Eutelsat W4

 2000-028A

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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

College Life 201: Sophomore Studies

 https://welib.org/md5/a8940aff0ff2e5b35707c9b90a07c9fd

Cluster 1

2000-041A

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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

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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

Kepler

 2009-011A

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Kepler is a search for Earth-sized planets with orbital periods less than two years by transit photometry, studying a single field with 1E5 stars at 1941+349, l,b=69.6+5.7 covering the lower half of Cygnus between gamma and beta. between M29 and M56, for four years. It was selected as a Discovery mission in Dec 2001.

Kepler carries a 0.95-meter aperture Schmidt telescope with a 1.4-meter primary mirror and a 12 degree field of view, with an array of 42 CCD cameras each 2200 x 1024 pixels. The images from each star are intentionally defocussed to a resolution of 10 arcseconds for added precision; the system can monitor the 4000-8500A brightness of magnitude 14 stars every 15 minutes to less than 100 micromag. At least 50 Earth-sized planets are predicted to be found.

The mission depends on the assumption that most stars are like the Sun in that they don't vary much on timescales of minutes to hours.

Kepler will download its photometric data once a week to the Deep Space Network.

NASA-ARC PI; built by Ball.

Mass is 1052 kg including 12 kg of hydrazine. Size is 2.7m dia 4.7m long. Launch by Delta 7925-10L into solar orbit with 371 day period.

20 ppm in 6.5 hr at V=12. Detect Earths to 1AU around targets.

Dust cover ejection 7.5 or 7.74kg 1.1m/s 1.7 x 1.4m.

In 2013 a 10 day safemode was used to protect the degrading reaction wheels.

Kepler
Date	Time	Event	Orbit
2009 Mar 7	0349:57	Launch by Delta 7925-10L	KSC SLC17B
		T+1:03 GEM 1-6 out
		T+1:06 GEM 7-9 on
		T+1:06 GEM 1-6 sep
		T+2:08 GEM 7-9 out
		T+2:11 GEM 7-9 sep
	0354	T+4:23 MECO
		T+4:29 VECO
		T+4:31 St 1 sep
		T+4:36 SEIG-1
		T+4:41 Fairing sep
	0359:53	T+9:56 SECO-1 185 x 185 x 28.5
	0443:07	T+53:10 SEIG-2
	0444:10	T+54:13 SECO-2	174 x 2815 x 28.55 (s)
	0445	Stage 2 sep
		109.85 166 x 2273 x 28.56
	0445:30	T+55:33 TES
	0446:57	T+57:00 TECO 202 km
	0451:40	T+1:01:43 Yo-yo deploy
	0451:45	T+1:01:48 Stage 3 sep
	0455:30	T+1:05:33 Target point 1530 km	184.3 km, C3=0.60
	0655	Pass GEO	185 x -1372167 x 28.54
2009 Mar 7		SES-3
		SECO-3 depletion	2246 x 7360 x 28.55
	1733	Pass EL1:4
2009 Mar 9	0436	Pass lunar orbit
2009 Mar 14	0339	Range 929000 km, leave Earth sphere
2009 Mar 20	1140	Range 1.49E6 km
	1236	Booster leaves Earth sphere
2009 Apr 8	0218	Dust cover ejected Range 3.1Mkm
2009 Apr 20	0000	Range 4.5M km	0.967 x 1.041 AU x 0.5 deg
2013 Jan 17		Begin 10 day safemode

Payload:

• Kepler telescope-photometer, 1m Schmidt

After Apollo? : Richard Nixon and the American Space Program

 https://welib.org/md5/9c37a816d6d9542c5c5b5d91e6a5a785

USA-147

 1999-067A

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The first 5D-3, S-15 (F-15 after launch) launched by Titan II in Oct 1999. It was placed in a 0915/2115LT orbit, later than earlier missions to help tactical operations. F-15 replaced F-12 and F-14 in one of the two DMSP planes. S-15 used the 5D-3 bus but carried the old 5D-2 payload complement.

By the time 5D-3 was launched, DMSP was operated by NOAA although managed by USAF SMC. NOAA SOCC/Suitland, MD checks out the spacecraft. It's turned over to the NPOESS IPO (Nat. Polar Orbiting Env Satellite System Integrated Program Office), which delegates operations back to the NOAA OSO (Office of Satellite Operations). Mass was 1030 kg. Size was 7.3m long.

According to Jane's Spaceflight Directory, the 5D-3 was intended to carry a "Star 37FP" apogee motor with a 19 percent offload. This may be the same as the Star 37XFP.

DMSP F-15
Date	Time	Event	Orbit
1999 Dec 12	1738:01	Launch by Titan II	V SLC4W
		T+2:45 Stage 1 sep
		T+4:00? Fairing sep
	1743:41	T+5:40 Stage 2 MECO
	1744:15	T+6:14 Stage 2 sep
	1751:38	T+13:37 Star 37 burn
	1752:29	T+14:28 Star 37 burnout
	1757:31	T+19:30 Solar array deploy
	1805?	Stage 2 reentry
1999 Dec 19			101.81 837 x 851 x 98.9
2003 Nov		Secondary status
2006 Aug 14		orbit adjust
2007 Apr 29			101.69 833 x 843 x 98.5
2007 Jul		Still operating
2016 Mar		Secondary operational sat at 0240 LT