Friday, January 23, 2009
Thursday, January 22, 2009
Navstar 57
2007-062A
GPA IIR-18 (IIRM-5). SVN 57, PRN 29. Mass 2059 kg.
| GPS 57 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2007 Dec 20 | 2004:00 | Launch by Delta 7925 | CC SLC17A |
| T+1:03 SRM 1-6 off | |||
| T+1:05 SRM 7-9 on | |||
| T+1:07 SRM 1-6 sep | |||
| T+2:08 SRM 7-9 off | |||
| T+2:11 SRM 7-9 sep | |||
| T+2:20 Stage 1 dogleg 20s | |||
| 2008:23 | T+4:23 MECO | ||
| T+4:31 St 1 sep | |||
| T+4:36 SEIG-1 | |||
| T+4:43 St 2 dogleg, 10s | |||
| T+4:57 Fairing sep | |||
| 2014:48 | T+10:48 SECO-1 | 174 x 203 x 37.5 | |
| 2106 | T+1:02:29 SEIG-2 | ||
| 2107 | T+1:03:12 SECO-2 | 191 x 1241 x 37.95 | |
| 2108 | T+1:04:01 spinup | ||
| 2108 | T+1:04:04 St 2 sep | ||
| 2108 | T+1:04:42 TES | ||
| 2110 | T+1:06:08 TECO | 193 x 20368 x 40.0 | |
| 2112 | T+1:08:02 St 3 sep | ||
| 2112 | T+1:08:04 Yo weight from St 3 | ||
| T+1:47:12 SES-3 depletion | |||
| SECO-3 | 204 x 1224 x 32.91 | ||
| T+4:03:23 First apogee | |||
| 2007 Dec 22 | 2320 | AKM | 20149 x 20310 x 55.0 |
| 2007 Dec 31 | 719.94 20143 x 20317 x 55.0 | ||
Wednesday, January 21, 2009
NSS-7
2002-019A
New Skies NSS-7 is an A2100AX replacing NSS-K and NSS-803. Control from NSS/s'Gravenhage. K and Cu for AOR. Launch by Ariane by 2001. Mass 4700 kg.
Size 6.7 x 3.6 x 3.6m; ? span.
NSS-7 will provide TV, internet and video/data traffic.
| NSS 7 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2002 Apr 16 | 2302 | Launch by Ariane 44L | CSG ELA2 |
| T+2:30 PAL sep | |||
| T+3:30 St 1 sep | |||
| T+3:31 St 2 burn | |||
| T+4:17 Fairing sep | |||
| T+5:43 St 2 sep | |||
| T+5:46 St 3 burn | |||
| 2320 | T+18:52 St 3 MECO | ||
| 2322 | T+20:50 St 3 sep | ||
| 2002 Apr 16 | 630.79 221 x 35750 x 7.0 | ||
| 2002 Apr 21 | LAM-1 | 938.53 15047 x 35703 x 1.7 | |
| 2002 Apr 23 | LAM-2 | 1149.50 24200 x 35742 x 0.7 | |
| 2002 Apr 29 | 1030? | LAM-3 | 1436.07 35778 x 35793 x 0.0 |
| 2002 May 5 | 1436.09 35778 x 35794 x 0.0 GEO 23.0W | ||
| 2002 May 28 | mv to 21.5W | ||
| 2002 Jul 18 | 1436.14 35784 x 35789 x 0.1 GEO 21.6W | ||
| 2006 Aug 8 | 1436.10 35777 x 35796 x 0.0 GEO 22.0W | ||
Tuesday, January 20, 2009
SWAS
1998-071A
A NASA-GSFC SMEX mission, the Submillimeter Wave Astronomy Satellite was to be the first in that waveband. Originally scheduled for a 1995 launch, SWAS slipped to late 1998 because of Pegasus problems. Principal investigator was Gary Melnick of SAO, which operated the mission science center.
The 0.71m primary antenna was used to study molecular clouds.
600x600 km x 70 deg orbit. Launch by Pegasus XL from VAFB.
Spacecraft was a wasp-shaped double cone with two solar panels, plus the instrument module with the primary mirror, three radiator horns, and a magnetometer. Size 1.65 l 0.97 d, mass is 282 kg.
m1/m2 = 484/1254
The last science observations were taken on 2004 Jul 23; GSFC will use it as a software testbed until 2005 Sep.
| SWAS | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1998 Dec 5 | 2358 | L-1011 takeoff from VAFB | |
| 1998 Dec 6 | 0057:54 | Drop 12.2 km | |
| T+0:05 Stage 1 burn | |||
| T+1:05 Stage 1 burnout | |||
| T+1:31 Stage 2 burn | |||
| T+2:08 Fairing sep | |||
| 0100 | T+2:42 Stage 2 burnout | ||
| T+9:18 Stage 2 sep | |||
| T+9:29 Stage 3 burn | |||
| T+10:37 Stage 3 burnout | |||
| 0109:34 | T+11:37 Stage 3 sep | ||
| T+11:47 Deploy solar arrays | 98.09 634 x 699 x 70.0 | ||
| 2003 Sep | End of main mission | ||
| Begin Mars/Venus mission | |||
| 2003 Dec | Mars campaign | ||
| Idle | |||
| 2004 Mar | 2-week Venus campaign | ||
| 2004 Jul | 2-week Venus campaign | ||
| 2004 Jul 23 | End of science ops | ||
| 2005 Jun | Reactivate for Deep Impact obs | ||
| 2005 Aug | Deactivated | ||
Payload:
- 0.6m Al mirror Cassegrain telescope
Monday, January 19, 2009
Tance 1
2003-061A
\imps{2.5}{images/03061}
Launch of TC-1
\imps{2.5}{images/03061A}
The TC-1 satellite
Tan Ce (Explorer) 1, or Double Star DSP-E, Chinese/ESA magnetospheric satellites, to supplement the Cluster system and using backup European Cluster instruments. Equatorial DSP-E 550 x 66970 x 28.5 planned orbit. Launch Dec 2003 and Apr 2004 by CZ-2C/SM (or CTS). CTS top stage derived from SD. Places 1400 kg in SSO. Has FG-47 solid motor.
Spin-stabilized satellites, 350 kg built by CATC's Space Tech Inst. Spacecraft is a 2.1m dia 1.4m high spin stabilized (15 rpm) cylinder, with overall size 4.0m high 8.3m span. Used a direct ascent orbit with all three stages burning without coast phase, giving perigee around 23 deg N.
The PKM was described in a paper at IAC 2004. It is 1.4m dia. Mass is 2929 kg full, 2620 kg prop, 309 kg dry. Total impulse is 7477 kNs and Isp is 291.0s (Ve=2.854 km/s). For a TC-1 mass of 350 kg, the rocket equation gives a dV of 2.854 ln ( 3279 / 659 ) = 4.579 km/s.
Another source gives SM? 2.7m dia 1.5m long, 125 + 50 kg prop, 10.7 kN, Ve 2804 SMA: 2.7m dia 0.9m long, 21.7 kg propellant, 10.4 kN, Ve 2804 SM: 1.4m dia 2.3m long 2620 kg prop, 101 kN Ve 2863
Apogee was higher than planned.
| TC-1 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2003 Dec 29 | 1906:18 | Launch by CZ-2C/CTS | Xichang |
| 1908 | Stage 2 burn | ||
| 1914? | Stage 2 sep | ||
| 1915? | SM burn | -3604? x 570 x 28.5 | |
| 1915? | SM burnout | 555 x 78051 x 28.5 | |
| 1918? | SM sep | 570 x 78947 x 28.2 | |
| 1924? | Stage 2 reentry over 166E 3N | ||
| 2004 Jan 15 | 1643.59 557 x 78954 x 28.25 | ||
| 2007 Oct 14 | Reentry | ||
Payload:
- ASPOC Active spacecraft potential control
- FGM Fluxgate magnetometer
- PEACE Plasma electron and current expt
- HIA Hot ion analyser
- STAFF/DWP Spatio-temporal analysis of field fluctuations
- HEED High energy electron detector
- HEPD High energy proton detector
Sunday, January 18, 2009
Orion 1
1994-079A
Orion 1 was a Eurostar 2000 class satellite built for Orion Network Systems Inc, Rockville MD by British Aerospace Space Systems Ltd. It provided commercial transatlantic communication services.
This was the first comsat to use a very high apogee supersynchronous transfer. LEOP control was from MMS SCC,Stevenage. ORION had a ground station at Mt Jackson, Virginia. The satellite was reportedly registered with the UN by the UK (although the document does not appear to be in the public archive). It was also registered by the US in ST/SG/SER.E/288.
In Nov 1999 Loral Orion renamed the satellite Telstar 11. Loral Orion then became Loral Skynet.
| Orion 1 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1994 Nov 29 | 1021 | Launch by Atlas IIA (AC-110) | CC LC36A |
| 1025? | MECO, Atlas sep | ||
| 1026? | Centaur MES1 | ||
| 1031? | Centaur MECO1 | 185 x 188? x 26.0? | |
| 1045? | Centaur MES2 | ||
| 1048? | Centaur MECO2 | ||
| 1051 | Centaur sep | ||
| 1994 Nov 29 | 185 x 123855 x 25.69 (MMCLS) | ||
| 1994 Nov 29 | 2936.21 401 x 122688 x 25.5 | ||
| 1994 Nov 30 | 1023? | LAM-1 | 3766.27 25073 x 122543 x 3.4 |
| 1994 Nov 30 | 1130? | A1 at 123000 km | |
| 1994 Dec 1 | 1900? | P1 at 25073 km | |
| 1994 Dec 3 | 0112? | LAM-2 | 4140.99 35500 x 122584 x 1.3 |
| 1994 Dec 3 | 0240? | A2 at 123000 km | |
| 1994 Dec 4 | 1300? | P2 at 35500 km | |
| 1994 Dec 5 | 2300? | A3 at 123000 km | |
| 1994 Dec 7 | 0831? | LAM-3 | 2247.98 35725 x 65207 x 0.8 |
| 1994 Dec 7 | 1000 | P3 at 35000 km | |
| 1994 Dec 8 | 0430? | A4 at 65000 km | |
| 2300? | P4 at 35000 km | ||
| 1994 Dec 9 | 2249.17 35686 x 65286 x 0.8 | ||
| 1800? | A5 at 65000 km | ||
| 1994 Dec 10 | 1230? | LAM-4 | 1437.89 35625 x 36018 x 0.0 GEO 41.1W+0.5W |
| 1230? | P5 at 36000 km | ||
| 1994 Dec 25 | Move in | 1436.12 35776 x 35797 x 0.0 GEO 37.5W | |
| 1995 May 3 | 1436.13 35776 x 35798 x 0.0 GEO 37.5W | ||
| 1998 Sep 23 | 1436.22 35781 x 35797 x 0.0 GEO 37.6W | ||
| 1999 Oct 15 | 1436.13 35780 x 35794 x 0.0 GEO 37.5W | ||
| 1999 Nov | Renamed Telstar 11 | ||
| 2006 Aug 3 | 1436.13 35763 x 35811 x 2.1 GEO 37.6W | ||
| 2008 Feb 25 | 1436.12 35768 x 35805 x 3.6 GEO 37.6W | ||
Saturday, January 17, 2009
Cosmo-Skymed 3
2008-054A
Mass 1900 kg. Launch on azimuth 196 deg.
| COSMO 3 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2008 Oct 25 | 0228:21 | Launch by Delta 7420-10 | V SLC2W |
| T+1:04 SRB burnout | |||
| T+1:22 SRB sep | |||
| T+4:24 MECO | |||
| T+4:32 Stage 1 sep | |||
| 0232:58 | T+4:37 SEIG-1 | ||
| T+4:41 Fairing sep | |||
| 0239:46 | T+11:25 SECO-1 | 185 x 645 x 97.8 | |
| 0321:48s | T+53:27 SEIG-2 | ||
| 0322:00s | T+53:39 SECO-2 | ||
| 0326:21s | T+58:00 Stage 2 sep | 620 x 632 x 97.8 | |
| 0345:01 | T+1:16:40 SEIG-3 evasive | ||
| T+1:16:45 SECO-3 | 185 x 616 x 97.9 | ||
| 0355:01s | T+1:26:40 SEIG-4 Depletion burn, over Thule | ||
| T+1:26:51 Depletion initiation | |||
| T+1:27:08 SECO-4 | 185 x 605 x 98.3 | ||
Friday, January 16, 2009
Friday, January 9, 2009
Thursday, January 8, 2009
USA-110
1995-022A
The second Titan 4/Centaur SIGINT payload was launched on 1995 May 14. This launch had a 26.2 m payload fairing, suggesting a different payload, probably the successor to ORION. Launch details were classified from 4 min into the flight and launch sequence times are based on a standard profile. Observers noted that the Titan flew due east, suggesting a geostationary orbit launch.
| USA 110 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1995 May 14 | 1345 | Launch from LC40 | |
| 1347 | SRM sep (2:10) | ||
| 1349 | Payload fairing sep | ||
| 1350 | K-23 Stage 1 cutoff, sep | ||
| 1354 | K-23 Stage 2 cutoff | ||
| 1354 | TC-17 MES 1 | ||
| 1357 | TC-17 MECO1 | 165 x 455 x 28.5 (UN) | |
| 1408 | TC-17 MES 2 | ||
| 1413 | TC-17 MECO2 | 200? x 35900? x 26? | |
| 1926 | TC-17 MES 3 | ||
| 1928 | TC-17 MECO3 | 35800 x 36100? x 1? | |
| 1932 | TC-17 sep from USA 110 | ||
| 2001 Nov 20 | 1436.24 35289 x 36289 x 9.6 GEO 127.1E | ||
| 2003 Jan 1 | 1436.11 35367 x 36206 x 10.4 GEO 127.4E | ||
| 2004 Feb 24 | 1436.09 35447 x 36124 x 12.0 GEO 126.8E | ||
| 2007 Jun 15 | 1436.12 35468 x 36105 x 13.4 GEO 126.9E | ||
Sunday, January 4, 2009
Kosmos 2420
2006-017A
This was the second Kobal't-M satellite.
| Kosmos-2420 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2006 May 3 | 1738 | Launch by Soyuz-U | PL LC16/2 |
| 1742 | Blok A sep | ||
| 1747 | Blok I MECO | ||
| 1747 | Blok I sep | 168 x 338 x 67.2 | |
| 2006 May 6 | 89.41 166 x 323 x 67.1 | ||
| orbit raise | 89.93 186 x 355 x 67.1 | ||
| 2006 May 24 | 78.24 178 x 296 x 67.1 | ||
| 2006 May 25 | orbit raise | 89.93 189 x 352 x 67.1 | |
| 2006 May 28 | SpK-1 fiducial | ||
| 0741? | Deorbit | ||
| 0803? | Landed | ||
| 2006 Jun 17 | 89.32 184 x 297 x 67.1 | ||
| Orbit raise | 89.93 178 x 363 x 67.1 | ||
| 2006 Jun 30 | SpK-2 fid | ||
| 0625? | Deorbit | ||
| 0647? | Landed | ||
| 2006 Jul 2 | 89.30 173 x 306 x 67.1 | ||
| Orbit raise | 89.83 181 x 350 x 67.1 | ||
| 2006 Jul 7 | 89.66 181 x 333 x 67.2 | ||
| 2006 Jul 15 | 89.09 171 x 287 x 67.2 | ||
| 2006 Jul 19 | 168 x 270 x 67.1 | ||
| 1643? | Deorbit | ||
| 1709? | Landed | ||
Saturday, January 3, 2009
DSP-19
1999-017A
The Titan 4B returned to flight with core K-32, vehicle B-27, SRMU-8, a 402B model carrying the IUS-21 upper stage. SRM-1 burned and the IUS/DSP stack coasted to apogee. Then the SRM-1 motor was partially separated, but one connector stayed attached. Thermal tape wrapped on the connector made the separation system work incorrectly, a design problem that went back to the early days of IUS - it was just luck that it hadn't happened before. The SRM-2 exit cone was extended, but was fouled by SRM-1. The SRM-2 burn failed, stranding DSP 19 in transfer orbit. Orbital details were classified. DSP-19 was tumbling and it took several weeks to bring it under control.
The spacecraft was used for studies of high radiation dose effects and as a testbed for command software; it was shut down in 2008.
| USA 142 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1999 Apr 9 | 1701:00 | Launch by Titan 4B-27/IUS | CC LC41 |
| T+2:11 Stage 1 burn | |||
| T+2:26 SRMU sep | |||
| 1704:29 | T+3:26 Fairing | ||
| T+5:21 Stage 2 burn | |||
| T+5:22 Stage 1 sep | |||
| T+8:47 Stage 2 MECO | 188 x 718 x 28.6 | ||
| 1709:58 | T+8:56 Stage 2 sep | ||
| 1815:20 | T+1:13:27 SRM-1 | ||
| T+1:20:56 RCS-1 burn | 400? x 35000? x 28.5 | ||
| 2328:55 | T+6:29:44 SRM-1 sep partially | ||
| 2332:22 | T+6:33:08 SRM-2 burn | ||
| T+6:33 SRM-2 burn failed | |||
| 2334:15 | SRM-2 cutoff | ||
| 2341:52 | RCS depleted | ||
| 2354:59 | T+6:58 SRM-2 sep | ||
| 1999 Apr 10 | 0117:22 | IUS SRM-2 battery depleted | |
| 1999 Apr 30 | DSP under control | ||
| 2006 Aug | 593 x 34728 x 29.3 | ||
| 2008 Jul | Decommissioned | ||