STS-116 (Discovery)

 2006-055A

---

STS-116 will dock with the ISS on mission 12A.1. Launch mass is 120413 kg, landing is 102217 kg.

Sunita Williams will transfer to the Ex14 crew, joining Lopez-Alegria and Tyurin. Tomas Reiter joins the STS-116 crew.

Discovery's RMS is used to unberth the P5 spacer and hand it to the SSRMS. On EVA-1 (Quest), Curbeam and Fuglesang help install P5 to P4. Then, the port half of the P6 array, side 4B, is powered down and retracted and a TCS is filled with NH3. P3/P4 SARJ solar tracking is now activated. P1-3A DDCU-E thermal covers are removed.

P6 carries 2B and 4B power channels; P4 has 2A and 4A. S4 has 1A/3A, S6 has 1B/3B.

Now, US Segment is configured to get power from P4-2A and P6-4B via MBSU 2 and 3 and EATCS Loop B.

Then, P6 4B is deactivated and US segment is configured for power via P4-4A and MBSU 1 and 4, via EATCS Loop A. S1-4B and S0-4B DDCU-E thermal covers removed.

On EVA-2, Curbeam and Fuglesang reroute power channel 2/3 through the MBSUs. The MBSUs need the ammonia TCS to be working. During this work, channel 1/4 is carrying the load for the entire ISS.

On EVA-3, Williams and Curbeam route power channel 1/4 through their MBSUs while the station runs off channel 2/3.

At last, the P4 arrays will be activated. MT will be moved to the S1 end of the truss. to await S3/S4.

Finally, the SMDPs and adapter are transferred to PMA-3 aft GF.

After undocking, the STP-H2 payloads will be deployed.

According to Spacehab, LSM is 5399 kg full 2858 kg empty. ICC is 839 empty, with 1657 kg of payload. TA is 112 kg. STS 116 cargo transfer MD to ISS 592 kg plus 140 kg consumables, SHAB to ISS 1620 kg; ISS to MD 610 kg, ISS to SHAB 1617 kg.

STS-116
Date	Time	Event	Orbit
2006 Nov 1		Roll to VAB
2006 Nov 9		Roll to LC39B
2006 Dec 7		Scrub WX
2006 Dec 10	0147:35	Launch	KSC LC39B
	0149:39	SRB sep
	0149:49	OMS ASS
	0151:27	OMS ASS CO
	0155:58	MECO
	0156:19	ET sep	58 x 220 x 51.6
	0224:42	T+38:11s OMS-2 57.3m/s 124s
	0226:44	OMS-2 CO	220 x 250 x 51.6
	0316:09	PLBD open
	0436:42	OMS-3 T+2:49:07 NC1 OMS both 30.8m/s 1:07	250 x 335 x 51.6
	0437:47	OMS 3 CO
	1845:14	T+16:57:39 NC2 OMS-4 both 36s 17.2m/s 112642 kg	293 x 348
	1845:50	OMS 4 CO
	1912	Grapple OBSS
2006 Dec 11	0120?	Reberth OBSS
	0130?	Ungrapple OBSS
	0444:18	NC3 RCS 111907 kg
	1756:32	OMS 5 NC4 OMS 16s
	1756:48	OMS 5 CO
	1831	NCC RCS 0.2m/s
	1912	Tally-ho ISS 15 km
	1928:22	OMS-6L TI 2.6m/s single OMS-L, 11s, 111448
	1928:33	OMS 6 CO
	1948	MC1, 3s 0.8m/s
	2010?	Out of plane tweak
	2039	MC3
	2048	MC4 0.3m/s rdot is 1m/s
	2116	-Rbar 120m
	2128	+Vbar 110m
		Approach PMA on +Vbar
	2158	At 20m
	2204	At 10m
	2205	Begin final approach
	2211:55	Soft dock with PMA
	2225	Retracted
	2354	HO, bell rung
2006 Dec 12
	0100?	Suni Williams IELK transfer
	0118	RMS grapple P5
		SSRMS is at end of truss (W7?)
	0225	Unberth P5
	0318?	SSRMS grapple P5
	0324	RMS ungrapple P5
		EVA-1 from Quest: Curbeam, Fuglesang
	2022	2 psi
	2024	0.8psi
	2026	Airlock depress (JCM)
	2028	26mm, 0.6psi
	2030	HO
	2031	Battery power
	2040?	Egress
		Translate to P5; remove launch locks
	2208	Contact between P5 and P4
	2217	P5 soft dock
	2243	P5 bolted, still tightening
	2245	SSRMS ungrapple P5; SSRMS at W7? or W8?
	2320	P5 work complete
	2330	Remove GF for stowage on truss
2006 Dec 13	0015	GF stowed on MBS
	0115	Moving to S1
	0205	New S1 camera installed
	0245	Fuglesang loses PGT extension socket
		Return to airlock
	0258	Curbeam ingress
	0300?	F ingress
	0302	HC
	0307	Repress
	0400?	MT moves from W8 to W3
	1828	P6 SAW-4B wing retract begins
		P6 retract stopped at 17.5 bays
2006 Dec 14		EVA-2
	1923	3.5 psi
	1932	1.0 psi
	1935	Depress
	1940	Hatch open
	1941	Battery power
	1957	Egress Curbeam
	2000?	Egress Fuglesang
		Rewire MBSU, DDCU
2006 Dec 15
	0019	Curbeam ingress
	0029	Fuglesang ingress
	0033	TC closed
	0038	HC
	0041	Repress
2006 Dec 16
	1919?	1.4 psi
	1923?	Depress complete
	1924?	HO
	1925	Battery power?
	1934	Egress Curbeam
	1940	egress williams
	2112	Reconfiguration complete
		Ready to install SMDP
	2139	SW on arm heading to bay
	2148	SW unberth bundle 4
	2150?	Bundle 4 on adapter
	2200	SW unberth bundle 3
	2208	Bundle 3 on adapter
	2220	Bundle 2 unberthed
	2226	Bundle 2 on adapter
	2230	Unberth SMDP adapter
	2255	Install adapter on PMA3
	2325	Digital camera floats loose from S Williams
	2350	Install AGB grapple bar on ESP
2006 Dec 17	0021	Translating to P6
	0050	Shaking P6
	0144	Retract 1 bay
	0230	Down to 11 bays; run out of time
	0245?	Ingress
	0252	HC
	0256	Repress 7:31 (NASA)
2006 Dec 18
		EVA-4 Curbeam, Fuglesang
	1855	Depress
	1859	HO
	1900	Battery power
	1908	Egress Curbeam
	1915	Egress Fuglesang
		Translate to P6
		Using tool to free up stuck SAW panels
	2328	At 1-bay position
	2356	Retract complete, but guide wire loose
2006 Dec 19	0034	SABB latched
	0050	Fixing SSRMS elbow insulation
	0120?	Ingress Fuglesang
	0128	Ingress Curbeam
	0135	HC
	0138	Repress
	1942	Hatches to ISS closed
	2209:19	Undocking
	2236	At 120m on Vbar, begin flyaround
	2248	On +R bar, 200m
	2257	On -V bar?
	2259	Sep-1 burn
		Sep-2 burn
2006 Dec 20	0011:46	Sep-3 OMS 11s
	0011:57	OMS-7 CO
2006 Dec 21
	0019:50	MEPSI
	0156:44	RAFT/Marscom deploy
	1822:47	ANDE canister deploy
	1823:29	ANDE canister top from middle sep
	1823:35	NRL FCAL separate from top can
	1823:36	ANDE MAA fails to sep from lower can
	1823:36	Center disk separate from lower can
	1852:35	RCS burn (ANDE sep) 106829 kg 0.6m/s 8s
2006 Dec 22
	1719:14	PLBD closed
	2127:05	OMS DO for KSC203 3:46 117.3m/s
	2130:53	OMS DO CO	33 x
	2159:55	EI
	2231:59	MGTD 12:20:44:24 KSC RW15
	2232:12	NGTD
	2232:52	WS
2006 Dec 23	0330	Roll to OPF3

Progress MS-04

 2016-F02

---

MS-04 carried 2442 kg of cargo including 710 kg prop, 420 kg water, 52 kg O2, 1260 kg dry cargo. Launch mass was 7285 kg.

The stage 3 engine failed in some way, possibly due to a turbopump fire, and the third stage disintegrated. The Progress then prematurely separated from the third stage debris, but the stage then hit the Progress twice. The debris of stage and payload fell to Earth in the Tuva republic.

MS04
Date	Time	Event	Orbit
2016 Dec 1	1451:52	Launch by Soyuz-U	KB LC1
	1456:40	Blok-A sep, Blok-I burn
	1458:14	T+6:23 Loss of contact with rocket at 181 km
	1459:16	Progress separation
	1459:50	Loss of contact with Progress
		Debris impact Tuva (Choisky District)

IGS-4

 2009-066A

---

Third Optical satellite launched by H-IIA F16. It was rumoured in Jan 2010 that the satellite had failed to operate but a 2014 CSICE diagram showed its primary mission concluding in that year.

Kougaku 3 gouki.

IGS O3
Date	Time	Event	Orbit
2009 Nov 28	0121	Launch by H2A F16	TNSC LP1
		T+1:40 SRB-A burnout
		T+1:47 SRB-A sep
		T+4:20 4S? PLF sep
	0127	T+6:35 St 1 MECO
		T+6:43 St 1 sep
	0127	T+6:49? Stage 2 burn
	0136?	T+15? SECO
	0140?	Payloads separate
			96.0 587 x 601 x 97.7 (UN)
2014		Primary mission complete
2015		Reserve status

July 12,2016

 https://planet4589.org/space/jsr/back/news.728.txt

The New Girl

 https://welib.org/md5/1cd13817f58a2de2ccb4b650a64642d5

The International Atlas of Mars Exploration: 1953 to 2003

 https://welib.org/md5/f3fdeacb57e213260342df2b7c22b7f8

COROT

 2006-063A

---

COROT (Convection, Rotation and Planetary Transits), a CNES satellite for astroseismology and extrasolar planet transit photometry search, using the Proteus bus. 600 kg mass. Launch mid 2006 by Soyuz-2-1b No. 001 from Baykonur within 14D23 upper stage engine and Fregat No. 1013 fourth stage and S (4m) fairing. ESA provides the 0.30m telescope. There are two 0.27m afocal off-axis parabolic mirrors.

Launch mass 626 kg. (605 kg PK). Size 4.10m long 1.98m dia. Box-cyl + 2 panels. Height 9m in orbit. Span unknown.

Prop system with 90m/s delta-V. The telescope is by LAM/Marseille, the detector by LEISA/Paris-Meudon. Control from Toulouse. Spacecraft by Alcatel Alenia Space/Cannes.

After a successful mission the science operations ended in 2012. The spacecraft's orbit was lowered in Jan 2014 and the vehicle was decommissioned in Jun 2014.

COROT
Date	Time	Event	Orbit
2006 Dec 27	1423:38	Launch by Soyuz-2-1b	KB PL31/6
	1425	T+1:55 Strapons sep
	1428	T+4:47 Blok A sep
	1428	T+4:48 KhO sep
	1428	T+4:49 GO sep
	1432:52	T+9:14 Blok I MECO	214 x 226 x 90.0
	1432:55	T+9:17 Blok I sep
	1433	Fregat MES-1
	1434:30	MECO-1	218 x 950? x 90.0
	1511	Fregat MES-2
	1512:54	End Fregat second firing
	1513:00	T+50:02 Separation of Corot	103.01 893 x 908 x 90.0
	1824	Fregat depletion
	1850?	Fregat reentry
2009 Mar		Instrument side 1 fails
2012 Nov 2		Science instrument side 2 failure, end of sci mission
2013 Jan		Spacecraft still transmitting
2013 Jun 24		COROT to be switched off, begin end ops
		Orbit lowering planned
2013 Sep 1			102.98 895 x 903 x 90.0
2014 Jan 7			102.76 877 x 901 x 90.0
2014 Jan 12		Orbit lower	101.52 754 x 907 x 90.0
2014 Jan 14		Orbit lower	101.41 753 x 896 x 90.0
2014 Jan 15		Orbit lower	100.83 697 x 897 x 90.0
2014 Jan 20		Orbit lower	100.30 648 x 897 x 90.0
2014 Jan 23		Orbit lower	99.85 605 x 896 x 90.0
2014 Jan 29		Orbit lower	99.82 604 x 895 x 90.0
2014 Jun 17		End of ops per ST/SG/SER.E/756
2014 Jul 15			99.79 600 x 896 x 90.0

Payload:

• COROT telescope

• Focal unit, with 4 2048 x 4096 CCDs in the 3700-9500A range, and dioptric f=1200mm objectiv

Xinnuo 3

 2007-021A

---

CAST DFH-3 satellite, Sinosat-3 (Xinnuo 3) Acquired by China Telecom in 2010 and renamed Zhongxing 5C, moved to 163E. In 2011, acquired by Eutelsat and moved to 1.6E to the ITU-registered F-Sat-Ku-E-1.6E location [947], but shortly afterwards moved to 3.0E and renamed Eutelsat 3A. It later moved to 8W before retirement.

Sinosat 3
Date	Time	Event	Orbit
2007 May 31	1608	Launch by CZ-3A	XSC
		T+2:25 Stage 1 MECO
		T+2:27 Stage 2 MES, Stage 1 sep
		T+3:52 Fairing sep
		T+4:15 St 2 MECO
		T+4:20 St 2 VECO
		T+4:21 St 2 sep, St 3 MES
	1618	T+10:19? St 3 MECO-1	200 x 200 x 28.5?
	1628?	MES-2
	1630?	MECO-2
	1632	St 3 sep
2007 May 31			753.42 194 x 41904 x 25.1
2007 Jun 16			1436.10 35779 x 35793 x 0.3 GEO 125.1E
2010 Apr 6			1436.10 35776 x 35796 x 0.0 GEO 125.0E
2010 Oct 20			GEO 125E
2010 Oct 20?		Moved to 163E
2010 Nov 1			1436.29 35780 x 35799 x 0.1 GEO 163.0E
2010 Dec 14			1436.11 35779 x 35794 x 0.0 GEO 163.0E
2010 Dec 28		Move out
			1441.51 35869 x 35915 x 0.2 dr 1.4W/d
2011 Apr 20		Move in at 1.5E
2011 Apr 30			1436.16 35779 x 35796 x 0.1 GEO 1.6E
2011 Jul 9		Move from 1.5E to 3.0E
2011 Jul 13			1435.78 35771 x 35799 x 0.1 GEO 3.0E
2014 Jun 30			1436.12 35786 x 35787 x 0.1 GEO 3.3E
2014 Jul 4		Move out from 3E
2014 Jul 27		Move in at 8W
2014 Jul 28			1436.91 35786 x 35818 x 0.2 GEO 7.9W
2014 Nov 2			1436.09 35764 x 35808 x 0.4 GEO 7.9W

ST-1

 1998-049A

---

The Singapore-Taiwan-1 (ST-1) satellite (Singasat) is a Eurostar 2000+ built by Matra Marconi Space/France. It was launched by Ariane 44P. The project is a joint venture between Singapore Telecom (SingTel) and Chunghwa Telecom of Taiwan. Mass is 3255 kg full, 1753 kg BOL, 1502 kg dry. Size is 2.5 x 1.7 m x 2.9m The satellite was stationed at 88E, raising concerns about conflicts with the nearby Chinastar.

In 2001, SingTel also absorbed the Optus satellite system. The satellite was relocated in 2013 to 125E and then moved again.

ST-1
Date	Time	Event	Orbit
1998 Aug 25	2307	Launch by Ariane 44P (V-109)
		T+1:11 SRM sep
		T+3:32 St 1 sep
		T+3:35 St 2 burn
		T+4:28 Fairing sep
		T+5:44 St 2 sep
	2312	T+5:49 St 3 burn
	2326	T+19:01 St 3 cutoff
	2327	T+20:33 St 3 sep
1998 Aug 26			632.42 295 x 35759 x 3.9
1998 Aug 27	1230?	LAM-1
1998 Aug 27			776.80 7491 x 35736 x 1.8
1998 Aug 28	1420?	LAM-2
1998 Aug 29			1166.88 24937 x 35967 x 0.3
1998 Aug 30	0500?	LAM-3
1998 Aug 31			1430.92 35420 x 35950 x 0.2 GEO 84.0E+1.3E
1998 Sep 21			1436.09 35755 x 35817 x 0.0 GEO 88.0E
1998 Dec 2			1436.12 35779 x 35794 x 0.0 GEO 88.0E
1999 Oct 16			1436.12 35777 x 35795 x 0.0 GEO 88.0E
2006 Aug 3			1436.10 35771 x 35802 x 0.0 GEO 88.0E
2013 Jan 16		Move out 88E	1436.11 35771 x 35802 x 1.2 GEO 88.1E
2013 Apr 9		Move in 125E	1436.03 35769 x 35801 x 1.4 GEO 124.9E
2013 Jul 20			1436.14 35770 x 35804 x 1.6 GEO 124.8E

Cluster 2

2000-045B

---

Cluster FM8, C4 is launched with FM5 on the second dual Soyuz-Fregat launch. Mass 1186 kg launch, 550 dry.

Cluster FM8
Date	Time	Event	Orbit
2000 Aug 9	1113:35	Launch by Soyuz-Fregat
	1116:34	Strapons sep
	1117	Fairing
	1119	Blok-A sep
	1119	Blok-I burn
		Fairing sep
		Blok-I underburn
		Blok-I MECO	SO x 64.8
	1122	T+8:48 Blok-I sep, 217 km
	1122	T+8:50? Fregat burn 1 3:45
	1126?	Fregat MECO-1	200 x 200 x 64.8
		Fregat MES-2
		Fregat MECO-2
	1243?	Fregat sep, alt 1000 km
		FM8 sep from FM5
2000 Aug 10	0853	LAM-1	239 x 23199 x 64.9
2000 Aug 11	0458	LAM-2	240 x 33997 x 64.9
2000 Aug 12	0019	LAM-3
2000 Aug 12	1636?	LAM-4
2000 Aug 13	1658	Inc mvr
2000 Aug 15	s	Rendezvous
2000 Oct 25		Begin boom deploy
2000 Nov	s	Complete boom deploy
2001 May 10		Manuevers begin
2003 Jun 4			18699 x 119082 x 89.5
2006		Move to along-track sep from C3
2010 Jul 21	1911	TCM
2010 Jul 30	2016	TCM
2010 Aug 8			1856 x 130941 x 129.6
2011 Nov 15			1089 x 131679 x 140.9
2012 Jan 31			1644 x 131141 x 141.6
2012 Oct 3			4325 x 128464 x 140.16
2012 Oct		Orbit adjust
2012 Oct 12			8124 x 128639 x 130.64
2013 Jul 15		New close formation
2013 Jul 27			8897 x 123909 x 136.75
2013 Aug 30	0037	Closest pass of 9.1 km to C1
2014 Jun 17			14857 x 118216 x 133.6

2000-045A

---

The Cluster Flight Model 5 satellite was refurbished after the Ariane 5 failure to become Project Phoenix. It was renamed Rumba. It was launched with Cluster FM8 on a Soyuz in Jul 2000. into a 250 x 250 km x 51.8 deg orbit. A Fregat kick stage raises the orbit to 250 x 18000 km x ?. Then the satellites separate from the kick stage and use their S400 engines to get to the 4 x 19.6 Re orbit. 25500 x 125000 km polar.

Mass of Cluster/Fregat at Blok I sep is 7847 kg. After MECO-1 mass is 6810 kg.

The Blok I suffered an 3.5s underburn,possibly due to the stage having too little fuel loaded. The Fregat made up the difference. A report said that the second Fregat burn went till depletion, but other indications are that the Fregat did make a third deorbit burn since Space Command tracked it with a negative perigee after apogee.

Cluster FM5 was known after launch as Rumba and as C1.

Cluster FM5
Date	Time	Event	Orbit
2000 Aug 9	1113:35	Launch by Soyuz-Fregat
	1116:34	Strapons sep
	1116:41	Fairing
	1119	Blok-A sep
	1119	Blok-I burn
		Fairing sep
		Blok-I MECO 3.5s early	-1301 x 206 x 64.8
	1122:21	T+8:48 Blok-I sep
	1122:29	T+8:54 Fregat burn 1 (MDU burn for 3:28)
	1123:21	MDU on (3:28)
	1126:50	Fregat MECO-1	186 x 202 x 64.8
	1134?	Blok I reentry
	1228:04	T+1:14:29 Fregat burn 2
	1229:00	Fregat MDU MES-2
	1237:20	T+1:24:10 Fregat MECO-2	251 x 17075 x 64.9
	1242:59	sT+1:29:51 Fregat sep, alt 1000 km
	1243:09	sT+1:30:01 FM5/FM8 sep
	1510	Fregat apogee
	1510:15	T+3:56:41 Fregat deorbit
	1513:32	T+3:59:21 Fregat MECO-3	-157 x 17075 x 64.9
	1741:44	Fregat reentry 21:28S 70:06W
		(Chile coast)
2000 Aug 10	1359	LAM-1	239 x 23199 x 64.9
2000 Aug 11	0340	LAM-2	240 x 33997 x 64.9
2000 Aug 11	2335	LAM-3
2000 Aug 12	1630?	LAM-4
2000 Aug 13	1655	Inc mvr	17200 x 120600 x 90
2000 Aug 15	s	Rendezvous
2000 Sep 7		Boom deploy begin to 15m
2001 May 10		Manuevers begin
2010 Jul 21	1923	TCM
2010 Jul 30	2037	TCM
2010 Sep 2	1901	TCM
2010 Sep 7	0736	TCM
2013 Jul 15		New close formation
2013 Jul 31			12280 x 120510 x 139.4
2013 Aug 30	0037	Closest pass of 9.1 km to C4
2013 Sep 19	1112	Closest pass of 5 km to C3
2015 Mar 11			22016 x 110774 x 135.6

True Prep

https://welib.org/md5/d8b4fb2c5b691b75aefb9ade7b45c4d4

Crowded Orbits : Conflict and Cooperation in Space

 https://welib.org/md5/5eec9c0261c9dcdc87a9c8555cc5a7b6

DirecTV 1R

 1999-056A

---

DIRECTV Inc. satellite (DirecTV-1R). HS-601HP to supplement DBS series at 101W. Total power 7.5kW. Mass 3447 kg. Launch by Zenit-3SL from 154W 0N.

In Oct 2012 DTV-1R was transferred to 56.16E for RSCC (Kos. Svyaz) services in inclined orbit, backing up the Bonum 1 satellite.

DirecTV 1-R
Date	Time	Event	Orbit
1999 Oct 10	0328:00	Launch by Zenit-3SL	Odyssey
		T+2:26 Stage 1 sep, 76 km
		T+3:16 PLF sep, 116 km
	0337	T+9:05 Stage 2 sep, 200 km	-2220? x 200 x 1
	0337	T+9:15 DM-SL burn 1, 200 km
	0344	T+16:41 DM-SL MECO, 193 km	184.0 180 x 8495 x 0.6
	0417:55	T+49:55 DM-SL burn 2, 4323 km
	0421:04	T+53:04 DM-SL MECO-2, 4800 km
	0429:14	T+1:01:14 DM-SL sep
1999 Oct 11			682.13 2827 x 35753 x 0.6
1999 Oct 12	1830?	LAM-1
1999 Oct 12			842.48 10582 x 35758 x 0.8
1999 Oct 13	2230?	LAM-2
1999 Oct 13			1296.90 30242 x 35789 x 0.2
1999 Oct 15	1830?	LAM-3
1999 Oct 15			1406.04 34609 x 35782 x 0.1
1999 Oct 16	1930?	LAM-4
1999 Oct 17			1435.59 35763 x 35789 x 0.1 82.0W+0.1E
1999 Oct 26			1436.11 35781 x 35792 x 0.1 GEO 81.6W
1999 Nov		Control to DirecTV
1999 Nov 9			1436.11 35780 x 35792 x 0.0 GEO 81.6W
1999 Nov		Relocate to 101W
1999 Nov 28			1436.10 35785 x 35788 x 0.0 GEO 101.2W
2002 Jul 3			1436.08 35774 x 35797 x 0.0 GEO 101.2W
2002 Sep		Move to 100.8W
2002 Oct 24			1436.10 35777 x 35795 x 0.0 GEO 100.8W
2006 Aug 3			1436.09 35778 x 35794 x 0.0 GEO 100.8W
2007 Mar 10		Move out of 100W
2007 Apr 10		Move in at 72.5W
2012 Jan 9			1436.11 35776 x 35797 x 0.1 GEO 72.5W
2012 Jan		Move from 72.5W to 109.8W
2012 Jan 12		Mv out	1438.11 35813 x 35838 x 0.1 GEO 74.0W+0.5W/d
2012 Mar 24		Mv in	1436.14 35777 x 35797 x 0.3 GEO 109.8W
2012 Sep 1			1436.09 35770 x 35802 x 0.6 GEO 109.8W
2012 Sep 13		Move out, drift E
2012 Sep 20			1429.21 35631 x 35671 x 0.6 GE 94W+1.7E/d
2012 Oct		Lease to RSCC for Bonum services
2014 Apr 9			1436.08 35777 x 35795 x 1.5 GEO 55.9E
2014 Apr 30			1436.07 35775 x 35796 x 1.5 GEO 55.9E

The Hubble Space Telescope: From Concept to Success

https://welib.org/md5/235b8300e032911db880f50027eb16bf

Get More (A Boy Shopping Novel)

 https://welib.org/md5/935b1c1cd8c40ef01ef9624c2b5c64aa

Ofeq 11

 2016-056A

---

\uni{ אופק }{ }

11

Possibly OPSAT-2000 (like previous Ofeq sats) or a new OPSAT-3000 satellites.

Times based on earlier missions. Launch was reported to be around 1430 UTC; Russian sources (in particular the Novosti Kosmonavtiki forum) reported 1438 UTC.

O11
Date	Time	Event	Orbit
2016 Sep 12	1438?	Launch by Shavit	Palmachim
		Stage 1 MECO at T+0:52
	1439?	Stage 1 sep
		Stage 2 MECO at T+1:44,
	1440?	Stage 2 sep, 110 km
	1445?	Fairing (2 pieces) sep, 250 km
	1445?	Main equipment compartment sep
	1446?	Stage 3 92s burn over W Med.
	1447?	Stage 3 sep	250 ? x 600? x 141?

The Swans of Fifth Avenue

https://welib.org/md5/f43c09724831a5e59fc76426f17d5d15

Eutelsat W1

 2000-052A

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Launch mass is 3250 kg. Dry mass is 1430 kg. Size is 2.5 x 3.4 x 5.0m, 8.0m high deployed, Span 31.7m. Stage 3 plus VEB has a mass of 2190 kg. Launch due 2000 Sep to 10E to replace 2F4.

Eutelsat W1 will occupy the 10E orbital slot. The first Eutelsat W1 satellite, an Alcatel Spacebus 3000, was damaged in a fire in the Cannes factory in 1998. Construction of a second Eutelsat "W1R", another Spacebus 3000, was begun as well as a ground spare, called Ressat, built by Matra Marconi Space/Toulouse (now part of the Astrium company) and using a Eurostar 2000+ bus. This second Eutelsat W1 was reassigned to become Eurobird, and will be launched to 28E, with Ressat becoming the third and final Eutelsat W1. This satellite, the Eurostar 2000+, was the one launched on Sep 6. Its mass is 1430 kg, with a further 1820 kg of propellant at launch for its Primex R-4D liquid apogee engine. The box-shaped 2.5 x 5.0 m satellite has two rectangular solar panel arrays spanning 31.7m and two dishes, a European beam and a steerable beam. The payload includes 28 Ku-band transponders.

The satellite was named Eurobird 4A at some point, probably in June 2009.

Eutelsat W1
Date	Time	Event	Orbit
2000 Sep 6	2233	Launch by Ariane 44P V132	CSG ELA2
		T+1:12 PAL sep
		T+3:33 St 1 sep
		T+3:34 St 2 TIG
		T+4:26 Fairing 01 sep
		T+5:44 St 2 sep
		T+5:47 St 3 TIG
		T+10:30 v=5.8	-3200 x 300
		T+12:00 v=6.3	-2300 x 300
		T+13:10 v=6.8	-1300 x 300
		T+14:30 v=7.33	289 x 350
		T+15:35 v=7.81	285 x 2400
		T+16:30 v=8.2	287 x 5000
		T+18:00 v=9.1	306 x 15000
	2251	T+18:49 St 3 MECO
		T+19:30 v=9.6	300 x 31530
	2253	T+20:09 W1 sep
		T+20:14 St 3 sep burn
		T+21:38 V132 mission complete
2000 Sep 8			632.94 313 x 35769 x 7.0
2000 Sep 8		LAM-1	800.26 8604 x 35744 x 2.9
2000 Sep 9		LAM-2	1321.61 31271 x 35758 x 0.2
2000 Sep 11?		LAM-3
2000 Sep 19			1436.19 35774 x 35802 x 0.1 GEO 1.6E
2000 Oct 14			1430.39 35619 x 35730 x0.0 GEO 13.0E+1.4E
2000 Oct 21		Move in at 10.0E
2000 Nov 19			1436.10 35669 x 35903 x 0.1 GEO 10.0E
2005 Aug 10		Attitude control problem
2005 Aug 11		problem fixed
2006 Aug 1			1436.07 35767 x 35805 x 0.1 GEO 10.0E
2009 May 28			1436.14 35770 x 35804 x 0.0 GEO 10.1E
2009 Jun 1		Move out
2009 Jun 5		Move in at 4E
2009 Jun 11			1436.08 35774 x 35798 x 0.1 GEO 4.0E
2012 Feb 9			1436.08 35758 x 35814 x 0.4 GEO 4.0E