Anik D2

 1984-113B

---

Anik D-2 was the second HS-383 class satellite built by Spar Aerospace. It was owned by Telesat Canada at the time of launch, from Shuttle mission 51-A.

Anik D-2
Date	Time	Event	Orbit
1984 Nov 9	2105	Deploy from OV-103
	2149	PAM-D burn
	2150	PAM-D burnout
	2152	PAM-D sep
1984 Nov 10	0700		638.92 306 x 36083 x 25.7
1984 Nov 10	1326		653.81 1065 x 36084 x 22.5
1984 Nov 11			653.72 1062 x 36083 x 22.5
1984 Nov 12	0927?	Star 30B burn at 6th apo
1984 Nov 12			1379.16 33232 x 36097 x 1.6 GEO 134.4W+14.9E
1984 Nov 13	1000?	TCM
1984 Nov 13			1419.46 34816 x 36104 x 1.9 GEO 116.7W+4.2E
1984 Nov 14			1436.15 35769 x 35806 x 1.9 GEO 111.6W
1984 Nov 19		On-orbit storage	GEO 111.5W
1985 Mar 8		Depsin system problems
1985 Oct 17			1436.08 35779 x 35792 x 1.5 GEO 111.5W
1986 Aug 18			1436.01 35775 x 35793 x 0.7 GEO 111.6W
1986 Aug		mv out to 110.5W
1986 Sep 30		mv in	1435.99 35774 x 35794 x 0.6 GEO 110.5W
1986 Nov 18		In service, repl. Anik B
1986 Nov 20			1436.08 35774 x 35797 x 0.1 GEO 110.4W
1987 Nov 14			1436.10 35783 x 35789 x 0.1 GEO 110.5W
1989 May 11			1436.09 35779 x 35793 x 0.1 GEO 110.5W
1990 Feb 15			1436.08 35734 x 35838 x 0.0 GEO 110.4W
1990 May 10		Slow drift to 111W	1436.09 35759 x 35813 x 0.1 GEO 110.7W
1990 Oct 24			1436.08 35769 x 35803 x 0.1 GEO 110.8W
1991 Oct 26			1436.09 35776 x 35796 x 0.0 GEO 111.0W
1991 Oct		Leased to GE Americom
		Renamed Satcom 4R
1991 Nov 8			1436.08 35773 x 35799 x 0.1 GEO 111.0W
1991 Nov 16		mv out	1430.74 35659 x 35704 x 0.2 GEO 101.3W+1.3E
1991 Dec 13		mv in	1436.12 35781 x 35792 x 0.0 GEO 82.0W
1993 Jan 9			1436.14 35781 x 35793 x 0.0 GEO 82.0W
1993 Apr 2			1436.15 35785 x 35790 x 0.1 GEO 82.1W
1993 Apr 5		mv out
1993 Apr		Returned to Telesat Canada
1993 Jul 5			1432.86 35709 x 35737 x 0.4 GEO 3.0W
1993 Aug 3		Leased to Arabsat
		Renamed Arabsat 1D
1993 Aug 16		mv in	1436.08 35782 x 35790 x 0.5 GEO 20.0E
1994 Jul 4			1436.05 35770 x 35800 x 1.0 GEO 20.0E
1994 Jul 17		mv out (misid?)	1436.73 35542 x 36055 x 1.1 GEO 19.1E+0.1W
1994 Aug 18		(misid?)	1438.01 35816 x 35831 x 0.1 GEO 18.1E+0.5W
1994 Sep 6			1436.10 35776 x 35797 x 1.2 GEO 20.0E
1994 Nov 6			1436.05 35706 x 35864 x 1.3 GEO 19.9E
1995 Jan 22			1436.08 35736 x 35836 x 1.5 GEO 20.0E

Mars 1B

  1960-F14

---

1M No. 2 was launched a few days after 1M No. 1 and was also a failure. The new Blok-I stage, on its second flight, failed to ignite its 8D715K engine and the Mars probe was lost. A leaky oxygen valve had caused the kerosene in the engine pump inlet to freeze while the rocket was on the pad. 

1M No. 2
Date	Time	Event	Orbit
1960 Oct 14	1351:03	Launch by 8K78	KB LC1
	1355	Blok-A sep
	1355:53	Blok-I failed to ignite T+290s

Dynamics Explorers 1/2

 1981-070A

---

Dynamics Explorer 1 (DE 1, DE-A, Dynamics Explorer A) was one of a pair of space science satellites and was designed to study the solar wind, the ionosphere, and the magnetosphere. The 409 kg NASA-GSFC satellite was built by RCA. Both satellites were launched on a single Delta 3913 launch vehicle at 0956 on 1981 Aug 3. The first Delta burn was completed at 1004:39; the stage coasted in parking orbit and then restarted at 1008:28. However the Delta had not been correctly fuelled, and the engine cut off when the tank ran dry at 1010:35, leaving the payload in an unexpectedly low 382 x 969 km x 89.9 deg orbit. DE-B separated at 1011, and at 1037 the DE-A/Star 37N combination separated from the Delta and the Star 37N third stage ignited. The Star 37N was developed for the Japanese N vehicle and this was its only flight on the Delta. DE-A separated from the third stage at 1039, in a 440.0 min, 675 x 24875 km x 90.0 deg orbit. It operated until 1991 Feb 28.

DE-A mass was 424 kg. DE-B mass was 420 kg. DE-A had two 4.0m antennae one 5.8m loop antenna, and two 100m electric field wire antennae (200m tip to tip)

SAI had three optical systems - two in the 3175-6300A range and one in the 1200-1800A range. FOV was 0.3 deg; they had long collimators, and small off-axis focussing mirrors.

DE 1
Date	Time	Event	Orbit
1981 Aug 3	0956:00?	Launch by Delta 3913	CC LC17
		T+0:57 SRM 1-6 burnout
		T+1:00 SRM 7-9 burn
		T+1:18 SRM 1-6 sep
		T+1:58 SRM 7-9 burnout
		T+2:03 SRM 7-9 sep
		T+3:46 MECO
		T+3:59 St 2 SES
	1000:04	T+4:04 Fairing sep
	1004:39	T+8:39 SECO-1	163 x 330 x 90.0
	1008:28	T+14:10s SES-2
	1010:35	SECO-2	(306 x 1300 x 90.0) (plan)
	1015:10?	T+19:10 DE-B sep	301 x 1006 x 90.00
	1018:55	T+22:55 DE-B PAF sep
	1036:37	T+40:37 St 2 sep
	1037:18	T+41:18 St 3 ignition
	1037:59	T+41:59 St 3 burnout
	1039:15	T+43:15 St 3 sep from DE-A	440.0 675 x 24875 x 90.0
	1130?	St 2 depletion?	98.17 380 x 962 x 90.0
1981 Aug?		Booms deployed
1991 Feb 28		DE-A end of tx

Payload:

• RIMS Retarding Ion Mass Spectrometer (MSFC/Chappell)

• EICS Energetic Ion Mass Spectrometer (Lockheed/Shelly)

• HAPI High Altitude Plasma Instrument (SWRI/Burch)

• SAI Spin scan Auroral Imager (Iowa/Frank)

• MAG-A Fluxgate magnetometer (GSFC/Sugiura)

• PWI Plasma wave detector (Iowa/Shawhan)

1981-070B

---

DE 2 (DE-B, Dynamics Explorer B) was designed to study the composition of the neutral atmosphere and measure upper atmosphere temperatures, winds, and suprathermal ion flow. The 403 kg satellite was built by RCA. Launched with DE 1 on 1981 Aug 3, it separated from the Delta second stage at 1011 into a 97.66 min, 298 x 996 km x 90.0 deg orbit. It was still transmitting when it reentered on 1983 Feb 19.

The satellite has 6 11-m booms, one 6-m boom.

Payload:

• LANG Langmuir probe (GSFC/Brace)

• RPA Retarding potential analyser (UTD/Hanson)

• IDM Ion drift meter (UTD/Heelis)

• MAG-B Fluxgate magnetometer (GSFC/Sugiura)

• VEFI Vector electric field detector (GSFC/Maynard)

• NACS Neutral atmosphere composition spectrometer (UM/Carignan)

• WATS Wind and temperature spectrometer (GSFC/Spencer)

• FPI Fabry-Perot interferometer (UM/Hays)

• LAPI Low altitude plasma instrument (electrons, ions) (SWRI/Winningham)

The Story of Mankind

 https://gutenberg.org/files/754/754.txt

Gorizont 6

 1982-103A

---

The sixth Gorizont satellite (11F662 No. 16) was launched by Proton from Baikonur on 1982 Oct 20.

Gorizont 16
Date	Time	Event	Orbit
1982 Oct 20	1626:00	Launch by Proton	KB
	1635	Stage 3 sep	183 x 208 x 51.6
	1743?	DM burn 1	295 x 35808 x 47.3
	2258?	DM burn 2
	2303?	Blok-DM No. 37L sep
1982 Oct 20			1435.07 35706x35834x0.4 GEO 91E dr
1982 Oct 26		On station at Statsionar 6	1435.92 35749x35824x0.8 GEO 89.5E
1982 Nov 1			1435.97 35745 x 35822 x 0.8 GEO 89.7E
1983 Apr 1			1436.13 35773 x 35801 x 0.4 GEO 90.3E
1984 Jan 13			1436.20 35784 x 35793 x 0.3 GEO 89.8E
1984 Mar 6		mv out	1436.13 35784 x 35790 x 0.5 GEO 90.1E
1984 Apr 15		mv in	1436.16 35755 x 35820 x 0.5 GEO 140.3E
1984 Apr 28			1436.26 35759 x 35820 x 0.5 GEO 140.0E
1984 May		Statsionar 7/Luch 4/Volna 6	GEO 140E
1986 Oct 28			1435.97 35779 x 35789 x 2.8 GEO 140.4E
1988 Apr 18			1435.94 35780 x 35786 x 4.2 GEO 139.3E
1988 Jul 19			143.10 35784 x 35789 x 4.5 GEO 140.5E
1988 Jul 21		mv out	1431.97 35623 x 35788 x 4.5 GEO 142.8E+1.0E
1988 Sep 11		mv in	1436.03 35777 x 35793 x 4.6 GEO 170.0W
1989 Feb 10		mv out	1436.48 35791 x 35797 x 5.0 GEO 169.8W-0.1W
1989 Mar 28			1436.13 35782 x 35792 x 5.1 GEO 171.6W+0.01W
1989 Apr 5		out of service
1989 Apr 27			1435.96 35778 x 35789 x 5.2 GEO 171.1W+0.03E
1991 Nov 11			1437.45 35800 x 35825 x 7.4 GEO 75.6W+0.3W
1995 Sep 10			1437.62 35793 x 35839 x 10.2 GEO 96.8W+0.38W

NOAA 1

  1970-106A

---

The satellites following Tiros M were given ITOS designations, the first being ITOS A. By the time ITOS A was launched, by Delta from Vandenberg at 1130 on 1970 Dec 11, ESSA had become NOAA and so instead of being ESSA 10 the satellite was renamed NOAA 1 on reaching orbit. NOAA 1 operated in a 114.9 min, 1429 x 1479 km x 101.9 deg orbit until 1971 Aug 19 when its attitude control failed.

NOAA 1
Date	Time	Event	Orbit
1970 Dec 11	1130:00	Launch by Delta N6
		SRM 1-3 sep
		T+0:31 SRM 4-6 burn
	1131	T+1:00? SRM 4-6 sep
	1133	T+3:39 MECO
	1133	T+3:45? St 1 sep
	1133:45?	SES-1 6:19
	1140:04?	SECO-1
	1231?	SES-2
	1231:41	T+1:01:41 SECO-2
	1233?	St 2 sep	114.9 1429 x 1479 x 101.9
1971 Aug 19		End of ops

The World Almanac and Book of Facts 1995

 https://welib.org/md5/ad1e508978602b7df5089c59f5b2590b

Starlette

 1975-010A

---

Starlette was the first laser geodetic satellite, preceding NASA's Lageos by a year. The 0.24m diameter Al-Mg sphere contained a depleted U-238 core to give it a mass of 48 kg. The surface was studded with 60 laser reflectors. Starlette boasted the somewhat contrived acronym of `Satellite de Taille adaptee avec Reflecteurs pour les etudes de la Terre'. It was launched on the test flight of the Diamant B P.4 from Kourou in Feb 1975, featuring a new second stage booster. The third stage was 750 kg full 62 kg empty.

Presumably there was additional attach hardware but its mass is unknown.

A radio transmitter operated for 5 hours, but the main mission of the satellite was entirely passive. Starlette was built in-house by CNES.

Starlette
Date	Time	Event	Orbit
1975 Feb 6	1635	Launch by Diamant B P.4	CSG ELD
	1636:58?	T+1:58? Emeraude MECO
	1636:59	Stage 2 P4 burn 62s
	1638:01?	P4 MECO
		Coast
		Fairing sep
	1640?	T+5m Stage 2 sep
	1641?	Stage 3 burn
	1642?	Stage 3 burnout
	1645?	Spin down, weights
	1647	Stage 3 sep, Orbit insertion	104.1 806 x 1108 x 49.8
	2136	End of transmissions

ECS-1

 1983-058A

---

The ECS 1 (European Communications Satellite 1) was built for ESA by the British Aerospace BAe/MESH consortium, based on the OTS/MARECS bus.

In 1983 Oct ownership of ECS 1 was transferred from ESA to the European Telecommunications Satellite Organization (EUTELSAT) and it was later renamed Eutelsat I F-1.

In Sep 1984, ECS 1 suffered a partial power loss due to short circuits in the solar panels.

In 1993 it was planned to move F1 from 25.5E to 36E to improve Central Asian communications.

ECS 1
Date	Time	Event	Orbit
1983 Jun 16	1159:03	Launch by Ariane 1 (L6)	CSG ELA1
		T+2:26 St 1 MECO
		T+2:30 St 1 sep
		T+2:31 St 2 MES
		T+2:38 Stage 2 acceleration rockets jettison
		T+4:14 Fairing
		T+4:47 St 2 MECO
		T+4:52 St 2 sep	-4550 x 290 x 9
		T+4:56 St 3 burn 9:18
		T+5:07 Jettison of st 3 accel rockets
		T+5:23 Stage 2 LOS
	1213:17	T+14:14 St 3 MECO	627.09 214 x 35566 x 8.6
	1214:54	ECS 1 sep (T+15:41)
	1214:46?	T+15:43 Sylda 1 sep
	1216:52	Amsat sep (T+17:41)
1983 Jun 17			626.79 208 x 35557 x 8.6
1983 Jun 18	0051:50	ECS 1 Mage 2 burn 20s
	0052:10	Mage 2 burnout 1.516 km/s
	0221	Begin spindown
	0800	3-axis, arrays deployed
	1009	Earth acquired
1983 Jun 19		Orbit adjust
1983 Jun 19			1429.89 35457 x 35873 x 0.1 GEO 27.8W+1.6E
1983 Jul 5			1427.50 35197 x 36039 x 0.1 GEO 6.2E+2.1E
1983 Jul 6		Braking
1983 Jul 7	1158	Move in, on station	GEO 10E
1983 Jul 8		Control to ECS SCC Redu	1435.91 35775 x 35790 x 0.0 GEO 10.0E
1983 Jul 10		Comms payload on
1983 Sep 27		mv out	1436.11 35774 x 35798 x 0.0 GEO 10.0E
1983 Oct 11			1436.03 35774 x 35796 x 0.0 GEO 13.0E
1983 Oct 12		Ownership from ESA to EUTELSAT
1984 Jan 10			1436.09 35772 x 35800 x 0.0 GEO 13.0E
1984 Sep 30		Short circuit
1985 Aug 15			1436.03 35762 x 35808 x 0.0 GEO 13.0E
1986 Oct			GEO 13E
1987 May 13			1436.04 35766 x 35804 x 0.0 GEO 13.0E
1988 Mar 6			1436.05 35772 x 35799 x 0.1 GEO 13.1E
1989 Feb 26			1435.99 35733 x 35835 x 0.0 GEO 13.0E
1989 Mar		move to 16E
1989 May 1			1436.03 35598 x 35972 x 0.0 GEO 15.3E
1989 Jun 6			1436.05 35707 x 35863 x 0.1 GEO 16.2E
1990 Jul 15			1436.05 35447 x 36123 x 0.9 GEO 16.8E
1991 Jun 22			1436.05 35740 x 35831 x 1.7 GEO 16.2E
1991 Oct 31		out	1435.94 35772 x 35794 x 2.0 GEO 16.6E+0.03E
1991 Dec 10		in	1436.04 35594 x 35976 x 2.1 GEO 17.3E
1992 Jan 30			1436.02 35759 x 35810 x 2.2 GEO 17.5E
1992 Feb 21		mv out	1436.01 35771 x 35798 x 2.3 GEO 17.6E+0.01E
1992 Jul 1		mv in	1436.03 35735 x 35834 x 2.6 GEO 25.4E
1992 Sep 29			1436.07 35769 x 35802 x 2.8 GEO 25.5E
1993 Aug 20			1436.00 35783 x 35786 x 3.6 GEO 25.7E
1993 Sep 5		mv out	1435.92 35773 x 35792 x 3.6 GEO 26.2E+0.04E
1993 Dec 13			1434.73 35747 x 35772 x 3.8 GEO 48.0E
1993 Dec?		mv in	GEO 48E
1994 Mar 8			1436.35 35776 x 35806 x 4.0 GEO 48.0E
1995 May 12			1436.04 35768 x 35802 x 4.9 GEO 48.0E
1996 Jan 19		mv out	1436.05 35777 x 35794 x 5.4 GEO 48.0E
1996 Mar 12		mv in	GEO 36E
1996 Mar 21		mv in	1436.05 35772 x 35799 x 5.5 GEO 36.0E
1996 Dec 8			1436.03 35764 x 35806 x 6.0 GEO 36.1E
1996 Dec 11		Orbit raised
1996 Dec 30			1456.48 36156 x 36212 x 6.0
1997 Apr 12			1456.42 36150 x 36217 x 6.2

Luna 1960

  1960-U01

---

The next E-2A type probe was given an improved radio system and redesignated called E-3; it replaced a proposed E-2F mission which would have had a Yenisey-3 camera. They were intended as Luna-3-like photographic circumlunar flights. They had a simpler design, using the E-2A pressure container but with a single 750mm focal length camera. The first E-3 probe was launched on 1960 Apr 15. The Blok-E stage cut off too early and E-3 No. 1 carried out a high apogee suborbital flight, velocity 110 m/s (or 130 m/s) too low. This was the first failure of the Blok-E.

E-3 No. 1
Date	Time	Event	Orbit
1960 Apr 15	1506:45	Launch by 8K72 L1-9	KB
	1518:51	Blok-E cutoff 3s early T+726s
1960 Apr 16	0930?	Pass EL1:4
1960 Apr 17	1500?	Apogee 200000 km
1960 Apr 19	1500?	Reentry

Payload:

• Yenisey-2 photo-TV unit

• Camera with 750 mm focal length

Salyut 2

  1973-017A

---

The first Almaz orbital piloted station (OPS 1, 11F71 No. 101) was launched on 1973 Apr 3. To hide the existence of the military Almaz program, it was given the same Salyut cover name as the civilian DOS stations, becoming Salyut-2 on reaching orbit.

17 debris objects were cataloged shortly after launch and it appears that the third stage of the Proton launch vehicle disintegrated shortly after OPS 1 separated. Failure to vent the stage led to overpressurization of the rocket body and explosion. The debris objects reentered over a 27 day period. OPS 1 raised its orbit on Apr 4 to 240 x 259 km, similar to DOS 1's operational orbit. On Apr 6 three more debris objects were tracked, reentering quickly over the next 4 days.

On Apr 8 the orbit was raised again to 261 x 284 km; then on Apr 14 it appears that the station was depressurized and possibly entered a spin - three new, large debris objects were tracked, possibly the solar panels; two of them (17Z and 17AA) remained in orbit for another month. On Apr 28 it was announced that the mission had been completed. By May 27 the altitude of the station had decayed to only 160 km and the next day it made an uncontrolled reentry.

Salyut-2
Date	Time	Event	Orbit
1973 Apr 3	0900:00	Launch by Proton-K	KB
	0910	Sep from Proton-K 8S812	152 x 288 x 51.6
	2236	8S812 disintegrated (17D-V)
			202 x 253 x 51.6
1973 Apr 4			204 x 245 x 51.6
		Orbit raise rev 18, 17m/s	240 x 259 x 51.6
1973 Apr 5	1430		238 x 260 x 51.6
1973 Apr 6?		3 objects (17W-Y) cataloged, 3-4 d
1973 Apr 6			232 x 262 x 51.6
1973 Apr 7			236 x 259 x 51.6
1973 Apr 8			237 x 256 x 51.6
		Orbit raise rev 82, 13m/s	261 x 284 x 51.6
1973 Apr 14	0930	Last contact before failure
1973 Apr 14		Impact by stage 3 debris? (17F,G,J,K, or Z?)
		Station depressurized, lost control
		3 debris objects (17Z,AA,AB)
1973 Apr 15	0015	Reacquired via the backup telemetry system
1973 Apr 16	0612	end of tx
1973 May 27			158 x 160 x 51.6
1973 May 28	1150?	Reentered 3000 km E of New Guinea

Aviation Week: February 23,1998

 https://welib.org/md5/1179a19aa3d736bb1f40b886ab722b8a

Contemporary Legend: A Reader

 https://welib.org/md5/c8ba1b29e206937c58efbace7814dbf4#

Elizabeth Solves It All

https://welib.org/md5/c9d6593f9d254b8629ca68a5065bc149

DMSP 6

  1972-018A

---

The F28/Block 5B F-2 satellite, DMSP 5528, was launched by Thor Burner 2A on 1972 Mar 24.

DMSP 5528
Date	Time	Event	Orbit
1972 Mar 24	0846:12	Launch by Thor Burner 2A	V SLC10W
	0848	Thor sep
	0849?	Star 37B burn 42s
	0849?	Star 37B sep	-3000? x 800? x 99
	0859?	Star 26 burn 18s
	0900?	Star 26 sep
			101.8 803 x 885 x 98.8
1972 Jun 16		Declared operational

Kosmos 1262

 1981-032A

---

Two-tone telemetry; Hi res satellite 19.989 MHz

Kosmos-1262
Date	Time	Event	Orbit
1981 Apr 7	1051	Launch by Soyuz-U	Plesetsk
	1055	Blok-I burn
	1059	Blok-I sep
1981 Apr 7			90.43 197x393x72.9
1981 Apr 10			90.62 218x391x72.9 from 90.40 197x391
1981 Apr 10			89.95 217x326x72.9
1981 Apr 13			89.33 214x268x72.9 from 89.92 217x323
1981 Apr 17			89.72 206x314x72.9 from 89.03 210x242
1981 Apr 21			89.65 209x304x72.9
1981 Apr 21
	0457?	Deorbit
	0507?	PO sep
	0514?	Entry
	0530?	Landed

Progress M-31

 1996-028A

---

Progress M No. 231 was launched on 1996 May 5. Mass was 7140 kg. It carried 1140 kg of fuel and 1700 kg of cargo.

Progress M-31
Date	Time	Event	Orbit
1996 May 5	0704:18	Launch by Soyuz-U	KB LC1
1996 May 7	0854:19	Docked with Mir -X
	1025:11	Hatch opened
1996 Aug 1	1644:54	Undocked
	1944:30	Deorbit over Pacific
	2033:03	Reentry over S Pacific

Kosmos 1406

 1982-089A

---

Kosmos-1406
Date	Time	Event	Orbit
1982 Sep 8	1020	Launch by Soyuz	Plesetsk
	1024	Blok-I burn
	1028	Blok-I sep
1982 Sep 8			88.82 211 x 220 x 82.3
1982 Sep 10			88.94 212 x 231 x 82.3
1982 Sep 13			88.82 207 x 225 x 82.3
1982 Sep 14			88.97 216 x 230 x 82.3
1982 Sep 19			88.77 208 x 219 x 82.3
1982 Sep 23
	0624?	Deorbit
	0635?	PO sep
	0639?	Entry
	0658?	Landed

Soyuz TM-18 (Derbent)

 1994-001A

---

Soyuz TM (7K-STM) 11F732 No. 67 was the first space launch of 1994, entering orbit on Jan 8 as Soyuz TM-18.

Soyuz TM-18, Flight 1
Date	Time	Event	Orbit
1994 Jan 8	1005:34	Launch by Soyuz-U	KB LC1
	1010:21	Blok-I ignition
	1014:24	Blok-I sep
			201 x 246 x 51.6
	1341	TCM1
	1432	TCM2	244 x 344 x 51.6
1994 Jan 9	1059	TCM3
	1133	TCM4	269 x 328 x 51.6
1994 Jan 10	0944	TCM5
	1004	Kurs radar on
	1035	TCM6
	1112	TCM7
	1118	TCM8
	1127	Rendezvous with Mir, 170m
	1144	Recommence approach
	1150:20	Docked with 37KE +X
	1317	Hatch open, crew to Mir

Soyuz TM-18, flight 2
Date	Time	Event	Orbit
1994 Jan 21	0312	Soyuz TM-18 undocked from 37KE +X
	0318	At range 120 m
	0501	Docked with Mir -X, 1h 43m flight

Soyuz TM-18, Flight 3
Date	Time	Event	Orbit
1994 Jul 9	0530	Afanas'ev and Usachev to Soyuz
	0712:59	Undocked from Mir -X
	0717:12	Sep burn 8 s at 17m
	0937:32?	Deorbit
	0941	DO CO 115.2m/s 256.3s
	1006:00?	Modules sep
	1009:12	Entry
	1032:35	Landed

Trends in High School Media: spring and summer 1995

 https://welib.org/md5/111d18430615ed8595aedef61caf5e85