Yaogan 1

 2006-015A

---

SAST Remote Sensing (Yaogan) satellite, mass 2700 kg. Thought to be a radar satellite. Also called Yaogan Weixing, YW-1.

Yaogan
Date	Time	Event	Orbit
2006 Apr 26	2248	Launch by CZ-4C	TY
	2250	T+2:32? St 1 sep
	2250	St 2 burn
	2250	T+2:47? Fairing sep
	2254	T+6:48? Stage 2 MECO
	2254	T+6:49? St 2 sep
		Stage 3 burn 1
	2258?	Stage 3 MECO 1
	2300?	Stage 3 sep	601 x 621 x 97.8
		Stage 3 MES-2 depletion
		Stage 3 MECO-2	452 x 624 x 97.8
2006 Apr 29			97.03 606 x 626 x 97.8
		Orbit raise	97.21 623 x 626 x 97.8
2006 May 10			97.28 628 x 629 x 97.8

The Clique

 https://welib.org/md5/c72c6f2e7048fe62738c30de363672a2

TD-1A

  1972-014A

---

The TD-1A satellite was ESRO's first astronomy satellite, the TD standing for Thor Delta (the launch vehicle). It was built by Matra and controlled from the ESOC facility, TD-1A made the first ultraviolet stellar sky survey. The early loss of the satellite’s tape recorders meant that extra tracking stations were pressed into service.

TD-1A
Date	Time	Event	Orbit
1972 Mar 12	0155:08	Launch by Delta N	V
		SRM sep
	0158:45	T+3:37 MECO
		T+3:39 St 1 sep
	0158:48	T+3:40 SES-1 6:21
		T+3:56 Fairing sep
	0205:03	T+9:55 SECO-1
	0245:36	T+50:28 SES-2
	0245:40	T+50:32 SECO-2
	0247	T+52:07 Delta sep	95.4 524 x 551 x 97.6
1972 Mar 15		1-m optics cover ejected
1972 Apr 19		No.2 tape recorder problem
1972 May 23		No.1 tape recorder failed
1973 Oct		S59 and S2/68 switched off; S77 on
1973 Dec		S2/68 back on for airglow
1974 May 5		end of stabilization
1975?		end of transmissions
1980 Jan 9		Reentered

International Reference Guide to Space Launch Systems

https://welib.org/md5/311482cc6e9678bbc038791fba99af5c

The Perfect Manhattan

https://welib.org/md5/80f1e14af28837008e8016064bb3b2d9

TDRS-3

 1988-091B

---

The TDRS C payload was named TDRS 3 on reaching orbit. TDRS 3 was carried into space on the first `return to flight' mission, STS-26R. Discovery was launched on 1988 Sep 29 and the TDRS/IUS was deployed at The first IUS burn, at 2250 on Sep 29, left TDRS in a 632.98 min, 287 x 35797 km x 26.71 deg orbit. The second burn, at 0406 on Sep 30, put it in a 1433.48 min, 35673 x 35798 km x 2.3 deg circular orbit. By Oct 5 it had reached the TDRS WEST position at 171 W. In around 1992 it was moved to 62W as TDRS SPARE, but in 1994 it was reassigned to move back to the TDRS WEST position.

TDRS 3
Date	Time	Event	Orbit
1988 Sep 29	1537:00	Launch from LC39B
	1539:05	SRB sep, 46.3 km
	1545:33	MECO, 110.0 km	88.03 65 x 289 x 28.5 (PK)
	1545:50	ET sep, 111.9 km	88.21 69 x 302 x 28.5 (OMS dV)
	1616:56	OMS-2 (2:21) 68m/s	90.55 299 x 304 x 28.5
	1619:18	OMS-2 CO
	2100?		90.55 300 x 303 x 28.5
	2150:04	TDRS deploy
1988 Sep 29	2250:04	IUS-7 SRM-1
	2252:33	SRM-1 burnout
	2257:33	RCS-1
	2257:53	RCS-1 end
1988 Sep 29			632.98 287 x 35797 x 26.7
1988 Sep 30	0356:49s	SRM-2 exit cone deploy
1988 Sep 30	0402:29s	SRM-1 sep
1988 Sep 30	0406:48	IUS SRM-2 1:49
	0408:37	IUS SRM-2 burnout
	0412:18?	RCS-2 burn 1:37
	0413:55?	RCS-2 burn end
	0421?	TDRS solar array deploy
	0444:50s	SRM-2 sep
	0450?	IUS SRM-2 CAM burn
	0451?	IUS SRM-2 RCS depletion burn
1988 Sep 30			1433.48 35673 x 35798 x 2.3
1988 Sep 30			1434.75 35718 x 35803 x 0.1
1988 Oct 1			1435.07 35722 x 35811 x 0.1 GEO 178.1W+0.25E/d
1988 Oct 4			1424.40 35554 x 35561 x 0.1 GEO 172.3W+3E/d
1988 Oct 18		mv in	1436.50 35785 x 35803 x 0.0 GEO 149.5W
1988 Nov 29			1436.11 35772 x 35801 x 0.0 GEO 151.1W
1988 Dec 13			1436.01 35769 x 35801 x 0.1 GEO 151.0W
1988 Dec 21		mv out
1989 Jan 16		mv in	1436.23 35776 x 35801 x 0.2 GEO 171.1W
1989 Jan		TDRS W	171W
1990 Apr 16			1436.02 35777 x 37593 x 0.1 GEO 171.0W
1990 May 2		Drift to 174W
1990 May 16			1436.16 35774 x 35801 x 0.0 GEO 174.1W
1991 Jan 27			1436.07 35777 x 35794 x 0.7 GEO 174.4W
1991 Oct 7			1436.02 35565 x 36005 x 0.0 GEO 173.9W
1991 Oct 8		mv out
1991 Nov 3			1424.64 35555 x 35568 x 0.1 GEO 99.7W+2.9E
1991 Dec 10		mv in	1436.01 35771 x 35798 x 0.1 GEO 62.2W
1992 Jan		TDRS SPARE	62W
1992 May 10			1436.13 35776 x 35797 x 0.5 GEO 61.9W
1993 Aug 4			1436.21 35774 x 35803 x 0.3 GEO 61.9W
1994 May 16			1436.00 35777 x 35792 x 1.0 GEO 61.8W
1994 May 22		mv out
1994 Jul 13			1442.44 35899 x 35921 x 1.1 GEO 153.7W+1.5W
1994 Jul 30		mv in TDRS W	1436.18 35779 x 35797 x 1.1 GEO 171.3W
1995 Mar 29			1435.95 35772 x 35795 x 1.6 GEO 171.0W
1995 Apr 22		mv out
1995 May 29		mv in	1436.21 35768 x 35809 x 1.7 GEO 85.2E
1998 Mar 8			1436.01 35770 x 35799 x 3.7 GEO 85.0E
1999 Jun 13			1436.11 35771 x 35802 x 4.6 GEO 85.4E
2003 Sep 5			1436.23 35779 x 35799 x 7.6 GEO 84.5E
2006 Jul 23			1436.12 35710 x 35863 x 9.7 GEO 85.1E

Private Secondary Schools 2004-2005

 https://welib.org/md5/7e489181a4ff937330f0d09230e657a9

Spaceflight: November 2006

 https://welib.org/md5/9499fe2cd2c14b942ac6ee268ecb15da

Soyuz TM-33 (Derbent)

 2001-048A

---

The EP-2 crew of Afanas'ev (Kdr), Kozeev (BI-2) and Claudie Haignere (BI-1) were launched in Soyuz 207 (Soyuz TM-33) in Oct 2001.

Soyuz TM-33
Date	Time	Event	Orbit
2001 Oct 21	0859:35	Launch by Soyuz-U	KB
	0901:31	T+1:55 SAS sep
	0901:34	T+1:59 St 1 sep
	0902:18	GO sep
	0904:23	T+4:47 St 2 sep
	0904:35	T+5:00 KhO sep
	0908:21	T+8:46 St 3 MECO
	0908:24	Blok I sep
	1243:31s	TCM-1 27.1m/s
	1315:54s	TCM-2 16.7m/s
2001 Oct 23	1021	At 155m, already in flyaround
	1031	At 100m
	1033	Switch to Zarya Kurs
	1040	Final approach, 42m
	1044:15	Docking at Zarya nadir
	1216	Hatch open
2002 Apr 20
	0730	HC
	0916	Undock from Zarya nadir
	0924	Stationkeep at 160m
	0931	Aligned with Pirs
	0937	Docked with Pirs, 21 min
	1025	HO
2002 May 4		Crew Gidzenko, Vittori, Shuttleworth
	2250?	HC
2002 May 5	0031:08	Undocked from Pirs
	0032?	Sep burn
	0101	At 'several hundred m'
	0225		374 x 396 x 51.6
	0257:27	DO 4 min 252.4s 115.2m/s
		DO over 47S 56W
	0301:39	DO complete	-1 x 380 x 51.59
	0321?	BO, PAO sep
	0351:53	Landed

Iridium 76

 1998-048B

---

This satellite was launched with SV3 in the first CZ-2 replenishment mission in Aug 1998. The satellite reached operational altitude by then end of April and was still in the constellation in 2004.

Iridium SV76
Date	Time	Event	Orbit
1998 Aug 19	2301:46	Launch by CZ-2C/SD from TY
		T+2:02 Stage 1 MECO
		T+2:03 Stage 1 sep, Stage 2 burn
		T+3:50 Fairing
		T+5:02 Stage 2 MECO
	2311:57	T+10:11 Stage 2 VECO
	2312:00	T+10:14 Stage 2 sep	92.91 179 x 654 x 86.37
	2349:54	T+48:08 SD burn
	2350:30	T+48:44 SD burnout	97.16 616 x 629 x 86.4
	2351:49	T+50:03 SD sep
	2355:40	T+53:54 SD deorbit burn	92.70 195 x 618 x 86.32
1998 Aug 20			97.18 617 x 630 x 86.4
1998 Aug 25			98.71 694 x 699 x 86.4
1998 Aug 28			100.39 775 x 778 x 86.39
1998 Aug 31			100.41 775 x 779 x 86.40
2004 Feb 14			100.40 776 x 779 x 86.40

Progress M-57

 2006-025A

---

Mass 7283 kg including 1167 kg of prop and fluids. Mass at docking 7000 kg. 11F615A55 No. 357 spacecraft, launch by 11A511U-PVB No. Zh15000-101. Vehicle 357, Flight 22P.

PM57
Date	Time	Event	Orbit
2006 Jun 24	1508:18	Launch by Soyuz-U	KB LC1-5
		T+1:58 Strapons sep
		T+2:42 Fairing sep
		T+4:45 Blok A MECO
		T+4:47 Blok-A sep
		T+4:57 KhO sep
		T+8:45 Blok-I MECO
	1517:07	T+8:49 Blok-I sep	140 x 220 x 51.3
	1859:09	DV1 22.4m/s 56s SKD	235 x 270 x 51.6
	1941:49	DV2 12.1m/s 31s SKD	255 x 280 x 51.6
2006 Jun 25	0924		255 x 271 x 51.6
	1606:07	DV3 1.3m/s 4.6s SKD	256 x 281 x 51.6
2006 Jun 26	1432:52	DV4 7.7m/s 23s SKD
	1455:32	DV5 1.1m/s 28s DPO
	1518:53	DV 23.8m/s 62s SKD
	1600:11	DV 8.0m/s 28s SKD, range 3 km
	1605:25	DV 5.4m/s 63s DPO, range 1 km
	1608:24	DV 2.5m/s 35s DPO, range 630m
	1610	Range 390m
	1615	Range 159m, lined up with Pirs
	1616	Auto approach
	1624:36	Docked with Pirs	335 x 349 x 51.6
2006 Jun 28			91.38 335 x 349 x 51.6
2007 Jan 16	2329:12	Undocked from Pirs
	2332:13	Sep burn 15s	328 x 371 x 51.6
2007 Jan 17	0229:00	Deorbit 174s 87 m/s
	0231:59	DO CO
	0303:28	Reentry
	0309:17	Breakup at 70 km over 35 26S 144 53W
	0315:20	Impact in Pacific 41 18S 135 47W

Soyuz TMA-2 (Agate)

 2003-016A

---

Soyuz TMA-2 was spacecraft No. 212 for mission ISS 6S. Following the loss of Columbia, a new Expedition 7 station crew was assigned with commander Yuriy Malenchenko and NASA astronaut Ed Lu, to be launched on Soyuz TMA-2. The crew's mission was to maintain the Station while waiting for Shuttle flights to resume.

 

Soyuz TMA-2
Date	Time	Event	Orbit
2003 Apr 26	0353:52	Launch by Soyuz 11A511U-FG No 6	KB LC1
		T+1:53 SAS off
		T+1:57 BVGD sep
		T+2:37 GO sep
		T+4:47 Blok A sep
		T+4:57 KhO sep
	0402:35	T+8:44 Blok I MECO
	0402:39	T+8:48 Blok I sep
	0642	DV1
	0829	DV2
2003 Apr 27	0511	DV3 2.3m/s
2003 Apr 28	0533	Begin flyaround
	0545	150m from docking port
	0546	In final approach
	0556:22	Docked with Zarya nadir
	0726	HO
2003 Oct 27	2014	HC
	2317:09	Undock
	2320	Sep-1
2003 Oct 28	0146:51	Deorbit 255.8s 115.2m/s 46 46S 49 09 W
	0151:07	Deorbit CO 37 58S 31 18W	88.17 -14 x 382 x 51.6
	0213:40	Modules sep
	0216:45	Entry
	0225:31	Parachutes
	0240:20	Landing 49 57 06N 67 02 15E

Spaceway 2

 2005-046A

---

Spaceway F2 is an Ka-band BS-702-2000 for DirectTV. Launch mass is 6116 kg, 3940 kg dry. Size is 5.1 x 3.2 x 3.4m with 40.9m solar array span. Ariane Flight V167, L522.

The satellite will be stationed at 99.2W to cover N America and Hawaii. Using electric propulsion, it took a long time to reach GEO - almost 3 months.

V167 uses a medium fairing with a 2m ACY 5400D (the ACY remains attached to the ESC-A). Spaceway is on a Boeing/SAAB PAS1663 adapter on a SYLDA 5C (0.9m extension, total 5.8m height 4.6m dia) Telkom, under Sylda, is on a CASA 937VB5 adapter and a 3936 payload cone on the ESC-A. The 5ECA has two P240 boosters, an H175/Vulcain 2 core stage, and the ESC-A upper stage.

Spaceway 2
Date	Time	Event	Orbit
2005 Nov 16	2346:00?	Launch by Ariane 5ECA	CSG ELA3
		T+2:19 EAP sep
		T+2:30 80 km 2.1 km/s
		T+3:14 Fairing sep 117km 2.36 km/s
		T+6:40 EPC at 165 km
		T+7:45 162.8 5.31 km/s
	2354:56	T+8:56 EPC MECO
	2355:02	T+9:02 EPC sep at 161 km	-1047 x 161 km x 6.5 deg
	2355:06	T+9:06 ESC-A MES-1
		EPC impact in Gulf of Guinea 4.5W 0N.
	2359:28	T+13:28 ESC-A at 157 km
2005 Nov 17
	0010:41	T+24:41 ESC-A MECO
	0013:24	T+27:24 Spaceway 2 sep
	0017:34	T+31:34 SYLDA 5C sep
	0019:22	T+33:22 Telkom 2 sep
	0021:20	T+41:20 end of mission
2005 Nov 17			633.53 282 x 35830 x 7.0
2005 Nov 21			699.90 562 x 38906 x 7.0
2005 Nov 23			752.13 567 x 41467 x 6.7
2005 Nov 28			1037.83 11533 x 43621 x 0.6
2005 Dec 1			1305.61 22670 x 43713 x 0.3
2005 Dec 2?		LAM
2005 Dec 5			1436.36 27823 x 43759 x 0.3 GEO 116.8W+0.07
2005 Dec 11			1431.94 28050 x 43360 x 0.2 GEO 115.6W+1.0E/d
2005 Dec 28			1433.72 30078 x 41401 x 0.2 GEO 101.3W+0.6E/d
2006 Jan 8			1433.88 31422 x 40064 x 0.2
2006 Jan 19			1435.39 33562 x 37983 x 0.1
2006 Feb 2			1435.57 35475 x 36073 x 0.1 GEO 98.0W+0.15E/d

BeppoSAX

 1996-027A

---

The Satellite per Astronomia a raggi X (X-ray Astronomy Satellite) or SAX was a joint project between ASI, ESA and the Dutch agency NIVR. SAX, built by Alenia with a mass of 1400 kg, carried out broad band spectral observations of X-ray sources from 0.1 to 200 keV using an imaging concentrator telescope. A wide field telescope observed perpendicular to the main instruments. The satellite was placed in a low inclination orbit by a two-burn Atlas Centaur mission.

After launch, SAX was renamed BeppoSAX to honor Guiseppe (Beppo) Occhialini (1907-1993), who was involved in early experimental research on positrons and pi mesons, and was a pioneer in Italian gamma ray and cosmic ray astronomy and closely associated with the founding of ESRO.

SAX
Date	Time	Event	Orbit
1996 Apr 30	0431:01	Launch by Atlas I Centaur (AC-78)	CC LC36B
		Azimuth 105.1 deg
		T+2:34 BECO
		T+2:37 Booster sep
		T+2:59 Insulation panels sep
		T+3:29 Fairing sep
		T+4:35 Atlas SECO
	0436:36	T+4:37 Atlas sep
	0436:56	T+4:58 Centaur MES1
	0442:00	T+10:05 Centaur MECO1, transfer orbit	250? x 605? x 28.6?
	0456:40	T+24:44 Centaur MES2
	0458:20	T+28:25? Centaur MECO2
	0459:21	T+29:21? Centaur sep	96.55 581 x 605 x 4.0
	0522?	Centaur perigee lower	(95.13 462 x 587 x 4.0)
2002 Apr 30	1338	end of ops

Payload:

• Narrow Field Instruments

  • Concentrators

  • MEGSPC Medium energy GSPC (3), 1-10 keV

  • LEGPSC Low energy GSPC, 0.1-1 keV (ESTEC)

  • PDS Phoswich detector system, 10-200 keV

• HEGSPC High energy GSPC, 3-120 keV

• Wide Field Instruments

  • Coded Mask Telescope

  • Wide Field Cameras, 20 deg FOV, 2-30 keV (NIVR)

DirecTV-7S

 2004-016A

---

Loral SS/L 1300 satellite with 54 transponders and highly focused spot beams. 119W, may move to 101W later. Mass 5483 kg (or 5565 kg, TsENKI).

Launch by Zenit 3SL in 2004, using a single burn of the DM for direct ascent to GTO. The second stage impacted 4826 km downrange.

Directv 7S
Date	Time	Event	Orbit
2004 May 4	1242:00	Launch by Zenit-3SL
		T+2:29 St 1 sep
		T+3:37 Fairing sep
	1250:41	T+8:41 Stage 2 MECO, sep	-2188 x 182 x 0
		T+8:51 DM-SL MES-1
	1301:31	T+19:31 DM-SL MECO-1
	1311:21	T+29:21 DM-SL sep	142 x 35721 x 0.1
2004 May 10			1426.76 35403 x 35803 x 0.1
2004 May 19			1436.11 35771 x 35802 x 0.1 GEO 129.2W
2004 May 28		Relocate to 119W
2004 Jun 2		Move in at 119W
2004 Jun 2			1436.06 35780 x 35791 x 0.1 GEO 119.2W
2006 Aug 7			1436.06 35775 x 35796 x 0.0 GEO 119.2W

People: July 10,2006

 https://welib.org/md5/7998dfe18957e42dbbadbd1608614735