Shenzhou 9

 2012-032A

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Zhilingzhang (Cdr) Jing Haipeng (or zhihuichang); crew Liu Wang and Liu Yang. Liu Yang is the first woman to fly on a Chinese spaceship.

China Manned Space Engineering Office Zhongguo zairen hangtian gongcheng bangonghsi

Liu Yang is responsible for hagtian yixue kongjian kexue shiyan (aerospace medicine science experiments)

Backup crew Nie Haisheng, Zhang Xiaoguan, Wang Yaping.

SZ9
Date	Time	Event	Orbit
2012 Jun 16	1037:21	Ignition
	1037:25	Launch by CZ-2F Y9	JQ
		T+2:00 LES sep
		T+2:34 SOB burnout, sep
		T+2:35 St 1 MECO
		T+2:36 St 1 sep, St 2 burn
		T+3:28 Fairing sep, 2 halves
	1045:01	T+7:36 St 2 MECO
	1046:56	T+9:31 VECO
	1046:59	St 2 sep T+9:34
	1045	St 2 sep
	1050	Solar panels out	202 x 312 x 42.7
	1735?	Orbit adjust	261 x 316 x 42.8
		32E ejected?	263 x 378 x 42.8
2012 Jun 17	1440?	Orbit adjust	315 x 326
2012 Jun 18		Approach to TG-1
	0543	Range 400m
	0601	Range 140m/
	0603	Stationkeep at 30m
	0606?	Final approach
	0608	Docking
	0614	Docking complete
	0907	HO, entry
2012 Jun 24
	0309	Undocking
	0312	Undocking (CMSE report)
		Retreat to 400 m
		Approach to 140 m
		Final approach
	0449	Docking by Liu Wang
	0455	Docking complete (CMSE report)
2012 Jun 26
	0642	180 deg yaw change
2012 Jun 28
	0122	Manual undocking by Liu Wang
	0124	Undocking (CMSE)
		Stationkeep at 140m
		Stationkeep at 5 km
		Approach TG-1, automatic
	0300?	Stationkeep at 140 m
	0435?	Sep burn, perigee raise
2012 Jun 29	0101:28	Deorbit at 77.023, 15.184; 335.118, -2.585, -5.784, -7.106
	0116?	OM sep
	0117	Retrofire
	0138?	SM sep
	0143?	Entry
	0159	On parachutes descending
	0202	Land 111.30E 42.27N

Dragon C2

 2012-027A

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A test version of SpaceX's Dragon cargo delivery vehicle: it consists of a cylindrical service module with two solar arrays, and a conical reentry vehicle. Falcon 9 has 4.0 and 5.2m diameter fairings. SM has 18 Draco MMH/N2O4 thrusters with 400N thrust. The Draco thruster can fire for up to 10 min.

Dragon will carry 7 crew or 2500 kg of cargo. It comprises a Pressure Section, a Service Section and a Trunk Section for unpressurized cargo; a nosecone during ascent. Solar panels are on the trunk.

Carries 18 MMH/NTO thrusters with 1230 kg of prop. Size is 3.7m dia 4.6m high at launch; 3.0m high after nosecone ejected.

Falcon 9 has nine Merlin 1C engines for a total of 3680 kN thust; second stage has Merlin 1C Vac with 427 kN.

The C1 mission will fly 4.5 orbits. C2 will flyby ISS, C3 will berth with ISS. The C2 and C3 flights were combined to "C2+" or "C2/C3".

Dragon is 3.0m tall 3.66m dia, trunk is 2.3m tall 3.66m dia; 16.5m span.

Nominal mass is 6130 wet, 4900 kg dry; up to 6000 kg of cargo. On this flight cargo is 520 kg up, 660 kg down. So launch mass is 6650 kg.

Stage 1 dry is 17726 kg; Stage 2 is 2957 kg. Density of LOX and Kero are 1.41 kg/l and 0.81 kg/l, volume 39k 25k and 7.3k 4.6k 3.7854 liter = 1 gal so 1 gal LOX = 5.34 kg, 1 gal Kero = 3.07 kg so mass is 208t 77t, 39.0t 14.1t

Dragon COTS 2
Date	Time	Event	Orbit
2012 May 22	0744:38	Launch by Falcon 9	CC SLC40
		T+3:00 MECO
		T+3:05 St 1 sep
		T+3:12 St 2 burn
		T+3:52 Nose cone sep
	0753:52	T+9:14 SECO
	0754:27	T+9:49 Stage 2 sep
			297 x 346 x 51.6 (SpX)
	0755	T+11:18? Jettison solar array covers
	0755	T+11:53 Solar panel deploy
		T+54:49 AGPS demo
	1030?	T+2:26:48 GNC bay door open
		T+2:40:49 Rel nav checkout
	0933?	Orbit adjust
		T+4:11:20 Coelliptic
		T+8:46:52 PHA1 Abort backoff demo, single burn
		T+9:31:25 PCE1 burn
		T+9:57:58 Pulsed abort demo
		T+10:37:58 Free drift demo
2012 May 23	1022:03s	HA1 burn
	1108:06s	CE1 Coelliptic burn
2012 May 24	0757	HA2 Height adj burn, flyby
	0843	CE2 burn coelliptic
	0930	RGPS demo
2012 May 24	0954	Range 23 km
	0957	Pettit tallyho Dragon
	1125	R-bar nadir crossing at 2.5 km
		UHF comm demo
		Crew command panel (CCP) demo on ISS
		back off to range 7 to 10 km
	1133	End pass, strobe off
	1209	DHA burn
	1253:10	DCE burn
2012 May 25	0235s	Rear HA
	0321s	Rear CE
	0454:58	HA2 Height adjust
	0532s	CE2
	0703:40	HA3
	0717s	HA3-MC1
	0737?	HA3-MC2
	0748?	CE3
	0818:52	HA4/AI (Approach initiation) burn
	0828s	HA4-MC1
	0852	HA4-MC2
		ISS approach to 2.5 km
	0844	ISS app to 1.4 km, approach ellipsoid
	0912?	Hold at 350m nadir
		Yaw mvr
	0920	Approach to 250 m
	0929	Hold at 250m
		LIDAR test
	0956	Resume approach
	1000	Approach at 235m nadir
	1000	Retreat to 250m hold point
	1006	Hold at 250m
	1019	Approach
	1022	Hold at 240m?
	1103	Approach to 200 m
	1114	Hold at 200m
	1121	Enter Keep Out Sphere (KOS) at 200m
	1133	Hold at 150m
	1144?	Resume approach towards 30m
	1201	Hold at 78m for LIDAR reconfig
	1221	resume approach
	1225	At 59m, command retreat
	1228	Hold at 78m
		Reflections off JEM EF require LIDAR reconfig
	1303	resume approach
	1313	hold at 30m
	1329	resume
	1347	hold at 10m
	1350	Go for capture
	1356:01	SSRMS capture Dragon (Pettit)
	1552	SSRMS berth Dragon, stage 1
	1602	Berth complete on Harmony nadir CBM
2012 May 26
	0953	Dragon hatch open
2012 May 27
		SSRMS ungrapple Dragon
		SSRMS grapple Dextre
2012 May 29?
	1930?	SSRMS/SPDM inspect Dragon trunk
		SSRMS berth SPDM on MBS PDGF-2
		SSRMS ungrapple SPDM
		SSRMS grapple Dragon
2012 May 30		Dragon hatch close
2012 May 31
	0807	Unberth
	0949	SSRMS deploy at 10m point, ungrapple
	0950	Sep burn 1, retreat on R-bar
	0951	Sep burn 2
	1001	sep-3, leave approach ellipsoid
		GNC bay door close
	1451	Deorbit burn (ungrap+4h) 9:50 100m/s
	1509	Jettison trunk
	1525	Entry
	1536s	Parachute deploy
	1542	Land in Pacific, 450 km off California
		120N 27W

Payload:

• ISS cargo, 520 kg (660 kg return): food, water, clothing

  • 306 kg food and provisions

  • 21 kg NanoRack Module 9, ice bricks

  • 123 kg cargo bags

  • 10 kg computers

  • 60 kg packaging

• Return cargo, 660 kg

  • 143 kg crew pref items

  • 93 kg payloads: Plant Signalling hardware, SHERE polymer experiment, MSRR cartridges, other experiment components and tapes

  • 345 kg: Multifiltration bed, FPCA (fluids control and pump assy) Iodine water containers, JAXA Multiplexer

  • 39 kg, EMU hardware and gloves

Kompsat 3

 2012-025B

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KOMPSAT-3 built by KARI with Astrium support, similar to Kompsat-2. Hex cyl + 3 panels 800 kg

Date	Time	Event	Orbit
2012 May 17	1639	Launch by H-2A 202	TNSC Y LP1
		T+2:05 SRB-A sep 59 km
		T+4:16 Upper fairing sep (2 halves) 148 km
		T+6:36 MECO 301 km
		T+6:44 St 1 sep 313 km
	1645	T+6:50 SEIG
	1654	T+15:26 SECO-1 676 km
	1655	T+16:16 Kompsat-3 sep
	1658	T+19:21 Adapter sep
	1658	T+19:26 Lower fairing 2 side panels sep.
	1702	T+23:11 GCOM-W1 sep
	1712	T+33:20 SDS-4 sep
	1729	T+50:00 Horyu-2 sep over S Atlantic, 692 km
		Stage 2 thermal experiments

Payload:

• AEISS Advanced Earth Imaging Sensor System, pan and MS imager 1.2m dia

Tianhui 2

 2012-020A

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The PLA's TH-1 series may be identical to ZY-3 (State Bureau of Surveying and Mapping) 

TH1B
Date	Time	Event	Orbit
2012 May 6	0710:05	Launch by CZ2D	JQ SLS2 (LC43 Pad 603)
		T+2:36 St 1 MECO
		T+2:36 St 1 sep
		St 2 burn
	0712	T+3:06 Fairing sep
	0715	T+5:34 Stage 2 MECO
	0720	T+10:26 Stage 2 VECO
	0721	T+11:11 Stage 2 sep	490 x 506 x 97.4
		Stage 2 deorbit

Intelsat 22

 2012-011A

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First Boeing 702MP (medium power)

IOR satellite at 72E to replace IS-4 and provide ADF payload.

Box + 2 panels.

Mass 6249 kg (ILS MO), 6199 kg (IS web page).

IS-22
Date	Time	Event	Orbit
2012 Mar 25	1210:32	Launch by Proton-M	KB LC200/39
	1212:31	St 1 sep
	1215:59	St 2 sep
	1216:17	GO sep
	1220:14	St 3 MECO	-495 x 170 x 51.5
	1220:14	St 3 sep
	1221:48	MES-1
	1226:14	MECO-1	173 x 173 x 51.5
	1401:02	MES-2
	1420:36	MECO-2	294 x 5989 x 51.0
	1634:21	MDU-3	295 x 5996 x 51.0
	1643:28	MECO-3
	1644:18	DTB sep	363 x 14407 x 50.8
	1645:45	MDU-4
	1654:27	MECO-4	433 x 69497 x 50.38
2012 Mar 26
	0325:37	MDU-5
	0328:48	MECO-5	3783 x 64892 x 28.4
	0340:32	IS-22 sep
	0650:52	SOZ-7
	0800:42	SOZ-8
2012 Mar 26			1363.57 3876 x 64833 x 28.5
2012 Mar 29		LAM-1	1432.55 6644 x 64784 x 21.2 GEO 94.6W+0.6E/d
2012 Mar 31		LAM-2	1578.38 12288 x 64766 x 13.2
2012 Apr 2			1578.5 12289 x 64769 x 13.2
2012 Apr 4		LAM-3	2153.47 32880 x 65864 x 2.6
2012 Apr 7		LAM-4	1545.92 35789 x 40029 x 0.4
2012 Apr 9		LAM-5	1451.84 35786 x 36402 x 0.1
2012 Apr 10			1450.48 35783 x 36351 x 0.1

DSP-21

 2001-033A

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DSP-21 launched by Titan 4B-31 with the IUS-16 upper stage. Shortly afterwards, DSP 17 vacated the 103E position and was replaced by DSP 18 which moved there from the 70E position; it seems a reasonable assumption that DSP 21 occupied the prime 70E Indian Ocean position.

DSP 21 carried a sensor to detect space weather related anomalies.

DSP-21
Date	Time	Event	Orbit
2001 Aug 6	0728:00	Launch by Titan 4B	CC LC40
		T+2:11 St 1 MES
		T+2:26 SRMU sep
		T+3:26 PLF sep
		T+5:21 St 1 MECO, sep
		T+5:21 St 2 MES
	0736	T+8:55 St 2 MECO
	0737	T+9:05 St 2 sep	94.54 328 x 663 x 28.7
			189 x 764 x 28.6 (UN)
	0841	T+1:13:29 IUS SRM-1
	0843	T+1:15:51? IUS SRM-1 cutoff
	1357	T+6:29:32 SRM-1 sep	39.1 367 x 36033 x 28.1 (UN)
	1400	T+6:32:56 SRM-2 burn
	1402	T+6:34:40? SRM-2 burnout
	1422	T+6:54:51 SRM-2 sep
2001 Aug 7?		Cover sep
2001 Sep?			GEO 70E?
2003 Nov		DSP Indian Ocean	GEO 70E
2011 Oct 4		DSP Indian Ocean	1436.12 35773 x 35800 x 6.1 GEO 69.6E
2012 Jan 1		Move to DSP E Hem?	1436.12 35763 x 35801 x 6.4 GEO 103.8E

Shiyan

 2004-046A

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Shiyan-2 was launched by CZ-2C from Xichang. The 300 kg remote sensing satellite was developed by DFH Satellite Co. It is also known as Qianshao 1,

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A large piece of debris (2004-046G) was tracked in a 662 x 697 km orbit in Dec 2004 but not subsequently; this may have been an erroneous cataloging.

Shiyan 2 was a scientific experimental microsatellite, 300kg, based on platform CAST2000, developed by DFHSat. It has high precision control systems and rapid slewing capability. The satellite validated the the bus technology for scientific experimental small satellites; 6 new technologies were demonstrated: high precision control, integrated satellite systems, high efficiency battery, multi-function structure, etc It also tested infrared sensors, possibly for the SJ-11 series, and according to Lissov (nasaspaceflight.com) a signals intelligence payload.

On 2007 Jul 4 the satellite's orbit changed slightly, lowering by 2 km. This may represent an end of life maneuver. However it was reported to be operating in 2010.

SY-2
Date	Time	Event	Orbit
2004 Nov 18	1045	Launch by CZ-2C
	1058	Stage 2 sep
2004 Nov 19			694 x 711 x 98.2
2007 Jun 14			98.83 694 x 710 x 98.2
2007 Jul 4			98.83 695 x 709 x 98.2
		Orbit adjust	98.80 695 x 707 x 98.2
2007 Jul 7			98.80 694 x 708 x 98.2
2007 Nov 29			98.80 693 x 709 x 98.2

WGS-4

 2012-003A

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Payload ops by Army Stratcom. Also designated USA-233.

WGS 4
Date	Time	Event	Orbit
2012 Jan 20	0038:00	Launch by Delta	CC SLC37B
		T+1:34 SRM burnout
		T+1:40 GEM 1,2 sep
		T+1:42 GEM 3,4 sep
		T+3:27 Fairing sep
		T+4:06 MECO
		T+4:12 Stage 1 sep
		T+4:25 St 2 ignition 976s
	0058	T+20:43 SECO-1	185 x 6880 x 25.59
		T+28:27 St 2 restart 188s
		T+31:36 SECO-2
	0118	T+40:42 St 2 sep	439 x 66872 x 24
		St 2 depletion	1251.86 474 x 63722 x 23.9
			1332.4 503 x 66960 x 23.9 (UN)