Viking 2

  1975-083A

---

The Viking A spacecraft was launched on 1975 Sep 9 at 1839 by Titan IIIE Centaur from Cape Canaveral and became Viking 2.

The initial injection had a closest approach at 1976 Aug 9 0919 UTC with a miss distance of 655575 km (BT,BR= 581970, -301786).

Once in solar orbit, the MC1 burn was made on Sep 19 to correct the trajectory. An approach burn was made on 1976 Jul 27.

Mars Orbit Insertion was on 1976 Aug 7. A series of orbit trim burns were made to synchronize the orbit, ending with MOT4 on Aug 27. The Lander was separated on Sep 3. In this case, the bioshield base remained attached to the Orbiter, VO-2.

After a propulsion test on Sep 29, a major orbit change was made on Sep 30, with the inclination increased to 75 deg. The Viking Extended Mission began on 1976 Dec 14. On 1977 Mar 2, VO-2 had re-synchronized its orbit over the VL-2 landing site. On 1977 Apr 18, the Survival Automatic Mission was begun while Mars approached perihelion (Apr 30).

On 1977 Sep 26, VO-2 trimmed its orbit to approach Deimos. Another burn on Oct 9 synchronized the orbit with that of Deimos. Deimos encounters followed on Oct 10, Oct 12, Oct 15, and twice more in the Oct 16-22 period. The Oct 15 encounter was only 33km from the center of Deimos. A burn on Oct 23 ended the Deimos encounter period.

The Bioshield base was finally jettisoned on 1978 Mar 3. After Mars aphelion on Apr 9, the Viking Contination Mission began on May 31. However, VO-2's attitude gas was exhausted at 0601 on 1978 Jul 24 and the mission came to a close.

VO2
Date	Time	Event	Orbit
1975 Sep 9	1839:00	Launch by Titan TC-3
	1840:52	St 1 burn
	1841:02	SRM sep
	1843:21	St 1 cutoff
	1843:21	St 1 sep, St 2 burn
	1843:33	CSS sep
	1846:50	St 2 MECO
	1846:53	St 2 sep
	1847:05	Centaur MES 1
	1849:13	Centaur MECO 1, 20 min coast	185? x 185? x 28.6?
	1907:27	Centaur MES 2
	1912:27	Centaur MECO 2	178 x -65940 x 29.3
1975 Sep 9	1916:07	Centaur sep	279259 km miss dist
1975 Sep 9	2047:00	Bioshield cap sep
1975 Sep 10	0314	Viking pass EL1:4
1975 Sep 10	0322?	Centaur pass EL1:4
1975 Sep 14	0010	Viking leave ELS1 sphere
1975 Sep 14	0132	Perihelion of post-MC1 orbit
1975 Sep 14	0213	Perihelion of pre-MC1 orbit
1975 Sep 14	0230?	Centaur leave ESL1 sphere
1975 Sep 19			1.00659 x 1.66949 AU x 2.92
1975 Sep 19	1630?	MC1	1.00658 x 1.67114 AU x 2.92
1976 Jul 28		Approach	7775 x -26940 x 42.81
1976 Jul 28	0100	AMC Approach trim	1653 x -20782 x 55.18
1976 Aug 2	2007?	Enter Mars sphere
1976 Aug 7	1129:52	MOI burn 39:35 1.101 km/s
	1209:27	MOI complete	27.6h 1519 x ? x 55.0
1976 Aug 9	1716:00	MOT1 6s 4.1m/s	27.32h 1499 x35531 x 55.2 50.4
1976 Aug 14	0831:15	MOT 2 1.8m/s 3s
1976 Aug 25	1748:29	MOT3 42.7m/s 78s
1976 Aug 27	2025:38	MOT4 11.3m/s 19s sync	24.62h 1489 x 32605 x 55.4 52.2
1976 Sep 3	1920	Lander sep
1976 Sep 29	0433:20	MOT5A 5.0m/s
1976 Sep 30	2107:38	MOT5 342.6m/s	26.78h 1518 x 34933 x 75.1 63.6
1976 Dec 14		Viking Extended Mission
1976 Dec 20		MOT8	26.48h 778 x 35350 x 80.1 -60.6
1977 Mar 2		MOT9	24.73h 751 x 33464 x 80.2 54.4
1977 Apr 18		MOT10	22.73h 723 x 31251 x 80.5 51.9
1977 Apr 18		Survival Automatic Mission
1977 Sep 26		MOT11	24.29h 712 x 33015 x 80.3 34.3
1977 Oct 9		MOT12	24.22h 594 x 33056 x 80.3 32.6
1977 Oct 10		Deimos pass
1977 Oct 12		Deimos pass
1977 Oct 15		Deimos pass
1977 Oct 17?		Deimos pass
1977 Oct 22?		Deimos pass
1977 Oct 23		MOT13	23.98h 302 x 33080 x 80.3 24.8
1978 Mar 3		Bio base jettison
1978 May 31		Viking Continuation Mission
1978 Jul 24	0601	end of ops

1975-083C

---

Viking Lander 2 (VL-2) landed on Mars on 1976 Sep. The biology unit operated until 1977 May 28 and the data storage memory failed on 1979 Nov 19. Low battery voltage on 1980 Apr 12 caused the end of VL-2's mission.

VL2
Date	Time	Event	Orbit
1976 Sep 3	1919:29	Sep from VO2
	1926:30	S+7:01 Deorbit 23 min burn 156m/s
	1948:46	S+29:17 end burn	-103 x 31205 x 55.5
	2228:46	S+3:09:17 entry 244 km 4.6121km/s -17.08 deg
	2236:00	S+3:16:31 Parachute deploy 5.9 km
		Aeroshell base sep 5.0 km
		Aeroshell top sep
	2237:04	S+3:17:35 Terminal descent 1.5 km
	2237:50	S+3:18:21 Touchdown
	2244	Biology PDA lid deploy
	2255	First pictures
1976 Sep 5	1005	Arm cover eject
1976 Sep 7	1439	GCMS PDA lid deploy
1977 May 28		Biology unit off
1980 Apr 12		end of tx
1996 Jul 20		Renamed Gerald A. Soffen Memorial Station

People: June 28,1999

 https://welib.org/md5/94f6a0c47f44cdbd945b72716ef070c1

Kiku 5

 1987-070A

---

ETS-5 (Kiku-5) was launched by H-I on 1987 Aug 27. The satellite was built by Mitsubishi and featured the first flight of the Nissan H-1 apogee motor and the H-1 third stage.

Kiku-5
Date	Time	Event	Orbit
1987 Aug 27	0920	Launch by H-I	TNSC
		T+0:38 SRM 1-6 burnout
		T+0:40 SRM 7-9 on
		T+1:19 SRM 7-9 burnout
		T+1:25 SRM sep
		T+4:28 MECO
		T+4:34 VECO
		T+4:36 St 1 sep
		T+4:40 LE-5 burn
	0925	T+5:04 Fairing
	0930	T+10:38 LE-5 SECO
	0945	T+25:04 LE-5 sep over equator	167 x 215 x 30.4 (B)
	0945	T+25:27 St 3 burn
	0946	T+26:34 St 3 TECO
	0947	T+27:29 Nissan St 3 sep, 219 km at 145W 3S	651.4 212 x 36812 x 27.8 (C)
	0947	T+27:31 St 3 tumble
			216 x 36812 x 27.7
	1530?	Apo 1
	2030?	Peri 1
1987 Aug 28	0230?	Apo 2	629.45 194 x 35708 x 27.5
	0730?	Peri 2
	1300?	Apo 3
	1800?	Peri 3
1987 Aug 29	0000	Apo 4
	0400?	Peri 4
	0900?	Apo 5
	1400?	Peri 5
	1900?	Apo 6	629.38 191 x 35797 x 27.6
1987 Aug 30	0300?	Peri 6
	0600?	Apo 7
1987 Aug 30	0551?	apo 7 AKM burn over 84E, 55s
1987 Aug 31			1386.81 33534 x 36097 x 0.2 GEO 108.2E+12.8E
1987 Sep 3			1395.73 33669 x 36316 x 0.2 GEO 144.3E+10.4E
1987 Sep 4			1410.42 34252 x 36312 x 0.1 GEO 150.7E+6.6E
1987 Sep 9			35702x36178x0.16 GEO 150.8E-2E/d
1987 Sep 10	1400	35708x35978x0.16 GEO 148.9E-0.7/d
1987 Sep 11	1400	35703x35790x0.2 GEO 148.2E+0.5/d
1987 Sep 17		On station
1987 Sep 19			1435.96 35777 x 35790 x 0.1 GEO 150.0E
1987 Nov 11		First NSSK
1988 Dec 20			1436.12 35767 x 35806 x 0.0 GEO 149.9E
1989 Mar 31		end of main program
1991 Feb 22			1436.12 35762 x 35811 x 0.0 GEO 150.0E
1992 Feb		Partners educational transmissions
1993 Apr 21			1436.11 35767 x 35806 x 1.6 GEO 150.3E
1995 Oct 5			1436.12 35766 x 35807 x 3.5 GEO 150.3E
1997 Sep 8			1436.09 35773 x 35799 x 4.9 GEO 150.3E

Kosmos 2349

 1998-009A

---

Kometa 11F660 No. 19 (Kosmos-2349) was launched in Feb 1998. The mission was sponsored by MO RF and RKA's Sovinformsputnik as part of the SPIN-2 commercial mapping program. The payload included the usual panoramic and topographic cameras, and a laser altimeter and doppler instrument.

Kosmos-2349
Date	Time	Event	Orbit
1998 Feb 17	1035:00	Launch by Soyuz-U from KB LC31
	1043	Blok-I MECO
	1043	Blok-I sep
	1455		89.17 200 x 266 x 70.4
	1922		89.13 194 x 268 x 70.38
1998 Feb 18	0254	Orbit raise	89.65 228 x 285 x 70.37
	0717		89.41 212 x 277 x 70.37
1998 Feb 25	0349		89.31 209 x 271 x 70.36
	0638	Orbit raise	89.42 213 x 278 x 70.4
1998 Mar 5	2116		89.33 210 x 271 x 70.4
1998 Mar 6	0444	Orbit raise	89.42 212 x 279 x 70.4
1998 Mar 28			89.35 211 x 273 x 70.4
1998 Mar 29		Orbit raise	89.93 212 x 331 x 70.4
1998 Apr 2			89.90 211 x 327 x 70.4
1998 Apr 3	2325?	Deorbit	-181 x 326
		SB sep
		AO sep
	2345?	Reentry
	2355	Landed

Payload:

• KVR-1000 panoramic camera, 2-m resolution

• TK-350 topographic camera, 10-m resolution

• Star camera

• Laser altimeter

• Doppler instrument

TERRIERS

 1999-026A

---

The Tomographic Experiment using Radiative Recombinative Ionospheric EUV and Radio Sources (TERRIERS) is a UNEX (STEDI) explorer built by AeroAstro/Herndon for PI institution Boston University to study the ionosphere. TERRIERS is based on the HETE bus. Terriers is 0.5 dia x 1.0 long, 125 kg. Terriers and MUBLCOM are separated by an adapter cone of 19 kg, 0.2 x 1.0m.

The Terriers and MUBLCOM satellites were launched on May 18 by an Orbital Sciences Corp. Pegasus XL/HAPS vehicle. The L-1011 Stargazer aircraft took off from Vandenberg's runway 30/22 at 0412 UTC on May 18 and headed to the drop box over the Pacific at 36.0N 123.0W. Stargazer dropped the Pegasus at 0509 UTC and the first stage solid motor ignited five seconds later. At 0518 UTC the third stage motor (cataloged as 1998-26C) burned out and separated, leaving the payload stack in a 405 x 548 km x 97.7 deg orbit. The PRIMEX HAPS-Lite stage then made the first burn of its hydrazine engine and entered a 540 x 553 km x 97.7 deg orbit. The box-shaped Terriers satellite was deployed at 0520 UTC. A minute later the conical Payload Adapter Fitting (1998-26E) was jettisoned, leaving the disk-shaped MUBLCOM satellite attached to HAPS. The second HAPS burn at 0522 UTC raised apogee to 775 km, followed by a third, apogee burn at 0610 UTC which circularized the orbit. MUBLCOM was deployed to a 769 x 776 km x 97.7 deg orbit. The final HAPS burn then placed the depleted HAPS stage (1998-26D) in a lower 388 x 722 km x 97.1 deg disposal orbit.

TERRIERS is a University Explorer (UNEX), part of NASA's Student Explorer Demonstration Initiative (STEDI). It was to be operated by the space physics group at Boston University for ionospheric studies, and carries TESS, a set of extreme ultraviolet (EUV) spectrographs to get electron density and thermospheric emission profiles. The GISSMO instrument will measure the solar EUV flux. The spacecraft was built by AeroAstro and based on HETE.

After orbit insertion, TERRIERS failed to orient itself correctly and lack of solar power depleted the spacecraft battery.

Terriers
Date	Time	Event	Orbit
1999 May 18	0412	T/O Vandenberg RW30/22
	0509:36	Drop
		T+00:05 Pegasus F-27 Stage 1 burn
		T+01:15 Stage 1 BO
		T+01:31 Stage 1 sep
		T+01:31 Stage 2 burn
		T+2:09 Fairing sep
		T+2:43 Stage 2 burnout
	0516:34	T+6:58 Stage 2 sep
	0516:43	T+7:09 Stage 3 burn
	0517:53	T+8:17 Stage 3 cutoff	94.60 447 x 550 x 97.7 (ILAM)
	0518:53	T+9:17 HAPS 1 burn
	0519:06	T+9:30 HAPS 1 cutoff
	0520:07	T+10:31 Terriers sep	95.66 549 x 551 x 97.7 (ILAM)
	0521:07	T+11:31 Adapter cone sep	95.60 541 x 553 x 97.7
	0522:06	T+12:30 HAPS 2 burn
	0522:25	T+12:49 HAPS 2 cutoff	97.75 649 x 652 x 97.7 (ILAM)
	0611:22	T+1:01:46 HAPS 3 burn
	0611:40	T+1:02:04 HAPS 3 cutoff
	0612:20	T+1:02:44 MUBLCOM sep	100.34 773 x 775 x 97.8 (ILAM)
	0614:20	T+1:04:44 HAPS CCAM
	0614:21	T+1:04:45 HAPS cutoff	460 x 775 x 97.8
	0643:01	T+1:33:25 HAPS depletion	95.62 390 x 706 x 97.1 (ILAM)

JCSat 1

 1989-020A

---

Japan Satellite Communication Co. launched the JCSAT 1 satellite as one of the first commercial Japanese domestic communications satellites with 32 Ku-band transponders.

JCSAT 1
Date	Time	Event	Orbit
1989 Mar 6	2329:00	Launch by Ariane 44LP	CSG
		T+1:06 PAP sep
		T+2:29 PAL sep
		T+3:32? St 1 sep
		T+3:34 St 2 MES
		T+4:45 Fairing sep
		T+5:44 St 2 sep
		T+5:58 St 3 MES
	2336:40	T+17:40 St 3 MECO
	2349:12	T+20:12 JCSAT sep
	2351:40	T+22:40 SPELDA sep
	2353:19	T+24:19 MOP 1 sep
1989 Mar 8	0330	LAM-1 20min
	0610	LAM-2 20min
	1145	LAM-3 small burn
	1700	LAM-4 trim
1989 Mar 10			1436.30 35691 x 35889 x 0.1 GEO 150.7E
1989 Jun 30			1436.12 35780 x 35793 x 0.0 GEO 149.9E
1991 Feb 22			1436.12 35780 x 35793 x 0.0 GEO 150.0E
1993 Jul 28			1436.13 35778 x 35796 x 0.0 GEO 150.0E
1996 Jun 3			1436.12 35776 x 35798 x 0.1 GEO 150.0E
1997 May 24			1436.12 35779 x 35794 x 0.1 GEO 150.0E

Apollo 16 (Casper)

 1972-031A

---

Apollo 16 crew

---

• CDR Commander: John W. Young, Capt. USN

• CMP CM Pilot: Thomas K. Mattingly, Lt Cdr USN

• LMP LM Pilot: Charles Duke, Lt Col USAF

Apollo CSM 113, named Casper by the crew, was the Apollo 16 Command and Service Module. It rode into space on a Saturn V in 1972 Apr 16. The S-IVB delivered it onto a translunar trajectory. Once in lunar orbit, the commander and LM pilot entered the Lunar Module (Orion) and undocked. But as the CSM moved away from the LM a fault was detected in its SPS engine. The lunar landing was postponed while the problem was investigated. The LM was only 1 to 2 km away, and resumed stationkeeping at about 200m for a while - it's a bit marginal whether to count this as a separate rendezvous or not. Finally the lunar landing was given the goahead, the circ burn was made, and Orion was given the GO for PDI.

Orion's ascent stage docked back with Casper at 0335 on Apr 24. By 2054 Orion had been jettisoned, and soon after the SIM subsatellite was ejected into lunar orbit. The SPS fired successfully at 0215 on Apr 25 to send Casper back towards Earth.

At 2038 on Apr 25 the CM hatch was opened, and Mattingly retrieved film cassettes from the SIM bay in three trips. The MEC was also exposed. Duke assisted from the hatch area. The CM was depressurized for 1h 24min.

The CSM reentered the Earth's atmosphere on Apr 27, splashdown coming at 1945 UT in the Pacific Ocean. Recovery was by the aircraft carrier USS Ticonderoga.

CSM 113 Mission Log
Date	Time	Event	Orbit
1972 Apr 16	1754:00	SA-511 launch
1972 Apr 16	1756:17	Center engine cutoff
1972 Apr 16	1756:41	Outboard engine cutoff	-6013 X 118
1972 Apr 16	1756:44	S-IC separation, S-II ignition
	1757:14	Interstage sep
	1757:20	LES jett
1972 Apr 16	1801:41	Center engine cutoff
1972 Apr 16	1803:19	Outboard engine cutoff	-2033 x 168 x 32.5
1972 Apr 16	1803:20	S-II separation, S-IVB ignition 2:22
1972 Apr 16	1805:46	S-IVB cutoff T+706s	87.84 167 x 168 x 32.54
	1825	Optics cover jettison
1972 Apr 16	2027:37	S-IVB TLI 5:42 3.166km/s
	2033:18	ECO
1972 Apr 16	2033:29	Translunar injection	310 x 494260 (s)
		V = 10.847 km/s	202 x 471165 x 32.51
	2054	5563 km alt, 8.049km/s
1972 Apr 16	2058:59	CSM separation from SLA-20, mass 30378
		Alt 6967 km	203 x 483905
1972 Apr 16	2109:18	Docked with LM 11/SIVB
	2115:53	Hard docked
1972 Apr 16	2153:15	CSM/LM separation from SIVB
1972 Apr 17	0230	HO to LM to check venting particles
	0315?	HC to LM
1972 Apr 17	1014?	Pass EL1:4
1972 Apr 18	0033:01	MCC2 mid course correction; perilune 131 km
	0033:03	MCC2 cutoff
		HO to LM
1972 Apr 19	0513:45	Equigravisphere
1972 Apr 19	1553:01	SIM door ejection, range 20634 km vel 1.188km/s
1972 Apr 19	2022:28	LOI-1 burn (SPS) 854m/s
1972 Apr 19	2028:43	Lunar orbit insertion	108 x 315 km
1972 Apr 20	0027:45	DOI/LOI-2 burn (SPS) 24s 18797 kg 62m/s	20 x 108 km
1972 Apr 20	1600?	Cdr, LMP transfer to LM
1972 Apr 20	1807:31	LM undocked
1972 Apr 20	1807:31	Small sep burn	19 x 110 km
	1934:17	SPS sep burn cancelled
1972 Apr 20		Fault detected in SPS
	2000	At 200m to Orion
	2157	At 1 km to Orion
1972 Apr 20		Rev 14 re-rendezvous with Orion from 2 km
	2219	RCS burn
	2225	At 1.7 km, 1m/s
	2235	RCS
	2236	1 km, 1m/s
	2302	At 216m, 0.6m/s
1972 Apr 21	0024:00	Sep burn 2, 0.3m/s	21 x 111 km
1972 Apr 21	0115:42	Circ burn 17733 kg	98 x 126 km
1972 Apr 23	1859:52	LOPC-1 plane change burn	102 x 120 km
1972 Apr 24	0335:18	Docking by LM 11 Orion ascent stage
1972 Apr 24		Cdr and LMP transfer to CSM with cargo
1972 Apr 24	2054:12	Orion undocked	100 x 126 km
1972 Apr 24	2057:13	Sep burn	97 x 123 km
1972 Apr 24	2117:12	Mass spectrometer boom jettisoned 2m/s
1972 Apr 24	2156:09	Subsatellite ejected
1972 Apr 25	0215:33	TEI burn (SPS) 1.026km/s 4:02
1972 Apr 25	0218:15	Transearth Injection
1972 Apr 25	1435:51	Leave lunar sphere
1972 Apr 25	1629:03	MCC-5
	1629:25	MCC-5 cutoff
1972 Apr 25		EVA for film retrieval
	2034	Begin depress from 3.5psi
	2036	At 1 psi
	2037	At 0.7psi
	2039	At 0.1psi
	2041	HO
	2043	Jett bag
	2044?	CMP egress
		At 322180 km
	2051	2 pan camera covers removed (jett?)
	2101	2 mapping camera covers removed
	2117	MEED deploy
	2132	Retrieve MEED
	2140	CMP ingress
	2141	HC
	2145	Begin repress
	2146	0.7psi
	2158	3.5psi at 317431 km
1972 Apr 26
1972 Apr 27	1631:21	MCC-7 4s 0.4m/s
	1631:27	MCC-7 CO
1972 Apr 27	1916:33	SM-113 separation
1972 Apr 27	1931:31	Entry interface
1972 Apr 27	1945:05	Splashdown in Pacific Ocean, 5 N 158 W.
1972 Apr 27	Recovered by USS Ticonderoga

Hispasat 1A

 1992-060A

---

The Eurostar 2000 satellite was built by MMS/BAe for Hispasat of Spain as the first Spanish domestic comsat. It provided FSS and DBS services to the Iberian peninsula, and Ku-band FSS services to Latin America.

Hispasat 1A
Date	Time	Event	Orbit
1992 Sep 10	2304	Launch by Ariane 4	CSG ELA2
	2305	PAL sep (T+1:07)
	2306	Stage 1 sep (T+2:28)
	2307	Fairing sep (T+3:35)
	2308	Stage 2 sep (T+4:39)
	2309	H-10+ ignition (T+5:47)
	2322	H-10+ shutdown (T+18:17)
	2324	Hispasat 1A sep (T+20:32)
	2327	SPELDA sep (T+23:21)
	2328	Satcom C3 sep (T+24:55)
	2329	H10+ sep mvr (T+25:25)
	2334	H10+ blowdown (T+29:55)
1992 Sep 11	0600?	Deploy DBS antenna and booms	631.09 217 x 35769 x 6.9
1992 Sep 12	1200?s	LAM1 burn	834.16 10234 x 35715 x 2.6
1992 Sep 14	1900?s	LAM2 burn
1992 Sep 16	1300?	LAM3 burn
1992 Sep 17		Deploy solar panels
1992 Sep 20			1430.96 35611 x 35759 x 0.1 GEO 35.4W+1.3E
1992 Sep 25			1434.20 35736 x 35762 x 0.1 GEO 30.8W+0.4E
1992 Sep 30			1436.03 35777 x 35793 x 0.0 GEO 30.1W+0.0E
1992 Dec 4			1436.14 35781 x 35793 x 0.0 GEO 29.9W
1993 Aug 28			1436.03 35769 x 35801 x 0.0 GEO 30.1W
1994 May 24			1436.14 35776 x 35798 x 0.1 GEO 30.0W
1997 Jan 8			1436.12 35779 x 35794 x 0.0 GEO 30.0W

Kosmos 1205

 1980-068A

---

Two-tone telemetry; Hi res satellite

Kosmos-1205
Date	Time	Event	Orbit
1980 Aug 12	1150	Launch by Soyuz-U	Plesetsk
	1154	Blok-I burn
	1158	Blok-I sep
1980 Aug 12			89.46 198x296x72.8
1980 Aug 14			89.57 199x306x72.8
1980 Aug 15			89.87 229x306x72.8
1980 Aug 16			89.63 226 x 285 x 72.8
1980 Aug 20			89.55 224x279x72.8
1980 Aug 26
	0536?	Deorbit
	0545?	PO sep
	0553?	Entry
	0610?	Landed

Kosmos 2282

 1994-038A

---

Kosmos-2282 was launched in Jul 1994 and operated for slightly over a year from the 24W Atlantic Ocean position. It appears to have used the 5th orbit perigee burn.

Kosmos-2282
Date	Time	Event	Orbit
1994 Jul 6	2358:51	Launch by Proton-K/DM-2	KB
1994 Jul 7	0008	Stage 3 sep
	0710?	DM burn 1
	1230?	DM burn 2
	1250?	DM sep
1994 Jul 7			1453.23 36102 x 36140 x 2.4 GEO 0.8W+4.2W
1994 Jul 13			1443.11 35759 x 36088 x 2.2 GEO 21.9W+1.7W
1994 Jul 21			1436.68 35756 x 35839 x 2.3 GEO 24.5W+0.1W
1994 Jul 22			1435.96 35754 x 35813 x 2.3 GEO 24.4W
1994 Oct 2			1436.13 35745 x 35828 x 2.1 GEO 23.7W
1995 Apr 4			1436.18 35763 x 35812 x 1.8 GEO 24.5W

NATO 2B

  1971-009A

---

NATO IIB was launched in 1971 to supplement NATO IIA. Initially stationed at 26W over the Atlantic, it was stationed at 105W from the mid 1970s until 1983, when it moved slightly to 110W, stored in the stable location in the `western pit'.

NATO IIB
Date	Time	Event	Orbit
1971 Feb 3	0141:40	Launch by Delta M	CK LC17
		Azimuth 100 deg
		SRM 1-3 sep
	0145:19	T+3:39 MECO
		St 1 sep
	0145:22?	SES-1 6:14.6
	0151:36?	SECO-1
	0206?	St 2 sep	-186 x 286 x 28.6
	0207?	TES 43.5s
	0208?	TECO
	0209?	St 3 sep	665.05 283 x 37437 x 25.9 (TLE)
			673.90 273 x 37712 x 25.9 (MOR Post)
1971 Feb 5	0456	AKM 20.1s over 135E, 1E/d	34493 x 37053 x 0.0
1971 Feb 10	s	Over Camp Parks, Calif.
1971 Mar		AOR	GEO 26W
1975 Jun		alter location?
1975 Dec			GEO 18W
1976 Aug 19		Last TWTA failed
1976 Oct 31		On-orbit tests, mv in	GEO 107W
1977 Jan 25			1436.11 35777 x 35795 x 2.4 GEO 105.1W
1980 Dec 14			1436.07 35759 x 35813 x 5.0 GEO 105.1W
1981 Jun			GEO 105W+0.05E 5.4
1982 Oct			GEO 105W
1982 Nov 27			1436.09 35762 x 35811 x 6.3 GEO 105.6W
1982 Dec?		Move to 110W
1983 Feb 18			1436.09 35766 x 35806 x 6.6 GEO 110.2W
1983 May 5			1436.04 35769 x 35801 x 6.7 GEO 109.9W
1983 May		Begin drift
1983 Oct 25			1435.95 35767 x 35801 x 7.1 GEO 105.0W
1983 Dec 4		Move in	1436.01 35755 x 35814 x 7.0 GEO 104.9W
1984 Jun 1			1436.10 35779 x 35793 x 7.4 GEO 105.0W+0.0E
1984 Oct 11			1436.21 35780 x 35797 x 7.6 GEO 101.9W
1984 Dec 30			1436.22 35776 x 35801 x 7.7 GEO 104.3W
1989 Mar 14			1436.1 35769 x 35803 x 10.9 GEO 104.9W
1983 Nov 2			GEO 104.8W +0.02/d
1994 Nov 7			1436.09 35783 x 35789 x 14.3 GEO 105.5W
1998 Aug 4			1436.07 35772 x 35799 x 15.2 GEO 105.2W

NTS 2

 1977-053A

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NRL's Navigation Technology Satellite 2 (Space Test Program mission P76-4/NRL-116) was launched on 1977 Jun 23 as a prototype for the Navstar GPS system. The single Star 37 used to orbit NTS 1 was replaced by a two-stage SVS which placed NTS 2 in the higher 12-hour orbit used by GPS. Fairchild was the SVS contractor. Like NTS 1 it used an octagonal structure and two gravity booms, but two orientable solar panels were used.

Apogee burn had been planned on first apogee but was delayed until sixth apogee. The satellite worked into the 1980s. It was known by NRL as Timation IV.

NTS 2
Date	Time	Event	Orbit
1977 Jun 23	0817	Launch by Atlas F/SVS (65F)	V SLC3W
	0822	T+6m Atlas sep
		SVS spinup
	0822	S+20s SVS stage 1 (Star 37E) burn
	0823	SVS Stage 1 burnout
	0823	SVS stage 2 (Star 37E) burn
	0824	SVS stage 2 burnout
	0828	SVS sep	160 x 20106
	1130?	Apo 1
	1700?	Apo 2
	2300?	Apo 3
1977 Jun 24	0500?	Apo 4
	1100?	Apo 5
1977 Jun 24	1630?	Apo 6
	1633?	AKM (TLE) Star 27 burn
	1637?	Star 27 AKM sep
1977 Jun 29		RCS burn 0.48m/s
1977 Jul 1		RCS burn 0.67m/s
1977 Jul 6		RCS burn 0.92m/s
1977 Jul 7		Solar panels deployed
1977 Jul 23			718.02 20178 X 20188 X 63.3
1977 Oct 24			717.96 19995 X 20368 X 63.3
1979 Jul 25			717.89 20143 x 20216 x 63.6
1983 Nov 12			717.88 20093 x 20266 x 64.4
1996 Dec 29			718.19 20068 x 20306 x 63.4

Crystal 9

 1988-099A

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The final KH-11 satellite was launched in Nov 1988. CRYSTAL 9 (USA 33) was placed in a west plane (0948LTDN) orbit with a 1000 km apogee.

CRYSTAL 9
Date	Time	Event	Orbit
1988 Nov 6	1803	Launch by Titan 34D	V SLC4E
	1804	Core engines on (T+1:47)
	1804	SRM jettison (T+1:56) at 39 km
	1807?	T+4min? Stage 1 sep
	1807?	Stage 2 ignition (T+4:33?)
	1807?	Fairing off (T+4:46?)
	1811?	Stage 2 cutoff (T+7:58?)
	1811?	Stage 2 sep (T+8:08?)
			156 x 1012 x 97.9 (UN)
			154 x 1008 x 97.9 (UN, 99B)
1989 Aug 9			97.24 330x922x98.0
1989 Aug 13			97.71 322x976x98.0
1989 Aug 18			97.70 289x1008x97.9
1990 Jun 1			97.54 283x997x97.8
1991 May 27			97.49 290x986x98.0
1996 May 12			97.64 270 x 1020 x 97.9

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