.90.92.94.96.98 1.00 GEOMETRY CORRECTION FACTOR Figure 21. K(So,X) vs. altitude for MUMP 10. 57

34 MUMP 9 16 JANUARY 1971 320 00:55 GMT WALLOPS IS., VA. 280 260- i240 co - Q[: -2 180 160 140 120 107 108 09 100 0" AMBIENT N2 DENSITY (PART/CC) Figure 22. MUMP 9 ambient N2 density vs. altitude.

340 -MUMP 10 15 JANUARY 1971 320 -20:30 GMT WALLOPS IS., VA. 300 280 260 2240 w220 200 - < 180 160 140 120 I,o Io 1 I 111 I I I 111o'~ 7 8 0 10 10 10 10 10 AMBIENT N2 DENSITY (PART/CC) Figure 23. MUMP 10 ambient N2 density vs. altitude.

Table III N2 AMBIENT DENSITY DATA MUMP 9 16 January 1971 00:55 GMT 15 January 1971 19:55 EST Wallops Island, Virginia Altitude Temperature Density (km) (~K) (part/cc) 145.5 632 4.11 x 1010 145 644 3.75 150 688 2.78 155 729 2.10 160 769 1.61 165 804 1.26 170 837 1.00 x 10 175 861 8.10 x 10 180 881 6.62 185 895 5.46 190 904 4.55 195 910 3.81 200 914 3.20 205 915 2.70 210 917 2.28 215 918 1.92 220 920 1.62 225 921 1.37 250 923 1.16 x 108 235 923 9.78 x 10 240 924 8.27 245 925 7.00 250 926 5.93 255 926 5.02 260 926 4.25 265 927 3.60 270 927 3.05 275 927 2.59 280 928 2.20 285 928 1.86 290 928 1.58 295 928 1.34 297 928 1.26 x 10 Fit Parameters: T = 928.17~K 00 T = 629.98~K at 145 km -8 P, = 1.29 x 10 torr b C = 4.80 x 10-2 40

TABLE III (Concluded) MUMP 10 15 January 1971 20:30 GMT 15:50 EST Wallops Island, Virginia Altitude Temperature Density (km) (~K) (part/cc) 145 651 4.69 x 10 150 686 3.51 155 719 2.68 160 751 2.07 165 782 1.62 170 811 1.28 175 839 1.03 x 109 180 866 8.31 x 10 185 890 6.76 190 912 5.54 195 932 4.57 200 950 3.80 205 966 3.17 210 982 2.66 215 996 2.24 220 1009 1.90 225 1020 1.62 230 1031 1.38 235 1041 1.18 240 1049 1.01 x 108 245 1058 8.64 x 10 250 1065 7.43 255 1072 6.40 260 1078 5.53 265 1084 4.77 270 1089 4.13 275 1094 3.58 280 1098 3.10 285 1101 2.69 289.6 1104 2.39 x 10 Fit Parameters: T = 1143.4~K T = 779.84~K at 165 km Pb = 2.6788 x 10-8 torr a = 1.8051 x 10-2 41

6.3. NEUTRAL PARTICLE TEMPERATURE The ambient temperatures shown in Figures 24 and 25 and tabulated in Table III were obtained by integrating the hydrostatic equation using the measured N2 density profile to obtain a partial pressure profile, and by relating the known density and pressure to the temperature through the ideal gas law. In this procedure the assumptions of hydrostatic equilibrium and perfect gas behavior are implicit. It can be shown that the density integral is stable and highly convergent when carried out in the direction of increasing density. The pressure or temperature at the initial (upper) boundary of integration is determined analytically by means of a least squares fitting procedure using a fitting function based on the empirical expression for the temperature profile given by Jacchia (1964), and more particularly by Walker (1965). The procedure is described in detail by Simmons (1969). The fit parameters listed in Table III are the apparent exospheric temperature (TI), the reference temperature at the lower boundary (To), the apparent N2 partial pressure at the upper boundary (Pb), and an estimate of the exponential model shape factor (a). 6.4. ELECTRON TEMPERATURE AND DENSITY The cylindrical Langmuir probe technique used in MUMP 10 has been described a number of times before (e.g., Spencer, et al., 1965; Taeusch, et al., 1968), and will not be discussed here. The charged particle results for MUMP 10 are shown in Figure 26 and tabulated in Table IV. MUMP 9 did not include the instrument. 6.5. GEOPHYSICAL INDICES The 10.7 cm solar flux (F10.7) and the geomagnetic activity indices (ap) for the appropriate periods are shown in Figures 27 and 28. 42

320 MUMP 9 300 - 16 JANUAF Y 1971 00:55 GMT WALLOPS IS., VA. 280 260 240 220 - 200 180 160 140 600 700 800 900 1000 TEMPERATURE (OK) Figure 24. MUMP 9 neutral particle temperature vs. altitude. 43

300 MUMP 10 15 JANUARY 1971 20:30 GMT 280 WALLOPS IS., VA. 260 240 2 I/ 220 C / i — 200 180 160 140 700 800 900 1000 1100 TEMPERATURE (~K) Figure 25. MUMP 10 neutral particle temperature vs. altitude. 44

11I1 I11 I111 I I 1111 I 1 I11 III il IIIm l- 111111 MUMP 10 15 JANUARY 1971 a2030 GMT WALLOPS IS., VA. 250 -200 150 500 51o00 100 150 2010 10- 10 TEMPERATURE (K) ELECTRON DENSITY (electrons/mn Figure 26. Charged particle results for MUMP 10.

TABLE IV CHARGED PARTICLE RESULTS MUMP 10 15 January 1971 20:30 GMT Wallops Island, Virginia Altitude Te Ne (km) ( ~K) (electrons/m ) 90 2.95 x 1010 100 8.00 x 1010 110 1.70 x 10 120 1.71 150 1.82 140 1065 1.67 150 1203 1.92 160 1522 2.38 170 1424 2.99 180 1516 3.85 190 1597 5.03 200 1666 6.82 210 1721 8.90 x 1012 220 1760 1.09 x 10 230 1788 1.24 240 1808 1.37 x 10 250 1820 260 1840 270 1865 280 1894 289.6 1923 46

220| Wb1. T70- FEB. 71 200 180 160 L- 140 120 O o0 100 M M from Solar Geophysical Data (prompt reports), No. 319, Part 1, U.S. Department of Commerce OI-OCT 70 01-NOV.70 OI-DEC.70 OI-JAN.71 OI-FEB.71 Figure 27. Solar flux at 10.7 cm wavelength. 47

18 15 JANUARY 1971 WALLOPS IS., VA. 16 A = 8 from Solar Geophysical Data (prompt reports), No. 319, Part 1, U.S. Department of Commerce MUMP 9 12 IO Pso I MUMP 10 8 5 3 2 2 0 3 6 9 12 15 18 21 24 3 15 JANUARY 1971 (GMT TIME) Figure 28. Three-hour geomagnetic activity index (ap). 48

7. REFERENCES Ballance, James 0., An Analysis of the Molecular Kinetics of the Thermosphere Probe, George C. Marshall Space Flight Center, NASA Technical Memorandum, NASA TM X-53641, July 31, 1967. Carter, M. F., The Attitude of the Thermosphere Probe, University of Michigan Scientific Report 07065-4-S, April 1968. Jacchia, L. G., Static Diffusion Models of the Upper Atmosphere with Empirical Temperature Profiles, Research in Space Science, Smithsonian Astrophysical Observatory Special Report No. 170, 1964. Niemann, H. B., and Kennedy, B. C., "An Omegatron Mass Spectrometer for Partial Pressure Measurements in Upper Atmosphere," Review of Scientific Instruments, 37, No. 6, 722, 1966. Parker, L. T., Jr., A Mass Point Trajectory Program for the DCD 1604 Computer, Technical Document Report AFSW-TDR-49, Air Force Special Weapons Center, Kirtland Air Force Base, New Mexico, August 1962. Simmons, R. W., NASA 18.49 Thermosphere Probe Experiment, University of Michigan Sounding Rocket Flight Report 07065-9-R, May 1969. Spencer, N. W., Brace, L. H., and Carignan, G. R., "Electron Temperature Evidence for Nonthermal Equilibrium in the Icnosphere," Journal of Geophysical Research, 67, 151-175, 1962. Spencer, N. W., Brace, L. H., Carignan, G. R., Taeusch, D. R., and Niemann, H. B., "Electron and Molecular Nitrogen Temperature and Density in the Thermosphere," Journal of Geophysical Research, 70, 2665-2698, 1965. Spencer, N. W., Taeusch, D. R., and Carignan, G. R., N2 Temperature and Density Data for the 150 to 300 Km Region and Their Implications, Goddard Space Flight Center, NASA Technical Note X-620-66-5, December 1965. Taeusch, D. R., Carignan, G. R., Nagy, A. F., and Niemann, H. B., Diurnal Survey of the Thermosphere (Final Report), NASA Contractor Report CR61481, NASA-George C. Marshall Space Flight Center, Huntsville, Alabama, November 1968. 49

7. REFERENCES (Concluded) Taeusch, D. R., Carignan, G. R., Niemann, H. B., and Nagy, A. F., The Thermosphere Probe Experiment, University of Michigan Rocket Report 07065-1-S, March 1965. Walker, J. C. G., "Analytic Representation of Upper Atmosphere Densities Based on Jacchia's Static Diffusion Models," Journal of Atmospheric Sciences, 22, No. 4, 462-463, July 1965. 50

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