1974-082A
Kosmos-691 carried out a 12 day mission, with engine separation on the 10th day.
| Kosmos-691 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1974 Oct 25 | 0930:01 | Launch | KB |
| 0934 | Blok-I burn | ||
| 0938 | Blok-I sep | ||
| 1350 | 89.53 171 x 330 x 65.0 | ||
| 1974 Oct 29 | 2343 | 89.42 170 x 321 x 65.0 | |
| 1974 Nov 3 | 1526 | 89.30 169 x 310 x 65.0 | |
| 1974 Nov 6 | |||
| 0553? | Deorbit | ||
| 0603? | PO sep | ||
| 0607? | Entry | ||
| 0623? | Landed | ||
1985-076C
American Satellite Corp. was a joint venture of Fairchild and Continental Telecom, Inc. It was bought by Contel in 1985, forming Contel ASC. Contel merged with GTE in Mar 1991, and Contel ASC became part of GTE Spacenet.
The ASC 1 (sometimes referred to as Amersat 1 in the early 1980s) satellite was launched in 1985 on Shuttle mission 51-I. It was used for data transmissions and occasional business video.
| ASC 1 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1985 Aug 27 | 2207:34 | Deploy from OV-103 | |
| 1985 Aug 27 | 2252:34? | PAM-D | |
| 2254 | PAM-D burnout | ||
| 2256? | PAM-D sep | ||
| 1985 Aug 28 | 639.45 365 x 36051 x 27.1 | ||
| 1985 Aug 31 | 639.47 388 x 36029 x 27.1 | ||
| 1985 Aug 31 | 1729 | Star 30C burn | |
| 1985 Aug 31 | 1472.06 36043 x 36931 x 0.9 GEO 86.1W+8.8W | ||
| 1985 Sep 1 | 1476.71 36052 x 37103 x 0.8 GEO 96.2W+9.9W | ||
| 1985 Sep 5 | 1441.36 35862 x 35916 x 0.7 GEO 115.7W+1.3W | ||
| 1985 Oct 14 | 1436.11 35783 x 35790 x 0.1 GEO 128.0W+0.01W | ||
| 1985 Dec 17 | 1436.08 35781 x 35790 x 0.1 GEO 128.0W | ||
| 1986 Mar 31 | 1436.07 35780 x 35792 x 0.0 GEO 128.0W | ||
| 1987 Jun 1 | 1436.06 35776 x 35795 x 0.0 GEO 128.1W | ||
| 1989 May 13 | 1436.04 35776 x 35794 x 0.0 GEO 128.1W | ||
| 1991 Mar | Ownership to GTE Spacenet | ||
| 1991 Oct 15 | 1436.04 35772 x 35798 x 0.1 GEO 127.9W | ||
| 1993 May 10 | 1436.05 35759 x 35811 x 0.0 GEO 127.8W | ||
| 1994 May 20 | 1436.05 35765 x 35806 x 0.2 GEO 127.5W | ||
1981-006A
| Kosmos-1241 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1981 Jan 21 | 0829 | Launch by 11K65M | PL |
| 0837? | Stage 2 MECO-1 | ||
| 0932? | Stage 2 MECO-2 | ||
| 1981 Jan 26 | 105.0 977x1011x65.8 | ||
1994-015A
STS-62 was launched on 1994 Mar 4 on a research flight. The USMP microgravity payload was the main science. 55 melting and solidification cycles were carried out for the MEPHISTO experiment to study phase transitions. The IDGE experiment showed that dendritic solidification of molten metals happened at a different rate when supercooling effects are low. The Zeno experiment located the critical point of xenon to an accuracy of 10 microKelvins.
The OAST-2 payload studied spacecraft glow and carried out technology tests.The DEED dexterous end effector demonstration was used on the end of the robot arm, using its MAT magnetic attachment tool to pick up objects and a mirror to reflect its target to a payload bay video camera. MAT and a task bar were stored on an ESAP (GABA) plate on the sidewall. The DEE was used successfully, and the MAT could grapple objects within a distance of 1 cm, although there were problems in daylight with aligning the tool.
| STS-62 mission events | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1994 Feb 3 | Rollover | VAB | |
| 1994 Feb 10 | Rollout | LC39B | |
| 1994 Mar 4 | 1353:00 | Launch | LC39B |
| 1355:06 | SRB sep | ||
| 1401:31 | MECO | 80 x 285 x 39.0 | |
| 1401:50 | ET sep | 88.31 85 x 295 x 39.0 (OMS dV) | |
| 1435:20 | OMS 2 2:12 64m/s | 90.53 296 x 304 x 39.0 | |
| 1437:32 | OMS 2 CO | ||
| 1528 | PLBD open | ||
| 1843 | RMS uncradle | ||
| 2018 | RMS grapple DEE MAT | ||
| 2030? | RMS unberth DEE MAT | ||
| 2100? | RMS reberth DEE | ||
| 2138 | RMS cradle | ||
| 1994 Mar 8 | 2100 | 90.54 297 x 305 x 39.0 | |
| 1994 Mar 12 | 1453 | RMS unberthed, camera used to monitor EISG payload | |
| 1540 | RMS reberthed | ||
| 1994 Mar 13 | 1300 | 90.51 296 x 303 x 39.0 | |
| 1994 Mar 14 | 0702:39 | OMS 3R 42s 10m/s | |
| 0703:21 | OMS 3 CO | 260 x 303 x 39.0 | |
| 0743:29 | OMS 4L 47s 11m/s | ||
| 0744:16 | OMS 4 CO | 89.73 255 x 266 x 39.0 | |
| 0837 | RMS unberthed | ||
| 0855 | RMS grapple DEE | ||
| 0900? | RMS unberth DEE | ||
| 1994 Mar 14 | 0900 | 89.73 256 x 266 x 39.01 | |
| 1150 | DEE ops underway | ||
| 1500? | DEE berthed? | ||
| 1620 | DEE ungrappled | ||
| 1994 Mar 15 | RMS ops with DEE | ||
| 0701 | RCS tests for DSO 324 | ||
| 0732 | RMS grapple DEE | ||
| 0842 | RMS/MAT grapple DEED task bar | ||
| 1208 | DEE RMS insertion task - in slot | ||
| 1416 | Task bar experiments finished | ||
| 1530 | MAT berthed and ungrappled | ||
| 1994 Mar 15 | 2200 | 89.72 256 x 265 x 39.0 | |
| 1994 Mar 16 | 0808:33 | OMS 5 (OAST 2) 37s 19m/s | 89.04 199 x 254 x 39.01 |
| 0809:10 | OMS 5 CO | ||
| 1043 | RMS grapple DEE/MAT | ||
| 1300? | RMS berth, ungrapple MAT | ||
| 1994 Mar 17 | 1031 | RMS cradled | |
| 1994 Mar 18 | 0600 | 89.03 199 x 253 x 39.0 | |
| 0934 | PLBD closed | ||
| 1994 Mar 18 | 1216:50 | OMS DO 2:07 65m/s | |
| 1218:58 | OMS DO CO | 86.84 -17 x 253 x 39.0 | |
| 1238:06 | Entry interface | ||
| 1309:41 | MGTD | ||
| 1310:00 | NGTD | ||
| 1310:35 | Wheels stopped | ||
1989-040A
This was the second mission to fly the two-phase 180 and 150 km profile.
| Kosmos-2025 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1989 Jun 1 | 1259:59 | Launch by Soyuz | PL |
| 1304 | Blok-I burn | ||
| 1308 | Blok-I sep | ||
| 1989 Jun 1 | 89.58 250x257x62.8 | ||
| 1989 Jun 2 | 89.58 249 x 257 x 62.8 | ||
| 1989 Jun 2 | |||
| 1989 Jun 2 | 89.86 179x356x62.8 | ||
| 1989 Jun 8 | 89.76 179 x 346 x 62.8 | ||
| 1989 Jun 9 | 180? x 290? x 62.8 | ||
| 1989 Jun 11 | 88.90 153 x 287 x 62.8 | ||
| 1989 Jun 12 | 89.06 153x303x62.8 | ||
| 1989 Jun 14 | 88.97 150x297x62.8 | ||
| 1989 Jun 15 | |||
| 0307? | Deorbit | ||
| 0315? | PO sep | ||
| 0328? | Entry | -186 x 201 x 62.81 | |
| 0342? | Landed | ||
1996-F01
Intelsat 708 was flown to Xichang Space Center to become the first Intelsat for launch on a Chinese rocket. It was the very first flight of the Chang Zheng 3B variant, which combined the CZ-3A core with the CZ-2E strapons. As the CZ-3B cleared the launch tower on 1996 Feb 14, the rocket tilted over and started flying horizontally. One observer described it as a `20-story cruise missile'. It crashed into the ground 25 sec after liftoff, destroying buildings and killing six people with 57 injured, according to the Chinese. Western observers claimed much higher casualty figures. The accident investigation found that the inertial guidance system failed 2 seconds after takeoff.
The 2011 CZ user guide records the satellite mass as 4594 kg, although contemporary accounts said 3750 kg.
| Intelsat 708 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1996 Feb 14 | 1901 | Launch by CZ-3B | XSC |
| 1901 | Guidance failed, T+2s | ||
| 1901 | CZ-3B off course | ||
| 1901 | CZ-3B impact and explosion | ||
1971-032A
The first DOS station, DOS 1, was originally to be named Zarya, but was renamed Salyut after launch on 1971 Apr 19. It had the designation 17K No. 121.
The first crew reached the station on Apr 24; Soyuz-10 soft docked but could not complete the seal and had to undock and return to Earth without boarding the station.
A second crew docked on Jun 7 aboard Soyuz-11. Georgiy Dobrovolskiy, Viktor Patsaev, and Vladislav Volkov became the first space station crew, and settled into a routine of on-board experiments. After shattering the spaceflight duration record they prepared to return to Earth. The crew transferred back to Soyuz-11, closed the Salyut hatch, and undocked from the station completing the first station expedition.
Salyut was maintained in orbit for several months, but was deorbited over the Pacific in October when it became clear that the Soyuz program would remain grounded for some time. This set the precedent for the controlled reentry of massive spacecraft in empty areas of the South Pacific Ocean.
Soyuz-10 was docked to Salyut for 5h30m. Soyuz-11 was docked for 22d10h40m and the hatch open/close time was about 22d08h35m.
| Salyut | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1971 Apr 19 | 0140:00 | Launch by Proton-K | KB |
| Stage 1 sep | |||
| Stage 2 sep | |||
| Stage 3 MECO | |||
| 0149? | Stage 3 sep | 170 x 206 x 51.4 | |
| 0930 | 177 x 211 x 51.6 | ||
| 167 x 196 x 51.6 | |||
| 1971 Apr 20 | 168 x 175 x 51.6 | ||
| 0230 | Orbit raise | 201 x 211 x 51.6 | |
| 1971 Apr 23 | 150 x 160 x 51.6 | ||
| 190 x 190 x 51.6 | |||
| 1971 Apr 24 | 184 x 240 x 51.6 | ||
| 0147 | Soyuz-10 docked | ||
| 0717 | Soyuz-10 undocked | ||
| 1900 | 189 x 227 x 51.6 | ||
| 1971 Apr 26 | 186 x 220 x 51.6 | ||
| Orbit raise | 253 x 277 x 51.6 | ||
| 1971 Apr 28 | 252 x 271 x 51.6 | ||
| 1971 May | Orbit trim | ||
| 1971 May | Orbit trim | ||
| 1971 Jun 1 | 200 x 207 x 51.6 | ||
| 204 x 209 x 51.6 | |||
| 193 x 204 x 51.6 | |||
| 1971 Jun 3 | 193 x 194 x 51.6 | ||
| 187 x 221 x 51.6 | |||
| 1971 Jun 4 | 188 x 215 x 51.6 | ||
| 208 x 217 x 51.6 | |||
| 1971 Jun 5 | 208 x 212 x 51.6 | ||
| 193 x 257 x 51.6 | |||
| 1200 | 209 x 240 x 51.6 | ||
| 1971 Jun 7 | 0745 | Soyuz-11 docked | |
| 0940? | Crew entry | ||
| 1971 Jun 8 | 206 x 227 x 51.6 | ||
| 1971 Jun 8 | 0802 | Orbit raise | 225 x 262 x 51.6 |
| 1971 Jun 9 | 0706 | 257 x 264 x 51.6 | |
| 1971 Jun 9 | OS checkout | ||
| 1971 Jun 16 | Minor fire from electrical equipment | ||
| 1971 Jun 24 | Svinets observations of rocket launches | ||
| 1971 Jun 25 | 230 x 244 x 51.6 | ||
| 232 x 240 x 51.6 | |||
| 1971 Jun 27 | Soyuz checkout | ||
| 1971 Jun 29 | 1815 | Crew transfer to Soyuz-11 | |
| 1825:15 | Soyuz-11 undocked | ||
| 1971 Jun 30 | 229 x 232 x 51.6 | ||
| Orbit raise | 238 x 284 x 51.6 | ||
| 1971 Jul 28 | 200 x 237 x 51.6 | ||
| 226 x 292 x 51.6 | |||
| 1971 Aug 17 | 199 x 250 x 51.6 | ||
| 249 x 299 x 51.6 | |||
| 1971 Aug 18 | 249 x 299 x 51.6 | ||
| 284 x 318 x 51.6 | |||
| 1971 Sep 25 | 270 x 295 x 51.6 | ||
| Lower orbit | 218 x 272 x 51.6 | ||
| 1971 Oct 11 | 171 x 182 x 51.6 | ||
| 0328? | Guess for deorbit | ||
| 0350? | Guess for impact | ||
1977-118A
NASDA's CS (Communications Satellite) program was aimed at developing a domestic comsat system for Japan. The telecom services were provided by NTT. CS 1 was built by Mitsubishi and Ford, and launched on an American Delta from Cape Canaveral in Dec 1977. It was named Sakura (`cherry blossom') after launch.
| Sakura 1 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1977 Dec 15 | 0047 | Launch by Delta 2914 | CC LC17 |
| T+38s SRM 1-6 out | |||
| T+39s SRM 7-9 burn | |||
| T+1:17 SRM 7-9 out | |||
| T+1:27 SRM 1-9 sep | |||
| T+3:45 MECO | |||
| T+3:53 St 1 sep | |||
| T+3:59 St 2 burn | |||
| T+4:37 Fairing sep | |||
| 0055 | T+8:53 SECO-1 167 km 7.394 km/s | 166 x 167 km x 28.5? | |
| 0108 | T+21:06 SES-2 166 km 7.396 km/s | ||
| 0108 | T+21:15 SECO-2 | ||
| T+22:10 spinup | |||
| 0109 | T+22:15 St 2 sep 166 km 7.510 km/s | 167 x 600? x 28.5 | |
| 0109 | T+22:57 St 3 burn | ||
| 0110 | T+23:41 TECO 169 km 9.929 km/s | ||
| 0111 | T+24:46 St 3 sep 194 km 9.831 km/s | 166 x 35936 x 28.8 | |
| 0217? | St 2 depletion | 111.32 483 x 2090 x 28.7 | |
| 1977 Dec 16 | 0327 | AKM 43s burn | |
| 1977 Dec 24 | GEO 135E | ||
| 1978 Feb 2 | NSSK burn | 1436.09 35782 x 35789 x 0.1 GEO 135.0E | |
| 1978 May 5 | NSSK burn | ||
| 1978 Jul 4 | NSSK burn | ||
| 1978 Sep 19 | NSSK burn | ||
| 1978 Nov 29 | NSSK burn | ||
| 1979 Jan 27 | NSSK burn | ||
| 1979 Apr 24 | NSSK burn | ||
| 1979 Jul 5 | NSSK burn | ||
| 1979 Aug | GEO 135E | ||
| 1979 Sep 10 | NSSK burn | ||
| 1979 Dec 4 | NSSK burn | ||
| 1980 Aug | GEO 135E | ||
| 1982 Apr | GEO 134E | ||
| 1983 Aug | GEO 135E | ||
| 1983 Aug 15 | 1436.18 35786 x 35789 x 1.3 GEO 134.9E | ||
| 1983 Oct | GEO 131E+0.1/d | ||
| 1984 Jan | GEO dr | ||
| 1984 Feb 5 | 1436.07 35778 x 35794 x 1.7 GEO 150.2E | ||
| 1984 Feb | On station | GEO 150E | |
| 1985 Sep | GEO 150.0E | ||
| 1985 Nov 13 | GEO 150.0E | ||
| 1985 Nov 19 | 1436.13 35781 x 35793 x 3.3 GEO 150.1E | ||
| 1985 Nov 19 | mv out | GEO +0.2/d | |
| 1985 Nov 24 | 1456.00 36167 x 36812 x 3.3 | ||
1994-024A
| Kosmos-2279 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1994 Apr 26 | 0214:15 | Launch by 11K65M | PL LC132 |
| T+2:10 St 1 MECO | |||
| T+2:12 St 1 sep | |||
| T+2:12 St 2 burn 59km | |||
| T+2:27 Fairing 76km | |||
| 0222 | T+8:03 St 2 MECO 150 km | 150 x 1003? x 83 | |
| 0316? | T+1:02:19 St 2 MES2 | ||
| 0316? | T+1:02:30 St 2 MECO2 | ||
| 0317? | T+1:03 St 2 sep | ||
| 1994 May 11 | 104.73 956 x 1007 x 82.95 | ||
1988-031A
The fourth Foton flight was the first to be named Foton. It used the refurbished reentry vehicle from Kosmos-1841.
| Foton No. 4 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1988 Apr 14 | 1700:00 | Launch by Soyuz-U | PL LC41/1 |
| 1704 | Blok-I burn | ||
| 1708 | Blok-I sep | ||
| 1988 Apr 15 | 90.44 216 x 375 x 62.8 | ||
| 1988 Apr 27 | 90.26 214 x 359 x 62.8 | ||
| 1988 Apr 28 | |||
| 0721? | Deorbit | ||
| 0732? | PO sep | ||
| 0740? | Entry | ||
| 0754? | Landed | ||
1964-069A
DS-MG No. 2 was the second magnetic field survey satellite,named Kosmos-49 on reaching orbit. It operated for 10 days until the telemetry system failed. A US source claimed it also studied the IR and UV flux from the Earth but I haven’t found this confirmed from Soviet sources. Kosmos-45 did carry such experiments so this US source may have confused or conflated the two satellites.
| Kosmos-49 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1964 Oct 24 | 0517 | Launch by 63S1 | GTsP4 |
| 0519 | Stage 2 | ||
| 0524 | Stage 2 sep | 91.78 264 x 466 x 49.0 | |
| 1964 Nov 3 | End of operations | ||
| 1965 Aug 21 | Reentered | ||
1988-041A
Kosmos-1944 was the first Kometa flight of 1988.
| Kosmos-1944 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1988 May 18 | 1030:01 | Launch by Soyuz-U | Baikonur |
| 1039 | Blok-I sep | ||
| 1988 May 18 | 89.37 198x290x64.8 | ||
| 1988 May 18 | 89.24 214x260x64.8 from 89.13 226x237 via 89.36 198x289 | ||
| 1988 May 23 | 89.27 213x264x64.78 | ||
| 1988 May 31 | 89.50 225x275x64.8 | ||
| 1988 Jun 1 | 89.28 206x272x64.8 | ||
| 1988 Jun 7 | 89.40 215x276x64.8 from 89.18 204x264 | ||
| 1988 Jun 14 | 89.30 214x266x64.8 from 89.20 206x264 | ||
| 1988 Jun 22 | 89.13 210x253x64.8 | ||
| 1988 Jun 23 | |||
| 2338? | Deorbit | ||
| 2357? | Entry | ||
| 1988 Jun 24 | 0014? | Landed | |
1979-096A
The Interkosmos-20 satellite was the USSR's first oceanographic satellite. The AUOS-Z class spacecraft, known as Okean-IK, was launched on 1979 Nov 1 by Kosmos-3M from Plesetsk.
Mass was 995 kg.
| Interkosmos-20 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1979 Nov 1 | 0805 | Launch by 11K65M (Kosmos-3M) | NIIP-53 |
| 0807 | S3 burn | ||
| 0813? | T+8m? S3 MECO-1 | ||
| 0838? | T+33m? S3 MES-2 | ||
| 94.4 462 x 519 x 74.1 | |||
| 1981 Mar 3 | Reentered | ||
1982-087A
ETS-3 was the fourth Engineering Test Satellite to be launched, and was renamed Kiku-4. Its N-I launch vehicle placed it in a 107 minute orbit. ETS-3 tested new methods of attitude control.
| Kiku-4 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1982 Sep 3 | 0517 | Launch by N-I | TNSC |
| T+38s SOB burnout | |||
| T+1:20 SOB sep | |||
| T+3:38 MECO | |||
| T+3:44 VECO | |||
| T+3:46 Stage 1 sep | |||
| T+3:48 SES | |||
| 0521 | T+4:02 Fairing | ||
| 0524 | T+7:50 SECO | -2200? x 980 x 31.1 | |
| 0525 | S-13s St 2 sep | ||
| 0525 | S+0s TES | ||
| 0525 | S+40s TECO | ||
| 0527 | S+145s St 3 sep | ||
| 1982 Sep 3 | 0527 | Despin | |
| 1982 Sep 3 | 107.1 965 x 1228 x 44.6 | ||
| 1985 Mar 8 | end of ops | ||
1975-093A
The three day flight of Kosmos-772 in Sep 1975 was a cover for the second test flight of the new 7K-S spaceship, 11F732 No. 2L.
| Kosmos-772 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1975 Sep 29 | 0415:00 | Launch by Soyuz | KB |
| 0417 | Blok BVGD sep | ||
| 0419 | Blok A sep | ||
| 0423 | Blok I MECO | ||
| 0423 | Blok I sep | ||
| 1975 Sep 29.42 | 88.49 154x246x51.81 | ||
| 1975 Sep 29.54 | 89.14 193x270x51.74 | ||
| 1975 Sep 30.41 | 89.45 195x300x51.78 | ||
| 1975 Oct 1.47 | 89.25 196x329x51.76 | ||
| 1975 Oct 1.59 | 89.46 196x300x51.80 | ||
| 1975 Oct 2 | 0328? | DO ignition | |
| 0332? | DO CO | ||
| 0344? | BO, PAO sep | ||
| 0352? | Entry | ||
| 0415:46 | Landed | ||
1985-012A
| Kosmos-1628 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1985 Feb 6 | 1100 | Launch by Soyuz | PL |
| 1104 | Blok I burn | ||
| 1108 | Blok I MECO | ||
| 1108 | Blok I sep | ||
| 206 x 393 x 72.9 | |||
| 1985 Feb 14 | 368 x 434 x 72.9 | ||
| 1985 Feb 20 | |||
| 0501? | Deorbit | ||
| 0512? | PO sep | ||
| 0528? | Entry | ||
| 0543? | Landed | ||
1986-014A
This was the first of two PARCAE missions to utilize a USA designation.
| PARCAE 8 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1986 Feb 9 | 1006 | Launch by Atlas H | V SLC3 |
| 1008 | BECO | ||
| 1011 | Atlas VECO, sep | ||
| 1033? | Star 20 burn | ||
| 1035? | Plume shield sep | ||
| 1058 x 1158 x 63.0 | |||
| 1986 Feb 27? | USA 16-17 cataloged | ||
| 1986 Mar | USA 18 cataloged | ||
1989-092A
Kosmos-2051 ended up in a low perigee orbit after the 11K69 rocket apparently reached too low an altitude; multiple burns were used to raise the orbit. RCS was 23m2.
| Kosmos-2051 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1989 Nov 24 | 2322:00 | Launch by Tsiklon from Baikonur | |
| 2324 | Stage 1 sep | ||
| 2326 | Stage 2 sep | ||
| 1989 Nov 25 | 0010? | AKM burn | |
| 1989 Nov 25.0 | 91.54 280x420x64.8 | ||
| 1989 Nov 25.3 | 91.77 278x444x64.9 | ||
| 1989 Nov 27.5 | 92.74 327x489x65.0 from 91.80 279x446 via 280x489 | ||
| 1989 Nov 28.3 | 92.79 352x470x64.9 from 92.73 332x483 | ||
| 1989 Nov 29.2 | 92.85 360x468x64.9 | ||
| 1989 Nov 29.9 | 92.90 370x463x64.9 | ||
| 1989 Dec 2.4 | 92.77 367x452x64.9 | ||
| 1989 Dec 5.7 | 92.77 370x450x64.9 | ||
| 1989 Dec 12.1 | 92.78 405x415x64.9 from 92.77 373x447 | ||
| 1990 Aug 10.7 | 92.77 404x416x64.9 | ||
| 1990 Aug 11.2 | 92.71 398x416x64.9 from 92.77 404x416x64.9; end of active life | ||
| 1990 Aug 14.6 | 92.67 396x414x64.9 | ||
| 1990 Aug 27.1 | 92.50 389x404x64.9 | ||
| 1990 Oct 2.1 | 92.22 374x391x64.9 | ||
| 1991 Jan 1 | 90.64 297x314x64.9 | ||
| 1991 Jan 17 | 89.22 229x242x64.9 | ||
| 1991 Jan 21 | 86.90 115x125x64.8 | ||
| 1991 Jan 29 | reentered | ||
1969-030A
NASA's Mariner G (Mariner VII) was JPL's M69-2 spacecraft. (M69-1 was a test model, M69-4 was a flight backup). Atlas 5402 was damaged during launch preps on 1969 Feb 14 and replaced by Atlas 5105. M69-3, originally intended for the mission, became Mariner 6 instead and M69-2, with a launch mass of 383 kg, was used for Mariner 7. Launch was at 2222:01 on 1969 Mar 27 from LC36 at Kennedy. Again, the Centaur made a single burn to enter solar orbit without entering Earth parking orbit first. A course correction at 2021(?) on Apr 8 put Mariner VII on course for its Mars encounter. Mariner flew past Mars at 0500:49 on 1969 Aug 5. This flyby was targeted to allow observations of the south polar cap. Mariner 7 was reported as still transmitting on 1970 May 25.
| Mariner 7 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1969 Mar 27 | 2222:01 | Launch by Atlas Centaur | |
| 2224:31 | BECO | ||
| 2224:34 | Booster sep | ||
| 2225:16 | Insulation sep | ||
| 2225:53 | Fairing sep | ||
| 2226:16 | Atlas SECO | ||
| 2226:18 | Atlas sep | ||
| 2226:27 | Centaur MES1 | ||
| 2233:53 | Centaur MECO | 112 x Inf x 31.0 | |
| 2235:28 | Centaur sep | ||
| 1969 Mar 27 | 2239:22 | Solar panels deployed | |
| 2248:04 | Centaur venting | ||
| 1969 Apr 8 | 2022:09 | TCM 8s 4.3m/s | |
| 1969 May 8 | 1527E | Scan plaform unlatched | |
| 1969 Jul 30 | 1407 | Battery problems | |
| 2206 | Loss of signal | ||
| 1969 Jul 31 | 0515 | Reacquired | |
| 1969 Aug 2 | 0906 | Far encounter begins | |
| 1969 Aug 3 | 1544 | Centaur flyby Mars at 637019 km | |
| 1969 Aug 4 | 0615 | Enter Mars sphere | |
| 1969 Aug 5 | 0219 | Near encounter begins | |
| 1969 Aug 5 | 0500:49 | Mars flyby 3430 km | |
| 1969 Aug 6 | 0345 | Leave Mars sphere | |
| 1969 Sep | UVS astronomy obs. | ||
| 1969 Nov 1 | Begin extended mission | ||
| 1970 May 25 | end of tx | ||
1996-023A
The final Mir module was 77KSI Priroda (77KSI No. 174-01). Originally scheduled for 1992, it was finally launched in Apr 1996. Priroda did not have solar panels, so there was some concern when one of two electrical systems failed, but the short three-day rendezvous and docking was successful. The mass of Mir now stood at 128.98 tonnes. Mass of Priroda at EOI was 19470 kg, at rendezvous with Mir it was 18630 kg.
The day after docking, the Lyappa arm was used to transfer the module to the +Z port. After the hatch was opened, the EO-21 crew began sealing the battery systems in bags and transferring them to Mir for later disposal in a Progress.
| Priroda | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1996 Apr 23 | 1148:50 | Launch by Proton-K | KB LC81L |
| 1150 | St 1 sep T+2:06 | ||
| 1151 | T+3:00 GO sep | ||
| 1153 | T+5:35 St 2 sep | ||
| 1158:27 | T+9:37 St 3 MECO | ||
| 1158:39 | T+9:49 St 3 sep at 220 km | 89.94 214 x 328 x 51.7 | |
| 1996 Apr 24 | 1332:04 | TCM-1 10m/s | |
| 1533:19 | TCM-2 25m/s | 91.16 281 x 381 x 51.6 | |
| 1996 Apr 25 | 1138:12 | TCM-3 22m/s | |
| 1213:40 | TCM-4 2 m/s | 92.00 360 x 384 x 51.7 | |
| 1996 Apr 26 | 0938:44 | TCM-5 1 m/s | 92.11 365 x 390 x 51.7 |
| 1996 Apr 26 | 1235 | At 182m, stationkeeping | |
| 1996 Apr 26 | 1242:32 | Docked with Mir -X | 92.43 391 x 395 x 51.65 |
| 1996 Apr 27 | 0832 | Rotate to +Z | |
| 0920 | Rotation complete, docked at +Z | ||
| 1006 | Rotation completed | ||
| 1320 | Hatch opened | ||
