Thursday, August 22, 2002
Wednesday, August 21, 2002
Pioneer 7
1966-075A
Pioneer B was launched at 1520:17 on 1966 Aug 17 by Delta E1 from Kennedy. The Delta separated at 1544:53 and the FW4 ignited at 1545:37. SP-278 and SP-280 give inconsistent values for the injection azimith corresponding to orbit inclinations of 22 and 42 deg respectively, with TR-1022 confirming the 42 deg value. Pioneer VII malfunctioned in 1972 Jul while at aphelion and lost some power, but it was still operable in 1980.
| Pioneer 7 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1966 Aug 17 | 1520:17 | Launch by Delta E1 | CK LC17A |
| T+0:42 SRM burnout | |||
| T+1:11 SRM sep | |||
| 1522:45 | T+2:28 Thor MECO 95 km | -5522 x 188 | |
| 1522 | T+2:32 Delta burn 6:15 | ||
| T+2:33 Thor sep | |||
| T+2:54 Fairing | |||
| 1529:04 | T+8:47 Delta SECO | ||
| 1544:53 | T+24:36 Delta sep | 97.4 254 x 1022 x 33.00 | |
| 1545:37 | FW4D burn, 30.8s | ||
| 1546:09 | FW4D cutoff | 367 x +Inf x 41.9 | |
| 1547:09? | FW4D sep | ||
| Delta orbit | 97.04 252 x 994 x 32.8 | ||
| 1966 Aug 26? | Solar orbit | ||
| 1966 Sep 25 | In geotail at 1000 Re | ||
| 1966 Sep 26 | XYZ(SE) = -900, 55, 22 | ||
| 1966 Sep 28 | XYZ(SE) = -950, 85, 25 | ||
| 1966 Sep 30 | XYZ(SE) = -1000, 130, 28 | ||
| 1972 Jul | Electrical system malfunction | ||
| 1980 | Still operational | ||
Molniya 319
1982-083A
Molniya-3 (F21, N19) was launched in Aug 1982 into plane A. It originally failed to make any burns to stabilize its ground track, but in mid September it started a series of small burns and later that month it was on station to replace F15 (N13). It reportedly carried an experimental SHF transponder.
| Molniya-3 No. 33 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1982 Aug 27 | 0002 | Launch by 8K78M | PL |
| BVGD sep | |||
| GO sep | |||
| T+4:46 Blok A sep | |||
| T+4:56 KhO sep | |||
| T+8:46 Blok-I MECO | |||
| 0010 | T+8:50 Blok-I sep | ||
| T+53:16 BOZ burn | |||
| 0055 | T+53:56 BOZ sep | ||
| ML burn | |||
| T+56:46 ML MECO | |||
| 0058 | T+56:54 ML sep | ||
| 1982 Aug 29 | 736.6 450 x 40827 x 62.9 | ||
| 1982 Sep 15 | Begin TCM burns | ||
| 1982 Nov 11 | 717.8 498 x 39856 x 62.9 | ||
| 1987 Apr 2 | end of ops | ||
| 2002 Jan 18 | Reentered | ||
MARECS 2
1984-114B
INMARSAT's second successful MARECS, leased from ESA, was launched in Nov 1984. The 1050 kg ECS-bus satellite was built by British Aerospace.
| MARECS 2 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1984 Nov 10 | 0114:18 | Launch by Ariane 3 (V11) | CSG |
| T+0:32 PAP sep | |||
| T+2:15 St 1 MECO | |||
| T+2:20 St 1 sep | |||
| T+2:20 Stage 2 burn | |||
| T+3:39 Fairing sep | |||
| T+4:24 St 2 MECO | |||
| T+4:29 St 2 sep | |||
| T+4:32 Stage 3 burn | |||
| T+4:43 St 3 ullage motors sep | |||
| 0130:50 | T+16:32 St 3 MECO | ||
| T+17:36 St 3 spinup | |||
| T+17:51 St 3 spindown | |||
| 0132:41 | T+18:23 Spacenet 2 sep from Sylda 4400 | ||
| 0133:44 | T+19:26 Sylda sep | ||
| 0135:21 | T+21:03 MARECS 2 sep | ||
| 1984 Nov 11 | 0324:33 | Mage burn 43s | |
| Despin, uses 33 kg of hydrazine | |||
| Solar array deploy | |||
| 1984 Nov 11 | 1434.79 35606 x 35916 x 3.2 GEO 135.5E+0.3E | ||
| 1984 Nov 13 | 1431.51 35600 x 35793 x 3.1 GEO 136.2E+1.1E | ||
| 1984 Nov 16 | Comms payload on | ||
| 1984 Dec 9 | 1431.77 35634 x 35769 x 3.1 GEO 165.1E+1.1E | ||
| 1984 Dec 19 | Braking | ||
| 1984 Dec 21 | mv in | 1436.33 35782 x 35800 x 3.0 GEO 177.5E | |
| 1985 Jan 8 | Operational, POR Spare | GEO 177.5E | |
| 1986 Jan 14 | 1436.07 35773 x 35799 x 2.4 GEO 177.5E | ||
| 1986 Jan 15 | Traffic to MCS-D | ||
| 1986 Jan 15 | mv out | GEO 177.5E dr | |
| 1986 Feb 15 | 1456.60 36178 x 36195 x 2.3 GEO 17.8E+5.1W | ||
| 1986 Feb 25 | AOR Primary, replaced MARECS 1 | GEO 26W | |
| 1986 Mar 2 | 1436.08 35769 x 35802 x 2.3 GEO 25.9W | ||
| 1987 Sep 25 | 1436.11 35774 x 35799 x 1.9 GEO 26.0W | ||
| 1989 Sep 7 | 1436.04 35772 x 35798 x 3.0 GEO 26.0W | ||
| 1990 Aug 31 | 1436.11 35775 x 35798 x 3.2 GEO 26.1W | ||
| 1990 Sep 19 | 1436.15 35773 x 35802 x 2.2 GEO 25.9W+0.02W | ||
| 1990 Nov | Moved to make new region | ||
| 1990 Nov 11 | 1436.16 35776 x 35799 x 1.7 GEO 55.4W+0.02W | ||
| 1990 Nov 19 | 1436.09 35774 x 35798 x 1.7 GEO 55.3W | ||
| 1992 Jun 26 | 1436.08 35774 x 35798 x 3.1 GEO 55.4W | ||
| 1992 Jul 7 | mv out | 1432.16 35689 x 35729 x 3.1 GEO 43.6W+0.9E | |
| 1992 Aug 11 | mv in | ||
| 1992 Sep 2 | 1436.07 35774 x 35798 x 3.2 GEO 15.1W | ||
| 1993 Mar 21 | 1436.09 35765 x 35807 x 3.7 GEO 15.0W | ||
| 1996 Mar 15 | 1436.10 35770 x 35803 x 6.0 GEO 15.0W | ||
| 1997 Jan 30 | 1436.13 35764 x 35810 x 6.6 GEO 15.5W | ||
| 1997 Feb | Move to 26W | ||
| 1997 Feb 20 | 1436.05 35771 x 35800 x 6.7 GEO 25.9W | ||
| 1999 May 17 | 1436.15 35769 x 35805 x 8.1 GEO 26.1W | ||
| 2002 Jan 18 | 1436.11 35769 x 35803 x 9.60 GEO 26.3W | ||
Tuesday, August 20, 2002
Sunday, August 18, 2002
Koronas-I
1994-014A
A new generation of AUOS satellites, the AUOS-SM, was introduced by Koronas-I, the first science satellite launched by the Russian Space Agency. KORONAS is an acronym for Kompleksnie Orbital'nie Okolozemnie Nablyudeniya Aktivnosti Solntsa (Near Earth Orbital Complex for Studying Solar Activity). The I stands for IZMIRAN (Institut Zemnovo Magnetizma, Ionosferi i rasprostraneniya radiovoln AN Rossii), the terrestrial magnetism and ionospheric research institute of the Russian Academy Of Sciences. Koronas had the prelaunch designation AUOS-SM-KI-IK ( AUOS-SM-KI-IK) No. 801. The satellite was a 2298 kg 3-axis stabilized cylinder with solar panels. It was 5.0 m high and 2.3m in diameter, with a span of 12.8m once deployed. The satellite achived 40 arcsecond pointing (only 10 arcmin was required).
| Koronas-I | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1994 Mar 2 | 0325 | Launch by 11K68 Tsiklon-3 | NIIP-53 LC32 |
| 0327:00 | T+2:00 Stage 1 sep (alt 48.1km) | ||
| 0329:37 | T+4:37 Stage 2 sep (alt 147.5 km) | ||
| 0330:20 | T+5:20 S5M burn 1 (alt 170.7 km) | ||
| 0332:04 | S5M MECO1 (alt 193.1 km, in transfer orbit) | 170? x 507 x 82.5 | |
| 0415:00 | S5M burn 2 (alt 506.4 km) | ||
| 0415:09 | S5M MECO2 (alt 507.1 km) | ||
| 0415:39 | S5M sep | 94.78 488 x 528 x 82.5 | |
| 1994 Jul? | lost attitude control | ||
| 1995 Apr | end of ops? | ||
| 2001 Mar | Reentered | ||
Payload:
- Terek Soft XR telescope-coronagraph spectroheliometer