Navstar 28

 1992-019A

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SVN 28 (USA 80) was launched into plane C-2 on 1992 Apr 10.

Navstar 28
Date	Time	Event	Orbit
1992 Apr 10	0320:00	Launch by Delta 7925	CC LC17
		SRM 1-9 sep
		St 1 sep
	0324	T+4:40? SES-1
	0331	T+11:00? SECO-1	185 x 185 x 34.0?
		T+20? SES-2 36s?
	0340	T+20? SECO-2	180? x 715? x 34.0?
		T+21? St 2 sep
	0342	T+22? TES 1:24
	0343	T+23? TECO
	0345	T+25? St 3 sep	179 x 20410 x 34.61
	0426?	SES-3 depletion	530 x 715 x 21.2
1992 Apr 12	0644?	Star 37XFP burn
			715.80 19872 x 20385 x 55.12
1992 Apr 25		In service
1997 Feb 1		Operating at slot C-5

The Cheerleader’s Almanac

https://welib.org/md5/ab8d43d31dc269b0e467ce5bf12e7fd8

Intelsat 507

 1983-105A

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Intelsat V F-7 was the first Intelsat to be launched by a non-US launch vehicle. It took off in Oct 1983 from South America aboard a European Ariane rocket, carrying C and Ku-band transponders for INTELSAT and the MCS-C L-band package for INMARSAT.

Intelsat V F-7 (MCS)
Date	Time	Event	Orbit
1983 Oct 19	0045:32	Launch by Ariane (L7)	CSG ELA1
		T+2:26 St 1 MECO
		T+2:30 St 1 sep 66 km	-6200 x 188 x 10?
		T+2:32 St 2 burn
		T+4:15 Fairing 173 km	-5449 x 244 x 8
		T+4:51 St 2 sep 205 km	-4550 x 290 x 8?
	0050:27	T+4:55 St 3 MES
	0059:49	T+14:17 St 3 MECO
	0101:02	T+15:30 St 3 sep	629.4 259 x 35647 x 8.4
		T+15:33 St 3 avoidance
	0630?	Apogee 1
	1130?	Perigee 1
	1700?	Apogee 2 over 80W
	2250?	Peri 2
1983 Oct 20	0300?	Apo 3 over 125E
1983 Oct 20			629.43 255 x 35645 x 0.5
	0830?	Peri 3
	1300?	Apo 4 over 30W
	1900?	Peri 4
1983 Oct 21	0030?	Apo 5 over 160E
	0530?	Peri 5
1983 Oct 21	1004?	Star 37XF burn 20s
	1030?	Apo 6 over 12E
1983 Oct 21			1387.66 35100 x 35567 x 0.3
1983 Oct 24			1431.14 35471 x 35907 x 0.5 GEO 19.8E+1.2E
1983 Oct 28			1433.24 35512 x 35949 x 0.4 GEO 24.7E+0.7E
1984 Jan 4			1436.13 35672 x 35902 x 0.4 GEO 22.8E
1984 Jan		Move to IOR
1984 Feb		IOR Primary	GEO 60E
1984 Mar 7			1436.16 35767 x 35808 x 0.1 GEO 60.0E
1984 Oct 10			1436.14 35772 x 35802 x 0.0 GEO 60.0E
1985 Nov 7			GEO 60.1E
1985 Dec 18			1436.13 35776 x 35798 x 0.1 GEO 60.0E
1985 Dec		INMARSAT IOR Spare	GEO 66E
1986 Jan 14			1436.13 35751 x 35823 x 0.0 GEO 65.8E
1986 Sep			GEO 66E
1987 Jan 3			1436.08 35773 x 35799 x 0.1 GEO 65.9E
1988 Feb 28			1436.07 35766 x 35805 x 0.04 GEO 66.0E
1990 Jan 19			1436.08 35761 x 35811 x 0.1 GEO 66.0E
1991 Jan 12			1436.10 35690 x 35882 x 1.1 GEO 66.1E
1991 Jan 14		mv out
1991 Feb 6		mv in	1436.11 35768 x 35805 x 0.6 GEO 57.0E+0.01W
1991 Jul 21			1436.05 35750 x 35821 x 1.0 GEO 57.0E
1992 Oct 20			1436.07 35760 x 35811 x 2.0 GEO 57.0E
1995 Jan 4			1436.05 35546 x 36024 x 3.8 GEO 57.2E
1995 Jan 21		mv out	1435.97 35765 x 35802 x 3.9 GEO 57.3E+0.03E
1995 Apr 27		mv in	1436.09 35767 x 35805 x 4.0 GEO 47.0E
1996 Jul 17			1435.99 35770 x 35798 x 4.9 GEO 47.2E

Progress M-23

 1994-031A

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Progress M (7K-TGM) No. 223 was launched in May 1994 and announced as Progress M-23. It carried the last VBK reentry capsule. Mass was 7117 kg. The launch vehicle was built to the Soyuz-U2 standard but fuelled and used as a Soyuz-U, according to Igor Lissov.

Progress M-23
Date	Time	Event	Orbit
1994 May 22	0430:04	Launch by Soyuz-U	KB
	0438:52	Blok I cutoff	193 x 247 x 51.6
1994 May 24	0618:35	Docked with Kvant DP2
1994 Jul 2	0846:49	Undocked
	1444	TDU deorbit
	1455:45	VBK sep
	1457:35	Reentry
	1509:00	VBK landed

Resurs 1997

 1997-072A

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Resurs F-1M was an upgraded Resurs F-1 with a new camera payload. It was launched on 1997 Nov 18.

Resurs F-1M
Date	Time	Event	Orbit
1997 Nov 18	1114:59	Launch by Soyuz-U	PL
	1123	Blok I MECO
	1123	Blok I sep
			88.66 179 x 236 x 82.3
	2000?	orbit raise
1997 Nov 20			89.02 208 x 243 x 82.3
1997 Nov 24			88.97 206 x 240 x 82.3
		Orbit raise
1997 Nov 25			89.02 209 x 243 x 82.3
1997 Nov 28			88.99 207 x 242 x 82.3
1997 Nov 29		Orbit raise	89.03 210 x 242 x 82.3
1997 Dec 2			88.99 209 x 240 x 82.3
1997 Dec 3		Orbit raise	89.59 238 x 269 x 82.3
1997 Dec 9			89.52 234 x 267 x 82.3
		Lower perigee	88.95 174 x 270 x 82.3
1997 Dec 11		Orbit raise	89.02 212 x 238 x 82.3
1997 Dec 13			88.99 210 x 238 x 82.3
1997 Dec 14	0533?	KDU sep
	0535?	Deorbit
	0542?	PO sep
	0552?	Entry
	0555?	Landing (PSC)
	0604?	Landing

ATS-4

  1968-068A

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ATS D (Applications Technology Satellite 4) was the second gravity gradient ATS test. The Hughes satellite included the SR-28-3 AKM and was intended for geostationary orbit, unlike ATS A. An Atlas Centaur launch vehicle was to have placed the satellite in geostationary transfer orbit of 664 x 35882 km x 16.2 deg. Atlas 5104C left pad 36A and fell away, followed by the first burn of Centaur AC-17, which inserted the ATS/Centaur combination into a 219 x 767 km x 29.0 deg parking orbit. However, AC-17 failed to reignite because of boost pump failure and remained attached to ATS IV. Three attempts to fire the AKM failed because the spacecraft was still attached. Some experiments returned limited data, confirming that they operated. The primary gravity booms were extended 10 meters. The ATS/AKM/Centaur combination reentered over the South Atlantic Ocean on 1968 Oct 17.

ATS-4
Date	Time	Event	Orbit
1968 Aug 10	2233:02	Launch by Atlas Centaur	CC LC36A
		T+2:32 BECO
		T+2:35 Booster sep
		T+3:17 Insulation panels sep
		T+3:53 Fairing sep
		T+4:06 SECO
		T+4:08 Atlas sep
		T+4:18 Centaur burn 1
	2242:58	T+9:56 Centaur MECO-1	94.13 186 x 767 x 29.14
		61 min coast
	2344:07	T+1:11:05 Centaur burn 2 failed
1968 Aug 11			94.54 221 x 771 x 29.1
1968 Sep 2			93.69 217 x 692 x 29.0
1968 Oct 17		Reentered