Chinasat 20

 2003-052A

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CAST/CASTC DFH-3. According to sinodefense.com, this satellite was Shen Tong 1 and used for Ku-band mobile strategic communications.

\uni{ 神通一号}{ }

Mass 2300 kg. Served at 103E from 2003 to 2008, then at 98E.

In 2008, ZX-20 and ZX-22A exchanged positions `due to the needs of users'. In 2013, ZX-22A moved slightly and ZX-20 returned to the 103E position.

ZX-20
Date	Time	Event	Orbit
2003 Nov 14	1601	Launch by CZ-3A	XSC
		T+2:25 Stage 1 MECO
		T+2:27 Stage 2 MES, Stage 1 sep
		T+3:52 Fairing sep
		T+4:15 St 2 MECO
		T+4:20 St 2 VECO
		T+4:21 St 2 sep, St 3 MES
	1611?	T+10:19 St 3 MECO-1	200 x 200 x 28.5?
	1621?	T+20:00 St 3 MES-2
	1623?	T+22:00 St 3 MECO-2
	1625?	Stage 3 sep	212 x 41981 x
2003 Nov 14			754.15 198 x 41934 x 24.98
2003 Nov 20			1435.96 35770 x 35796 x 0.31 GEO 103.0E
2003 Nov 26			1436.00 35775 x 35793 x 0.29 GEO 103.0E
2006 Aug 8			1436.13 35770 x 35804 x 0.1 GEO 103.0E
2008 Jun 7			1436.12 35781 x 35793 x 0.1 GEO 103.4E
2008 Jun 24		Still tracked at 103E (error?)
2008 Jun 25		Move in at 98E	1436.13 35777 x 35796 x 0.1 GEO 98.1E
2011 Oct 19			1436.03 35775 x 35795 x 0.0 GEO 98.1E
2012 Nov		NSSK ends
2013 Apr 6			1436.07 35763 x 35808 x 0.4 GEO 98.0E
2013 Apr 17		Move out, drift E
2013 May 11		Move in at 103.2E
2013 May 20			1436.01 35773 x 35796 x 0.5 GEO 103.2E
2015 Nov 15			1436.12 35765 x 35808 x 1.4 GEO 103.3E
2017 Dec 19			1436.19 35768 x 35808 x 3.9 GEO 103.1E

Elektro-L 1

 2011-001A

---

NPO Lavochkin took over the plans for a cheaper GOMS satellite, Elektro-L No. 1. Uses Navigator bus. Customers are the Rosgidromet and Planeta agencies. Mass 1766 kg (NK; other sources give 1701 kg, 1740 kg sep, 1620 kg?) launch, 1180 kg EOL; box + panel + antennae.

Launch by Zenit/Fregat to GEO 76E; or, Zenit-3M/Fregat-SB. Once in GEO, the spacecraft adopted the role GOMS-2

Fregat-SB (Sbrasivaemiye baki) with separable tanks. Additional tanks provide extra burn time, total 1767 s?

SBB: Sbrasivaemiye baki banov : Annulus

RB 1050 kg dry, 1.5m high 3.9m dia SBB 360 kg dry 3.9m dia? total 2.4m high so SBB 0.9m? (NK says SBB 357 kg, RB 950 kg). ISP 333.2s, trhust 1400-2000 kg, mass of prop 7100 kg? RB total mass 11600 kg.

Zenit-3SLBF (Zenit-3F) launch vehicle comprises Zenit-2SB80 No. 1-2007/1 and Fregat-SB.No. 2001.

The Zenit second stage reentered on Mar 19 over Los Angeles, with debris falling in Colorado and Utah.

The satellite operated until Nov 2016.

Elektro-L
Date	Time	Event	Orbit
2011 Jan 20	1229:01	Launch by Zenit-3SLBF	KB LC45
	1231:29	T+2:28 St 1 sep
	1234:10	T+5:09 GO sep
	1236:08	T+7:07 St 2 MECO
	1237:38	St 2 sep	178 x 640 x 51.3
	1344:26	MES-1
	1352:40	MECO-1
	1353:17	SBB sep	306 x 4440 x 50.4
	1558:02	MES-2
	1608:59	MECO-2
			361 x 35914 x 48.6
	2119:06	MES-3
	2127:43	MECO-3
	2128:13	Fregat sep
			35413 x 35785 x 0.5
2011 Jan 21	0028:19	MES-4
	0029:39	MECO-4
		Fregat disposal	34196 x 35781 x 0.5
2011 Feb 20			1436.10 35785 x 35788 x 0.4 GEO 76.0E
2014 Mar		Reduced operation
2014 Nov 8			1436.10 35781 x 35791 x 0.5 GEO 75.9E
2016 Jul 12			1436.10 35771 x 35801 x 1.8 GEO 75.8E
2016 Jul 13			1436.10 35771 x 35801 x 1.8 GEO 75.8E
2016 Jul 15			1444.19 35800 x 36089 x 1.8 drift
2016 Sep 9		Move in at 14W	1436.11 35784 x 35780 x 1.9 GEO 14.1W
2016 Oct 1			1436.16 35783 x 35792 x 1.9 GEO 14.3W

Blagovest 2

 2018-037A

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Satellite 14F149. ISS Reshetnev satellite for high speed data transmission. Ekpress-2000 bus. The satellite will be operated by Voentelekom, the new military counterpart to GKPS.

Date	Time	Event	Orbit
2018 Apr 18	2212	Launch by Proton	KB LC81/24
		T+2:00 St 1 sep
		St 2 burn 3:28
		T+5:27 St 2 sep
		T+5:31 St 3 burn
		T+5:46 Fairing sep
	2221	T+9:40 Stage 3 sep
	2223	T+11:16 Briz MES-1
	2228	T+15:22 Briz MECO-1
	2319	T+1:07:28 Briz MES-2
	2337	T+1:25:10 Briz MECO-2	300 x 5000?
2017 Aug 17	0142?	T+3:28:57 Briz MES-3
	0158	T+3:46:49? Briz MECO-3
	0203	T+3:48:10 DTB sep	399 x 35698 x 48.6
2018 Apr 19	0700	T+8:48:17 Briz MES-4
	0713	T+9:01:36 Briz MECO-4
	0714	T+9:02:46 Briz sep
2018 Apr 27			1429.23 35556 x 35748 x 0.1 GEO 71.5E+1.7E/d
2018 Jun 6			1436.11 35776 x 35797 x 0.0 GEO 80.0E

Luxury : A Rich History

https://welib.org/md5/26c6fd2a0df4535f41c428e5dea9ebfe

Kardashian Dynasty

https://welib.org/md5/20b714ca2769ebfd34be23c4577c0289

Fermi

 2008-029A

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FGST, the Fermi Gamma-ray Space Telescope, known as Gamma Ray Large Area Space Telescope until 2008 Aug 26. The NASA/DoE GLAST observes at GeV energies. Delta-class mission. The LAT uses a CsI calorimeter array with a plastic scintillator anticoincidence detector. Field of view is 20 percent of the sky; the telescope is over 30 times more sensitive than EGRET and has a spatial resolution of a few arcmin. The GBM is a successor to BATSE; smaller and less sensitive, it has a wider energy range and is optimised to detect bursts in the same direction as LAT, to provide full spectral coverage from the lowest GBM to the highest LAT energies.

Gamma Ray Large Area Space Telescope (GLAST) is the successor to Compton and covers the range from 10 MeV to 300 GeV. Resolution is 1 arcmin with field of view 20 percent of the sky and 4 percent energy resolution.

Launch by Delta 7920H-10. Mass 4277 kg. Orbit 565 x 565 x 28.5.

NASA-OSS is the sponsor and GSFC manages GLAST; LAT PI is Stanford, with Huntsville and MPE making the GBM.

The Orbital/Gilbert, formerly General Dynamics C4 Systems (Spectrum Astro) Leostar-3 (formerly SA-200) spacecraft is about 2.8m high 2.5m dia box with 2 panels. Mass 4627 kg of which 3097 kg is LAT. Prop is 358 kg. Launch by Delta 7920H-10 with a 6915 PAF adapter.

GLAST
Date	Time	Event	Orbit
2008 Jun 11	1605:00	Launch by Delta 7920H-10C	CC SLC17B
		T+1:17 SRM 1-6 out
		T+1:19 SRM 7-9 on
		T+1:20 SRM 1-6 sep
		T+2:35 SRM 7-9 out
		T+2:39 SRM 7-9 sep
		T+4:24 MECO 119 km Vi 6.316 km/s
		T+4:33 Stage 1 sep
		T+4:38 SES-1
		T+4:43 Fairing sep
	1615:13	T+10:13 SECO-1	185 x 600 x 28.51 (PK)
			189 x 588 x 28.51 (TLE)
	1713:10	T+1:08:10 SES-2
	1714:15	T+1:09:15 SECO-2	557 x 557 x 28.5
	1720:02	T+1:15:02 Stage 2 sep
	1741:42	T+1:36:42 SES-3 evasive
	1741:48	T+1:36:48 SECO-3	213 x 552 x 25.51
	1755:31	T+1:50:31 SES-4 depletion
	1755:47	T+1:50:47 SECO-4	183 x 537 x 20.42
	2058		95.69 542 x 561 x 25.6
2012 Apr 3		TCM to avoid Kosmos-1805
2018 Mar 22		Safemode, stuck solar array
2018 Mar 28		Reactivate with fixed array

Payload:

• LAT Large Area Telescope 20 MeV-300 GeV CsI Calorimeter/tower module (25) (Stanford/Michelson)

• GBM Gamma Burst Monitor 10 keV - 30 MeV (MSFC/Meegan)

The Planets: Photographs from the Archives of NASA

 https://welib.org/md5/a58dc86027de65d6e1f788cc15dade80

Dragon CRS-15

 2018-055B

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Launch cargo 2697 kg (1712 kg cargo with packaging, 985 kg trunk). Ecostress is 550 kg, LEE is 435 kg with FRAM.

Last orbital flight for Block 4 core. Stage 2 performed a long duration (6h 20m) coast test. Deorbit over N Atlantic around 55W 32N.

CRS15
Date	Time	Event	Orbit
2018 Jun 29	0942:42	Launch by Falcon 9	CC SLC40
		T+2:45 MECO
		T+2:48 St 1 sep
		T+2:56 St 2 burn
	0951:13	T+8:31 SECO
	0952:13	T+9:31 St 2 sep
	0954:58	T+12:15 Solar array covers ejected
	0954:58	T+12:16 Solar arrays deploy
	1022?	St 2 orbit adjust
	1605	T+6h22 St 2 deorbit 400 m/s
	1615?	St 2 reentry over N Atlantic
2018 Jul 2	0911	Depart 350m hold
	0916?	250m hold point
	0918	200m range
	0945	At 30m hold
	1023	At 10m capture point
	1054	Grapple by SSRMS
	1338	First stage capture on Harmony
	1352	Second stage capture

Payload:

• ECOSTRESS, for JEM EF Site 10. ECOsystem Spaceborne Thermal Radiometer Experiment on Space Station, with PHyTIR Prototype HyspIRI Thermal Infrared Radiometer. 40m res IR sensor with 1.6mu cloud band and five 8-12.5mu IR bands. Measures vegetation temperature. 490 kg. 1.85 x 0.80 x 0.93m box.

USA-172

 2003-048A

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Launch by 2SLS/LMAO, the LMMS satellite DMSP S-20 was built by LMMS/East Windsor and had been stored at Sunnyvale. The satellite is 1960 kg full, probably about 1300 kg on orbit.

It was the first to carry a full 5D-3 set of instruments.

It is 4.4m long 1.22m dia with 6.6m x 2.7m solar panels. Two steel despin cables 4.6m long and 0.006m dia. 10 days after launch the OLS cover (1.0m x 0.4 x 0.4m) and the OLS cooler cover (0.30 x 0.02m) will be jettisoned.

Launch in Jan 2001 was cancelled due to problems with the DMSP IMU. Multiple delays led to an Oct 2003 launch. After launch the satellite is turned over to NPOESS and operated by NOAA's Office of Satellite Operations.

Cover name is USA-172.

DMSP
Date	Time	Event	Orbit
2000 Oct		Stacking at SLC-4W
2001 Jan 20		T-3min scrub, GSE problem
2001 Jan 21		T-28s scrub, valve sluggish
2001 Jan 22		T-20h? scrub, fuel leak
2001 Jan 23		T-12h? scrub, IMU problem
2001 Oct?		Titan turbopump seals problem, delay
2002 Jan		Hydrazine thruster problem, delay
2002 Feb		Destack Titan
2002 Jul		Restack Titan
2002 Oct		SSMIS soldering problem, delay
2002 Nov		Destack Titan
2002 Aug		Restack
2003 Oct 18	1617	Launch by Titan 23G-9 'Cindy Marie'	V SLC4W
		T+2:30 St 1 MECO
		T+2:30 St 2 TIG
		T+3:35 Fairing sep
	1622	T+5:25 St 2 MECO
	1623:29?	T+6:29 St 2 sep
	1623:36?	T+6:36 RCS sep burn	-2603 x 891 x 98.6
	1630:58?	T+13:58 Star 37 burn 51s
	1631:49?	T+14:49 Star 37 burnout	102.00 849 x 856 x 98.8
	1631:59?	T+14:59 21s RCS burn
	1633?	Despin weights
2003 Oct 19			101.88 843 x 852 x 98.93
2016 Mar		Secondary operational sat at 0410 LT

Iridium 97

 2002-031A

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Replenishment mission IS-2, two Iridiums (97 and 98) on a Rokot from Plesetsk.

Iridium SV97
Date	Time	Event	Orbit
2002 Jun 20	0933:46	Launch by 14A05 Rokot	PL LC133-3
		T+2:12 St 2 vernier
		T+2:16 St 1 sep
		T+2:21 St 2 MES
		T+3:07 Fairing
		T+4:48 St 2 MECO
		T+5:18 St 2 VECO
	0938	T+5:19 St 2 sep
		T+5:25 Briz 3L MES-1
	0948	T+14:45 Briz MECO-1	92.8 156 x 668 x 86.59
	1046:45	T+1:12:59 Briz MES-2
	1047:08	T+1h? Briz MECO-2
	1111:41	SV97 sep	658 x 669 x 86.6
	1111:41	SV98 sep
	1129:21	CCAM burn	238 x 659 x 86.6
2002 Jun 26			98.02 658 x 669 x 86.6
2002 Jul 13			98.19 669 x 675 x 86.6
2002 Oct 5			98.19 667 x 676 x 86.6
2004 Jun 30			98.19 669 x 673 x 86.6
2007 Jan 5			98.19 670 x 673 x 86.6
		Raised to operational orbit, replacing 36
2007 Jan 9			100.40 773 x 781 x 86.40
2007 Feb 27			100.40 776 x 778 x 86.40
2018 Feb 15			100.40 776 x 778 x 86.40

GRACE

 2002-012A

---

The second ESSP mission is the Gravity Recovery and Climate Experiment (GRACE), a joint NASA/DLR mission. Two GRACE satellites in 450 x 450 km x 90 deg orbits will measure gravity field variations and maintain a 200 km distance. The two satellites, each with a mass of 475 kg, will be launched on a single Rokot rocket in 2001 Jul. The satellites will be built Astrium (Dornier)/Friedrichshafen, and the project is a joint effort between NASA and DLR, run by the U Tex. Austin and GFZ (GeoForschungsZentrum) in Potsdam with project management by JPL. It uses the Astrium FlexBus platform, like CHAMP.

3.1 x 0.77 x 1.9m, 475 kg each, stacked vertically on either side of an MSD (Multi Satellite Dispenser) aboard Briz-M. MSD is built by Krunichev and Astrium RST/Rostock. FM1 and FM2 nicknamed 'Tom' and 'Jerry' during integration.

Sats to be spaced 220 km apart. GRACE 1 swapped with G2 to become the trailing satellite in Dec 2005. Separation was reduced to 70-170 km for one month.

GRACE 1
Date	Time	Event	Orbit
2002 Mar 17	0921:27	Launch by Rokot	PL LC133/1
		T+2:16 St 1 sep
		T+3:05 Fairing sep
		T+5:19 St 2 sep
		T+5:19 Bris MES-1
	0936:28	T+15:01 Briz MECO-1	300 x 300 x 86.4?
	1042	T+1:20:38 Briz MES-2 34s	300 x 500 x 86.4
		T+1:20:54 Briz MECO-2
	1047	T+1:25:38 GRACE sep	500 x 500 x 90
		T+1:41 CCAM burn
2005 Apr 6		Small inclination diff added
2005 Dec 3		OTM-1 Grace-2 Orbit trim for swap burn at -203 km
2005 Dec 10	0347	GR-2 pass GR-1 at 406m
2005 Dec 12		GR-2 OTM-2, +58 km, 3.3 km/d
2006 Jan 11		GR-2 OTM-3 at +170 km, 0.5 km/d
2017 Dec		Out of prop
2017 Dec 13		Last contact
2018 Mar 10	0610?	Reentered

Payload:

• GPS system

• Microwave intersatellite link

2002-012B

---

The second ESSP mission is the Gravity Recovery and Climate Experiment (GRACE), a joint NASA/DLR mission. Two GRACE satellites in 450 x 450 km x 90 deg orbits will measure gravity field variations and maintain a 200 km distance. The two satellites, each with a mass of 475 kg, will be launched on a single Rokot rocket in 2001 Jul. The satellites will be built Astrium (Dornier)/Friedrichshafen, and the project is a joint effort between NASA and DLR, run by the U Tex. Austin and GFZ (GeoForschungsZentrum) in Potsdam with project management by JPL. It uses the Astrium FlexBus platform, like CHAMP.

3.1 x 0.77 x 1.9m, 475 kg each, stacked vertically on either side of an MSD (Multi Satellite Dispenser) aboard Briz-M. MSD is built by Krunichev and Astrium RST/Rostock. FM1 and FM2 nicknamed 'Tom' and 'Jerry' during integration.

Sats to be spaced 220 km apart. GRACE 1 swapped with G2 to become the trailing satellite in Dec 2005. Separation was reduced to 70-170 km for one month.

GRACE 1
Date	Time	Event	Orbit
2002 Mar 17	0921:27	Launch by Rokot	PL LC133/1
		T+2:16 St 1 sep
		T+3:05 Fairing
		T+5:19 St 2 sep
		T+5:19 Bris MES-1
	0936:28	T+15:01 Briz MECO-1	300 x 300 x 86.4?
	1042	T+1:20:38 Briz MES-2 34s	300 x 500 x 86.4
		T+1:20:54 Briz MECO-2
	1047	T+1:25:38 GRACE sep	500 x 500 x 90
		T+1:41 CCAM burn
2005 Apr 6		Small inclination diff added
2005 Dec 3		OTM-1 Grace-2 Orbit trim for swap burn at -203 km
2005 Dec 10	0347	GR-2 pass GR-1 at 406m
2005 Dec 12		GR-2 OTM-2, +58 km, 3.3 km/d
2006 Jan 11		GR-2 OTM-3 at +170 km, 0.5 km/d
2017 Sep 3		Partial battery failure
2017 Sep 8		Mission recovered
2017 Oct 27?		End of science mission
2017 Dec 24	0016?	Reentered