STS-61-B (Atlantis)

 1985-109A

---

The second flight of Atlantis was one of the most ambitious of the 1985 missions. Three PAM-D satellite deployments were followed by a pair of spacewalks to study on-orbit assembly. A single GAS can carried experiments by Canadian high school students. The Continuous Flow Electrophoresis System and a 3M experiment for Diffuse Mixing in Organic Solids (DMOS) flew on the middeck.

After launch on 1985 Nov 27, the Mexican Morelos communications satellite was deployed only 5 hours after payload bay door opening. Morelos was a standard American-built Hughes HS-376 model spinning comsat, but because of its presence the Mexican government had been invited to send along a payload specialist, Dr. Rodolfo Neri Vela. Dr. Neri carried out a series of mid-deck experiments under the MPSE (Morelos Payload Specialist Experiments) program, mostly life sciences related.

The following day, the Aussat satellite and the Satcom K-2 satellite were deployed.

Nov 29 saw the first spacewalk of the mission. Sherwood `Woody' Spring and Jerry Ross entered the payload bay and practiced assembling and disassembling two large structures mounted on a payload bay MPESS carried. ACCESS consisted of a truss structure made of many small components, while the rival EASE was a tetrahedron consisting of a few large tubes joined by special nodes. During the EVA, Spring carried out a small device called OET from the airlock, and jettisoned it into space by hand. The OET (OEX Target, Orbiter Experiments Target) was a radar target to allow Atlantis to perform rendezvous experiments.

After a day of rest, Spring and Ross returned to the bay for EVA-2. This EVA continued the work of the first, with the EASE and ACCESS structures being reassembled and disassembled.

Atlantis returned to Earth on Dec 3, landing at Edwards AFB.

STS 61-B
Date	Time	Event	Orbit
1985 Nov 8		Tow to VAB	VAB/3
1985 Nov 8		ET mate
1985 Nov 12		Rollout	LC39A
1985 Nov 27	0029:00	Launch from LC39A
	0031:03	SRB sep at 44.7 km
	0037:31	MECO at 109.9 km	88.63 63 x 350 x 28.5
	0037:49	ET sep at 112.1 km	88.72 69 x 353 x 28.5
	0109:24	OMS-2 (3:00) 85m/s
	0112:25	OMS-2 CO	91.66 353 x 359 x 28.5
	0202	PLBD open
	0746:50	Morelos deploy
	0802	OMS-3 (RH 13s) 3m/s	91.78 356 x 366 x 28.5
1985 Nov 28	0120:33	Aussat deploy
	0135	OMS-4 (RH 13s) 3m/s	91.90 364 x 370 x 28.5
	2157:31	Satcom deploy
	2213?	OMS-5 (LH 16s) 4m/s	92.04 368 x 381 x 28.5
1985 Nov 29
	2143	EVA-1 depress?
1985 Nov 29	2145	EVA-1 (05:32)
	2147	Hatch open
		Spring, Ross egress
	2200?	Begin ACCESS experiment
	2245?	ACCESS assembled bays 1-10
		Disassemble ACCESS
	2311	Stow ACCESS
	2316	at PSA
1985 Nov 29	2330?	EASE experiment
		Assemble/disassemble 6 times
	2335?	Cycle 1
	2350?	Cycle 2
1985 Nov 30	0010?	Cycle 3
	0030?	Cycle 4
	0050?	Cycle 5
	0115?	Cycle 6
	0130?	Cycle 7
	0155?	Cycle 8
	0215?	Stow EASE
	0224	In airlock
	0225	Obtain AAPS target (OET)
1985 Nov 30	0230	OET deployed by Spring	92.06 368 x 382 x 28.5
	0240	Moving RMS for OEX deploy obs
	0255	Target stable
	0310	Ingress procedures
	0317	End EVA-1
	0323	Repress
	0816?	Stationkeep with OET (DAP test) at 10m
	1130	End OET test	92.08 368 x 383 x 28.5
1985 Dec 1	0140?	OMS-6 (RH 49s) 15m/s	91.60 322 x 383 x 28.5
	2022	Depress?
	2023	Hatch open?
1985 Dec 1	2030	EVA-2 (06:38)
	2030?	Spring, Ross egress
	2037	Working with MFR
	2050?	MFR grapple
	2100?	ACCESS configured, built 1-9
	2129?	Getting in MFR
	2130?	EV-1 in MFR, built bay 10
	2230?	EV-1 manipulate ACCESS from MFR
	2240?	EV-1 off MFR
	2245?	EV-2 on MFR
	2250?	Disassemble bay 10
		Task work on bay 8
	2330?	Rebuild bay 10
	2340?	EV-2 on MFR manipulate ACCESS
	2350?	Disassemble ACCESS
1985 Dec 2	0000?	EV-2 off MFR
	0010?	Stow ACCESS, unstow EASE
	0015?	EV2 on MFR
	0030?	Work with heat pipe assembly
	0045?	Build EASE
	0100?	EV2 manipulate EASE
	0110?	EV2 off MFR, EV1 on
	0115?	EV1 manipulate EASE
	0145?	EV1 in MFR disassemble EASE
	0155?	EV1 build heat pipe
	0215?	EV1 egress MFR
	0225?	Stow EASE
	0230?	Stow MFR
	0230	Cleanup
			332 x 382 x 28.5
	0256?	Ingress
	0258	HC
1985 Dec 2	0308	End EVA-2
1985 Dec 3	1716	PLBD close	91.62 322 x 384 x 28.5
1985 Dec 3	2026:45	OMS DO (169s) 96 m/s
	2029:34	OMS DO CO
	2103:17	Entry
	2133:49	Landed at RW22 EAFB
	2134:00	NGTD
	2135:07	Wheels stop
1985 Dec 7	1430	SCA takeoff	EAFB
	1750	SCA landing	Kelly AFB TX
	1932	SCA takeoff
	2215	SCA landing	KSC SLF
1985 Dec 8	0330	Tow to OPF

Kosmos 205

  1968-016A

---

Zenit-2 No. 58 was launched in Mar 1968 from Plesetsk. It landed 300 km W of Tselinograd at 50 58 N 67 09 E.

Kosmos-205
Date	Time	Event	Orbit
1968 Mar 5	1230	Launch by 11A57	NIIP-53 LC41/1
	1234	Blok-I burn
	1239	Blok-I sep	89.4 199 x 292 x 65.7
			89.4 201 x 310 x 65.7 (TASS)
	1514		89.39 196 x 292 x 65.7
1968 Mar 11	1709		89.24 193 x 280 x 65.6
1968 Mar 13	0621?	Deorbit
	0621?	PO sep
	0645	Landed after 7.76d

Parcae 1

  1976-038A

---

The first PARCAE satellite was launched on 30 Apr 1976. According to the NRL list, the dispenser was designated MSD (Multiple Satellite Dispenser) and operated for 41 days.

PARCAE 1
Date	Time	Event	Orbit
1976 Apr 30	1912	Launch by Atlas F
	1914	T+2:04 Booster sep
	1914	T+2:24 Fairing
	1917	T+5:21? SECO
	1917?	Atlas sep	-790? x 1050 x 63.5
	1939?	Kick stage burn
	1941?	Plume shield sep
1976 May 12?		PL181 deployed
1976 May 12?		PL183 deployed
1976 May 13?		PL182 deployed
			107.5 1092 x 1128 x 63.5
1976 Jun 10		end of transmissions

Hollywood Confidential

https://welib.org/md5/1bc3e1fae114b88f425a1e70ccaf4945

Kosmos 884

  1976-123A

---

N. Johnson reports that Kosmos-884 was destroyed on Dec 29 after recovery failed, according to Russian sources. The absence of the usual signs of such a failure makes me wonder if the claim could be an error for another satellite.

Kosmos-884
Date	Time	Event	Orbit
1976 Dec 17	0930	Launch by Soyuz-U	Baikonur
	0934	Blok-I burn
	0938	Blok-I sep
1976 Dec 17			89.62 167 x 344 x 65.1
1976 Dec 18			89.33 165 x 318 x 65.0
1976 Dec 23			89.23 164 x 307 x 65.0
1976 Dec 24			89.68 169 x 347 x 65.0
1976 Dec 25			89.66 169 x 336 x 65.0
1976 Dec 26		Change orbit	89.83 170 x 361 x 65.0
1976 Dec 27		Change orbit	89.39 169 x 319 x 65.0
1976 Dec 28		KDU ejected
1976 Dec 29	0601?	Deorbit
	0611?	PO sep?
	0615?	Entry?
	0631?	Landed

Kosmos 2311

 1995-014A

---

Kosmos-2311 flew a 70 day mission in spring 1995. It was kept within a relatively narrow orbital altitude range.

Kosmos-2311
Date	Time	Event	Orbit
1995 Mar 22	1644:59	Launch by Soyuz-U
	1653	Blok-I sep
1995 Mar 22			89.54 167 x 335 x 67.2
1995 Mar 30			89.02 161 x 289 x 67.1
1995 Mar 30		Orbit raise	90.10 170 x 388 x 67.2
1995 Apr 11			89.49 165 x 333 x 67.1
1995 Apr 11		Orbit raise	89.70 178 x 340 x 67.1
1995 Apr 14		SpK-1 fiducial
1995 Apr 18			89.41 174 x 315 x 67.1
1995 Apr 18		Orbit lower	88.89 170 x 267 x 67.1
1995 Apr 20			88.84 172 x 261 x 67.1
1995 Apr 20		Orbit raise	90.02 175 x 374 x 67.1
1995 Apr 29			89.57 171 x 335 x 67.1
1995 Apr 30		Orbit raise	89.82 181 x 349 x 67.1
1995 May 5			89.59 179 x 328 x 67.1
1995 May 5		Orbit raise	89.76 179 x 347 x 67.1
1995 May 8		SpK-2 fiducial
1995 May 12			89.50 176 x 322 x 67.1
1995 May 12		Orbit raise	89.76 185 x 339 x 67.1
1995 May 19			89.47 182 x 314 x 67.1
1995 May 20		Orbit raise	89.98 193 x 353 x 67.1
1995 May 27			89.72 184 x 337 x 67.1
1995 May 27		Orbit lower	89.60 178 x 330 x 67.1
1995 May 31			89.44 177 x 315 x 67.1
1995 May 31
	1739?	Deorbit
	1754?	Entry
	1805?	Landed

USA-67

 1990-097B

---

The USA-67 spacecraft was launched in Nov 1990 aboard Shuttle mission STS-38. The Space Command satellite catalog lists the STS-38 flight, 1990-97A/20935, in a 219 x 261 km x 28.5 deg orbit with a recovery date of 1990 Nov 20. It also lists payload USA 67 (1990-97B/20963), cataloged on Nov 27, and two rocket bodies USA 67 R/B(1) (1990-97C/20964) and USA 67 R/B(2) (1990-97D/20965). The orbits of objects 20963-20965 are classified. This is all that is known officially about USA 67.

The Oct 22, 1990 issue of Aviation Week reported that the payload was designated Air Force Project 658, and had a gross weight of 22000 lb. It would be placed in an orbit with an altitude of 400 nautical miles, using an upper stage. The payload carried digital cameras and other sensors.

The Aviation Week article said ``The Defense Dept. satellite ... will focus on the Persian Gulf region to provide both strategic and tactical recon information for Desert Shield air and ground commanders.''. It futher said, referring to the quoted gross weight, ``Existing launch system/upper stage combinations cannot put this much weight into geosynchronous orbit, ...''.

There are a couple of problems with these statements. First, it seems likely that the gross weight quoted includes the upper stage, in which case the mass could be comparable to a TDRS geosynchronous mission. Quoting payload weights inclusive of the upper stage is not unusual in the NASA Shuttle program. So a geosynchronous mission cannot be ruled out on this basis. Secondly, it seemed implausible that a mission dedicated to Desert Shield could be launched so quickly, especially since it had been sitting on the launch pad since before the invasion of Kuwait - the launch was delayed for 4 months due to hydrogen leaks in the Shuttle. Further, the low inclination of 28.5 degrees is barely enough to see Iraq - Baghdad is at 34 degrees north latitude. Why not launch such a payload to a slightly higher inclination?

Therefore, most analysts at the time discounted the Aviation Week story and assumed that the 28.5 degree inclination meant a geosynchronous payload. The presence of two rocket stages was consistent with an IUS launch, which made the most probable payload a MAGNUM signals intelligence satellite like those flown on missions 51-C and STS-33.

However, I later found evidence that only three classified STS/IUS missions were flown: 51-C, 51-J, and STS-33. All other IUS flights are accounted for. Therefore, (as suggested by D-Day a couple of years ago) the STS-38 mission did not fly an IUS. This makes a geostationary payload less likely and the Aviation Week story regains plausibility. Perhaps the AFP-658 payload was modified during the hydrogen leak standdown to observe the Gulf region. It would be interesting to see if there is any evidence that the original July flight plan for STS-38 involved a higher inclination flight. The presence of two rocket bodies implies the use of solid perigee and apogee motors rather than liquid engines (you would only need a single, restartable, liquid engine). We must imagine a large payload and a relatively small pair of kick stages. Presumably these would not be spin stablized as there would be no mechanism to fit a spin table of that size in the Orbiter. The most probable upper stage configuration is therefore something like the SGS-II which involved a pair of Star 48 motors (the same motors used in the spin-stabilized PAM-D). This dual stage rocket was used for Navstar launches on Atlas, and would take up about half the quoted weight. What was the payload? It might be similar to the USA 53 payload launched in Feb 1990 on STS-36, which was later found in an 800 km high orbit, not too far off the claimed 400 naut. mi. for STS-38's payload. However this doesn't square with the two rocket bodies, which were not cataloged for USA 53. The low inclination makes USA 67 hard to see for high latitude observers, explaining why it has not been tracked yet by amateurs.

The UN submission quoted an orbit of 78 x 226 km x 28.5 deg. This represents the orbit of the Shuttle prior to the OMS-2 burn, long before deployment of USA 67, and clearly represents deliberate disinformation.

A new identification for USA 67 emerged in 1996 during an anti-discrimination suit by Hughes employees, when satellites referred to as B-1 and B-2 were discussed. It seems likely that B-1 was USA 40 and B-2 was USA 67. This suggests that USA 67 may have been a version of the SDS-II modified for geostationary use. The court documents reported `launch of the B-2 satellite in Winter of 1990 ... was mistimed, satellite fuel was consumed improperly, leaving little to reach its projected orbit', allegedly as the result of incompetence by managers appointed after the demotion of Hughes' first black manager, who had been in charge of some aspect of the project.

Another interpretation has been advanced in which the second rocket stage is for a second, uncataloged NRO payload, and the SDS-II had LEASAT-style liquid apogee engine.

USA 67
Date	Time	Event	Orbit
1990 Nov 16	0656?	Deploy from OV-104	217 x 268 x 28.5
1990 Nov 17	0130?	Solid motor 1 burn	240 x 7500?
	0131?	Burnout
	0345?	Apogee 1
	0140?	PKM sep	220? x 7930? x 28.5
1990 Nov 17		GEO?

Scene One,Take Two

https://welib.org/md5/e713cc0509d4d0407c1a50eec36ea1d7

Reference Books Bulletin 1992-93

 https://welib.org/md5/4336a60e483119e112f98b6f9e0118f1

HCMM

 1978-041A

---

Applications Explorer Mission A (AEM-A) was the Heat Capacity Mapping Mission (HCMM). HCMM's mission was to generate thermal maps, carry out thermal source location, and study plant canopy temperature, soil temperature cycle, thermal effluents, feasibility of remote sensing geothermal source locator, and snow field studies. It was launched on 1978 Apr 26 by a Scout D-1 from Vandenberg into a 96.7 min, 560 x 641 km x 97.6 deg. Operations with HCMM began on 1978 May 11. By June the internal propulsion system had raised the orbit to 607 x 630 km x 97.6 deg. A small burn was made on 1979 Mar 7. HCMM transmitted until 1980 Sep 15 and reentered on 1981 Dec 22.

HCMM
Date	Time	Event	Orbit
1978 Apr 26	1020	Launch by Scout D-1	V SLC5
		T+1:23 St 1 burnout
		T+1:28 St 1 sep
		T+1:35 St 2 burn 39s
		T+2:06 St 2 burnout
		T+2:31 Fairing
		T+2:33 St 2 sep
		T+2:33 St 3 burn
		T+3:06 St 3 burnout 182 km 5.546 km/s
		T+9:49 Spinup
	1029	T+9:51 St 3 sep
	1029	T+9:55 St 4 burn 33s 621 km 4.805 km/s
	1030	T+10:29 St 4 burnout 621 km 7.547 km/s
	1035	T+14:51 St 4 sep
	1035	T+14:56? Despin
		Solar arrays deploy
1978 Apr 26			96.67 548 x 649 x 97.6
1978 Apr 27			96.80 561 x 649 x 97.6
1978 May 3		Operational orbit achieved	97.15 605 x 639 x 97.6
1978 Nov 22			97.16 614 x 630 x 97.6
1979 Mar 6			97.13 614 x 627 x 97.6
1979 Mar 7			97.16 618 x 627 x 97.6
1980 Feb 6			97.13 615 x 626 x 97.6
1980 Feb 20			97.12 615 x 625 x 97.7
1980 Feb 21			97.00 609 x 620 x 97.7
1980 Feb 24			95.57 539 x 551 x 97.7
1980 Mar 12			95.54 537 x 552 x 97.7
1980 Sep 14		end of ops
1980 Sep 21			95.51 538 x 548 x 97.7
1980 Oct 3			95.38 533 x 540 x 97.7
1980 Dec 14			95.08 521 x 523 x 97.7
1981 Jul 21			93.86 461 x 465 x 97.7
1981 Dec 14			90.25 279 x 293 x 97.7
1981 Dec 22		reentered

Rhyolite 2

  1973-013A

---

Rhyolite 2 was a US Air Force electronic intelligence satellite launched from Cape Canaveral aboard an Atlas Agena-D rocket. It was placed in a geosynchronous orbit.

Rhyolite 2
Date	Time	Event	Orbit
1973 Mar 6	0930	Launch by Atlas Agena D	CC LC13
	0932	Atlas BECO
	0932	Atlas booster sep
	0933	Atlas SECO
	0936	Atlas sep
	0936	Agena burn 1
	0936?	Fairing
	0939?	Agena MECO-1	178 x 180 x 28.5 ?
	1042?	Agena MES-2
	1044?	Agena MECO-2	178 x 33700? x 28.2
	1045?	Agena sep
		LAM-1
			1435.1 35679 x 35855 x 0.2
1973		GEO for W USSR	GEO 70E

Venera 13

 1981-106A

---

4V-1 No. 760 (Venera-13) was launched in Oct 1981 as the first of two Venera-81 probes.

Venera-13
Date	Time	Event	Orbit
1981 Oct 30	0604	Launch by Proton-K	KB
		T+2m St 1 sep
		T+5m St 2 sep
		T+5m GO sep
	0613	T+9m St 3 MECO
	0617?	Blok-D burn 1
	0619?	Blok-D MECO-1
	0724?	Blok-D burn
	0727	Solar orbit injection
	0732?	Blok-D cutoff, solar orbit	180 x -61780?
	1520	Pass EL1:4
1981 Nov 3	0845?	Pass L1 distance
1981 Nov 10	0900	TCM 2.60m/s
1982 Feb 21	0430	TCM 5.16m/s
1982 Feb 27	0251	SA sep
	0253	Divert burn 224.35m/s
1982 Feb 26	1540	Enter Venus sphere
1982 Mar 1	0351:51	Flyby
1982 Mar 3	1600?	Exit Venus sphere
1982 Jun 10	0400	Vega test burn 192m/s	107 x 168 Mkm x 5 deg
1983 Jan			0.72 x 1.13 AU x 5.4 deg

1981-106D

---

Venera-13 landed at 7 30 S 303 05 W. At the landing site the temperature was 738 K and the pressure was 89.5 bar.

Venera-13 SA
Date	Time	Event	Orbit
1981 Oct 30		Launch
1982 Feb 27	0251	Sep from Venera-13
1982 Mar 1	0251	Entry
	0255:00	Entry -18.7 deg 11.2 km/s
	0255:40	Entry 125.0 km 11.194km/s -18.68 deg at 305.0 -6.5	-427 x -44046 x 135?
		Braking at 65 km
	0256:16	Parachute deployed
	0309	Parachute sep
	0357:21	Landed -7.5, 303 05
	0358	Soil sampling
	0604	end of ops

Kosmos 1051

 1978-109A

---

Kosmos-1051 was satellite 1 of Strela-1M octuplet no. 21.

Kosmos-1051
Date	Time	Event	Orbit
1978 Dec 5	1812	Launch by 11K65M	PL
	1814	Stage 2 burn 1
	1819	T+7m Stage 2 MECO-1
		Stage 2 burn 2
	1910?	T+58m? Stage 2 sep
1979 Jan 16			114.72 1397 x 1487 x 74.02

Kosmos 1961

 1988-066A

---

Geizer No. 16L was launched in Aug 1988 as Kosmos-1961. It was stationed at 14W by Aug 25. In 1992 it was moved to 80E, where it operated until mid-1993.

Kosmos-1961
Date	Time	Event	Orbit
1988 Aug 1	2104:00	Launch by Proton	KB
	2113	Stage 3 sep	88.25 184x192x51.6
	2220?	DM burn 1
1988 Aug 2	0343?	DM burn 2
	0347?	DM sep
1988 Aug 4			1463.07 36213 x 36412 x 1.5 GEO 72.6E
1988 Aug 25			1435.96 35777 x 35780 x 1.4 GEO 13.9W
1988 Oct 31			1436.10 35768 x 35805 x 1.2 GEO 13.9W
1989 Sep 6			1436.15 35775 x 35799 x 0.5 GEO 14.0W
1990 May 3			1436.11 35768 x 35804 x 0.2 GEO 13.6W
1991 Jan 2			1436.09 35761 x 35811 x 0.8 GEO 13.6W
1992 Feb 13			1436.08 35764 x 35808 x 1.8 GEO 13.7W
1992 Mar 2			1436.09 35764 x 35808 x 1.8 GEO 13.6W
1992 Mar 5		mv out
1992 Apr 13		mv in
1992 Apr 18			1435.76 35776 x 35783 x 1.9 GEO 80.3E
1992 Jun 23			1436.17 35781 x 35794 x 2.1 GEO 79.8E
1993 Apr 6			1436.14 35777 x 35797x 2.8 GEO 79.8E

Kosmos 9

  1962-048

---

Zenit-2 11F61 No. 7 (Kosmos-9) flew from 1962 Sep 27 to Oct 1. It carried supplementary sodium iodide and cesium iodide radiation counters to study the radiation belts. 

Kosmos-9
Date	Time	Event	Orbit
1962 Sep 27	0940	Launch by Vostok	KB LC1
	0944	Blok-A sep
	0949	Blok-E sep
1962 Sep 27			90.9 301 x 358 x 65.0 (TASS)
	2008		90.88 299 x 336 x 65.0
1962 Sep 28			90.9 292 x 346 x 65.0 (RAE)
1962 Sep 29	1907		90.90 297 x 339 x 65.0
1962 Oct 1	0900?	Deorbit
	0905?	PO sep
	0923	Landed near Kustanai

ESSA 5

  1967-036A

---

ESSA V was another global weather monitoring satellite with an AVCS camera system. Launched from Vandenberg on 1967 Apr 20, it entered a 1361 x 1423 km x 102.0 deg orbit and replaced ESSA III. It transmitted until 1970 Feb 20.

ESSA 5
Date	Time	Event	Orbit
1967 Apr 20	1121:10	Launch by Delta E	V SLC2E
		T+0:43 SRM out
		T+1:10 SRM sep
	1123:42	T+2:32 Thor S/N 20215 MECO
		T+2:34 Thor sep
	1123	T+2:34 Delta S/N 20214 burn 6:11
		T+2:38 Fairing sep
	1129:59	T+8:49 Delta SECO V=5.87 km/s
	1139:33	T+18:23 X-258C4 RH141 burn 23s
	1139:56	T+18:46 X-258 burnout	1361 x 1423 x 102.0
	1141:18	T+20:08 X-258 sep
1967 Apr 24		Cameras on
1967 May 8		To ESSA,replaced ESSA 3
1970 Feb 20		end of tx

Progress M-4

 1990-072A

---

Progress M 11F615A55 No. 204 (Progress M-4) was launched in Aug 1990. It docked with Mir on Aug 17 delivering 2689 kg of cargo. After undocking on Sep 18 it carried out the Fokus plasma gun experiment injecting plasma into the ionosphere. One debris object was cataloged prior to reentry, possibly related to Fokus. 

Progress M-4
Date	Time	Event	Orbit
1990 Aug 15	0400:38	Launch by Soyuz-U	KB
	0405	Blok-I burn
	0409	Blok-I sep
	0840		88.52 183 x 219 x 51.61
	1200		89.70 249 x 269 x 51.60
1990 Aug 16	0700		89.73 250 x 271 x 51.61
1990 Aug 17	0230		89.71 249 x 270 x 51.61
	0526:18	Docked with Mir DP1
1990 Aug 18	1000		92.03 367 x 380 x 51.61
1990 Sep 17	1242:43	Undocked
1990 Sep 18	0500		92.37 373 x 407 x 51.61
	0620	Fokus plasma source release
1990 Sep 19	1730	Object 72C tracked
1990 Sep 20	1105	Retrofire
	1142:49	Reentered over Pacific

Kosmos 1008

 1978-049A

---

This was the third Tselina-OK satellite.

Kosmos-1008
Date	Time	Event	Orbit
1978 May 17	1439	Launch by 11K65M	Plesetsk
	1441	S3 burn
	1447?	T+8m? S3 MECO-1
	1512?	T+33m? S3 MES-2
	1512?	S3 sep
1978 May 17			95.1 499x549x74.0
1981 Jan 8		reentered

Meteor-1 18

  1974-052A

---

Meteor 11F614M No. 24 was launched on 1974 Jul 9. It was a prototype of the new Meteor-Priroda series. The satellite was later given the designation Meteor-Priroda 11F651 No. 1. It was the second mission to carry a low thrust plasma engine. 

Meteor-Priroda No. 1
Date	Time	Event	Orbit
1974 Jul 9	1440	Launch by Vostok 8A92M	PL
	1444?	Blok E burn
	1450?	Blok E sep
			102.6 865 x 893 x 81.2
1975 Nov			103.1 890 x 918 x 81.2
1976 Oct 28		end of ops

Kosmos 305

  1969-092

---

Kosmos-305 (E-8-5 No. 404) suffered the same fate as Kosmos-300 in the following month's launch window. Various reports claimed that the Blok-D disintegrated or that the payload may have entered a high orbit, but the modern consensus seems to be that the second burn was cut short and occurred at the wrong orientation, with rapid reentry of the payload and Blok-D.

Kosmos-305
Date	Time	Event	Orbit
1969 Oct 22	1409:59	Launch by Proton-K	KB LC81
	1412?	Stage 2 burn
	1415?	Stage 3 burn
	1419	Stage 3 sep	-800? x 210 x 51.5
	1425?	Blok-D burn 1
	1427?	Blok-D cutoff 1, parking orbit	182 x 210 x 51.5?
	1436?	Stage 3 reentry
	1520?	Blok-D burn 2
	1520?	SOZ burn
	1520?	SOZ sep (92A/B)
	1530?	Blok-D MECO?	70? x 187? x 51.5
	1615	Reentry over Australia?

IRS-1A

 1988-021A

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IRS-1A took off from Baikonur aboard a Vostok 8A92M on a southbond trajectory to polar sun-synchronous orbit.

IRS-1A
Date	Time	Event	Orbit
1988 Mar 17	0643:30	Launch by Vostok 8A92M	KB LC31
	0645:30	Blok-BVGD sep (T+2:00)
	0646:30	Fairing sep (T+3:00), 160 km
	0648:40	Blok-A cutoff, Blok-E burn (T+5:10)
	0654:30	Blok-E cutoff (T+11:00)
	0654:40	Payload release (T+11:10)
			102.82 870 x 914 x 99.0
1988 Apr 7		Complete orbit maneuvers
1991		Still operating
1995 Mar 17		On standby status

Payload:

• Radiometers

• LISS cameras - linear imaging self scanning CCD

• LISS 1: 72m res, 148 km swath, 4000-9000A in 4 bands

• LISS 2: 36m res, 74 km swath, 4000-9000A in 4 bands