Saturday, March 21, 2009
Friday, March 20, 2009
Wednesday, March 18, 2009
Optus B1
1992-054A
The second generation Aussat satellites, named Optus after their new owners Optus Communications Pty., used the larger HS-601 bus and were launched by the Chinese CZ-2E rocket from Xichang, with a Star 63F solid perigee kick motor to place them in geostationary transfer orbit. The satellites were originally owned by Hughes HCI, and delivered to Aussat on-orbit.
The first attempt to launch B1 was aborted two seconds after the Chang Zheng (Long March) 2E first stage ignited, and before it left the pad. A month later a new attempt met with success. Optus B1 lost its primary control processor on 2005 May 23. The 601 satellites had a recurrent problem with SCP failures, and by the time of the problem on this first HS-601 the issue was well understood and the satellite quickly resumed operations on the backup processor.
| Optus B1 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1992 Jun 26 | 1040 | Launch abort at TIG+2s | XSC |
| 1992 Aug 13 | 2300 | Launch by CZ-2E | XSC |
| T+2:05 Booster CO | |||
| T+2:07 Booster sep 40 km? | |||
| T+2:39 Stage 1 MECO | |||
| T+2:40 Stage 1 sep | |||
| T+3:20 Fairing | |||
| T+7:40 Stage 2 MECO | |||
| 2309 | T+9:33 Stage 2 VECO | ||
| 2310 | T+10:00? Stage 2 sep | ||
| 1992 Aug 14 | 97.13 200 x 1041 x 28.0 | ||
| 1992 Aug 14 | 0102 | Star 63F PKM burn | |
| 0104 | Burnout | ||
| 1992 Aug 14 | 0105? | Star 63F sep | 661.47 350 x 37188 x 23.5 |
| 1992 Aug 16 | 1400? | LAM-1 | 799.24 7064 x 37236 x 10.8 |
| 1992 Aug 20 | 1200? | LAM-2 | 1472.36 35657 x 37329 x 0.4 GEO 163.3E+8.9W |
| 1992 Aug 26 | 1435.85 35661 x 35902 x 0.3 GEO 152.0E | ||
| 1992 Nov 7 | 1436.17 35692 x 35883 x 0.2 GEO 151.7E | ||
| 1992 Nov 9 | mv out | ||
| 1992 Nov 15 | 1434.05 35690 x 35802 x 0.1 GEO 158.1E+0.5E | ||
| 1992 Nov 21 | 1436.04 35769 x 35801 x 0.1 GEO 160.2E | ||
| 1992 Dec 29 | 1436.11 35778 x 35795 x 0.0 GEO 160.0E | ||
| 1994 Apr 15 | 1436.11 35773 x 35800 x 0.0 GEO 160.0E | ||
| 1997 Apr 21 | 1436.10 35769 x 35804 x 0.0 GEO 160.0E | ||
| 1999 Jun 14 | 1436.10 35771 x 35801 x 0.1 GEO 160.0E | ||
| 2005 May 23 | Primary SCP loss | ||
| 2006 Aug 1 | 1436.09 35765 x 35807 x 0.1 GEO 160.0E | ||
| 2006 Aug | end of active inclination control | ||
| 2006 Dec 19 | 1436.10 35762 x 35810 x 0.5 GEO 160.2E | ||
| 2007 Feb | Move to 164E | ||
| 2008 Apr 12 | 1436.04 35767 x 35802 x 1.7 GEO 164.8E | ||
Tuesday, March 17, 2009
Raduga 2000
2000-049A
Globus No. 16L was launched in Aug 2000.
By error it was initially announced as a Kosmos satellite, Kosmos-2372.
| Raduga-1 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2000 Aug 28 | 2008:00 | Launch by Proton-K 401-02 | LC81/24 |
| 2017 | T+9:44 Stage 3 sep | ||
| Adapter sep | 88.23 184 x 190 x 51.6 | ||
| 2142? | Blok DM2 No 87L MES-1 | ||
| Debris 49E sep | 91.42 183 x 506 x 51.6 | ||
| 2149? | Blok DM2 MECO-1 | 645.15 239 x 36469 x 48.7 | |
| 2000 Aug 29 | 0240? | SOZ sep? | |
| 0240? | Blok DM2 MES-2 | ||
| 0245? | Blok DM2 MECO-2 | 1470.92 36377 x 36554 x 2.21 | |
| 0249 | Blok DM2 sep | ||
| 1472.49 36408 x 36583 x 2.2 GEO 88.6E+9.0W | |||
| 2000 Sep 9 | 1466.51 36275 x 36484 x 1.5 GEO 1.2E | ||
| 2001 Mar 2 | 1436.20 35784 x 35792 x 1.0 GEO 48.9E | ||
| 2001 Jun 6 | 1436.03 35778 x 35792 x 0.9 GEO 48.7E | ||
| 2003 Nov 13 | Relocate from 49E | ||
| 2003 Dec 6 | 1436.06 35781 x 35790 x 1.4 GEO 44.6E | ||
| 2004 May 26 | 1436.24 35785 x 35793 x 1.8 GEO 44.9E | ||
| 2006 Aug 3 | 1436.13 35779 x 35795 x 3.9 GEO 44.8E | ||
| 2008 Jul 18 | 1436.13 35763 x 35811 x 5.7 GEO 44.5E | ||
Monday, March 16, 2009
MSX
1996-024A
The Midcourse Space Experiment (MSX) was built by APL for BMDO.
Its main experiment was the SPIRIT 3 solid hydrogen-cooled infrared telescope which maintains the dewar at a temperature of 8.5K. The sensors aboard MSX are designed to study targets simulating ballistic missiles in their coast phase against the background of Earth and space.
An MSX dedicated target launch on Aug 31 from Kauai deployed 26 test objects from its post boost vehicle as targets for MSX. Between Aug 1996 and Feb 1997 five emissive reference spheres were ejected, with a sixth reflective sphere failing to eject.
In Nov 2000, the satellite was transferred to AFSPC from BMDO and used as a satellite tracking asset. By 2008 the SBV sensor performance was degraded to unusability and the satellite was removed from service by USAF Space Command.
The satellite had a mass of 2812 kg including 78 kg of solid hydrogen, was 5.1m high and 3.3m in diameter (1.8m across not counting the arrays). Control was from APL.
| MSX | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1996 Apr 24 | 1227:40 | Launch by Delta 7920-10 | V SLC2 |
| 1228:43 | GEM 1-3,7-9 burnout (T+1:03) | ||
| 1228:45 | GEM 4-6 ignite (T+1:05) | ||
| 1228:46 | GEM 1-3,7-9 sep (T+1:06) | ||
| 1229:48 | GEM 4-6 burnout (T+2:08) | ||
| 1229:51 | GEM 4-6 sep (T+2:11), 60 km | ||
| 1232:00? | St 1 MECO | ||
| 1232 | St 1 sep | ||
| 1233:14? | SES-1 T+4:34? | ||
| 1233:20? | Fairing sep | ||
| 1237:35? | SECO-1 | 185? x 900 x 99.4 | |
| 1322? | SES-2 | ||
| 1322? | SECO-2 | ||
| 1325 | Delta stage 2 sep | 103.02 897 x 906 x 99.4 | |
| 1404? | Delta stage 2 depletion | (224 x 863 x 96.6) | |
| 1996 May 1 | 1016 | SPIRIT 3 cover ejected | |
| 1996 Aug 25 | 896 x 907 x 99.4 | ||
| 1996 Aug 25 | 1334 | Emissive reference Sphere 1 ejected | 905 x 953 x 99.4 (sphere) |
| 1996 Aug 31 | Observed STARS launch | ||
| 1996 Sep 12 | Emissive ref sphere ejected at 14m/s | ||
| 1996 Oct 16 | Observed Red Tigress launch | ||
| 1996 Nov 11 | ERS 3 ejected | ||
| 1996 Dec 19 | ERS 4 ejected | ||
| 1997 Feb 12 | Observed LCLV launch | ||
| 1997 Feb 20 | Sphere 5 ejected | ||
| 1997 Feb 23 | Observed LCLV launch | ||
| 1997 Feb 26 | SPIRIT 3 cryogen depleted | ||
| 1997 Sep | Observed launches from Anna Plains | ||
| 2000 Nov | Transfer to Space Command | ||
| 2008 Jun 1 | out of operational service | ||
| 2008 Jul | Decomissioned | ||
Payload:
- SPIRIT 3 0.35m LWIR telescope, 2.5 to 28 microns; Band A: 6-11 mu; Band B: 4.23-4.36 mu; Band B2 4.2-4.5, Band C 11-13, Band D 13.5-16, Band E 18-26.
- Dewar cover with 15l of Ar (less than 1 kg)
- UVISI APL UV/vis spectrometer/imager
- Contamination experiments; Space environment effects
- OSDP Onboard IR signal processor
- SBV MIT-LL Space-based visible surveillance sensor with CCD camera
CBERS-1
1999-057A
\imps{2.5}{images/99057A}
ZY-1
The 1540 kg China-Brasil Earth Resources Satellite 1, ZY-1 ("Resource") is built by CAST. Size is 1.8 x 2.0 x 2.0 m, 9.8m span box +1 panel.
The Chinese use the Xian control center, China; the Brazilian center is CRC/INPE, San Jose dos Campos.
From late October to early November the satellite's on board engine raised the orbit to sun-synchronous altitude. After that, very small orbital tweaks have maintained the altitude. In 2003 Aug the X-band transmitter failed, ending the mission. A slightly larger burn on 2003 Aug 13 marked the satellite's retirement, according to analyst Phillip Clark. The upper stage broke up into more than 125 pieces in Mar 2000.
In Mar 2007, more pieces were cataloged, but in the orbital plane of the payload, suggesting a separate event.
| ZY-1 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1999 Oct 14 | 0316 | Launch by CZ-4B | TY |
| T+2:33 Stage 1 MECO | |||
| T+2:34 Stage 1 sep | |||
| T+2:54 Fairing | |||
| T+4:37 St 2 MECO | |||
| T+4:47 St 2 VECO | |||
| T+4:48 St 2 sep | |||
| T+4:48 St 3 burn | |||
| 0327 | T+11:18 St 3 MECO | ||
| 0328 | T+12:28 ZY 1 sep | ||
| 0330? | T+12:55 SACI-1 sep | ||
| 1999 Oct 20 | 99.54 727 x 746 x 98.6 | ||
| Cal burn | 99.59 733 x 745 x 98.6 | ||
| 1999 Nov 3 | Orbit raise | 99.63 734 x 748 x 98.6 | |
| 1999 Nov 5 | Orbit raise | 99.92 747 x 763 x 98.6 | |
| 1999 Nov 6 | Orbit raise | 100.06 753 x 770 x 98.6 | |
| 1999 Nov 8 | Orbit raise | 100.27 770 x 772 x 98.6 | |
| 1999 Nov 9 | Orbit raise | 100.32 773 x 774 x 98.6 | |
| 1999 Dec 17 | Orbit trim | 100.32 773 x 775 x 98.6 | |
| 2000 Feb 28 | Orbit trim | ||
| 2000 Mar 29 | Orbit trim | ||
| 2000 Mar 11 | 1304 | Stage 4 breakup | |
| 2000 Apr 22 | Orbit trim | ||
| 2000 Jun 23 | Orbit trim | ||
| 2000 Jun | WFI failed | ||
| 2000 Aug 16 | Orbit trim | ||
| 2000 Nov 10 | Orbit trim | ||
| 2000 Dec 21 | Orbit trim | ||
| 2001 Feb 12 | Orbit trim | ||
| 2001 Apr 12 | Orbit trim | ||
| 2001 Jul 6 | Orbit trim | ||
| 2001 Oct 10 | Orbit trim | ||
| 2001 Nov 1 | Orbit trim | ||
| 2001 Dec 6 | 100.31 772 x 775 x 98.5 | ||
| 2001 Dec 6 | Orbit trim | 100.32 773 x 774 x 98.5 | |
| 2003 Aug 13 | X-band system failure | 100.32 773 x 774 x 98.4 | |
| 2006 Feb? | mv | 100.41 774 x 782 x 98.4 | |
| 2007 Mar | Objects released | ||
Payload:
- Wide Field Imager, 860 km FOV with 260m res
- Hi Res CCD Camera, 20m res
- IR Multispectral Scanner, 80m res
Sunday, March 15, 2009
Skynet 4F
2001-005B
Skynet 4F was built by Astrium/Stevenage (fka Matra Marconi Space UK) for MOD's DPA (Defense Procurement Agency). Mass is 1489 kg launch 830 kg dry (or BOL?). Star 30E is 667 full 40 dry, rest of satellite is 822 full 790 dry? Launch was by Ariane in Feb 2001. Size is 1.5 x 1.8 x 1.9m with 16.1m span.
| Skynet 4F | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2001 Feb 7 | 2306 | Launch by Ariane 44L | CSG ELA2 |
| T+2:28 PAL sep | |||
| T+3:32 St 1 sep | |||
| T+3:35 St 2 TIG | |||
| T+4:02 Fairing sep | |||
| T+5:44 St 2 sep | |||
| T+5:48 St 3 TIG | |||
| 2325 | T+19:16 St 3 MECO | ||
| 2326 | T+20:55 SICRAL sep | ||
| 2328? | Spelda sep | ||
| 2331 | T+25:53 Skynet 4F sep | ||
| 2001 Feb 8 | 631.98 222 x 35811 x 7.0 | ||
| 2001 Feb 10 | 1842? | AKM | |
| 2001 Feb 12 | 1422.04 34707 x 36315 x 3.9 | ||
| 2001 Feb 14 | 1413.13 34719 x 35952 x 3.9 | ||
| 2001 Mar 7 | 1432.04 35619 x 35794 x 3.9 GEO 5.6E | ||
| 2001 Apr 3 | 1436.04 35777 x 35794 x 3.8 GEO 5.9E | ||
| 2001 Jun 6 | 1435.55 35762 x 35789 x 3.7 GEO 4.9E+0.13E/d | ||
| 2006 Aug 2 | 1436.09 35774 x 35798 x 1.4 GEO 6.0E | ||