Fobos-Grunt

 2011-065A

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The Fobos-Grunt (Phobos Sample) mission uses a new Lavochkin bus and has a mass of 2000 kg. Launch mass is 8120 kg; includes the MDU stage. Launch mass of PM is 1550 kg. MDU is 6100 kg and is a Flagman stage, Fobos ADU derived with S5.92 engine, similar to Fregat-SB. VA mass is 215 kg and SA for Earth entry is 8 kg. MDU has 4675 kg oxidizer, 2340 kg fuel; SBB has 2004 kg oxidizer, 997 kg fuel.

NIIMASH PM propulsion system: dry mass 56 kg, prop mass 135 kg and 6 kg N2 gas (total 197 kg?) N2O4/UDMH engine 1530N, 2982m/s Isp.) made of 4x 11D458F engine each with 382.4N, 304s Isp, plus small thrusters. Prop mass 343 kg oxidizer 186 kg fuel (max loading) for total prop 529 kg.

Carries out Fobos landing, Fobos launch to Mars orbit, transearth insertion and TCM in transearth cruise.

SA cone, 7 kg VA propulsion system 124N, Isp 3002 m/s, Box

(Based on 11D414NS 13.3N version for elliptical orbit comsat (Meridan?) with Isp 273.3s, 56 kg dry, 42 kg prop, total impulse 79.1 kNs)

Also flyby module, attitude control with 4 x 11D457F thruster with 54N thrust, 1 x 17DF58EF with 12.5N thrust.

Launch vehicle core is the two-stage Zenit-2SB41.1; with the payload this is known as the Zenit-2FG launch vehicle, and had serial number 70181302.

	Guess		NK
SA	7	7	7	7
VA dry	139	146	148	155
VA prop	135	281	139	294
PM	550	831	550	844
PM DU	180	1011	212	1056
PM prop	1050	2061	1058	2114
Frame	172	2233	150	2264
YH-1	115	2348	115	2379
MDU dry	735	3083	735	3114
MDU prop	7015	10098	7015	10129
SBB dry	335	10433	375	10504
SBB prop	3001	13434	3001	13505

After insertion, no communications until late Nov when ESA/Perth had a few successful contacts, but later contacts yielded only silence.

FG
Date	Time	Event	Orbit
2011 Nov 8	2016:03	Launch by Zenit-2	KB
		T+2:22 Stage 1 sep
		T+5:04 GO sep
		Stage 2 MECO
	2027:28	Stage 2 sep	207 x 347 x 51.43
2011 Nov 22	1844	St 2 entry over Australia
2012 Jan 15	1746?	Entry 46S 87W

FG prelaunch plan
Date	Time	Event	Orbit
	2255:48	T+2h:30 MDU MES-1 8.4min 0.83km/s
	2305:18	MDU MECO-1 to ellip orbit	237 x 4250 x 51.42
	2307:17	SBB sep
		4.2 hour coast
2011 Nov 9	0102:49	T+6.8h? MDU MES-2 8.5m 1.105 km/s
	0120:10	MDU MECO-2 to ellip orbit	312.0 240? x 17500
		7 day parking orbit for orbit det
		MDU MES-3
		MDU MECO-3 to solar orbit Vinf 3.1 km/s
		T+5-10d TCM1
		T+65d TCM2
		MOI-21d? TCM3
2012 Aug		Mars arrival with 700-1000 km periapsis height
2012 Aug 25		Mars orbit insertion, MDU burn to 3 day orbit	900 x 77000 km
		MDU sep
		YH-1 sep
		Truss sep
2012 Sep
		MOI-2	9900 x 77000
2012 Oct		Enter observation orbit
		MOI-3	9900 x 9900
		PM Phobos rendezvous
2013 Jan		Quasi-synchronous Phobos orbit, 100 km range
2013 Feb
		PM Phobos landing, 8 to 16 hor on surface
2013 Mar		VA Phobos launch
		VA in Mars orbit, just lower than Phobos
2013 Aug?
		TCM to 9900? x 77000?
		TCM to 900? x 77000?
2013 Sep		TEI burn
2014 Aug		Earth approach
		SA/VA sep (T - few days)
		SA entry
2014 Aug		Landing on Earth

Payload:

• MDU (Marshevaya DU) for EPO and solar orbit insertion

• PM (Pereletniy Modul', cruise module): lander spacecraft.

• Sample arm/drilling rig

• Propulsion system

• Science instruments

• VA (Return spacecraft)

• Ascent propulsion system

• SA (Descent module)

• TDA Thermal Difference Analyzer (IKI/Gerasimov)

• GC Gas Chromatograph (Vernadsky/)

• MAL Mass spectrometer (MPS Lindau/)

• MIMOS Mossbauer spectrometer for mineralogy (IAAC Mainz/IKI/Klingelhofer)

• FOGS Gamma spectrometer for surface composition (Vernadsky/Moskaleva)

• HEND Neutron spectrometer for surface hydrogen (IKI/Mitrofanov, ESTEC/)

• AOST IR Spectrometer (IKI/Korablev)

• LASMA Laser time of flight spectrometer (IKI/Managadze)

• MANAGA Secondary ions mass spectrometer (IKI/Managadze)

• TERMOFOB Thermo Detector (Vernadsky/Marov)

• LWR Long Wave Planetary Radar (KotelnikovInst/Smirnov)

• SEISMO-GRAS Gravimetry (Schmidt Inst, IKI / Manukin)

• METEOR Dust counter (Vernadskiy/)

• FPMS Plasma experiment Ion/electron spectrometers, magnetometer (IKI/Skalsky)

• LIBRATION Star sensor, Phobos libration study (IKI/Lipatov)

• USO Ultrastable oscillator for celest. mech expt (IKI/Gotlib)

• TSNG TV System for landing support, surface mapping (IKI/Avanesov)

• Robotic Arm (IKI/Koslov)

• Panoramic/Stereo TV cameras

Comstar 4

 1981-018A

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The final Comstar satellite was launched in 1981. G. Falworth's newsletter reported an apogee burn time of 2336 UTC Feb 24, but the post launch MOR reported a Feb 23 burn and the TLEs prefer a burn around 2130 UTC on Feb 24.

In late 2001 D4 was relocated over 69E after purchase by SSC Parallax as Parallax 1. In Apr 2002, Tongasat (Friendly Islands Satellite Communication Ltd ) bought the satellite and renamed it Esiafi 1. The satellite began to drift off station in early 2004, and oscillated between 70E and 80E. In 2011 Tongasat still claimed to be operating the satellite but it is not clear whether the vehicle was really still active.

Comstar D4
Date	Time	Event	Orbit
1981 Feb 21	2323	Launch by Atlas Centaur	LC36A
		Azimuth 101 deg
		T+2:23 Booster sep
		T+3:33 Fairing
		T+4:17 SECO
		T+4:19 Atlas sep
		T+4:25 MES-1 5:02
	2332	T+9:35 MECO-1	180? x 1800? x 27.0
	2346	T+23:42 MES-2 1:24
	2348	T+25:06 MECO-2	554 x 36526 x 20.7
	2351	T+28:34 Centaur sep
		T+30:31 Centaur venting	636 x 36345 x 20.4
1981 Feb 22			652.27 552 x 36518 x 20.7
	0600?	Apo 1 over 85E
	1600?	Apo 2 over 80W
1981 Feb 23	0300?	Apo 3 over 120E
	1400?	Apo 4 over 40W
1981 Feb 23	2336?	SVM-4A apogee firing 42s
1981 Feb 24	0030	Apo 5 over 150E
	1200?	Apo 6 over 10W
	2230	Apo 7 over 178W
1981 Feb 24	2136?	SVM-4A apogee firing 42s
1981 Feb 24	2336?	SVM-4A apogee firing 42s
1981 Mar 3			1425.91 35385 x 35788 x 0.2 GEO 147.9W+2.5E
1981 Mar 9			1435.30 35385 x 35788 x 0.2 GEO 142.6W+0.2E
1981 Mar 12			1436.07 35146 x 36426 x 0.3 GEO 140.2W
1981 Mar 22			1436.19 35771 x 35805 x 0.3 GEO 142.2W
1981 Apr 14			1436.07 35774 x 35798 x 0.3 GEO 142.5W
1981 Apr		Move to 127W
1981 May 4			1436.14 35777 x 35797 x 0.2 GEO 127.3W
1982 Jan			GEO 127W
1983 Oct 6			1436.07 35783 x 35788 x 0.1 GEO 127.0W
1984 Jan			GEO 127W
1985 Sep		Ownership to AT&T;	GEO 127W
1985 Sep 9			1436.08 35783 x 35789 x 0.0 GEO 127.1W
1985 Sep		Move to 75W
1985 Oct 17			1435.97 35778 x 35789 x 0.2 GEO 75.3W
1985 Nov			GEO 76W
1986 Mar 26			1436.20 35785 x 35791 x 0.2 GEO 75.5W
1990 Aug 18			1436.17 35784 x 35791 x 4.3 GEO 76.0W
1992 Aug 5			1436.14 35786 x 35788 x 6.1 GEO 76.0W
1994 Dec 17			1436.07 35782 x 35789 x 7.9 GEO 76.0W
1997 Feb 24			1436.08 35774 x 35798 x 9.2 GEO 75.9W
1999 Apr 23			1436.11 35784 x 35789 x 10.3 GEO 75.9W
2001 Jul 4			GEO 76W
2001 Jul 20		Move out
2001 Dec		Arrive at 70E
2001 Dec 3			1436.06 35772 x 35799 x 11.2 GEO 70.3E
2003 Sep 1			1436.04 35770 x 35800 x 11.8 GEO 70.3E
2004 Jan		Begin drift between 70E and 80E.
2004 Aug 7			1435.95 35773 x 35793 x 12.4 GEO 78.9E+0.03E

In the Hamptons Too : Further Encounters with Farmers, Fishermen, Artists, Billionaires, and Celebrities

 https://welib.org/md5/c45da4b19da6a4eb8215267a25ed8074

Helios 1A

 1995-033A

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Launched on 1995 Jul 7, Helios 1A was inserted into sun synchronous orbit. Spain and Italy had joined France in the Helios program by the time of launch.

The 2537 kg satellite was built by Matra Marconi Space/France. The satellite was retired in late 2011, and hobbyist observers located it in a lower retirement orbit in 2012.

Helios 1A
Date	Time	Event	Orbit
1995 Jul 7	1623	Launch
	1625	Stage 1 sep
	1628	Stage 2 sep
	1628	H-10-3 ignition
	1641	H-10-3 sep (T+18:19)
		CERISE and UPMSAT sep
1995 Jul 8			98.24 672 x 676 x 98.1
1999		Still operating
2006 Aug 4			98.37 679 x 682 x 98.1
2009 Dec 8			98.37 679 x 681 x 98.1
2011 Sep 4			98.37 678 x 682 x 98.1

February 19,1998

 https://web.archive.org/web/20080504032215/http://digest-archive.degrassi.ca/DD12.htm

Seventeen: September 2011

 https://welib.org/md5/9a9fb05478f69bf5508281a94a1cce96

Kosmos 2428

 2007-029A

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Zenit-2 No. 21L was modified to Zenit-2M No. 1-2005. The payload was a Tselina-2 satellite.

Kosmos-2428
Date	Time	Event	Orbit
2007 Jun 29	1000:00	Launch by Zenit-2M	KB LC45
	1002	T+2:23 St 1 MECO
	1002	T+2:25 Stage 1 sep
	1002	T+2:25 Stage 2 burn
	1002	T+2:40 GO sep
	1006	T+6:42 Stage 2 MECO	150? x 850? x 71.0
		Sep motor cover perigee
	1013?	T+13m? Stage 2 VECO
	1013?	Stage 2 sep motor covers
	1013:51	Stage 2 sep
2007 Jun 30			101.96 846 x 856 x 71.0

Kosmos 2415

 2005-034A

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Kometa No. 21 flew a 44 day mission to complete the series.

Kosmos-2415
Date	Time	Event	Orbit
2005 Sep 2	0950	Launch by Soyuz	KB LC31
	0958	Blok I sep	196 x 285 x 64.9
2005 Sep 3		Orbit raise	205 x 284 x 64.9
2005 Sep 8			201 x 280 x 64.9
2005 Sep 15		Apogee raise
2005 Sep 21		Apogee raise	197 x 288 x 64.9
2005 Sep 27			195 x 281 x 64.9
2005 Sep 27		Perigee raise	203 x 278 x 64.9
2005 Oct 6		Perigee raise	206 x 268 x 64.9
2005 Oct 7			205 x 276 x 64.9
2005 Oct 13			204 x 269 x 64.9
		Apogee raise	204 x 311 x 64.9
2005 Oct 15			204 x 309 x 64.9
	2144	Landing after 43.5d
2005 Oct 16	0345	58E 55N southbound rev 706
	0520	55E 39N southbound rev 707
	1655	105E 41N northbound rev 715
	1825	84E 42N northbound rev 716
	1950	62E 43N northbound rev 717
	2112?	Deorbit over 17E 0S
	2128	51E 53N northbound rev 718
	2135?	Landing