Jason 1

 2001-055A

---

The TOPEX-Poseidon Follow On mission, Jason (retrospectively Jason-1), is built by Aerospatiale and is the first use of the Proteus satellite bus. [113], [114]  [115]. It is a joint CNES/NASA/JPL project. It uses a C/Ku band radar altimeter. A microwave radiometer corrects for signal delay by measuring H2O and wind-related variations in sea surface emission. Mass is 506 kg and launch will be by Delta 7920-10 along with TIMED.

Proteus is developed by CNES in collaboration with Aerospatiale. Shape is box + 2 panels. 1.9 x 1.9 x 3.3m with about 5.0m span. Carries 28 kg of hydrazine.

In Apr 2002, commanding was transferred from CST to JPL, although CNES continued to support engineering and navigation.

In 2012 the satellite was preemptively moved to its final orbit; it continued operating, completing a nominal 406 day gravity mission. The spacecraft was turned off on 2013 Jul 1.

Jason
Date	Time	Event	Orbit
2001 Dec 7	1507:35	Launch by Delta 7920-10C	V SLC2W
		T+1:26 SRM 1-6 sep
		T+2:11 SRM 7-9 sep
		T+4:23 MECO 161km 5.665 km/s
		T+4:37 SES-1
		T+4:41 Fairing sep
	1517:40	T+10:05 SECO-1	215 x 1343 x 66.18
		T+51:25 SES-2 285m/s 24s
	1559:24	T+51:49 SECO-2	1320 x 1330 x 66.04
	1602:55	T+55:20 Jason sep
	1607:15	T+59:40 DPAF sep
	1613:57	T+1:06:22 SES-3
	1614:39	T+1:07:04 SECO-3	636 x 1330 x 71.32
	1706:11	T+1:58:36 SES-4
	1706:51	T+1:59:16 SECO-4	627 x 640 x 74.09
	1712:35	T+2:05:00 TIMED sep
		T+2:08:20 Cold gas evasive maneuver
		T+2:37:30 SES-5
	1745	T+2:37:47 SECO-5 depletion	187 x 630 x 76.8
2002 Jan 10		TCM to operational orbit	1337 x 1337
2002 Mar 16		Small debris hit, two objects ejected
2002 Apr 26		Ops from CNES to JPL
2012 Mar 3		out of service
		Leave altimetry reference orbit
		Lower orbit, partial service
2012 May 4		Resume ops	1323 x 1323
2013 Jul 1		end of ops

Payload:

• GPS receiver (NASA)

• LRA Laser Retroreflector Array

• DORIS Doris antenna for orbit location

• POSEIDON Poseidon 2 altimeter 1.2m dia, 13.6 and 5.3 GHz

• Microwave Radiometer (JPL), 18.7, 23.8 and 34.0 GHz

Inmarsat 304

 1997-027A

---

The Ariane V97 flight was pushed ahead when V96 was rolled back to the assembly building after a payload delay. Inmarsat 3 F4 launch mass was 1999 kg. BOL mass 1149 kg, dry 895 kg. It was 3.2 x 2.3 x 2.1 m in size with 7.6 m height deployed and 20.7m span.

Inmarsat III F4
Date	Time	Event	Orbit
1997 Jun 3	2320	Launch by Ariane 44LP V97	CSG ELA2
	2323	Stage 1 sep T+3:32
	2324	Fairing sep T+4:48
	2325	Stage 2 sep T+5:42
	2338?	Stage 3 MECO
	2341	H10-3 sep from Inmarsat T+21:17
	2344	Mini Spelda top sep T+24:17
	2346	H10-3 sep burn
			201 x 35745 x 7.0
1997 Jun 4			630.28 204 x 34741 x 7.0
1997 Jun 5			630.30 217 x 35728 x 7.0
1997 Jun 6	0940?	AKM
1997 Jun 10			1432.70 35611 x 35829 x 0.2 GEO 22.5E+0.8E
1997 Jun 13			1434.77 35688 x 35863 x 0.2 GEO 24.9E+0.3E
1997 Jun 25			1436.17 35770 x 35805 x 0.3 GEO 28.0E
1997 Jun 30		mv out
1997 Aug 1		mv in	1436.08 35771 x 35800 x 0.3 GEO 53.8W
1997 Aug		In service as AOR West
1997 Oct 31			1436.15 35773 x 35802 x 0.1 GEO 54.0W
1999 Oct 17			1436.12 35772 x 35802 x 0.0 GEO 54.0W
2006 Feb 1			1436.16 35766 x 35809 x 0.0 GEO 54.0W
2006 Feb 1		Move out of GEO
2006 Apr		Arrive 142W
2006 Aug 4			1436.11 35748 x 35825 x 0.1 GEO 142.0W
2008 Sep 28			1536.09 35769 x 35804 x 0.1 GEO 142.1W
		Move out
2009 Jan 10		Move in AOR-W	1436.08 35768 35804 x 0.1 GEO 54.0W
2013 Aug 1			1436.11 35767 x 35806 x 3.1 GEO 54.0W
2016 Apr 4			1436.18 35766 x 35810 x 5.0 GEO 54.4W

Atlantic Bird 1

 2002-040A

---

Satellite is an Alenia Spazio GeoBus. Eutelsat 12.5W sat to complement Eu1F5. Replace EuIIF2 currently at this slot. Alenia Spazio is contractor and delivers on orbit. Eutelsat leased the satellite from ALS SpA until 2006. 

Mass 2700 kg full 1550 kg dry. Size 2.1 x 2 x 2.8m with 19m span.

Launch by Ariane 5 in 2002 with Ariane Short Fairing and Sylda 5C. The flight also carried ballast in the form of an MFD (Modular Fitting Dummy), a cylinder between the EPS and the payload adapter. MFD-500 is 650 kg 2.6m dia and 0.5m (MFD 500); MFD-325 is 575 kg and 0.325mm (MFD 325) high. Two MFD500 were carried on this flight.

The EADS press kit gives identical EPC target orbit parameters to the previous launch, which is likely an error.

AB1
Date	Time	Event	Orbit
2002 Aug 28	2245	Launch by Ariane 513/V155	CSG ELA3
		T+2:23 EAP sep
		T+3:17 Fairing sep
	2254:36	T+9:36 EPC MECO
	2254:42	T+9:42 EPC Sep	55 x 2006 x 7.2
	2254:49	T+9:49 EPS MES
	2311:30	T+26:30 EPS MECO
	2313:04	T+28:04 AB1 sep
	2316:45	T+31:45 Sylda 5 sep
	2321:12	T+36:12 MSG 1 sep
2002 Aug 29	0030?	EPC reentry
2002 Aug 31			642.62 647 x 35931 x 6.0
2002 Sep 3?		LAM
2002 Sep 5			1417.00 3454 x 35869 x 0.0
2002 Sep 8			1436.04 35724 x 35847 x 0.0 GEO 12.5W
2006 Aug 8			1436.09 35781 x 35791 x 0.0 GEO 12.5W
2012 Mar 1		Renamed EUTELSAT 12 West A
2015 Dec 17			1436.09 35767 x 35805 x 0.1 GEO 12.3W
2015 Dec 20		Move out
2016 Jan 30		Move in	1436.08 35782 x 35789 x 0.1 GEO 36.0W
2016 Jan 30?		Renamed EUTELSAT 36 West A
2016 Mar 6			1436.12 35775 x 35798 x 0.1 GEO 36.0W

Yearbook on Space Policy 2012/2013 : Space in a Changing World

 https://welib.org/md5/3e2e37cf90be5d3a07ceb108bf825e17

XSS-11

 2005-011A

---

XSS-11 Experimental Satellite System will be a 100 kg microsat built by LMA/Denver for the AFRL as a 'Davis-class' space demonstration mission. XSS-11 will demo autonomous on-orbit operations with minimal intervention from the ground. The experiment is part of NASA's Space Technology 6 project and of STP. Launch by Minotaur in Nov 2004. Customer was SMC Det 12.

In Sep 2005 it was announced that XSS-11 had completed several rendezvous operations with its final stage.

XSS-11
Date	Time	Event	Orbit
2005 Apr 11	1335	Launch by Minotaur	V SLC-8
		T+1:05? Stage 1 sep, Stage 1 burn
		T+2:15? Stage 2 sep, Stage 3 burn
		T+2:27? Fairing
		T+ 3:30? Stage 3 burnout
		T+10:30? Stage 3 sep
	1345	T+10:40? Stage 4 burn
	1346	T+11:50? Stage 4 burnout
	1348?	Stage 4 sep	102.1 847 x 873 x 98.8
2005 Jul		(late) Rendezvous with Stage 4, 1.6km
		Image stage 4
		Sep burn
2005 Aug		Rendezvous 2
2005 Aug		Rendezvous 3
2005 Aug?		Rendezvous 4? to 0.5 km
2005 Nov 9		Rendezvous to 0.3 km?
2006 Jan 22			102.05 846 x 865 x 98.9
2006 May			100.15 756 x 774 x 99.2
2006 Aug 11		Rendezvous with DMSP-5D2 F6

Sicral 1A

 2001-005A

---

Sicral (Sistema Italiano per Comunicazioni Riservate e di Allarme) is the first Italian military commsat. It was built by the SITAB consortium of Alenia Spazio, FiatAvio and Telespazio. It will be stationed at 16E and carries beams for Italy, Europe and the Mideast. Sircal is operated by the Segretariato Generale della difesa/direzione nazionale degli armamenti (DNA) of the Ministero della Difesa.

FiatAvio built the propulsion system, although it may have an R4D engine.

Control from Centro di Controllo e Gestione, Vigna di Valle.

Based on Italsat/Artemis bus. Mass is 2596 kg full 1253 kg dry. Size is 2.8 x 3.4 x 4.9m with 24.5m span.

Sicral
Date	Time	Event	Orbit
2001 Feb 7	2306	Launch by Ariane 44L	CSG ELA2
		T+2:28 PAL sep
		T+3:32 St 1 sep
		T+3:35 St 2 TIG
		T+4:02 Fairing sep
		T+5:44 St 2 sep
		T+5:48 St 3 TIG
	2325	T+19:16 St 3 MECO
	2326	T+20:55 SICRAL sep
	2328?	Spelda sep
	2331	T+25:53 Skynet 4F sep
2001 Feb 8			631.06 222 x 35763 x 7.0
2001 Feb 9	1200?	LAM-1
2001 Feb 9			715.69 4507 x 35744 x 4.3
2001 Feb 10	1200?	LAM-2
2001 Feb 10			840.49 10495 x 35751 x 2.4
2001 Feb 20	1030?	LAM-3
2001 Feb 20			1426.87 35445 x 35766 x 0.1
2001 Feb 27			1426.84 35444 x 35765 x 0.1
2001 Apr 4			1436.11 35769 x 35803 x 0.1 GEO 16.1E
2006 Aug 3			1436.05 35772 x 35799 x 0.1 GEO 16.1E
2006 Oct		Control lost due to solar activity
2007 Nov?		Control regained
2007 Dec		Returned on station
2013 May 22			1436.10 35770 x 35802 x 4.7 GEO 16.3E
2013 May		Move out
2013 May?		Move in?
2013 Aug 2			1436.12 35769 x 35804 x 4.8 GEO 37.0E
2014 Apr 11			1436.12 35766 x 35808 x 5.3 GEO 37.1E
2014 May 2			1436.12 35755 x 35818 x 5.3 GEO 34.5E
2014 May		Move out
2014 Jul		Moved to register Lux-G6-6 GovSat slot
2014 Jul 4			1436.12 35768 x 35805 x 5.5 GEO 21.8E
2014 Aug 7			1436.14 35763 x 35811 x 5.6 GEO 21.8E
2014 Dec 31			1436.06 35759 x 35812 x 5.8 GEO 22.2E
2015 Sep 10			1436.12 35772 x 35801 x 6.3 GEO 21.8

XM-1 (Roll)

 2001-018A

---

XM-1 Roll was a Boeing 702 satellite.

Solar panels are 40.4m span. 4667kg launch 2940 kg BOL. 7.0 x 3.3 x 3.0m, in size.

DM-SL is 3407 kg dry, 4,9m l 3.7d.

 

XM-1
Date	Time	Event	Orbit
2001 Jan 5		Arrive at 154W 0N
2001 Jan 8	2235	Abort T-11s
2001 May 5		Arrive at 154W 0N
2001 May 8	2210:29	Launch by Zenit-3SL
		T+2:23 St 1 MECO
		T+2:25 St 1 sep
		T+2:31 St 2 MES
		T+3:29 PLF sep
		T+7:21 St 2 MECO
	2219:05	T+8:36 St 2 sep	-2137 x 191 x 1.25
		T+8:46? DM adapter jettison
		T+8:46 DM MES1
	2223:50	T+13:21 DM MECO1	180 x 990 x 1.25
	2258	T+48:28 DM MES2 6:06
		T+54:33 DM MECO2	902 x 35922 x 1.25
	2315:42	T+1:05:13 DM sep
2001 May 11	1030?	LAM-1
2001 May 14			710.24 1238 x 38744 x 1.3
2001 May 14		LAM-2
2001 May 14			832.86 7157 x 38733 x 0.8
2001 May		LAM-3
2001 May 16			1094.57 18894 x 38714 x 0.1
2001 May 18	1815?	LAM-4
2001 May 18			1405.35 31653 x 38712 x 0.1
2001 May 20	1630?	LAM-5
2001 May 21			1431.80 32693 x 38712 x 0.1
2001 Jun 5			1437.65 34011 x 37623 x 0.1
2001 Jun 29			1436.10 35785 x 35788 x 0.0 GEO 85.1W
2005 Apr 11			1436.14 35782 x 35792 x 0.1 GEO 85.2W
2005 Apr 26		Relocate to 115W
2005 May 13			1436.09 35766 x 35796 x 0.0 GEO 115.0W
2006 Aug 3			1436.13 35783 x 35791 x 0.0 GEO 115.0W
2015 Oct 16			1436.07 35767 x 35805 x 0.1 GEO 115.2W

The Right People : The Social Establishment in America

 https://welib.org/md5/0f7099af963bdae1ca05e832439413ff

The Soyuz Launch Vehicle: The Two Lives of an Engineering Triumph

 https://welib.org/md5/f2ad06fb35ba2c99c0b98bd12204c10a

BEAM

 2016-024

---

BEAM, Bigelow Expandable Activity Module, 1413 or 1578 kg, 3.7m l 3.2m dia; 1.75m high 2.36m dia packed. Delivered to ISS aboard Dragon CRS-8 and installed on Node 3 aft.

BEAM
Date	Time	Event	Orbit
2016 Apr 16	0500?	SSRMS grapple BEAM
	0600?	SSRMS unberth BEAM
	0620	BEAM out of CRS-8 trunk
	0900	BEAM next to N3
	0921	Ready to latch
	0937	Berthed on N3 aft (Stage 2 capture)
2016 May 25		N3 HO to BEAM vestibule opening
2016 May 26		Expand attempt, small motion 96 in to 111 in
2016 May 28	1305	113in Introduce 22s air
	1313	8s air
	1338	3s air
	1352	1s air
	1443	1s air
	1510	5s air
	1525	3s air
	1620	1s? air, 32 in long 118 dia
	1644	2s air
	1652	2s air (try 13, 54s total), 34 x 118
	1712	1s air, 35 x 119
	1724	1s air, 37 x 119
	1748	1s air 38 x 120
	1808	1s air 39 x 120
	1825	1s air 40 x 120
	1853	2s air 41 x 120
	1918	42 x 120
	1936	8s air 56 x 123
	1943	10s air (try 21) 59 x 125
	1946	14s air 63 x 127
	1950	15s air 66 x 127
	1955	30s air 66.5 x 127
	2003	9s air 67 x 127
	2010	Manual expansion declared complete
	2034	Begin pressurization
	2044	Pressurization complete
2016 Jun 6	0847	Williams and Skripochka entry

Eutelsat W4

 2000-028A

---

W4 is an Alcatel Spacebus 3000B2 ordered late 1997. It will fly to 36E and provide coverage of Russia (19 transponders) and sub-Saharan Africa. Its transponders are slightly lower power than W2 and W3, but it has more of them. Launch by first Atlas 3A, with 14' fairing.

Launch mass 3190 kg. The Centaur 3A has an RL10A-4-1B single engine. BOL mass around 1900 kg? Dry mass is 1285 kg.

Date	Time	Event	Orbit
2000 May 24	2310	Atlas 3A AC-201	CC LC36B
		T+3:02 RD-180 BECO
		T+3:13 Atlas sep
		T+3:23 RL10 nozzle extended
		T+3:31 Centaur 3A MES-1
		T+3:39 Fairing sep
		T+12:15 MECO-1	188 x 486 km x 26.8
		T+22:39 MES-2
		T+26:15 MECO-2
	2338	T+28:53 Centaur sep	835.37 230 x 45777 x 19.9
2000 May 26	1030?	LAM-1	940.93 5100 x 45759 x 11.1
2000 May 28	0930?	LAM-2	1338.02 21888 x 45800 x 2.4
2000 May 31	0430?	LAM-3 (?)	1620.47 32872 x 45771 x 0.2
2000 Jun 1	0700?	LAM-4	1397.03 34163 x 35873 x 0.1
2000 Jun 3	1230?	LAM-5	1434.60 35497 x 36017 x 0.1
2000 Jun 13			1436.06 35784 x 35787 x 0.1 GEO 32.0E
2000 Jul 11		Arrive at 36E
2000 Aug 12			1436.07 35774 x 35797 x 0.0 GEO 36.0E
2006 Aug 3			1436.07 35773 x 35798 x 0.1 GEO 36.1E
2012 Mar 1		Renamed EUTELSAT 36A
2016 Feb 21			1436.07 35768 x 35803 x 0.1 GEO 35.9E
2016 Feb 25		Move out
2016 Apr 4		Move in 70E
2016 May 18			1436.10 35760 x 35813 x 0.2 GEO 70.5E

Cluster 1

2000-041A

---

Cluster FM7 (C3) was launched with FM6.

Each of the 4 wire booms extends to 43m long.

In early 2001, the vehicles studies the polar cusp. In May 2001, the spacecraft began to increase their separation distance from 600 to 2000 km, to study larger features in the magnetotail.

In Feb 2004, the Cluster spacing was 250 km to study small structures.

In early 2007 the spacing was 450 km between Samba and Tango, and 10000 km to Rumba and Salsa. The spacing was shrunk further and on 2007 Jun 20, Samba and Tango reached a 17 km separation.

Cluster FM7
Date	Time	Event	Orbit
2000 Jul 16			321.30 250 x 18072 x 64.68
2000 Jul 17	1121:01	Burn 1	422.67 245 x 24311 x 64.88
2000 Jul 18	0833	Burn 2	616.81 241 x 35007 x 65.10
2000 Jul 19	0515	TCM-3 10 min	241 x 57010 x 65.1
2000 Jul 19	2325	TCM-4 10 min	246 x 119523 x 64.9
2000 Jul 21	0004	TCM over VILSPA	16869 x 121098 x 90
2000 Oct		Boom deploy
2001 May 10		Manuevers begin
2006		C3 and C4 moved to similar orbits
2010 Jul 21	1923	TCM
2010 Jul 30	2040	TCM
2010 Sep 2	1919	TCM
2010 Sep 7	0754	TCM
2013 Jul 15		New close formation
2015 Nov 1		Samba burn to move closer to Tango
2015 Nov		Samba and Tango within 4 km

Payload:

• WBD Wideband data analyser, E field to 100 kHz

• EFW Electric field and wave, 50 m antennae

• STAFF Spatio temporal analysis of field fluctuation

• FGM Fluxgate magnetometer

• EDI Electron drift instrument

• PEACE Plasma electron and current experiment

• CIS Cluster Ion spectrometer

• RAPID Research with adaptive particle imaging detectors

• WHISPER Waves of high frequency and sounder for probing of electron density by relaxation;

• DWP Digital wave processor

• ASPOC Active spacecraft potential control experiment.

2000-041B

---

Cluster FM6/C2 is the first of three brand-new replacement Cluster satellites. It was launched with FM7 in Jun 2000.

Cluster has 4 50-m wire antennae, two 5-m rigid booms, 2 axial comm antenna booms. 550 kg dry, 650 kg prop, 1.3 h, 2.9dia. The spacecraft spins at 50 rpm.

Fregat had thrust of 19.6 kN with Isp of 328.5s. Taking the upper values, a 3:45 initial burn corresponds with a prop burn rate of 19.6/3.22 = 6.08 kg/s to 1367 kg. The 9:42 second burn is 3538 kg for a total fuel use excluding deorbit burn of 4905 kg. In fact the nominal prop load was 5350 kg for Fregat,

Mass 6450 full 1100 kg dry, with payload 2400 kg.

Burn 1: 8850 to 7483 kg Est Dv = 540 Burn 2: 7483 to 3945 kg Est Dv = 2061 Actual Dv = 1940? Burn 3: 1545 to 1100 kg Est Dv = 1094

So the burn 2 values agree quite well.

Actual info found in another doc for mission 2

Burn 1: 7837 to 6810 kg est DV = 452 Burn 2: 6810 to 3840 est DV = 1845 Burn 3: 1440 to 1261 est DV = 427, actual DV less

In May 2001, the spacecraft began to increase their separation distance from 600 to 2000 km.

Note that the early TLE orbit data for FM6 and FM8 are swapped.

Cluster FM6
Date	Time	Event	Orbit
2000 Jul 16	1239:34	Launch by Soyuz/Fregat	KB
	1241:34	Strapons sep
	1242	Fairing
	1244:24	Blok-A sep
	1244:24	Blok-I burn
		Fairing sep
		Blok-I MECO	SO x 64.8
		T+8:48 Blok-I sep	-1120? x 217 x 64.8
	1249	T+8:50? Fregat burn 1 3:45
	1251	Fregat MECO-1	217 x 217 x 64.8
	1257?	Blok I reentry
	1355:42	T+1:15:00 Fregat burn 2, 9:42
	1403	Fregat MECO-2	251 x 18050 x 64.8
	1410	S+0 FM7 sep
	1410	S+10s FM6 sep
2000 Jul 16			321.54 259 x 18078 x 64.81
2000 Jul 16	1640?	Fregat deorbit at apogee
2000 Jul 16	1916?	Fregat reentry	-47? x 18058 x 64.8
2000 Jul 17	1121:00	Apogee raise 1, 10:33
	1131		424.06 247 x 24390 x 64.89
2000 Jul 18	0828	Apo raise 2	625.10 261 x 35417 x 65.10
2000 Jul 19	0508	Apo raise 3	250 x 56677 x 64.9
2000 Jul 19	2259	TCM-4	246 x 119523 x 64.9
2000 Jul 20	2302	TCM-5 18min over PERTH	16869 x 121098 x 90.5 (ESA)
2000 Jul 20		ASPOC and CIS covers open
2000 Jul 22			16714 x 121090 x 90.48
2000 Sep 5		Boom deploy begin to 15m
2000 Sep 11	s	Deploy to 35m
2000 Sep 20	s	Deploy to 43m
2001 May 10		Manuevers begin
2006		Move to tetrahedral config
2010 Jul 20	2020	TCM
2010 Jul 30	2035	TCM
2010 Aug 5	1555	TCM
2010 Aug 12	1055	TCM
2010 Aug 20	0441	TCM
2010 Sep 2	1821	TCM
2010 Sep 7	0655	TCM
2016 Feb 2		TCM