1976-009A
Medium res photo recon satellite. PDM telemetry, extended duration
| Kosmos-799 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1976 Jan 29 | 0830 | Launch by Soyuz-U | Baikonur |
| 0834 | Blok-I burn | ||
| 0838 | Blok-I sep | ||
| 1976 Jan 29 | 89.62 201 x 309 x 71.4 | ||
| 1976 Feb 9 | 89.52 202 x 299 x 71.4 | ||
| 1976 Feb 10 | |||
| 0530? | Deorbit | ||
| 0540? | PO sep | ||
| 0546? | Entry | ||
| 0602? | Landed | ||
1996-S07
The HYFLEX lifting body was launched on the first test flight of the J-1 rocket. The J-1 performed perfectly and Hyflex reentered the atmosphere, proving performance of the heat shield tiles and control systems. However, the vehicle's flotation device separated after splashdown and Hyflex sank before it could be recovered. 12 of the 14 experiments returned their data via telemetry successfully, but the post-flight condition of the thermal protection system could not be inspected.
Splashdown was at 143.5E 28.5N.
Mass was 1054 kg, size was 4.4 l 1.4m dia.
| Hyflex | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1996 Feb 11 | 2300 | Launch by J-1 (1F) | TSNC O |
| T+1:35 St 1 burnout | |||
| T+2:15 H-1 SRB sep 80 km | -6365 x 95 ? | ||
| T+2:17 M23 burn | |||
| 2303 | T+3:27 M23 burnout | ||
| T+3:36 Fairing sep | |||
| 2304 | Apogee 107 km 3.9km/s | ||
| 2304 | T+3:58 M23 sep 136E 30.5N | -5450 x 107 x 30.6 | |
| Reentry | |||
| 62 km 4 km/s | |||
| Parachute deploy | |||
| 2311? | Splashdown near Ogasawara I | ||
1973-010A
Tselina-OM satellite Kosmos-549 was launched in Feb 1973, keeping up a high launch rate.
| Kosmos-549 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1973 Feb 28 | 0433? | Launch by 11K65M | PL |
| 0435? | Stage 2 burn | ||
| 0441? | Stage 2 coast | ||
| 0506? | Stage 2 burn 2 | ||
| 0506? | Stage 2 sep | ||
| 1973 Mar 1 | 0230 | 95.23 513 x 545 x 74.0 | |
| 1980 Jun 29 | Reentered | ||
1978-003A
Soyuz-27 (7K-T No. 44) was launched on 1978 Jan 10 and docked with the front port of Salyut-6 on Jan 11. Crew Vladimir Dzhanibekov and Oleg Makarov transferred to Soyuz-26, leaving the fresh craft for the EO-1 crew of Romanenko and Grechko.
| Soyuz-27 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1978 Jan 10 | 1226:00 | Launch by Soyuz-U | KB |
| 1228 | Blok BVGD sep | ||
| 1230 | Blok A sep | ||
| 1234 | Blok I MECO | ||
| 1234 | Blok I sep | ||
| 88.7 190 x 237 x 51.6 | |||
| 89.9 241 x 304 x 51.6 | |||
| 257 x 302 x 51.6 | |||
| 1978 Jan 11 | 91.3 330 x 350 x 51.6 | ||
| 1406 | Docked with Salyut-6 -X | ||
| 1625 | Crew transfer | ||
| 1978 Mar 15 | 1100 | Crew entry | |
| 1134 | Test burn | ||
| 1978 Mar 16 | 0800 | Undocked | |
| 1030? | Retrofire | ||
| 1033? | DO CO | ||
| 1048? | Modules sep | ||
| 1054? | Entry | ||
| 1118:47 | Landed | ||
1983-030A
The RCA F payload, an Advanced Satcom bus built by RCA Astro Electronics, was launched in 1983 to replace Satcom 1 and was named Satcom 1R on reaching orbit. In 1988 the satellite became the property of GE Americom.
The post launch MOR records the apogee burn time as Apr 14 1430 EST (well, it says EDT but that is an obvious error). The final transfer orbit TLE from Apr 13 puts the spacecraft at 140W at that time at 7th apogee, while the first post-burn TLEs from Apr 15 put it at 90W. Perhaps a further burn occurred prior to the Apr 15 data - those TLEs put the vehicle at 103-107W on Apr 15-16. More likely, however is that the MOR document, despite its almost contemporary nature (dated 1984 Jul 26) and official provenance, is in error and the burn was delayed to 9th apogee on Apr 15 at 1700 UTC.
| Satcom 1R | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1983 Apr 11 | 2239 | Launch by Delta 3924 | CC LC17B |
| T+0:59 SRM 1-6 burnout | ||
| T+1:03 SRM 7-9 burn | |||
| T+1:04 SRM 1-6 sep | |||
| T+2:02 SRM 7-9 burnout | |||
| T+2:03 SRM 7-9 sep | |||
| T+3:43 MECO | |||
| T+3:52 St 1 sep | |||
| T+3:57 SES | |||
| T+4:19 Fairing | |||
| 2249 | T+9:53 SECO-1 | 163 x 211 x 29? | |
| 2259 | T+20:30 SES-2 | ||
| 2301 | T+22:37 SECO-2 | 163 x 3997 | |
| 2301 | T+22:39 St 2 sep | ||
| 2302 | T+23:21 TES | ||
| 2303 | T+24:05 TECO | 172 x 35786 (s) | |
| 1983 Apr 11 | 2304 | T+25:32 Star 37E sep | 634.16 173 x 35977 x 24.12 |
| 2342 | T+1:03:21 SES-3 depletion | ||
| 2342 | SECO-3 | 304 x 4025 x 25.4 | |
| 1983 Apr 12 | 0500 | Apo 1 over 88E | |
| 1600 | Apo 2 over 75W | ||
| 1983 Apr 13 | 0200 | Apo 3 over 130E | 191 x 36048 x 24 |
| 1300 | Apo 4 over 40W | ||
| 2300 | Apo 5 over 173E | ||
| 1983 Apr 14 | 1000 | Apo 6 over 12E | |
| 2000 | Apo 7 over 144W | ||
| 1983 Apr 14 | 1930 | Star 30B burn (MOR) | |
| 1983 Apr 15 | 0700 | Poss. Apo 8 over 55E | |
| 1704? | Star 30B burn (TLEs) | ||
| 1730 | Poss Apo 9 over 105W | ||
| 1983 Apr 15 | 1483.09 36030 x 37380 x 0.3 GEO 101.5W+11W/d | ||
| 1983 Apr 16 | 1472.1 | ||
| 1983 Apr 18 | 1450 | ||
| 1983 Apr 22 | 1432 | ||
| 1983 Apr 23 | 1436.1 35734 x 35846 x 0.2 GEO 139W | ||
| 1983 Apr | GEO 139W | ||
| 1984 Nov 12 | 1436.00 35768 x 35801 x 0.3 GEO 138.8W | ||
| 1986 Oct | GEO 139W | ||
| 1987 Jan 9 | 1436.07 35779 x 35792 x 0.0 GEO 139.0W | ||
| 1990 Feb 14 | 1436.06 35784 x 35787 x 0.0 GEO 139.1W | ||
| 1991 Jan 29 | 1436.02 35778 x 35791 x 0.0 GEO 138.9W | ||
| 1991 Jan 30 | move to 131W | 1436.07 35778 x 35793 x 0.1 GEO 130.9W | |
| 1992 Jan 16 | 1436.04 35767 x 35803 x 0.1 GEO 131.0W | ||
| 1992 Dec 27 | orbit raise | 1436.09 35774 x 35798 x 0.1 GEO 131.0W | |
1990-043A
DARPA's MACSATs (Multiple Access Comsats) were followons to the GLOMR payloads and demonstrated tactical communications relays. The 70kg satellites, built by DSI, were launched together on a single Scout G-1 from Vandenberg in May 1990. They reached a 612 x 768 km orbit comparedwith the planned 740 km circular one. The MACSATs were 0.61m in diameter and 0.36m high, with a 6.1m gravity gradient boom.
The Master Control Station was in McLean, Virginia.
| Macsat 1 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1990 May 9 | 1750 | Launch by Scout G-1 | V SLC5 |
| T+1:18 St 1 burnout | |||
| T+1:18 St 2 burn | |||
| T+1:59 St 2 burnout | |||
| T+2:03 Heatshield sep | |||
| T+2:05 Stage 3 burn | |||
| T+3:53? Stage 3 burnout | |||
| 1801? | T+11m? Stage 3 sep | ||
| 1801? | T+11m? Stage 4 burn | ||
| 1802 | T+12m? Stage 4 burnout | ||
| 1803? | T+13m? sep from Stage 4 | ||
| 98.57 612 x 768 x 89.9 | |||
Macsat 2 was intended for experimental use but was pressed into service to support the US Marine Corps during the Persian Gulf conflict. The 68kg UHF communications store-forward satellite was built by DSI for DARPA.
| Macsat 2 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1990 May 9 | 1750 | Launch by Scout G-1 | V SLC5 |
| 98.57 612 x 768 x 89.9 | |||
| 1990 Aug 22 | Used for USMC Persian Gulf support | ||
| 1991 Apr | Persian Gulf support concluded | ||
1986-035A
The first 7K-STM spacecraft, 11F732 No. 51, was launched on 1986 May 21 and named Soyuz TM.
| Soyuz TM, Flight 1 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1986 May 21 | 0821:51 | Launch by Soyuz-U2 | KB |
| 0823 | Blok-BVGD sep | ||
| 0826 | Blok-A sep | ||
| 0830 | Blok-I cutoff | ||
| 0830 | Blok-I sep | ||
| 1100 | 192 x 225 x 51.6 | ||
| 2130 | 195 x 291 x 51.6 | ||
| 1986 May 22 | 340 x 377 x 51.6 | ||
| 1986 May 23 | 1011:45 | Docked -X | |
| Soyuz TM, Flight 2 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1986 May 29 | 0922:45 | Undocked -X | |
| 1986 May 30 | 0300? | BO sep | |
| 1986 May 30 | 0426? | Deorbit | |
| 0430? | DO CO | ||
| 0452? | PAO sep | ||
| 0456? | Entry | ||
| 1986 May 30 | 0518:08 | Landed | |
1962-062A
The final launch in the 1962 series of 2MV probes was 2MV-3 No. 1, a planned Mars lander. During ascent, a pressurization system problem in the core stage caused cavitation in its turbopumps, and the resulting rough ride shook loose the igniter connection in the Blok L main engine, preventing its operation.
| 2MV-3 No. 1 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1962 Nov 4 | 1535:15 | Launch by 8K78 | KB |
| 1539:35 | Blok-A LOX pump cavitation | ||
| 1540:07 | Blok-A fuel pump cavitation | ||
| 1540 | Blok-A sep | ||
| 1540 | Blok-I burn | ||
| 1544 | Blok-I sep | 200 x 226 x 64.8 | |
| 1635? | BOZ burn | ||
| 1636? | Blok-L failed to ignite | ||
| 1962 Nov 5 | 0020 | 87.90 170 x 170 x 64.9 | |
| 1962 Nov 5 | 0100 | 88.86 185 x 250 x 64.9 | |
| 1962 Nov 5 | 1520 | Reentered | |
1991-064A
Kosmos-2155 was the second flight to stay in parking orbit until fifth equator crossing. Kosmos-2155 was on station at 24W from 1991 to mid 1992. It then raised its orbit and began drifting.
| Kosmos-2155 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1991 Sep 13 | 1751:02 | Launch by Proton | KB |
| 1800 | Stage 3 sep | ||
| 1991 Sep 13 | 1908 | NEC 1 | |
| 2036 | NEC 2 | ||
| 2204 | NEC 3 | ||
| 2334 | NEC 4 | ||
| 1991 Sep 14 | 0118? | DM burn 1 | |
| 0734? | DM burn 2 | ||
| 0736? | DM sep | ||
| 1991 Sep 18 | 1438.75 35773 x 35903 x 1.3 GEO 23.3W+0.6W | ||
| 1991 Sep 22 | 1436.06 35761 x 35810 x 1.3 GEO 25.0W | ||
| 1991 Oct 15 | 1435.98 35763 x 35805 x 1.3 GEO 24.2W | ||
| 1992 Jun 11 | 1436.03 35781 x 35789 x 0.7 GEO 24.0W | ||
| 1992 Jun 16 | 1436.85 35779 x 35823 x 0.7 GEO 24.6W+0.2W | ||
| 1992 Aug 27 | 1436.92 35787 x 35818 x 0.5 GEO 36.8W+0.2W | ||
| 1994 Apr 29 | 1436.01 35773 x 35796 x 0.9 GEO 175.4E+0.01E | ||
| 1995 Jan 8 | 1434.73 35747 x 35772 x 1.4 GEO 143.4W+0.03E | ||
