Friday, February 25, 2011
Thursday, February 24, 2011
Resurs 2006
2006-021A
TsSKB Yantar' based satellite launched by Soyuz-U from Baykonur into a 350 x 350 km x 71 deg orbit. Based on Terilen. 0.8m res pan, 3m color. Design life 3 years. Size is 7.9m long 2.72m dia.
Mass is 6570 kg full 5670 kg dry.
DK1 46KS No. 1L Launch by 11A511U-PBV No. 34/132 or No. 096.
The 730 kg PAMELA experiment mounted on the spacecraft is a magnetic spectrometer which detects cosmic ray antiparticles, including 80 MeV - 190 GeV antiprotons and 50 MeV - 270 GeV positrons.
Payload operated by NTs OMZ, Moscow (NTSOMZ).
| DK1 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2006 Jun 15 | 0800:00 | Launch by Soyuz-U No. 096 | KB LC1 |
| T+1:58 strapons sep | |||
| T+2:50 GO sep | |||
| T+4:47 Blok A sep | |||
| T+5:07 KhO sep | |||
| T+8:45 MECO | |||
| 0808:48 | T+8:48 Blok I sep | ||
| 2006 Jun 15 | 89.82 193 x 337 x 70.0 | ||
| 2006 Jun 18 | 89.80 191 x 338 x 70.0 | ||
| 1300 | Orbit raise | 94.01 355 x 584 x 69.9 | |
| 2010 Sep 10 | 93.89 355 x 573 x 69.9 | ||
| 1656 | Orbit raise | ||
| 2010 Sep 17 | 96.08 567 x 573 x 69.9 | ||
Payload:
- Geoton-1 High resolution imaging camera, 1 m pan and 3m color, 28 km swath (Vavilov/)
- MRI-PAMELA Italian Payload for Antimatter-Matter Exploration and Light Nuclei Astrophysics.
Wednesday, February 23, 2011
Insat 4C
2007-037A
Launch by GSLV in Sep 2007. At 83s after launch a control actuator stuck and roll rates built up, causing premature SOM shutdown with a 120m/s underspeed. The inertial measurement unit lost reference as well, and as a result the insertion inclination was 15.8 deg instead of the planned value, presumably 19.5 deg, and the apogee was low. The payload was able to make up the insertion errors.
Mass is 2130 kg full 941 kg dry. Size is 1.6 x 1.5 x 2.4m box + 2 panels span 9.5m.
| Insat 4C | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2007 Sep 2 | 1250 | Launch by GSLV F04 | SDSC |
| T+1:23 L40 strapon actuator failure | |||
| SOM shutdown | |||
| T+2:29 GS1 burnout 70 km | |||
| T+3:47 Fairing sep 115 km | |||
| T+4:52 GS2 burnout | |||
| 1306 | T+16:42 GS3 burnout 220 km | ||
| 1306 | T+16:55 GS3 sep | 555.17 174 x 31821 x 15.8 | |
| 2007 Sep 3 | 0247 | LAM-1 27min | 2983 x 31702 x 11.1 |
| 2981 x 35721 x 11.1 | |||
| 2007 Sep 4 | 2305 | LAM-3 3140s burn | 15994 x 35385 x 3.2 |
| 15993 x 35384 x 3.2 | |||
| 2007 Sep 6 | 0700s | LAM-4 | 1340.93 32579 x 35226 x 0.3 |
| 2007 Sep 7 | 1530? | LAM-5 | |
| 2007 Sep 14 | 1428.15 35026 x 35226 x 0.3 GEO 27.3E+25.6E/d | ||
| 2007 Sep 15 | 1436.07 35769 x 35803 x 0.1 GEO 73.9E | ||
| 2007 Oct 10 | 1436.07 35772 x 35799 x 0.1 GEO 74.1E | ||
| 2010 Nov 4 | 1436.12 35758 x 35815 x 0.05 GEO 73.7E | ||
Sunday, February 20, 2011
Satcom C3
1992-060B
GE Americom's Series 3000 class Satcom C-3 replaced the aging Satcom 1R at 131W.
| Satcom C-3 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1992 Sep 10 | 2304:00 | Launch by Ariane 44LP | CSG ELA2 |
| 2305 | PAL sep (T+1:07) | ||
| 2306 | Stage 1 sep (T+2:28) | ||
| 2307 | Fairing sep (T+3:35) | ||
| 2308 | Stage 2 sep (T+4:39) | ||
| 2309 | H-10+ ignition (T+5:47) | ||
| 2322 | H-10+ shutdown (T+18:17) | ||
| 2324 | Hispasat 1A sep (T+20:32) | ||
| 2327 | SPELDA top sep (T+23:21) | ||
| 2328 | Satcom C3 sep (T+24:55) | ||
| 2329 | H10+ sep mvr (T+25:25) | ||
| 2334 | End of mission V53 (T+29:55) | ||
| 1992 Sep 11 | 630.17 219 x 35720 x 6.9 | ||
| 0500? Apo 1 over 8E | |||
| 1000? | Peri 1 | ||
| 1500? | Apo 2 over 66W | ||
| 2030? | Peri 2 | ||
| 1992 Sep 12 | 0200? | Apo 3 over 132E | |
| 0700? | Peri 3 | ||
| 1230? | Apo 4 over 25W | ||
| 1730? | Peri 4 | ||
| 2300? | Apo 5 over 177E | ||
| 1992 Sep 13 | 0400? | Peri 5 | |
| 0930? | Apo 6 over 19E | ||
| 1430? | Peri 6 | ||
| 1930? | Apo 7 over 134W | ||
| 1992 Sep 13 | 1930? | Star 30C burn | |
| 1992 Sep 13 | 1443.43 35731 x 36128 x 0.2 GEO 136.1W+1.8W | ||
| 1992 Sep 14 | Solar panels deployed | ||
| 1992 Sep 20 | 1437.86 35692 x 35949 x 0.1 GEO 142.0W+0.4W | ||
| 1992 Sep 25 | 1436.22 35778 x 35800 x 0.1 GEO 142.8W+0.04W | ||
| 1992 Nov 1 | 1436.00 35775 x 35793 x 0.0 GEO 143.0W | ||
| 1992 Nov 6 | mv out | ||
| 1992 Nov 12 | 1434.64 35750 x 35766 x 0.0 GEO 141.0W+0.4W | ||
| 1992 Dec 13 | mv in | 1436.03 35778 x 35792 x 0.1 GEO 130.9W+0.0W | |
| 1993 Aug 18 | 1436.12 35780 x 35793 x 0.0 GEO 131.0W | ||
| 1994 Aug 23 | 1436.12 35764 x 35809 x 0.0 GEO 131.0W | ||
| 1996 Jul 10 | 1436.06 35774 x 35797 x 0.1 GEO 131.0W | ||
| 1998 Oct 14 | 1436.13 35785 x 35788 x 0.1 GEO 131.0W | ||
| 1999 Oct 15 | 1436.04 35777 x 35793 x 0.1 GEO 130.9W | ||
| 2005 Apr 10 | 1436.09 35780 x 35792 x 0.4 GEO 130.9W | ||
| 2005 Apr 30 | mv out | ||
| 2005 Jul 30 | mv in | ||
| 2005 Aug 1 | 1436.16 35777 x 35798 x 0.8 GEO 79.0W | ||
| 2006 Jul 23 | 1436.10 35781 x 35791 x 1.7 GEO 79.1W | ||
| 2010 Sep 25 | 1436.10 35780 x 35792 x 5.5 GEO 79.0W | ||
Saturday, February 19, 2011
Friday, February 18, 2011
Sunday, February 6, 2011
Tranquility
2010-004
Node 3 is built by Alenia. It is 7.19m long 4.48m dia. (6.7m long in ESA docs). Node 3 is the Hub Control Zone. 50 percent larger than Node 1, it will hold 8 racks. Node 3 will dock to Node 1 port (opposite Quest); the Cupola is launched attached to Node 3 port and will be relocated to Node 3 nadir. PMA-3 will be transferred from Node 2 zenith to Node 3 port. (Since Node 3 is attached to Node 1 port, the end ports on node 3 are 'port' and 'starboard' instead of forward and aft.)
Zenith port on Node 3 will be a base for Dextre and cannot be used as a CBM berth.
Manifested for STS-130/20A
Mass is 15500 kg at launch according to ESA, but according to FRDR baseline it is 14809 kg with Cupola, so 13004 kg without.
Combined Operational Load Bearing External Resistance Treadmill (COLBERT) will be transferred there as well as ARS (Air Revitalization System) rack.
Regen ECLSS racks also deleivered on 130.
Node 3 is launched with 5 racks and 3 empty rack positions. The ISP racks will return on STS-131.
The operational (post STS-131) rack layout will be
Payload:
- Avionics rack 1
- Avionics rack 2
- ARS Air revitalization system
- OGS Oxygen Generation system
- WRS1 Water Recovery System 1
- WRS2 Water Recovery System 2
- WHC Waste Hygiene Compartment Rack (toilet)
- T2 Colbert Treadmill
and in addition an ARED (Advanced Resistive Exercise Device) will be in the node.
The launch rack layout is:
Payload:
- Avionics rack 1
- Avionics rack 2
- ISP rack 1 (Integrated Stowage Platform)
- ISP rack 2 (Integrated Stowage Platform)
- ISP rack 3 (Integrated Stowage Platform)
Friday, February 4, 2011
N-Star-B
1996-007A
N-STAR b was built for Nippon Telegraph and Telephone (NTT) and NTT DoCoMo, the mobile comms provider subsidiary. The FS-1300 was operated by SS/L mission control in Palo Alto until on orbit delivery and control by NTT Nakano for in orbit testing. NTT and TAO operate the satellite from then on. N-STAR replaces the CS-3 satellites.
Launch mass was 3420 kg, on orbit 2062 kg, and dry mass 1618 kg. The bus is a 2.4 x 2.2 x 6.3m box with 27.3m solar panel span.
In 2000, JSAT acquired a 60 percent interest in the N-Star satellites.
The satellite was retired in May 2007.
| N-STAR b | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1996 Feb 5 | 0719:38 | Launch by Ariane 44P | CSG ELA2 |
| 0720 | PAP sep | ||
| 0722 | St 1 sep | ||
| 0722 | St 2 ig | ||
| 0723 | Fairing | ||
| 0725 | St 2 sep | ||
| 0725 | St 3 burn | ||
| 0738 | St 3 MECO | ||
| 0740 | St 3 sep | ||
| 1996 Feb 5 | 630.80 171 x 35801 x 7.0 | ||
| 1996 Feb 6 | 1000? | LAM-1 | |
| 1996 Feb 6 | 761.81 6726 x 35779 x 3.58 | ||
| 1996 Feb 8 | 1250? | LAM-2 | |
| 1996 Feb 8 | 1271.56 29236 x 35766 x 0.53 | ||
| 1999 Feb 9? | LAM-3 | ||
| 1996 Feb 14 | 1425.65 35371 x 35793 x 0.58 | ||
| 1996 Feb 15 | 1436.10 35753 x 35820 x 0.09 | ||
| 1996 Mar 6 | 1436.15 35489 x 36085 x 0.0 GEO 136.1E | ||
| 1997 Oct 10 | 1436.09 35773 x 35799 x 0.1 GEO 136.0E | ||
| 1999 Oct 15 | 1436.15 35772 x 35803 x 0.1 GEO 136.0E | ||
| 2006 Aug 3 | 1436.11 35774 x 35799 x 0.1 GEO 136.1E | ||
| 2007 May 23 | 1436.14 35772 x 35802 x 0.5 GEO 136.1E | ||