Saturday, December 23, 2000
Friday, December 22, 2000
Kosmos 2369
2000-006A
| Kosmos-2369 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2000 Feb 3 | 0926 | Launch by Zenit-2 | KB |
| 0928 | T+2:23 Stage 1 MECO | ||
| 0928 | T+2:25 Stage 1 sep | ||
| 0928 | T+2:25 Stage 2 burn | ||
| 0928 | T+2:40 GO sep | ||
| 0932 | T+6:42 Stage 2 MECO | 150? x 850? x 71.0 | |
| Sep motor cover perigee | |||
| 0939? | T+13m? Stage 2 VECO | ||
| 0939? | Stage 2 sep motor covers | ||
| 0939? | T+13m? Stage 2 sep | ||
| 2000 Jun 28 | 847 x 854 x 71.0 | ||
Mariner 2
1962-041A
Mariner 2 was launched at 0653:14 on 1962 Aug 27 by Atlas Agena B from Cape Canaveral. The Atlas separated at 0658 and the Agena began its first 2.5 minute burn, entering Earth parking orbit at 0701. At 0717 the Agena re-ignited and separated at 0721 to insert Mariner II in solar orbit. At around 0722 the Agena made a small avoidance maneuver to ensure it would not hit Venus.
A course correction at 2249 on 1962 Sep 2 decreased the Venus miss distance from 370000 km to only 15000 km. Mariner II flew past Venus at 1952 on 1962 Dec 14, sending back measurements of its atmosphere in the first successful planetary flyby. Mariner II continued transmitting until 1963 Jan 2.
| Mariner 2 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1962 Aug 27 | 0653:14 | Launch | |
| BECO | |||
| Booster sep | |||
| SECO | |||
| 0658 | Atlas sep | ||
| 0658:53 | Agena MES-1 | ||
| 0701:26 | T+8:12 Agena MECO-1 | 187 x 187 x 32.7? | |
| 0717:43 | T+24:29 Agena MES-2 | ||
| 0719:17 | T+26:03 Agena MECO-2, 14.87S 2.1W | ||
| 0721 | Agena sep | ||
| 0722 | Agena avoidance burn | ||
| 1962 Sep 4 | 2249 | TCM 83m/s 28s | |
| 1962 Sep 5 | 0245 | TCM complete | |
| 1962 Sep 8 | Temporary attitude loss | ||
| 1962 Dec 14 | 1952 | Venus flyby 34773 km (ctr?) | |
| 1962 Dec 27 | 0738 | Perihelion 0.705 AU | |
| 1963 Jan 3 | 0615 | End of tx | |
Payload:
- Microwave radiometer
- IR radiometer
- Magnetometer
- Cosmic ray particles detector
- Solar plasma spectrometer
STEP-1
1994-017A
STEP Mission 0 was the TAOS (Technology for Autonomous Operational Survivability) payload, built by TRW and USAF Phillips Lab using the DSI/TRW Eagle (LEOStar) bus, and operated by Phillips Lab. The mission was intended to test out technology to make satellites more autonomous of ground controllers. The 502 kg satellite was launched by the first Taurus launch vehicle from a `bare base' pad, 576-E, at Vandenberg AFB.
| STEP 0 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1994 Mar 13 | 2232 | Launch by Taurus 2110 | V 576E |
| T+1:22 Stage 1 sep 39 km 2.08 km/s | -6200 x 50? | ||
| T+1:22 Stage 2 burn | |||
| T+2:43 Stage 2 burnout | |||
| T+2:48 Stage 2 sep | |||
| T+2:50 Stage 3 burn 128 km 4.54 km/s | -5100? x 175? | ||
| T+2:53 Fairing sep 131 km 4.57 km/s | -5000? x 180? | ||
| 2236 | T+4:11 Stage 3 burnout | ||
| 2243 | T+11:21 Stage 3 sep | -3000? x 770 | |
| 2243 | T+11:32 Stage 4 burn | ||
| 2244 | T+12:40 Stage 4 burnout | ||
| 2246? | STEP 0 sep | ||
| 2248? | DARPASAT sep | ||
| 539 x 559 x 105.0 | |||
| 1994 Apr? | Attitude control failure | ||
| 1994 Sep | Operations resume | ||
| 1995 Mar 13 | Decommissioned per OSC | ||
| 1996 Jun | Control to AFSPACECOM | ||
| 2000 Mar | Still operating | ||
Thursday, December 21, 2000
Navstar 14
1989-013A
The first Block II GPS satellite was SVN 14 (PRN 14, USA 35). It used the first Delta 6925 (Interim Delta II) launch vehicle, and was the first GPS launch from Cape Canaveral. Navstar 14 entered the E plane (slot E1)
| Navstar 14 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1989 Feb 14 | 1830 | Launch by Delta II 6925 | CC LC17 |
| T+0:56 SRM 1-3,7-9 out | |||
| T+1:01 SRM 4-6 on | |||
| T+1:02 SRM 1-3 sep | |||
| T+1:03 SRM 7-9 sep | |||
| T+1:57 SRM 4-6 off | |||
| T+2:02 SRM 4-6 sep | |||
| T+4:25 MECO | |||
| T+4:31 VECO | |||
| T+4:33 Stage 1 sep | |||
| 1834 | Stage 2 TIG (T+4:38) | ||
| 1834 | Fairing sep (T+4:50) | ||
| 1841 | SECO-1 Stage 2 cutoff (T+11:37) | 166 x 200 x 35.66 | |
| T+20:55 spinup | |||
| 1850 | T+20:58 Delta sep | ||
| T+21:35 TES | |||
| 1853 | T+23:02 TECO | ||
| 1854 | T+24:55 Stage 3 sep | 358.66 157 x 20531 x 37.4 | |
| 1854 | T+24:57 Yo weight | ||
| T+1:05:00 SES-2 depletion | |||
| 1936 | T+1:06:20 SECO-2 depletion | 95.21 186 x 872 x 30.3 (B) | |
| 1989 Feb 16 | 1530? | Star 37 apogee burn | 720.01 20010 x 20455 x 55.1 |
| 1989 Feb 18 | 715.02 19870 x 20349 x 55.1 | ||
| 1989 Apr 15 | In service | ||
| 1997 Feb 1 | Operating in slot E1 | ||
| 2000 Mar 26 | Reaction wheel failure | ||
| 2000 Jun 14 | Decommissioned | ||
Tuesday, December 19, 2000
Granat
1989-096A
The Granat (`Garnet') satellite (article 1AS) was launched in Dec 1989 into a highly elliptical Earth orbit by a Proton-K with a Blok-D-M (11S824M) upper stage. Granat was dedicated to high energy astrophysics; its flagship instrument was the French-built SIGMA telescope which used a coded mask to make images in the hard X-ray band above 30 keV. SIGMA/Granat discovered several hard X-ray sources near the Galactic Center.
| Granat | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1989 Dec 1 | 2020:57 | Launch by Proton-K | KB |
| Stage 3 ignition | |||
| 2030 | Stage 3 cutoff | ||
| 2030 | Stage 3 sep | ||
| 2035? | Blok D burn 1 | ||
| 2038? | Blok D MECO, LEO | 107.56 224 x 2003 x 51.5 | |
| 2124? | Blok-D-M ignition 2 | ||
| 2124? | SOZ sep | ||
| 2131 | MECO-2 | ||
| 2131:22 | Blok-D-M sep | 5928.031 1764 x 202481 x 51.9 | |
| 5903.648 1956 x 201693 x 52.12 | |||
| 1989 Dec 2 | 1608? | Pass EL1:4 | |
1991 Sep 18 | 5894.01 20804 x 182610 x 81.97 | ||
| 1994 Sep | Begin sky survey | ||
| 1998 Nov 27 | 0602 | end of ops | 5901.68 6128 x 197474 x 65.51 |
| 1999 May 25 | reentered? | ||
Payload:
- SIGMA SIGMA gamma ray telescope 30 keV-2 MeV Systeme d'Imagerie Gamma a masque aleatoire (CNES)
- Konus GRB monitor 20 keV-2MeV
- Podsolnukh (Sov/Bulg.) 2-25 keV rotating platform, triggered by Konus