Intelsat 601

 

1991-075A

---

The satellite was a spin stabilized 5.4 m high, 3.6m diameter cylinder with an extendable solar array skirt (deployed height was 11.8m). The 1908 kg dry mass of the satellite was increased to 4260 kg when fuelled (BOL mass was 2560 kg). The masses of the various components of the Ariane 44L launch vehicle are tabulated below:

 

Ariane mass budget
Element	Dry mass	Fuel	Total
PAL (4)			17991
L220	18254	387244	405498
St 2	3696	35479	39175
H10	1279	10586	11865
Case a equipement	723		723
Adapteur	70		70
Intelsat 601	1908	2352	4260
Coiffe	815		815
Ariane total			480397

Intelsat VI~F-1
Date	Time	Event	Orbit
1991 Oct 29	2308:08	Launch by Ariane 44L (V47)	CSG ELA2
	2309	PAL1 and 2 sep (T+2:29)
	2309	PAL3 and 4 sep (T+2:30)
	2310	Stage 1 sep (T+3:33)
	2310	Stage 2 MES (T+3:36)
	2311	Fairing sep (T+4:19)
	2312	Stage 2 sep (T+5:45)
	2312	Stage 3 MES (T+5:50)
	2326:00	Stage 3 MECO (T+17:52)
	2330:45	Stage 3 sep (T+22:37)
	2331:39	Stage 3 sep burn (T+23:31)
1991 Oct 30	0430?	R4D test burn	634.83 280 x 35899 x 7.1
1991 Oct 31	0137s	LAM-1 R4D main burn 1
1991 Oct 31	1200		715.97 4532 x 35733 x 4.44
1991 Nov 1	0200?	LAM-2	1087.51 21572 x 35732 x 0.89
1991 Nov 2	1400?	LAM-3
1991 Nov 3			1436.01 35772 x 35797 x 0.0 GEO 38.0W
1991 Oct		Tests	GEO 38W
1991 Nov 14			1436.12 35673x35900x0.05 GEO 37.00W-0.01/d
1991 Nov		Spot beam malfunction discovered
1992 Jan 27			1436.15 35682 x 35892 x 0.1 GEO 37.2W+0.02W
1992 Feb 16		drifting
1992 Mar		Spot beam repaired
1992 Mar 27		In service
1992 Apr 4		mv in	1436.05 35773 x 35798 x 0.1 GEO 27.6W
1994 Feb 26			1436.12 35783 x 35790 x 0.0 GEO 27.5W
1996 Dec 27			1436.13 35777 x 35796 x 0.0 GEO 27.5W
1997 Oct 8		mv out	GEO 28W
1997 Oct 20		mv in	GEO 34W
1997 Oct 25			1436.04 35777 x 35793 x 0.0 GEO 34.5W
1999 Jun 15			1436.10 35784 x 35789 x 0.0 GEO 34.5W
2002 Jun 28		Move to 32E and then 64E
2002 Jul 11		mv in	1436.13 35783 x 35790 x 0.0 GEO 32.9E
2002 Sep 29		mv out	1436.06 35781 x 35789 x 0.0 GEO 33.0E
2002 Nov 1		mv in	1435.80 35754 x 35806 x 0.0 GEO 64.3E
2003 Sep 2			1436.09 35778 x 35794 x 0.0 GEO 64.3E
2006 Aug 3			1436.01 35780 x 35793 x 1.8 GEO 64.3E
2007 Oct 2		mv out from 63E
2007 Nov 4		Move in 47E
2011 Oct 14			1436.06 35784 x 35787 x 6.5 GEO 47.4E

Estrela do Sul

 2004-001A

---

Loral Skynet do Brasil's Estrela do Sul 1 (EDS-1, Telstar 14) is an LS-1300 with 36 Ku-band tsp and two spot beams. It will operate at 63W. Launch by Zenit-3SL No. 12 with Blok DM-SL No. 9L in 2004 Jan. Also known as Telstar 14; not registered with the UN by the USA, so presumably intended to be registered by Brasil. Mass 4694 kg.

The north solar array failed to deploy completely after launch; only three of five panels deployed. There was some concern a launch vehicle fairing problem might have been the cause, but in 2012 it was discovered that a solar panel manufacturing problem was to blame. The satellite was retired in 2011.

Telstar 14
Date	Time	Event	Orbit
2004 Jan 11	0412:59	Launch by Zenit-3SL No. 12
	0415	T+2:29 St 1 sep
	0416	T+3:13 Fairing sep
	0420	T+7:? St 2 MECO
		T+8:00 Verniers in burn
		T+8:50? St 2 VECO
	0421	T+8:50 St 2 sep	-2222 x 244 x 0
	0421	DM-SL adapter sep
	0422:00	T+9:00 DM-SL MES-1
	0426:31	T+13:35s MECO-1 214 km	180 x 913 x 0
	0501:58	T+49:04 DM-SL MES-2 over Africa
	0508s	T+55:07 MECO-2	756 x 35929 x 0
	0521:41	T+1:08:42 DM-SL sep
		T+6:12:19 Apogee 1	760 x 35786 x 0
2004 Jan 11?		Solar arrays partial deploy
2004 Jan 21			641.09 745 x 35755 x 0.1
2004 Jan 27			811.45 8927 x 35952 x 0.2
2004 Jan 29			956.99 14535 x 36145 x 0.4
2004 Feb 3			1348.65 31381 x 36732 x 0.1
2004 Feb 4	1940?	LAM
2004 Feb 5			1459.59 35728 x 36761 x 0.1 GEO 59.4W+6W/d
2004 Mar 11			1436.12 35777 x 35796 x 0.0 GEO 63.3W
2005 Dec 21			1436.14 35778 x 35796 x 0.0 GEO 63.1W
2006 Aug 3			1436.13 35780 x 35793 x 0.0 GEO 63.1W
2011 Aug 5			1436.11 35768 x 35805 x 0.1 GEO 63.0W
2011 Sep 30		Arrive 109W
2011 Oct 5			1436.14 35775 x 35799 x 0.2 GEO 109.3W
2011 Nov 14			1436.22 35766 x 35811 x 0.3 GEO 109.4W

The Arthur of the Italians: The Arthurian Legend in Medieval Italian Literature and Culture

 https://welib.org/md5/094e8fc2985bf167638e9e480eaf86d2

Spot 7

 2014-034A

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Spot Image/EADS Astrium 2 meter res imaging satellite to replace Spot 5. Launch with CanX-4, CanX-5, and AISat into 1000 LTDN SSO. In Dec 2014, sold to Azercosmos as Azersky; imaging outside Azeri region to continue being marketed by SPOT Image.

SPOT 7/Azersky
Date	Time	Event	Orbit
2014 Jun 30	0422	Launch by PSLV-C23	SHAR
		T+1:50 St 1 sep 53 km 1.55 km/s
		T+1:51 St 2 burn
		T+3:07 Heat Shield sep 131 km 2.257 km/s
		T+4:22 St 2 sep 219 km 3.572 km/s
		T+4:23 St 3 burn 220 km 3.568 km/s
	0430	T+8:41 St 3 sep 537 km 5.3448 km/s
	0430	T+8:51 St 4 burn 546 km 5.331 km/s
	0439	T+17:17 St 4 MECO 659 km 7.521 km/s
	0439	T+17:54 SPOT 7 sep
	0440	T+18:34 AISAT sep
	0441	T+19:03 NLS7.1 CAN X4
	0441	T+19:33 NLS7.2 CAN X5
	0441	T+19:58 VELOX-1 sep
2014 Jul 3			97.77 642 x 660 x 98.3
2014 Jul 4		Begin orbit raising
2014 Jul 5			98.36 679 x 681 x 98.3
2014 Jul 7			98.68 694 x 696 x 98.2
2014 Jul 9			97.71 694 x 699 x 98.2
2014 Jul 16			98.82 696 x 699 x 98.2

Payload:

• 2.2m res pan camera

• Multispectral camera, R, G, B, NIR, 8m res

TanDem-X

 2010-030A

---

Duplicate of TerraSar-X. Mass 1341 kg full 1221 dry, Astrobus platform. Infoterra, an Astrium subsid, will market the data.

T-X
Date	Time	Event	Orbit
2010 Jun 21	0214:08	Launch by Dnepr	KB LC109
		T+4:38 St 2 sep from upper stage
		T+4:42 Fairing sep
		Stage 3 shutdown
	0229:33	T+15:25 Stage 3 sep
2010 Sep		20 km behind TerraSAR-X
2010 Oct 15		Rendevous with TerraSAR-X at 350m
		Co-orbit with TerraSAR-X
2013 Aug 6		Begin orientation swap with TSX

Payload:

• TDX-SAR X-band SAR

• Spotlight mode, 1m res, 5 x 10 km

• Strip map mode, 30 km swath, 3 m res

• Scan mode, 100 km swath, 16m res.

• Propulsion module

• LCT Tesat Laser data relay terminal (EADS/DLR)

• TOR (Tracking Occultation, and Ranging Instrument Package); GPS receiver, laser reflector; GFZ/UoTx

Rein It In: An A Circuit Novel

 https://welib.org/md5/e46982b1aa5704373bb44f2aaec316e9

Town and Country: August 2014

 https://welib.org/md5/5c958503183d09a6799bc5b57960d734

USA-148

 2000-001A

---

This was the first of four Service Life Enhancement Program satellites. Mass is 1232 kg on orbit. Launch by AC-138/MLV-8 with the 11-ft fairing. Two burn to GTO. Station at 175E.

DSCS III B-8
Date	Time	Event	Orbit
2000 Jan 21	0103	Launch by Atlas IIA AC-138	CC SLC36A
		T+2:44 BECO
		T+2:47 Booster sep
		T+3:53 Fairing sep
		T+4:41 SECO
		T+4:43 Atlas sep
		T+5:00 Centaur MES-1
	0113	T+10:07 MECO-1	148 x 899 x 29.3
	0125	T+22:17 MES-2
		T+23:43 MECO-2
	0129	T+26:38 Centaur sep	621.54 240 x 35253 x 26.1
			619.2 234 x 35141 x 26.1 (UN,B)
			628.4 203 x 35550 x 26.2 (UN,A)
2000 Jan 22		IABS burn
2000 Jan 24		Deploy solar arrays
2014 Dec 30			1436.12 35771 x 35802 x 5.3 GEO 149.6E

Camille Flammarion's The Planet Mars: As Translated by Patrick Moore

 https://welib.org/md5/754bf7c531dfb43c3e3bd6bfff7b0430

King Arthur: History and Legend

 https://welib.org/md5/b20ef8a4a66262a9061632efcefea078

Angara A5-IPM

 2014-085A

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The first flight of Russia's new heavy lift launch vehicle, the Angara A5, appears to have been a success. Angara's main stages are powered by LOX/Kerosene engines, more enviromentally friendly than Proton's UDMH/N2O4, and the rocket is launched from Plesetsk rather than Baikonur to lessen Russia's dependence on Kazakhstan for access to space.

The Angara-A5's first stage consists of four strapon URM-1 rockets, powered by RD-191 engines, clustered around the second stage, another URM-1 acting as the vehicle core. After launch at 0557:25 UTC Dec 23 the strapon URM-1 boosters separated at 0600:55 UTC at an altitude of 82 km; the core URM-1 shut down and separated at 0602:55 UTC at an altitude of 148 km, reentering downrange near Tomsk. The nose fairing was jettisoned 10 seconds later. The third stage is a URM-2, powered by the RD-0124A engine; it reached a marginally suborbital trajectory and, after separating from the upper composite section, reentered in the Philippine Sea at a range of 2320 km from the launch site. Meanwhile, the fourth stage, a standard Briz-M (S/N 88801) propelled the stack into a 250 km, 63 deg parking orbit with a burn starting at 0611 UTC. After coasting to the equator, two perigee burns at 0703 and 0926 UTC boosted the apogee to 5000 km and 35800 km respectively, reducing inclination to 60.6 deg. The Briz-M's additional propellant tank was jettisoned into a 433 x 35808 km x 60.6 deg orbit and cataloged as 40355. The payload on this flight was a dummy satellite called the IPM (acronym unknown, but probably meaning something like Test Payload Model) or, according to Novosti Kosmonavtiki, MGM (Massogabaritniy Maketa). The stack coasted to apogee and at 1444 UTC began the 4th burn to enter circular geosynchronous orbit. At 1457 UTC the Briz sent a simulated separation command, but the payload remained attached to the stage as intended. After a few more hours, two burns of the Briz stage's SOZ auxiliary engines moved the stack to a graveyard orbit a few hundred km above GEO.

A5
Date	Time	Event	Orbit
2014 Dec 23	0557:00	Launch by Angara A5	PL
	0600:55	T+3:30 URM-1 (BB) boosters sep 86 km 3027m/s	-5900? x 100?
	0602	T+5:26 URM-1 (TsB) Core sep 159 km 4.807km/s	-4850? x 170?
		URM-1 impact 850 km range, Tomsk region
		T+5:42 Fairing, 169 km, 4.845m/s	-4830? x 175?
		T+5:28 URM-2 start
		Core impact 2320 km range, Tomsk
	0609	T+12:13 URM-2 MECO 215 km 7.145 km/s	-1065 x 220 x 63.15
	0609	T+12:15 St 3 sep
		URM-2 impact 8266 km range, Phliippine Sea
	0610:50	T+13:50 Briz MES-1
	0619:38	T+22:38 MECO-1	250 x 250 x 63
			215 x 215 x 63.18 (NK)
			175 x 190 x 64.6 (Zarya)
	0703:04	T+1:06:04 MES-2 18m?
	0718:04	T+1:21:04 MECO-2	307 x 5007 x 62.00
	0926:00	T+3:29:00 MES-3 18m?
	0941:11	T+3:44:11 MECO-3
	0942:32	T+3:45:32 DTB sep	636.02 444 x 35796 x 60.60
	1444:13	T+8:47:13 MES-4 12m?
	1456:26	T+8:59:26 MECO-4	1436.07 35793 x 35793 x 0.0
	1457:36	MGM simulated sep from Briz
		Planned graveyard orbit	1461.65 35625 x 35946 x 0.44
	1700:50	SOZ-5
	1701:05	SOZ-5 CO
	1812:00	SOZ-6 to graveyard orbit
	1813:40	SOZ-6 CO

Phoenix

 2007-034A

---

The first Mars Scout mission is Phoenix, led by LPL at the University of Arizona. Phoenix SOC will be at Tuscon. Spacecraft is built by Lockheed Martin Astronautics.

Phoenix will land in the north polar region ca. 70N The mission will determine polar climate and weather, and study the role of water and ice on the northern plains. It will carry a robot sampler arm to search for organic molecules. It will use the Mars Surveyor 2001 lander, whose mission was cancelled after the Mars 98 failures. The robot arm can excavate to a depth of 1m.

Launch by Delta II 7925-9.5. Approach Vinf = 3.5 km/s; entry at 5.75 km/s.

Cruise stage (with solar panels), aeroshell, MPL descent system. Operations at new U of Arizona SOC. Lander has 4 RCS and 4 ACS thrusters; they fired through the backshell for cruise operations. 12 landing thrusters each have 31N thrust.

Cruise is 2.64m dia 1.74m high 3.6m span, mass 82 kg.

Lander is 1.8m dia 1m? high disk + 2 panels each 2.0m dia, span 5.5m, total height 2.2m. Launch mass 680 kg. Entry mass 572.7 kg. Mass 524 kg at landing.

Mass budget
Cruise stage	82 kg
Lander cruise prop	25 kg
Back shell	110 kg
Aeroshell	62 kg
Lander dry	343 (363 on surf?)
Lander descent prop	58 kg
Lander descent prop used	38 kg
MP Total		680

Injection at 2255 km, vel 11.0215 km/s, C3 = 29.080, perigee 195.2 km

Planned landing site is 68.35N 233.0E (areocentric), the Green Valley site among the Scandia Colles in Vastitas Borealis. Initial postlanding estimate was 68.22N 234.30E. Pictures of the surface were transmitted via Odyssey one orbit later. Final estimate from MRO is 68.219N 234.248E.

16.9 kg prop left after landing. Parachute 7s later than predicted.

Backshell 90m S of lander, parachute 10m S of backshell.

Heatshield 50m SE of lander.

Phoenix
Date	Time	Event	Orbit
2007 Aug 4	0926:34	Launch by Delta 7925-9.5	CC SLC17A
		T+1:03 SRM 1-6 out
		T+1:05 SRM 7-9 out
		T+1:06 SRM 1-6 sep
		T+2:09 SRM 7-9 out
		T+2:11 SRM 7-9 sep
		T+4:23 MECO
		T+4:31 St 1 sep
	0931:10	T+4:36 SEIG-1
		T+5:03 Fairing sep
	0935:54	T+9:20 SECO-1	166 x 167 x 28.5
	1040:21	T+1:13:47 SEIG-2
	1042:36	T+1:16:02 SECO-2	162 x 5793 x 28.5
	1043:39	T+1:17:05 Stage 2 sep	148.41 163 x 5651 x 28.5
	1044:16	T+1:17:42 TES
	1045:44	T+1:19:10 TECO
	1050:39	T+1:24:05 Yo-yo despin
	1050:44	T+1:24:10 Stage 3 sep
	1054:16	T+1:27:42 Target interface point	195 x -40365 x 28.5
			193 x -40716 x 28.41 (Horizons)
	1718	Pass EL1:4
2007 Aug 6	0830	Leave Earth SOI (0.93Mkm)
2007 Aug 7	1336	Depart Earth sphere 1.5Mkm
		Mars miss distance 950000 km
2007 Aug 10	1830	TCM-1 18.5m/s 3:17
2007 Oct 24		TCM 46s 3m/s
2008 Apr 10		TCM 35s
2008 May 18	0045	TCM-5, 3s burn
2008 May 21	0924	Enter Mars sphere 1.082Mkm
2008 May 23	1345	Enter Mars SOI (0.58Mkm)
2008 May 25	2330?		-22 x -18951 x 69.72
	2323:40s	E-7 min Cruise separation
		E-5min Turn to entry
	2331:13	E-0s Entry 125 km, 5.7 km/s, gamma = -12
		5.6 km/s at -13.01 deg 77.7 az 197.7,69.36 124.5
	2334:50	E+228s Para deploy 13 km
	2335:03	E+236s Heat shield jettison 12 km
		E+261s Radar on
	2335:14	E+246s Leg deployment
	2338	E+405s Lander sep from backshell, 0.9 km
		Backshell Avoidance Manuever
		E+444 Throttle up
		E+465s Radar cutoff
	2338:39	E+446s Reconstructed landing time
	2338:24	E+470s Landing
		L+25min Solar array deploy
2008 Oct 27		Dust storm
2008 Nov 2		Last transmission
2009 May 25		end of ops

Payload:

• MARDI Descent imager (Malin)

• SSI Surface Stereoscopic Imager, Stereo Panoramic cameras (Arizona/Shinohara)

• Mass spectrometer

• RA Robotic arm - Trench digging arm, 2.4m (JPL/Bonitz) with ISAD (Icy Soil Acquisition Device).

• RAC Robotic arm camera (MPI-SolarSystem-Lindau/Arizona/Keller,Smith)

• TEGA Thermal evolved Gas Analyser (Arizona/UTD/Boynton)

• MECA Chemistry-microscopy instrument: (JPL/Hecht) optical and atomic force microscopes, wet chemistry lab for soil analysis

• TECP Electrical and thermal conducivity sensor probe (on arm)

• MET Meteorology lab (CSA,York/Whiteway); zenithal lidar, temperature/pressure station

Raduga 2010

 2010-002A

---

This launch appears to have been a 4-burn launch, with the earlier burns 3 and 4 combined and the DTB ending up in a true GTO rather than the intermediate orbit used previously.

Raduga 1M
Date	Time	Event	Orbit
2010 Jan 28	0018:00	Launch by Proton-M/Briz-M
		T+2:06 St 1 sep
		T+3:03 GO sep
		T+5:30 St 2 sep
	0027	T+9:34 St 3 MECO
		T+9:44 Stage 3 sep
	0029	T+11:19 ?Briz MES-1
	0036	T+18:55? MECO-1	173 x 173 x 51.49
	0126?	T+1:08? MES-2
	0143?	T+1:25? MECO-2	273 x 4991 x 48.8
	0348?	T+3:30? MES-3
	0404?	T+3:46? MECO-3
	0406?	T+3:48? DTB sep	408 x 35568 x 46.5
			415 x 35534 x 46.49
	0907?	T+8:52? MES-5
	0912?	MECO-5
	0916	Briz-M sep
2010 Jan 28			1436.00 35772 x 35797 x 0.1 GEO 55.4E
2010 Feb 3			1425.71 35535 x 35630 x 0.0 GEO 71.5E+2.6E/d
2010 Mar 8			1436.09 35775 x 35797 x 0.0 GEO 85.0E
2013 Jun 14			1436.10 35772 x 35801 x 0.0 GEO 85.0E