USA-136

 1997-068A

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This payload was 4.6m in diameter and 12.2m long. The separated Centaur stage is 4.3m diameter and 8.8m long. Launch vehicle was K-20 (A-17)/TC-16. An EHF Milstar polar adjunct package was announced as a secondary payload on an elliptical orbit Titan 4 payload in 1997. The package is derived from the UHF Followon payloads. According to USAF, the NRL's MPTB electronics test bed was launched into a high radiation orbit in 'fall 1997'; I believe this was probably on the K-20 flight.

Publications of space physics data confirm that this satellite is the third in the series of HEO payloads.

TRUMPET/USA 136
Date	Time	Event	Orbit
1997 Nov 8	0205	Launch by Titan 4A-17/TC-16	CC LC41
	0206	T+1:55 Stage 1 burn
	0207	T+2:03 SRMU sep
	0208	T+3:56 PLF sep
	0210	T+5:06 Stage 1 MECO
	0210	T+5:06 Stage 2 burn
	0213	T+8:50 Stage 2 MECO
	0213	T+8:56 Stage 2 sep
	0214	T+9:17 Centaur MES1
	0218	T+13:43 Centaur MECO1	88.19 185 x 185 x 55.0 (ILAM)
	0304	T+59:21 Centaur MES2
	0308	T+1:03:30 Centaur MECO2	484.21 204 x 27890 x 55.0 (ILAM)
	0400	T+1:55:17 Centaur MES3
	0401	T+1:56:28 Centaur MECO3	713.84 1100 x 39059 x 63.55 (ILAM)
	0418	T+2:12:58 Centaur TC-16 sep
		TC-16 orbit	708.9 1075 x 38839 x 64.3 (UN)
		(A)	712.8 1098 x 39012 x 63.6 (UN)

Pioneer Venus Orbiter

 1978-051A

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The Pioneer Venus Orbiter was launched at 1313 on 1978 May 20 by Atlas Centaur from Cape Canaveral. The Atlas stage separated at 1317:16 and the Centaur ignited at T+4:26. Centaur MECO at 1322 (T+9:36) left PVO in a 170 km parking orbit. At 1331 the Centaur reignited for a 2 min 17 s solar orbit insertion burn. When it separated at 1336, PVO was on a Type 2 Venus transfer trajectory with an aphelion of 1.08 AU. Control was transferred to the PMOCC at Ames on May 22. Correction burns TCM1 and TCM2 were made on Jun 1 and Nov 2.

The onboard solid insertion motor fired at 1558:05 on 1978 Dec 4 and placed PVO in a 23h 11m, 378 x 66900 km x 105.6 deg orbit around Venus. At 0527 Dec 6 it lowered periapsis to 233 km, and on Dec 9 the periapsis was lowered further to 180 km. By Dec 20 the orbit was synchronized to the Earth day, 1436 min 150 x 66900 km x 105 deg, when the last of 7 trim burns was made.

In 1979 Jan-Feb the periapsis was varied from 142 km to 175 km. On Feb 14 the OIR instrument failed. In August the PVO was turned off temporarily while the Deep Space Network supported the Pioneer Saturn encounter. The nominal mission was over on 1979 Aug 4, and was followed by EM1, the Pioneer Venus Extended Mission. By 1979 Sep periapsis had risen to 253 km and was lowered to 142 km. Extended Mission 2 ran from 1980 Apr 3 to Dec 2. In 1980 Jul the RCS gas ran low; the periapsis was allowed to rise. The period remains constant as the inclination, now at 17 degrees, would drift to 0 degrees by 1986, and back up to 17 deg in 1992. In 1981 the periapsis was too high for the ORM and it was turned off.

The Approach Phase began in 1991 Jan when periapsis began to drop from 1000 to 200 km. This was followed by the Entry Phase, starting in 1992 Jun. A periapsis raising burn (the 6th) was carried out on 1992 Oct 2, raising closest approach from 132.9 km to 141.7 km. On Oct 3 the propellant ran dry and the satellite had to be spun up on Oct 5. A final orbit raise of 1 km was made at 0525 on Oct 8 (apoapsis). After the next periapsis passage, 128 km at 1922 on Oct 8, no further transmissions were heard from PVO and the end of mission was declared.

PVO
Date	Time	Event	Orbit
1978 May 20	1313:00	Launch by Atlas Centaur
		T+2:19 BECO 57 km
		T+2:22 Booster sep 61 km
		T+3:04 Insulation panels sep 98 km
	1316:44	T+3:44 Fairing sep
		T+4:14 SECO
	1317:16	T+4:16 Atlas sep
	1317:26	T+4:25 Centaur MES-1
	1322:36	T+9:35 Centaur MECO-1	166 x 170 x
	1332	Centaur MES-2 2:17
	1334	Centaur MECO-2
	1337:46	T+24:46 Centaur sep (MECO2+2:15)	0.72 x 1.08 AU
	1337:49	T+24:49 Spinup to 6.5 rpm
	1650:30	MAG deploy
	2056?	Pass EL1:4
1978 May 21	1700?	HGA despin
1978 May 24	0544	Exit Earth sphere (L1)	0.72 x 1.08 AU
1978 Jun 1	1001	TCM-1 axial 0.5m/s
	1916	TCM-1 radial-1 1.6m/s
	2146	Spin rate trim
1978 Jun 2	0006	TCM1 radial-2 1.6m/s
1978 Nov 2	TCM-2
1978 Dec 1	1900?	Enter Venus sphere/L1
1978 Dec 4	1558:17	VOI burn 1108.7 m/s
		VOI burnout	1391.43 378.7 x 66900 x 105.0210
		HGA spinup 30 rpm
		SC bus despin to 15 rpm
		Inversion, spin axis to NEP at apo 1
		HGA despin
		ORAD antenna released
		ONMS cap jettison (VOI+36h?)
		OETP radial sensor deploy
1978 Dec 5		OTM-1	248 x 66900? x 105.6
1978 Dec 6		OTM-2	233 x 66900? x 105.6
1978 Dec 9		OTM-3	180 x 66900? x 105.6
1978 Dec 20		OTM-7?	1436.0 150 x 66900 x 105
		Spacecraft despin to 5 rpm
1979 Jan-Feb		Periapsis (km)	142-175
1979 Mar-Apr			150-170
1979 May-Jul			150-190
1979 Aug 4		End primary mission
1979 Aug 4		Start Extended Mission 1
1979 Sep			253
1979 Sep		Orbit lower	170
1979 Oct			142
1979 Oct			160
1979 Nov			145-160
1979 Dec			150-185
1980 Jan			150-185
1980 Feb-Mar			150-175
1980 Apr 3		Start Extended Mission 2
1980 Apr-Jun			150-180
1980 Jul		end of orbit maintenance
1980 Dec 2		End EM2
1981			400-800
1982			800-1500
1983			1500-1800
1984			1800-2000
1985			2000-2100
1986			2270-2350
1987			2000-2100
1988			1600-2000
1989			1200-1600
1990			1000-1200
1991 Jan		Approach Phase
1991 Mar 3			1000
1991 Dec			200 ?
1992 Jun		Entry Phase
1992 Oct			132.9
1992 Oct 2		PRM-6	141.7
1992 Oct 3		Fuel low
1992 Oct 5		spinup
1992 Oct 6			130.8 (orbit 5054)
1992 Oct 7			128.9 (orbit 5055)
1992 Oct 8	0525	PRM-7? 1km	128
1992 Oct 8	1922	Perapsis	128 x
		End of transmissions
1992 Oct		Entry

Progress M-42

 1999-038A

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Launch mass 7150 kg. At undocking, mass was 5800 kg. The Reflektor antenna was 6.4 x 5.2 x 1.1m deployed; the transport package was 0.62d 1.06l.

Progress M-42
Date	Time	Event	Orbit
1999 Jul 16	1637:33s	Launch by Soyuz-U	LC1
	1642	Blok A burn
	1646:13?	Blok I MECO
	1646	Blok I sep
	2021:51	DU-1 burn 35s 14m/s
	2054:12	DU-2 burn 19s, 14m/s
1999 Jul 17	1727:59	DU-3 burn 1m/s 3s
1999 Jul 18	1746:58	Distance to Kvant 150m
1999 Jul 18	1753:21	Docked Kvant +X
	1835	Hatch open
1999 Jul 20		Reflektor unloaded
1999 Aug 26		Closed TKG hatch
1999 Sep 14	0311:52	Undocked	90.73 298 x 321 x 51.6
	0610:40	Deorbit 78m/s 8:30
	0619:10	SKD cutoff
	0653	Reentered over Pacific

Saturn SA-7

  1964-057A

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The Apollo-Saturn 102 (AS-102) flight was launched on Saturn 107 at 1622:43 on 1964 Sep 18 from pad 37B. The Saturn S-4-7 stage entered orbit at 1633:15, with parameters 178 x 203 km x 31.7 deg. It reentered on Sep 22. Attached to the S-IV stage were S-IU-7 and Apollo BP-15.

SA-7
Date	Time	Event	Orbit
1964 Sep 18	1622:43	Launch by Saturn 107	CK LC37B
	1625:04	IECO
	1625:10	OECO
	1625:11	Sep, 76? km 23 deg 3.05km/s	-5940 x 159 x 32
	1625:13	S-4 MES
	1625:23	Ullage sep
	1625:23	LES sep 85? km 20 deg 3.08 km/s	-5910 x 152 x 32
	1627:36	SI apogee 159 km
	1631:40	SI impact
	1633:04	T+10:21 MECO	180 x 234 x 31,75 (MPR)
	1702	End of SA-7 tx
	2100	End of beacon
1964 Sep 18	2300?	End of BP-15 tx
1964 Sep 22	1150?	reentry 21.7S 56.4E
	1200?	impact 26.4S 69.0E

Kosmos 677

  1974-072A

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Kosmos-677 was satellite 1 of Strela-1M octuplet no. 10.

Kosmos-677
Date	Time	Event	Orbit
1974 Sep 19	1457	Launch by 11K65M	PL
		Stage 2 burn 1
	1504	T+7m Stage 2 MECO-1
		Stage 2 burn 2
	1555?	T+58m? Stage 2 sep
			114.53 1399 x 1469 x 74.03

Aviation Week: January 21,2002

 https://welib.org/md5/3c106ad066087693eb1083ef933e9143

Phillips Academy, Andover : an architectural tour

 https://welib.org/md5/d058630facd28e189048d0536f5d1403

Molniya 190

 1997-054A

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Another 11F658T satellite, no. 80046398, was launched in Sep 1997. It began orbital decay in 2010.

Molniya-1T F95
Date	Time	Event	Orbit
1997 Sep 24	2131:44	Launch by 8K78M	PL LC43/4
	2136	T+4:46 Blok A sep
	2136	T+4:56 KhO sep
	2140	T+8:46 Blok-I MECO
	2140	T+8:50 Blok-I sep
	2225	T+53:16 BOZ burn
	2225	T+53:56 BOZ sep
		ML burn
	2228	T+56:46 ML MECO
	2228	T+56:54 ML sep
1997 Oct 28			717.77 492 x 39962 x 62.9
1999 Apr 1			717.75 1181 x 39171 x 63.1