Friday, April 22, 2016

TRMM

 1997-074A


Part of NASA's Earth Probe series, the Tropical Rainfall Measuring Mission (TRMM) was built by GSFC as part of a joint NASA/NASDA project. It was launched in late 1997 on an H-II from Tanegashima. The satellite is 5m high and 14.5m span, with a launch mass of 3950 kg including 890 kg of fuel (however, at end of operations it was reported to have a dry mass of only 2621 kg. Its mission is to improve rainfall data for climate models, and study El Nino. In mid-2001 the orbit was raised to provide extended mission life.


TRMM 
 

DateTimeEventOrbit  

1997 Nov 27  2127  Launch by H-II 6F  TNSC 
 2141  T+14:12 Sep from H-II 
 2155  T+28:01 ETS-7 sep 
1997 Nov 28    92.07 366 x 385 x 35.0 
1997 Dec 4    92.01 365 x 380 x 35.0 
1997 Dec 10    91.94 361 x 377 x 35.0 
1997 Dec 12  0530   91.90 362 x 373 x 35.0 
  Orbit lower 
 1224 91.48 346 x 347 x 35.0 
1998 Jan 7    91.54 342 x 357 x 35.0 
1998 Feb 6    91.49 346 x 358 x 35.0 
1998 Jun 30    91.49 347 x 348 x 35.0 
2001 Aug   Begin orbit raise 
2001 Aug 22   Complete orbit raise  402 x 402 
2003 Apr 21    92.54 398 x 400 x 35.0 
2014 Jul 2    92.54 397 x 400 x 35.0 

In the Hamptons 4Ever

https://welib.org/md5/9d65efff195d96ead09b9ad923b7828f

Friday, April 15, 2016

Hitomi

2016-012A


Hitomi (

\uni{ ひとみ}{ }

or

\uni{ 瞳}{ }

- eye pupil) was the ASTRO-H mission, originally NEXT (Next X-ray Telescope for JAXA). a followon to Astro-E2 with a hard X-ray imaging telescope and a very long focal length.

Orbit 550 x 550 km x 31 deg. Size 4.5m long, 12m deployed, 2.2m dia. Mass 2700 kg. Launch by H-2A 202 with a 4S fairing.

The three HXT telescopes are 30-60 arcsecond resolution, 750 sq cm area, 8 arcmin field of view, 0.5-80 keV spectral range. The `super-mirror' coating and multilayers allow the hard X-ray imaging. Each HXT has a WXI Wide band X-ray Imager with an SXI CCD array (12 arcmin field of view) and an HXI CdTe detector (6 x 9 arcmin field of view). The single SXT has the SXS microcalorimeter at the focal plane, while the SGD is a Compton telescope for soft gammas.

SXS has 6x6 pixel array 28" pixels, 4 eV res at 3-12 keV in 12 m long spacecraft. Dewar operates at 50 mK.

By mid March the SXS had begun taking data, although not with its full energy range. The results were reported to be scientifically excellent, in preparation for the calibration observation phase due to begin in April. But on Mar 25 disaster struck - at 1910 UTC the satellite started tumbling and then at 0140 UTC Mar 26 the spacecraft partly disintegrated. US tracking found ten debris objects in orbit.

During the next scheduled passes, the first at 0740 UTC, JAXA received only a short burst of telemetry later determined to be from a different satellite. JSPOC reported:

Breakup Notification: SL-12 R/B (SCC# 33472) at approximately 0145z, 27 Mar 16. 21 associated pieces as of 1400z 27 Mar 16. ASTRO H (SCC# 41337) at approximately 0820z, 26 Mar 16. 5 associated pieces as of 1400z 27 Mar 16. The events are not related. All objects have been added to conjunction assessment screenings.


ASTRO-H 
 

DateTimeEventOrbit  

2016 Feb 17  0845  Launch by H-IIA F30  TNSC 
  Azimuth 104 deg
  T+1:39 SRB MECO 
  T+1:48 SRB sep 
  T+4:15 Fairing sep
 0851 T+6:38 MECO 311 km 4.8 km/s 
  T+6:46 St 1 sep 
  T+6:52 SEIG-1 
 0858 T+13:24 SECO-1 
 0859 T+14:14 St 2 sep  575 x 575 x 31.0 
 0907  T+22:34 Chubu2 sep 
 0912 T+27:34 Chubu 3 sep 
 0917 T+32:34 Horyu-4 sep 
2016 Feb 28   EOB extended 
2016 Feb 29   Begin Initial Func. Verif. Phase 
2016 Mar 25  1910  Attitude anomaly over S atlantic 
 2049  MSP pass, only partial telem 
 2231  MSP Santiago pass 
2016 Mar 26  0052  MGN W Aus pass 
  JAXA last comm pass, problem 
2016 Mar 26    96.11 563 x 581 x 31.0 
2016 Mar 26  0137 Debris event, over Mexico, orbit change  96.07 560 x 580 x 31.0 
 0740  scheduled pass over W Aus 
 1449  Beacon signal for 3 minutes over Japan 
 1623  Beacon signal for 4 minutes over Japan 
2016 Mar 28  1306  Beacon for 10s over Japan 
2016 Mar 28  1533  Last beacon signal intercepted for 6s, Santiago 

Payload:

  • SXT-1 Soft X-ray imaging system with SXI at focus, f= 5.6m

  • SXT-2 Soft X-ray Telescope - spectrometer with SXS detector, f = 5.6m, 0.3-12 keV

  • HXT-1 Hard X-ray Telescope (2) on extensible bench, focal len 12m (Nagoya/) 300 cm2 at 30 keV, 5-80 keV

  • HXT-2 Hard X-ray Telescope (2) on extensible bench, focal len 12m (Nagoya/) 300 cm2 at 30 keV, 5-80 keV

  • SXS Soft X-ray spectrometer, 0.3-10 keV, 0.45m outer dia mirror with XCS (X-ray Calorimeter Spectrometer).

  • SXI Soft X-ray imager, CCDs

  • HXI1 Hard X-ray imager, Si DSSD (Double Sided Si Strip)/CdTe cross-strip detectors 9' FOV at end of 6m extensible optical bench

  • HXI2 Hard X-ray imager, Si/CdTe cross-strip detectors 9' FOV at end of 6m extensible optical bench

Thursday, April 14, 2016

Meteosat 7

 1997-049B


Eumetsat/Darmstadt's Meteostat Transition Programme Satellite (MTP, or Meteosat 7) uses the same design as MOP. It is built by Aerospatiale/Cannes and has a launch mass of 689 kg, BOL 490 kg, dry 316 kg. The satellite is a cylinder 2.10m diameter and 3.06m high, spin stabilized.

Radiometer cover ejection gave dV of 0.023 m/s; if radiometer cover is 1 kg, conservation of momentum says it gets an 11 m/s dV and could change its orbit by a few hundred km.

Launch by Ariane in 1997 Sep 2. The satellite was moved to cover the Indian Ocean in 2006 for the IODC (Indian Ocean Data Coverage) mission previously handled by Meteosat-5 and 6. It will be retired in 2017.


Meteosat 7 
 

DateTimeEventOrbit  

1997 Sep 2  2221:07  Launch by Ariane 44LP  CSG ELA2 
 2222  T+1:07 PAP sep 
 2223  T+2:36 PAL sep 
 2224  T+3:32 Stage 1 sep 
 2224  T+3:35 Stage 2 burn 
 2225  T+4:45 Fairing 01 sep 
 2226  T+5:43 Stage 2 sep 
 2226  T+5:48 Stage 3 burn 
 2239  T+18:54 Stage 3 MECO 
 2241  T+20:32 HB 3 sep 
 2244  T+23:55 SPELDA sep 
 2245  T+24:56 Meteosat sep 
 2247  T+26:06 H-10-3 sep burn 
 2253  T+32:11 end of V99 mission
 2310  Spinup to 81 rpm, 1291s, 1.1 kg 
1997 Sep 3    629.77 216 x 35703 x 6.9 
 0500  Slew-1 
 1715  Slew-3 
1997 Sep 4  0750  Slew-4 
1997 Sep 4 1047:16 Mage burn 
 1051:31 Mage eject 
 1147:16  Spin axis erection sae-1 
 1215:44  sae-2 
 1700  Slew 
 1745  Spin to 100 rpm 
 2314:14  Acq-1 7.3m/s 1.1 kg 
1997 Sep 4    1425.82 35350 x 35781 x 1.8 GEO 17.5W+2.8E 
1997 Sep 12    1435.45 35753 x 35794 x 1.8 GEO 10.1W+0.1E 
1997 Sep 15    1436.11 35775 x 35798 x 1.8 GEO 10.1W 
1997 Sep 18   Cover eject 
1997 Sep 18?   Cooler Cover eject 
1998 Apr 7    1436.05 35774 x 35796 x 1.4 GEO 9.7W 
1998 Apr 29   mv out  GEO 9.3W+0.03E 
1998 Jun 16   mv in  1436.14 35777 x 35797 x 1.2 GEO 0.8E 
1999 Sep 1    1436.11 35784 x 35789 x 0.4 GEO 0.4W 
2006 May 6    1436.02 35743 x 35827 x 2.3 GEO -0.2W 
2006 Jul 10   move out of GEO 0E to relocate to IOR 
2006 Aug 1    1433.75 35734 x 35747 x 2.5 GEO 12.7E+0.6E/d 
2006 Oct 12   Move in 1436.24 35730 x 35848 x 2.7 GEO 57.6E 
2015 Apr 14    35783 x 35786 x 9.6 GEO 57.9E

Navstar 43

 1997-035A


GPS 43 (USA 132) was launched by McDonnell Douglas and the 1st SLS, 45th Space Wing using the new LC17 control center. Spacecraft is 1075 kg BOL, 2032 kg launch. 1.5 x 1.9 x 1.9m.


GPS 2R No. 3 
 

DateTimeEventOrbit  

1997 Jul 23  0343:00  Launch by Delta 7925  CC LC17 
 0344:06  SRM 1-6 burnout T+1:06 
 0344:06 SRM 7-9 ignite T+1:06 
 0344:06 SRM 1-3 sep T+1:06 
 0344:07 SRM 4-6 sep T+1:07 
 0345:09 SRM 7-9 burnout T+2:09 
 0345:12 SRM 7-9 sep T+2:12 
 0347:19 MECO 4:19 
 0347:28 Stage 1 sep T+4:28 
 0347:34 SES-1 T+4:34 
 0347:40 PLF sep T+4:40 
 0352:27 SECO-1 T+9:27  175? x 201? x 36.9 
 0402:54 SES-2 T+19:54 
 0403:29 SECO-2 T+20:29  187? x 1149? x 37.2 
 0404:12 Stage 2 sep T+21:12 
 0404:59 TES T+21:59 
 0406:56 TECO T+23:56 
 0408:19 PAM-D sep T+25:19 
 0408:21? Yo weight sep 
 0425?  SECO-3 depletion 
1997 Jul 23    356.65 189 x 20372 x 39.19 
   356.83 166 x 20407 x 38.95 
1997 Jul 25  0655? AKM burn 
1997 Jul 25    701.92 19367 x 20201 x 55.1 
1997 Jul 25    713.15 19902 x 20223 x 54.9 
1997 Aug 18    718.10 20123 x 20247 x 54.9 
2012 Oct 15    717.99 20073 x 20291 x 56.8 

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