https://web.archive.org/web/20080504033315/http://digest-archive.degrassi.ca/DD41.htm
Friday, February 12, 2010
Thursday, February 11, 2010
STS-99 (Endeavour)
2000-010A
STS-99 launch mass is 116374 kg, landing mass is 102362 kg. SRTM is about 14700 kg.
Total OMS/RCS fuel mass on the orbiter was 12120 kg.
A thruster on the mast failed to work, but that had only a limited impact on the mission. Initially the science program was to be cut short a day to allow for a possible spacewalk to save the mast if it failed to retract, but then NASA decided to just jettison the mast if there were problems. Indeed, on the first attempt the mast did not latch when retracted and it looked for several hours as if a jettison might be needed. But after several tries the canister latched safely.
The Shuttle Flight Weight Summary reports 118 kg deployed from STS-99, but this seems to be an error.
| STS-99 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1999 Dec 5 | Tow to VAB/1 | ||
| 1999 Dec 6 | ET mate | ||
| 1999 Dec 13 | 1200 | Roll to LC39A | |
| 2000 Feb 11 | 1743:40 | Launch | LC39A |
| 1745:43 | T+2:03 SRB cutoff | ||
| 1745:45 | T+2:05 SRB sep | ||
| 1745:56 | T+2:16 OMS assist 1:42 | ||
| 1747:38 | OMS Ass CO | ||
| 1752:03 | T+8:34 (or T+8:23) MECO | ||
| 1752:23 | ET sep | 80? x 225 | |
| 1818:40 | OMS-2 1:55 55.7 m/s | 89.24 227 x 245 x 57.0 | |
| 1820:35 | OMS-2 CO | ||
| 1916 | PLBD open | ||
| 2157:40 | RCS-1 7.6s 0.5m/s | ||
| 2327 | Mast deploy begins | ||
| 2344 | Mast deploy complete 61m | ||
| 2000 Feb 12 | 0531 | Begin mapping | |
| 2000 Feb 13 | 0743 | RCS trim 1 flycast, 15s 1.0m/s | |
| 2000 Feb 14 | 0836:40 | RCS trim 2 17s 1.1m/s | |
| 89.18 226 x 241 x 57.0 | |||
| 2000 Feb 15 | 0722 | RCS Trim 3 15s 1.1m/s | |
| 2000 Feb 16 | 0806 | RCS Trim 4 11s 0.8m/s | |
| 2000 Feb 17 | 0809 | RCS Trim 5 12s 0.9m/s | |
| 2000 Feb 18 | 0739 | RCS Trim 6 15s 1.1m/s | |
| 2000 Feb 19 | 2036 | RCS Trim 7 21s 1.4m/s | |
| 2000 Feb 21 | 1156 | end of mapping | |
| 1233 | OBA to stow position | ||
| 1317 | Mast stow begins | ||
| 1339 | Mast stowed but not latched | ||
| 1550 | Mast stow successful | ||
| 2000 Feb 22 | 1815 | PLBD closed | 89.12 226 x 235 x 57.0 |
| 2225:10 | Deorbit 72m/s 2:19 | ||
| 2217:30 | OMS cutoff | -20? x 230 x 57.0 | |
| 2250:08 | Entry interface | ||
| 2322:24 | Landing KSC RW33 | ||
| 2322:35 | NGTD | ||
| 2323:25 | Wheels stop | ||
| 2000 Feb 23 | 0430 | Tow to OPF/2 | |
Amos 3
2008-022A
IAI Spacecom (Space Communication) Ltd satellite, built by IAI.
Zenit-3M/DM-SLB launch from Baykonur, the first Land Launch mission. Launch Launch Zenit-3SLB built by Space International Services (Moscow), a collaboration of Energiya and Yuzhnoe; launch services and mission planning provided by SeaLaunch LLC. The Zenit-3SLB was Zenit-2SB60 No. 1 with the DM-SLB No. 1TL upper stage. It placed Amos 3 directly in geosynchronous orbit, eliminating the need for an apogee thruster. Located at 4W, replacing Amos 1. Alcatel payload.
| Amos 3 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2008 Apr 28 | 0500:00 | Launch by Zenit-3SLB | KB LC45/1 |
| 0502:28 | Stage 1 sep | ||
| 0505:23 | GO sep | ||
| Stage 2 MECO | |||
| 0508:33 | Stage 2 sep | ||
| 0508:40 | DM-SLB MES-1 dV about 1.01 km/s | -2250? x 180? | |
| 0511:09 | MECO-1 | 174 x 429 x 51.3 | |
| 0615:53 | MES-2 | ||
| 0621:25 | MECO-2 | 180 x 39064 x 48.8 | |
| 1205:49 | MES-3 | ||
| 1208:21 | MECO-3 | ||
| 1219:11 | DM sep | ||
| 2008 Apr 29 | 1488.33 34236 x 39368 x 0.7 | ||
| 2008 May 2 | Lower apogee | ||
| 2008 May 3 | 1440.80 34247 x 37509 x 0.7 | ||
| 2008 May 11 | 1433.87 35570 x 35915 x 0.1 GEO 0.4W+0.5E/d | ||
| 2008 May 12 | 1439.12 35762 x 35928 x 0.1 GEO 1.7W+0.8W/d | ||
| 2008 May 23 | 1436.11 35783 x 35790 x 0.0 GEO 2.5W | ||
Tuesday, February 9, 2010
Monday, February 8, 2010
USA-200
2008-010A
NROL-28 (USA 200) Atlas V 411 AV-006 from SLC3E. Carries SDS payload and HEO-2 SBIRS payload, and probably Interim Polar System 3, reported to have entered operation in Nov 2008.
| NROL 28 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2008 Mar 13 | 1002 | Launch | V SLC3E |
| T+1:35 SRM burnout | |||
| T+2:30 SRM sep | |||
| T+4:10 MECO | |||
| T+4:10 CCB sep | |||
| T+4:29 Centaur MES | |||
| T+4:39 Fairing sep | |||
| 1017? | T+15m? Centaur MECO-1 | 180? x 400? x ? | |
| 1026? | T+24m? MES-2 | ||
| 1030? | T+28m? MECO-2 | ||
| 1033? | T+31m? Centaur sep | ||
| 2008 Mar 22 | 684.39 1112 x 37581 x 63.6 | ||
Sunday, February 7, 2010
Xinnuo 2
2006-048A
In response to the growing demand of the regional market, SINOSAT is adding a new member, SINOSAT-2, to its fleet of satellites. With 24 Ku-band transponders on board, SINOSAT-2 will be the first spacecraft based on the chinese high power satellite platform, known as DFH-4.
Being the major satellite platform of new generation, DFH-4 is of high power, high quality and high reliability. Based on the mature DFH-3 platform, DFH-4 is designed and developed to meet similar performance as that of A2100AX, FS1300 and SB3000B3. To ensure the time schedule and performance requirements, the telecommunication payload of the SINOSAT-2 payload will be imported from Alcatel.
SINOSAT-2 is expected to be delivered in the first half of 2005. Scheduled to be launched in 2005, the lifetime of SINOSAT-2 will be 15 years. The new satellite will serve the need for TV broadcasting, DirecPC and broadband multimedia systems in China as well as the neighboring areas
Sinosat Comms. Co. Ltd of Beijing. First DFH-4. Chinese DBS satellite for Ku-band TV and broadband at 92.2E. Mass up to 5300 kg. Box + 2 panels. Launch by CZ-3B. Span would have been around 30m?
After orbit insertion, the satellite suffered a comprehensive failure, with the solar panels failing to deploy. The satellite was able to test out internal systems using the limited power available from the folded-up exterior panels. It was retired in 2008 and the orbit was raised in two stages in mid and late 2009.
| Sinosat-2 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2006 Oct 28 | 1620 | Launch by CZ-3B | Xichang |
| T+2:07 Booster sep | |||
| T+2:27 St 1 sep | |||
| T+3:52 Fairing sep | |||
| T+5:32 St 2 sep | |||
| T+5:32 St 3 MES-1 | |||
| 1630? | T+10:31? MECO-1 | 160? x 450? x 28.5? | |
| 1641? | T+21:21? MES-2 | ||
| 1644? | T+24:20? MECO-2 | ||
| 1644 | GTO perigee | ||
| 1646? | T+26:00? Stage 3 sep | ||
| 186 x 35797 x 28.70 | |||
| LAM-1 | |||
| 694.50 3372 x 35827 x 18.11 | |||
| 2006 Oct 31 | 866.18 11562 x 35889 x 7.7 | ||
| 2006 Oct 31 | 869.80 11721 x 35889 x 7.7 | ||
| 2006 Nov 1 | LAM | ||
| 2006 Nov 2 | 1427.95 35468 x 35784 x 0.4 | ||
| 2006 Nov 5 | 1435.81 35662 x 35900 x 0.4 GEO 92.5E | ||
| 2006 Nov 17 | 1435.74 35660 x 35899 x 0.4 GEO 93.4E | ||
| 2006 Nov 30 | 1435.93 35664 x 35902 x 0.3 GEO 94.5E+0.04E/d | ||
| 2006 Dec 21 | 1436.06 35666 x 35904 x 0.3 GEO 95.2E | ||
| 2007 Feb | Move out from 92E | ||
| 2007 Jul 7 | Move in at 101E | ||
| 2007 Sep 1 | 1436.11 35686 x 35887 x 0.4 GEO 103.4E+0.0E/d | ||
| 2007 Oct | Drift off station | ||
| 2007 Oct 28 | 1436.57 35704 x 35887 x 0.5 GEO 100.4E+0.1W/d | ||
| 2008 Jun 8 | 1436.50 35704 x 35884 x 1.1 | ||
| 2008 Jun 12 | 1436.49 35703 x 35884 x 1.1 GEO 62.2E+0.1W/d | ||
| Adjust orbit | |||
| 2008 Jun 14 | 1434.84 35675 x 35848 x 1.2 GEO 65E+0.3E/d | ||
| 2008 Jul 15 | 1434.79 35675 x 35846 x 1.2 | ||
| 2008 Nov 1 | 1435.21 35689 x 35858 x 1.5 GEO 105E+0.2E/d | ||
| 2009 May 10 | 1435.71 35701 x 35860 x 2.0 GEO 136E | ||
| 2009 Jul 15 | 1436.17 35709 x 35866 x 2.1 GEO 138.3E | ||
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