Friday, January 22, 2010
Thursday, January 21, 2010
GE-7
2000-054B
Launch by Ariane, 2000 LMMS/Sunnyvale A2100 small version. In-orbit spare for GE-8 at 137W, replacing Satcom C-1 for cable distribution coverage of the US and the Caribbean. Launch mass 1935 kg. Dry mass 912 kg. Size is 4.10 x 3.60m, span 14.5m. A2100A bus.
| GE 7 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2000 Sep 14 | 2254 | Launch by Ariane 506 V130 | CSG ELA2 |
| T+0:00 EPC burn | |||
| T+7:00 EAP ignition | |||
| T+7:03 Launch | |||
| T+2:25 EAP sep | |||
| T+3:22 Fairing sep | |||
| T+9:57 EPC MECO | |||
| T+10:03 EPC sep | 50? x 1500? x 7? | ||
| T+10:10 EPS burn | |||
| T+27:17 EPS MECO | |||
| T+28:42 Astra sep | |||
| T+30:28 Sylda 5 sep | |||
| T+37:39 GE 7 sep | |||
| T+54:08 EPS depleted | |||
| 2000 Sep 15 | 644.56 584 x 36094 x 7.0 | ||
| 2000 Sep 16 | 681.01 2706 x 35818 x 5.4 | ||
| 2000 Sep 18? | LAM | ||
| 2000 Sep 19 | 1439.39 35832 x 35869 x 0.1 | ||
| 2000 Oct 20 | 1432.06 35695 x 35719 x 0.0 GEO 138.1W+1.0E | ||
| 2000 Nov 25 | 1436.06 35780 x 35792 x 0.0 GEO 137.0W | ||
| 2006 Aug 4 | 1436.07 35771 x 35800 x 0.0 GEO 137.0W | ||
Monday, January 18, 2010
Intelsat 706
1995-023A
The next launch went aboard Ariane only two months later. It was the first of three Intelsat 7A satellites built by Space Systems/Loral, and was initially scheduled for operation over 53 W to provide telephone and TV relay service for Europe, Africa, and the Americas, and direct-to-home television to Latin America. The satellite bus was 2.2 x 2.45 x 3.0 m in size, with the full satellite being 5.1m high and 27.2 m in span. The satellite had a mass of 4180 kg at launch, while the third stage had a mass of 2056 kg at the end of its burn. The satellite separated at 20 minutes after launch at an altitude of 250 km over Zaire and deployed its solar panels at 2 h 47 m mission elapsed time. The first apogee motor ignition was scheduled for the third apogee at 26h 44m into the flight. On reaching GEO the satellite's mass had dropped to 3650 kg, with a dry mass of 1778 kg.
| Intelsat 706 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1995 May 17 | 0634 | Launch | |
| 0637 | Stage 1 sep | ||
| 0639 | Stage 2 sep | ||
| 0640 | Stage 3 TIG at 5:49 | ||
| 0652 | Stage 3 MECO at 18:48 | ||
| 0654 | Stage 3 sep and avoidance maneuver | ||
| 1995 May 17 | 630.56 174 x 35785 x 7.1 | ||
| 1995 May 18 | 0900? | LAM-1 | |
| 1995 May 18 | 714.20 4379 x 35798 x 4.0 | ||
| 1995 May 19 | 0900? | LAM-2 | |
| 1995 May 19 | 1098.89 22014 x 35778 x 0.4 | ||
| 1995 May 20 | 2130? | LAM-3 | |
| 1995 May 20 | 1441.30 35735 x 36041 x 0.1 GEO 52.2W+1.3W | ||
| 1995 May 22 | 1438.10 35732 x 35919 x 0.1 GEO 53.5W+0.5W | ||
| 1995 Jul 10 | 1436.10 35784 x 35789 x 0.0 GEO 53.0W | ||
| 1996 Sep 18 | 1436.12 35775 x 35799 x 0.0 GEO 53.0W | ||
| 1999 Oct 18 | 1436.12 35779 x 35794 x 0.0 GEO 53.0W | ||
| 2004 Sep 23 | mv out | GEO 53W | |
| 2004 Nov | move in at 50E | ||
| 2004 Nov 26 | 1436.07 35774 x 35797 x 0.0 GEO 50.3E | ||
| 2006 Aug 3 | 1436.08 35774 x 35797 x 0.0 GEO 50.3E | ||
| 2009 Mar 21 | 1436.06 35772 x 35798 x 0.0 GEO 50.3E | ||
Saturday, January 16, 2010
Wednesday, January 6, 2010
Inmarsat 204
1992-021B
The final Eurostar class Inmarsat II satellite was launched on 1992 Apr 15. In July 1996 it was the AOR W satellite, backed up by MARECS-B.
| Inmarsat II F-4 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1992 Apr 15 | 2325:27 | Launch by Ariane 44L (V50) | CSG ELA2 |
| 2328 | Stage 1 sep (T+3:35) | ||
| 2330 | Stage 2 sep (T+5:45) | ||
| 2343 | Stage 3 cutoff, in GTO | ||
| 2345 | Telecom 2B sep (T+20:29) | ||
| 2347 | SPELDA sep (T+22:46) | ||
| 2349 | Inmarsat sep (T+24:54) | ||
| 2350 | H10+ sep burn (T+25:19) | ||
| 1992 Apr 17 | 633.50 295 x 35815 x 3.8 | ||
| 1992 Apr 17 | 1240? | LAM1 burn | |
| 1992 Apr 18 | 754.47 6360 x 35788 x 3.0 | ||
| 1992 Apr 19 | 0200? | LAM2 | 1041.92 19546 x 35786 x 2.3 |
| 1992 Apr 20 | 1300? | LAM3 burn | 1430.72 35558 x 35804 x 2.0 GEO 38.2W+1.3E |
| 1992 Apr 20 | Solar panels deployed | ||
| 1992 Apr 22 | 1300 | 1429.71 35530 x 35792 x 1.96 | |
| 1992 Apr 24 | 1436.37 35777 x 35807 x 2.0 GEO 32.0W | ||
| 1992 May 14 | 1436.06 35768 x 35803 x 2.0 GEO 32.2W | ||
| 1992 May | mv out | ||
| 1992 May 29 | 1145 | 1447.87 35998 x 36034 x 1.81 GEO 52.70W-2.9/d | |
| 1992 Jun 4 | 1436.10 35775 x 35798 x 2.0 GEO 54.1W | ||
| 1992 Oct 16 | 1436.13 35775 x 35799 x 2.1 GEO 53.9W | ||
| 1994 Sep 14 | 1436.14 35774 x 35800 x 2.5 GEO 54.0W | ||
| 1996 Jul | AOR W | GEO 54W | |
| 1997 Jul 7 | 1436.24 35774 x 35804 x 2.6 GEO 54.5W | ||
| 1997 Jul 17 | mv out | GEO 55W | |
| 1997 Sep | mv in | GEO 17W | |
| 1997 Oct 2 | 1436.13 35771 x 35803 x 2.5 GEO 17.0W | ||
| 1999 May 8 | 1436.08 35766 x 35806 x 2.6 GEO 16.8W | ||
| 1999 May? | mv out | ||
| 1999 Jun 14 | 1426.45 35589 x 35605 x 2.6 GEO 75.6E+2.4E | ||
| 1999 Jul 7 | mv in 109E | 1436.06 35770 x 35801 x 2.6 GEO 109.0E | |
| 2006 Aug 3 | 1436.03 35775 x 35796 x 2.4 GEO 109.1E | ||
| 2008 Feb 24 | 1436.20 35778 x 35799 x 6.4 GEO 108.8E | ||
Sunday, January 3, 2010
Saturday, January 2, 2010
USA-193
2006-057A
The first United Launch Alliance launch. NROL-21 is thought to be an LMSC experimental prototype for the FIA program; originally developed by Boeing, the prime contractor role was transferred during development. After launch, the spacecraft reportedly failed to respond to ground commands. As reentry approached in early 2008, the decision was made to use an AEGIS SM-3 to intercept the satellite.
Mass was about 2300 kg, including 450 kg of hydrazine.
The second stage was placed in a low orbit and probably reentered after a few days.
| NRO | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2006 Dec 14 | 2100:00 | Launch by Delta 7920 | V SLC2 |
| T+1:04 SRM 1-6 off | |||
| T+1:05 SRM 7-9 on | |||
| T+1:26 SRM 1-6 sep | |||
| T+2:11 SRM 7-9 sep | |||
| T+4:23 MECO | |||
| T+4:31 St 1 sep | |||
| T+4:37 SES-1 | |||
| T+4:41 Fairing | |||
| 2110 | T+10:58 SECO-1 | 185 x 374 x 58.6 | |
| 2155 | T+55:13 SES-2 | ||
| 2155 | T+55:19 SECO-2 | 354 x 376 x 58.5 | |
| 2157 | T+57:50 Stage 2 sep | ||
| 2235 | T+1:35:50 SES-3 | ||
| 2235 | T+1:35:55 SECO-3 | ||
| 2320 | T+2:20:00 SES-4 | ||
| 2320 | T+2:20:59 SECO-4 depletion | 170 x 268 x 52.0 (B, UN) | |
| 2006 Dec 14? | 91.76 355 x 367 x 58.53 (UN) | ||
| 2006 Dec 20 | 91.73 351 x 367 x 58.5 | ||
| 2007 Jun 1 | 91.30 332 x 343 x 58.5 | ||
| 2008 Feb 1 | 89.94 270 x 272 x 58.5 | ||
| 2008 Feb 21 | 89.50 242 x 257 x 58.5 | ||
| 0330? | Intercept by SM-3 W of Hawaii | ||
| 0345? | Debris reentry over Prince George, B.C. | ||
| 2008 Mar-Apr | debris reentry | ||
| 2009 Oct 28 | Last debris (GH) entry | ||
Friday, January 1, 2010
Sirius 6
2007-057A
SES Sirius AB's Nordic television satellite at 5E. SES Sirius is the former Nordic Satellite AB (NSAB) and is owned 75 percent SES ASTRA and 25 percent SSC. It is based in Solna.
LM A2100AX with 46 Ku transponders. Launched by Proton M No 53523 and Briz M no 88523. Size is 2.2 x 2.2 x 5.5m, 27m span. Mass is 4600 kg (SES Sirius) or 4385 kg (ILS). The sub-Saharan-Africa beam provided the SES Astra 4A service previously assigned to AMC 12.
| Sirius 4 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2007 Nov 17 | 2239:47 | Launch by Proton-M 53523 | KB LC200/39 |
| T+2:03 St 1 sep | |||
| T+5:33 St 2 sep | |||
| T+5:48 Fairing sep | |||
| 2249:33 | T+9:46 St 3 sep | -942 x 164 x 51.5 | |
| 2251:07 | T+11:22 MES-1 | ||
| 2257? | St 3 reentry | ||
| 2258:39 | T+18:52 MECO-1 | 173 x 173 x 51.5 | |
| 2348:09 | T+1:08:22 MES-2 | ||
| 2007 Nov 18 | 0004:34 | T+1:24:47 MECO-2 | 258 x 5000 x 50.3 |
| 0209:16 | T+3:29:29 MES-3 | ||
| 0225:48 | T+3:46:01 MECO-3 | 375 x 35812 x 49.1 | |
| 0227:09 | T+3:47:22 DPB sep | 385 x 35681 x 49.1 | |
| 0730:03 | T+8:50:16 MES-4 | ||
| 0737:15 | T+8:57:28 MECO-4 | 7002 x 35776 x 17.3 | |
| 0752:47 | T+9:13:00 Briz 88523 sep | 6916 x 35478 x 17.4 (TLE) | |
| 2007 Nov 19 | 821.590 9604 x 35755 x 13.3 | ||
| 2007 Nov 21 | 887.51 12676 x 35751 x 10.0 | ||
| 2007 Nov 24 | 1250.94 28391 x 35767 x 1.8 | ||
| 2007 Nov 25 | 1047 | LAM | |
| 2007 Nov 26 | 1431.98 35636 x 35775 x 0.0 GEO 0.03E+1.0E/d | ||