1978-075A
The third SDS satellite,launched in Aug 1978,was the first to carry a nuclear explosion detection system.
| SDS 3 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1978 Aug 5 | 0500? | Launch by Titan 34B Agena D | |
| 0502? | Stage 2 burn | ||
| 0505? | Stage 2 MECO | ||
| 0506? | Agena MES-1 | ||
| 0510? | Agena MECO-1 | 180? x 700? x 63 | |
| 0536? | Agena MES-2 | ||
| 0538? | Agena MECO-2 | ||
| 0540? | Agena sep | ||
| 720.0 805 x 34272 x 63.5 | |||
| 2001 Feb 8 | Reentered | ||
1972-029A
| Prognoz No. 501 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1972 Apr 14 | 0054:36 | Launch by Molniya-M | KB |
| 0059 | Blok I burn | ||
| 0103 | Blok I MECO | ||
| 0103 | Blok I sep | ||
| 0155? | Blok L burn | ||
| Blok L MECO | |||
| 0159? | Blok L sep | ||
| 0217 | (Blok I?) | 91.21 223 x 444 x 64.92 | |
| 2028? | Pass EL1:4 | ||
| 1972 May 1 | 5782.1 1005 x 199667 x 65.0 | ||
| 1972 Oct | Still operating | ||
| 1975 Aug 24 | 5774.0 468 x 200002 x 64.9 | ||
| 1981 Apr | Reentered? | ||
2000-032A
\imps{2.5}{images/00032A}
FY-2B was developed by SARTI/Shanghai for CASC. It carries a 1.2km resolution radiometer. Launch mass is 1380 kg.
In the table below, velocities (supplied by CALT) are Earth-fixed.
FY-2C/D/E will have 5 radiometer channels but are otherwise similar.
| FY-2 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2000 Jun 25 | 1150 | Launch by CZ-3 | XSC |
| T+2:00 St 1 sep 55 km, 2.274 km/s | |||
| T+4:13 Fairing 178 km, 5.224 km/s | |||
| T+4:17 St 2 sep 181 km, 5.226 km/s | |||
| 1201 | T+11:43 St 3 MECO-1 299 km, 7.089 km/s | -400? x 300 x 27.4 | |
| T+17:48 St 3 MES-2 243 km, 7.189 km/s | |||
| 1213 | T+23:00 St 3 MECO-2 207 km, 9.804 km/s | ||
| 1213 | T+23:44 St 3 sep, 223 km, 9.797 km/s | 233 x 35820 x 27.4 | |
| 2000 Jun 26 | 0358? | AKM burn | |
| AKM sep | |||
| 2000 Jul 2 | 1438.22 35796 x 35859 x 1.1 | ||
| 2000 Jul 6 | First image | ||
| 2000 Jul 8 | 1436.00 35776 x 35793 x 1.1 GEO 104.4E | ||
| 2001 Jun 9 | 1435.72 35766 x 35792 x 0.3 GEO 103.1E | ||
| 2004 Jan 16 | 1436.11 35781 x 35791 x 0.3 GEO 104.7E | ||
| 2004 Oct | Move to 124E | ||
| 2004 Dec 1 | 1436.266 35788 x 35791 x 0.08 123.22E | ||
1985-109B
Morelos 2 was the second Mexican domestic comsat, owned by Mexico's SCT. It was deployed from Atlantis on 1985 Nov 27, on mission 61-B which included the Mexican payload specialist Rodolfo Neri Vela.
| Morelos 2 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1985 Nov 27 | 0746:50 | Deploy from Atlantis | |
| 0832 | PAM-D burn 86s | ||
| 0833 | burnout | ||
| 0835 | Sep | ||
| 1985 Nov 28 | 660.18 730 x 36742 x 24.5 | ||
| 1985 Nov 29 | 2058 | AKM burn | 1384.76 32793 x 36758 x 3.4 GEO 125.0W+13.4E |
| 1985 Dec 1 | 1434.93 35745 x 35781 x 3.0 GEO 106.5W+0.3E | ||
| 1985 Dec 2 | mv in | 1436.19 35774 x 35802 x 3.0 GEO 116.2W | |
| 1986 Jan 16 | In inclined orbit storage | GEO 116.5W | |
| 1986 May 26 | 1436.11 35776 x 35797 x 2.6 GEO 116.6W | ||
| 1988 Apr 4 | 1436.07 35775 x 35797 x 0.9 GEO 116.5W | ||
| 1989 May 10 | 1436.10 35725 x 35848 x 0.8 GEO 116.4W | ||
| 1989 May 11 | Incl. mvr | 1436.08 35780 x 35791 x 0.03 GEO 116.8W | |
| 1989 Jun | Operational use | ||
| 1990 Sep 26 | 1436.06 35772 x 35799 x 0.0 GEO 116.8W | ||
| 1992 Jan 25 | 1436.07 35784 x 35788 x 0.0 GEO 116.8W | ||
| 1994 Jan 1 | 1436.08 35780 x 35792 x 0.0 GEO 116.8W | ||
| 1996 Jan 30 | 1436.08 35778 x 35794 x 0.0 GEO 116.8W | ||
| 1998 Dec 8 | 1436.08 35777 x 35794 x 0.2 GEO 116.7W | ||
| 1998 Dec 16 | mv out | 1436.21 35783 x 35794 x 0.3 GEO 117.0W+0.04W | |
| 1999 Jan 26 | mv in | 1436.09 35778 x 35794 x 0.3 GEO 120.3W | |
| 2002 Jul 30 | mv out 120W | ||
| 2002 Aug 23 | mv in 110W | ||
| 2003 Sep 3 | 1436.10 35775 x 35797 x 4.2 GEO 109.3W | ||
| 2003 Sep 22 | mv out 109W | ||
| 2003 Nov 1 | mv in 115W | ||
| 2004 Jun 8 | 1436.08 35776 x 35795 x 4.9 GEO 115.0W | ||
2004-005A
A satellite launched as part of the Bezopasnost'-2004 military exercise was given the Kosmos-2405 name, but was renamed Molniya-1T in May 2004.
| Kosmos-2405 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2004 Feb 18 | 0706:16 | Launch by Molniya-M | PL 16/2 |
| 0715 | Blok-I MECO | ||
| 0715 | Blok-I sep | ||
| 0802? | Blok-L burn | ||
| 0804 | Blok-L sep | ||
| 2004 Feb 18 | 735.49 623 x 40600 x 62.8 | ||
| 2004 Feb 23 | 717.82 630 x 39726 x 62.8 | ||
2002-003A
Tsubasa, the MDS-1 Mission Demonstration Satellite is a generic bus built by NEC for NASDA, with a mass of 500 kg. It is possibly derived from the OICETS satellite and the MUSES-B bus. MDS-1 will test commercial satellite components. Launch is Jan 2002 on H2A 2024 No. 2. Mass is 449 kg (or 480 kg?), box + 2 panels. Size is 1.2 x 1.2 x 1.5m launch, 3.3 x 1.6 x 2m deployed. MDS is spin-stabilized. AOCS is 4 x 1N thrusters.
Planned orbit is 500 x 35735 km x 28.5 deg.
The H-IIA-2024 has four Castor IVXL SSBs and two SRB-As. This flight uses the 4/4D-LC fairing.
H-IIA made an experimental SES-3 burn at 60 percent thrust, terminated by depletion.
| MDS | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2002 Feb 4 | 0245 | Launch by H-2A | TNSC |
| T+0:10 SSB 1-2 on | |||
| T+1:10 SSB 1-2 sep 20 km 1.1 km/s | -6330 x 20 | ||
| T+1:16 SSB 3-4 on | |||
| T+2:16 SSB 3-4 sep 77 km 2.0 km/s | -6190 x 90 | ||
| T+2:24? SRB-A sep 84 km 2.0 km/s | -6190 x 100 | ||
| T+4:05 Fairing sep 168 km 2.9 km/s | |||
| T+6:30 St 1 MECO | |||
| T+6:38 St 1 sep 309 km 5.3 km/s | |||
| 0251 | T+6:44 Stage 2 MES | ||
| 0257 | T+12:19 Stage 2 MECO-1 | 499 x 500 | |
| T+24:36 Stage 2 MES-2 | |||
| T+27:28 Stage 2 MECO-2 | |||
| 0315 | T+30:18 Deployment of DASH failed | ||
| 0325 | T+40:55? VEP-3 sep | ||
| Adapter side panel sep | |||
| Adapter side panel sep | |||
| Spinup | |||
| 0331 | T+46:40 Stage 2 deploy MDS-1 | ||
| T+1:40:00 Stage 2 MES-3, test burn 50s, 60 percent thrust | |||
| T+1:40:51 MECO-3 | |||
| 2002 Feb 6 | 0152 | Magnetometer mast extended | |
| 2003 Feb 26 | Primary mission complete | ||
| 2003 Sep | endof SEDA operations | ||
1978-068A
Comstar D3 (Comstar 203) was Comsat General's third Intelsat 4A class satellite. From 1978 to 1984 it was stationed at 87W; from 1984 to 1986 it was at 76W. The satellite was retired in 1986.
| Comstar D3 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1978 Jun 29 | 2224 | Launch by Atlas Centaur | |
| T+2:20 BECO | |||
| T+2:23 Booster sep | |||
| T+3:05 Insulation panels sep | |||
| T+4:07 SECO | |||
| T+4:09 Atlas sep | |||
| T+4:19 MES-1 | |||
| 2234 | T+10:20 MECO-1 189 km Vrel = 7.786 km/s | 189 x 1810? x 28? | |
| 2248 | T+24:43 MES-2 559 km Vrel = 7.372 | ||
| 2250 | T+26:19 MECO-2 627 km Vrel= 9.406 | ||
| 549 x 35919 x 21.83 (MOR) | |||
| 2252 | T+28:34 Centaur sep, 807 km | ||
| 1978 Jun 30 | 0600? | Apo 1 | |
| 1600? | Apo 2 | ||
| 1978 Jul 1 | 0300? | Apo 3 | |
| 1300? | Apo 4 | ||
| 2330? | Apo 5 | ||
| 1978 Jul 1 | 2237 | AKM firing | |
| 1978 Jul 19 | 1428.11 35474 x 35786 x 0.1 GEO 157.0W+2.0E | ||
| 1978 Aug 1 | 1427.99 35470 x 35783 x 0.1 GEO 117.5W+2.0E | ||
| 1978 Aug 24 | mv in | 1436.17 35782 x 35793 x 0.1 GEO 86.9W | |
| 1979 Jan 4 | 1436.12 35780 x 35793 x 0.0 GEO 87.0W | ||
| 1980 Apr 30 | 1436.10 35783 x 35790 x 0.1 GEO 86.9W | ||
| 1982 Mar 23 | 1436.11 35783 x 35790 x 0.0 GEO 87.0W | ||
| 1984 Jan 1 | 1436.13 35782 x 35791 x 0.0 GEO 87.0W | ||
| 1984 Oct 28 | 1436.10 35783 x 35790 x 0.0 GEO 87.0W | ||
| 1984 Oct 31 | mv out of GEO | ||
| 1984 Nov 2 | mv out | 1431.76 35617 x 35785 x 0.1 GEO 83.6W+1.1E | |
| 1984 Nov 23 | mv in | 1436.13 35785 x 35789 x 0.2 GEO 75.9W | |
| 1985 Sep | Ownership to AT&T; | GEO 76W | |
| 1986 Mar 5 | 1436.10 35784 x 35788 x 0.0 GEO 76.0W | ||
| 1986 May 12 | 1436.15 35783 x 35792 x 0.2 GEO 76.0W | ||
| 1986 May 13 | mv out | 1438.11 35809 x 35842 x 0.2 GEO 76.0W+0.5W | |
| 1986 May 21 | orbit raise | 1451.69 36001 x 36181 x 0.2 | |
| 1988 Jun 4 | 1451.70 36006 x 36177 x 2.1 | ||
| 1992 Jul 10 | 1451.67 35991 x 36189 x 5.9 | ||