Meteor-3M

 2001-056A

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Meteor-3M 17F45 No. 101 Originally planned for 1998, funding problems delayed it to 2001.

Mass is 2476 kg. Control from TsUP-M, Korolev.

It carried Badr B, Maroc-Tubsat, Kompass and Reflektor The SAGE 3 instrument studies aerosols and the ozone layer.

Launch was southbound from Baykonur; after stage 2 main engine cutoff, low thrust engines continued firing to insert the vehicle into orbit by around 17 min after launch (representing about an equivalent 250 m/s apogee burn).

Meteor-3M
Date	Time	Event	Orbit
2001 Dec 10	1718:57	Launch by Zenit-2 No. 19K	KB PL45
	1721:20	T+2:23 Stage 1 MECO
	1721:22	T+2:25 Stage 1 sep
	1721	T+2:25 Stage 2 burn
	1721:37	T+2:40 GO sep
	1725:39	T+6:42 Stage 2 MECO	180? x 996? x 99.7
	1736:29	T+17:31 Stage 2 VECO
	1736:29	Meteor-3M sep
	1736:31	Satellites separate
	2202		105.25 996 x 1015 x 99.7

Payload:

• VIK-M1 Vis/IR imager with MSU-E visible and MSU-SM red channels, 30m

• BKNA Comprises MTVSZ, MIVZA, KGI-4S, MSGI-5EI?

• MR-700M Meteo instrument package, with MR-2000M1 TV camera and Klimat

• KGI-4S Particles: electron and proton spectra

• MSGI-5EI Electron and proton fluxes

• MTVZA Microwave sounder 18-36 GHz, 2600 km swath 30m res

• MIVZA Microwave sounder 42-94 GHz, 1700 km swath 12m res

• Cloud top heights

• Sea surface temperature measurements

• Temperature and humidity profiles

• SAGE 3 Stratospheric aerosol and gas profiles

Spaceflight: February 2008

 https://welib.org/md5/b72b661313952f760c390b9743f1a1af

The Voice of Dr Wernher von Braun

https://welib.org/md5/1c1f89bd61552b2a99bce2ea14844f61

DK visual encyclopedia of space

 https://welib.org/md5/7f260448ed332f7348396478eca87c82

TacSat 2

 2006-058A

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AFRL's JWS-D1 (Joint Warfighting Space - Demonstrator 1) or TacSat-2, also called Roadrunner, will use a NGMB (Next Generation Multifunctional Bus) from the cancelled TechSat-21 program, built by MicroSat systems/Littleton.

Launch by Minotaur from WI (transferred from Falcon 1) Spacecraft is box-cylinder + 2 panels, 370 kg. Estimate 1.7m long 1.0m dia 5.5?m span. Launch Nov 2006. Piggyback will be Genesat-1.

Program is to demonstrate stored state to orbit in 1 week (Rapid Call Up Experiment), with autonomous on-orbit commissioning on 1 day, and to demonstrate tactical command and control of the satellite from a mobile location as well as demo a high resolution imager and a system to determine the position of a radio emitting source and image it on the same pass.

A signals intelligence experiment was not immediately activated because of bureaucratic objections from NSA.

The Tacsat 2 bus was later named SN-200 by Sierra Nevada.

Tacsat 2
Date	Time	Event	Orbit
2006 Dec 16	1200:00	Launch by Minotaur	WI MARS LA0B
	T+1:01 St 1 sep
		T+1:18 Skirt sep
		T+2:13 St 2 sep
		T+2:15 St 3 burn
		T+2:23 61-inch Fairing sep
		T+3:29 St 3 burnout
		T+7:41 St 3 sep
	1207	T+7:52 St 4 burn
	1209	T+9:00 St 4 burnout
	1211	T+11:00 St 4 sep
	1220	T+20:58 Genesat 1 sep
2007 Dec 21		end of ops

Payload:

• ECI Enhanced Commercial Imager; 0.51m telescope; High res visible imager (1m) pan/3-color.

• ROPE RoadRunner On board Processing Experiment

• CDL Tactical Common Data Link radio system

• TIE Target indicator experiment

• OOCE Autonomous on-orbit checkout system experiment

• HET BHT-200 Hall Effect thruster

• ISC Inertial Stellar Compass (Draper lab); NASA ST6 mission

• SEI Specific Emitter Identification, Radio emission geolocation experiment (NRL)

• ATE Autonomous Tasking Experiment

• LPT Low Power Transceiver

• IGOR Integrated GPS Occultation Receiver

• ADS AFGL-705 Atmospheric Density Specification (ADS)

  ADS consisted of two complementary experiments to characterize the neutral wind of the upper atmosphere.

  • ACME (Anemometer Cross-track Measurement Experiment). ACME measured the cross-track component of the very rarefied atmosphere at the orbital altitude of 350 km; it required precise pointing knowledge to remove the spacecraft in-track velocity component from its measurement. ACME was made by the University of Texas at Dallas, TX.

  • ADMS (Absolute Density Mass Spectrometer). ADMS measured the atomic mass of the prevailing species in the wind in the range from 1 to 50. ADMS was developed at AFRL, Hanscom AFB, MA.

Koronas-F

 2001-032A

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Koronas (Complex orbital Near Earth obs. of solar activity). The Koronas F satellite was led by FIAN (Lebedev) and carried a UV/X-ray solar study payload. Mass was 2260 kg. The satellite was AUOS-SM-KF.

Koronas F
Date	Time	Event	Orbit
2001 Jul 31	0800:00	Launch
	0802	T+2:00 St 1 sep
	0803	T+3:31 Fairing
	0804	T+4:30 St 2 MECO
	0804	T+4:37 St 2 sep
	0805	T+5:20 S5M burn 1
	0807	T+7:04 S5M MECO-1	170? x 500? x 82.5
	0850	T+50:00 S5M MES-2
	0850:09	T+50:09 S5M MECO-2
	0850:39	T+50:39 min S5M sep	94.78 486 x 529 x 82.5
2002 Nov 7		Malfunction in transmitter, reduced data flow
2005 May		End of operations?
2005 Dec 6		Reentered

Payload:

• DIFOS Solar opt/uv total-disk variability (IZMIRAN)

• SORS Solar radio bursts (IZMIRAN), two crossed-antenna radiometers

• ZENIT Solar corona study 7500-8500 A, 1' res at 2 Rsun(IZMIRAN)

• SUFR Solar UV luminosity variability 1-1300A (Fedorov Inst)

• VUSS UV L-alpha resonance line, flux in 50A bandpass (Fedorov Inst)

• DIAGENESS Solar X active regions 5", 1s, 1-5 keV and 2-160 keV (Poland/IZMIRAN)

• RESIK Solar X crystal spectrometer (Poland/IZIMIRAN)

• IRIS Solar flare X-ray spectrometer 2-200 keV (Ioffe PTI)

• HELIKON Solar flare X and gamma ray detector 10 keV-8MeV(Ioffe PTI)

• SKL Solar cosmic ray spectrometer (gamma 0.03-100 MeV, n, e, p, He) (MGU)

• RES-K Solar active area X-ray line imaging 6" Fe, Mg, XUV (FIAN)

• SRT 1" resolution solar X-ray telescope (FIAN)

• RPS X-ray radiation from flares (IKI) 3-30 keV, at Fe 5.9 keV.

• SPR-N X-ray polarimeter (FIAN) 20-100 keV

• AVS Solar flare X and gamma ray detectors (MIFI) 3 keV - 6 MeV

Town and Country: October 2007

 https://welib.org/md5/bf52f4e6ff172af7df042ae7d0e7c89b

Reckless

 https://welib.org/md5/390a0071af0159d16d1122345dc63247

N-Star-A

 1995-044A

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The N-STAR a satellite is an FS-1300 class Space Systems/Loral satellite built for Nippon Telephone and Telegraph (NTT) of Japan.

N-STAR a was launched on the V77 flight of Ariane, using an Ariane 44P with an H-10 III third stage and the 01 fairing. The launch profile used a standard geostationary transfer orbit. N-STAR a is to replace the CS-3 satellite at 132E. The satellite was damaged during transportation from California to Guiane, and several weeks were needed for repairs.

The N-STAR a satellite has a launch mass of 3410 kg, a dry mass of 1617 kg, and a BOL mass of 2057 kg. The 3-axis stabilized satellite has a solar panel span of 27.3m, and a bus size of 2.4 x 2.2 x 2.2 m. Height is 6.3 m including the payload mast. The large composite antenna was 4.5 x 2.6 m in size. Mass of the third stage in orbit with the VEB is 2065 kg at orbit insertion, or 1770 kg after fuel depletion (1240 kg H-10-3, 530 kg VEB).

N-STAR a
Date	Time	Event	Orbit
1995 Aug 29	0641	Launch
	0642	PAP sep (T+1:07)
	0644	Stage 1 sep (T+3:32)
	0644	Stage 2 TIG (T+3:35)
	0645	Fairing sep (T+4:36)
	0647	Stage 2 sep (T+6:43)
	0647	H-10-3 TIG (T+6:48)
	0659	H-10-3 cutoff (T+18:46)
	0702	H-10-3 sep (T+21:27)	172 x 35775 x 7.0
	0702	H-10-3 sep burn (T+21:29)
	0704	V77 mission complete (T+23:11)
	0940?	Solar panels deploy (T+3h)
1995 Aug 29			630.38 173 x 35777 x 7.0
1995 Aug 30	0930?	LAM1 (26h, 3rd apo)	7384 x 35755 x 3.7
1995 Aug 30			774.99 7384 x 35755 x 3.7
1995 Aug 31	1100?	LAM2
1995 Aug 31			1390.22 34036 x 35731 x 0.1
1995 Sep 2	0900?	LAM3
1995 Sep 2			1428.81 35534 x 35753 x 0.1 GEO 128.0E
1995 Sep 16			1436.04 35773 x 35797 x 0.0 GEO 132.0E
1995 Oct 15			1435.94 35779 x 35788 x 0.0 GEO 132.0E
1999 Aug 30			1436.17 35779 x 35796 x 0.0 GEO 132.1E
1999 Oct 14			1436.10 35773 x 35799 x 0.1 GEO 132.1E
2006 Aug 1			1436.13 35776 x 35797 x 0.8 GEO 132.0E

Challenger Park

 https://welib.org/md5/18158a3acfb18e83e35f92b7596caa5e

The Social Climber's Guide to High School

https://welib.org/md5/da6efb751a28892571e5b13c891271bd

CBERS-3

 2003-049A

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The second China-Brazil Earth Resources Satellite, CBERS-2 was built at INPE in Brazil. It was launched from China in Oct 2003 on a CZ-4B and called ZY-1 No. 2 by the Chinese, although they also refer to it as

\uni{ 中巴地球资源卫星02星 }{ }

(Zhongba diqiu ziyuan weixing 02 xing, Brazil Earth Resources Satellite 02). Mass was 1550 kg.

\imps{3.0}{images/03049A}

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CBERS 2 before launch

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\imps{3.0}{images/03049Ab}

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Illustration of CBERS 2 on orbit

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ZY-1 No 2/CBERS-2
Date	Time	Event	Orbit
2003 Oct 21	0316	Launch by CZ-4B
		T+2:33 Stage 1 MECO
		T+2:34 Stage 1 sep
		T+2:54 Fairing sep
		T+4:37 St 2 MECO
		T+4:47 St 2 VECO
		T+4:48 St 2 sep
		T+4:48 St 3 burn
	0327	T+11:18 St 3 MECO
	0328	T+12:28 ZY 1 sep
	0328	T+12:55 CX sep
2003 Oct 22			99.62 730 x 750 x 98.54
2003 Oct 24		Orbit raise	99.98 751 x 763 x 98.5
2003 Oct 27		Orbit raise	100.27 770 x 771 x 98.5
2004 Jan 14			100.32 772 x 774 x 98.5
2006 Aug 8			100.32 772 x 774 x 98.4

Thuraya 3

 2008-001A

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Thuraya 3 is 5180 kg. 28.5E Boeing GEM satellite for regional mideast, africa, europe comms. Uses the primary gateway in Sharjah, UAE; Thuraya Sat Telecom Co. based in Abu Dhabi.

Zenit-3SL launch.

Thuraya 3
Date	Time	Event	Orbit
2008 Jan 15	1148:59	Launch by Zenit-3SL	Odyssey
		T+2:29 Stage 1 sep
		T+3:41 Fairing sep
	1156:19	T+8:20 Stage 2 sep	-1987 x 184 x 6.2
	1156:28	T+8:29 DM-SL MES-1
	1201:47	T+12:48 MECO-1	180 x 889 x 6.2
	1302:08	T+1:13:09 MES-2
	1308:30	T+1:19:31 MECO-2	736 x 35932 x 6.2
	1327:44	T+1:38:51 DM sep
		T+6:38:34 First apogee	740 x 35786 x 6.2
			641.60 726 x 35800 x 6.2
2008 Jan 18		LAM-1	798.21 8471 x 35827 x 6.2
2008 Jan 20		LAM-2	1049.81 19880 x 35795 x 6.2
2008 Jan 23?		LAM-3
2008 Jan 26			1419.50 35145 x 35776 x 6.4
2008 Feb 1			1436.02 35756 x 35814 x 6.2 GEO 98.4E

Progress M-45

 2001-036A

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Progress mission 5P, 11F615A55 No 245, to the ISS was launched on 2001 Aug 21. It carries 1300 kg of supplies, 600 kg of fuel. It delivered MPAC/SEED, which was installed on Zvezda on the 2001 Oct 15 EVA.

Progress M-45
Date	Time	Event	Orbit
2001 Aug 21	0923:54	Launch by Soyuz-U	KB
	0932:43	Blok-I sep
2001 Aug 23	0920	Range 1 km
	0943	Range 120m, final approach
	0951:11	Docked with Zvezda
	0959:14	Hard dock
2001 Aug 25	0740	HO
2001 Nov 21	1420	HC
2001 Nov 22	1612:01	Undocked
	2048:00	Deorbited
	2124:12	Entry

STS-91 (Discovery)

 1998-034A

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STS-91 was the final US mission to Mir, recovering long-stay astronaut Andy Thomas. Veteran space station designer, former cosmonaut, and Mir program manager Valeriy Ryumin, following a strenuous weight loss program, joined the STS-91 crew to carry out a brief inspection tour of the Mir station. STS-91 also carried the flight test of the Alpha Magnetic Spectrometer (AMS), a particle physics experiment. Most crucially, the launch of STS-91 featured the first test of the Al-Li superlightweight external tank, which performed correctly.

The Ku-band TV system failed, so TV coverage of the docking was curtailed and science downlink from AMS was severely hampered. An r-bar rendezvous was followed by docking on Jun 5, using an improved APAS docking mechanism for ISS. As soon as the hatches were opened, Thomas became part of the Discovery crew. Ryumin floated in to Mir for the first time to begin his inspection. During his stay, the crew celebrated the moment he reached a career total of 365 days in space. The DCAM and PCG GN2 experiments were recovered from the Mir. The GMSF experiment was delivered. 12.5 CWC containers with 550 kg of water were delivered.

After undocking, a flyaround failed to spot flourescent gas being injected into Spektr by the EO-25 crew.

On Jun 9, a software problem in the experimental onboard GPS navigation system triggered a series of events which by Jun 10 led to the Shuttle systems computers being overloaded with error messages and failing to select the correct communications antennas, leading to a temporary loss of communication with the ground. Investigation led to software fixes and a decision to require further flight testing of the GPS system before it completely replaced the old TACAN navigation system.

Discovery remained in orbit carrying out work with AMS, which send down enough data to verify detection of anitprotons, but not enough to fully calibrate the instrument. The SHUCS communications experiment also ran into problems. On Jun 11, radio telescope observations of an RCS firing were used to study the effect of thruster plumes on the ionosphere.

OMS-2 mass was 114809 kg.

STS-91
Date	Time	Event	Orbit
1997 Oct 1		Tow to VAB/2
1997 Oct 30		Tow to OPF/2
1998 Apr 27		Roll to VAB/1
1998 Apr 29		Mate to SLWT
1998 May 2	0726	Roll to LC39A
1998 Jun 2	2206:17	SSME ignition
	2206:24	Launch
	2208:25	T+2:01 SRM cutoff
	2208:27	T+2:03 SRB sep
	2214:54	T+8:30 MECO
	2215:13	T+8:49 ET sep	74 x 324 x 51.6
	2250:34	T+44:10 OMS-2 1:45 51.5m/s
	2252:20	T+45:56 OMS-2 C/O	90.18 239 x 326 x 51.6
	2350:02	PLB Open
1998 Jun 3	0147:42	OMS-3 raise peri 55s 26m/s
	0148:36	OMS-3 C/O	91.09 326 x 329 x 51.6
	1434:14	OMS-4 R Raise apogee 19s 4m/s
	1434:33	OMS-4 C/O	91.24 327 x 343 x 51.6
	2045		91.23 333 x 336 x 51.6
	2123:32	OMS 5 Raise apogee 28s 13m/s
	2124:00	OMS-5 C/O
1998 Jun 4	0000		91.71 342 x 374 x 51.6
	0600		91.70 342 x 373 x 51.6
	1036	Rendezvous begins
	1159:00	OMS-6 R burn 31s 7m/s
	1159:32	OMS-6 C/O
	1334:38	TI RCS
	1354:43	MC1
	1425:55	MC2
	1442:55	MC3
	1452:55	MC4
	1645	Stationkeep at 10m
	1650	Resume approach
	1658:19	Docked with Mir SO
	1712:00	Hard dock
	1806		92.03 370 x 378 x 51.6
	1828	Hatch open
	2205	Thomas part of STS crew
1998 Jun 6	0600		92.03 370 x 378 x 51.6
	1244	RMS test, uncradle
	1513	RMS recradle
	1756	Spektr gas release test
	1806	Release complete
1998 Jun 8	0600		92.03 368 x 379 x 51.6
	1307	Hatches closed
	1557	Begin undocking
	1601:46	Undocking from Mir SO
		Stationkeep at 75m on r-bar
		Flyaround Mir to v-bar
		Stationkeep at 60-80m on v-bar
	1643s	Spektr tracer gas experiment
	1705s	Flyaround continues
	1727:00	RCS Sep burn 1m/s 12s
1998 Jun 9		RMS tests
1998 Jun 11	0600		91.99 367 x 376 x 51.6
	1630:00	OMS-7 SIMPLEX, Lower perigee 12s 6m/s
	1630:12	OMS-7 C/O
	2200		91.78 350 x 372 x 51.6
1998 Jun 12	0629		91.78 350 x 373 x 51.6
	1418	PLBD closed
	1652:25	OMS-8 DO 4:10 126m/s
	1656:35	OMS C/O
	1728	Entry interface
	1800:24	Landed at KSC RW15 9d/19:53:54
	1800:27	NGTD
	1801:28	Wheels stop
1998 Jun 13	0145	Tow to OPF/2