Seventeen: June 1997

 https://welib.org/md5/3def9ccc7ba20150f24a78f2efba622c

Spaceflight: January 1997

 https://welib.org/md5/418a57a046f1311957f7fd38b62fc089

Club Management: January-February 1997

 https://welib.org/md5/04e11fdb1bfef9edcf769ddbbe2702d3

Kosmos 474

  1972-008A

---

The second 11F691 Zenit-4M mission of 1972 was Kosmos-474. It flew a 13 day mission from Baikonur in Feb 1972.

Kosmos-474
Date	Time	Event	Orbit
1972 Feb 16	0930:00	Launch by 11A57	KB
	0934	Blok-I burn
	0938	Blok-I sep
1972 Feb 17	0919		89.79 212 x 315 x 65.0
1972 Feb 17	0930		89.79 213 x 317 x 65.0 (RAE)
		Lower perigee
	1816		89.49 177 x 321 x 65.0
1972 Feb 21	1316		89.45 177 x 317 x 65.00
		Lower apogee
1972 Feb 22	0539		89.08 176 x 281 x 65.0
1972 Feb 27	2337		88.91 176 x 264 x 65.0
1972 Feb 27		Engine sep
1972 Feb 29	0640?	Retrofire
	0650?	PO sep
	0655?	Entry
	0711?	Landed after 12.9d

Aviation Week: February 17,1997

 https://welib.org/md5/43f29791b79a72db4f211487697a9efd

Pioneer 8

  1967-123A

---

Pioneer VIII was launched at 1408 on 1967 Dec 13 by Delta E1 from Kennedy. The Delta separated at 1438:44 and the FW4D firead at 1439:29 placing Pioneer VIII in solar orbit. Pioneer VIII was still working in 1996.

Pioneer 8
Date	Time	Event	Orbit
1967 Dec 13	1408:00	Launch by Delta E	CK LC17B
	1408:42	T+0:42 SRM off
	1409:10	T+1:10 SRM sep
	1410:29	T+2:29 Thor S/N 20219 MECO 100 km	-5397 x 262
	1410:33	T+2:33 Delta S/N 20218 burn 6:21
	1416:56	T+8:56 Delta SECO	305 x 494 x 32.9
	1438:44	T+30:44 Delta sep
	1438:58	T+30:58 FW4D S/N 2226-5 burn 34s
	1439:28	T+31:28 FW4D burnout	485 x -4788696 x 32.89
	1439:44	T+31:44 TTS sep from Delta
	1440:28?	FW4D sep
1968 Jan 16		Solar orbit	0.9892 x 1.0880 AU x 0.06 deg, 386.6d
1996 Aug 22		Successful contact on backup TWT

Kosmos 297

  1969-076A

---

Zenit-4 No. 72 was launched in Sep 1969 from Plesetsk, overlapping with the previous flight.

Kosmos-297
Date	Time	Event	Orbit
1969 Sep 2	1100:01	Launch by 11A57	PL
	1104	Blok-I burn
	1109	Blok-I sep
	1517		89.68 209 x 308 x 72.83
1969 Sep 5	1900		89.62 203 x 307 x 72.89
1969 Sep 9	0241		89.56 202 x 303 x 72.89
1969 Sep 10	0702?	Retrofire
	0726?	Landed after 7.84d

Navstar 20

 1990-025A

---

Navstar SVN 20 (USA 54) was launched on 1990 Mar 26 into plane B-2.

Navstar 20
Date	Time	Event	Orbit
1990 Mar 26	0245:01	Launch by Delta II 6925	CC LC17A
		T+0:56 SRM 1-3,7-9 out
		T+1:01 SRM 4-6 on
		T+1:02 SRM 1-3 sep
		T+1:03 SRM 7-9 sep
		T+1:57 SRM 4-6 off
		T+2:02 SRM 4-6 sep
		T+4:25 MECO
		T+4:31 VECO
		T+4:33 Stage 1 sep
	0249	Stage 2 TIG (T+4:38)
	0249	Fairing sep (T+4:50)
	0256	SECO-1 (T+11:37)	175 x 186? x 35.66?
		T+20:55 spinup
	0305	T+20:58 Delta sep
	0306	T+21:35 TES
	0308	T+23:02 TECO	355.32 171 x 20308 x 37.7
	0309	T+24:55 Stage 3 sep
	0309	T+24:57 Yo weight
1990 Mar 26	0348?	Delta depletion	91.75 182 x 537 x 30.23
1990 Mar 28	0930		354.69 169 x 20270 x 37.56
1990 Mar 29	0446?	Star 37XFP burn
1990 Mar 29	1604		707.61 19766 x 20085 x 54.91
1990 Apr 1	1424		716.16 20060 x 20214 x 55.08
1990 Apr 2	0321		716.00 20059 x 20207 x 55.05
1990 Apr 6	0224		717.80 20092 x 20267 x 55.1

The Language of Love

https://welib.org/md5/db9ce7b84668c58d5efd856040335b64

Journal of the British Interplanetary Society: January 1997

 https://welib.org/md5/36620bffec7533bff4dae0b270b167cc

Kopernikus 1

 1989-041B

---

The Deutsche Fernmeldesatelliten System (DFS) was operated by DBP Telekom. The satellites used a Spacebus 100 bus for German domestic TV relay and communications. DFS 1 was also called Kopernikus 1. Launch mass was 1415 kg, BOL mass 850 kg, and dry mass 645 kg. DFS used a 937 adapter. Stage 3 was 1262 kg (may include 308 kg of jettisoned ullage rocket) dry plus 1294 kg for VEB, Spelda, adapters and residuals. VEB was 534 kg. Fairing was 759 kg.

Total V31 payload 4428 kg.

In Aug 1990 control was given to DBP Telekom/Usingen from GSOC.

DFS 1
Date	Time	Event	Orbit
1989 Jun 5	2237:15	Launch by Ariane 44L V31	CSG ELA2
		T+2:30 PAL sep
		T+3:32 St 1 sep
		T+3:34 St 2 MES
		T+4:21 Fairing sep
		T+5:44 St 2 sep
	2243:03	T+5:48 St 3 MES
	2255:08	T+17:51 St 3 MECO
	2257:38	T+20:23 Superbird sep
	2259:48	T+22:33 Spelda sep
	2302:20	T+25:05 DFS sep
		T+25:10 H10 avoidance	632.72 214 x 35856 x 6.7
1989 Jun 6	0500?	Apo 1
	0930?	Peri 1
	1500?	Apo 2
	2000?	Peri 2
1989 Jun 7	0200?	Apo 3
	0630?	Peri 3
	1200?	Apo 4
	1200?	LAM-1, Apo 4
1989 Jun 9?		LAM-2, Apo 7
1989 Jun 11?		LAM-3, Apo 9
1989 Jun 11			1434.80 35645 x 35877 x 0.2 GEO 22.4E+0.3E
1989 Jun 25			1436.07 35765 x 35806 x 0.1 GEO 26.0E
1989 Jul 8			1436.08 35777 x 35795 x 0.1 GEO 23.5E
1989 Sep 18			1435.95 35757 x 35809 x 0.0 GEO 23.9E
1991 Dec 11			1436.04 35756 x 35814 x 0.0 GEO 23.5E
1993 Feb 2			1436.03 35772 x 35798 x 0.1 GEO 23.6E
1993 Feb 9		mv out
1993 Feb 27		mv in
1993 Mar 27			1436.02 35730 x 35839 x 0.0 GEO 33.3E
1995 Jul 22			1436.02 35770 x 35799 x 0.1 GEO 33.5E
1995 Dec 13			1436.13 35768 x 35806 x 0.1 GEO 32.9E
1995 Dec		Orbit lowered
1995 Dec 14			1433.41 35663 x 35805 x 0.1 GEO 33.6E+0.7E
1995 Dec 21			1430.59 35643 x 35714 x 0.1 GEO 39.7E+1.3E

Booklist: February 15,1997

 https://welib.org/md5/3609736272fe9c2d83c8f11d1cf66426

Kosmos 1267

 1981-039A

---

The second full TKS test flight was the first to dock with a Salyut station. The VA was recovered prior to the docking on May 24. The TKS remained docked to Salyut-6 and was used to deorbit it in 1982.

Kosmos-1267
Date	Time	Event	Orbit
1981 Apr 25	0201	Launch by Proton	KB
	0210	Stage 3 MECO
	0210	Stage 3 sep
1981 Apr 25			88.99 191 x 257 x 51.6
1981 Apr 27			254x273x51.6 from 188x261
1981 May 3			257x278x51.6 from 250x266
1981 May 8			252x294x51.6 from 252x266
1981 May 8-9			267x278x51.6 from 252x294
1981 May 16			264x286x51.6 from 259x269
1981 May 24
	1250	Eq cross at 20E
	1325	Orientation maneuver
	1407?	VA sep
	1410?	Deorbit
	1420?	BSO sep
	1431?	Entry
	1510?	Landed
1981 May 27			305x316x51.6 from 254x274
1981 Jun 6			299x311x51.6 from 303x315
1981 Jun 16			90.59 297 x 309 x 51.6
1981 Jun 18			91.52 340 x 357 x 51.6
1981 Jun 19			91.57 340 x 362 x 51.6
1981 Jun 19	0652	Docked with Salyut-6
1981 Oct 3		Test burn
1982 Jul 28			90.94 318 x 323 x 51.6
	0915?	Lower perigee
1982 Jul 29			89.95 222 x 321 x 51.6
1982 Jul 29		Deorbited, docked to Salyut-6
	0940?	Deorbit
	1000?	Entry
	1015?	Impact

Apple

 1981-057B

---

The APPLE (Ariane Passenger Payload Experiment) was India's first experimental comsat, a bridge between the ATS-6 experiments and the Insat series. One of the two solar panels failed to deploy but the satellite was successfully used for communications experiments.

Apple
Date	Time	Event	Orbit
1981 Jun 19	1233	Launch by Ariane LO3	CSG ELA1
		Stage 1 sep
	1235:30	Stage 2 TIG
	1237:25	Fairing sep
	1238:00	Stage 3 burn
	1247	EOI
	1249:18	CAT/Apple sep from H8
	1249:37	T+16:38 Meteosat/MTO sep from Apple
	1250:18	T+17:08? CAT sep from Apple
1981 Jun 20			635.56 200 x 35997 x 10.5
1981 Jun 21	2243:16	AKM fired by SHAR	GEO 2E dr
1981 Jun 22		Solar panels: 1 deployed, 1 failed
1981 Jun 22			1436.31 35579 x 36009 x 1.20 (Falworth)
1981 Jun		TCM
1981 Jun		TCM
1981 Jun		Second panel deployed
1981 Jul 16		On station	GEO 102E
1981 Jul 22		Telecom experiments start
1981 Aug			GEO 105E
1982?		end of regular ops
1983 Jan 27			1439.42 35746 x 35956 x 0.3 GEO 47.6W+0.8W
1983 Jun		Drifting	GEO 114E+0.3/d
1983 Sep 15			1439.49 35750 x 35955 x 0.9 GEO 140.1E+0.8W
1983 Sep 20		Decommissioned
1988 Apr 18			1439.30 35751 x 35947 x 5.1 GEO 138.6E+0.8W

SCATHA

 1979-007A

---

The Spacecraft Charging At High Altitudes (SCATHA) project, satellite P78-2, was launched into an elliptical synchronous orbit in Jan 1979. The spacecraft was built by Martin Marietta and operated by USAF Sunnyvale AFSCF.

SCATHA was spin-stabilized at 1 rpm. Initially SCATHA had its spin axis in the orbit plane, requiring frequent attitude maneuvers to keep the solar panels pointing at the Sun. When fuel ran low the spin axis was reoriented to ecliptic normal. This caused nutation of the satellite. AOCS propulsion was a hydrazine system with a 22N thruster and three 1N thrusters. The satellite had 10 kg of hydrazine at beginning of life; 5 kg was used in the nominal mission, 0.1 kg in th ecliptic-normal phase, and 1.5 kg in the termination phase.

Mission control was by TSC-1 (Test Support Complex 1) under Vehicles Operations-F at the CSTC (Consolidated Space Test Center) in Sunnyvale.

SCATHA
Date	Time	Event	Orbit
1979 Jan 30	2142	Launch by Delta 2914	Canaveral LC17
		T+3:48 MECO
		T+3:56 St 1 sep
		T+4:01 SES-1 4:54
		Fairing
	2150	T+8:55 SECO-1	189 x 869 x 28.6
	2204	T+22:35? St 2 sep
	2205	T+23:20? TES 43s
	2206	T+24:03? TECO	185 x 43903 x 27.4
	2206	Star 37 sep from P78-2
1979 Jan 31	0500?	Apo 1
	1800?	Apo 2
1979 Feb 1	0700?	Apo 3
1979 Feb 1	0853		781.23 180 x 43260 x 27.3
	2000?	Apo 4
1979 Feb 2	0900?	Apo 5
	2200?	Apo 6
1979 Feb 2	2144	AIM burn at 6th apo, 32s burn	1416.2 27543 x 43251 x 7.8
1979 Feb 2		AIM ejected
1979 Feb 5		final orbital burns
1979 Mar 1			1416.21 27580 x 43212 x 7.9
1979 Mar 9		E field antennae out
1982 Sep 22		Arcing events
1984 Aug 1			1417.10 27737 x 43090 x 4.3
1987 Jan 15		Reorienting to ecliptic normal
1987 Feb 4		end of reorientation burns
1987 May?		Transmitter 2 power decrease
1988 May 21			1415.65 28399 x 42371 x 5.8
1990 May 20		Transmitter 1 failed
1991 Jan 1		Orbit raise
1991 May 24		Final attitude maneuver
1991 May 28		end of ops
1991 Aug 6			1418.32 28327 x 42548 x 8.2
1993 Mar 24			1418.32 28114 x 42761 x 9.6

Navstar 10

 1984-097A

---

Navstar 10 was launched on 1984 Sep 8 into the A plane using an Atlas E and SGS-II upper stage. It was removed from operational service in Nov 1995, the last of the test constellation to be retired.

Navstar 10
Date	Time	Event	Orbit
1984 Sep 8	2141	Launch by Atlas E/SGS-II	V SLC3
	2143	T+2:04 Booster sep
		T+2:24 Fairing sep
		T+5:21 MECO
		T+6:00? Atlas sep
		T+6:21? Star 48 burn
	2148	T+7:46? Star 48 burnout
	2148	T+7:46? Star 48 sep
	2148	T+7:50? SGS upper Star 48 burn
	2150	T+9:15? Star 48 burnout
	2152	T+11m Star 48 sep
			553 x 20789 x 63.2
1984 Sep 9			369.20 552 x 20786 x 63.2
1984 Sep 10	1332?	Star 27 burn	718.0 19970 x 20420 x 63.3
1984 Sep 16		Despin
1984 Oct 3		In service
1990		Operating on Cs clock (A-1)
1995 Nov 18		end of ops

Clementine

 1994-004A

---

Formally known as the Deep Space Program Science Experiment (DSPSE), the Ballistic Missile Defense Organization's first space probe was known as Clementine. Lawrence Livermore National Lab (LLNL) provided sensors for this BMDO mission to expose advanced sensors to high radiation dosage; the probe was built by NRL and operated by NRL's Naval Center for Space Technology (NCST).

The probe had a dry mass of 183 kg, with 231 kg of propellant giving a mass of 414 kg after ISA separated. With the kick motor, the ISA and the launch adapter total launch mass was 1687 kg. Clementine was 1.1m in diameter and 1.8m high.

The initial attempt to fire the TTI (Transfer Trajectory Injection) burn on Feb 2 was unsuccessful due to a command error. Success came a day later, and the Star 37FM solid motor placed Clementine on the first leg of a stunted phasing loop trajectory. An engineering burn of the bipropellant engine was carried out to clear the fuel lines in preparation for a calibration burn, later cancelled because of delays in jettisoning the interstage just prior to first apogee. Two perigee burns of the engine were used to raise the apogee to lunar distance, and on Feb 19 the spacecraft executed the LOI-1 burn to enter lunar orbit. A second LOI burn to refine the orbit was aborted when telemetry incorrectly showed that the door protecting the delicate sensors was open; the LOI-2 burn was successfully carried out the following day and Clementine began its mapping of the Moon. A number of manuevers were made to ensure complete mapping coverage.

After its successful lunar mapping mission, Clementine departed lunar orbit on May 3. At perigee on May 7, a software failure caused all the attitude control propellant to be depleted. The original plan had called for Clementine to depart Earth orbit with a lunar flyby on May 27 and head off to fly past the minor planet (1620) Geographos on 1994 Aug 30, with a possible further flyby of (3221) Verenia on 1995 Oct 21. This plan was now impossible, and managers decided to try and keep Clementine in Earth orbit. The main propulsion fuel was unaffected by the failure, and it was realized that by using the sun sensor to tell the instant Clementine was pointing in the right direction as it spun on its axis once a second, and pulsing the engine at exactly those times, limited control of Clementine's orbit was possible. Two leading edge lunar swingbys could place Clementine in a 12000 x 240000 km orbit. On May 27 Clementine made its first lunar swingby, at a distance of 8900 km, and fell back toward perigee. The perigee burn on May 31 was only partially successful and a followup trim burn was also insufficient. Then, on June 4, the spacecraft started losing electrical power and its signal became too weak to track. On June 24 the probe passed by the Moon again (at a distance of around 10000-20000 km?) and finally on Jul 20 an 8200 km flyby sent the probe into heliocentric orbit. Contact was recovered briefly in May 1995.

Clementine
Date	Time	Event	Orbit
1994 Jan 25	1634	Launch by Titan 2G
1994 Jan 25	1636	Titan Stage 1 sep T+2:30
	1637?	Fairing sep
	1639?	Titan stage 2 MECO
	1639?	Titan stage 2 sep	259 x 296 x 67
1994 Jan 26	0000		251 x 287 x 66.96
1994 Jan 29	0000		247 x 285 x 66.96
1994 Feb 3	0000		244 x 285 x 66.96
1994 Feb 3	0610	Spinup	250 x 290 x 66.97
1994 Feb 3	0629	TTI burn, Star 37, 2960 m/s	51.2h 252 x 126728 x 66.42
1994 Feb 3	1859		284 x 126962 x 66.48
1994 Feb 3	1900	BPE engineering burn, 3.5 m/s	284 x 126962 x 66.48
1994 Feb 4	0800??	ISA separation near apogee	292 x 126938 x 66.48
1994 Feb 4		Apogee 1
1994 Feb 5	1000	Approach P1	289 x 126259 x 66.36
1994 Feb 5	1001	P1 burn, 213 m/s	413 x 364015 x 66.36
1994 Feb 6	0100	Pass EL1:4
1994 Feb 6	0959	Approach P1C	437 x 367462 x 66.31
1994 Feb 6	1000	P1C burn 31.9 m/s	437 x 367464 x 66.31
1994 Feb 7		Titan stage 2 exploded
1994 Feb 11	s	Apogee 2	385673 km?
1994 Feb 15	1252		855 x 390389 x 63.04
1994 Feb 15	1253	P2 burn, 7.4 m/s	856 x 385388 x 63.04
1994 Feb 16	1259		843 x 410558 x 63.25
1994 Feb 16	1300	P2C burn 1.4 m/s	860 x 409800 x 63.25
1994 Feb 17	0959		793 x 410158 x 64.25
1994 Feb 18	2040?	Enter lunar sphere
1994 Feb 19	1251	LOI approach	404 x Infinity x 89.5
1994 Feb 19	1251.32	LOI-1 burn 460.3 m/s
1994 Feb 19	1257.42	LOI-1 cutoff, lunar orbit	LO 401 x 5426 x 89.49
1994 Feb 20	1241	LOI-2 burn 1.2 m/s	402 x 5388 x 89.33 from 402 x 5425 x 89.33
1994 Feb 21	1216	LOI-2 burn, 2nd attempt, 103.5 m/s	397 x 2965 x 89.27
1994 Feb 22	1217	LOI-2 trim, 5.3 m/s	382 x 2971 x 89.32
1994 Mar 11	0600	Pre LOM 1	445 x 2909 x 89.78
1994 Mar 11	0629	LOM 1 burn, 19 m/s	445 x 2909 x 89.78
1994 Mar 26	0221	Apsidal Rot 1 burn, 106 m/s
		Move periselene from 30S to 30N	447 x 2904 x 89.78
	1241	Apsidal Rot 2 burn, 106 m/s	1008 x 3560 x 89.50
1994 Mar 27	1830	Rotation trim, 3.8 m/s	448 x 2905 x 90.06
1994 Apr 11	0629	LOM 2 burn, 8.7 m/s	428 x 2925 x 90.00
1994 May 3	1300		369 x 2984 x 89.76
1994 May 4	0324:15	LOD (Lunar Orbit Departure), 453.3 m/s
1994 May 4	0330		24737 x Infinity x 107.9
1994 May 5	0055	Depart lunar sphere
1994 May 7	1330		68424 x 452909 x 21.36
1994 May 7	1345	Attitude control failure	68429 x 451989 x 21.34
1994 May 8	0556	2P1 Perigee 68408
1994 May 12	0154	Pre Test mv 1	66832 x 453021 x 21.35
1994 May 12	0159	Test mv 1	66963 x 453381 x 21.30
1994 May 13	0030	Pre Test mv 2	66116 x 453547 x 21.30
1994 May 13	0034	Test mv 2	66057 x 451669 x 21.21
1994 May 16	0530	2A1 Apogee 454929 km?
1994 May 18	1300	Pre 2A2 burn	62600 x 451739 x 21.21
1994 May 20	1300	Post 2A2 burn	57261 x 444300 x 21.12
1994 May 24		2A2 Apogee
1994 May 27		Lunar flyby 8900 km
1994 May 31	2057	2A3 burn,	44768 x 388197 x 19.50
1994 May 31		Trim burn
1994 Jun 5		Contact lost
1994 Jun 24		Lunar flyby
1994 Jul 20		Lunar flyby 8200 km
1994 Jul 21		Solar orbit
1995 Feb 20		DSN contact
1995 Mar 1		Solar orbit	1.02 x 1.06 AU x 0.07
1995 Apr 10		Commanded DSPSE
1995 May 4		Fuel dump burn

Payload:

• UV/Vis imager

• HiRes camera (connected to LIDAR)

• LWIR camera

• NIR camera

• Lidar for laser altimetry Nd YAG laser

Kosmos 1460

 1983-043A

---

Two-tone telemetry; Medium res satellite

Kosmos-1460
Date	Time	Event	Orbit
1983 May 6	0910	Launch by Soyuz-U	Baikonur
	0914	Blok-I burn
	0918	Blok-I sep
1983 May 6			90.08 209 x 346 x 70.3
1983 May 9		Orbit raise	92.20 349 x 415 x 70.3
1983 May 15			92.20 349 x 415 x 70.3
1983 May 20
	0557?	Deorbit
	0607?	PO sep
	0625?	Entry
	0640?	Landed