Crystal 4

 1981-085A

---

The fourth KH-11 KENNEN was launched on 1981 Sep 3 by a Titan 3D to a 1009 LTDN SSO, the third mission in the west plane.

KENNEN 4
Date	Time	Event	Orbit
1981 Sep 3	1829	Launch by Titan 23D	V SLC4E
		T+1:49? Stage 1 burn 2:27
		T+1:55 SRM burnout
		T+1:55 SRM sep
		T+4:16 Stage 1 MECO
		T+4:16 Stage 1 sep
		T+4:16 Stage 2 burn
		T+5:05? Fairing
	1836?	T+7:44? Stage 2 MECO
	1837?	T+8:00 Stage 2 sep
1981 Sep 3			92.02 217x527x97.0
1981 Sep 3			92.29 243x526x97.0
1981 Sep 7			92.51 270x521x97.0 from 92.21 242x520
1981 Oct 9			92.60 266x533x97.0 from 92.03 266x478
1981 Oct 30			92.45 253x532x97.0 from 92.32 265x508
1981 Nov 5			92.46 276x511x97.0 from 92.37 276x502
1981 Nov 18			92.61 272x529x97.0 from 92.24 271x493
1981 Nov 29			92.62 277x524x97.0 from 92.03 265x480
1982 Jan 8			92.65 285x521x97.0 from 92.51 277x515
1982 Feb 26			92.77 302x515x97.0 from 92.27 279x489
1982 Mar 17			92.55 286x510x97.0 from 92.40 286x495
1982 Apr 26			92.20 293x469x97.0 from 92.09 282x469
1982 May 10			92.57 294x504x97.0 from 92.12 291x463
1982 Jun 18			92.56 290x506x97.0 from 92.38 290x490
1982 Jul 8			92.55 290x505x97.0 from 92.41 287x495
1982 Sep 16			92.39 297x483x97.0 from 92.22 286x477
1982 Nov 7			92.59 277x522x97.0 from 91.78 278x442
1982 Dec 17			92.32 283x490x97.0 from 92.19 272x488
1983 Feb 26			91.74 278x438x97.0 from ?
1983 Mar 17			92.10 325x427x97.0 from ?
1983 Mar 29			92.61 377x424x97.0 from ?
1984 Apr 30			92.2 369x399x97.0
1984 Nov 23		reentered after 1176d

GFO

 1998-007A

---

Geosat Follow On is built by Ball/Boulder for the USN Space and Naval Warfare Systems Command. It uses a modified Techstar bus. Originally planned for Pegasus XL, then LLV-1, finally remanifested to Taurus. Length is 2.7m, Mass is 365 kg. The GFO is the first altimeter satellite for tactical military applications; it will downlink altimeter data to US Navy ships, helping them avoid head-on currents and providing information for anti-submarine warfare. The intended orbit is 800 x 800 km x 108 deg. A year after launch, GFO was still in checkout and due to software problems had not been performing to spec. By late 1999, most problems had been fixed but altimeter accuracy values were still not meeting spec. Operated by SNWSC NSOC/Pt Mugu; it was transferred to NAVSPACECOM/Dahlgren when finally declared operational in early 2001.

The Taurus launch vehicle uses a new, larger payload fairing and the DPAF dual payload fitting. The Taurus 2210 version has the Castor 120 first stage.

Space Command orbital data in March 1998 repeatedly confused GFO (1998-07A) and the DPAF adapter (1998-07C); DPAF is the one in the 101.5 minute orbit.

GFO
Date	Time	Event	Orbit
1998 Feb 10	1320	Launch by Taurus	V 576E
	1321	T+1:22 Stage 1 sep 39 km 2.08 km/s	-6200 x 50?
	1321	T+1:22 Stage 2 burn
	1322	T+2:43 Stage 2 burnout
	1322	T+2:48 Stage 2 sep
	1322	T+2:50 Stage 3 burn 128 km 4.54 km/s	-5100? x 175?
	1322	T+2:53 Fairing sep 131 km 4.57 km/s	-5000? x 180?
	1324	T+4:11 Stage 3 burnout
	1331	T+11:21 Stage 3 sep	-3000? x 770
	1331	T+11:32 Stage 4 burn
	1332	T+12:40 Stage 4 burnout
	1334	T+14:31 GFO sep
	1335	T+15:21 DPAF sep
	1336	T+16:11 FM3 sep
	1337	T+17:31 FM4 sep
	1424		101.30 770 x 869 x 108.0
1998 Feb 11	0356		101.49 780 x 878 x 108.0
1998 Feb 27		Begin orbit lower	101.46 791 x 864 x 108.0
1998 Feb 28		101.26 780 x 856 x 108.0
1998 Mar 3		101.08 779 x 840 x 108.0
1998 Mar 5		100.94 785 x 820 x 108.0
1998 Mar 9		100.64 771 x 806 x 108.0
1998 Apr 1			100.68 779 x 802 x 108.0
1998 Apr 12			100.52 778 x 788 x 108.0
1998 Apr 18			100.59 781 x 791 x 108.0
1998 May 1			100.59 785 x 787 x 108.0

Anik A3

  1975-038A

---

Anik A-3 (Telesat C) was launched in 1975. In around 1976-1977 it was moved from 104W to the prime position at 114W. 

Anik A-3
Date	Time	Event	Orbit
1975 May 7	2335:26	Launch by Delta 2914	CC LC17B
		T+0:38 SRM 1-6 out
		T+0:39 SRM 7-9 on
		T+1:17 SRM 7-9 out
		T+1:25 SRM 1-9 sep
	2339:07	T+4:18 MECO
		T+4:24 VECO
	2339:15?	T+4:26 St 1 sep
	2339:27	T+4:31 Stage 2 SES-1
		T+4:55 Fairing
	2345:20	T+9:54 Stage 2 SECO-1	168 x 222 x 28.5?
	2358:48	T+23:22 St 2 sep
	2359:01	T+23:35 Star 37E burn
	2359:45	T+24:19 Star 37E burnout	231 x 35919 x 24.8
	0000:05	T+24:39 SES-2 experimental, 14s 462m/s
	0000:19	T+24:53 SECO-2
1975 May 8	0001	Star 37E sep
		SES-3 experimental, 10s
		SECO-3	210 x 2093 x 28.4
1975 May 8	0600?	Apo 1 90E
	1600?	Apo 2 70W
1975 May 9	0300?	Apo 3 128E
	1300?	Apo 4 26W
	2330?	Apo 5 171E
1975 May 10	1100?	Apo 6 8E
	2100?	Apo 7 146W
1975 May 10	1730	FW5 burn, based on source
	2130?	FW5 burn, based on TLEs
1975 May 12	1808		1424.95 35212 x 35923 x 0.0 GEO 129.2W+2.8E
1975 May 22		On station	GEO 104W
1975 Dec			GEO 104W (Morgan)
1977 Jan 26			1436.06 35774 x 35797 x 0.0 GEO 113.9W+0.0E
1977 Dec			GEO 114W (Morgan)
1979 Apr 20			1436.08 35783 x 35789 x 0.0 GEO 114.0W
1981 Feb 10			1436.08 35781 x 35791 x 0.0 GEO 114.0W
1982 May 28			1436.09 35775 x 35797 x 0.1 GEO 114.0W
1984 Nov 18	0334		1436.08 35780 x 35792 x 0.9 GEO 114.0W
1984 Nov 20	1103		1438.27 35823 x 35835 x 0.9 GEO 114.2W+0.5W
1984 Nov 22		Orbit raise
1984 Nov 23		Decommissioned
1984 Nov 25	0326		1439.04 35842 x 35845 x 0.9 GEO 116.0W+0.7W
1991 Sep 30			1439.46 35842 x 35862 x 7.2
1999 Apr 23			1439.11 35830 x 35861 x 11.9

Internet World: October 2002

 https://welib.org/md5/f20e2a3c48a1e2b9301ab2e821422bed

EarlyBird

 

48.1.2.1: EarlyBird

1997-085A

---

Their EarlyBird satellite  [994], [995],  [996] featured a 3-m panchromatic and 15-m color sensor suite for precision mapping, surveying and GIS data gathering. The 284 kg satellite would be placed in a 470 km orbit by a Start-1 from Svobodny in 1997. The LEOStar bus is built by Orbital-McLean (formerly CTA Inc.) with payload by WorldView in Pleasanton.

EarlyBird will be followed by QuickBird 1 and 2 in 1998.

EarlyBird
Date	Time	Event	Orbit
1997 Dec 24	1332	Launch by Start-1	Svobodniy
	1333	Stage 1 cutoff, coast
	1333:22	Stage 1 sep	-6320 x 55 ?
	1333:23	Stage 2 burn
	1333:40?	Stage 1/2 interstage sep
	1334:24	Stage 2 sep	-5800 x 150 ?
	1334:24	DU-3 burn
	1335:26	DU-3 MECO, 200 km
	1335:31	Stage 3 sep
	1336:22	GO (fairing) sep
	1338:46	Stage 4 burn
	1339:39	Stage 4 MECO
	1339:45	DS burn
	1343	DS cutoff
	1345	Stage 4 sep
			479 x 488 x 97.3
2000 Jul 17		end of ops

Payload:

• 3-m panchromatic camera 

• 15-m multispectral camera

Sindri

 2000-042A

---

The USAF Phillips Lab in Albuquerque, NM gave Spectrum Astro Inc. the contract for the three Mightysat Phase 2 technology demonstration satellites. Each SA200B satellite will have a mass of 113 kg and consist of a 0.5 x 0.5 x 0.25 m box with a deployable solar array.

The first in the series, Mightysat II.1 is called Sindri (P99-1). Mass 125 kg. Span 4.3m 0.7 x 0.9 x 0.9 box. Ground control by AFSCN and Kirtland RSC. Launch 2000 Jul by Minotaur. Another Aerospace Corp picosat pair, DARPA Picosat 7/8, were on board the satellite. They were deployed in Sep 2001.

Sindri is a name from Norse mythology: he was the dwarf who forged Thor's hammer.

Sindri
Date	Time	Event	Orbit
2000 Jul 19	2009	Launch by Minotaur	V CLF
		T+1:01 St 1 sep
		T+1:17 St 2 interstage sep
		T+1:58 Fairing sep
		T+2:06 SR19 sep
		T+2:15 Orion 50XL burn
		T+3:23 St 3 burnout	-4400 x 547 x 97.5
		T+9:16 St 3 sep
		T+9:16 Orion 38 burn
	2019	T+10:26 St 4 burnout
	2020	T+11:28 St 4 sep	547 x 546 x 97.5 s
2001 Sep 7	1939	Picosat ejected
2001 Nov 11		end of ops
2002 Nov 12	0055	reentered

Payload:

• Fourier Transform Hyperspectral Imager, 3500A-1.05 micron spectrometer with 17A resolution (Phillips Lab/Lasers and Imaging), for Earth imaging.

• SAC Composite solar array (Phillips Lab/SAMTD) with solar array concentrator

• NSX NRL SGLS transponder

• QC40 Quad-C40 processor

• SMATTE Shaped Memory Alloy Thermal Tailoring Expt

• SAFI Solar array Flexible Interconnect

Kosmos 690

  1974-080A

---

The Bion-2 flight carried white rats and tortoises.

Kosmos-690
Date	Time	Event	Orbit
1974 Oct 22	1800	Launch	PL
	1804?	Blok-I burn
	1808?	Blok-I sep
1974 Oct 22			90.31 215 x 363 x 62.8
1974 Oct 31			90.25 213 x 359 x 62.8
1974 Nov 8			90.15 213 x 350 x 62.8
1974 Nov 12	0520?	Deorbit
	0530?	PO sep
	0539?	Entry
	0550?	Landed after 20.5d

The A-List

https://welib.org/md5/a73e8e35d46547b823b455056b6db4bd

Iridium 9

 1997-030C

---

Iridium SV009 was one of seven launched on a Krunichev Proton in Jun 1997 into the second of six Iridium orbital planes, 30 deg E of the first plane. Mass was 657 kg for each satellite. NK's report may imply all seven satellites were ejected at the same time.

4600 kg for seven satellites. Assume 500 kg for the adapter and 14600 kg for the Blok DM for a total inorbit mass of 19700 kg full. DV1 is 100 m/s; DV2 is 1.8km/s, mostly plane change. hence expect mass of 19140 and 11380 kg, leaving 6280 kg in the DM, so 3000 kg of prop unaccounted. Prop used is 560 and 7760 kg, at 22.8 kg/s this corresponds to 24 and 340s burn times. Actual burn times were 25s and 291s, corresponding to prop of 570 and 6635 kg, so the reconstruction seems not too far off.

Iridium SV009
Date	Time	Event	Orbit
1997 Jun 18	1402:45	T+0 Launch by Proton-K	KB
	1405:11	T+2:26 Stage 1 sep
	1408:16	T+5:38 Stage 2 sep
	1408:31	T+5:46 Fairing sep
	1412	Stage 3 MECO
	1412:36	T+9:51 Stage 3 sep	170 x 170 x 73
	1439:49	T+37:04 DM-5 burn 1
	1440:14?	DM-5 cutoff	170 x 516 x 73
	1523:17	T+80:32 DM-5 burn 2
	1528:57?	DM-5 cutoff	516 x 516 x 86.4
	1531	T+88:23 Iridium SV009 sep
		Iridium SV010 sep
		Iridium SV011 sep
		Iridium SV012 sep
		Iridium SV013 sep
		Iridium SV014 sep
		Iridium SV016 sep
	1559	T+1:57:26 DM-5 burn 3, deorbit
	1628	T+2:25:35 DM-5 reentry over Pacific
1997 Jun 18			94.86 502 x 520 x 86.4
1997 Jun 22			94.88 503 x 522 x 86.4
1997 Jun 28			94.92 504 x 524 x 86.4
1997 Jun 29	1323		95.22 525 x 533 x 86.4
1997 Jun 30	0317		95.85 555 x 563 x 86.4
1997 Jul 1	1404		95.87 560 x 561 x 86.4
1997 Jul 3	1620		97.85 654 x 657 x 86.4
1997 Jul 5	0416		98.28 675 x 677 x 86.4
1997 Jul 8	0434		99.16 716 x 719 x 86.4
1997 Jul 9	1522		100.17 765 x 767 x 86.4
1997 Jul 10	0953		100.37 767 x 784 x 86.4
1997 Jul 13	0311		100.38 774 x 778 x 86.4
1997 Jul 14	1420		100.39 775 x 778 x 86.4
1997 Jul 30			100.40 776 x 779 x 86.4
1998 Mar 2			100.40 776 x 779 x 86.4
2000 Sep 6			100.40 776 x 778 x 86.4

Viking 1

  1975-075A

---

The Viking A (Lander 2/Orbiter 2) payload was hurriedly replaced by Viking B (Lander 1/Orbiter 1) on the pad at Cape Canaveral in Aug 1975 because of a battery problem, after an initial countdown scrub on Aug 14.

The Titan Centaur took off on 1975 Aug 20 at 2122 and inserted Viking 1 into solar orbit. TC-4's insertion predicted closest Mars approach at 1976 Jun 20 2319 UTC at a distance of 32227 km (T=164486, R=-277133). After blowdown

A mid course correction on 1975 Aug 28 set course for Mars. Approach burns AMC1 and AMC2 were made on 1976 Jun 10 and Jun 15, with Mars orbit insertion on Jun 19. The MOI-1 burn on Jun 21 refined the orbit to 24.66h, 1513 x 32625 km x 37.9 deg, with periapsis at 23.2 deg latitude. MOT5 trim burn on Jul 9 and MOT6 on Jul 14 synchronized the orbit over the landing site. The lander was separated on Jul 20. The bioshield base was jettisoned into Martian orbit.

A trim burn on Aug 3 was followed by MOT7 on Sep 11, starting a drift orbit 21.88h, 1491 x 29510 km x 38.1 deg, with periapsis at 30.8 deg. On Sep 20 the orbit was synchronized again over the VL2 site. MOT 9 on Sep 24 trimmed the orbit.

The Viking Extended Mission began on 1976 Dec 14. Viking Orbiter 1 (VO-1) was used to study the Martian moon Phobos. MOT10 on 1977 Jan 22 put VO-1 on a Phobos approach orbit. On Feb 4 and 12 the MOT11, MOT12 burns synchronized the orbit with that of Phobos. On Feb 20, VO1 made a flyby of Phobos at a distance of 88 km.

Further MOT burns were made over the next few months including MOT15 to avoid Phobos and MOT16 to perform a radio occultation experiment. A series of experiments flying through the shadow of Phobos were carried out on Sep 20, 23 and 27.

The Viking Continuation Mission began on 1978 May 31 and lasted until 1979 Feb 26 when the Deep Space Network was required for the Voyager encounters. MOT17 on 1978 Dec 2 put VO1 in a slow walk, at 24.85h 260 x 34088 km x 39.9 deg, with a periapsis at 38.5 deg south latitude. VO1 reached its lowest periapsis of 234 km on 1979 Jan 22.

The Viking Survey Mission began on 1979 Jul 19, and was replaced by the Mapping Completion Mission on Nov 6. The MOT20 burn on 1979 Nov 6 moved the periapsis latitude to -4.7 deg. The Survey II mission lasted from 1980 Apr 23 to 1980 Jul 14, and on Jul 15 VO1 began the Termination Phase. Test burns on Jul 15-18 were followed by a propellant depletion burn on Jul 31. The last images were taken on 1980 Aug 5 and VO-1 was turned off on command at 2000 on 1980 Aug 7.

 

VO1
Date	Time	Event	Orbit
1975 Aug 20	2122:00	Launch by Titan IIIE
	2123:40	Heat shield jettison
	2123:51	Stage 1 burn
	2124:01	SRM sep
	2126:19	Stage 1 MECO
	2126:20	Stage 1 sep
	2126:20	Stage 2 burn
	2126:32	CSS fairing sep
	2129:40	Stage 2 MECO
	2129:54	Stage 2 sep
	2130:06	Centaur MES 1
	2132:11	Centaur MECO 1, 19 min coast	158 x 165 x 29.21
	2147:33	Centaur MES 2
	2152:48	Centaur MECO 2
1975 Aug 20	2156:31	Centaur sep	183 x -50629 x 29.3
	2158:42	Solar panels deploy
	2210:41	Centaur retro
	2214:52	Centaur retro cutoff
1975 Aug 20	2329:00	Bioshield cap sep
1975 Aug 21	0505?	Leave EL1:4
1975 Aug 21	0549?	Centaur leave EL1:4
1975 Aug 24	1220?	Leave Earth sphere
1975 Aug 24	1457?	Centaur leave Earth sphere
1975 Aug 27			1.00120 x 1.66788 x 4.48
1975 Aug 27	1830:11	MC1 targeting 4.6m/s 12s 6kg	1.00121 x 1.66898 x 4.48
1975 Sep 6	2010	Post MC1 periapsis
1975 Sep 6	2039	Pre MC1 periapsis
1976 Sep 17		Mass 3464 kg
1976 Jun 9		He leak discovered
1976 Jun 10		Approach	1773 x -20117 x 36.44
1976 Jun 10	1100	AMC1 3464 kg, 60 kg used, 50.5m/s 122.4s
1976 Jun 10		Approach	2113 x -20918 x 38.44
1976 Jun 15	1400	AMC2 3404 kg, 70 kg used, 60.0 m/s 143s
1976 Jun 15		Approach	2164 x -21518 x 38.01
1976 Jun 17	1130	In Mars SOI
1976 Jun 19	2220:43	MOI 37:49 1.097 km/s
1976 Jun 19	2258:32	MOI cutoff	42.4h 1514 x 50300 x 37.7
1976 Jun 21	1726:21	MOT1 80.0m/s	24.66h 1513 x 32625 x 37.9 23.2
1976 Jul 9	0040:00	MOT5 25.7m/s 41s out of sync
1976 Jul 14	0712:00	MOT6 2.7m/ssync over 47W
1976 Jul 20	0832:15	Sep from VO1
1976 Jul		Bioshield base sep
1976 Aug 3	0300:00	SKT-2 burn 2.2m/s, stationkeep with VL1
1976 Sep 11	1903:54	MOT7 21.3m/s	21.88h 1491 x 29510 x 38.1 30.8
1976 Sep 20	2215:29	MOT8 3.7m/s
1976 Sep 24	1510:00	MOT9 22.9m/s
1976 Dec 14		Viking Extended Mission
1977 Jan 22		MOT10 Phobos sync	23.05h 1480 x 30856 x 39.1 38.1
1977 Feb 4		MOT11 Phobos trim	23.05h
1977 Feb 12		MOT12 Phobos trim	23.05h
1977 Feb 13		P236 Phobos-1 174 km
1977 Feb 14		P237 Phobos-2 159 km
1977 Feb 15		P238 Phobos-3 153 km
1977 Feb 16		P239 Phobos-4 157 km
1977 Feb 17		P240 Phobos-5 153 km
1977 Feb 18		P241 Phobos-6 127 km
1977 Feb 19		P242 Phobos-7 103 km
1977 Feb 20		P243, Phobos-8 flyby 89 km
1977 Feb 21		P244 Phobos-9 104 km
1977 Feb 22		P245 Phobos-10 137 km
1977 Feb 22		P246 Phobos-11 174 km
1977 Feb 23		P247 Phobos-12 194 km
1977 Feb 24		P248 Phobos-13 204 km
1977 Feb 25		P249 Phobos-14 213 km
1977 Feb 26		P250 Phobos-15 225 km?
1977 Feb 27		P251 Phobos-16 255 km?
1977 Feb 28		P252 Phobos-17 290 km?
1977 Mar 11		MOT13	21.92 299 x 30750 x 39.2
1977 Mar 24		MOT14	23.50 303 x 32540 x 39.3
1977 May 15		MOT15 Phobos avoidance	23.50h 323 x 32520 x 39.2 36.8
1977 Jul 1		MOT16	23.97h 321 x 33050 x 39.2 32.7
1977 Sep 20		Phobos shadow pass
1977 Sep 23		Phobos shadow pass
1977 Sep 27		Phobos shadow pass
1978 May 31		Viking Continuation Mission
1978 Oct 19		Possible Phobos pass, 612 km
1978 Dec 2		MOT17	24.85h 260 x 34088 x 39.9 -38.5
1979 Feb 26		DSN to Voyager
1979 May 19		MOT18	24.99 329 x 34148 x 39.9 -29
1979 Jul 19		MOT19	24.79h 357 x 33925 x 39.9 -20.0
1979 Jul 19		Viking Survey Mission
1979 Nov 6		MOT20	23.95h 351 x 32997 x 38.0 -4.7
1979 Nov 6		Mapping Completion Mission
1980 Apr 19?		MOT-21 951 kg 15 m/s	24.52h 369 x ? x 38.9
1980 Apr 23		Survey II Mission
1980 Jul 15		Termination Phase
1980 Jul 15		Test	36.36h 373 x 47857 x 37.7 31.9
1980 Jul 17		Test	41.82h 375 x 51038 x 37.5 31.8
1980 Jul 18		Test	47.56h 351 x 56273 x 36.9 31.2
1980 Jul 31		Depletion	47.63h 411 x 56275 x 37.9 31.7
1980 Aug 7	2000	Turned off

Payload:

• Vidicon cameras (0.48m telescopes)

• IR radiometer 0.05m telescope A, 18-24 mu; 0.05m telescope B 9.8-12.5mu; 0.05m telescope C 6-15mu; 0.025m telescope D with 0.3-3mu bandpass.

• IR spectrometer

1975-075C

---

VL-1 (Viking Lander 1) landed on Mars on 1976 Jul 20. The VL has both deorbit engines and braking engines, built by RRC. The Aeroshell Base contains the four RCS deorbit engines, with two fuel tanks mounted on the aeroshell itself; the engines are monopropellant hydrazine with Isp = 160s. The three terminal descent (TD) engines on the lander are 2.7 kN thrust each. An upper atmospheric mass spectrometer is mounted on the aeroshell and returns data from 7000 to 100 km altitude.

On 1981 Jan 7 Viking Lander 1 was renamed the Thomas A. Mutch Memorial Station in honor of a member of the VL-1 team (1931-1980) who had been killed in a climbing accident. It returned its last image on Sol 2238, 1982 Nov 5, and stopped transmitting on 1982 Nov 13.

VL1
Date	Time	Event	Orbit
1976 Jul 20	0832:15	Sep from VO1
	0839:16	S+7:01 Deorbit 23 min burn 156m/s
	0901:35	S+29:20 Deorbit complete
	1135:08	Orient for entry
	1144	Alt 245 km	-100 x 30828 x 37.9
	1144:08	S+3:11:53 Entry 243.8km 4.6098 km/s -16.99 deg
	1151:06	S+3:19:02 Parachute deploy 5.9 km
	1151:13	Aeroshell base sep 5.0 km
	1151:25	Legs deployed
	1151:25?	Aeroshell top sep
	1152:19	Terminal descent 1.5 km
	1153:05	Touchdown LT=19min
	1159	Biology PDA lid deploy
1976 Jul 22	0719	Arm cover eject
1976 Jul 23	1138	GMCS lid deploy
1976 Dec 14		Viking Extended Mission
1980 Aug 7		Lander Monitor Mission
1981 Jan 7		Renamed Mutch Memorial Station
1982 Nov 13		End of transmissions?
1982 Nov 20		End of operations
1983 Jun		Mission ended

Payload:

• SNAP-19 RTG

• Itek facsimile cameras

• TRW biology unit

• XRFS X-ray flourescence spectrometer

• GCMS Gas Chromatograph Mass Spectrometer

Kosmos 585

  1973-064A

---

The second high orbit Sfera mission was Kosmos-585, launched in Sep 1973.

Kosmos-585
Date	Time	Event	Orbit
1973 Sep 8	0150:00	Launch by 11K65M	PL
	0152	Stage 2 burn
	0158	Stage 2 coast
	0248?	Stage 2 burn 2
	0248?	Stage 2 sep
	0930		113.63 1368 x 1416 x 74.0

STS-56 (Discovery)

 1993-023A

---

The STS-56 flight carried the Atlas Spacelab Earth observing payload on its second flight and the Spartan 201 free-flyer solar observatory.

Atlas-2 studied solar energy output, middle atmosphere chemistry, and the ozone layer. The ATMOS obtained atmospheric density profiles for dozens of trace gases up to 140 km, concentrating on the S hemisphere to complement Atlas-1's northern observations. The MAS obtained water, ozone and ClO profiles and the SSBUV measured ozone and also SiO2 pollution. ACR, SOLCON and SOLSPEC obtained the overall solar spectral energy distribution from IR to UV while SUSIM obtained UV data for cross-calibration with UARS.

The SAREX amateur radio system was used for the first Shuttle-Mir communication on Apr 10. An AEM with rodents was also carried in the middeck for life sciences studies.

STS-56
Date	Time	Event	Orbit
1993 Mar 2		Tow to VAB
1993 Mar 3		ET mate
1993 Mar 15		Rollout	LC39B
1993 Apr 6	0632	RSLS hold T-11s
1993 Apr 8	0529:00	Launch from LC39B
	0531:06	SRB sep
	0537:34	MECO	87.79 31 x 299 x 57.0
	0537:53	ET-54 Sep
	0606:07	OMS-2 2:30 77m/s
	0608:37	OMS-2 CO	90.42 290 x 299 x 57.0
	0704	Open PLBD
	0919	Activate Atlas-2
1993 Apr 10	1440		90.42 292 x 298 x 57.0
1993 Apr 11	0445	RMS unstow
	0522	RMS grapple Spartan
	0536	RMS unberth Spartan
	0611:33	Deploy Spartan
	0612?	RCS sep
	0705	SPTN at 1 km
	0729		90.46 292 x 301 x 57.0
	1359		90.47 293 x 301 x 57.0
1993 Apr 12	0550	RCS NSR (Nominal Slow Rate) 1m/s
	0728	RCS NPC (Nominal Plane Change) 1m/s
	0939:37	NC1 (Nominal Correction) OMS-3R phasing 8s 2m/s	90.36 288 x 296 x 57.0
	0939:45	OMS-3 CO
	1529		90.37 288 x 296 x 57.0
1993 Apr 13	0514	RCS burn
	0720:05	RMS grapple Spartan 201
	0801:38	RMS berth Spartan	90.41 291 x 297 x 57.0
1993 Apr 14	0600		90.41 291 x 297 x 57.0
1993 Apr 15	2159		90.41 292 x 296 x 57.0
1993 Apr 16	0445	Waveoff WX
	0603	RCS for crossrange 56s 5m/s	90.24 281 x 291 x 57.0
1993 Apr 17	0530	Atlas 2 powerdown
	0800	PLBD close
	1034:25	OMS DO (3:28) 115m/s
	1037:54	OMS cutoff	9 x 300 x 57.0
	1105:53	Entry, 122 km
	1137:19	Landed RW33 KSC
	1137:32	Chute
	1137:34	NGTD
	1138:01	Chute sep
	1138:21	Wheels stop
	1445	Tow to OPF/3

Kosmos 742

  1975-048A

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Kosmos-742
Date	Time	Event	Orbit
1975 Jun 3	1321	Launch by Soyuz-U	Plesetsk
	1325	Blok-I burn
	1329	Blok-I sep
1975 Jun 3			89.83 177 x 353 x 62.9
1975 Jun 4			89.83 178 x 353 x 62.9
1975 Jun 5		Lower perigee	89.29 145 x 333 x 62.8
1975 Jun 7			89.12 148 x 314 x 62.8
1975 Jun 9			89.02 147 x 304 x 62.8
1975 Jun 12		Raise apogee	89.36 147 x 338 x 62.8
1975 Jun 14			89.16 147 x 318 x 62.8
	2200	Engine sep
1975 Jun 15
	0446?	Deorbit
	0456?	PO sep
	0459?	Entry
	0516?	Landed