Navstar 21

 1990-068A

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Navstar SVN 21 (PRN 21, USA 63) was the 8th Block II GPS launch. It went to plane E-2.

Navstar 21
Date	Time	Event	Orbit
1990 Aug 2	0539:00	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
	0543	Stage 2 TIG (T+4:38)
		Fairing sep (T+4:50)
	0550	SECO-1 (T+11:37)	186 x 186? x 35.66?
		T+20:55 spinup
	0559	T+20:58 Delta sep
	0600	T+21:35 TES
	0602	T+23:02 TECO	355.32 171 x 20308 x 37.7
	0603	T+24:55 Stage 3 sep
	0603	T+24:57 despin weights
	0644?	SES-3 depletion
	0644	St 2 peri	T+1:05 91.78 185 x 538 x 30.1 (Delta)
	1912		356.67 156 x 20407 x 37.7
1990 Aug 4	0252?	Star 37XFP burn
1990 Aug 6			722.71 19931 x 20672 x 54.71
1990 Aug 16			718.03 19931 x 20435 x 54.70
1990 Aug 24		Operational
1997 Feb 1		Operating at slot E-2
2002 Mar 5			717.96 19698 x 20640 x 56.1

Progress M-28

 1995-036A

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Progress 228 was launched on 1995 Jul 20, with mass 7125 kg at launch. It carried 400 kg of experiments (347 kg of them for ESA), 400 kg of water and 306 kg of food.

Progress M-28
Date	Time	Event	Orbit
1995 Jul 20	0304:41	Launch by Soyuz-U	LC1
	0313:30	Blok-I sep	88.69 191 x 258 x 51.6
	0647:29	TCM-1, dv 20 m/s
	0736:50	TCM-2, dv 13 m/s	89.83 246 x 308 x 51.6
1995 Jul 21	0406s	TCM-3
1995 Jul 22	0439:37	Docked with Mir -X
1995 Sep 4	0509:53	Undocked from -X
	0812	Deorbited E of New Zealand
	0858:55	Reentered

Nadezhda 6

 2000-033A

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The Nadezhda satellite launched in Jun 2000 was the first Plesetsk launch to sun-synchronous orbit. It may have carried only the COSPAS-9 payload and omitted the nav payload, according to some reports. 

Nadezhda
Date	Time	Event	Orbit
2000 Jun 28	1037:42	Launch by Kosmos-3M	PL
		T+2:10 St 1 MECO
		T+2:12 St 1 sep
	1040	T+2:12 Stage 2 burn
	1040	T+2:27 Fairing sep
	1046	T+8:03 Stage 2 MECO-1	-300? x 700? x 98.7
	1111	Stage 2 MES-2
	1112?	Stage 2 MECO-2
	1113:15	Stage 2 sep	683 x 708 x 98.1

Kosmos 869

  1976-114A

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Another year passed before 11F732 No. 3L (7K-S No. 3L) was launched. This time the ship remained in orbit for 18 days, maneuvering extensively. It went out of control for two days with loss of communications and an IR horizon sensor failure and the planned 8 day flight was extended to include all the planned test objectives. The spacecraft landed successfully.

Kosmos-869
Date	Time	Event	Orbit
1976 Nov 29	1600:00	Launch by Soyuz	KB
	1602	Blok BVGD sep
	1604	Blok A sep
	1608	Blok I MECO
	1608	Blok I sep
1976 Nov 29.67			89.36 196x290x51.78
1976 Dec 3.99			89.75 189x335x51.76 from 89.27 195x282
1976 Dec 4.93			90.46 259x336x51.76
1976 Dec 5.87			90.58 260x345x51.77 from 259x335
1976 Dec 6.69			90.85 265x368x51.79
1976 Dec 9.3			91.12 267x392x51.78
1976 Dec 12.7			90.62 300x310x51.78 from 268x390
1976 Dec 16.3			90.62 300x310x51.77
1976 Dec 17	0948?	DO
	0952?	DO CO
	1002?	BO sep
	1004?	PAO sep	-77? x 303 x 51.8
	1012?	Entry
	1034:30	Landed

NEAR Shoemaker

 1996-008A

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The first Discovery probe was NEAR, the Near Earth Asteroid Rendezvous. It was built and operated by JHU-APL. The box-shaped satellite had 4 fixed (but hinged) solar panels and no extensible booms to save money; the science instruments were in the base of the bus. An Aerojet propulsion system included a 100lb LEROS 1 thruster. Launch mass was 805 kg full, 468 kg dry, 337 kg prop. (816 full 475 kg dry per APLTD19-2-157, APLTD23-1-73). The propulsion system mass was 438 kg. The vehicle is a box 2.80m tall and 1.47m in diameter with four deployable solar panels attached to the upper edge and a 1.5m high gain antenna. The despin cables are around 12m long.

NEAR was launched by a Delta into a hyperbolic trajectory with C3 = 26 (km/s)².

NEAR flew past (253) Mathilde in 1997. Mathilde was the first C-type asteroid to be visited and was found to have a diameter of 52 km. Flyby speed was 10 km/s.

In Dec 1998, the biggest burn to date was planned: a 650 m/s burn of the main engine. A 3-minute fuel settling burn was successful, but then 0.2s after ignition for the main burn the engine aborted with only 0.2m/s of velocity change. The failure resulted in a 1 km/s flyby of Eros. A burn on 1999 Jan 3 placed NEAR in a rendezvous orbit with a maximum distance of 1 million km, with re-rendezvous on 2000 Feb at 0.04 km/s. Orbit insertion was successful on Valentine's Day 2000. Eros has a mass of around 7 teratonnes and a 50 km radius orbit around it has a period of about 30 hours. In Mar 2000 NEAR was renamed NEAR Shoemaker in honor of planetary scientist Eugene Shoemaker.

On Feb 12, NEAR landed on Eros at 35S 279W. Impact was 1.9m/s; signals were received after touchdown confirming NEAR survived the impact. NEAR was switched off on Feb 28.

 

NEAR
Date	Time	Event	Orbit
1996 Feb 17	2043:27	Launch by Delta 7925-8	CC LC17B
	2044	6 SRB sep
	2045	3 SRB sep
	2047:55	MECO
	2048:07	Stage 1 sep
	2048:12	Stage 2 ignition
	2048:24	Faring sep
	2052:50	Stage 2 SECO1	180 x 185 x 28
	2105:20	Stage 2 burn 2
	2108	Stage 2 SECO2	172 x 5550
		Spinup Stage 3 to 59 prm
	2108:29	T+25:02 St 2 sep
	2109	Stage 3 burn 87s
	2110	Stage 3 cutoff
	2112?	Stage 3 sep, 1.8m/s
		Yo-yo despin of NEAR to 0.8 rpm
	2117	NEAR detumble burn
		Delta stage 2 depletion burn
1996 Feb 18	0357	Pass EL1:4
1996 Feb 21	0350?	Leave Earth sphere
1996 Feb 24	2132		Desat burn
1996 Mar 2	2000	TCM-1; reduced Mathilde flyby from 869000 km to 82000 km
1996 Mar 23	1200		0.98 x 2.18 AU x 0.76 deg
1996 May 13		Geotail crossing
1996 Sep 13	1700	TCM-2A
1996 Sep 13	1730	TCM-2B, trim Mathilde miss to 2440 km
1997 Jan 6	1300	TCM-3
1997 Jan 29	1400	TCM-4, trim miss to 1032 km
1997 Jun 18		TCM-5
1997 Jun 27	1245	Enter Mathilde sphere
	1256:01	Flyby (253) Mathilde at 1256 km, 2.0AU
	1310	Leave Mathilde sphere
1997 Jul 3	0630:00	TCM-7 (DSM-1) Deep space maneuver for Earth flyby, 269 m/s
1997 Jul 23		TCM-8 (DSM-2), 5 m/s
1997 Sep 24		NLR and NIS covers opened (not ejected)
1997 Nov 17	1600	TCM-9 targeting 1m/s
1998 Jan 9	1500	TCM-10 0.1 m/s
1998 Jan			0.52 x 0.95 AU x 2.18
1998 Jan 20	2011	Enter Earth L1 sphere
1998 Jan 23	0723	Earth flyby 532 km over Iran
1998 Jan 25	1841	Depart Earth L1 sphere
1998 Feb			0.98 x 1.77 AU x 10.04
1998 Feb 11	1400	CAL-1 thruster cal test 0.01 m/s
	1430	CAL-2 test
	1500	CAL-3 test
	1700	CAL-4 test
	1730	CAL-5 test
1998 Apr 1	1600	TCM-12, post-swingby targeting 1m/s
1998 Oct 14	1700	TCM-15 0.3 m/s
1998 Dec 20	2200	TCM-16 Eros braking 1, aborted
1998 Dec 23	1842:15	Flyby Eros at 3827 km, 0.965 km/s
1999 Jan 3	1700	TCM17/DSM-2 0.94km/s, 24 min 940m/s
1999 Jan 20	1700	TCM-18 DSM-2 cleanup burn 14m/s
1999 Aug 12	1700	TCM-19 2-min burn 21m/s
1999 Oct 20	1530	TCM-20,
1999 Dec 6	1530	TCM-21
2000 Feb 2	0500	Safemode
		Control recovered
2000 Feb 3	1700	TCM 22, range = 8000 km
2000 Feb 8	2200	TCM 23s, range = 4600 km
2000 Feb 11	1533	Enter Eros hill sphere
2000 Feb 14	0758:48	Flyby at 182 km from center
	1533:06	Eros orbit insertion 57s, 333 km from Eros center
	1534:03	Cutoff	321 x 366 km T=27.6d
2000 Feb 24	1700	Descent burn OCM-1	204 x 366 km
2000 Mar 3	1800	OCM-2 22s	205 x 205 km
2000 Mar 10			205 x 205
2000 Apr 2	0203	OCM-3	101 x 209
2000 Apr 11	2120	OCM-4	100 x 100
2000 Apr 22	1750	OCM-5	50 x 101
2000 Apr 30	1615	OCM-6 2:20 dv=5 kph v=11kph	49 x 52 x 89.6
2000 May 13		NIS shut down
2000 Jul 7	1800	OCM-7	35 x 50 x 90
2000 Jul 14	0300	OCM-8	34 x 39 x 90
2000 Jul 24	1700	OCM-9	37 x 50 x 90
2000 Jul 31	2000	OCM-10	49 x 51 x 90
2000 Aug 8	2325	OCM-11 inc change	50 x 52 x 105
2000 Aug 26	2325	OCM-12 2min burn	49 x 102 x 113
2000 Sep 5	2300	OCM-13	100 x 103 x 115
2000 Oct 13	0545	OCM-14	50 x 98 x 130
2000 Oct 20	2140	OCM-15	50 x 52 x 133
2000 Oct 25	2210	OCM-16	51 x 19 x 131
2000 Oct 26	0655:10	5.5km close flyby
	1740	OCM-17	64 x 203 x 145
2000 Nov 3	0300	OCM-18 3.5s	194 x 196 x 147
2000 Dec 7	1520	OCM-19	34 x 193 x 179
2000 Dec 13	2015	OCM-20: begin XGRS science	33 x 37 x 179
2001 Jan 24	1605	OCM-21	21 x 35 x 179
		6 km flyby
2001 Jan 26		within 4.9 km
2001 Jan 27		within 13 km
2001 Jan 28	0125	OCM-22	19 x 37 x 179
	1024	2.7km flyby
	1805	3.8s burn, OCM-23
2001 Jan 28	1345	OCM-23	35 x 36 x 178
2001 Feb 2	0900	OCM-24	35 x 37 x 178
2001 Feb 6	2315	OCM-25	33 x 35 x 178
2001 Feb 12	1513:36	EMM-1 Deorbit 20s	7.5 x 35 x 135
	1858:35	EMM-2 braking 3min	5 alt x 35 x 50
	1914	EMM-3 5min12s	3 alt x 35 x 50
	1930	EMM-4 6min	1km alt x 35 x 50
	1942	EMM-5 4min	350 alt
		Last image from 120m
	1944:17	Landed on Eros, 1.9m/s
		279.3W 40.0S
2001 Feb 13	0130?	One telemetry frame received
2001 Feb 14?		XGRS and magnetometer movements
2001 Mar 1	0000	end of mission

Payload:

• MSI Multispectral imager 4400A-1.1mu 2 deg FOV

• MAG Magnetometer

• NIS Near IR spectrometer 0.8-2.6 microns

• XRS X-ray spectrometer 1-10 keV;

• GRS gamma ray spectrometer 0.3-10 MeV

The American country club : its origins and development

https://welib.org/md5/478296a7c002c94d38fc91f226de2d6c

Rocket and Space Corporation Energia: The Legacy of S. P. Korolev

 https://welib.org/md5/b60592a16528dbb9d83a8cb0eca790aa

Astra 1K

 2002-053A

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SES satellite ordered 1998 from Aerospatiale. It is the first Spacebus 4000.  The Spacebus 4000 is also called Spacebus 3000B3S; but is different from the Spacebus 3000B3, e.g. Eurasiasat 1. 1K has the Spacebus 3000 avionics, unlike later SB4000 model. Astra 1K is to replace Astra 1B, and provide extra capacity for eastern Europe. It will also carry Ka-band capacity to back up Astra 1H. The Ku-band 10.7-11.7 GHz payload provides pan-European coverage. Beams cover UK/Ireland, continental Europe, and European CIS. Mass will be 5250 kg.

SCS (Societe Commune des Satellites) formed 1998 to merge Alcatel and Aerospatiale/Cannes built the satellite.

Launch mass 4650 kg.

MES-2 terminated after 1s with excessive fuel flow to DM engine followed by SC sep. DM vented fuel shortly after and reentered empty on Nov 28. Astra 1K was deorbited on command.

Reentry time based on TLEs was around 0120 UTC, not 0200 UTC as reported by SES.

The spacecraft was not registered by Luxembourg; an Alcatel fact sheet described Alcatel's role as a ground delivery of the satellite combined with provision of on-orbit testing (as opposed to on-orbit delivery). This implies that the owner of the satellite during the launch was SES and not Alcatel even if the former delegated operational control to the latter, and thus that Luxembourg was a launching state together with Russia.

Astra 1K
Date	Time	Event	Orbit
2002 Nov 25	2304:23	Launch by Proton 408-02/DM24L	LC81/23
	2306:26	T+2:03 St 1 sep
	2309:54	T+5:31 St 2 sep
	2310:06	T+5:42 GO sep
	2313:56	T+9:32 MECO
	2314:06	T+9:43 St 3 sep	-744 x 183 x 51.6
	2320:08	T+15:45 MES-1 300m/s 77s
	2321:25	T+17:02 MECO-1	175 x 175 x 51.6
	2325?	St 3 impact at 24 23 N 161 46E.
2002 Nov 26	0017:45	T+1:13:22 MES-2
		MECO-2 premature
	0017	DM sep
			156 x 171 x 51.6
2002 Nov 26	2200?		146 x 299 x 51.6
2002 Nov 27			277 x 292 x 51.6
2002 Nov 28	1415	DM reentered over NW USA (Wash/Ore.)
2002 Nov 30			278 x 296 x 51.6
2002 Dec 1			257 x 308 x 51.6
2002 Dec 4			245 x 314 x 51.6
			240 x 323 x 51.6
2002 Dec 5			236 x 330 x 51.6
2002 Dec 8			218 x 344 x 51.6
2002 Dec 10			209 x 352 x 51.6
2002 Dec 12	0119	Deorbited over Pacific