Tance 2

 2004-029A

---

DSP-2, Polar. Satellite is 2.1m high 1.4m dia with mass 343 kg. DSP-P will have an orbit of 700 x 39000 x 90.0.

Launch southbound from Taiyuan; equator crossing at 0726 UTC. At 0735, the claimed insertion time, the satellite was over 110E 33S at 1200 km altitude.

If the burn was at the perigee of the final orbit, the Stage 2 orbit must have had a slightly negative perigee; the ground track is consistent with no inclination change. The delta-V required is lower than expected for the PKM.

Alternatively, the burn may have happened on the descending leg of the SM trajectory. At 0735 a preburn orbit of -4350 x 1500 km or -3643 x 1292 km would be consistent with the delta-V but not with a TYSC launch.

DSP-P
Date	Time	Event	Orbit
2004 Jul 25	0705	Launch by CZ-2C/SM	TYSC
	0707	Stage 2 burn
	0713?	Stage 2 sep	-120? x 666? x 89.1?
	0735	SM sep (?)	360.0 681 x 38278 x 90.0
	0742	SM burn
	0743	SM burnout
	0743	Perigee over 108E 66S
			695.16 666 x 38566 x 90.05
2009 Jul		Last comms

September 13,1998

 https://web.archive.org/web/20080504033310/http://digest-archive.degrassi.ca/DD40.htm

AMC-15

 2004-041A

---

Ku/Ka A2100 satellite for SES Americom. A2100 built at Newtown/Pa and Sunnyvale/Ca.

Launch mass 4021 kg.

Echostar is the anchor customer and refers to it as Echostar 15.

AMC-15
Date	Time	Event	Orbit
2004 Oct 14	2123:00	Launch by Proton-M 53508 /Briz-M 88510	KB PL200/39
		T+2:03 Stage 1 sep
	2128	T+5:35 Stage 2 sep
	2128	T+5:48 Fairing sep	-4900? x 140? x 51.5
	2132	T+9:48 Stage 3 sep
	2134	T+11:22 Briz-M MES-1
	2142	T+19:06 MECO-1	173 x 176 x 51.5
	2221	T+58:27 MES-2
	2258	T+1:32:29 MECO-2	890 x 35765 x 49.1
	2300?	T+1:33:50 DTB sep over 42N 37E	892 x 35725 x 49.0
2004 Oct 15	0358	T+6:35:17 MES-3
	0404	T+6:41:54 MECO-3
	0417	T+6:54:30 Briz-M sep	770.1 7130 x 35775 x 18.6
		MES-4 avoidance
		MECO-4
2004 Oct 18		LAM-1	872.20 11963 x 35759 x 11.5
2004 Oct 19		LAM-2	1005.68 17987 x 35757 x 6.6
2004 Oct 21		LAM-3	1196.68 26163 x 35755 x 2.8
2004 Oct 22	1830?	LAM-4
2004 Oct 27			1435.91 35772 x 35793 x 0.0 GEO 136.0W
2004 Dec 9		mv out
2005 Jan 1		mv in	1436.18 35786 x 35790 x 0.0 GEO 117.0W
2005 Mar 18		mv out
2005 Mar 24		mv in	1436.06 35783 x 35788 x 0.0 GEO 113.1W
2005 May 12		mv out
2005 Jun 2		mv in	1436.08 35784 x 35787 x 0.1 GEO 105.0W
2006 Aug 8			1436.09 35783 x 35789 x 0.0 GEO 105.0W
2008 Mar 4			1436.08 35776 x 35796 x 0.0 GEO 105.1W

Intelsat 806

 1998-014A

---

806 will be at 41.5W AOR, the slot disputed with Columbia Comms. Corp which was using C-band capacity on TDRS 4. While 801 to 804 provided voice and data relay replacing Intelsat 5, the 805 and 806 satellites were oriented to TV broadcast, and their transponders were higher power [870]. 806 was operated by Intelsat Video Services to provide service to Europe and Latin America. Atlas AC-151 launched 806 into a standard geostationary transfer orbit, after which multiple LAE burns took it to GEO. In 1998 I806 became part of the spinoff company New Skies Satellites NV and was renamed NSS 806.

Intelsat 806
Date	Time	Event	Orbit
1998 Feb 28	0021	Launch by Atlas IIAS AC-151	CC LC36
	0022	T+1:00 Air-lit SRM burn
	0022	T+1:07 Ground-lit SRM sep
	0022	T+1:57 Air-lit SRM sep
	0023	T+2:44 BECO
	0023	T+2:47 Booster sep
	0024	T+3:28 PLF sep
	0025	T+4:51 SECO
	0025	T+4:53 Atlas sep
	0026	T+5:10 Centaur MES1
	0030	T+9:43 MECO1	89.88 149 x 387 x 27.8
	0045	T+24:30 MES2
	0047	T+26:07 MECO2
	0051	T+30:07 Centaur sep
	0333		628.34 189 x 35656 x 23.9
1998 Mar 1	0330?	LAM-1
1998 Mar 1	0340		674.31 2449 x 35738 x 17.0
1998 Mar 5	1940?	LAM-2
1998 Mar 7	0540		1030.83 19133 x 35715 x 3.7
1998 Mar 8	1600?	LAM-3 over 62W
1998 Mar 9			1433.34 35727 x 35738 x 0.1 GEO 61.2W+0.7E
1998 Mar 19			1433.80 35725 x 35757 x 0.1 GEO 55.6W+0.5E
1998 Mar		Testing 55W
1998 Apr 5			1436.10 35784 x 35789 x 0.1 GEO 55.5W
1998 Apr 26			1436.16 35783 x 35792 x 0.1 GEO 55.5W
1998 Apr		Op 40.5W
1998 May 6			1436.12 35773 x 35800 x 0.0 GEO 40.5W
1998 Jun 25			1436.19 35775 x 35801 x 0.1 GEO 40.6W
1998 Nov 30		To New Skies NV
1999 Oct 17			1436.13 35775 x 35799 x 0.1 GEO 40.5W
2006 Jul 30			1436.11 35736 x 35837 x 0.0 GEO 40.5W

STS-93 (Columbia)

 1999-040A

---

After a launch delay, OV-102 was towed to the VAB to make room for OV-104 in the OPF.

Launch mass was 122534 kg. Landing mass is 99781 kg. Payload chargeable mass is 22753 kg.

Chandra launch mass 5865 kg. dry 4790 kg. IUS SRM-1 10064 kg full, 1164 kg. dry IUS SRM-2 3800 kg full, ASE 2434 kg. Other support 583.

CXO 5865 IUS 13871 ASE 2434 SE 583

Tot 22753 kg

5563 (CSC data); 5677 (to make the SODB deploy mass come out right).

Fuel cell pH signal by Collins; AC bus short very briefly. Lost one controller on center engine and one on right engine. There are 3 AC bus, each supports 2 controllers, each engine has 2 controllers, never from the same AC bus. If you lose both controllers,abort options need to be assessed. But we only lost one controller per engine, so there was no problem. Then, MECO came a second early with a 15 foot per second underburn due to being 4000 lb of LOX short. After launch it was discovered a loose pin repairing a cooling tube on an SSME broke loose, and three tubes ruptured causing a hydrogen leak during ascent. The controller spotted the low pressure in the combustion chamber and added more LOX to the mix.

The switch to the backup controller actually reduced the sensitivity of the fuel leak; it set a different bias value on the SSME engine pressure, which actually caused less of an underspeed than would have been the case.

STS-93
Date	Time	Event	Orbit
1999 Feb 10		Tow to VAB/2
1999 Apr 15	1600	Tow to OPF/1
1999 Jun 2		Tow to VAB/1
1999 Jun 3		Mated to ET/SRB
1999 Jun 7	0600	Roll to LC39B
1999 Jul 20	0436	RSLS hold T-7s
1999 Jul 22		WX scrub, lightning
1999 Jul 23	0431:00.04	Launch	KSC LC39B
	0431:05	short; ME-1 data lost
	0431:05	T+5s ME controllers down
	0433:03	T+2:03 SRB sep
	0439	O2 cutoff, 5m/s underspeed
	0439:27	T+507s MECO	87.96 78 x 269 x 28.5
	0439:47	ET sep
	0512:07	OMS-2 2:16 61.4m/s	90.09 267 x 290 x 28.5
	0514:23	OMS-2 CO
	0609:56	Open PLBD
	1000?	T+5:30 IUS table to 29 deg
	1138	Tilt table to 58 deg
	1147:01	deploy Chandra/IUS
	1148:25	D+0:01 sep RCS
	1202:25	D+0:15 10.5m/s sep burn OMS-3 L 34s, mass 97868 kg
	1202:59	OMS-3 CO
		Raise orbit 21 x 11 km
			90.42 288 x 301 x 28.5
	1230?	IUS table stow
1999 Jul 24	0102		90.42 288 x 301 x 28.5
		Flycast burn RCS test
	0142:05	OMS-4 R 15s 5m/s
	0142:21	OMS-4 CO
		Lower apogee 12 km
	0301		90.27 285 x 289 x 28.5
	0314:00	RCS 2.7m/s
	0709:35	OMS-5 L 10s 3m/s
	0709:45	OMS-5 CO
		Lower perigee 10 km
	0900		90.13 275 x 285 x 28.5
	1029:55	RCS MSX, 10s
	1030:14	RCS MSX, 10s
	1105:56	OMS-6 SIMPLEX 5s 3m/s
		Raise apogee 10 km
	1106:01	OMS-6 CO
	1106		90.21 274 x 295 x 28.5
	2200		90.21 273 x 295 x 28.5
1999 Jul 25	0549:01	OMS-7 L 10s 3m/s
	0549:11	OMS-7 CO
	0709:31	OMS-8 R 10s 3m/s
	0709:41	OMS-8 CO
	0709		90.21 272 x 297 x 28.5
	1032:16	OMS-9 L 10s 3m/s for MSX
	1032:26	OMS-9 CO
	1032		90.20 270 x 298 x 28.5
	2200		90.20 269 x 298 x 28.5
1999 Jul 26	0709:34	OMS-10 R 10s 3m/s for SIMPLEX
	0709:44	OMS-10 CO
	0709		90.10 262 x 295 x 28.5
	1034:16	OMS-11 R 10s 3m/s for MSX
	1034:26	OMS-11 CO
	1317		90.17 268 x 297 x 28.47
1999 Jul 27	0308	RCS 1.5m/s	90.22 271 x 299 x 28.47
	0448:59	OMS-12 R 10s 3m/s
	0449:09	OMS-12 CO
	0449		90.13 268 x 293 x 28.47
	0821:52	RCS orbit adjust 70s 6m/s
	0823		89.92 260 x 280 x 28.47
	2339	PLBD closed
1999 Jul 28	0219:00	Deorbit OMS-13 2:13 76m/s
	0221:14	OMS-13 DO CO	87.33 21 x 262 x 28.5
	0248:48	Entry
	0320:36	MGTD KSC RW33 4:22:49:36
	0320:44	NGTD
	0321:19	WS
	0815	Tow to OPF/3

‘The Old Order Changeth’: Arthurian literary production from Tennyson to White

 https://welib.org/md5/ed403243b7f4e231d34850c919ed0a01

MER-1 (Opportunity)

 2003-032A

---

MER-1 is "Opportunity".

MER-B Launch 2003 Jul 8 , landing 2004 Feb 25.

The pre-TCM1 miss distance is 340000 km, which is probably the flyby distance of the final stage.

B.R B.T = (204197,274289) with TCA 2004 Jan 26 1623:22.

Landing at around 2S, 354E. The landing site was named Challenger Memorial Station.

Landing site is 1.9462S 354.4734E. AIAA2004-4980 quotes actual as 1.94828S 354.47417E. Diff is (0.002,0.001) deg. Radius of Mars is 3397 km, so 0.001 deg corresponds to 17 murad or 60 meters. Hence 1 km = 0.01687 deg.

MER-1 entry mass was 832 kg, 5 kg more than Spirit.

At Gusev, b=14.57 so in X, 1 km = 0.01743 deg.

 

Date	Sol	DX, DY	Position	Location
2004 Jan 4	1	0 0	14.5719S 175.4785E	Columbia Memorial Station
2004 Jan 4	1	287 417	14.5649S 175.4835E	Heatshield
2004 Mar 14	70	216 212	14.5683S 175.4823E	Bonneville Crater SW Rim, Deserts
2004 Apr 20	106	500 -34	14.5725S 175.4872E	Missoula Crater N Rim
2004 May 4	120	1000 -255	14.5762S 175.4959E	Lahontan Crater W Rim
2004 May 27	142	1770 -756	14.5846S 175.5093E	Dagwood Sandwich Rock
2004 Jun 12	158	2350 -1110	14.5906S 175.5194E	Hank's Hollow
2004 Aug 21	226	2413 -1122	14.5908S 175.5205E	Ebenezer Rock, West Spur, Columbia Hills
2005 Feb 24	408	2779 -1068	14.5899S 175.5269E	Larry's Lookout, Husband Hill
2005 Jun 26	526	2724 -1200	14.5921S 175.5260E	Independence Rock, Husband Hill
2005 Sep 28	618	2950 -1185	14.5921S 175.5260E	True Summit, Husband Hill
2006 Jan 1	710	3060 -1500	14.5972S 175.5318E	Eldorado
2006 Feb 12	751	3090 -2000	14.6056S 175.5324E	Posey Rock, Home Plate
2006 Mar 26	792	3200 -2095	14.6072S 175.5343E	Tyrone Rock

A Sol is 24 hours 39 minutes 35.244 seconds

Spirit: (Sol 1 ends 2004-01-04 14:15 UTC) - = landing + 09:49 Spirit landed at 14:34 LST-A = 0426 UTC Jan 4. So 24:39 LST-A is 0426 + 10:05 = 1431 UTC Jan 4. 1415 UTC = 1434+0949 LST-A = 24:23 LST-A = EOLST - 13m. Wassup? ERT error? LT= 9min

If Sol 1 end = 14:15 ERT = 14:06 UTC, that's 24:14 LST-A.

LST-B = LST-A + 12:01:10 Oppo landed at 13:33 LST-B. 0454 UTC. Oppo: (Sol 1 ends at 2004-01-25 15:48 UTC) = 10:54 after landing = 24:27 LST-A = EOLST - 12min. LT = 11 min.

If Sol 1 end is 15:48 ERT = 1537 UTC then end is 24:16 LST-A.

Ahhh.. LST runs on a 24-hour martian day with 1 mars day = 88775.244 SI second = 86400 Mars seconds so 1 Mars second = 1.0275 Earth seconds. Thus, 9:49 Earth = 9:33 Mars and A Sol 1 ends at 14:34 + 9:33 = 24:07 ? 10:54 Earth = 10:36 Mars and B Sol 1 ends at 13:33 + 10:36 = 24:09 ? Suspect ERT. Conclude A Sol 2 starts at 1406 UTC 2004 Jan 4 and B Sol 2 starts at 1537 UTC 2004 Jan 25.

Nominal landing is at 0435 ERT and 0505 ERT (A,B).= 0426 and 0454 UTC.

JD = ( A Sol - 2 ) * 1.02749125 + 2453009.087500 = ( B Sol - 2 ) * 1.02749125 + 2453030.150694

A Sol = 2 + ( JD - 2453009.087500 ) * 0.9732443 B Sol = 2 + ( JD - 2453030.150694 ) * 0.9732443

 

Date	Sol	DX, DY	Position	Location
2004 Jan 25	1	0 0	1.9483S 354.4742E	Eagle Crater, Challenger Memorial Station
2004 Jan 25	1	716 -414	1.9553S 354.4863E	Heatshield
2004 Apr 6	72	190 40	1.9476S 354.4774E	Anatolia
2004 Apr 30	95	705 -100	1.9500S 354.4861E	Endurance Crater NW Rim
2004 May 21	116	840 -185	1.9514S 354.4884E	Endurance Crater SE Rim
2004 Aug 19	203	720 -160	1.9510S 354.4864E	Endurance Crater SW Inside Slope
2004 Dec 14	317	695 -182	1.9514S 354.4859E	Endurance Crater SW Rim
2004 Dec 22	325	705 -400	1.9550S 354.4861E	Heatshield area
2005 Feb 19	382	590 -850	1.9626S 354.4842E	Jason Crater W slope
2005 Mar 8	399	640 -1520	1.9739S 354.4850E	Yuri Rock, Vostok Crater
2005 Apr 2	423	485 -3140	2.0013S 354.4824E	Voyager Crater E slope
2005 Apr 25	446	462 -3471	2.0069S 354.4820E	Purgatory Dune
2005 Aug 3	543	490 -3750	2.0116S 354.4825E	Scoop Rock
2005 Oct 9	608	460 -3925	2.0145S 354.4820E	Snoopy Rock, Erebus Crater N Rim
2006 Feb 5	724	260 -4060	2.0168S 354.4786E	Roosevelt Rock, Erebus Crater W Rim
2006 Apr 4	780	385 -4640	2.0266S 354.4807E	(Southward traverse)

Rover B
Date	Time	Event	Orbit
2003 Jul 8	0318:15	Launch by Delta 7925H-9.5	CC SLC17B
		T+1:16 SRM 1-6 out
		T+1:19 SRM 7-9 on
		T+1:20 SRM sep 1-6 26 km 1.2km/s	-6300 x 35?
		T+2:39 SRM sep 7-9 68 km	-5800 x 85?
		T+4:23 MECO
		T+4:31 St 1 sep
	0322:52	T+4:37 SES-1	-3400 x 120
	0322:57	T+4:42 Fairing sep	-3390 x 120
	0327:03	T+8:48 SECO-1	160 x 180 x 28.5 (Prelaunch)
			155 x 175 x 29.40 (TLE)
	0426:12	T+1:07:57 SES-2 0.949 km/s
	0428:24	T+1:10:09 SECO-2	163 x 4762 x 28.5 (Prelaunch)
			161 x 6509 x 29.40 (TLE)
	0429:16	T+1:11:01 St 2 sep
	0429:53	T+1:11:38 TES 90s over 170E 15N (175E 11N?)
	0431:20	T+1:13:05 TECO C3= 10.3457 p=184 km
	0436:03	T+1:17:48 Yoyo
	0436:08	T+1:17:53 Star 48 sep
	0458	SES-3 depletion at 20.9N 75.5W 2658 km
	0459	SECO-3	164 x 6517 x 26.00
		Injection C3= 14.322 RLA DLA = 334.65, -3.89 (EME2000)
2003 Jul 8	1247	Pass EL1:4
2003 Jul 9			233 x -68660 x 29.47
2003 Jul 12	1122	Depart Earth sphere 1.5Mkm
2003 Jul 18	1930	TCM-B1 54m 16.2m/s
2003 Sep 8	1600	TCM-B2 2m 0.53m/s
2004 Jan 17	0200	TCM-B4 0.1m/s
2004 Jan 20	2150	Enter Mars sphere
2004 Jan 25		Mars arrival
	0433:42	Cruise sep
	0448:42	Entry 5.70 km/s -11.47 deg	12 x -17335 x 4.5
	0453	Parachute deploy
	0453:04	Heat shield sep
	0453:15	Backshell sep
	0454:27	RAD/TIRS burn
	0454:30	Bridle cut
	0454:33	Landing at Meridiani Planum
		26 bounces
	0500	Rolling
	0502?	At rest
	0508:59	MFSK LANDED ACCEL tone
	0706	Petal opening
2004 Jan 28		Wheels deploy
2004 Jan 31	0950:07	Begin to move off lander (83s drive)
2004 May 1		Arrive Endurance crater
2004 Dec 12		Leave Endurance
2004 Dec 22		Arrive at heat shield
2006 Sep		Arrive at rim of Victoria
2007 Sep 11		Enter Victoria crater
2008 Aug 28		Leave Victoria crater

Cosmo-Skymed 2

 2007-059A

---

COSMO: Constellation of Satellites for Mediterranean Basin Observation.

Second launch in the system. 1900 kg mass.

COSMO 2
Date	Time	Event	Orbit
2007 Dec 9	0231:42	Launch by Delta 7420-10	V SLC2W
		T+1:04 SRB burnout
		T+1:22 SRB sep
		T+4:24 MECO
		T+4:32 Stage 1 sep
		T+4:37 SEIG-1
		T+4:41 Fairing sep
	0243:07	T+11:25 SECO-1	185 x 645 x 97.8
	0325:09s	T+53:27 SEIG-2
	0325:21s	T+53:39 SECO-2
	0329:42s	T+58:00 Stage 2 sep	620 x 637 x 97.8
		T+1:16:40 SEIG-3 evasive
		T+1:16:45 SECO-3	185 x 616 x 97.9
		T+1:26:40 SEIG-4 Depletion burn, over Thule
		T+1:26:51 Depletion initiation
		T+1:27:08 SECO-4	185 x 605 x 98.3 (s)
		(R/B)	196 x 624 x 98.5 (TLE)
2007 Dec 9	1137		97.18 621 x 624 x 97.9

Iridium 42

 1997-077A

---

Following the two Iridium MFS dummy satellites, Iridium 42 and 44 were the first to be launched on the Chinese vehicle. After a brief period in the operational orbit, SV42 was lowered to the engineering orbit.

Iridium 42
Date	Time	Event	Orbit
1997 Dec 8	0716:49	Launch by CZ2-SD	TY
	0719	Stage 1 sep
	0720	Fairing sep
	0722	Stage 2 MECO
	0727	Stage 2 VECO, sep	93.09 185 x 665 x 86.3
	0805?	SD burn
	0807?	SD sep	626 x 636 x 86.3
	0816	Deployment complete
	0816	SD orbit lower	92.97 209 x 630 x 86.2
1997 Dec 8			97.34 626 x 636 x 86.3
1997 Dec 14			97.40 629 x 639 x 86.3
1997 Dec 16			98.36 678 x 681 x 86.4
1997 Dec 18			100.33 771 x 776 x 86.4
1997 Dec 19			100.38 775 x 778 x 86.4
1997 Dec 23	0349		100.42 774 x 782 x 86.4
		Orbit lower
	1352		100.15 761 x 769 x 86.4
	1852		100.20 766 x 769 x 86.4
1997 Dec 28			100.21 767 x 770 x 86.4
1998 Jan 5	0603		100.23 768 x 770 x 86.4
	2245		100.14 762 x 767 x 86.4
1998 Jan 8			100.15 763 x 768 x 86.4
1998 Mar 9			100.17 764 x 768 x 86.4
2004 Feb 14			100.40 776 x 779 x 86.4
2007 Jun 29			100.40 775 x 779 x 86.4

Kosmos 2416

 2005-048B

---

This is a Rodnik satellite built by NPO PM. After retirement of the sextet launches on Tsiklon-3, two satellites were launched on a Kosmos-3M; - one Gonets and one Rodnik/Strela-3.

Gonets
Date	Time	Event	Orbit
2005 Dec 21	1934	Launch by Kosmos-3M No. 232	PL LC132/1
	1936	Stage 1 sep
	1936	T+2:26? GO sep
	1941	T+7:38? Stage 2 MECO-1
	2027?	Stage 2 MES-2
	2027?	Stage 2 MECO-2
	2028	Gonets sep from Stage 2

Coriolis

 2003-001A

---

The Coriolis mission is an STP flight P98-2 carrying Windsat and SMEI. Coriolis will use a Spectrum Astro SA-200HP bus and launch by Titan II. Windsat operates as a USN/ONR satellite managed by NRL under the STP, as part of the Coriolis mission. Windsat uses a polarimetric microwave radiometer to measure wind speed and direction; earlier missions did not have all the Stokes parameters and so could not determine direction. It has a 1.8m microwave reflector and horns operating at 10.7, 18.7 and 37 GHz. Horns at 6.8 and 23.8 GHz will measure only 2 of 6 polarization components.

Assembly by Det 12 STP/Kirtland, oprations at Kirtland for first year and then by NSOC Pt Mugu. Mass 377 kg bus, 827 kg total. 4.7h 1.3dia + panel. Cylinder + truss + panel. 82 kg propellant. First use of large 7.6m fairing on the Titan 2 SLV.

It was inserted into a 281 x 845 km transfer orbit on 2003 Jan 6 and used onboard propulsion to reach its operational 822 x 841 km x 98.7 deg orbit by Jan 18.

Coriolis
Date	Time	Event	Orbit
2003 Jan 6	1419	Launch by Titan II	V SLC4W
		T+2:34 St 1 MECO
		T+2:35 Stage 1 sep
		T+2:35 Stage 2 TIG
		T+3:33 Fairing sep
	1424	T+5:32 Stage 2 MECO	219 x 824 x 98.7
	1514	T+55:48 Titan stage 2 RCS burn, 110s burn	278 x 827 x 98.7
	1517	T+58:38 Titan 2 sep	273 x 830 x 98.7
2003 Jan 9			95.93 281 x 845 x 98.7
2003 Jan 10			97.08 391 x 846 x 98.7
2003 Jan 11			98.14 489 x 849 x 98.7
2003 Jan 12			99.12 579 x 853 x 98.7
			99.57 621 x 855 x 98.7
2003 Jan 13			100.03 663 x 855 x 98.7
2003 Jan 14			100.46 703 x 857 x 98.7
2003 Jan 15			101.31 781 x 860 x 98.7
2003 Jan 16			101.38 814 x 833 x 98.7
2003 Jan 17			101.17 804 x 823 x 98.7
2003 Jan 18			101.55 822 x 841 x 98.7
2003 Feb 8			101.55 822 x 841 x 98.7
2005 Feb 13		Windsat BAPTA lube failure?
2005 Jul		Windsat operations resume

Payload:

• Windsat Passive ocean surface wind vector polarimetric radiometry, NRL; 6.8, 10.7, 18.7, 23.8 and 37 GHz; 1.83m reflector, 1025 km swath.

• SMEI Solar Mass Ejection Imager, USAFRL, camera with 0.1 percent photometry. GL-802

USA-198

 2007-060A

---

NROL-24 'Scorpius' Launch by Atlas V 401, 4m fairing, CCB and SEC Centaur from CC LC41. The satellite is thought to be an SDS satellite replacing USA 125, and operating with USA 137 and USA 179.

NROL-24
Date	Time	Event	Orbit
2007 Dec 10	2205:00	Launch by Atlas V 401 AV-015	CC SLC41
		Az 47.07 deg
		T+4:11 BECO
		T+4:17 Atlas sep
		T+4:28 Centaur MES-1
	2209	T+4:36 Fairing sep
	2215?	MECO-1	209 x 262 x 60.0
	2314	MES-2
	2315?	MECO-2
	2320?	Centaur sep	301.59 261 x 16776 x 60.0 (A)
		Centaur depletion	301.63 272 x 16768 x 60.7 (B)
		Orbit (UN)	294.0 220 x 16322 x 60.7
2007 Dec 17			301.52 258 x 16774 x 60.0
2007 Dec 28?		Orbit raise
2007 Dec 30			715.08 515 x 39705 x 62.6

Intelsat 10

 2004-022A

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IS10 is a 5575 kg Eurostar 3000. The satellite uses a plasma thruster for stationkeeping. Dry mass is 3125 kg.

Intelsat 10
Date	Time	Event	Orbit
2004 Jun 16	2227:00	Launch by Proton-M 53506 / Briz-M 88509	KB LC200/39
		T+2:03 St 1 sep at 41.8 km	-6160? x 45? x 50.5
		T+5:29 St 2 sep at 120 km	-4920? x 130 x 51.4
		T+5:42 Fairing sep	-4900? x 135? x 51.4
		T+8:36 141 km alt
		T+9:38 Stage 3 sep
	2237	T+10:00 147 km alt	-900? x 149 x 51.6
	2238	T+11:12 Briz MES-1
	2245	T+18:52 Briz MECO-1	173 x 173 x 51.5
	2335	T+1:08:12 Briz MES-2
	2352	T+1:24:54 MECO-2	258 x 5000 x 50.3
2004 Jun 17
	0155	T+3:28:45 MES-3
	0205	T+3:38:15 MECO-3
	0205	T+3:38:30 DTB jettison over 45W 0N	246.32 309 x 12967 x 49.7
	0207	T+3:40:20 MES-4
	0214	T+3:47:03 MECO-4	414 x 35849 x 49.0 (TLE)
	0720s	T+8:53:09 MES-5
	0725s	T+8:58:49 MECO-5	4184 x 35804 x 23.7 (TLE)
	0737	T+9:10:20 Briz sep
	0942s	T+11:15:00 Briz depletion
2004 Jun 20?		LAM-1
2004 Jun 21		LAM-2	1251.90 28436 x 35761 x 1.9
2004 Jun 23	1100?	LAM-3	1432.88 35678 x 35678 x 0.1
2004 Jul 6			1436.59 35787 x 35805 x 0.2 GEO0.02E+0.6E
2004 Jul 8			1436.26 35777 x 35802 x 0.1 GEO 0.7E+0.05W
2004 Jul 20			1436.02 35768 x 35801 x 0.1 GEO 0.9E
2004 Aug 19		Relocate to 1.0W
2004 Sep 2			1436.10 35782 x 35790 x 0.0 GEO 1.0W
2006 Aug 8			1436.06 35781 x 35790 x 0.0 GEO 1.0W

Addled : A Novel

https://welib.org/md5/304d64a215f0e6738b49f8d5c6c47300

Palapa C1

 1996-006A

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The Palapa C-1 satellite was owned by PT Satelindo (PT Satelit Palapa Indonesia), a regional company which replaced PT Telekomunkasi as the operator of the Palapa system. It was located at 113E and will cover Indonesia, SE Asia, and parts of China, Japan, India and Australia. Launch mass was 2989 kg, on orbit mass is 1775 kg.

By 1998 Palapa C-1 was owned jointly by PT Satelindo and PT Pasifik Satelite Nusantara (PSN). The satellite lost the ability to charge its batteries in late 1998.

In Nov 2000 the satellite was reowned by Hughes Global Services, which renamed it HGS-3 and then leased the satellite to Kalitel/San Diego, who in turn leased capacity to Turk Telecom as Anatolia 1. It was then moved to 50E.

In late 2002 it was leased by Pakistan's Ministry of Information Technology and Telecommunications, which called it Paksat 1, and moved to 38E.

The national Perumtel/Telkom organization handed over the Palapa C satellites to Satelindo in 1996; Telkom then began to launch 'Telkom' satellites.

Palapa C-1
Date	Time	Event	Orbit
1996 Feb 1	0115:01	Launch by Atlas Centaur (AC-126)	CC LC36B
	0117	BECO
	0117	Booster sep
	0118	Fairing sep
	0119	SECO
	0119	Atlas sep
	0120	Centaur MES1
	0125	Centaur MECO-1	160? x 400? x 28.2?
	0137?	Centaur MES2
	0139?	Centaur MECO2
	0143:47	Centaur sep	1923.25 240 x 89462 x 21.9
			1935.12 255 x 89869 x 21.8 (TLE)
		167 x 90327 x 21.8 (AWST)
	1714	First apogee eq crossing at 60.6W 0.0N
1996 Feb 4	0530?	LAM-1
1996 Feb 6			2811.95 29234 x 89996 x 2.26
1996 Feb			LAM-2
1996 Feb			LAM-3
1996 Feb 12			1509.96 35521 x 38920 x 0.22
1996 Feb 13	1600?	LAM-4
1996 Feb 13			1436.57 35493 x 36099 x 0.14
1996 Feb 13			1435.97 35495 x 36074 x 0.11
1996 Feb 19			1435.66 35481 x 36074 x 0.1 GEO 125.0E+0.1E
1996 Feb 27			1436.18 35493 x 36083 x 0.1 GEO 124.3E+0.03W
1996 Mar 3		Drift
1996 Mar 16		Move in	GEO 113E
1996 May 30			1436.12 35779 x 35795 x 0.0 GEO 113.2E+0.01W
1996 Aug 14			1436.14 35776 x 35798 x 0.0 GEO 112.9E
1996 Aug 15		Move out
1996 Sep 12		Move in	GEO 150E
1996 Sep 19			1436.13 35767 x 35806 x 0.1 GEO 150.5E
1999 Oct 15			1436.11 35778 x 35795 x 0.5 GEO 150.9E
2000 Nov		Renamed HGS-3
2000 Nov 24			1436.15 35771 x 35803 x 1.4 GEO 151.3E
2000 Dec		Reloc to 49E	1448.05 36008 x 36032 x 1.4
2001 Jan 25			1436.10 35688 x 35885 x 1.5 GEO 49.8E
2001 Jun 5			1436.11 35773 x 35800 x 0.1 GEO 50.0E
2002 Nov 28			1436.06 35771 x 35799 x 0.0 GEO 50.0E
2002 Dec 5		mv out	1440.50 35867 x 35878 x 0.0
2003 Jan 23		mv in as PAKSAT
2003 Feb 7			1436.04 35778 x 35792 x 0.0 GEO 38.0E
2004 Feb 10			1432.10 35773 x 35800 x 0.0 GEO 38.0E
2006 Aug 1			1436.05 35772 x 35798 x 0.0 GEO 38.0E