USA-161

 2001-044A

---

Titan 4B with a 66' fairing from SLC-4E. CRYSTAL replacing USA-116. It was launched to a 1300 LTDN orbit.

It was stored in a high perigee orbit from 2002 to 2006, when its orbit was synchronized with that of USA 186.

In 2011 it was moved to a lower circular orbit, a new regime for this class of satellite. It was deorbited in late 2014.

USA
Date	Time	Event	Orbit
2001 Oct 5	2121:01	Launch by Titan 4B-34	V SLC4E
		Stage 1 burn
		SRMU sep
	2126	Fairing sep
	2127	Stage 1 sep
	2127	Stage 2 burn
	2130	Stage 2 MECO
	2130:33	T+9:32 Stage 2 sep
			96.7 202 x 1041 x 97.8 (UN)
2002 Jan		Change orbit	405 x 857 x 97.9
2005 Mar 20			407 x 890 x 97.9
2006 Jan 10			405 x 888 x 97.9
2006 Mar 16		Apogee raise
2006 Mar 27			309 x 985 x 98.9
2010 Oct 15			97.47 309 x 965 x 97.9
2011 Aug 6			96.84 302 x 912 x 97.9
2011 Sep		Lower orbit
2011 Sep 29			95.06 265 x 777 x 97.8
2012 May 14			92.19 362 x 401 x 97.5
2012 Aug 16			92.23 358 x 409 x 97.1
2013 Aug 8			92.34 385 x 392 x 97.0
2014 Nov 20?		Deorbited

Intelsat 603

 1990-021A

---

Intelsat 603 was the first single-payload launch aboard a Commercial Titan 3. Martin Marietta failed to rewire the logic to take into account the fact that no dual-launch `top' satellite was present; the Intelsat and its Orbus 21S perigee kick motor remained attached to the Titan core second stage, waiting in vain for the non-existent top satellite to separate. Controllers commanded the Intelsat to separate from its kick motor, and used the liquid apogee motor to raise the satellite's orbit and avoid an early reentry. The Titan stage reentered on Mar 28 at 1420 UTC, over the Pacific southeast of Taiwan.

In 2003 usage of IS-603 was transferred to New Skies (although it's not clear if ownership changed). An on orbit operations licence was given to Intelsat Global/UK by the UK government on 2010 Nov 17; on 2013 Jan 8 the satellite's control was transferred to Argentina to provide ARSAT service at 81W. 

Intelsat VI~F-3
Date	Time	Event	Orbit
1990 Mar 14	1152:31	Launch by Titan 3	CC
	1154:20	T+1:49 Stage 1 ignition
	1154:28	T+1:57 SRM sep
	1156:58	T+4:27 Stage 2 ignition, St 1 sep
	1157:09	T+4:38 Fairing sep
	1200:37	T+8:06 Stage 2 cutoff
1990 Mar 14		Titan stage 2 MECO
1990 Mar 14	1217	Stage 2 failed to sep from I603/Orbus-21	89.87 169 x 366 x 28.6
1990 Mar 14		I603 sep from Titan/Orbus 21S	89.75 169 x 355 x 28.6
1990 Mar 15		Begin LAM orbit raise
1990 Mar 16			91.13 262 x 397 x 28.3
1990 Mar 18			92.32 375 x 401 x 28.3
1990 Mar 26	1200		93.98 372 x 565 x 28.3 from 92.92 373 x 399 x 28.3
1990 Mar 29	2100		95.81 544 x 570 x 28.3 from 93.98 372 x 565 x 28.3
1991 Mar 18			95.78 546 x 565 x 28.3
1992 Jan 31			95.82 546 x 569 x 28.3
1992 Mar 9			95.79 545 x 568 x 28.3
1992 Mar 10		orb trim	95.82 545 x 571 x 28.3
1992 May 7			95.83 550 x 567 x 28.3
1992 May 8	0344	Orbit lower OL1 burn	93.65 355 x 570 x 28.32
1992 May 8	1356s	Orbit lower OL2 burn	92.04 344 x 414 x 28.31
1992 May 8	1835	Orbit lower OL3 burn	91.56 355 x 366 x28.31
1992 May 9	0930s	Orbit CIRC	91.70 365 x 369 x 28.31
1992 May 11	1049	Spacing burn	91.60 355 x 370 x 28.31
1992 May 11	2318	OV-105 contact Intelsat, fail to grapple
1992 May 13		STS-49 retrieval
	2359:31	Capture of Intelsat VI F-3	91.60 355 x 370 x 28.31
1992 May 14	0147:41	RMS grapple CB/Intelsat
	0300	RMS berth Intelsat
	0300	RMS ungrapple Intelsat
	0453:22	Intelsat deploy
	1723:52s	PKM burn
1992 May 14	1725	Orbus 21S fired
1992 May 14	1851	Orbus 21S sep	1548.00 776 x 75123 x 17.7 GEO 42.2E+26.1W
1992 May 14	1851?	Docking adapter/capture bar sep
1992 May 14			1548.0 776 x 75122 x 17.68
1992 May 15	0601	LAM0 2-min burn	1442.76 347 x 71486 x 19.3 GEO 53.2E+1.6W
1992 May 17	0601	LAM1 18.3 min burn	1566.74 5076 x 71537 x ?
1992 May 18	0816	LAM2 11.5min burn	1676.88 9171 x 71582 x 7.3
1992 May 18			1670.90 9152 x 71379 x 7.53
1992 May 18			1677.60 9169 x 71624 x 7.28
1992 May 19	1200	LAM3 31.8 min burn	2298.95 31156 x 71489 x ?
1992 May 21	0228	LAM4 3.8 min burn	2432.65 35582 x 71495 x ?
1992 May 21	2204	LAM5 21 min burn	1426.09 35584 x 35997 x 1?
1992 May 22	0000		1435.71 35617 x 35945 x 0.63
1992 May 22		Deploy antennas
1992 May 22			1435.82 35617 x 35945 x 0.6 GEO 36.8W
1992 May 25			1436.24 35580 x 35998 x 0.6 GEO 37.3W
1992 May 31			1436.33 35578 x 36003 x 0.6 GEO 37.7W
1992 Jul 5			1436.10 35584 x 35988 x 0.5 GEO 37.7W
1992 Jul 17		AOR, replaced 506	1436.11 35774 x 35799 x 0.5 GEO 33.5W
1992 Aug 1			1436.15 35777 x 35798 x 0.4 GEO 33.6W
1994 Mar 13			1436.15 35785 x 35789 x 0.0 GEO 34.6W
1997 Jan 1			1436.13 35780 x 35794 x 0.0 GEO 34.5W
1997 Oct 26			1436.08 35778 x 35794 x 0.0 GEO 34.4W
1997 Nov		Move to 24W
1997 Nov 7			1436.03 35776 x 35793 x 0.0 GEO 24.5W
1999 Jun 16			1436.13 35776 x 35798 x 0.0 GEO 24.5W
2002 Aug 2		Mv out 25W
2002 Aug 9		mv in 20W
2006 Jul 30			1436.09 35779 x 35793 x 3.7 GEO 20.0W
2010 Mar 5			1436.12 35773 x 35801 x 7.0 GEO 20.0W
2010 Mar 18		Mv out 0.4E/d
2010 May 20		On station 11.5E
2013 Jan 10		GEO 11.5E
2013 Jan 10		Move out
2013 May 2			1438.38 35820 x 35842 x 9.5 GEO 48.6W+0.6W/d
2013 Jul 4		Move in at 80.6W	1436.07 35771 x 35801 x 9.6 GEO 80.4W
2015 Jan 5			1436.08 35765 x 35807 x 10.5 GEO 80.3W

WMAP

 2001-027A

---

The Microwave Anisotropy Probe is a MIDEX mission launched by Delta 7425-10 to the Earth-Sun L2 point. 3 month transit to L2 with lunar flybys.

The satellite observes from 22 to 90 GHz with a resolution of 13-55 arcmin. Mass 837 kg full, incuding 72 kg prop.

Box 3.8 h 2.0w? 5.0 span with a circular deployable solar array/thermal shield panel. GSFC mission and GSFC-built spacecraft. The instrument was built in collaboration with Princeton.

A slight SES-1 overburn was required to achieve the desired parking orbit.

In Feb 2003 MAP was renamed WMAP, the Wilkinson Microwave Anisotropy Probe, after David T. Wilkinson (1935-2002), one of the leaders of the COBE and MAP satellite programs. The WMAP team announced their preliminary results at the same time, with values of the Hubble Constant, the age of the universe, the breakdown of baryonic matter, dark matter and dark energy, and the first measurement of the time of reionization.

Close passes (less than 10 million km) to the Earth are predicted in Apr 2025 and Nov 2039.

MAP
Date	Time	Event	Orbit
2001 Jun 30	1946:46	Launch by Delta 7425-10	CC SLC17B
		T+1:03 SRM 1-4 burnout
		T+1:08 SRM 1-4 sep 22 km	-6320 x 28 ?
		T+4:24 MECO
		T+4:30 Stage 1 sep
		T+4:37 SES-1 113 km	-4470 x 160 ?
		T+4:58 Fairing sep 125 km 5.4 km/s	-4400 x 160 ?
		T+5:48	-4189 x 159
		T+7:52	-3426 x 167
		T+10:16	-1767 x 170
		T+10:30	-1482 x 170
		T+10:58	-926 x 169
		T+11:08	-741 x 169
		T+11:24	-370 x 169
	1958:29	T+11:43 SECO-1 (7s late)	167 x 204 x 28.75
	2004	Solar array deploy
	2104:29	T+1:17:43 SES-2
	2104:33	T+1:17:47 SECO-2	181 x 308 x 28.8
	2105:26	T+1:18:40 Stage 2 sep
	2108:03	T+1:19:17 TES
	2108:31	T+1:20:45 TECO
	2112:13	T+1:25:27 Yo-yo despin
	2112:18	T+1:25:32 Stage 3 sep	182 x 290991
	2127s	SES-3 depletion	201 x 325 x 26.9
2001 Jun 30			181 x 289038 x 28.7
2001 Jul 1			182 x 292492 x 28.7
	1308	Pass EL1:4
2001 Jul 2		Apogee 1
2001 Jul 3	2214	Pass 96479 km from the Moon
2001 Jul 4	1322	A1 Cal burn, 0.8kg 105s 1.9m/s	1017 x 299475 x 28.7
2001 Jul 7		Delta stage 2 reentry
2001 Jul 8	0433	Perigee 1 burn TCM 1275s 20.2m/s
2001 Jul 8			3100 x 347000 x 28.3
2001 Jul 12	1611	A2 cal burn 40s 0.2m/s at 347891 km
2001 Jul 17	0336	Perigee 2, TCM 176s 2.5m/s at 2955 km
2001 Jul 18			3002 x 354103 x 28.3
2001 Jul 21	1854	A3 cal burn 40s 0.3m/s 356012 km
2001 Jul 25			4720 x 355851 x 28.8
2001 Jul 26	1229	Perigee 3, TCM 546s 7.4m/s 4741km
2001 Jul 27	0430	P3C, TCM 23.8s 0.3m/s at 158306 km
2001 Jul 29	2011	Enter Lunar sphere
2001 Jul 30	1637	Lunar flyby 5279 km
2001 Jul 31	1257	Depart Lunar sphere
2001 Aug 1			182832 x 1178307 x 28.1
2001 Aug 6	1637	MCC1 17.8s 0.1m/s at 755736 km
2001 Aug 9		Begin science data collection
2001 Aug 13			213681 x 1175513 x 28.1
2001 Aug 21			203451 x 1262240 x 29.25
2001 Aug 26		Within 1.2Mkm
2001 Aug 28			239618 x 1333433 x 30.85
2001 Sep 14	1551	MCC2 6.6s 0.04m/s at 1402107 km
2001 Sep 29			270609 x 1468691 x 40.28
2001 Oct 1		Arrive L2
2001 Oct 10			258144 x 1479888 x 42.22
2001 Nov 2			306445 x 1495753 x 38.15
2001 Dec 13			327623 x 1453870 x 30.87
2002 Jan 4			418706 x 1444582 x 32.19
2002 Jan 8			385538 x 1440816 x 32.80
2002 Jan 15			357519 x 1441727 x 33.02
2002 Jan 16	1650	SK1 72s 0.4m/s
2002 May 8	1603	SK2 53s 0.34m/s
2002 Jul 30	1638	SK3 72s 0.5m/s
2002 Nov 5	1921	SK4 96s 0.56m/s
2003 Mar 12	1350	SK5 50s 0.3m/s
2003 Nov 12	1511	SK6 42s 0.25m/s
2004 Mar 9	1524	SK7 112s 0.66m/s
2010 Aug 14		end of science ops
2010 Aug 19		end of calibration ops
2010 Sep 8		To heliocentric orbit , 20 min burn
2010 Sep 30	1540	Departure burn
	1640:55	End burn
2010 Oct 19	2020	Begin final burn
	2124	Complete burn, 27.7m/s
2012 Jan			1.002 x 1.090 AU x 0.15
2013 Jan			1.001 x 1.085 AU x 0.15

Payload:

• Dual Gregorian 1.4 x 1.6m reflectors

• Differential microwave radiometers 22, 30, 40, 60 and 90 GHz

QuickBird

 2001-047A

---

DigitalGlobe's QuickBird made it to orbit safely. Planned orbit was lowered to beat Ikonos' resolution and achieve 0.6m. Mass is 1028 kg.

In 2011 the orbit was boosted to 475 km and then allowed to decay until its 2015 reentry.

QuickBird 2
Date	Time	Event	Orbit
2001 Oct 18	1851:26	Launch by Delta 7320-10C	V SLC2W
		T+1:04 SRM 1-3 out
		T+1:39 SRM 1-3 sep
		T+4:24 MECO
		T+4:32 St 1 sep
		T+4:48 SES-1
		T+4:57 Fairing sep
	1902:08	T+10:42 SECO-1	185 x 472 x 98.1
		T+55:00 SES-2
		T+57:51 SECO-2	463 x 472 x 97.3
	1955:38	T+1:04:12 Delta sep	93.87 461 x 465 x 97.2
	2020?	Delta depletion	90.67 167 x 447 x 108.9
2002 Jan 4			93.47 442 x 447 x 97.2
2002 Jan 5		mv up	93.53 445 x 449 x 97.2
2013 Jan 1			93.54 446 x 448 x 97.2
2011 Mar 24			93.55 446 x 450 x 97.1
2011 Mar 24		Begin boost	93.60 448 x 453 x 97.1
2011 Apr 7		Boost complete	94.16 476 x 479 x 97.3
2013 Mar 14			93.46 442 x 444 x 97.2
2013 Dec 20			92.95 417 x 420 x 97.2
2014 Mar 3			92.72 407 x 408 x 97.1
2015 Jan 27	0030?	Reentered	87.42 141 x 151 x 97

Payload:

• Pan camera, 0.61m res, 16 km swath

• Multispectral camera, 2.5m res

Progress M-27M

 2015-024A

---

Spacecraft 426, mission 59P. Mass 7289 kg including 879 kg prop, refuelling prop 494 kg, 50 kg O2, Rodnik water, 420 kg; cargo in GO 1393 kg. Total cargo 2357 kg.

After launch the vehicle was found spinning rapidly in yaw, with no vehicle telemetry and unresponsive to ground command, although onboard video was downlinked. Early element sets showing a lower than planned orbit were incorrect. The failure was linked to structural resonance issues in the third stage separation sequence, a design error in the Progress/Soyuz-2-1a combination.

Progress M-27M
Date	Time	Event	Orbit
2015 Apr 28	0709	Launch by Soyuz-2-1a	KB LC31?
		T+1:57 Strapons sep
		T+4:36 Blok-A MECO
		T+4:47 Blok-A sep
		T+4:56 KhO sep
		T+4:58 GO sep
	0715	T+8:44 MECO
	0715	T+8:48 Blok-I sep	187 x 259 x 51.7
2015 May 8	0204	Reentry over Pacific

Beidou 1

 2000-069A

---

The Beidou (`Northern Dipper', or `Ursa Major') navigation technology satellite for the People's Liberation Army was launched by CZ-3A in late 2000. It was built by CAST/Beijing. Also referred to as Beidou Daohang Jishu Weixing, 'Ursa Major Navigation Technology Satellite', and Chinasat-32 (in the UN registration). China refers to the first satellites as a 'navigation demonstration system'.

On Nov 6, the apogee motor was fired to place the satellite at GEO 140E, the Chinasat-32 position. Phillip Clark speculated that further Beidou satellites would be launched to Chinasat-31 and -33, at 80E and 110.5E. The satellite was retired in Nov 2011.

The Beidou uses the DFH-3 bus.

Mass of the first satellite was 2315 kg.

Beidou
Date	Time	Event	Orbit
2000 Oct 30	1602	Launch by CZ-3A	XSC LC2
		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
	1612	T+10:19? St 3 MECO-1
		T+20:00? St 3 MES-2
		T+22:00? St 3 MECO-2
	1625?	T+23:40? Stage 3 sep
2000 Oct 30			753.14 194 x 41890 x 25.0
2000 Nov 6	0530?	AKM burn
2000 Nov 7		(?)	753.77 192 x 41922 x 25.0
2000 Nov 9			1436.12 35772 x 35801 x 0.2 GEO 140.0E
2000 Dec 1			1436.05 35773 x 35798 x 0.1 GEO 140.0E
2006 Aug 4			1436.12 35784 x 35790 x 0.0 GEO 140.0E
2010 Sep 20			1436.27 35773 x 35807 x 1.7 GEO 139.0E
2010 Sep		Slow drift W
2010 Oct 17			1436.41 35775 x 35808 x 1.7 GEO 137.7E
2010 Oct 27		Move out
2010 Nov 24		Move in
2010 Nov 30			1436.09 35761 x 35811 x 1.9 GEO 59.2E
2011 Jul 21			1435.95 35771 x 35796 x 2.4 GEO 58.9E

Eros A

 2000-079A

---

The US/Israeli joint venture West Indian Space Ltd. (incorporated in the Cayman Is.) plans to launch 8 Eros satellites based on the Ofeq-3 design. Mass is 250 kg. Launch of Eros-A1 1999 Dec by Start-1 from PL. Eros-A2 2000 Sep. WIS is a venture by IAI/Lod, El-Op/Rehovot, and Core Software Tech/Pasadena. 

Puskoviye Uslogi launched Eros A1 on Start-1. It appears that the DS stage was either not carried or did not separate from the fourth stage.

EROS A has 1.9m resolution. Its final orbit maneuver was on 2012 Apr 24 and it probably stopped operating in the 2012-2013 period.

EROS A1
Date	Time	Event	Orbit
2000 Dec 5	1232	Launch by Start-1	Svobodniy
		T+1:27 St 1 sep
		T+1:27 St 2 burn
		T+1:56 Interstage sep
	1234	T+2:28 St 2 sep
	1234?	T+2:28 Stage 3 burn 168 km
	1235	T+3:31 Stage 3 sep	-4510 x 500
	1236	T+4:55 Fairing sep	-4506 x 495
	1240	T+8:08 Stage 4 burn 207s	-4506 x 495
	1241	T+8:58 Stage 4 burnout
	1241	T+8:58 PBPS burn
		6:15 coast delay before sep
	1244	T+12:43 DS burnout
	1247	T+15:12 St 4 sep
2001 Jun 7			93.91 459 x 472 x 97.3
		Orbit raise	94.29 472 x 496 x 97.4
2001 Nov 12			93.94 454 x 480 x 97.4
		Orbit raise	94.46 480 x 505 x 97.4
2002 Mar 14			93.98 460 x 477 x 97.4
2002 Mar 21		Orbit raise	94.50 475 x 513 x 97.4
2002 Sep 9			93.75 444 x 471 x 97.4
2002 Sep 10		Orbit raise	94.37 468 x 507 x 97.4
2002 Dec 2			93.97 451 x 486 x 97.4
2002 Dec 4		Orbit raise	94.09 458 x 490 x 97.4
2003 Apr 14			93.61 435 x 466 x 97.4
2003 Apr 16		Orbit raise	94.07 458 x 488 x 97.4
2003 Apr 30		Orbit raise	94.31 479 x 491 x 97.4
2003 May 5		Orbit raise	94.55 480 x 512 x 97.4
2003 Jul 7			94.45 477 x 506 x 97.4
2003 Jul 10		Orbit raise	94.75 501 x 512 x 97.4
2004 Mar 14			94.40 483 x 495 x 97.4
2004 Mar 15		Orbit raise	94.59 486 x 511 x 97.4
2004 Mar 25		Orbit raise	94.78 504 x 511 x 97.4
2004 Sep 19			94.65 499 x 503 x 97.4
2004 Sep 20		Orbit raise	94.71 500 x 507 x 97.5
2004 Oct 4		Orbit raise	94.78 504 x 510 x 97.5
2006 Feb 20			94.46 490 x 494 x 97.4
2006 Feb 20		Orbit raise	94.62 493 x 506 x 97.4
2006 Feb 27		Orbit raise	94.79 504 x 511 x 97.5
2008 Sep 8			94.56 493 x 501 x 97.5
2009 Mar 2			94.53 491 x 500 x 97.3
2009 Mar 3		Orbit raise	94.62 498 x 501 x 97.4
2009 Mar 16		Orbit raise	94.79 500 x 516 x 97.5
2009 Mar 23		Orbit raise	94.87 507 x 517 x 97.5
2011 Feb 9			94.71 498 x 511 x 97.4
2011 Feb 9		Orbit raise	94.81 503 x 515 x 97.5
2011 Feb 15		Orbit raise	94.91 506 x 522 x 97.5
2011 Feb 21		Orbit raise	95.02 514 x 524 x 97.5
2011 Mar 1		Orbit raise	95.12 515 x 533 x 97.5
2011 Mar 8		Orbit raise	95.22 525 x 532 x 97.6
2011 Mar 15		Orbit raise	95.32 527 x 540 x 97.6
2011 Mar 22		Orbit raise	95.42 534 x 543 x 97.6
2011 Mar 29		Orbit raise	95.52 536 x 550 x 97.6
2012 Mar 27			95.25 524 x 536 x 97.6
2012 Mar 27		Orbit raise	95.33 524 x 544 x 97.6
2012 Apr 3		Orbit raise	95.41 530 x 546 x 97.6
2012 Apr 10		Orbit raise	95.50 535 x 550 x 97.6
2012 Apr 24		Orbit raise	95.57 537 x 555 x 97.6
2015 May 7			93.65 447 x 458 x 97.6

Genesis 2

 2007-028A

---

Bigelow due for launch Jan 2007 by Dnepr. Same third-scale size as Genesis 1: 4.6m long 2.4m dia, 4 solar arrays. Mass around 1350 kg.

Genesis 2
Date	Time	Event	Orbit
2007 Jun 28 1502:20	Launch by Dnepr	Yasny
		T+1:49? Stage 1 sep
		T+4:36? GO
		T+4:41? St 2 sep
	?	T+4:45? DU on
	1516:27	Stage 3 sep
	2320	Payload acquired by ground station
2007 Jun 30			95.83 555 x 561 x 64.5
2015 May 31			205 x 229 x 64.5