Thursday, December 2, 2010

Proba 2

 2009-059B


Proba-2 will have a mass of 100 kg. It will test on-board automatic detection of solar storm activity. The experiment payload is led by Belgium.

SSTL provides the butane propulsion system.

Box + 2 panels 0.6 x 0.6 x 0.9m, 130 kg. Control from Redu.

Built by Verhaert Design and Development NV of Belgium, a subsidiary of QinetiQ (UK). Kruibeke, Belge. Control from Redu.

After SMOS launch, Briz KM makes an extra burn to lower orbit altitude.

Carries Li ion batteries, LEON processor, star sensors, GPS receivers, command decoder, sun sensor.


Proba 2 
 

DateTimeEventOrbit  

2009 Nov 2 0150:51s Launch by Rokot 
  T+2:16 69 km St 1 sep  -5910 x 168 
  T+2:59 Fairing sep 119 km  -5731 x 192 
  T+5:19 St 2 sep 253 km  -4153 x 345 
  T+5:20 Briz-KM burn 1 9:59 
 0206:11 T+15:20 KM MECO-1  153 x 888 x 99.48 
 0253:41 T+1:02:50 KM MES-2 70s 
 0254:51 T+1:04:00 KM MECO-2  749 x 768 x 98.44 
 0300:58 T+1:10:07 SMOS sep 
 0314:11 T+1:23:20 KM Vernier DKI-1 17s 
  T+1:23:37 DKI cutoff  723 x 763 x 98.37  
 0357:45 T+2:06:55 KM DKI-2 17s 
 0358:03 T+2:07:12 DKI cutoff  725 x 725 x 98.30 
 0407:31 T+2:16:40 PS (adapter section) separation  709 x 723  
 0450:20 T+2:59:29 Proba-2 sep 
 0511:11 T+3:20:20 KM sep burn 100s 
  T+3:22:00 KM cutoff  511 x 726 x 98.5 
2009 Nov 19    99.18 709 x 728 x 98.3 

Payload:

  • SWAP EUV Solar imager, cadence 60s. Sun Watcher/Active Pixel System. 175A EUV line. 1 deg FOV (Liege/)

  • LYRA Lyman Alpha Radiometer, total solar radiation. (Liege/)

  • TPMU Thermal Plasma measurement unit (AN Czech IPA)

  • DSLP Dual Segmented Langmuir probe (AN Czech IPA).

  • SSTL low thrust Xe engine, 20 mN

Thor 5

 2008-006A


Telenor Satellite Broadcasting's Thor 5 (Thor 2R) built by Orbital. Mass 2012 kg or 1960 kg (2024 kg with adapter?), 1090 kg dry. 


Thor 2R 
 

DateTimeEventOrbit  

2008 Feb 11  1134:00 Launch by Proton  KB LC200/39 
  T+2:03 St 1 sep 
  T+5:33 St 2 sep 
  T+5:45 GO sep 
 T+9:33 St 3 MECO 
 1143:45 T+9:45 St 3 sep  -682 x 178 x 51.58 
 1145:19 T+11:19 Briz MES-1 
 1150:56 T+16:56 MECO-1  173 x 173 x 51.6  
 1201?  St 3 reentry 
 1242:30 T+1:08:30 MES-2 
 1258:56 T+1:24:56 MECO-2  298 x 5000 x 50.3 
 1457:56 T+3:23:56 MES-3 
 1516:58 T+3:42:58 MECO-3 
 1518:12 T+3:44:12 DTB sep  496 x 36846 x 49.1  
 2034:02 T+9:00:02 MES-4 
 2044:32 T+9:10:32 MECO-4 
 2056:50 T+9:22:50 Briz sep in GEO  36746 x 36840 x 0.0  
 2300:00 T+11:26:00 SOZ-6 burn 25s 
 2300:25 T+11:26:25 SOZ-6 CO   
2008 Feb 12  0226   1473.52 35946 x 37085 x 0.12 GEO 51.2E+9W/d 
2008 Feb 19   mv  1451.48 35953 x 36221 x 0.1 
2008 Feb 23   mv in 1439.31 35774 x 35924 x 0.1 GEO 16.5W 
2008 Feb 29   mv out  
2008 Mar 4    1426.29 35585 x 35603 x 0.1 GEO 7.4W+2.4E/d 
2008 Apr 28   mv in at 0.7W 1436.06 35767 x 35804 x 0.07 GEO 0.7W 
2010 May 2    1436.08 35775 x 35796 x 0.0 GEO 0.7W 

People: August 23,2010

 https://welib.org/md5/14263b148099e257f789ceac7070ec1a

Wednesday, December 1, 2010

Protostar 1

 2008-034A


Protostar 1 is an FS-1300(HP). China Telecommunications Broadcast Satellite Corp (Chinasat), a division of PRC MPT (Ministry of Posts and Telecomms), ordered Chinasat 8 with 16 Ku and 36 C. Was to be launched late 1998 by CZ-3B. Export licence killed in 1998 Dec. Put in storage; in 2007 sold to Protostar Ltd for launch May 2008 aboard Ariane 5.

Protostar Ltd. had its HQ in Bermuda with engineering at Protostar Satellite Systems (PSS) in San Francisco; would provide Asian satellite TV broadcasting at 98.5E. The EADS press kit implies that the Loral and Arianespace contract is with PSS, and so that Protostar 1 is a US and not a Bermudan satellite. ITU registration on 2008 Oct was by Belarus. Continuing legal problems led to the sale of Protostar to Intelsat in 2009 Oct as IS-25.

Mass 4191 kg launch 1774 kg dry, size 3.8 x 2.4 x 2.1m with 31.1m span and 6.2m deployed height. Ariane 5 used EPC-C, H175/Vulcain 2, EAP-B, ESC-A, Sylda 5A and 17m long fairing. ESC-A, VEB and Cone 3936 were assembled at Bremen.


Protostar 
 

DateTimeEventOrbit  

2008 Jul 7 2147 Launch by Ariane 5ECA  CSG ELA3 
  T+0:00 Launch  
  T+2:13 EAP sep 
  T+3:08 Fairing sep
 2155 T+8:50 EPC MECO 
  T+8:55 EPC sep  -1071 x 164 x 7.3  
 2156 T+9:00 ESC-A burn 
 2211 T+24:48 ESC-A MECO  
 2214 T+27:30 Proto 1 sep 
 2216 T+29:10 Sylda sep 
 2222 T+35:32 BADR 6 sep 
  T+45:33 end of V184 mission
   631.59 251 x 35761 x 2.0 
2008 Jul 9    776.24 7469 x 35731 x 0.7 
2008 Jul 10    1024.17 18836 x 35721 x 0.2 
2008 Jul 13    1288.68 32326 x 33372 x 3.0 
2008 Jul 14    1431.70 35660 x 35740 x 0.1 
2008 Jul 15    1433.14 35702 x 37555 x 0.05 
2008 Aug 3    1436.18 35779 x 35796 x 0.01 GEO 98.3E 
2009 Oct   Bought by Intelsat and renamed IS-25 
2009 Nov 1    1436.12 35777 x 35796 x 0.0 GEO 98.4E 
2010 Jan 8   Move out 
2010 Feb 7    1444.05 35929 x 35954 x 0.0 GEO 37.8E+2.0W/d 
2010 Mar 15   Arrive at 31.5W 
2010 Apr 13    1436.10 35774 x 35798 x 0.0 GEO 31.5W 

College Guide for Visual Arts Majors 2009

 https://welib.org/md5/93f93e3a2d6fe58e1548f19e37449e1e

Amos 2

 2003-059A


IAI MBT Div. to build Amos-2. Spacecom Ltd./Tel Aviv is service provider for Amos-2; the satellite was delivered on orbit by IAI. Mass 1350 kg full (or 1374 kg), 646 kg dry, size 2.7 x 2.1 x 2.4m span 11.0m. It will backup Amos 1 at 4W and include service to the eastern US. Launch by Starsem Soyuz-Fregat in Dec 2003.

Followon AMOS HP with 20 Ku-band transponders and 2600 kg mass?


Amos 2 
 

DateTimeEventOrbit  

2003 Dec 27  2130:00s Launch by Soyuz-FG/Fregat ST12  KB PL31/6 
  T+1:58 BVGD sep 
  T+4:13 Fairing sep
  T+4:48 Blok A sep 
  T+4:58 KhO sep 
  T+8:45 Blok I MECO 
 2138:48 T+8:48 Blok I sep  58 x 190 x 51.8 
 2138:53 T+8:53 SOZ-1 burn 
 2139:49 T+9:48.5 MES-1 20.5s 
 2140:09 T+10:09 MECO-1 EPO  190? x 190? 
 2215? Blok I reentry 
  T+1:09:29 SOZ-2  
 2240:24 T+1:10:24 MES-2 ascending node=10.25W 25S 25W, 659s 
 2251:23 T+1:21:23 MECO-2 intermediate 16N 2E 250? x 35780 x 49?  
2003 Dec 28  0403:34 T+6:33:34 SOZ-3 burn 
 0404:29 T+6:34:29 MES-3 over 90E 0N, 137s 
 0406:46 T+6:36:46 MECO-3  4407 x 35788 x 23.63 
 0406:47 T+6:46:47 Fregat sep  4409 x 35779 x 23.58 
 0446:47 T+7:16:47 SOZ-4 Fregat depletion  
 0447:02 T+7:17:02 SOZ cutoff 
2003 Dec 29    714.42 4409 x 35779 x 23.58 
2003 Dec 30  0317  ABM-1 46min burn  19000 x 35800  
 2040?  Apogee 
2003 Dec 31  1350  ABM-2 17min burn  34000 x 35800  
2004 Jan 5    1402.99 34439 x 35832 x 0.3 
2004 Jan 12   On Station  GEO 4W 
2004 Feb 19   Delivered to Spacecom 
2006 Aug 1    1436.07 35777 x 35794 x 0.1 GEO 4.0W

November 20,2006

  https://en.wikipedia.org/wiki/Association_football