Wednesday, May 24, 1989
Monday, May 22, 1989
Kosmos 1584
1984-076A
Two-tone telemetry; Medium res satellite
| Kosmos-1584 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1984 Jul 27 | 0859:59 | Launch by Soyuz | PL |
| 0904 | Blok I burn | ||
| 0908 | Blok I MECO | ||
| 0908 | Blok I sep | ||
| 1984 Jul 27 | 182x248x82.4 | ||
| 1984 Jul 27 | 181x240x82.4 | ||
| 1984 Jul 28 | 0720? | Orbit raise | 180x365x82.4 |
| 1984 Aug 6 | 179x352x82.4 | ||
| 1984 Aug 10 | 0400? | KDU sep | |
| 0511? | Deorbit | ||
| 0517 | Eq cross | ||
| 0521? | PO sep | ||
| 0526? | Reentry | ||
| 0540? | Landed | ||
Tuesday, May 16, 1989
Saturn SA-9
1965-009A
The Apollo-Saturn 103 (AS-103) flight of SA-9 was the first to carry an attached Pegasus micrometeoroid satellite and the first to have a prototype production IU. Saturn SA-9 was launched at 1437 on 1965 Feb 16 from LC37B at Cape Kennedy. It reached a 96.80 min, 495 x 733 km x 31.73 deg orbit at 1447. The stage cut off 7s earlier than nominal, matching the targeted velocity. The Pegasus A satellite was a truss structure extending from the Saturn Saturn S-4-9 stage nose. SA-9 reentered on 1978 Sep 17.
| SA-9 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1965 Feb 16 | 1437:03 | Launch by Saturn | |
| 1439:23 | IECO | ||
| 1439:28 | OECO | ||
| 1439:29 | Sep | ||
| 1439:31 | S4 MES | ||
| 1439:41 | Ullage sep | ||
| 1439:41 | LES sep | ||
| 1442:54 | SI apogee 263 km | ||
| 1447:24 | S4 MECO | ||
| 1447:34 | Insertion | 496 x 745 x 31.76 (MPR) | |
| 1449 | SI impact | ||
| LH2 tank NPV blowdown | |||
| 1450:26 | Pegasus fwd restraint sep | ||
| 1450:26 | Apollo BP sep | ||
| 1451:26 | Pegasus wing deploy | ||
| 1452:05 | Pegasus wing complete | ||
| 1519 | Beacon end | ||
| 1640? | S-4 end of tx | ||
Tuesday, May 9, 1989
Monday, May 8, 1989
Kosmos 1973
1988-088A
Two-tone telemetry; Medium res satellite
| Kosmos-1973 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1988 Sep 22 | 1020:00 | Launch by Soyuz | PL |
| 1024 | Blok I burn | ||
| 1028 | Blok I MECO | ||
| 1988 Sep 22 | 90.14 194x368x72.9 | ||
| 1988 Sep 23 | 92.26 368x403x72.9 | ||
| 1988 Oct 4 | 92.26 356x415x72.9 | ||
| 1988 Oct 9 | 92.25 356x413x72.9 | ||
| 1988 Oct 10 | |||
| 0335? | Deorbit | ||
| 0345? | PO sep | -80 x 405 x 72.86 | |
| 0403? | Entry | ||
| 0415? | Landed | ||
Sunday, May 7, 1989
CAT-1
1979-104A
CAT, the Capsule Ariane Technologique, was a cylinder containing a ballast Al alloy sphere. CAT carried instruments to measure accelerations, noise levels, temperature, pressure and stress during launch of the first Ariane rocket.
| CAT 1 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1979 Dec 24 | 1414:41 | Launch by Ariane LO1 | CSG |
| 1417:11 | Stage 1 sep 51 km (T+2:30) | -6130 x 81 x 14 | |
| 1417:41 | T+3:00 L140 LOS | ||
| 1418:49 | Fairing sep (T+4:08) | -5489 x 130 x 14.9 | |
| T+4:48 L33 MECO | |||
| 1419:34 | Stage 2 sep (T+4:53) | -4028 x 199 x 17 | |
| 1423:49 | T+4:57 St 3 burn 9:08 | ||
| 1428:46 | T+14:05 St 3 burnout | ||
| 1429:53 | CAT sep (T+912s) | ||
| 635.3 201 x 36003 x 17.6 | |||
| 1979 Dec 27 | end of ops? | ||
| 1982 Nov 14 | Reentered | ||
Saturday, May 6, 1989
Friday, May 5, 1989
Thursday, May 4, 1989
Explorer 15
1962-059A
The EPE-C (Energetic Particles Explorer C, S-003B) payload was modified for the SERBD (Study of Enhanced Radiation Belt Dynamics) mission, to analyse the new population of trapped particles around the Earth created by the US STARFISH nuclear explosion; it also detected particle injections by USSR high altitude nuclear tests. It was launched on 1962 Oct 27 at 2315:01 by Delta A from Canaveral into a 313 x 17640 km x 18.0 deg orbit. Explorer XV transmitted until 1963 Feb 9. In the 1980s Space Command recorded a decay date of 1983 Dec 19, but in 2000 this was amended to 1978 Jan 15, presumably following review of archival data. Satellite number 5992 is probably a rediscovery of Explorer 15.
This was the first launch from the Cape to a low inclination, involving a dogleg burn either in the Delta or the Altair phases. The Altair would have provided a total delta-V of around 3.5km/s. As a possible reconstruction, we can find a Delta trajectory of -1980 x 307 x 30.3 deg and a 30 degree yaw on the Altair apogee burn, which is a plausible solution. Alternatively, a -2380 x 306 x 28.6 deg Delta trajectory with a 25 degree Altair yaw gives the same final orbit. This is the minimum likely Delta inclination, so I adopt it as my reference solution.
| Explorer 15 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1962 Oct 27 | 2315:01 | Launch by Delta | CC LC17B |
| 2317:22 | T+2:21 MECO 82.6 km 4.918 km/s | -5030 x 300 ? | |
| Thor sep | |||
| 2317 | Delta S/N 2022 burn, 1:47 | ||
| 2319 | Delta SECO | -2380? x 306 x 28.6 | |
| 2328? | Altair burn, with yaw | ||
| 2330 | Altair sep | 313 x 17640 x 18.0 | |
| 1963 Feb 9 | End of ops | ||
| 1963 May 19 | End of tx | ||
| 1978 Jan 15 | Reentered | ||