1994-051A
Molniya-3 (F48, N46) was launched in Aug 1994.
| Mol3 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1994 Aug 23 | 1430:59 | Launch by Molniya-M | PL |
| 1440 | Blok-I sep | ||
| 1524? | Blok-L burn | ||
| 1527 | Perigee | ||
| 1527? | Blok L MECO | ||
| 1527? | Blok L sep | ||
| 1994 Aug 23 | 700.52 595 x 38904 x 62.8 | ||
| 1994 Aug 28 | 701.29 599 x 38938 x 62.8 | ||
1991-005A
RCS was 27m2.
| Kosmos-2122 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1991 Jan 18 | 1134:40 | Launch by 11K69 | Baikonur |
| 1136 | Stage 1 sep | ||
| 1139 | Stage 2 sep | ||
| 1222? | AKM burn | ||
| 1991 Jan 18 | 92.80 406x417x65.0 | ||
| 1991 Jan 21 | 92.78 404x417x65.0 | ||
| 1992 Mar 4 | on station | ||
| 1993 Feb 9 | 82.78 401 x 420 x 65.0 | ||
| 1993 Mar 3 | 92.78 402 x 418 x 65.0 | ||
| 1993 Mar 4 | |||
| 1993 Mar 5 | 91.14 246 x 414 x 65.0 | ||
| 1993 Mar 28 | 87.59 140 x 169 x 65.0 | ||
1990-001B
JCSAT 2 was the second HS-393 spinner and had a mass of 1260 kg on orbit. It was launched aboard a Commercial Titan 3, with an added Orbus 21S perigee kick motor placing it into geostationary transfer orbit.
| JCSAT 2 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1990 Jan 1 | 0007 | Launch by Commercial Titan 3 | CC LC40 |
| 0008:49 | T+1:49 Stage 1 ignition | ||
| 0008:57 | T+1:57 SRM sep | ||
| 0011:27 | T+4:27 Stage 2 ignition, St 1 sep | ||
| 0011:38 | T+4:38 Fairing sep | ||
| 0015:06 | T+8:06 Stage 2 cutoff | ||
| 0015 | Earth orbit insertion | 165 x 612 x 28.6 | |
| 0118:52 | T+1:11:52 Skynet 4A sep from Titan | ||
| 0220:30 | T+2:13:30? Extension module separated | ||
| 0251:46 | T+2:44:46 JCSAT 2 sep from Titan | ||
| 0337? | Orbus 7S burn | ||
| 0339? | Burnout | ||
| 0345? | Orbus sep | 300 x 19294 x 26.8 | |
| Perigee burn | |||
| Apogee burn | |||
| 1990 Jan 5 | 1436.33 35668 x 35913 x 0.4 GEO 153.9E | ||
| 1990 Jan 7 | 1436.28 35671 x 35909 x 0.3 GEO 153.8E | ||
| 1990 Feb 15 | 1436.12 35775 x 35798 x 0.1 GEO 154.0E | ||
| 1993 Mar 29 | 1436.12 35778 x 35795 x 0.0 GEO 154.0E | ||
| 1996 May 26 | 1436.10 35780 x 35792 x 0.1 GEO 154.0E | ||
| 2000 Jul 4 | 1436.12 35773 x 35800 x 0.1 GEO 154.0E | ||
1978-064A
Seasat was built by Lockheed and based on the Agena D satellite. While Spacecraft Agena D satellites launched on Atlas D and Atlas SLV-3 boosters were considered to be part of the Atlas Agena D launch vehicle, Seasat's Agena D was considered to be a payload, launched by an Atlas F. The Seasat mission used a 120 inch diameter fairing from LMSC (larger than the standard Convair 84 inch Agena fairing). SAMSO 6595ATW at Vandenberg provided the launch services, and SAMSO provided the Atlas F. LeRC was responsible for the Atlas from the NASA side, with JPL responsible for the Agena and payload.
The Atlas F launch came at 0112 UT on 1978 Jun 27. The Atlas 23F sustainer engine cut off at T+4:45. The Atlas separated at T+5:08 and the Agena coasted until T+6:23 when it ignited for its first burn. Main engine cutoff came at T+10:14, with Seasat in an elliptical transfer orbit. At T+55:48, the Agena reignited, burning until T+57:34. Seasat 1 was now in a 773 x 803 km x 108.0 deg orbit. In October transmissions from Seasat were suddenly cut short by an electrical short circuit.
The radar altimeter had a 3 ns pulse time and operated at 13.5 GHz, with a nadir swath of 2-12 km and determined altitude and wave heights. The SAR was 20 deg off-nadir and had a swath of 100 km, with a spatial resolution of 25m. The scatterometer determined surface winds to 2 m/s. The VIRR, derived from the ITOS SR, provided cloud and temperature data. The SMMR provided sea surface temperature, sea ice mapping and surface winds.
| Seasat 1 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1978 Jun 27 | 0112 | Launch by Atlas F | |
| T+2:09 BECO | |||
| T+2:12 Booster sep | |||
| T+3:27 Fairing | |||
| 0116 | Sustainer cutoff (T+4:45) | ||
| T+5:03 VECO | |||
| 0117 | Atlas sep (T+5:08) | ||
| 0118 | Agena MES-1 (T+6:25) | ||
| 0122 | Agena MECO-1 T+10:14 | 185 x 784 x 108.0 | |
| 0209:28 | T+57:15s MES-2 | ||
| 0209:34 | T+57:21s MECO-2 | ||
| 773 x 803 x 108.0 | |||
| 1978 Aug 26 | Rev 863, orbit adjust burn | ||
| 1978 Oct 10 | 0312:02 | Power failure | |
1995-062A
ESA's Infrared Space Observatory was launched by Ariane 44P (V80) with the 02 fairing. The spacecraft, built by Aerospatiale, is 3.56 x 2.77 m across ( with a 2.3m diameter dewar section) and 5.3m long. Launch mass of ISO is 2498 kg; BOL mass is 2418 kg; dry mass is 1515 kg. The initial orbit is to be 530 x 71620 km x 5.3 deg; the hydrazine thrusters will raise this to a geosynchronous 1000 x 70568 km in two burns at T+2d (Perigee) and T+6d (apogee adjust). The inclination slowly decreased to 2 degrees during the mission. Control from Villafranca center will begin at T+5 days. A cryo cover was released after a fortnight.
On 1996 May 30 the spacecraft accidentally observed the Earth for a period of about 2 minutes, while out of contact with the ground during perigee passage. Temperatures increased significantly with the baffle at 42K and the support structure at 10K; the spacecraft entered safemode. Only a small amount of helium seems to have been lost, and the spacecraft cooled down and resumed observations two days later. The cryogen finally ran out in Apr 1998. Observations with SWS in the post-cryo phase included 2-4 micron spectra of stars.
| ISO | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1995 Nov 17 | 0120 | Launch by Ariane 44P (V80) | CSG ELA2 |
| 0123 | Stage 2 burn | ||
| 0125 | Stage 3 burn | ||
| 0138 | Stage 3 cutoff | ||
| 0140 | Stage 3 separation | 1448.8 570 x 71498 x 5.2 | |
| 1475.25 534 x 72564 x 5.4 | |||
| 1995 Nov 19 | 1310 | Perigee raise, 1h 51m burn | 1030 x 71606 x 5.2 |
| 1995 Nov 24 | 0245 | Apogee lower, 39m | 1437.16 1036 x 70578 x 5.2 |
| 1995 Nov 27 | 1027 | Cryo cover ejected | |
| 1995 Nov 28 | ISOCAM first light image (M51) | ||
| 1996 May 30 | Accidental earth view | ||
| 1996 May 18 | 1436.38 1047 x 70536 x 3.8 GEO 172.1W+0.1W | ||
| 1996 Sep 6 | 1435.60 1074 x 70479 x 2.6 GEO 132.5W0.1E | ||
| 1996 Sep | Orbit trim | ||
| 1996 Sep 14 | 1437.41 1082 x 70542 x 2.5 GEO 132.0W+0.3W | ||
| 1996 Oct 11 | 1437.25 1087 x 70530 x 2.2 | ||
| 1997 May 14 | 0030 | Orbit trim no. 2 | |
| 1997 Dec 11 | Orbit trim no. 3 | ||
| 1998 Apr 8 | 0700 | LHe depleted, warmup | |
| 2307 | Observing complete, 4K | ||
| 1998 Apr 9 | Engineering tests | ||
| 1998 Apr | SWS stellar spectra survey | ||
| 1998 May 4 | 1436.3 1331 x 70251 x 2.2 | ||
| 1998 May 11 | Orbit lower | ||
| 1998 May 16 | 1418.4 684 x 70196 x 2.2 | ||
| 1998 May 18 | end of ops | ||
| 1999 Oct 14 | 1417.71 463 x 70388 x 5.7 | ||
