https://web.archive.org/web/20120203193937/http://digest-archive.degrassi.ca/DD58.htm
Saturday, June 6, 2009
Thursday, June 4, 2009
Panamsat 9
2000-043A
A new PAS 9, an HS-601HP satellite, was ordered in 1998 for launch in 2000. Launch by Sea Launch in Jul 2000 2000 Jul 28 2242 UTC sched. 3650 kg launch, 2389 kg BOL, 26m span 7m w. Two dishes, two panels. C and Ku band replacing PAS 5 at 58W.
| PAS 9 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2000 Jul 28 | 2242:00 | Launch by Zenit-3SL | |
| T+2:23 St 1 MECO | |||
| T+2:26 St 1 sep | |||
| T+2:29 St 2 MES | |||
| T+3:10 Fairing sep, 124 km | |||
| 2251 | T+9:05 St 2 MECO, sep | -2220 x 264 x 1.2 | |
| Lower fairing sep | |||
| T+9:15 DM-SL MES-1 | |||
| 2256 | T+14:40 MECO-1 | 110.07 200 x 2260 x 1.2 | |
| T+53:57 MES-2 | |||
| T+59:40 MECO-2 | |||
| 2352 | T+1:09:54 DM-SL sep | 664.64 1928 x 35772 x 1.2 | |
| T+3h50m DM-SL disposal burn | |||
| 2000 Jul 29 | 664.64 1928 x 35772 x 1.2 | ||
| 2000 Jul 31 | 0100? | LAM1 | 765.41 6919 x 35759 x 0.1 |
| 2000 Aug 1 | 1550? | LAM2 | 998.61 17672 x 35760 x 0.1 |
| 2000 Aug 3 | 1730? | LAM3 | 1427.35 35444 x 35786 x 0.1 |
| 2000 Aug 9 | 1436.08 35778 x 35794 x 0.1 GEO 61.5W | ||
| 2000 Aug 30 | mv out | ||
| 2000 Sep 4 | mv in | 1436.18 35786 x 35790 x 0.0 GEO 58.0W | |
| 2006 Jul 31 | 1436.10 35780 x 35792 x 0.0 GEO 58.0W | ||
Wednesday, June 3, 2009
Risat-2
2009-019A
India bought a TECSAR-class radar satellite from Israel after its own RISAT-1 fell behind schedule.
PSLV-C12, a CA model, was assigned to the mission. It used S139 first tage, PL40 second stage, S7 third stage and L1.6 PS4.
Mass 300 kg.
Planned orbit 550 x 550 x 41.
| RISAT 2 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2009 Apr 20 | 0115 | Launch by PSLV-CA | SDSC SLP |
| T+0:53 Sep PS1 50 km | |||
| T+0:53 PS2 burn 50 km | |||
| T+3:23 Fairing sep | |||
| T+4:23 PS2 sep 147 km? | |||
| T+4:245 HPS3 burn 148 km | |||
| 0123 | T+8:38 HPS3 burnout 283 km? | ||
| 0129:30? | T+15m? PS4 burn 560 km over equator | -1000? x 560 x 20? | |
| 0132? | PS4 burnout | 455 x 557 x 41.1 | |
| 0133:20 | T+18:20 PS4/RISAT sep | ||
Tuesday, June 2, 2009
Monday, June 1, 2009
ATV-1 (Jules Verne)
2008-008A
Launch by Ariane 5ES, a version with the Vulcain 2 based EPC and uprated EAP combined with the Ariane 5G's P2000 EPS, uprated for a second short burn but with a short fuel load of only 5200 kg (formerly known as EPS-V, Versatile EPS). The ATV itself uses R4D engines, already ISS-qualified.
Launch mass 19400 kg. Ariane launch mass 775t. EPS is 1300 kg dry 7500 kg full not including VEB (usually 1370 kg full 1300 kg dry) and 345 kg, 3.94m dia SDM (Separation and Distancing Module) adapter.
Later flights will have a 20750 kg mass and will be delivered to 300 x 300 km. Jules Vernes is spacecraft M8002MS to the TDRS nework.
Propulsion module is EADS-ST/Bremen; Avionics module is EADS-Astrium/Toulouse; cargo module is Thales Alenia/Torino. Overall management is EADS-ST/Les Mureaux. Integration was in Bremen. ATV-CC at CNES Toulouse.
The Automated Transfer Vehicle will fly on a single-stage Ariane 5E. Lead design is Aerospatiale/Les Mureaux (Ae Matra Lanceurs) with DASA/Bremen (Astrium Space Infrastructure) for production. Now EADS LV/ATV Les Mureaux; Arianespace/Evry. Mangement by ESA/MSM. Shell by Alenia Spazio/Torino.
The ATV will fly every 1.5 yr for supply and reboost.
Size is 10.3m long 4.5m dia.Span 22m. Four R-4D-11 490N main engines and 28 (span 18.5 in another source)
On deorbit, ATV can carry 6500 kg of garbage to reentry over the Pacific.
At Feb 2008:
| ATV dry w SDM | 10470 kg | |
| ATV dry no SDM | 10075 kg | |
| ATV prop | 6475 kg | |
| ATV wet no SDM | 16550 kg | |
| JV dry cargo | 1300 kg | |
| JV Water/O2 | 302 kg | |
| JV ISS prop | 860 kg | |
| JV total cargo | 2462 | |
| ATV w/cargo | 19012 kg | |
| SDM | 345 | |
| Reserve? | 50 | |
| ATV w/cargo and SDM | 19407 |
Size 9.79m long 4.48m dia 22.3m span.
Propulsion module by Astrium SI/Bremen includes MON (mixed oxides of Nitrogen)/MMH with 4 x 490N Marquardt R4D engines and RCS with 20 x 220N. Astrium/Lampoldshausen 220N thrusters. Spacecraft structure by Oerlikon Cotraves, integrated cargo carrier by Alenia Spazio.
The Automated Transfer Vehicle is built by DASA/Astrium in production. The first ATV, the Jules Verne ATV, is built at EADS-LV/Les Mureaux. It has 5 R-4D engines.
During phasing, ATV will demo attitude control, GPS navigation, orbit control, and a collision avoidance manuever (CAM).
The EPS deorbit burn occured at 06:28:31 UTC and lasted 16 seconds. It was followed 8 seconds later by a propellant dump. It was then in a direct reentry trajectory that was followed by the Awarua tracking station. Contatc was lost at an altitude of 120 km. The crash into the ocean came a few minutes later. (ESA info via Dan Deak)
At undocking in Sep, ATV arried 900 kg dry waste and 254 kg liquid waste.
| Jules Verne | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2008 Mar 9 | 0403:04 | Vulcain 2 ignition | |
| 0403:11 | T+0:07 Launch by Ariane 5ES-ATV L528 | CSG ELA3 | |
| T+2:19 EAP sep 60.8 km Vrel=2.007 km/s | |||
| T+3:29 Fairing sep, 106.3 km | |||
| 0411:59 | T+8:55 EPC MECO 132 km | -1304 x 139 x 51.24 | |
| 0412:04 | T+9:00 EPC sep 133 km | ||
| 0412:12 | T+9:08 EPS MES-1 9m, 134 km | ||
| 0417? | EPC reentry | ||
| 0420? | EPC impact off coast of Portugal 14.7W | ||
| 0420:17 | T+17:13 EPS MECO-1 146 km | 137 x 260 x 51.6 | |
| 45 min coast | |||
| 0505:14 | T+1:02:10 EPS MES-2 30s 270 km | ||
| 0505:44 | T+1:02:40 EPS MECO-2 | 260 x 260 x 51.6 | |
| 0509:43 | T+1:06:39 EPS sep | ||
| 0509:53 | T+1:06:49 Avoidance burns | ||
| ATV arrays deploy | |||
| 0628:31 | T+2:24:27 EPS MES-3 deorbit | ||
| 0628:47 | T+2:24:43 EPS MECO-3 | ||
| 0648? | EPS reentry over S Pacific | ||
| 0651 | T+2:48 EPS end of mission | ||
| 2008 Mar 11 | 0537 | 89.77 253 x 272 x 51.6 | |
| 2008 Mar 11 | 1501:09 | Main engine burn TE1 6m/s | |
| 1612:39 | Main engine burn TE2 6m/s | ||
| 2052 | 90.18 275 x 291 x 51.6 | ||
| 2008 Mar 12 | 1312:23 | TP1 dV 6m/s | |
| 1401:29 | TP2 dV 6m/s | 90.72 302 x 316 x 51.7 | |
| 2008 Mar 14 | 0757:35 | Collision avoidance test burn CAM, 5.3m/s | |
| burn 2 | |||
| 2008 Mar 18 | Height adjust burn 1 | 90.71 306 x 311 x 51.6 | |
| 2008 Mar 18 | Height adjust burn 2 | ||
| Flyby under ISS at 30 km | 91.16 327 x 335 x 51.6 | ||
| 2008 Mar 19 | 0530:03 | TV2-1 Orbit adjust 2.1m/s | |
| 0615:41 | TV2-2 Orbit adjust 2.1m/s | ||
| 1021:02 | IF1 0.14m/s burn to enter parking pos | ||
| 1106:48 | IF2 0.02m/s | ||
| 1151:04 | IF3 1.32m/s | 91.35 339 x 341 x 51.6 | |
| Parking position 2000 km ahead of ISS | |||
| 2008 Mar 20 | 1313:50s | SK1-1 stationkeeping | |
| 1404:41s | SK1-2 stationkeeping | ||
| 2008 Mar 25 | 91.35 340 x 341 x 51.6 | ||
| 2008 Mar 27 | Move to prep for D-0 | ||
| 2008 Mar 27 | 91.35 340 x 341 x 51.6 | ||
| 2008 Mar 29 | D+0 Demo Day 1 | ||
| 1419 | Prox ops begin at 39km range, 5 km below | ||
| 1557 | At S2 hold point, 3.5km | ||
| Flyby 3.5 km from ISS above Vbar using rel GPS | |||
| 1730 | Escape mvr | ||
| 2008 Mar 29 | 91.00 321 x 325 x 51.6 | ||
| 2008 Mar 31 | Demo day 2 | ||
| D+2d Demo Day 2 | |||
| Begin prox ops at 39 km range, 5 km below | |||
| On Vbar at 250m | |||
| 1550? | Approach at 150 m | ||
| Retreat to 180m | |||
| 1617 | Hold at 19m, S4 hold | ||
| 1638 | Approach to 11m of ISS on Vbar, S41 hold | ||
| 1643 | Retreat to 20m, S4 hold | ||
| 1652 | Escape mvr | ||
| 1702? | Hold at 800m | ||
| 2008 Apr 1 | 0000? | E+7hr TA burn, transfer above ISS | |
| 2008 Apr 1 | 0224 | 91.18 325 x 339 x 51.6 | |
| 1900 | 91.53 348 x 351 x 51.6 | ||
| 2000? | E+27hr TB burn, transfer below ISS | ||
| 2008 Apr 3 | 1119s | S1 hold point, 15.5km | |
| 1205s | S2 hold point, 3.5km | ||
| 1237s | Leave S2 | ||
| 1317s | Arrive at 250m S3 hold | ||
| 1333 | Optical tracking on, 250m range | ||
| 1354s | Resume approach from S3 | ||
| 1415 | 19m, begin hold at S4 | ||
| 1435 | Resume approach from S4 | ||
| 1438 | 11m, S41 hold, final approach | ||
| 1445 | Docking with Zvezda | ||
| 2008 Apr 4 | 1100 | 91.31 338 x 339 x 51.6 | |
| 2008 Apr 21 | ISS orbit raise | ||
| 2008 Jun 19 | 0641 | ISS orbit raise with OCS engines | |
| 2008 Jul 22 | 91.42 337 x 351 x 51.6 | ||
| 2008 Jul 23 | 1618s | ATV burn 1237s | 91.56 344 x 358 x 51.6 |
| 2008 Aug 13 | 0758 | ISS orbit raise with OCS engines | |
| 2008 Aug 27 | 1611 | DAM Burn to avoid K2426 deb, 1m/s | |
| 2008 Sep 5 | 2129 | Undocking | |
| 2130s | Sep-1 burn 4m/s 316s | ||
| 2008 Sep 15 | 91.40 338 x 347 x 51.6 | ||
| 2008 Sep 18 | Orbit lower | 90.74 300 x 321 x 51.6 | |
| 2008 Sep 28 | Orbit raise | ||
| 2008 Sep 29 | 0100 | 91.13 322 x 337 x 51.6 | |
| 2008 Sep 29 | 1000:27 | DO-1 29.8m/s? 6 min | |
| 1258:18 | DO-2 70.3m/s 14:20 | ||
| 1312:38 | DO-2 CO | -11? x 334 x 51.6 | |
| 1331 | Reentry over approx 130W 45S at 120km | ||
| 1335? | Breakup at 75 km | ||
| 1346? | Debris impact Pacific | ||
NOAA-19
2009-005A
NOAA N' will be launched by Delta 2 in 2009 Feb. On 2003 Sep 6 NOAA N' was dropped while being moved and was heavily damaged.
NOAA 19 will replace NOAA 18 in a 2pm orbit as the primary afternoon spacecraft.
The spacecraft was 4.2 m long 1.88m dia, with a 2.7 x 6.1m solar array. Mass was 1420 kg launch incl. 4 kg of prop.
| NOAA N' | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2009 Feb 6 | 1022 | Launch by Delta II 7320-10C | V SLC2W |
| T+1:39 SRM jettison | |||
| T+4:24 MECO | |||
| T+4:32 Stage 1 sep | |||
| T+4:38 SEIG-1 | |||
| T+4:56 Fairing sep | |||
| 1033 | T+11:16 SECO-1 | 182 x 867 x 98.7 | |
| 1121 | T+59:21 SEIG-2 | ||
| 1121 | T+59:34 SECO-2 | ||
| 1127 | T+1:05:40 NOAA-N sep | 857 x 864 x 98.7 | |
| Solar array boom deploy | |||
| SRA deploy | |||
| Sunshade deploy | |||
| SEIG-3 | |||
| SECO-3 | |||
| Delta orbit | 94.60 177 x 821 x 102.0 | ||
Payload:
- AVHRR/3 Advanced Very High Resolution Radiometer 3
- HIRS/4 High Res. IR Radiation Sounder 4
- AMSU-A Advanced Microwave Sounding Unit A
- MHS Microwave Humidity Sounder
- SBUV-2 Solar Backscatter UV Radiometer 2
- SEM/2 Space Environment Monitor 2
Sunday, May 31, 2009
Fengyun-2-06
2008-066A
FY2-06 is the 02 batch of service application satellites and the follow-on to FY-2C,D.
It is operated by the Zhongguo qixiangju (Chinese meteorological bureau).
Mass 1390 kg.
The CZ-3A third stage performed the EM-1 extended mission,(EM-1 de kuozhan renwu), coasting for 25 min after payload sep to test extended cooling for deep space launches.
| FY2-6 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2008 Dec 23 | 0054 | Launch by CZ-3A | XSC |
| T+2:00 St 1 sep | |||
| T+4:13 Fairing sep | |||
| T+4:17 St 2 sep | |||
| 0105? | T+11:43 St 3 MECO-1 | -400? x 300 x 27.4 | |
| 0111? | T+17:48 St 3 MES-2 | ||
| 0117? | T+23:00 St 3 MECO-2 | ||
| 0118 | Stage 3 sep | ||
| 0143 | End of Stage 3 EM-1 | ||
| 2008 Dec 23 | 623.48 260 x 35333 x 24.2 | ||
| 2008 Dec 3 | 1653 | AKM | |
| 2008 Dec 23 | 1408.86 35055 x 35447 x 2.7 | ||
| 2008 Dec 24 | 1415.77 34977 x 35797 x 2.7 | ||
Hot Bird 9
2008-065A
Eurostar 3000, HB9 by EADS Astrium; 11 kW satellite. Identical to HB8. Replace HB3 at 13E.
Mass 4880 kg launch 2338 dry. Size 2.7 x 3.4 x 6.3m 38m span (Arianespace kit); 2.4 x 2.9 x 4.0m 39.4m span (EADS kit).
HB9 is on a PAS1194C-A adapter on a Sylda 5A.
Launch by Ariane 5.
| HB9 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2008 Dec 20 | 2235:14 | Launch by Ariane 543 ECA | CSG ELA3 |
| T+2:13 EAP sep | |||
| T+3:09 Fairing sep | |||
| 2244:04 | T+8:50 EPC MECO | ||
| 2244:10 | T+8:56 EPC sep | -1102 x 161 x 6.3 | |
| T+9:00 ESC-A burn | |||
| EPC impact at 6W 0.7S | |||
| 2300:01 | T+24:47 ESC-A MECO | ||
| 2301:51 | T+26:37 HB9 sep | ||
| 2305:37 | T+30:23 Sylda | ||
| 2307:17 | T+32:03 W2M sep | ||
| 2008 Dec 20 | 629.10 258 x 35626 x 4.1 | ||
| 2009 Jan 5 | 1436.07 35785 x 35786 x 0.0 GEO 1.0E | ||
| 2009 Feb 4 | Move out of 1E | ||
| 2009 Feb 16 | Move in at 13E | ||
| 2009 Feb 23 | 1436.04 35779 x 35791 x 0.0 GEO 13.0E | ||
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