Arase

 2016-080A

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Exploration of Energization and Radiation in Geospace (ERG) is the second Epsilon/SPRINT satellite. It was renamed 'Arase' after launch.

ERG
Date	Time	Event	Orbit
2016 Dec 20	1100	Launch by Epsilon	Uchinoura
		T+1:49 St 1 cutoff 71 km 2.5 km/s
		T+2:30 Fairing sep 115 km 2.4 km/s
		T+2:41 St 1 sep 124 km
		T+2:25 St 2 ignition
		T+4:53 St 2 cufoff 194 km 5.9 km/s
	1106	T+6:38 St 2 sep 229 km 5.9 km/s
		T+6:42 St 3 burn
	1108	T+8:11 St 3 burnout
	1113	T+13:27 St 3 sep	564.36 228 x 32259 x 31.4
2017 Jan 16		PWE wires deployed
2017 Jan 17	2300	PWE deployment complete, spin rate to 7.5rpm

Payload:

• XEP-e Extremely high energy electrons (ISAS/Higashio,Matsumoto)

• HEP-e High energy electrons (ISAS/Mitani)

• MEP-e Med. energy Electron analyser (Tokyo/Kasahara)

• LEP-e Low energy Electron analyser (Taiwan NCKU/

• MEP-i Med. energy ion mass analyser (Tokyo/Kasahara)

• LEP-i Low energy ion mass analyser (ISAS/Asamura)

• MGF Magnetic field experiment, two 5.0m booms. (ISAS/Matsuoka)

• PWE Plasma Wave Experiment, 4 antennae. Span 30.0m. (Kanazawa U/Y.Kasahara)

• S-WPIA Software wave-particle interaction analyser (Kyoto/Kojima)

Elite Traveler: January-February 2017

 https://welib.org/md5/217f2892f17ce6127cfd6319334a6153

Tiankun 1

 2017-012A

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Tiankun-1 was a test payload from CASIC on the first flight of the KT-2 (Kaitouzhe-2) rocket, which can carry 350 kg to LEO. 

TK1
Date	Time	Event	Orbit
2017 Mar 2	2353	Launch by KT-2
		Stage 1 burn
	2355?	Stage 2 burn
		Stage 3 burn
2017 Mar 3	0001?	Stage 3 burnout
2017 Mar 3	0003?	Stage 3 sep	92.33 373 x 404 x 96.9
	0008?	Stage 3 depletion	90.66 214 x 399 x 96.7

CYGNSS

 2016-078D

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Cyclone Global Navigation Satellite System, eight SSTL sats on one rocket for wind monitoring in hurricanes.

NASA Earth Venture 2 mission (under the ESSP program), following EV-1 which was an airplane based experiment.

GPS signal scattering can penetrate heavy rain to study storm conditions. PI is C. Ruf (U Mich.). Spacecraft by SWRI and SSTL/Colo who also have the MOC; SOC at Michigan. NASA/Langley supported the project. 8 satellites on the cylindrical Sierra Nevada dispenser; 29 kg each, truncated triangular prism, + 2 solar arrays; 0.51 x 0.64 x 0.27m span 1.7m. The satellites slowly spread out along their orbital plane, their separation controlled by attitude changes which modify drag.

Pegasus takeoff from the Skid Strip and drop 203 km E of Daytona Beach. Possible drop point 29 00N 78.45W

CYGNSS FM01
Date	Time	Event	Orbit
2016 Dec 12	1237	Takeoff from RW13
	1330	Launch abort due to hydraulic system problem
	1430?	Land back at CC
2016 Dec 15		Launch by Pegasus XL	CCAFS RW31/13
	1238:00	Takeoff RW13
	1337:00	Drop at 11.9 km over 78.5W 29.0N
		L+0:05 St 1 burn 1:13
		L+1:18 St 1 cutoff 53 km
		L+1:33 St 1 sep
		L+1:34 St 2 burn 2:48
		L+2:12 Fairing sep
		L+2:48 St 2 cutoff
		L+6:45 St 2 sep
		L+6:56 St 3 burn 1:10
	1345	L+8:04 St 3 burnout	510 x 510 x 35
	1350	L+13:04 S+0:00 A/C upper Pair 1 out, 1m/s
		S+0:30 E/G lower Pair 2
	1351	S+1:00 F/H lower Pair 3
	1351	L+14:34 S+1:30 B/D upper Pair 4
		S+10:00 Solar panels deploy
	1411	L-1011 land at RW31/31
2017 Jan 24			95.15 514 x 536 x 35.0

Mars Odyssey

 2001-013A

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Mars Surveyor 2001 Orbiter, bus identical to MCO. Launch Apr 7 2001. Mineralogical global mapping and characterization of orbital radiation environment, plus radio relay. JPL/JSC/Lockheed Martin Astronautics-Denver. The GRS will map the elemental surface composition. 

Launch mass was 730 kg, with 347 kg prop and 383 kg dry.

79 kg fuel after MOI, so mass post MOI is 456 kg.

Size is 2.2m long 1.7m high 2.6m wide; 5.7m span Box+panel + boom, with 6-m GRS boom. Mass 376 kg dry, 725 kg full, 349 kg prop.

The orbiter enters a 25-hr capture orbit on 2001 Oct 20 with a 263 kg prop burn. Aerobraking for 76 days to final 400 km orbit.

TMO
Date	Time	Event	Orbit
2001 Apr 7	1502:21.860	Launch by Delta 7925
		T+1:06 SRB 1-6 sep
		T+2:16 SRB 7-9 sep
		T+4:23 MECO	-5000? x 190? x 37?
		T+4:36 SES
		T+4:42 Fairing sep
	1512	T+10:03 SECO-1 195 km	195 x 215 x 51.9
	1524:46	T+22:24 SES-2 51s?
	1525:36	T+23:15 SECO-2	182 x 1804 x 51.9
	1526:30	T+24:08 St 2 sep
	1527:07	T+24:45 TES 87s
	1528:35	T+26:13 TECO C3=10.767 km2/s2	185 x -50218 x 51.9 (prelaunch)
	1533:17	T+30:55 Despin yo-yo
	1533:22	T+31:00 St 3 sep	185 x -87212 x 51.8
		Bias offset to Mars: 450000 km intended; 74000 km actual
	1620?	St 2 depletion	177 x 1805 x 40.0
2001 Apr 8	0020	Pass EL1:4
2001 Apr 10	1900	Passes 1 Mkm
2001 Apr 12	1224	Depart Earth sphere, 1.5Mkm
2001 May 1			0.982 x 1.384 AU x 3.05
2001 May 23	1730	TCM-1 3.6m/s 82s
2001 Jul 2	1630	TCM-2 0.9m/s 23s
2001 Sep 17	0400	TCM-3 12s, 0.5m/s
2001 Oct 12	0400	TCM-4 3s 0.1m/s
2001 Oct 20	1318	Enter Mars sphere
2001 Oct 24	0218	MOI burn 1219s 1433 m/s 267 kg
	0228:14	LOS
	0231	Periapsis 300 km
	0237	MOI cutoff	300 x 28000 18hr36min
	0248	End occultation
	0256ERT	End occultation at Earth
2001 Oct 25	0628?	Stage 3 flyby Mars at 74000 km ?
2001 Oct 27		Begin Walkin	158 x 27000? x 93.5
2001 Oct 30		Aerobraking	128 x 27000 x 93.5
2001 Nov 6		Main aerobrake phase 1
2001 Nov 13		Aerobraking	110 x (15hr)
2001 Nov 30			10hr, 103 x 15300 x 93.6
2001 Dec 18		Main aerobrake phase 2
2001 Dec 20	0449	Apoapsis A0134	261.24 96 x 6020 x 93
	0909	Apo A00135	258.72 96 x 5940 x 93
2001 Dec 22	1000	Apo A00147	230.34 97 x 4988 x 93
2001 Dec 26		Endgame phase
2001 Dec 28	0642	Apo A00188	173.82 99 x 2951 x 93
	0935	Apo A00189	171.42 99 x 2869 x 93
2001 Dec 30		Apo A00206	105 x 2628 x 93
2002 Jan 1		Apo A00226	107 x 2042 x 93
2002 Jan 3		Walkout phase
2002 Jan 11			116 x 500 x 93
2002 Jan 11	0818	ABX-1 raise orbit 20m/s	201 x 500 x 93
2002 Jan 12			197 x 502 x 93
2002 Jan 15			186 x 502 x 93
		ABX-2 Apo 393, 56m/s	419 x 520 x 93.1
2002 Jan 17	2200	ABX-3 27m/s rev 417	387 x 450 x 93
2002 Jan 28		ABX-4 15s 1m/s
2002 Jan 30	2014	ABX-5 25s 2m/s
2002 Jan		Begin primary mission	387 x 450 x 93
2002 Feb 8		HGA deploy
2002 Feb 18		Nadir point of orbit drift
2002 Feb 19	0700?	Open GRS door
2002 Jun 4	1800?	Deploy GRS boom
2003 Oct 20		Sun-synch burn 9.8m/s
2003 Oct 30		'Halloween' solar flare
2004 Aug 25		end of primary mission
2006 Mar 22	0730	Safemode
2006 Mar 23		Out of safemode
2008 Sep 30		Orbit adjust, 6 min burn
		Leave 5pm SSO
2009 Jun 9		End drift, enter 3:45pm SSO
2012 Mar		Orbit adjust to support MSL, drift to later LT
2012 Jun 8		Safemode
2012 Jul 11		Safemode
2012 Jul 16		Exit safemode
2012 Jul 24		OTM, 6s burn, support MSL
2012 Nov		Switch to backup computer
2014 Feb 11	2003	29s burn, orbit drift to AM daylight orbit
2014 Aug 5		OTM for C/2013A1 flyby
2015 Nov		Burn to lock SSO at 0645am

Payload:

• THEMIS High res camera and thermal imaging spectrometer.

• GRS Mars Observer Gamma Ray Spectrometer

• MARIE Martian Radiation Environment Experiment

Optus 10

 2014-054B

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SingTel Optus satellite at 164E. Loral 1300, with 24 Ku. Light LS-1300, mass 3200 kg. Lower position on Ariane 5.

O10
Date	Time	Event	Orbit
2014 Sep 11	2205	Launch by Ariane 5 VA218 L573	CSG ELA3
		T+2:14 EAP sep
		T+3:16 Fairing sep
	2213	T+8:49 EPC MECO	-1001 x 168 x 6.2
	2213	T+8:55 EPC sep
	2214	T+8:59 ESC-A burn
	2230	T+25:04 ESC-A MECO
	2231	T+26:47 Measat sep
	2233	T+28:34 Sylda sep
	2239	T+34:19 Optus sep
	2255	T+50:44 Passivation of ESC-A
2014 Sep 12			630.89 259 x 35717 x 5.94
2014 Sep 14			758.36 6574 x 35762 x 2.9
2014 Sep 14			989.89 17287 x 35760 x 1.0
2014 Sep 16			1367.98 33118 x 35767 x 0.1
2014 Sep 17			1434.84 35738 x 35785 x 0.1 GEO 174.6E+0.3E/d
2014 Sep 29			1436.08 35774 x 35797 x 0.1 GEO 176.0E
2014 Oct 16		Move out of 176E
2014 Nov 1		Move in 164E
2014 Nov 22			1436.10 35777 x 35795 x 0.1 GEO 164.0E

Bonum 1

 1998-068A

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BONUM-1 is an HS-376HP satellite for the BONUM-1 subsidiary of Russia's Media Most broadcasting company. Launch was by Delta 2 7925-9.5 in 1998. Mass 1425 kg (1224 kg BOL). It has 8 Ku tsp. and went to 36E. Mission is to broadcast 50 channels of direct-to-home TV to western Russia. In Jul 2000 it moved to 55E. On 2003 Oct 1, ownership was transferred to Kos. Svyaz, following Media Most's suppression by the Russian government. 

BONUM
Date	Time	Event	Orbit
1998 Nov 22	2354:00	Launch by Delta 263	CC LC17B
		T+1:03 SRM 6-9 on
		T+1:06 SRM 1-3 sep
		T+2:11 SRM 6-9 sep
		T+4:23 MECO
		T+4:29 VECO
		T+4:31 Stage 1 sep
	2358	T+4:36 Stage 2 burn
1998 Nov 23
	0003:58	T+9:58 SECO-1	87.96 157 x 189 x 29.21 (ILAM)
	0016:29	T+22:29 Stage 2 burn
	0017:13	T+23:13 SECO-2	99.46 159 x 1304 x 28.25
	0102:29	T+1:08:29 Stage 2 burn
	0103:23	T+1:09:23 SECO-3	115.01 1228 x 1683 x 26.74 (ILAM)
	0104:43	T+1:10:53 Star 48B burn
	0106:20	T+1:12:20 TECO
	0108:13	T+1:14:13 Stage 3 sep	676.75 1285 x 37025 x 20.61 (ILAM)
	0124:12	T+1:30:12 Stage 2 depletion complete	102.70 240 x 1533 x 25.88 (ILAM)
1998 Nov 23	0700	Apogee 1
	1800	Apogee 2
1998 Nov 24			670.38 1285 x 36703 x 19.5
	0500	Apogee 3
	1700	Apogee 4
1998 Nov 25	0300	Apogee 5
	1400	Apogee 6
1998 Nov 26	0200	Apogee 7
	1300	Apogee 8
1998 Nov 27	0000	Apogee 9
	1200	Apogee 10
	2300	Apogee 11
1998 Nov 28	1000	Apogee 12
	2040	Apogee 13
1998 Nov 28	2040?	AKM burn 52s
		Guess at orbit	1446.28 35056 x 36915 x 1.0 (guess)
		Guess at orbit	1446.28 35720 x 36251 x 1.0 (guess)
1998 Nov 29	1930?	Fiducial (guess) burn
1998 Nov 30			1431.45 35670 x 35720 x 0.1 GEO 34.5E+1.1E
1998 Dec 2	0930?	mv in
1998 Dec 8			1436.15 35766 x 35809 x 0.1 GEO 36.3E
1999 Nov 8			1436.05 35782 x 35788 x 0.0 GEO 36.4E
2000 Jul		mv out
2000 Aug 10		mv in	1436.14 35783 x 35791 x 0.0 GEO 56.1E
2003 Oct 1		To GPKS
2006 Aug 1			1436.09 35776 x 35796 x 0.0 GEO 56.0E
2014 Nov 30			1436.09 35775 x 35797 x 2.6 GEO 56.1E

Since Last Summer

 https://welib.org/md5/ab783ff21d12f1c43fcc821ecaed9525

Mozihao

 2016-051A

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This was the Quantum Science Experimental Satellite (QUESS). By Jan 2017 the satellite had completed spacecraft bus testing, payload self test and the world-wide integrated link test verifying pointing accuracy and a single quantum channel link.

QUESS
Date	Time	Event	Orbit
2016 Aug 15	1740	Launch by CZ-2D	JQ
	1746?	St 2 MECO
	1748	St 2 VECO
	1749?	St 2 sep	94.54 488 x 504 x 97.4
	1753?	St 2 deorbit
	1830?	St 2 reentry
2016 Aug 19			94.53 487 x 504 x 97.4
2017 Jan		Testing phase complete