Ekspress 1

 1994-067A

---

The first Ekspress satellite was launched in 1994. Ekspress No. 11L was designated Ekspress-2 on orbit at 14W. The satellite failed in Jun 2001, interrupting Intersputnik services briefly until traffic was transferred to Ekspress-3A.

Ekspress No. 11
Date	Time	Event	Orbit
1994 Oct 13	1619:00	Launch by Proton	KB
	1628	Stage 3 sep
	1628	Adapter sep	185? x 200? x 51.6
	1732?	DM burn 1
		DM MECO-1	200? x 36000? x 48.0?
	2250?	DM burn 2
	2300?	DM sep
1994 Oct 13			1440.78 35862 x 35893 x 0.2 GEO 91.1E+1.1W
1994 Oct 24			1441.47 35863 x 35920 x 0.2 GEO 76.2E+1.3W
1994 Nov 8			1435.87 35778 x 35785 x 0.2 GEO 70.7E+0.05E
1994 Dec 28			1436.12 35781 x 35792 x 0.1 GEO 71.3E
1995 Jan 4			1436.11 35779 x 35793 x 0.1 GEO 71.3E
1995 Jan 5		mv out
1995 Feb 14		mv in	1436.04 35776 x 35794 x 0.1 GEO 14.0W
1995 Jun 14			1436.14 35773 x 35801 x 0.1 GEO 13.9W

Kosmos 2290

 1994-053A

---

Kosmos-2290 was deorbited in Apr 1995 over the Pacific, reentering approx 2720 km E of Wellington, NZ. According to Phillip Clark, mass of Kosmos-2290 was around 10600 kg.

The Yuzhnoe book implies the name Orlets.

At launch, the usual four high-orbit Zenit rocket separation motor covers were cataloged. In addtion, two small debris objects were found in the payload orbit, which may be sensor covers of some kind. The satellite was deorbited on 1995 Apr 4; two days earlier four objects were ejected.

Debris was found in Mexico, including parts from a 17D62 engine.

Kosmos-2290
Date	Time	Event	Orbit
1994 Aug 26	1200:00	Launch by Zenit-2	KB
	1202:28	Stage 1 sep
	1204:58	Fairing sep
	1207:18	Stage 2 MECO
	1210:28	Stage 2 VECO
	1210:29	Stage 2 sep
1994 Aug 26			89.55 211 x 292 x 64.8
1994 Aug 30			89.50 210 x 288 x 64.8
1994 Sep 6			89.38 208 x 279 x 64.8
1994 Sep 6		Orbit raise	90.08 208 x 347 x 64.8
1994 Sep 30			89.66 201 x 314 x 64.8
1994 Oct 1		Orbit raise	89.84 209 x 323 x 64.8
1994 Oct 14			89.53 204 x 298 x 64.8
1994 Oct 14		Orbit raise	89.89 206 x 330 x 64.8
1994 Oct 20			89.79 203 x 323 x 64.8
1994 Oct 20		Orbit raise	90.13 205 x 356 x 64.8
1994 Oct 29			89.96 201 x 342 x 64.8
1994 Oct 29		Orbit raise	90.32 213 x 366 x 64.8
1994 Nov 5			90.21 212 x 357 x 64.8
1994 Nov 10			90.12 210 x 350 x 64.8
1994 Nov 11		Orbit raise	90.28 209 x 366 x 64.8
1994 Nov 15			90.22 209 x 361 x 64.8
1994 Dec 14			89.74 200 x 322 x 64.8
		Orbit raise
1994 Dec 14			90.37 202 x 382 x 64.8
1994 Dec 28			90.13 200 x 361 x 64.8
		Orbit raise
1994 Dec 28			90.63 200 x 410 x 64.8
1995 Jan 26			90.16 193 x 371 x 64.8
1995 Jan 26		Orbit adjust
1995 Jan 27			89.88 192 x 344 x 64.8
1995 Jan 30			89.79 190 x 337 x 64.8
1995 Jan 31		Orbit raise	90.34 191 x 391 x 64.8
1995 Feb 7			89.96 177 x 367 x 64.8
1995 Feb 8		Orbit raise	90.35 181 x 401 x 64.8
1995 Feb 12			89.19 179 x 387 x 64.8
1995 Feb 13		Orbit raise	90.33 181 x 399 x 64.8
1995 Feb 22			89.97 178 x 367 x 64.8
1995 Feb 23		Orbit raise	90.72 180 x 439 x 64.8
1995 Mar 5			90.31 177 x 401 x 64.8
		Orbit raise	90.96 184 x 458 x 64.8
1995 Mar 15			90.65 183 x 429 x 64.8
1995 Mar 16		Orbit lower	90.39 182 x 404 x 64.8
1995 Mar 27			90.00 179 x 370 x 64.8
1995 Mar 28		Orbit raise	82.14 181 x 576 x 64.80
1995 Apr 2		53J,K,L,M ejected
1995 Apr 3			91.93 180 x 557 x 64.80
1995 Apr 4	2355	Deorbited over Pacific
1995 Apr 5	0155?	Entry over Mexico?

USA-82

 1992-037A

---

The second Atlas II launch for DSCS III carried the B-12 satellite, named USA 82 on orbit. The IABS placed B-12 in the correct orbit, but the IABS IRU/gyro system had an electronics failure that precluded its use on-orbit, and the satellite operated using the standard DSCS system.

DSCS III B-12
Date	Time	Event	Orbit
1992 Jul 2	2154	Launch by Atlas II	CC LC36A
	2156	Booster sep (T+2:49)
	2159	Centaur MES1 (T+5:00)
	2205	Centaur MECO1 (T+11:20)
	2218	Centaur MES2 (T+24:00, burn 1:50)
	2220	Centaur MECO2
	2223	Centaur sep (T+29:10)	617.3 223 x 35053 x 26.5 (UN)
1992 Jul 4?		IABS burn
			1416.6 35289 x 35520 x 0.3, IABS (UN)
			1436.2 35775 x 35800 x 0.2 (UN)
1995 Jul		ELANT Prime	GEO 12.0W
1997 Oct		ELANT Prime	GEO 12.0W
2002 Jun		Orbit raised
2002 Jul 30		Decommissioned

Aviation Week: August 25,2003

 https://welib.org/md5/b2ce716ec50981ee3c66d89432b6e0c9

Westar 6 (Asiasat 1)

 1984-011B / 1990-030A

---

The Westar 6 satellite was carried into orbit on the Space Shuttle Challenger in Feb 1984. Deployment from the cargo bay was normal, but when the PAM-D upper stage ignited the nozzle failed and the satellite was left in a low elliptical orbit. It was recovered by the 51-A mission. The underwriters, Merritt Syndicates, sold the satellite to Asiasat. Asiasat (the Asia Satellite Telecommunications Co. of Hong Kong) is a consortium of Cable & Wireless, Hutchinson Wampoa and the China International Trust and Investment Corp. (CITIC). Asiasat got Hughes to refurbish the satellite; it was then relaunched from China aboard a CZ-3 rocket, this time reaching GEO successfully. It was used for regional SE Asian communications.

Westar 6 (Asiasat 1)
Date	Time	Event	Orbit
1984 Feb 3	2059:23	Westar 6 deploy from OV-099
1984 Feb 3	2145	PAM-D burn
1984 Feb 3		PAM-D loss of control
1984 Feb 3	2146?	PAM-D sep	100.0 300 x 1214 x 27.7
1984 Feb 6			100.02 303 x 1215 x 27.7
1984 Feb 8			100.02 303 x 1215 x 27.7
1984 Feb 9			99.94 295 x 1215 x 27.7
1984 Feb 27			99.89 296 x 1210 x 27.7
1984 May 5			99.74 305 x 1186 x 27.7
1984 May 12			99.75 305 x 1187 x 27.7
1984 May 12		mv up	107.64 357 x 1192 x 27.9
1984 May 12	1648	AKM fired	107.64 1070 x 1164 x 28.5
1984 Jul 19			107.64 1070 x 1165 x 28.5
1984		Ownership to Merritt Syndicates
1984 Aug 6		mv	106.11 1042 x 1050 x 28.5
1984 Oct 9			106.11 1042 x 1050 x 28.5
1984 Oct 11		lower orbit	103.81 820 x 1056 x 28.5
1984 Oct 12			100.34 490 x 1058 x 28.5
1984 Oct 13		lower orbit	99.06 370 x 1056 x 28.5
1984 Oct 14			99.05 364 x 1061 x 28.5
1984 Oct 16			98.76 352 x 1046 x 28.5
1984 Oct 18			97.75 354 x 947 x 28.5
1984 Oct 19			96.96 355 x 867 x 28.5
1984 Oct 23			95.27 357 x 706 x 28.5
1984 Oct 27			92.73 352 x 463 x 28.5
1984 Oct 28			91.72 342 x 375 x 28.5
1984 Nov 2			91.91 361 x 375 x 28.5
1984 Nov 14			91.77 353 x 369 x 28.5
1984 Nov 14		OV-103 rendezvous with Westar 6
	1232	MMU/Gardner dock Westar
		RMS grapple Westar
		MMU undock ACD
	1327?	MMU berthed
	1442	Base adapter on
		Westar berthed
1984 Nov 16		OV-103 landed
1987 Jun 25		Sold to Asiasat
1990 Apr 7	1330:02	Launch by CZ-3	XSC
	1332:09	Stage 1 sep, 50km
	1334:25	Stage 2 sep
	1334:25	Stage 3 MES1
	1341:30	T+11:28 Stage 3 MECO
	1345:32	Stage 3 MES2
	1351:29	Stage 3 sep at perigee
1990 Apr 9	0343?	Star 30C burn
1990 Apr 9			1438.01 34902 x 36745 x 0.3 GEO 130.3E+0.4W
1990 Apr 14			1456.17 35797 x 36559 x 0.3 GEO 109.1E+4.9W
1990 Apr 15		On station	GEO 105.5E
1990 Apr 19			1436.10 35782 x 35790 x 0.2 GEO 105.6E
1992 Mar 29			1436.16 35776 x 35799 x 0.1 GEO 105.5E
1994 Feb 10			1436.11 35785 x 35788 x 0.0 GEO 105.5E
1996 Mar 5			1436.06 35777 x 35794 x 0.0 GEO 105.6E
1999 Jun 14			1436.15 35785 x 35789 x 0.2 GEO 105.6E
1999 Jun 17		mv out
1999 Aug 14		Move in to 122E
2000 Jun 10			1436.10 35783 x 35790 x 1.0 GEO 122.1E
2003 Jan 23			1436.28 35784 x 35796 x 3.2 GEO 121.4E

USA-174

 2003-057A

---

The contract for an extra UHF satellite was given in 1999. HS-601 launch by Atlas 3B/SEC AC-203. Launch mass 3041 kg.

UHF F11
Date	Time	Event	Orbit
2003 Dec 18	0230	Launch by Atlas 3 AC-203	CC SLC36B
	0224:00	Launch per Cleary report
		T+3:00 BECO
		T+3:07 Atlas sep
		T+3:18 MES1
	0233	T+3:26 Fairing sep
		T+4:40	172 km 3.933 km/s
	0244	T+14:54 MECO-1	185 x 1092 x 28.1
	0254	T+24:37 MES-2
	0257	T+27:42 MECO-2
	0302	T+32:25 Centaur sep	288 x 35905 x 27.0
2003 Dec 19?		LAM burn

Gruzomaket

 2003-055A

---

978 kg dummy Kondor-E satellite on Strela test launch. Refurbished UR-100NU. NPO-M (Mashinostroenie). The satellite is a box

KGCh-2 payload section; rocket is 29.2l 2.5d 100t (Strela can also have KGCh-1 normal warhead fairing). Third stage is APB-OIA: agregatno-priborniy blok, equipment-service stage, with extra 2.4m dia 0.8m long otsek ismeritel'noy apparaturi, instrumentation module. The Strela rocket has the designation 14A036 and the APB is 14S425.

Mark Wade's site suggested an APB mass of 1100 kg full 725 kg empty with an Isp of 200s. With a 1000 kg payload this gives a delta-V of 1961 ln ( 2100 / 1725 ) = 386 m/s implying a preburn orbit of around -770 x 460 km. A plausible range given uncertainties in mass and Isp is 350-450 m/s, giving (-950 to -650) x 460 km.

The Strela user manual gives details of an ascent to a 1000 km orbit; the stage 2 sep, pre-APB orbit is then -600 x 1000 km. The fairing jettison at 114 km is to a -5485 x 190 km orbit; the stage 1 seps to -5740 x 165 km at 70 km.

The RKN 14A036 Strela used the 15S300 booster, the 14S425 APB, and the payload was KGCh 14S135, consisting of the 14S620 OIA, the 14S134 fairing, and the mass model GVM30201-14S135.

Gruzomaket
Date	Time	Event	Orbit
2003 Dec 5	0600:00	Launch by Strela	KB PL175/2
	0602	T+2:07 Stage 1 MECO
	0602	T+2:07 Stage 2 burn 3:03
	0602	T+2:08 St 1 sep
		T+2:59 Fairing sep at 114 km
	0604	T+4:48 Stage 2 MECO
	0605	T+5:06 Stage 2 VECO
	0605	T+5:07 Stage 2 sep at 200 km
	0605	T+5:07 OIA burn for attitude control
	0616	T+16:27 OIA cutoff
	0616	T+16:27 APB burn
	0619	T+19:20 APB MECO
	0619	T+19:52 APB sep	93.74 452 x 461 x 67.08
	0620	T+20:17 APB depletion	93.04 389 x 457 x 67.08

STS-83 (Columbia)

 1997-013A

---

STS-83 was the MSL-1 (Microgravity Science Lab) Spacelab/EDO mission. An afternoon launch on April 4 followed a one-day technical delay; the count was held at the T-19 hour mark to add thermal insulation to a water coolant line. Columbia carried the Spacelab Long Module as well as the OARE acceleration monitor and a Hitchhiker-G experiment (CRYOFD) in the cargo bay. The middeck included a set of protein crystallography experiments.

Commander Jim Halsell was on his third flight, but his first as commander. Susan Still became the second woman to sit in the pilot's seat, while Janice Voss was payload commander with mission specialists Michael Gernhardt and Don Thomas. Thomas was lucky to be aboard - he broke an ankle during training, and Cady Coleman was named as a last-minute backup. A couple of weeks before launch, however, Thomas was cleared for flight and Coleman stood down. Two payload specialists completed the crew, both materials scientists. Roger Crouch was a long-time NASA scientist currently stationed at NASA Headquarters. He had been alternate PS for an earlier Spacelab mission. Gregory Linteris worked at the National Institute for Standards and Technology.

Problems with Fuel Cell 2 became apparent on Apr 5, and on Apr 6 after hours of discussion Mission Control declared a Minimum Duration Flight (MDF), with a return to Earth on Apr 8 instead of the originally planned Apr 19.

Date	Time	Event	Orbit
1997 Mar 5		Tow to VAB
1997 Mar 11	1130	Rollout to LC39A
1997 Apr 4	1920:32	Launch	KSC LC39A
	1922:35	SRB sep
	1929:04	MECO
	1929:23	ET sep	88.22 69 x 303 x 28.46
	2000:27	OMS 2 2:23 68m/s	90.56 300 x 303 x 28.46
	2002:50	OMS 2 CO
	2109	PLBD open complete
	2120?	Fuel cell problem
1997 Apr 5			90.55 299 x 303 x 28.47
1997 Apr 6	1930	Fuel Cell 2 shut down
		MDF declared
1997 Apr 7			90.53 298 x 303 x 28.47
1997 Apr 8	1455	PLBD closed	90.52 297 x 301 x 28.47
	1731:18	OMS DO 3:22 99.0m/s	-34 x 301 x 28.5
	1734:40	OMS DO CO
	1801	Entry interface
	1833:11	MGTD KSC RW33, 3:23:12:39
	1833:23	NGTD
	1834:10	Wheels stop

Gossip Girl #2: You Know You Love Me

 https://welib.org/md5/c90341d4198a0b07a59f6007b326dc45

Apollo 8

  1968-118A

---

---

Apollo 8 Crew

---

• Commander: Frank Borman, Col. USAF

• Senior Pilot: James Lovell Jr., Capt. USN

• Pilot: William Anders, Maj. USAF

Apollo CSM 103 was launched on the AS-503 mission (Apollo 8) at 1251 on 1968 Dec 21. Apollo 8 was a historic mission - for the first time human beings would leave Earth's gravitational sphere of influence and head for the Moon. Apollo 8 entered a 179 x 190 km x 32.6 deg Earth parking orbit at 1302, and at 1541 the S-IVB stage reignited for translunar injection - TLI. The Apollo separated from the Saturn, turned around for practice at stationkeeping, and then moved away to begin its cruise to the Moon.

At 2029 on 1968 Dec 23, Borman, Lovell and Anders passed through the point at which the Moon's gravity became greater than the Earth's. At 1003 on Dec 24 they fired up the SPS engine to enter an elliptical orbit around the Moon. The orbit apogee was lowered to circularize the path at 1426.

The Apollo 8 spaceship spent a day in lunar orbit, taking the famous `Earthrise' photo of the Earth rising above the lunar horizon.

CSM 103 began its flight back to the Earth at 0610 on 1968 Dec 25, the SPS engine boosting it out of lunar orbit. At 1519 on Dec 27 the Service Module was jettisoned to burn up in the Earth's atmosphere. The CM began reentry at 1537, at 122 km altitude, making the first piloted `skip reentry'. CM-103 descended to 55 km and then rose again to 64 km before descending toward the Pacific. It would fly a range of 2500 km from entry to splashdown. The Command Module touched down in the Pacific at 1551 on 1968 Dec 27.

Apollo CSM 103 Mission Log
Date	Time	Event	Orbit
1968 Dec 21	1251:00	Launch of SA-503
1968 Dec 21	1253:06	S-IC center engine cutoff
1968 Dec 21	1253:33	S-IC outboard engines cutoff
1968 Dec 21	1253:34	S-IC-503 separation, altitude 80.5 km
1968 Dec 21	1254:08	LES separation
1968 Dec 21	1259:44	S-II-3 separation	-2286 x 192 x 32.66
1968 Dec 21	1259:45	S-IVB burn ignition
1968 Dec 21	1302:25	S-IVB main engine cutoff
1968 Dec 21	1302:35	Earth orbit insertion,	179 x 190 km x 32.6 deg
	1333:05	Optics cover jettison
1968 Dec 21	1541:38	S-IVB TLI burn
1968 Dec 21	1546:55	S-IVB main engine cutoff
1968 Dec 21	1547:05	Translunar injection	214 x 544356 x 30.71
		C3 = -1.479	218 x 545303 x 31.07
1968 Dec 21	1611:59	S-IVB-503 separation	141 x 538222 x 30.71
1968 Dec 21	1613	Stationkeeping exercise
1968 Dec 21	1631:01	Sep (RCS)
1968 Dec 21	1736:01	Sep-2 (RCS) 2.3m/s
1968 Dec 21	2351	MCC-1 (SPS mid course correction)	308 x 535599 x 30.6
1968 Dec 23	2029	Equigravisphere
1968 Dec 24	0150:55	MCC-4 (RCS mid course correction)
1968 Dec 24	0959:02	Begin LOI-1	122 x -11021 x 145.49
	1003:27	LOI-1 (SPS lunar orbit insertion, 4:06)	110 x 293 x 151.2
1968 Dec 24	1007:34	Lunar orbit insertion,	112 x 313 km x 168 deg
1968 Dec 24	1426:07	LOI-2 (SPS burn, 10s)	109 x 305 x 156.8 (MR)
	1426:17	LOI-2 CO	112 x 113 km x 168 deg
1968 Dec 25	0610:16	TEI (SPS 3min23s burn)	105 x 115 x 150
1968 Dec 25	0613:39	Transearth Injection	110 x -8518 x 153.7
		Return to Earth gravity sphere
1968 Dec 25	2050:54	MCC-5 (midcourse correction)	-585 x 982887 x 37.7
1968 Dec 27	1519:48	SM-108 separation
1968 Dec 27	1537:12	Entry interface 11.040km/s at -6.50deg	38 x 1038993 x 37.2
1968 Dec 27	1551:42	Splashdown, 08 08 N, 165 W, Pacific Ocean
1968 Dec 27	1645	Recovery by USS Yorktown

Transit 4A

  1961-015A

---

The Transit IVA satellite tested out the SNAP 3A radioisotope thermoelectric generator (RTG), a nuclear power supply. The spacecraft bus was a new cylindrical design and used magnetic rather than yo-yo despin. The SR and Injun satellites separated from Transit.

The Ablestar rocket exploded when residual propellants ignited.

Gatland (1961) reports a launch time of 1623 UTC (1223 EDT), 12 hours off from the value I have.

Transit IVA
Date	Time	Event	Orbit
1961 Jun 29	0423	Launch by Thor Ablestar	CC LC17
	0425	Thor sep
	0426?	Ablestar burn 1
		Ablestar MECO	150? x 1000? x 66
		Ablestar burn 2
	0451	Ablestar MECO-2
		Ablestar sep
		SR/Injun sep
			881 x 998 x 66.81
	0608:10	Ablestar exploded
1961 Jul 15		Solar cell experiment end of ops
1970 May		Beacon still transmitting
1974?		End of transmissions?

Payload:

• Beacons C 54/324 MHz Z 150/400 MHz

• SNAP 3A RTG

• Solar cell test panel

Town and Country: June 2003

 https://welib.org/md5/5b5f83ec5df9a6db760b4a0810b790c6

Nozomi

 1998-041A

---

THe ISAS Planet B mission will study the Martian atmosphere and its interaction with the solar wind. It will have a periapsis of 150 km. Mass is 540 kg. Fuel is 278 kg. Craft has 4 25-m wire antennae giving 50m span, were to be deployed at Mars; this did not happen because of the failures.

Launch Jul 4 1998, lunar swingby, Mars MOI Oct 1999. Planet B is built by NEC Corp. Planet B's NMS instrument is a modernized version of the one flown on Pioneer Venus.

Named Nozomi (`Desire' or `Hope') after launch. Nozomi made six elliptical orbits from Jul to its first lunar flyby in 1998 Sep. It then arced out to 1.7 Mkm around Nov 10 and fell back to a second lunar swingby in December, followed two days later by an Earth pass for solar orbit injection. The perigee burn didn't provide enough thrust, so the Oct 1999 MOI was delayed to Dec 2003.

A double Earth swingby in Dec 2002 and Jun 2003 has been discussed.

In Apr 2002 solar flares damaged the spacecraft's communication systems and the heaters for the RCS system. The hydrazine froze but warmed up as Nozomi got closer to the Sun. In the absence of telemetry, ISAS used a capability to switch the radio beacon on and off to confirm that commands were being received correctly during the Dec 2002 swingby.

On 2003 Dec 1, Nozomi was on a 894 km x Inf Mars hyperbolic trajectory with periapsis on Dec 14.

Stage 3 burn: M34 mass 11600 900 Isp 301 burn 102 thrust 294 Ve 2952 Mdot is T/Ve = 99.6 kg/s so for 102s have 10160 kg. m1/m2 = 11600+P/900+P, P = 1864 so 13464 / 2764 dV = 4674m/s

Stage 4 burn: KM-V mass 1324 124 + 540. m1/m2 = 1864/664 Ve = 2942 dV = 3036 m/s

Planet B
Date	Time	Event	Orbit
1998 Jul 3	1812	Launch by M-V-3	KASC
		Stage 1 burn
		T+1:15 Stage 1 sep
		T+1:15 Stage 2 burn
		T+3:33 St 2 sep?
		T+3:38 Stage 3 burn
	1817	T+5:23 Stage 3 burnout
			161 x 422 x 31.10 (ISAS p319)
			146 x 417 x 31.7
		T+19:59 Spin motor ig
	1832	T+20:24s? Stage 3 sep
	1832	T+20:11s KM burn Isp 300s
	1833	T+21:22s KM burnout dV= 3.160km/s
	1835	T+23:19? KM-V1 sep
			359 x 401491 x 28.6
1998 Jul 4	0933	Pass EL1:4
1998 Sep 24		Lunar flyby 1, 4000 km
1998 Nov 10?		Apogee	? x 1.7 Mkm
1998 Dec 18	0734	Lunar flyby 2 C/A = 4547 km
1998 Dec 20	0809:54	Perigee C/A=7381 km, 7min TMI burn, underspeed
		Earth escape
1998 Dec 20	2301	Correction burn 1
1998 Dec 20	2339	Correction burn 2
1999 Jan			146 x 216 Mkm x 3.0 485d
1999 Jan			0.978 x 1.446 AU x 2.9 deg 487d
1999 Mar 1		DV10 TCM
1999 May 2		Small gas leak
1999 Jul 5		S-band downlink problem
1999 Aug 28		Mars C/A 5.5Mkm
2000 Jun 22		DV11 TCM
2002 Apr 26		Loss of contact due to solar flare damage
2002 Apr 28		DV12 TCM aborted
2002 Jul 14		Recovered beacon
2002 Sep 2		reorientation
2002 Sep 10	0737?	DV13 TCM
2002 Oct 5		DV14 TCM
2002 Nov 22		DV15 TCM
2002 Dec 21	0737	Earth pass 30000 km
2003 Jan			0.832 x 1.167 AU x 6.2 deg 365d
2003 Jun 19	1444	Earth pass 15872 km (22250 km C/A)
2003 Jul			1.013 x 1.508 AU x 7.7 deg 517d
2003 Jul 8		Loss of beacon
2003 Dec 9		TCM attempt failed
2003 Dec 9	1618	Enter Mars sphere
2003 Dec 9		RCS burn to tweak flyby distance
2003 Dec 13	1819	Flyby Mars at 1000 km
2003 Dec 17	2200?	Leave Mars gravity
2003 Dec 19		End of mission

Payload:

• Energetic electron detector

• Energetic ion detector

• High energy particle detector

• Electron temperature probe

• Fluxgate magnetometer, 5m mast

• UV spectrometer

• EUV spectrometer

• HF plasma wave detector/sounder

• LF plasma wave detector

• CCD Cameras

• WANT Wire Antennae,4: 25m each

• TPA Thermal Plasma Analyser, CSA

• NMS Neutral Mass spectrometer, NASA GSFC

Iridium 88

 1998-074A

---

Iridium 88 was launched on 1998 Dec 19 at 1130 UTC from Taiyuan. It was assigned the operation number 20. The satellite was kept in an intermediate orbit until Apr 1999 when it moved to the operational constellation.

Iridium 88
Date	Time	Event	Orbit
1998 Dec 19	1139:44	Launch by CZ-2C/SD
		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
	1149:55	T+10:11 Stage 2 VECO
	1149:58	T+10:14 Stage 2 sep	92.89 177 x 655 x 86.37
	1227:52	T+48:08 SD burn
	1228:28	T+48:44 SD burnout	97.50 622 x 655 x 86.4
	1229:47	T+50:03 SD sep
	1233:38	T+53:54 SD deorbit burn	92.94 212 x 624 x 86.33
1998 Dec 26			97.55 625 x 657 x 86.4
1999 Jan 1			97.60 627 x 659 x 86.4
1999 Jan 7			98.78 687 x 713 x 86.5
1999 Apr 1			98.78 686 x 714 x 86.5
1999 Apr 5			99.37 722 x 734 x 86.5
1999 Apr 10			100.40 776 x 778 x 86.4

USA-95

 1993-056A

---

The second UFO (UHF Followon) satellite was successfully launched into geostationary orbit and delivered to US Naval Space Command from Hughes Communications Inc.

The satellite had a mass of 1279 kg in GEO, 2840 kg in GTO.

In early 2002 it was reactivated from on-orbit spare status to provide extra capacity to forces in Afghanistan.

UHF F/O F2
Date	Time	Event	Orbit
1993 Sep 3	1117	Launch by Atlas 1	CC LC36B
1993 Sep 3		Atlas sep
1993 Sep 3	1121	Centaur MES1 (T+4:45)
1993 Sep 3	1127	Centaur MECO1 (T+10:15)
1993 Sep 3	1141	Centaur MES2 (1:14)
1993 Sep 3	1142	Centaur MECO2	222 x 16394
	1145?	Centaur sep
			273.91 224 x 14961 x 27.1
1993 Sep 6		P-1	321.96 314 x 18050 x 26.8
1993 Sep 7		P-2	388.73 293 x 22237 x 26.9
1993 Sep 8		P-3	489.06 287 x 28080 x 26.8
1993 Sep 9		P-4	648.18 296 x 36566 x 26.6
1993 Sep 10		LAM-1	834.15 9392 x 36557 x 13.0
1993 Sep 11		LAM-2	1126.50 22573 x 36396 x 9.6
1993 Sep 11	2300?	LAM-3
1993 Sep 14			1435.36 34969 x 36574 x 5.1
1993 Sep 20			1436.55 35130 x 36460 x 5.1 GEO 173.1W+0.12W
1993 Sep 26			1436.40 35139 x 36445 x 5.1 GEO 173.6W+0.1W
1993 Oct 19			1436.03 35136 x 36434 x 5.1 GEO 173.3W+0.02
1993 Nov 1		mv out
1993 Nov 16			1452.48 35790 x 36422 x 5.1
1993 Dec 7		Delivered to USN Space Command
1993 Dec 18		mv in	1436.07 35772 x 35800 x 5.0 GEO 71.5E
1994 Feb 1			1436.02 35773 x 35797 x 5.0 GEO 72.1E
1994 Sep 12			1436.02 35762 x 35807 x 4.8 GEO 71.9E
1995 Aug 19			1436.03 35771 x 35799 x 4.4 GEO 71.7E
1997 Mar 6			1436.05 35765 x 35806 x 3.9 GEO 72.6E
1999 Jul 27			1436.03 35164 x 36406 x 2.8 GEO 71.8E

Kosmos 576

  1973-044A

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Zenit-4MT flight 4 was a 12 day mission in Jun 1973. It carried a capsule with a micrometeorite detector and the Kettering group detected the TL recovery beacon.

Kosmos-576
Date	Time	Event	Orbit
1973 Jun 27	1150:01	Launch by 11A511M	PL
	1154	Blok-I burn
	1158	Blok-I sep
	1308		89.85 205 x 328 x 72.9
1973 Jun 28	1430		89.88 204 x 332 x 72.8
1973 Jul 1	0530		89.81 202 x 326 x 72.9
1973 Jul 9		Capsule sep	91.42 212 x 478 x 72.9
1973 Jul 9	0335		89.72 201 x 319 x 72.9
1973 Jul 9	0628?	Retrofire
	0638?	PO sep
	0644?	Entry
	0700?	Landed after 11.79d