DSP-17

 1994-084A

---

DSP 17 was launched on a Titan 4/IUS on 1994 Dec 22.

DSP 17
Date	Time	Event	Orbit
1994 Dec 22	2219	Launch by Titan 402/IUS	CC LC40
	2221	T+2:00 St 1 MES
	2221	T+2:04 SRM sep T+52 km
	2222	T+3:59 Fairing 115 km
	2224	T+5:09 St 2 MES
	2224	T+5:10 St 1 sep 142 km
	2228	T+8:50 St 2 MECO
	2228	T+8:59 Titan 4 stage 2 sep	156 x 159 x 28.6 (UN)
	2326	T+1:07:19 IUS SRM-1 burn
	2328	T+1:09:46 IUS SRM-1 burnout
	2333	T+1:14 IUS RCS-1
1994 Dec 23	0436	T+6:17 IUS SRM-1 sep
	0439	T+6:20 IUS SRM-2
	0441	T+6:22 SRM-2 burnout
	0444	SRM-2 RCS
	0501	T+6:42 IUS SRM-2 sep from DSP
1995 Oct			GEO 103E
1999 Jan			GEO 103E
2001 Dec		mv out	GEO 103E
2002 Mar?		mv in	GEO 145E
2003 Mar			GEO 145E
2006?		Move to Atlantic
2008 Sep			GEO 49W
2009 Feb 2			1436.12 35732 x 35841 x 9.3 GEO 49.4W

GSAT-5P

 2010-F04

---

36 C-band transponders to replace Insat 2E at 55E. Also known as GSAT 5 prime. Possibly same as Insat 4D. Mass 2310 kg full 975 kg dry, 1.6 x 1.5 x 3.09m box + 2 panels.

Launch by GSLV-F06 with C15 stage - a lengthened version of the KVD-1A based C12 used on earlier flights, with engine uprated to 126% of rated thrust. This moved the stage 2 impact point to the Andaman Sea.

At 47s the strapon boosters failed to steer, losing communication with the flight computer. A set of connectors on the stage 2/3 interface were broken due to structural failure of their support fairing, causing the steering failure. This failure was a generic issue and could have happened on any of the previous GSLV flights. At 61s altitude was 13 km and relative velocity was 0.42 km/s. The vehicle was destroyed by aerodynamic stresses. Impact prior to 292s (T+4:52) at 2.7 km downrange.

The control failure occurred at 47 seconds and around 10 km altitude? And breakup a few seconds later at 51 s (estimated from video) at a similar altitude? Destruct signal at 63s but by then the rocket had already broken up. The screenshot at 61s shows altitude 12 km and velocity 0.453 km/s but whether that is true realtime data or the planned trajectory is unclear. It looks like it might be real data as the altitude reaches a max of 15.0 km at 80 s, vrel 0.05km/s and 6 km range and then starts to fall.

GSAT-5P (plan)
Date	Time	Event	Orbit
2010 Dec 25		Launch by GSLV-F06	SHAR SLP
		T+2:28 GS1 burnout 68 km
		T+3:46 Fairing 115 km
		T+4:49 GS2 burnout 137 km
		T+18:51 GS3 burnout 250 km 10.2 km/s
		T+19:06 GS3 sep

GSAT-5P (actual)
Date	Time	Event	Orbit
2010 Dec 25	1034	Launch by GSLV-F06	SHAR SLP
		T+47s SOB steering failed
		T+51s Breakup 14 km, 0.2km/s
		T+1:03 Destruct command sent
		T+1:20 Apogee 21 km
		T+4:52? impact

Astra 1D

 1994-070A

---

Astra 1D had a launch mass of 2730 kg and a BOL mass of 1700 kg. (Prelaunch info: 2924 kg launch, 1250 kg dry; 160 kg will be used to raise apogee after the PVA insertion). Size is 3.4 x 2.8 x 4.5m with 21m span. It was the second HS-601 class satellite launched for SES of Luxembourg. In Mar 1998 it was moved from 19.2E to inaugurate a new SES orbital slot at 28.2E. Astra 1F replaced it as the prime satellite.

Astra 1D
Date	Time	Event	Orbit
1994 Nov 1	0037	Launch by Ariane 42P (V69)	CSG ELA2
		T+1:25 PAP sep
	0040	T+3:24 Stage 1 sep
		T+3:27 St 2 MES
	0041	T+4:29 Fairing sep
	0042	T+5:35 Stage 2 sep
	0042	T+5:40 Stage 3 burn
	0055	T+18:10 Stage 3 MECO
	0057	T+19:57 Stage 3 sep
1994 Nov 1			540.88 217 x 31006 x 7.0
1994 Nov 1	1830?	PVA/LAM-1
1994 Nov 2			632.33 214 x 35836 x 7.0
1994 Nov 4	1500?	LAM-2
1994 Nov 4			724.05 4818 x 35844 x 5.0
1994 Nov 5	1400?	LAM-3
1994 Nov 5			920.73 14048 x 35897 x 2.2
1994 Nov 9	1030?	LAM-4
1994 Nov 9			1435.44 35687 x 35860 x 0.2
1994 Nov 13			1436.04 35712 x 35858 x 0.1 GEO 14.7E
1995 Jan 6			1436.07 35761 x 35810 x 0.1 GEO 19.3E
1998 Jan 30			1436.06 35769 x 35802 x 0.0 GEO 19.1E
1998 Mar		Move to 28E
1998 Mar 11			1435.97 35747 x 35820 x 0.1 GEO 27.6E
1998 Apr 30			1436.09 35781 x 35791 x 0.0 GEO 28.2E
1998 Jun 7			1436.04 35780 x 35790 x 0.0 GEO 28.2E
1998 Nov 17			1436.03 35725 x 35844 x 0.0 GEO 28.5E
1998 Nov		Move to 19E
1998 Nov 26			1436.10 35778 x 35795 x 0.0 GEO 19.3E
1999 Oct 14			1436.02 35773 x 35797 x 0.0 GEO 19.3E
1999 Nov 11			GEO 19.2E
1999 Nov		Move out
1999 Dec 6		move in	1436.08 35768 x 35804 x 0.0 GEO 28.2E
2000 Jun 13			1436.07 35780 x 35791 x 0.1 GEO 28.2E
2001 Feb		Move to 24E
2001 Jun 6			1436.08 35770 x 35801 x 0.1 GEO 24.1E
2003 Nov 12		Move to 23E
2003 Nov 26			1436.43 35779 x 35797 x 0.1 GEO 23.0E
2003 Dec 20			1436.10 35775 x 35797 x 0.1 GEO 23.0E
2006 Aug 1			1436.06 35770 x 35801 x 0.1 GEO 23.5E
2007 Oct 23		Move out from 23E
2007 Nov 6		Move in at 31.0E
2008 Jan 15		Relocated to 31.3E
2010 Jun 11		Move out at 31E	1436.08 35774 x 35800 x 2.5 GEO 31.3E
2010 Jul 30		Mv in at 1.8E
2010 Aug 20			1436.12 35771 x 35803 x 2.7 GEO 1.8E

June 17,1999

https://web.archive.org/web/20080504033834/http://digest-archive.degrassi.ca/DD65.htm

https://web.archive.org/web/20080504033840/http://digest-archive.degrassi.ca/DD66.htm

Insat 4B

 2007-007A

---

Insat 4B was an Ariane 5 payload similar to 4A. Mass 3028 kg launch 1335 kg dry, 3.1 x 1.8 x 2.0 m with 15.4m span. Mass 3029 kg launch 1325 kg dry according to EADS. Build by ISAC-Bangalore with 440N LAE.

In 2010 one solar array failed, reducing the satellite to half capacity.

Insat 4B
Date	Time	Event	Orbit
2007 Mar 11	2203	Launch by Ariane 5ECA
		T+2:19 EAP sep
		T+3:16 Fairing sep
	2211	T+8:58 EPC MECO
	2212	T+9:04 EPC sep	-1251 x 157 x 7.22
	2212	T+9:08 ESC-A MES
	2227	T+24:47 ESC-A MECO
	2229	T+26:40 Skynet 5A sep
	2231	T+28:58 Sylda 5 sep
	2234	T+31:02 Insat 4B sep
2007 Mar 21	1911		631.91 246 x 35782 x 4.5
2007 Mar 13		LAM
2007 Mar 13	1605		921.83 14257 x 35737 x 1.2
2007 Mar 14		LAM
2007 Mar 15	0847		1361.11 32877 x 35734 x 0.2
2007 Mar 16	0506	LAM 3:50
2007 Mar 20			1432.31 35700 x 35724 x 0.2 GEO 55.5E+19.9E/d
2007 Mar 23			1433.8 35703 x 35781 x 0.1 GEO 80.4E+0.6E/d
2007 Apr 12		Arrive 93.5E
2007 May 18			1436.2 35771 x 35804 x 0.1 GEO 93.5E
2010 Jul 7		Solar array failure

Poor Little Rich Girl

https://welib.org/md5/e4679a64f9396aa77c12d118a46328c6

Progress M-60

 2007-017A

---

11F615A55 No. 360 with a launch mass of 7264 kg. Flight 25P.

M-60 was used for the Plazma-Progress experiment,involving ground observations of plasma effects from Progress rocket burn.

 

PM60
Date	Time	Event	Orbit
2007 May 12	0325:38	Launch by Soyuz U Ts15000-104 (106)	KB
	0334:27	T+8:49 Blok I sep
	0715:23	DV1 22.0m/s
	0759:23	DV2 5.1 m/s
2007 May 14	0429:18	DV3 1.3m/s
2007 May 15	0505	Braking
	0509:57	Docked with Zvezda
2007 Sep 19	0037:00	Undocked from Zvezda	91.30 331 x 344 x 51.6
		Begin Plasma-Progress experiments
	2152	Burn 1, SKD, 1.5m/s 5s	91.25 331 x 340 x 51.6
2007 Sep 20	1010		91.24 328 x 341 x 51.6
	2039:52	Burn 2, SKD, 6.3s 2.7m/s	91.22 325 x 343 x 51.6
2007 Sep 21	2100:13	Burn 3, DPO 5s 2.6m/s retro	91.18 322 x 341 x 51.6
2007 Sep 22	1944:59	Burn 4 SKD 6.3s 2.5m/s	91.16 320 x 343 x 51.6
2007 Sep 23	2004:19	Burn 5, DPO 6.6s 1.6m/s	91.16 319 x 343 x 51.6
2007 Sep 24	2023:25	Burn 6, DPO 5s, 1.1m/s posi	91.19 320 x 345 x 51.6
2007 Sep 25	1901:00	Deorbited, 147s SKD, 84.2m/s
	1903:27	SKD burn end	54 x 324 x 51.6 (dV)
	1936:42	Entry interface
	1948?	Impact Pacific

Soyuz TMA-3 (Inguli)

 2003-047A

---

The TMA-3 crew comprised MKS-8, the 8th main expedition, and EP-5, the 5th visting expedition, on mission ISS 7S.

Mike Foale is TMA-3 BI-2 and ISS Commander and Science Officer. Aleksandr Kaleri is TMA-3 Kdr and ISS flight engineer. Callsign was Ingul'. Pedro Duque is TMA-3 BI-1 and EP-5 ("Cervantes") crewmember.

Launch by Soyuz-FG; spacecraft 213. Callsign Inguli. Mass 7270 kg.

The Soyuz TMA-3 spaceship landed in Kazakhstan on Apr 30, returning the Expedition 8 and ESA DELTA crews to Earth. Mike Foale, Aleksandr Kaleri and Andre Kuipers entered TMA-3 from the Station's Pirs module and closed the hatches at 1747 UTC on Apr 29. They undocked from Pirs at 2052 UTC and fired their deorbit engines at 2320 UTC. The 115 m/s burn near apogee lasted 4min 23s and lowered the orbit from 354 x 371 km to about -32 x 369 km. The orbital and propulsion modules were jettisoned at 2345 UTC, and the descent module landed at 50 38N 67 20E around 0012 UTC on Apr 30, 55 km NE of Arkalyk.

Soyuz TMA-3
Date	Time	Event	Orbit
2003 Oct 18	0538:03	Launch by Soyuz-FG
		T+1:53 SAS jettison
		T+1:57 Strapons sep
		T+2:37 Fairing sep
		T+4:47 Blok A sep
		T+4:57 KhO sep
	0546:48	T+8:45 Blok I MECO
	0546:51	T+8:48 Blok I sep7 88.58 190 x 218 x 51.65
	0913:08	DV1 44s 17m/s
	0950:55	DV2 43s 17m/s	89.90 266 x 272 x 51.6
2003 Oct 19	0637:19	DV3 2m/s 6.2s	89.94 269 x 273 x 51.6
2003 Oct 20	0504:47	DV4 42.1s 16.87m/s
	0549:36	DV5 82.1s 33.69m/s	92.15 375 x 384 x 51.6
	0638	Range 5 km
	0645	Range 1.6 km
	0650	Range 550m
	0655	Begin flyaround
	0703	Stationkeeping at 120m?
	0708	Resume approach
	0709	Range 107m
	0710	Range 80m
	0711	Range 50m
	0714	Range 10m
	0715:58	Docked with Pirs
	0729	Hard dock
	1019	HO to Pirs	92.15 375 x 384 x 51.6
2004 Apr 29	1747	HC to Pirs
	2052:09	Undock
	2320:04	DO 4:23 115.2m/s	354 x 371 x 51.6
	2324:19	DO CO	-32 x 369 x 51.6
	2345:36	Modules sep
	2348:19	Entry interface at 101 km
	2354	End of blackout
	2357	Parachute deployed
2004 Apr 30	0011:15	Landed

Aviation Week: August 23-30,2010

 https://welib.org/md5/5302a1542264454d15643b42c9736392

Raduga 2004

 2004-010A

---

The Globus satellite launched in Mar 2004 was originally named Kosmos-2406, but was redesignated Raduga-1 in May 2004.

Kosmos-2406/Raduga-1
Date	Time	Event	Orbit
2004 Mar 27	0330	Launch by Proton-K	KB LC81
		T+2:06 St 1 sep
		T+3:03 GO sep
		T+5:30 St 2 sep
		T+9:34 St 3 MECO
	0339	T+9:44 Stage 3 sep
	0443	T+1:13:25 Blok DM-2 MES-1
	0450	T+1:20:28 DM MECO-1	x 49.2
	1000	T+6:33:49? SOZ burn
	1000	T+6:33:49 DM MES-2
	1004	T+6:37:02 DM MECO-2
	1006	DM sep
2004 Apr 21			1436.01 35772 x 35797 x 1.4 GEO 85.0E
2004 May 18		DM orbit	1438.60 35498 x 36172 x 1.3
2006 Aug 8			1436.07 35777 x 35794 x 1.3 GEO 85.4E
2010 Feb 5			1435.40 35757 x 35788 x 4.4 GEO 85.0E

Magnificent desolation : the long journey home from the moon

 https://welib.org/md5/99ec6c798f377e0aac5a56e39068fb1d

Progress M-56

 2006-013A

---

11F615A55 No. 356. Launched by 11A511U-PBV P15000-100. Mission 21P to dock with Zvezda. Mass 7281 kg.

Progress M-56
Date	Time	Event	Orbit
2006 Apr 24	1603:25	Launch by Soyuz-U	KB LC1
		T+1:59 Strapons sep
		T+2:41 GO sep
		T+4:47 Blok A sep
		T+4:57 KhO sep
		T+8:46 Blok I MECO
	1612:14	T+8:49 Blok I sep
	1938s	DV1
	2029s	DV2
2006 Apr 25	1709	DV3
2006 Apr 26	1703	Braking
	1720	Flyaround begins at 400m
	1731	Stationkeep at 160m
	1732	Final approach
	1741:31	Docked with Zvezda
2006 May 4	1129	Orbit raise 393s burn
2006 Aug 23	1604	PM56 orbit raise
2006 Sep 19	0028:17	Undocked
	0031	Sep burn
	0328:00	Deorbit 162.9s 85.3 m/s	334 x 349 x 51.6
	0330:43	Deorbit CO	55 x 338 x 51.6
	0403:44	Entry

NATO 4B

 1993-076A

---

NATO IVB was launched in Dec 1993. After two months slow drift across the Atlantic, it was placed on station in early Mar 1994 over 6E. In 1998 it was moved to the 20W position.

NATO IVB
Date	Time	Event	Orbit
1993 Dec 8	0048:00	Launch by Delta 7925	CC LC17
		Az 95 deg
		T+1:03 SRM 1-6 off
		T+1:06 SRM 1-6 sep
		T+2:09 SRM 7-9 off
		T+2:12 SRM 7-9 sep
		T+4:20? MECO
		T+4:28 St 1 sep
		T+4:34 Delta stage 2 burn
	0059	T+11:03 Delta SECO-1	185? x 2119? x 29.4?
			164? x 2119? x 29.4
	0109	T+21:25 Delta SES-2
	0109	Delta SECO-2	300? x 2119? x 29.4
	0110	Delta sep
	0111	TES
	0112	TECO
	0114	T+26 Stage 3 sep	643.70 725 x 35908 x 23.2
	0142?	SES-3 depletion	109.77 313 x 2119 x 23.0
1993 Dec 10	1239?	Star 30E AKM
1993 Dec 11			1448.20 35095 x 36951 x 4.2 GEO 14.7W+3.0W
1994 Jan 9			1440.95 35117 x 36645 x 4.1 GEO 59.6W+1.2W
1994 Mar 11		mv in	1436.20 35786 x 35790 x 3.8 GEO 5.9E
1994 Jun 2			1436.06 35782 x 35789 x 3.9 GEO 6.0E
1997 Jul 22			1436.07 35776 x 35795 x 2.3 GEO 6.0E
1998 Jan 14		mv out	1436.20 35773 x 35803 x 2.1 GEO 5.8E
1998 Feb 1			1438.54 35776 x 35892 x 2.1 GEO 6.1W+0.6W
1998 Mar 28		mv in	1436.11 35776 x 35797 x 2.0 GEO 20.2W
1999 Oct 17			1436.12 35772 x 35801 x 1.5 GEO 20.3W
2006 Jul 10			1436.11 35772 x 35801 x 5.3 GEO 20.3W
2006 Nov?		Move out
2007 Feb 4			1435.90 35777 x 35787 x 5.8 GEO 35.4E
2008 Nov 25			1436.11 35774 x 35799 x 7.0 GEO 34.9E

DirecTV 5

 2002-023A

---

SS/Loral, former Tempo 1. Launched May 2002 by Proton/DM3. DirecTV is a subsidiary of GM/Hughes. Mass 3640 kg.

In Aug 2004 it was moved to 72.5E.

DirecTV-5
Date	Time	Event	Orbit
2002 May 7	1700:00	Launch by Proton	PL81/24
		T+2:06 St 1 sep
		T+5:35 St 2 sep
		T+5:44 GO sep
	1709	T+9:37 St 3 MECO
	1709	T+9:48 St 3 sep	198 x 245 x 51.6
	1710	Adapter sep
	1813:54	T+1:13:54 DM MES-1
	1820:31	T+1:20:31 DM MECO-1	202 x 35856 x 51.6
2002 May 7	2310	T+6:10:07 DM MES-2
	2312	T+6:11:58 DM MECO-2	6600 x 35786 x 17.6
	2332	T+6:31:58 DM sep
2002 May 8			759.19 6568 x 35809 x 17.7
2002 May 9		LAM-1	991.84 17333 x 35799 x 6.4
2002 May 11	1530?	LAM-2	1406.83 34643 x 35779 x 0.2
2002 May 15		LAM-3	1434.22 35646 x 35852 x 0.1 GEO 130.3W+0.5E
2002 May 31		Testing	1436.15 35777 x 35797 x 0.1 GEO 129W
2002 Jun 5		Move to 119W
2002 Jul 19			1436.11 35773 x 35800 x 0.1 GEO 119.2W
2004 Aug 10			1436.08 35774 x 35798 x 0.0 GEO 119.3W
2004 Aug 20		mv out
2004 Aug 24			1428.29 35621 x 35645 x 0.0 GEO 99.4W+2.0E/d
2004 Sep 10		mv in at 73W
2005 Feb 1			1436.07 35775 x 35796 x 0.1 GEO 72.5W
2005 Sep 1			1436.13 35779 x 35794 x 0.0 GEO 72.7W
2005 Sep 28		Move to 109.8W to replace DTV6
2005 Oct 17		Move in at 109.8W
2006 Aug 8			1436.09 35771 x 35801 x 0.0 GEO 109.8W

Foothold in the Heavens: The Seventies

 https://welib.org/md5/448b50a5e108a73bdaf265b269828430

Thor 5

 2008-006A

---

Telenor Satellite Broadcasting's Thor 5 (Thor 2R) built by Orbital. Mass 2012 kg or 1960 kg (2024 kg with adapter?), 1090 kg dry. 

Thor 2R
Date	Time	Event	Orbit
2008 Feb 11	1134:00	Launch by Proton	KB LC200/39
		T+2:03 St 1 sep
		T+5:33 St 2 sep
		T+5:45 GO sep
	T+9:33 St 3 MECO
	1143:45	T+9:45 St 3 sep	-682 x 178 x 51.58
	1145:19	T+11:19 Briz MES-1
	1150:56	T+16:56 MECO-1	173 x 173 x 51.6
	1201?	St 3 reentry
	1242:30	T+1:08:30 MES-2
	1258:56	T+1:24:56 MECO-2	298 x 5000 x 50.3
	1457:56	T+3:23:56 MES-3
	1516:58	T+3:42:58 MECO-3
	1518:12	T+3:44:12 DTB sep	496 x 36846 x 49.1
	2034:02	T+9:00:02 MES-4
	2044:32	T+9:10:32 MECO-4
	2056:50	T+9:22:50 Briz sep in GEO	36746 x 36840 x 0.0
	2300:00	T+11:26:00 SOZ-6 burn 25s
	2300:25	T+11:26:25 SOZ-6 CO
2008 Feb 12	0226		1473.52 35946 x 37085 x 0.12 GEO 51.2E+9W/d
2008 Feb 19		mv	1451.48 35953 x 36221 x 0.1
2008 Feb 23		mv in	1439.31 35774 x 35924 x 0.1 GEO 16.5W
2008 Feb 29		mv out
2008 Mar 4			1426.29 35585 x 35603 x 0.1 GEO 7.4W+2.4E/d
2008 Apr 28		mv in at 0.7W	1436.06 35767 x 35804 x 0.07 GEO 0.7W
2010 May 2			1436.08 35775 x 35796 x 0.0 GEO 0.7W

Amos 2

 2003-059A

---

IAI MBT Div. to build Amos-2. Spacecom Ltd./Tel Aviv is service provider for Amos-2; the satellite was delivered on orbit by IAI. Mass 1350 kg full (or 1374 kg), 646 kg dry, size 2.7 x 2.1 x 2.4m span 11.0m. It will backup Amos 1 at 4W and include service to the eastern US. Launch by Starsem Soyuz-Fregat in Dec 2003.

Followon AMOS HP with 20 Ku-band transponders and 2600 kg mass?

Amos 2
Date	Time	Event	Orbit
2003 Dec 27	2130:00s	Launch by Soyuz-FG/Fregat ST12	KB PL31/6
		T+1:58 BVGD sep
		T+4:13 Fairing sep
		T+4:48 Blok A sep
		T+4:58 KhO sep
		T+8:45 Blok I MECO
	2138:48	T+8:48 Blok I sep	58 x 190 x 51.8
	2138:53	T+8:53 SOZ-1 burn
	2139:49	T+9:48.5 MES-1 20.5s
	2140:09	T+10:09 MECO-1 EPO	190? x 190?
	2215?	Blok I reentry
		T+1:09:29 SOZ-2
	2240:24	T+1:10:24 MES-2 ascending node=10.25W 25S 25W, 659s
	2251:23	T+1:21:23 MECO-2 intermediate 16N 2E	250? x 35780 x 49?
2003 Dec 28	0403:34	T+6:33:34 SOZ-3 burn
	0404:29	T+6:34:29 MES-3 over 90E 0N, 137s
	0406:46	T+6:36:46 MECO-3	4407 x 35788 x 23.63
	0406:47	T+6:46:47 Fregat sep	4409 x 35779 x 23.58
	0446:47	T+7:16:47 SOZ-4 Fregat depletion
	0447:02	T+7:17:02 SOZ cutoff
2003 Dec 29			714.42 4409 x 35779 x 23.58
2003 Dec 30	0317	ABM-1 46min burn	19000 x 35800
	2040?	Apogee
2003 Dec 31	1350	ABM-2 17min burn	34000 x 35800
2004 Jan 5			1402.99 34439 x 35832 x 0.3
2004 Jan 12		On Station	GEO 4W
2004 Feb 19		Delivered to Spacecom
2006 Aug 1			1436.07 35777 x 35794 x 0.1 GEO 4.0W

Seventeen: April 2010

 https://welib.org/md5/ce0d1381c9c6c6da1dbad191ea0172a1

GeoLITE

 2001-020A

---

GeoLITE is the geosynchronous lightweight technology experiment, an NRO experimental satellite. Launch by Boeing Delta II from CC in early 2001. The TRW-built T-310 satellite has a mass of 1870 kg, with a UHF comms payload from Hughes and a laser comms payload from Lincoln Lab. The new T-310 bus is based on the Rocsat/EOS-Common (STEP) satellite. Dry mass is 929 kg. Size is 3.0 x 1.8 x 1.8m with 8.8m span.

The satellite was assigned the designation USA 158 after launch.

The satellite carried a TRW TR-500 SCAT dual mono/bipropellant 40N hydrazine thruster, which was used to reach GEO in over a dozen orbit raising burns.

As well as the one-year laser comms experiment, GeoLITE hosted an `operational TDDS mission' with a planned lifetime of 9 years. TDDS is the TRAP (Tactical Related Applications) Data Dissemination System which `provides worldwide dissemination of high-interest ELINT, contact reports, and parametric information at the SECRET level.' GeoLITE carried a UHF transponder for the TDDS system (Crosslink, Spring 2005). TDDS was apparently also called IBS-S (Integrated Broadcast Service-Simplex).

The mission control for the lasercom experiment phase was at TRW/DSD in Virginia and the satellite was originally stationed at that longitude. For the TDDS phase it was drifted to another location (possibly the Indian Ocean).

GeoLITE
Date	Time	Event	Orbit
2001 May 18	1745:00	Launch by Delta 7925-9.5	CC SLC17B
		SRM 1-6 sep
		SRM 7-9 sep
		MECO
		St 1 sep
		St 2 SES-1
	1750	Fairing sep
	1755:32	T+10:32 SECO-1
	1806:37	T+21:37 SES-2 69s
	1807:46	T+23m SECO-2	187 x 2011 x 24.7 (UN)
	1809	T+24m St 2 sep
	1809:30	T+24:30 TES
	1811	T+26 TECO	187 x 35800? x 26.5
	1815	Yo-yo despin
	1815:31	T+30:31m St 3 sep
2001 May 20?		AKM burn
2010 Jan 1			1436.12 35653 x 35920 x 3.0 GEO 99.9E

The Long Road to Annapolis : The Founding of the Naval Academy and the Emerging American Republic

 https://welib.org/md5/d4c4720757544d13fb96e013fe15d34f

The Arthur of the Welsh: The Arthurian Legend in Medieval Welsh Literature

 https://welib.org/md5/c3168681e12445d6fbab8e6a70a87afc

USA-116

 1995-066A

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The USA 116 spacecraft was launched on 1995 Dec 5 by a Titan 4 with a 57 foot payload fairing. Launch occurred 22 min before the USA 86 spacecraft passed over Vandenberg, leading to speculation that USA 116 was replacing the older satellite. An ITAR-TASS report quoted Russian Defense Ministry sources as saying that the satellite was an advanced Keyhole type spacecraft and gave the initial orbit. The satellite flew in a 1258 LTDN SSO, the east plane orbit.

USA 116
Date	Time	Event	Orbit
1995 Dec 5	2118:00	Launch by Titan 4	V SLC4E
	2120?	T+2:00 St 1 MES
	2120?	T+2:04 SRM sep
	2121?	T+3:59 Fairing
	2123?	T+5:09 St 2 MES
	2123?	T+5:10 St 1 sep
	2126?	T+8:50 St 2 MECO
	2127?	T+8:59 Titan 4 stage 2 sep
			97.3 265 x 1006 x 97.8 (UN)
			95.7 156 x 976 x 98.7
		Raise perigee
1996 Jun 15			97.59 263 x 1023 x 97.87
1997 Jun 17			97.61 255 x 1032 x 97.9
1998 Jul 24			97.35 259 x 1004 x 97.93
1998 Sep 9			97.44 281 x 991 x 97.93
1999 Mar 22			97.37 320 x 944 x 97.9
1999 Jul 10			97.18 324 x 922 x 97.9
2000 Sep 4			97.34 319 x 943 x 97.9
2001 Aug 22			97.48 318 x 958 x 97.9
2001 Sep 4			97.34 317 x 955 x 97.9
2005 Mar 20			96.82 410 x 802 x 97.8
2007 Jan 22			96.73 403 x 800 x 97.2
2007 Apr		Raise apogee
2007 May 20			97.13 405 x 837 x 97.2
2007 Nov 29			97.12 396 x 844 x 97.8
2008 May 6			97.11 401 x 839 x 97.9

Aviation Week: January 14,2008

 https://welib.org/md5/70929f7b4325608b79ae30130fd8602f

Globalstar 26

 1999-041A

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M26 was the first of a new group of four launched on 1999 Jul 25. Launch was delayed a day to give STS-93 a third chance to launch.

Mass 448 kg; dispenser is 269 kg. Total stack (4 sats and dispenser) 2061 kg.

Globalstar 26
Date	Time	Event	Orbit
1999 Jul 25	0746:03	Launch by Delta	CC LC17A
		T+1:03 SRB burnout
		T+1:07 SRB sep
		T+4:24 MECO
		T+4:32 St 1 sep
		T+4:37 St 2 TIG
		T+4:47 PLF sep
	0757:21	T+11:18 SECO1	185 x 1361 km x 51.9
	0847:55	T+1:01:52 SES2
	0848:21	T+1:02:18 SECO2	1367 x 1367 km x 52.0
	0855:13	T+1:09:10 U1/U2 sep
	0859:23	T+1:13:20 L1/L2 sep
	0934:23	T+1:48:20 SES3 evasive
		T+1:48:25 SECO3	1010 x 1373 x 52
	0941:53	T+1:55:50 SES4 depletion
		T+1:55:56 SECO4	422 x 1360 x 52
1999 Jul 25			113.13 1369 x 1371 x 52.0
1999 Aug 10		Orbit raise
1999 Aug 12		114.08 1412 x 1414 x 52
2010 Sep 7			114.08 1413 x 1413 x 52
2010 Sep 10		Orbit raise	118.07 1590 x 1597 x 52.0
2010 Sep 17		Orbit raise	124.24 1866 x 1872 x 52.0
2010 Sep 24		Orbit raise	127.01 1989 x 1994 x 51.9