April 9,2000

https://web.archive.org/web/20080504034924/http://digest-archive.degrassi.ca/DD91.htm

DFH-45

 1997-029A

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The FY-2 weather satellite was launched in Jun 1997 after a long delay caused by the explosion of the first flight model during testing.

The spin-stabilized FY-2 was built by the Shanghai Aerospace Technology Research Institute and had a mass of 1380 kg. It will be stationed at 105E and controlled from the Xi'an control center. The satellite is a 2.1m dia 4.5m high cylinder with antenna deployed and AKM attached. The main bus is 2.1 dia 1.6m high, with antenna but without AKM it is 3.0m high. The FG-36 AKM is a cylinder-cone 1.5m high 1.0m dia and 729 kg full 70? empty, leaving a BOL mass for FY-2 of 651 kg. AKM Burn time is 43s, Isp 289.0. After the AKM fires and is ejected, an imager cover is also ejected into near-GEO.

FY2
Date	Time	Event	Orbit
1997 Jun 10	1201	Launch by CZ-3	XSC
		T+2:06 St 1 MECO
		T+2:07 St 2 burn
		T+4:15 St 2 MECO
		T+4:19 Fairing sep
		T+4:22 St 2 VECO
		T+4:23 Stage 3 burn
	1212	T+11:08 MECO-1
	1216	T+15:35 MES-1
	1221	T+20:53 Stage 3 MECO-2
	1222	T+21:32 Stage 3 sep
1997 Jun 10			635.12 206 x 35987 x 28.5
1997 Jun 10			141 x 36043 x 27.8 (R/B?)
1997 Jun 11	0418?	AKM burn
1997 Jun 11	0430?	AKM separated	1399.72 34099 x 36044 x 0.3
1997 Jun 11			1396.45 34015 x 35998 x 1.3
1997 Jun 11			1403.34 34069 x 36216 x 1.3 GEO 114.9E+8.4E
1997 Jun 17			1436.08 35780 x 35792 x 1.2 GEO 105.0E
1997 Jul 10			1436.01 35781 x 35788 x 1.1 GEO 104.1E
1999 Oct 13			1436.09 35784 x 35788 x 0.7 GEO 104.8E
2000 Apr 23		Moved out	1548.33 35773 x 36278 x 0.1 GEO 104E dr
2000 May 10		mv in	GEO 85.5E
2000 Jun 11			1436.15 35767 x 35807 x 0.3 GEO 85.6E
2004 Feb 14			1436.07 35784 x 35787 x 3.5 GEO 87.2E

LCROSS

 2009-031B

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Lunar Crater Observation and Sensing Satellite, NASA-Ames/NGST. Launch on same LV as LRO. Makes lunar flyby (LSB, Lunar SwingBy) to high inc 37-day orbit and then re-encounters moon 87 days (two orbits) later. Sep 7 hr prior to impact. Impact at 2.5 km/s 65 deg or 80 deg. This is known as a LGALRO orbit - Lunar Gravity Assist, Lunar Return Orbit. Eclipitic incl. 80 deg.

Upper stage will crash into south pole crater; flyby will observe and fly through plume. Finally flyby sc will impact itself 10-15 min later.

Flyby is S-S/C Shepherding Spacecraft. PAFs connect SS to LRO and SS to EDUS.

Stage is EDUS - Earth Departure Upper Stage, i.e. Centaur.

SS is built around ESPA ring 1.5m dia 0.6m high surrounded by offset panels carrying instruments, making it around 2.0m tall 2.6m dia, span 3.3m across antennae. ESPA was developed by CSA Engineering, Mountain View, Calif. The satellite is an NG EagleSat.

Mass 901 kg SS including 590 kg prop, 2000 kg EDUS

Mass is 891 kg launch ( 585 kg dry and 306 kg hydrazine.). Mass at impact ranges from 621 to 866 kg depending on exact trajectory and prop usage.

Centaur is 2249 kg to 2366 kg (nominal 2305 kg).

Impact target is crater Cabeus.

LCROSS
Date	Time	Event	Orbit
2009 Jun 18	2132	Launch by Atlas V 401 AV-020	CC LC40
		T+4:10 Atlas sep
		T+4:20 MES-1
		T+4:30 Fairing sep
		T+14:30 MECO-1	167 x 200
		T+36:42 MES-2
		T+41:42 MECO-2	165 x ?
	2218	T+46:12 EDUS/LCROSS sep from LRO
	2218	CCAM
		T+46:16 Begin blowdown	133 x 348640 x 28.0
	2341	MES3
	2345	MECO-3
2009 Jun 19	0131:06	T+4:00:00 LCROSS takes over Centaur control
	1334	Pass EL1:4
		37-day orbit
2009 Jun 20	1115	TCM-1 8.1m/s 9:40 using 22N thrusters
	2315	TCM-2
2009 Jun 22	1030	TCM-3
2009 Jun 22	1704	Enter lunar sphere, 66200 km
2009 Jun 23	1030:33	R=5008 km h=3270	3270 x -18741 x 85.13
		T+5d Lunar flyby
	1220	Lunar swingby?
2009 Jun 24	0346	Leave lunar sphere, R=66200 km
2009 Jun 26			57267.254 347952 x 623592 x 45.50
2009 Jul 10		Apogee-1 R=582000
2009 Jul 15	1700	Cold side bakeout of ice, 0.03m/s dV
2009 Jul 21	1300	TCM 5a 21.1m/s, target lunar impact
2009 Jul 30	1600	CSB-2, 0.01m/s
2009 Jul 31		Perigee-1 R=357000
2009 Aug 16		Apogee-2 R=521000
2009 Aug 21	1107	Anomaly, LCROSS spinning, 150 kg prop used
2009 Sep 3		Perigee-2 R=381000
2009 Sep 22		Apogee-3 R=570000
2009 Sep 25	1028	TCM-7 to target Cabeus A1, 0.32m/s
2009 Sep 30	1500	TCM-8, switch to Cabeus, 0.35m/s
2009 Oct 6	0000	TCM-9 7.6s
2009 Oct 8	1748	Enter lunar sphere of inf.R= 66183 km
2009 Oct 9
	0030	44800 km range
		Centaur tail-first	-1707 x -17258 x 87.10
	0150	Centaur sep, I-9h:40, +0.15m/s
	0201	Centaur 0.8 km range from SS
	0230	SS braking burn I-9h:00 4m5s
	1036	Activate instruments at range 300m, I-0:56
	1131:19	Centaur impact, I-0h:00 -84.675 311.275E, Cabeus
		84.6778S 48.7254W
	1135:45	SS impact, I+0:04 -84.729 310.64E
		84.7193S 49.6203W

Payload:

• VIS Visible Camera (10 cm ap?)

• NIR1 Near IR Camera 1 (4 cm?)

• NIR2 Near IR Camera 1 (4 cm?)

• MIR1 Mid IR Camera 1 (3 cm ap?)

• MIR2 Mid IR Camera 1 (3 cm ap?)

• VSP Visible Spectrometer (3 cm?)

• NSP1 Near IR Spectrometer 1 (10 cm?)

• NSP2 Near IR Spectrometer 2

Oceansat

 2009-051A

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Derived from IRS bus. Box + 2 panels. 960 kg inc 100 kg of hydrazine.

Launched with UWE 2, BEESAT, ITUpSAT-1, SwissCube. Uses L2.5 stage.

Oceansat
Date	Time	Event	Orbit
2009 Sep 23	0621	Launch by PSLV CA	SHAR
	0623	T+111 PS1 sep 51 km 1.58 km/s
	0623	T+112 PS2 burn 51 km 1.58 km/s
	0624	T+187 Heatshield sep 115 km
	0625	T+242 PS2 sep 214 km 3.65 km/s
	0625	T+263 HPS3 burn
	0629	T+529? HPS3 sep 550 km
	0629	T+538? PS4 burn 5.37 km/s 541 km
	0638	T+17:07 T+1027s 740 km PS4 cutoff
	0638	T+17:44 T+1064s 729 km 7.49 km/s PS4 sep
	0638	Nanosats sep

Payload:

• OCM Ocean color monitor Vis/NIR 8-band imager, 1420 km swath

• SCAT Scanning Microwave radar scatterometer

• ROSA Radio Occultation Sounder for Atmospheric Studies

USA-194

 2007-027A

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AV-009 Atlas V 401 from SLC41.

3250 kg each?

NOSS launch codenamed 'PYXIS'. The Centaur second burn had a problem and the payload was delivered to a lower than planned orbit; it was expected that on board propulsion would let the mission reach its planned orbit, assumed to be 1150 km x 63 deg.

After the first Centaur burn, a valve failed to close and fuel leaked out during the coast phase, leading to early fuel depletion during the second burn.

The UN-released orbit was 714 x 953 km x 63.3 deg. The 2009 EELV Cape history by M. Cleary spun the issue as 'there was some loss in performance during the second stage burn, but the payload was launched successfully'. Nevertheless the orbit achieved was signicicantly different from the desired one and I count this flight as a launch failure for statistical purposes.

NROL-30
Date	Time	Event	Orbit
2007 Jun 15	1512:00	Launch by Atlas AV-009	CC SLC41
		Ascent on Az 46.85
		Atlas MECO
		T+4:15? Atlas sep
		T+4:23? Centaur MES-1
		T+4:38? Fairing
	1530?	T+18 min? Centaur MECO-1
	1629?	T+1:17? Centaur MES-2
		Centaur premature shutdown
	1630?	T+1:18? Centaur MECO-2	105.22 783 x 1225 x 63.6
	1634?	T+1:22? Payload sep
		Centaur blowdown	101.57 715 x 951 63.4
2007 Jun 18			105.45 847 x 1183 x 62.7
2007 Aug 11			106.08 904 x 1186 x 63.4
2008 Feb 17			107.36 997 x 1211 x 63.4
2008 Jun 10		Orbit raise to operational alt	107.41 1014 x 1198 x 63.4
2009 Apr 26			107.42 1033 x 1181 x 63.4

March 29,1998

 https://web.archive.org/web/20080504032647/http://digest-archive.degrassi.ca/DD17.htm