Reflections of Cape Carnival

https://welib.org/md5/9a0e737346cf7b82c47afb2568f1fd7a

GOES-10

 1997-019A

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GOES K was launched in Apr 1997 on the final Atlas I Centaur and renamed NOAA GOES 10. Mass was 2100 kg. GOES 10 was placed in on orbit storage as an operational spare. The plan was to spin-stabilize it while in storage. A solar panel drive failure in Jun 1997 threatened the mission, but operating it in reverse (and flipping the whole satellite) fixed the problem, at the cost of rewriting the ground analysis software.

GOES 10
Date	Time	Event	Orbit
1997 Apr 25	0549	Launch by AC-79	CC LC36B
	0551	BECO T+2:36
	0551	Booster sep T+2:39
	0552	Fairing sep T+3:36
		Atlas SECO
	0553	Atlas sep T+4:27
	0553	Centaur TIG1 T+4:49
	0559	Centaur MECO1 T+10:03	148 x 407 x 28.4 (s)
	0613	Centaur TIG2
	0614	Centaur MECO2
	0618	Centaur sep	757.57 167 x 42131 x 27.0 (A)
	0642	Centaur depletion	751.80 136 x 41883 x 27.1 (B)
	0710	Solar panel deploy begins
1997 Apr 25			757.9 140 x 42175 x 27.1
1997 Apr 27	0200?	LAM1
1997 Apr 27		Intermediate?	850.38 4503 x 42205 x 27.6
1997 Apr 27			991.84 10909 x 42224 x 8.1
1997 Apr 29	2030?	LAM2 over 44W
1997 Apr 30			1409.68 28230 x 42305 x 1.1
1997 May 1	1930?	LAM3 over 30W
1997 May 1			1607.36 35593 x 42257 x 0.5
1997 May 3	1330?	LAM4 over 103W
1997 May 4			1436.94 35596 x 36010 x 0.5
1997 May 8			1437.70 35615 x 36020 x 0.4 GEO 104.4W+0.4W
1997 May 13			1436.16 35772 x 35803 x 0.4 GEO 105.1W
1997 Jun		Solar panel drive failed
1997 Jul 31		Spacecraft rotated 180 deg
1998 May 2			1436.00 35769 x 35800 x 0.3 GEO 104.6W
1998 Jun 5		GOES 10 turned over to NOAA
1998 Jul 9		Activated	GEO 105W
1998 Jul 20			1435.93 35772 x 35794 x 0.4 GEO 103.8W
1998 Jul 26		mv out	1440.03 35794 x 35932 x 0.4
1998 Sep 14		mv in	1436.20 35778 x 35799 x 0.3 GEO 135.1W
1999 Oct 17			1436.00 35774 x 35794 x 0.2 GEO 135.2W
2006 Jun 29			1435.95 35774 x 35793 x 0.9 GEO 134.5W
2006 Jun 30		move out
2006 Aug 4			1435.01 35759 x 35771 x 1.0 GEO 125.5W+0.3E/d
2006 Dec 4		Arrived at 60W
2007 Oct 11			1436.18 35764 x 35812 x 2.1 GEO 59.6W
2009 Jun		S American imaging support
2009 Nov 30			1436.25 35772 x 35806 x 4.0 GEO 60.4W

HETE-2

 2000-061A

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The HETE-2 gamma ray burst locator satellite was funded to replace the original HETE lost in a launch failure. It replaced the UV sensor with an extra soft X-ray imager, following the discovery by BeppoSAX of X-ray afterglows to gamma ray bursts. HETE-2 is built by MIT rather than AeroAstro, using left over HETE parts. The ground network is a series of small terminals across the world, which relay data back to MIT. MIT operates the satellite; management is GSFC.

HETE-2 was staged from KMR on Pegasus mission P-35. The Pegasus H (Hybrid) has standard stages 1 and 2, with XL's stage 3 and avionics. Takeoff from PKWA (Bucholz Army Airfield) RW 06/24, at 08 42.9N 167 43.6E. Drop point is 7.65N 167.7E; azimuth is 118.45 deg, altitude 11.9km.

Launch control was remotely from CCAFS Hangar AE.

Mass is 124 kg. Size is about 1.0h 0.5d 2.5 span. Resolution 10' to 10".

In Dec 2005 NASA stopped funding but MIT continued operating the satellite.

HETE 2
Date	Time	Event	Orbit
2000 Oct 9	0440	TO from PKWA
	0538:18	Drop Pegasus P-35
	0538:23	Ignition
		T+1:21 St 1 burnout
		T+1:30 St 1 sep
		T+2:10 fairing sep
		T+2:49 St 2 burnout
		527 s coast
		T+8:58 St 2 sep
	0547:32	T+9:09 St 3 burn
	0548:39	T+10:16 St 3 burnout
	0550:34	T+11:16 Stage 3 sep
		Orbit	600 x 600 x 2
2000 Oct 10			97.02 595 x 636 x 1.95
2005 Dec		Control transfer to NASA
2007 Mar 28		Still operational, sporadic ops
2009?		end of operations
2010 Aug 30			96.24 561 x 594 x 1.95

Payload:

• FREGATE French Gamma Telescope, Lilas-derived Omnidirectional gamma ray spectrometer, 2 sr resolution, 6-400 keV

• WFXM Wide field X-ray monitor, coded mask 2-25 keV

• SXC Soft XR imagers, 2; 33" resolution