Thursday, July 21, 2011

SAMPEX

 1992-038A


The first SMEX was SAMPEX, the Solar and Anomalous Magnetospheric Particles Explorer. It carried a set of experiments from a team lead by the University of Maryland, and was built in-house at NASA-GSFC.

The 158 kg satellite was a box + 2 panels 0.86m in diameter and 1.5m long. It studied trapped radiation in the magnetosphere, solar flare composition, cosmic rays, and precipitating electrons.

LEICA is a high resolution mass spectrometer for low energy particles in an approximate range of 0.2-10 MeV/nucleon. MAST measures isotopic composition with a mass resolution of 0.3 amu in the 15-300 MeV/nucleon range; PET measures H and alpha in the same range and electrons in 0.4-30 MeV. HILT detects particles in the 10-200 MeV/nucleon range.

Launch was at 1419 on 1992 Jul 3 by Scout S215C from Space Launch Complex 5 at Vandenberg AFB into a 550 x 657 km x 82 deg orbit. SAMPEX was still operating in 1994. POCC was at GSFC with a Science Ops Center at Maryland. In 2010, SAMPEX was being operated by the Bowie State control center in Maryland.


SAMPEX 
 

DateTimeEventOrbit  

1992 Jul 3  1419  Launch by Scout  SLC5 
  T+1:24 Stage 1 burnout 
  T+1:28 St 1 sep 
  T+1:28 St 2 burn 
  T+2:09 St 2 burnout 
  T+2:20 Fairing sep
  T+2:22 St 2 sep, St 3 burn 
  T+3:10 St 3 burnout 
  T+9:54 St 3 sep 
 1429 T+9:59 St 4 burn 
 1429 T+10:32 Stage 4 burnout 
 1430 T+11:36 Stage 4 sep 
 1434 T+14:56 SAMPEX Yo-yo despin 
1997 Oct   SAMPEX control to Bowie, MD 
2004 Jun 30end of sci ops
2004 Dec 27   Observed large X-ray flare 
2005 Jan 20   Observed GLE event 
2005 Mar   Still operational 
2010 Aug Still operational 

American Beauty: An A-List Novel

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The Rich: A New Study of the Species

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Teaching Children Science : Hands-On Nature Study in North America, 1890-1930

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Wednesday, July 20, 2011

Maclean’s: September 29,2008

 https://welib.org/md5/f08dd00503c41145dfbb3ff2f7b57aec

Galaxy 4R

 2000-020A


HS-601HP satellite to replace Galaxy 4 at 99W. Distribute video and comms and broadband internet pipe. Galaxy 6, 7 and 11 will relocate.

Galaxy 4R developed XIPS engine problems in June 2003. It was retired in 2009.

Launch mass is 3668 kg, BOL 2216, dry mass 1895 kg. Size is 4.0 x 3.6 x 2.7m, 26m span.


Galaxy IV-R 
 

DateTimeEventOrbit  

2000 Apr 19  0029  Launch by Ariane 42L V129  CSG ELA2 
  T+2:20 PAL sep 
  T+3:14 St 1 sep 
  T+3:17 St 2 burn 
  T+4:05 Fairing sep
  T+5:26 St 2 sep 
  T+5:31 St 3 burn 
 0047 T+18:40 St 3 MECO 
 0050  T+20:48 St 3 sep 
  T+20:52 St 3 avoidance maneuver 
  T+22:37 end of V129 mission 
   219 x 32007 x 7.0 
2000 Apr 19    559.49 219 x 32007 x 7.0 
2000 Apr 20?  LAM-1 
2000 Apr 21    566.40 587 x 32009 x 7.0 
2000 Apr 23?  LAM-2 
2000 Apr 24    740.30 5683 x 35776 x 4.2 
2000 Apr 25  1600?  LAM-3  
2000 Apr 27    1435.70 35765 x 35792 x 0.1 GEO 67.4W+0.05W 
2000 May 1    GEO 67W 
2000 May 26    1436.09 35785 x 35787 x 0.0 GEO 73.0W 
2000 Jun   Move to 99W 
2000 Jun 25    1436.09 35785 x 35787 x 0.0 GEO 99.0W 
2000 Oct 18   1436.10 35785 x 35787 x 0.0 GEO 99.0W 
2003 Jul 3    1436.11 35773 x 35799 x 0.0 GEO 99.0W 
2006 Aug 4    1436.04 35780 x 35790 x 0.0 GEO 99.0W 
2006 Sep   Move to 77W 
2006 Oct 2    1436.06 35777 x 35794 x 0.1 GEO 76.8W 
2009 Mar 29    1436.11 35773 x 35799 x 2.5 GEO 76.9W 

Radarsat 1

 1995-059A




The CSA's Radarsat was built by Spar Aerospace. The 4.2m long, 2.8m wide spacecraft bus, built by Ball and based on the RME satellite, carried a large solar array and a 15 x 1.5m C-band synthetic aperture radar. It had a mass of 2750 kg. The radar has a 500 km swath width and can be steered electronically, with a fine (8-m resolution) 50 x 50 km area mode and a scan (100 m resolution) 500 x 500 km mode. It is intended to image the Arctic region and Canada, and will also improve maps of the Antarctic. 15 percent of the observing time is allocated to the US in return for the launch. Radarsat is to be operated by the Canadian Space Agency from the Radarsat Control Center at St Hubert, Quebec. Radarsat was launched into a 6am/6pm sun-synchronous orbit for continuous solar array illumination.

In Sep 1997 the satellite was flipped in orientation (yaw) to begin the Antarctic-1 mapping mission, imaging to the left of the satellite track.

The MDA company operates Radarsat. The Dept. Foreign Affairs and the military DND does tasking for surveillance to MDA; commercial tasking is done directly by MDA, while civil tasking is sent to MDA by CSA.

Payload:

  • C-band 1.5 x 15m SAR radar, 5.3 GHz


Radarsat 
 

DateTimeEventOrbit  

1995 Nov 4  1422  Launch by Delta 7920-10  V SLC2W 
  SRM 1-9 sep 
 1426  Stage 1 sep 
 1426  Delta stage 2 burn 
 1427  Type 10 fairing sep 
 1432? Delta stage 2 cutoff  190? x 784 x 98.6 
 1523? Delta stage 2 MES2 
  Delta stage 2 MECO2 
 1526  Delta stage 2 sep 
 1552  Solar array deploy 
 1615SAR begin deploy 
1995 Nov 4    100.57 783 x 787 x 98.6 
1995 Nov 4  1540? Delta SES-3 
  SECO-3  786 x 1462 x 98.6 
1995 Nov 4  1608? Delta SES-4 
  Delta/SURFSAT SECO-4  934 x 1494 x 100.64  
1995 Nov 7    100.57 783 x 787x 98.6 
1995 Nov 15   Begin orbit adjust 
1995 Dec 16   In operational orbit 
1995 Dec 16    100.70 791 x 792 x 98.6 
1997 Sep 9   Reorient satellite 
1997 Sep 11   Begin Antarctic-1 mission (AMM) 
2002 Nov   safemode, AOCS problem 
2002 Dec 24   Resume ops 
2011 Mar 31    100.70 791 x 792 x 98.6

Tuesday, July 19, 2011

GSAT-2

 2003-018A


GSAT-2 launch mass was 1823 kg, 840 kg dry. Prop was MMH/MON-3. Size 2.4 x 1.6 x 1.5m with 9.6m span. Launch 2003 May by GSLV-D2 into GTO; LAM to GEO at 48E.

D2 had 10t of extra prop in stage 1, and improved strapon and stage 2 engines. Mass 414t at launch. The S139 first stage has four L40H strapons. GS2 is 11.6l 2.8d with 39.3t prop of UH25/N2O4 and 804 kN thrust. GS3 is cryo, 8.7l 2.9dia. The payload adapter was also made lighter, for a total gain of 485 kg; the lower-than-design Isp of the 12KRB represented a loss of 200 kg.

Launch from SDSC-SHAR (Satish Dhawan Space Center). Azimuth 104 deg.

The satellite carried SOXS, a solar X-ray spectrometer.


GSAT 2 
 

DateTimeEventOrbit  

2003 May 8  1128  Launch by GSLV D2  
  T-4.8s L40H ignite 
  T+0:0 S139 ignite 
  T+1:47 S139 burnout 
  T+2:29 L40H burnout 69km 
  T+2:30? GS-2 MES 
  T+2:33? S139 sep 
  T+3:48? Fairing sep
  T+4:46? GS-2 MECO 
  T+4:50 GS-2 sep 131 km 
 1132  T+4:50 GS-3 burn 11:45 5.4 km/s 
 1144  T+16:35? GS-3 MECO 
 1144  T+16:37 GS3 sep 198 km  180 x 36000  
2003 May 9   LAM-1  8850 x 36000 x 7.4 
2003 May 9    801.1 8826 x 35562 x 7.4 
2003 May 10  0600  LAM-2 41min  1384.0 34000 x 36000 x 0.3 
2003 May 11  0520  LAM 79s 
2003 May 11    1436.81 33601 x 37999 x 0.3  
2003 May 12   Solar array deploy 
2003 May 23    1436.13 35782 x 35791 x 0.0 GEO 48.0E 
2003 May 27    1436.11 35783 x 35790 x 0.0 GEO 48.0E 
2003 Dec 19    1436.15 35713 x 35861 x 0.1 GEO 48.0E 
2004 Feb 11    1436.08 35775 x 35797 x 0.0 GEO 48.0E 
2011 May 4    1436.00 35767 x 35802 x 0.4 GEO 48.1E

Monday, July 18, 2011

IceSat

 2003-002A


EOS Laser ALT-1, or ICESAT (Ice, Cloud and Land Elevation Satellite), launched to 705 x 705 x 94. ICESAT is built by Ball Aerospace/Boulder under an IDIQ contract with the BCP-2000 (Ball Commercial Platform) bus. ICESAT will study the Greenland and Antarctice ice sheets.

The 300 kg ICESAT is mounted on the RH-DPAF (Reduced Height Dual Payload Attach Fitting) containing CHIPSAT. RH-DPAF consists of an upper cone/cylinder and a lower cone.

The GLAS lidar instrument is a 1-m telescope with a ND-YAG 0.5 and 1 micron laser. ICESAT is 3.1m tall, 1.9m in dia, with two 2.1 x 2.3m solar panels for an approx 6.5m span.

The first of ICESAT's 3 lasers failed after only 36 days due to a solder contamination problem. A second laser was activated in Sep 2003.


ICESAT 
 

DateTimeEventOrbit  

2003 Jan 13 0045:00 Launch by Delta 7320-10  V SLC2W 
  T+1:04 SRM1-3 burnout 
  T+1:39 SRM 1-3 sep 32 km  -6350 x 35?  
  T+4:24 MECO 
  T+4:32 St 1 sep 
  T+4:37 SES-1 121 km 4.830 km/s  -4900 x 150?  
  T+4:57 Fairing 135 km 4.892 km/s  -4830 x 170 ? 
 0056:05 T+11:05 SECO-1  185 x 597 x 93.96 
 0144:50 T+59:50 SES-2 
 0144:58 T+59:58 SECO-2 
 0149:00 T+1:04:00 Icesat sep  585 x 591 x 94.0 
 0205:00 T+1:20:00 RH DPAF sep  559 x 585 x 94.0  
 0208:20 T+1:23:20 Chipsat sep  559 x 585 x 94.0  
  T+1:26:40 Stage 2 retro 
  T+1:46:40 SES-3 evasive  561 x 583 x 94.0 
  T+1:46:45 SECO-3  498 x 585 x 94.84 
  T+2:06:40 SES-4 depletion 
  T+2:07:16 SECO-4 depletion  198 x 546 x 97.30 
2003 Jan 13    96.40 578 x 593 x 94.0 
2003 Jan 20    96.39 577 x 593 x 94.0 
2003 Jan 23    96.40 578 x 593 x 94.0 
 2214  orbit raise  96.50 584 x 598 x 94.0 
2003 Jan 26   orbit raise  96.59 588 x 602 x 94.0 
2003 Feb 8    96.61 590 x 601 x 94.0 
2003 Feb 20   GLAS turned on 
2003 Mar 12    96.61 594 x 598 x 94.0 
2003 Mar 28   GLAS laser failed (1 of 3), science suspended 
2003 Jul 2    96.61 594 x 598 x 94.0 
2003 Sep 25   Laser 2 activated 
2009 Apr   End of primary mission? 
2009 Oct 11   Laser 3 failed, end of science data 
2010 Feb 24   Attempts to restart lasers abandoned 
2010 Feb 24   Decommissioning phase 
2010 Jun 23    96.59 592 x 597 x 94.0 
2010 Jun 24   Lower orbit 96.33 572 x 593 x 94.0 
2010 Jul 1    96.33 572 x 593 x 94.0 
2010 Jul 7    95.65 509 x 591 x 94.0 
2010 Jul 8   Lower orbit  94.32 410 x 561 x 94.1 
2010 Jul 12   Lower orbit 93.08 265 x 584 x 94.0 
2010 Jul 15   Lower orbit 92.38 200 x 581 x 94.0 
2010 Aug 12    90.81 192 x 436 x 94.0 
2010 Aug 30    87.16 128 x 139 x 94.0 
2010 Aug 30   Reentered over Barents Sea 

Payload:

  • GLAS Geoscience Laser altimeter System, GSFC

Eyewitness Companions: Wines of the World: Your Essential Handbook

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May 13,2026

  https://planet4589.org/space/jsr/back/news.855.txt