Cheerleading Secrets

https://welib.org/md5/960ee5425208d4b44ba1d7f17079c963

America's Space Sentinels: The History of the DSP and SBIRS Satellite Systems

 https://welib.org/md5/701c46740de21d47767f32c85472713c

May 26,2000

 https://web.archive.org/web/20080504034957/http://digest-archive.degrassi.ca/DD97.htm

Aviation Week: February 17,2014

 https://welib.org/md5/997d5999b2dabe48725db583d5e46e77

Progress M-10M

 2011-017A

---

Flight 42P, 11F615A61 No. 410. Launch mass 7286 kg. Undocking mass 5743 kg. Cargo mass 2645 kg including BTLS payload 96 kg.

M10M
Date	Time	Event	Orbit
2011 Apr 27	1305:21	Launch by Soyuz-U Yu15000-116	KB LC1
	1309	Blok A sep
	1314	Blok I MECO
	1314:10	Blok I sep	88.66 189 x 227 x 51.6
	1644:15	DV 46s 17.2m/s
	1739:13	DV 25s 9.8m/s	89.43 228 x 264 x 51.6
2011 Apr 28	1406:53	DV3 29s 2m/s	89.44 231 x 261 x 51.6
2011 Apr 29
	1406	Begin flyaround at 400m
	1413	Stationkeep at 170m
	1418	Begin final approach	91.47 344 x 348 x 51.65
	1428:44	Docked with Pirs
2011 Sep 20		Fuel transfer, 170 kg fuel 102 kg ox
2011 Oct 29	0903:38	Undocking	375 x 404 x 51.6
	0906:45	DPO Sep burn 0.7 m/s 15s
	1210:33	SKD Deorbit 99.7 m/s 3:10	376 x 413 x 51.6 (NK)
	1213:43	DO cutoff
	1248?	Entry	52? x 386 x 51.6
	1254?	Breakup
	1300	Debris impact Pacific 50 11S 136 20W

SES-3

 2011-035A

---

 Launch 2011 on Proton dual with Kazsat-2. SES World Skies/Princeton (former Americom) satellite. Orbital Star-2.4E bus. Mass 3170 kg launch, 3112 kg separated.

Procured on orbit by SESSL, then transferred to SESWS. Former AMC 5R. Carried C and Ku band payload as well as military Ka-band.

Upper stage Briz-M no. 99519

After initial checkout at 77W in Jul-Aug 2011, SES-3 was moved to 98W from Sep 19 to Dec 14. Here it provided an SES in-orbit spare and to bring into use the EchoStar USATSAT-70V Ka-band service until Echostar 17 entered service in Oct 2012.

It was then drifted around the planet to 108E, where it stayed from Feb 2012 to 2012 Jul under the control of SES/Gibraltar. Its next location was at 103W starting at 2012 Sep 26.

SES-3
Date	Time	Event	Orbit
2011 Jul 15	2316:10	Launch by Proton-M 93518
		T+2:00 St 1 sep
		T+5:25 St 2 sep
		T+5:50 Fairing sep
	2325:45	T+9:35 St 3 sep	-477 x 189 x 48.0
	2327:59	T+11:49 MES-1
	2333:17	T+17:07 MECO-1	133 x 273 x 48.0
2011 Jul 16
	0022:18	T+1:06:08 MES-2
	0039:29	T+1:23:19 MECO-2	240 x 5000 x 46.8
	0243:28	T+3:27:18 MES-3
	0258:52	T+3:42:42 MECO-3
	0259:52	T+3:43:42 APT sep	341 x 25235 x 45.7
	0301:19	T+3:45:09 MES-4
	0303:16	T+3:47:06 MECO-4	380 x 35289 x 45.6
	0659:14	T+7:43:04 MES-5
	0704:33	T+7:48:23 MECO-5
	0717:10	T+8:01:00 SES-3 sep	3690 x 35786 x 24.7
	0812:00	T+8:55:50 PS Adapter sep
	0822:33	T+9:06:23 MES-6
	0827:08	T+9:10:58 MECO-6
	0840:10	T+9:24:00 Kazsat-2 sep
	1046	T+11:30 SOZ sep burn
	1151	T+12:35 SOZ depletion burn
2011 Jul 17			698.76 3683 x 35728 x 24.7
2011 Jul 18			797.14 8447 x 35753 x 14.8
2011 Jul 18			1036.21 19325 x 35758 x 5.3
2011 Jul 22			1240.43 27960 x 35767 x 2.0
2011 Jul 25			1431.70 35619 x 35781 x 0.1 GEO 79.5W+1.1E/d
2011 Jul 29		1436.10 35784 x 35788 x 0.1 GEO 77.2W+0.0W/d
2011 Aug 26			1435.95 35775 x 35791 x 0.1 GEO 77.2W
2011 Aug 26		Move out
2011 Sep 1			1439.41 35849 x 35853 x 0.1 GEO 83.6W+0.8W/d
2011 Sep 19		Arrive 98W
2011 Sep 21			1436.07 35773 x 35798 x 0.0 GEO 98.9W
2011 Dec 11			1436.09 35774 x 35798 x 0.0 GEO 98.8W
2011 Dec 14		Move out
2012 Feb 1			1420.86 35398 x 35577 x 0.0 GEO 95.2E+3.8E/d
2012 Feb 6		Arrive 108E
2012 Feb 7			1436.07 35775 x 35796 x 0.0 GEO 108.3E
2012 Jun 28			1436.11 35785 x 35788 x 0.1 GEO 108.2E
2012 Jul 5		Move out
2012 Aug 28			1446.34 35981 x 35991 x 0.0 GEO 40.3W+2.5W/d
2012 Sep 26		Move in	1436.13 35777x 35796 x 0.0 GEO 103.1W
2012 Nov 7			1436.09 35776 x 35796 x 0.0 GEO 103.1W

The New Yorker: October 7,2013

 https://welib.org/md5/94f37700f6d82086837f2c1708e17ff3

All the wrong moves [bk. 2] : a Fab life novel

 https://welib.org/md5/ab7d79f3b244dc3623b372644d8cdae0

Kosmos 2479

 2012-012A

---

Oko-1 71Kh6 No. 7128 with a modified sensor system. Launch by Proton-K No. 410-18 with DM-2 No. 117L.

Kosmos-2479
Date	Time	Event	Orbit
2012 Mar 30	0549	Launch by Proton-K	KB LC81/24
	0551	T+2:06 St 1 sep
		T+3:03 GO sep
		T+5:30 St 2 sep
	0558	T+9:34 St 3 MECO
	0559:16	T+9:44 Stage 3 sep
	0702:58	T+1:13? DM2 MES-1 422s
	0710:00	T+1:20? DM2 MECO-1
	1223:10	T+6:33? SOZ	219 x 35910 x 49.3
	1223:10	T+6:33 MES-2 193s
	1226:23	T+6:37 MECO-2
	1226:38	DM sep	1442.48 35898 x 35924 x 2.3 GEO 89.6E+1.5W/d
2012 Apr 10			1436.79 35697 x 35902 x 2.3 GEO 80.1E+0.2W/d
2012 Apr 16			1436.06 35690 x 35881 x 2.2 GEO 80.3E
2012 Jul 18		Move out from 79.5E
2012 Jul 22			1432.05 35681 x 35733 x 2.1 GEO 83.5E+1.0E/d
2012 Oct 21		Move in at 166E
2012 Nov 7			1436.08 35780 x 35791 x 1.8 GEO 165.6E

Tacsat 4

 2011-052A

---

Prototype standardized satellite platform with 10-channel UHF telecom payload for data relay, friendly forces tracking and mobile comms using handheld radios.

Box-cone + 2 panels + 3.7m dish

Mass 460 kg.

4-hour elliptical orbit, 8000 km apogee. Minotaur IV launch with 92-inch fairing and Star 48 motor. Led by USN/NRL with ONR funding. Spacecraft bus was built by APL and NRL.

Star 48V mass 2164 kg full 138 kg empty. Assume extra 500 kg stage hardware as a fiducial value. Isp 292.1 over 84.1s with 460 kg s/c: dV = ln 3124 / 1098 * 9.807 * 292.1 = 2994 m/s

Tacsat 4
Date	Time	Event	Orbit
2011 Sep 27	1549	Launch by Minotaur 4/Star 48	KLC
		T+00:57 Stage 1 sep
		T+1:55 Stage 2 burnout
		T+2:05 St 2 sep, St 3 burn
		T+2:17 Fairing sep
	1552	T+3:18 SR120 St 3 burnout
	1611	T+22:55 Stage 3 sep	-3380? x 1000? x 64
	1612	T+23:06 Star 48 burn
	1613	T+24:28 Star 48 burnout	189 x 11833 x 63.4
	1616	T+27:48 Star 48 sep
	1837?	Perigee raise burn	230.98 340 x 11843 x 63.5
	2220?	Perigee raise	234.44 597 x 11835 x 63.6
2011 Sep 28	0930?	Perigee raise	235.15 647 x 11836 x 63.6

Payload:

• COTM Comms on the Move (COMMx), with UHF legacy and MUOS capability.

• BFT Blue Force Tracking, UHF relay

• SCP SCP-3 Satellite Comms Payload, Data-X Data exfiltration experiment (ONR/Praxis/), IP based USN buoy comms with ODTML Ocean Data Telemetry Microsat Link (ONR/)

Chinasat 12

 2012-067A

---

\uni{ 中星十二号卫星}{ }

ZX-12 for China Satcom, also branded as SupremeSAT-1 for SupremeSAT Pvt Ltd. of Sri Lanka. Originally built as Apstar 7B. TAS SB4000C2 with 24 C and 23 Ku. 5054 kg.

ZX12
Date	Time	Event	Orbit
2012 Nov 27	1013:03	Launch by CZ-3B	XSC LC2
		T+5:44 St 2 sep
	1023	T+10:20 St 3 MECO-1
	1034	T+21:04 MES-2
	1037?	T+24:04? MECO-2
	1038?	T+25:42? St 3 sep
2012 Nov 28			932.08 228 x 50231 x 26.7
2012 Dec 10			1435.92 35758 x 35807 x 0.0 GEO 81.5E
2012 Dec 15			1436.09 35779 x 35793 x 0.0 GEO 81.6E
2012 Dec 28		Move out
2013 Jan 15		Move in at 51E
2013 Feb 25			1436.11 35775 x 35797 x 0.0 GEO 51.5E

Meteosat 10

 2012-035B

---

Meteosat-10 (MSG-3) was launched in 2012. Built by Thales Alenia.

MSG 3
Date	Time	Event	Orbit
2012 Jul 5	2136	Launch by Ariane 5 VA207	CSG ELA3
		T+2:15 EAP sep
		T+3:10 Fairing sep
		T+8:52 EPC burnout
	2145	T+8:57 EPC sep	-1064 x 172 x 7.2
	2145	T+9:02 ESC-A burn
	2200	T+24:51 ESC-A burnout
	2203	T+27:28 Echostar sep
	2207	T+31:10 Sylda sep
	2210	T+34:04 MSG sep
		T+48:55 ESC-A passivation
2012 Jul 6	0130?	Spinup 55rpm
2012 Jul 7	1030?	LAM-1
2012 Jul 8	1130?	LAM-2
2012 Jul 10	1230?	LAM-3
2012 Jul 11	1130?	LAM-4
2012 Jul 13	0406	Cooler and SEVIRI baffle covers ejected
2013 May 1			1435.98 35776 x 357912 x 1.2 GEO 0.2E

ATV-2 (Johannes Kepler)

 2011-007A

---

Mass 20061 kg launch 10854 kg dry. Size 10.3m long 4.5m dia 22.3m span. 19712 kg ATV mass, 349 kg SDM adapter.

7100 kg cargo - 1600 of dry cargo incl Geoflow, food, equipment, 3 physiology experiment camera. 430 kg added at last minute. 4100 kg reboost prop 850 kg for FGB prop, 100 kg of air/O2/N2.

4 kg reentry vehicle to record reentry of ATV-2.

ATV-2
Date	Time	Event	Orbit
2011 Feb 16	2151:02	Launch by Ariane 5ES-ATV L544 V200
	2150:55	T-0:07 Ignition
		T+2:15 EAP sep
		T+3:22 Fairing sep
	2159:47	T+8:45 EPC MECO	-1274 x 139 x 51.2
	2159:53	T+8:51 EPC sep
	2159:59	T+8:57 EPS burn 1
	2206?	EPC reentry over circa 28W 33N
	2208:12	T+17:10 EPS MECO-1	137 x 258
			142 x 256 x 51.61
	2250:23	T+59:21 EPS MES-2
	2250:50	T+59:48 EPS MECO-2	263 x 271
	2254:49	T+1:03:47 ATV sep
		T+1:03:57 avoidance maneuver
2011 Feb 17
	0015:07	T+2:24:05 EPS MES-3 deorbit
	0035?	T+2:44:32 MECO (dubious?)
	0030?	EPS entry over S Pacific
2011 Feb 24
		Begin approach to ISS
	1341	At 3.5 km
	1534	At 19m
	1537	Resume approach
	1542	At 11m
	1559:03	Docking with Zvezda
	1608:30	Hard dock
2011 Mar 18	0600	OCS burn 14:43 2.2m/s 290 kg, ISS orbit raise
2011 Apr 2	0600	ISS debris avoidance, orbit raise 882s
2011 May 5	1120	OCS burn 4:03 0.6m/s boost
2011 Jun 2	2230	OCS burn 16:51 2.5m/s, 4.3 km orbit raise, 366 kg prop
2011 Jun 12	1415	OCS burn 36:06 5.2m/s 9.2 km gain
	1820	OCS burn 40:12 5.8m/s 10.1 km
2011 Jun 15	1555	OCS burn 39:40 5.84m/s 10.2 km
2011 Jun 17	1621	OCS burn 26:53 3.96m/s 6.9 km
2011 Jun 19	1530	HC
2011 Jun 20	1446:30	Undock
	1447	Sep burn
	1830	Debris avoidance burn 1.5m/s	91.99 359 x 384 x 51.6
2011 Jun 21
	1706:49	Orbit lower burn 609s Lower peri	220 x 380 x 51.6
	1716:58	burn cutoff
	2004:32	Deorbit burn 849s 66.81m/s	0 x
	2018:41	burn cutoff
	2024	Begin tumble
	2025	REBR recording
	2037	REBR jettison
	2041:39	LOS at 80 km
	2048:40	Impact 48.63S 147.02E

Apstar 7

 2012-013A

---

Thales Alenia Spacebus 4000C2, ITAR-free, to replace APstar 2R at 76.5E.

Launch 2012 by CZ-3B/E.

APT Satellite Holdings Ltd, Hong Kong is the operator.

In Chinese, the satellite is "Yatai qi hao" (Asia Pacific No. 7)

Apstar 7
Date	Time	Event	Orbit
2012 Mar 31	1027	Launch by CZ3BE	XSC LC2
		T+5:44 St 2 sep
	1037	T+10:20 St 3 MECO-1
	1048	T+21:04 MES-2
	1051?	T+24:04? MECO-2
	1052?	T+25:42 St 3 sep	187 x 35804 x 26.1
2012 Apr 1			929.93 238 x 50123 x 27.4
2012 Apr 22			1436.09 35783 x 35789 x 0.1 GEO 81.5E
2012 May 6		Depart 81.5E	1439.97 35861 x 35862 x 0.1 GEO 80E+1.0W/d
2012 May 15		Arrive 76.5E, on station
2012 May 27			1436.09 35784 x 35788 x 0.0 GEO 76.6E

C/NOFS

 2008-017A

---

P00-3 PL-602 Comm/Nav Outage Forecasting System. CNOFS will be built by Spectrum Astro for launch and on-orbit delivery on Pegasus in Feb 2004. Low inclination orbit from KMR. Will develop models to map equatorial ionosphere and forecast ionos scintillation.

Orbit 375 x 720 x 13. Delayed to early 2008 following damage to solar panels 2.8m long 1m dia, modified SA-200B. Operation by AFRL and SMC/TE. Mass 360 kg Hexagonal cylinder + 6x 10m booms.

CINDI is Coupled Ion Neutral Dynamic Investigation and consists of the IVM and NWM instruments.

C/NOFS
Date	Time	Event	Orbit
2008 Apr 16	1604:00	L-1011 T/O from KMR
	1702:48	Drop
		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
		T+9:09 St 3 burn
	1712?	T+10:16 St 3 burnout
	1713?	T+11:16 Stage 3 sep
2008 Apr 25			97.29 405 x 852 x 13.0
2013 Jun 3		In safemode

Payload:

• PLP Planar Langmuir Probe, plasma density (AFRL-VS/Hunton)

• VEFI Vector electric field instrument (GSFC/Pfaff)

• CINDI

  • IVM Ion velocity meter (SMEX MO) (UTD/Heelis)

  • NWM Neutral Wind Meter, in situ composition and flow (UTD/Earle)

• CORISS C/NOFS Occultation Receiver for Ionospheric Sensing and Specification, gives electron density profile from GPS satellite rising and setting. (AeCorp/Straus)

• CERTO Coherent Electromagnetic Radio Tomography, ionospheric radio beacons (NRL/Bernhardt)

Rascom-QAF 1

 2007-063A

---

Alcatel fixed satellite system for Regional African Sat Comm Org, owned by RascomStarQAF (RSQ) of Port-Louis, Mauritius (Republique de Maurice); subsidiary of Rascom in Abidjan, Ivory Coast. Rascom-BOT is Build-Operate-Transfer. Thales-Alenia-Space Spacebus 4000B3 satellite. Satellite control station in Garyan, Libya. Mission center in Douala, Cameroun Located at 2.85E. Voice, data, internet to Africa.

Mass 3200 kg. 3160 kg launch, 1395 kg dry, 3.75 x 2.38 x 1.80m bus with 31.8m span.

Flight V180, L530

A propulsion system failure stalled the craft in GTO for a couple of weeks. Backup propulsion thrusters were used.

Rascom 1
Date	Time	Event	Orbit
2007 Dec 21	2141:55	Launch by Ariane 5GS L530	CSG ELA3
		T+2:20 EAP sep
		T+3:20 Fairing sep
	2151:37	T+9:42 EPC MECO	30 x 1730 x 7.3
	2151:43	T+9:48 EPC sep
	2151:50	T+9:55 EPS burn
	2208:25	T+26:30 EPS MECO
	2210:25	T+28:30 RASCOM sep
	2212:35	T+30:40 Sylda 5 sep
	2214:25	T+32:30 Horizons 2 sep
		T+40:30 end of flight V180
2008 Jan 1			637.79 587 x 35744 x 5.48
2008 Jan 1		LAM-1
2008 Jan		18 RCS burns
2008 Jan 28			1431.11 35673 x 35704 x 0.1 GEO 1.2E+1.2E/d
2008 Feb 2			1436.14 35777 x 35797 x 0.1 GEO 2.8E+0.02W/d
2008 Feb 10		On station at 2.8E
2008 Jul 14			1436.09 35782 x 35790 x 0.05 GEO 2.8E
2010 Oct 7			1436.11 35770 x 35802 x 0.0 GEO 2.9E
2010 Oct 8		Orbit raise	1454.01 36131 x 36141 x 0.0

Booklist: September 1,2013

 https://welib.org/md5/4f5a69c8235f1ced4195b3ad6b603bd2

Chandra X-ray Observatory

 1999-040B

---

The Advanced X-Ray Astrophysics Facility (AXAF) is a NASA Great Observatory. The AXAF mission was split in the early 1990s into AXAF-I (Imaging) and AXAF-S (Spectroscopic), but AXAF-S was later cancelled. The 5563 kg Chandra (AXAF) (formerly AXAF-I) spacecraft is a 10-meter focal length subarcsecond resolution X-ray telescope with both imaging and spectroscopic capability. It is 14.0 m long and 19.5m span across the solar arrays. Prime contractor was TRW/Redondo Beach; lead center was NASA-MSFC with operations and science center at the joint SAO/MIT AXAF Science Center in Cambridge, Massachusetts.

The spacecraft consists of the Spacecraft module, containing the Integral Propulsion System, the solar panels, and the aperture door; the HRMA; the optical bench; and the ISIM, Integrated Science Instrument Module with the science instruments.

The IPS uses MON-3 (0.97 N2O4 and 0.03 NO) oxidizer and N2H4 (hydrazine) for its bipropellant main thrusters. The RCS thrusters in the IPS use monopropellant N2H4. There is also a monopropellant hydrazine MUPS momentum unloading propulsion system which is used to unload momentum from the attitude control gyroscopes and uses 1N thrusters.

After deployment from the STS, the IUS burns at MET 9:42, and the SRM-2 burns at 9:46, placing AXAF in a 241 x 59923 km orbit. The solar panels are deployed. The IPS-1 burn is at MET 28:55 and raises to 241 x 140000 km; the IPS-2 burn is at MET 58:11 and raises orbit to 10000 x 140000 km. The IPS has 4 TR-308 ACLAE (Advanced Columbium Liquid Apogee Engine) liquid engines derived from TRW's TR-306 DM-LAE. The RCS are 89N monoprop hydrazine.

Launch mass is 5563 kg. After IPS-1, it's 5471 kg; after IPS-2, 5271 kg; after IPS-3, 4888 kg; after IPS-4, 4685 kg; after IPS-5, 4653 kg.

The IPS-4 burn was scrubbed because of performance concerns about LAE-3; the burn was replanned for LAE-2/LAE-4.

Mass at deploy: 19427 kg, post IUS1 10527, pre IUS2 9363, post IUS2 6642

AXAF
Date	Time	Event	Orbit
1970		HEAO LOXT (1.2m) telescope proposal
1973		HEAO descoped
1976		SAO 1.2m telescope proposal
1977		MSFC/SAO phase A study
1980		AXAF SWG report projects start in FY83
1982		Field committee makes AXAF top priority
1985		Phase B studies
1985		TMA test mirror
1988		AXAF new start, TRW prime
1991		AXAF science center at SAP
1991		Early tests of outer mirror pair
1992		Descoped to AXAF-I and AXAF-S
1994		AXAF-S cancelled
1995 Jul		Grinding and polishing completed at HDOS
1996 Feb		Mirrors coated at Santa Rosa
1996 Feb		Mirrors to Kodak, assembly
1997 Dec		XRCF HRMA tests begin
1997 Mar		SC structure complete
1997 May		XRCF instrument tests complete
1997 Jun		Ship HRMA to TRW
1997 Oct		SIM due at TRW
1997 Nov		Delivery delay announced
1998 Feb		ETE-1
1998 Mar 12		SA install, assembly complete
1999 Feb 4		Chandra delivery to KSC
1999 Mar 8		CTU and IU reinstalled
1999 Mar 23s		Solar array install
1999 Apr 5s		Hydr/N2O4 fuelling
1999 Jun 3		Mate to IUS-27
1999 Jun 24		Transfer to LC39B
1999 Jun 27		Install in OV-102
1999 Jul 20	0426	Attempt 1, scrub T-7 for leak
1999 Jul 22	0428	Attempt 2, wx
1999 Jul 23	0431:00.04	Launch by Shuttle	KSC LC39B
	0439:33	MECO
	0514:25	OMS-2
	0615	Power up
	1147:26	Chandra deploy from OV-102	90.10 268 x 290 x 28.5
	1244:30	LGA 1 deploy failed
	1247:26	D+1:00 IUS burn 1, 125s
	1247:25	LGA-1 deployed
	1249:31	IUS SRM-1 cutoff
	1251	IUS SRM-1 sep	257.63 226 x 13841 x 28.5
1999 Jul 23	1251:53	IUS burn 2	1456.26 330 x 72030 x 28.5
	1253:44	SRM-2 cutoff
	1322	Solar array deploy
	1348:55	SRM-2 sep (CXO mass 5563 kg)	1487.26 315 x 73240 x 28.5
1999 Jul 25	0111:27	IPS-1 (LAE-1/3) 5:00
	0116:27	IPS-1 end	1481.41 1179 x 72158 x 28.4
1999 Jul 26	0147:44	IPS-2 (LAE-1/3) 11:13
	0158:57	IPS-2 cutoff (CXO mass 5470 kg )	1537.59 3505 x 71995 x 28.5
1999 Jul 29			3449 x 72052 x 28.5 (OCC)
1999 Jul 31	2232:50	IPS-3 (LAE-1/3) (21:31)
	2254:21	IPS-3 cutoff	3591.10 3479 x 139125 x 28.5
1999 Aug 1			3480 x 139124 x 28.5 (DSN)
1999 Aug 4	1634:08	IPS-4 (5:00) (LAE-2/4)	5657 x 139141 x 28.5
	1639:08	IPS-4 cutoff	3557.44 5657 x 139141 x 28.5
1999 Aug 7	0538:31	IPS-5 (7:44) (LAE-2/4)
	0546:15	IPS-5 complete	3807.66 9856 x 138932 x 28.5
1999 Aug 8	2243	ACIS Door open
1999 Aug 13		Aft contam cover open
1999 Aug 13	1600	SSD open
1999 Aug 13		First image
1999 Aug 17	2017	Safemode
1999 Nov 25			3808.5 10157 x 138663 x 28.8
2010 Aug 31			3809.3 7600 x 141235 x 67.5

Payload:

• HRMA High Res Mirror Assembly, 4 nested Wolter I

• HRC High Resolution Camera (Murray)

• ACIS AXAF CCD Imaging Spectrometer (Garmire)

• LETGS Low Energy Transmission Grating Spec (Brinkman)

• HETGS High Energy Transmission Grating Spec (Canizares)

• ACA Aspect Camera Assembly

• IPS Integral Propulsion System

Tianlian 2

 2011-032A

---

Located at 177E until summer 2013, then moved to 171 E.

TL1B
Date	Time	Event	Orbit
2011 Jul 11	1541	Launch by CZ-3C	XSC
		T+2:07? Booster sep
		T+2:27? St 1 sep
		T+3:52? Fairing sep
		T+5:32? St 2 sep
		T+5:32? St 3 MES-1
	1551?	T+10:31? MECO-1	220? x 450? x 28.5?
	1602?	T+21:21? MES-2
	1605?	T+24:20? MECO-2	759.86 194 x 42215 x 18.0
	1605	Perigee
	1607?	Stage 3 sep
2011 Jul 19			1436.13 35781 x 35793 x 1.1 GEO 176.8E
2013 Jul 22			1436.04 35758 x 35812 x 0.1 GEO 177.0E
2013 Jul 24		move out
2013 Jul 29		Move in	1436.16 35777 x 35798 x 0.1 GEO 171.0E

Aviation Week: April 25-May 2,2011

 https://welib.org/md5/0b0a73641238e5dfc7c361dc9b72457f