Intelsat 703

 1994-064A

---

Intelsat 703 was launched on 1994 Oct 6 at 0635:02 UT by Atlas Centaur AC-111. The satellite is a 3-axis stabilized Space Systems/Loral FS-1300 with 26 C-band and 10 Ku-band transponders and will serve the Pacific Ocean region. The Martin Marietta Atlas IIAS Centaur delivered the satellite into a geostationary transfer orbit. The MA-5A main engine and two of the four Castor IVA solid rocket boosters ignited at liftoff; the other two solids ignited at 0636:02. The first two solids were jettisoned at 0636:14 and the second two at 0636:57. The MA-5A propulsion system on the Atlas consists of two booster engines and a central sustainer engine. At 0637:47 the booster engines were shut down, and at 0637:50 the tail section of the Atlas IIA fell away leaving the main sustainer engine exposed. At 0638:31 the payload fairing around the Intelsat payload was discarded - AC-111 was now high enough that aerodynamic protection was not needed. The Atlas sustainer cut off at 0639:53 and the Atlas IIA stage separated onto its suborbital trajectory at 0639:55. Intelsat 703 was now attached to the AC-111 Centaur IIA. At 0640:17 the two RL10-4A liquid hydrogen/liquid oxygen engines on the Centaur ignited and burned until 0645:17. The combination was now in a parking orbit. After a coast period, AC-111 reignited at 0659:29. It shut off at 0701:12, and separated from Intelsat 703 at 0703:22. Intelsat 703 was now in a 283 x 38575 km x 25.9 deg orbit. The apogee was higher than initially expected and will let the satellite save fuel on reaching its final orbit. Over the next few days it fired its R4D liquid apogee engine to enter first a 7598 x 38540 km x 11.2 deg orbit (Oct 9) and then a 35670 x 38552 km x 0.2 deg orbit (Oct 11). This final orbit is a little higher than geostationary; on Oct 11 at 1815 UT the satellite was over 138 deg East and drifting 16 degrees per day.

Ownership was transferred in 1998 to New Skies.

Intelsat 703
Date	Time	Event	Orbit
1994 Oct 6	0635:02	Launch by Atlas Centaur
	0636:14	SRB 1-2 sep
	0636:57	SRB 3-4 sep
	0637:47	BECO
	0637:50	Booster sep
	0638:31	Fairing sep
	0639:53	MECO
	0639:55	Atlas sep
	0640:17	Centaur MES1
	0645:17	Centaur MECO1
	0659:29	Centaur MES2
	0701:12	Centaur MECO2
	0703:22	Centaur sep	283 x 38575 x 25.9
1994 Oct 6			688.06 284 x 38593 x 25.9
1994 Oct 8	1030?	LAM-1 at 120E
1994 Oct 8			769.42 4293 x 38578 x 15.5
1994 Oct 9	1240?	LAM-2 at 94E
1994 Oct 9			838.16 7598 x 38540 x 11.2
1994 Oct 10	1600?	LAM-3
1994 Oct 11	0850?	LAM-4
1994 Oct 11			1504.40 35671 x 38555 x 0.2 GEO 140.7E+16.4W
1994 Oct 12	2240?	LAM-5
1994 Oct 12			1434.22 35667 x 35832 x 0.2 GEO 121.0E+0.5E
1994 Oct 14			1437.06 35671 x 35939 x 0.2 GEO 120.7E+0.1W
1994 Nov		Move to POR
1994 Dec 9			1436.07 35774 x 35797 x 0.1 GEO 177.0E
1994 Dec 26			1436.10 35776 x 35796 x 0.1 GEO 177.0E
1996 May 27		mv out	GEO 177E
1996 Jun 22		mv in	GEO 56E
1996 Nov 20			1436.11 35772 x 35800 x 0.0 GEO 57.0E
1998 Nov 30		To New Skies NV
1999 Oct 14			1436.01 35681 x 35888 x 0.1 GEO 57.1E
2002 May 5			1436.10 35773 x 35799 x 0.2 GEO 57.0E

Admissions

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Aviation Week: March 29,2004

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Space : the next business frontier

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USA-160

 2001-040A

---

The first of a new generation of NOSS satellites was launched in Sep 2001. The AC-160 launch was codenamed 'Gemini'.

There are two spacecraft operating in polar orbit to intercept radio transmissions. It is probably a followon to NOSS. The contract was awarded to LMA/Denver in 1994 (TRW was the rival bidder). In late 1998 it was reported that the program had large overruns.

AC-160 used a Centaur with RL10A-4-1 engines and a 14' PLF.

As well as USA 160 and the Centaur, a third object was cataloged. This was registered with the UN as a debris object but appears to be the second payload.

NRO
Date	Time	Event	Orbit
2001 Sep 8	1525:05	Launch by Atlas IIAS AC-160	V SLC3E
		T+0:57 SRB 3-4 ignition
		T+1:59 SRB 1-2 sep
		T+2:02 SRB 3-4 sep
		T+2:47 BECO
		T+2:50 Booster sep
		T+3:39 14' PLF sep
		T+4:33 SECO
		T+4:35 Atlas sep
		T+4:52 MES-1
	1535:45	T+10:40 MECO-1	160 x 1200 x 63? (guess)
	1629	T+1:04:10? MES-2 12s
	1629	T+1:04:22? MECO-2
	1633	T+1:08 Centaur sep	1000 x 1200? x 63?
2001 Sep 26		999 x 1203 x 63.4 (UN)

Apollo 14 (Kitty Hawk)

  1971-008A

---

Apollo CSM 110 was flown on the Apollo 14 mission to Fra Mauro. Commander Alan Shepard, CMP Stuart Roosa, and LMP Ed Mitchell named it `Kitty Hawk. On Feb 7 the crew carried out some of the first materials processing experiments done in space, including electrophoresis tests and a composite casting test.

Kitty Hawk (CSM 110)
Date	Time	Event	Orbit
1971 Jan 31	2103:02	Launch by Saturn V (SA-509)	KSC LC39A
	2105:17	S-IC CECO
	2105:45	S-IC OECO
	2105:47	S-IC sep, S-II ignition	-6009 x 112 x 30.70
	2106:16	Interstage sep	-5952 x 120 x 30.76
	2106:22	LES jet	-5937 x 122 x 30.77
	2110:45	S-II CECO
	2112:21	S-II OECO, sep 182.6 km	-1977 x 184 x 31.12
	2112:22	S-IVB ignition
	2112:33	Ullage case jettison	-1897 x 184 x 31.1
	2114:42	S-IVB cutoff
	2114:51	Earth orbit insertion	183 x 189 x 31.11
			185 x 185 x 31.11 (MPR)
	2115:32		184 x 185 x 31.1
	2123:02		184 x 190 x 31.1
	2124	Optics cover jettison
	2148:02		180 x 200 x 31.1
	2220:32		187 x 203 x 31.2
	2236:22	T+1:33:20	191 x 192 x 31.1
	2331:33	S-IVB TLI burn
	2337:24	S-IVB cutoff
	2337:34	Translunar injection at 337 km	214 x 461334 x 30.8
1971 Feb 1	0005:32	CSM sep from SLA/S-IVB	217 x 455424 x 30.8
		Transposition and docking maneuver
	0016:56	CSM failed to dock with LM, attempt 1A
	0017:03	Attempt 1B
	0017:06	Attempt 1C
	0017:11	Attempt 1D
	0017:46	Attempt 2
	0019:45	Attempt 3
		Stationkeep for 6 minutes
	0026:44	Attempt 4, failed to dock with LM
		Stationkeep for 70 minutes
	0037	S4B venting
	0136	Attempt 5, CSM failed to dock with LM
		Stationkeep for 20 min
	0157	At 3m
	0159:46	Attempt 6 to dock with LM, successful
	0159:58	CSM docked with LM
	0250:27	CSM/LM sep from S-IVB	220 x 454981 x 31.0
	1419	Pass EL1:4
1971 Feb 2	0339:09	MCC-2 burn 10s	120 x 456123 x 31.1
	0339:20	MCC-2 CO	-520 x 441384 x 31.2
1971 Feb 3	1512:03	Equigravisphere
1971 Feb 4	0201:13	MCC-4 burn 0.7s	140 x -14916 x 154.4
			134 x -14907 x 154.3
	0659:42	SPS LOI-1 burn 370.8s	111 x -14833 x 167.0
	0705:54	Lunar orbit insertion cutoff	109 x 315 x 166
	1113:54	SPS LOI-2 burn (DOI) 20.8s	18 x 109 x 166
	1114:16	DOI cutoff	19 x 109 x 156.1 (MR)
1971 Feb 5		Photography of Descartes site
		CDR and LMP transfer to LM
	0450:45	LM undocked	15 x 112 x 149.2
	0452	CSM sep burn	14 x 111
	0614:48	Circ burn 4s
	0614:52	Circ cutoff	104 x 118
	1832:35	LOPC-1 burn 18.5s	106 x 115
	1832:54	LOPC-1 cutoff
1971 Feb 6		Rendezvous by LM
	2035:52	LM docked with CSM
		CDR and LMP return to CSM
1971 Feb 6	2248:00	Antares undocked
	2252:45	Sep burn	105 x 115
1971 Feb 7	0139:04	SPS TEI burn 2:29
	0141:33	Transearth injection	110 x -10361 x 172.7
	1530	Homebound equigravisphere
	1837:58	MCC-5 burn 3s	-885 x 658137 x 42.37
1971 Feb 9	2035:44	SM-110 sep	40 x 663641 x 40.6
	2050:47	Entry	42 x 733353 x 40.47
	2104:59	Splashdown in Pacific 27 02 24S 172 41 24W
		Recovered by USS New Orleans

International Ultraviolet Explorer

 1978-012A

---

The International Ultraviolet Explorer was designed for a six month mission but was still operating 16 years later. IUE took ultraviolet spectra of astronomical objects - tens of thousands of them. It was the first astronomy satellite to be operated as an observatory, available for use by the whole astronomical community. Uniquely, it was in geosynchronous orbit, so that astronomers at the NASA-Goddard or ESA-Villafranca control centers could control the spectrographs in real time. IUE was jointly funded by NASA, ESA, and the UK Science Research Council; the orbit drifted back and forward across the Atlantic and observing was handled from the ESA ground station for 8 hours a day and from Goddard for 16 hours a day.

IUE was launched on 1978 Jan 26 at 1736 by a Delta 2914 from Cape Canaveral's Launch Complex 17A. The Delta stage entered a 96.6 min, 164 x 1024 km x 28.7 deg and separated from the third stage. The Star 37E third stage fired and placed IUE in a 846.7 min, 177 x 46367 km x 28.7 deg orbit. The Star 24 apogee motor fired to put the satellite in a final orbit of 1435.7 min, 25669 x 45888 km x 28.6 deg. Observations began a few days later. The internal propulsion system was used occasionally to maintain the satellite at the correct longitude.

On 1995 Oct 1 operational control of IUE was transferred completely to ESA-Villafranca. ESA and PPARC (the successor to SERC) would operate the spacecraft. IUE was shut down at 1842 UT on 1996 Sep 30.

IUE
Date	Time	Event	Orbit
1978 Jan 26	1736:00	Launch by Delta 2914	CC LC17A
	0135:38	SRM 1-6 cutoff
	0135:39	SRM7-9 burn
	0136:17	SRM7-9 cutoff
	0136:27	SRM 1-9 sep
		T+3:42 MECO
		T+3:49 Stage 1 sep
		T+3:55 Stage 2 burn
	1740	T+4:33 Fairing sep
	1745	T+8:47 SECO-1 164 km vrel 7.807	167 x 167? x 28.7
	1816	T+40:12 SES-2 172 km vrel 7.797
	1816	T+40:30 SECO-2 172 km 8.024	96.6 164 x 1024 x 28.7
	1817	T+41:22 Stage 2 sep 170 km 8.026
	1818	T+42:03 TES 172 km 8.025
	1818	T+42:47 TECO 176 km	846.7 177 x 46367 x 28.7
	1819	T+43:50 S/C sep 204 km
1978 Jan 27	0300?	Apo 1
1978 Jan 27	1454	Star 24 burn, apo 2	1435.7 25669 x 45888 x 28.6
1978 Jan 28		Despin using HAPS
1978 Jan 28	0602		1435.64 25668 x 45886 x 28.6 55.2W
1978 Jan 30	1630	Dust cover ejected
1978 Feb 1		First images from FES
1978 Feb 9		First data currently in archive
1978 Feb 13		Orbit correction
1978 Mar 30			1436.38 25711 x 45872 x 28.6 51.8W
1978 Jul 24		Orbit correction
1979 Jun 20		Orbit correction
1980 Feb 13		Orbit correction
1980 Apr 18			1435.66 25888 x 45667 x 28.2
1980 Jun 24		Orbit correction
1980 Dec 16		Orbit correction
1981 May 8		Orbit correction	1436.07 26080 x 45491 x 28.3
1981 Oct 29		Orbit correction
1982 Aug 17		Orbit correction	1435.54 26426 x 45125 x 28.6
1983 May 27		Orbit correction
1984 Jan 12		Orbit correction
1984 Feb 14		Orbit correction
1984 Nov 16		Orbit correction
1985 Jul 16			1436.63 27451 x 44142 x 29.7
1985 Aug 9		Orbit correction
1985 Sep 6			1435.59 27533 x 44020 x 29.8
1986 Mar 19		Orbit correction
1986 Jul 29		Orbit correction	1435.81 27952 x 43609 x 30.2
1986 Dec 18		Orbit correction
1987 Sep 9		Orbit correction
1988 Mar 18		Orbit correction
1988 Sep 8		Orbit correction
1989 Mar 13		Orbit correction
1989 Sep 8		Orbit correction
1990 Jun 6		Orbit correction
1990 Dec 3			1436.35 29787 x 41795 x 32.6 53.5W
1991 Jan 14			1436.46 29799 x 41787 x 32.3 56.9W
1991 Jan 12		Orbit correction
1991 Feb 6			1435.64 29811 x 41743 x 32.7
1991 Nov 5			1436.74 29881 x 41716 x 33.0 57.4W
1991 Oct 18		Orbit correction	1435.91 30045 x 41520 x 33.3 51.7W
1992 Aug 18			1436.86 30160 x 41443 x 33.5 68.6W
1992 Aug 19		Orbit correction	1435.72 30162 x 41395 x 33.5 68.0W
1992 Nov 19			1436.07 30208 x 41363 x 33.7 64.3W
1992 Nov 20		Orbit correction	1435.41 30213 x 41333 x 33.7 64.1W
1993 Aug 17			1436.53 30264 x 41325 x 34.1 45.2W
1993 Aug 19		Orbit correction	1435.77 30256 x 41304 x 34.1 46.1W
1993 Sep 20			1435.84 30264 x 41299 x 34.2 51.1W
1994 Feb 14			1436.49 30242 x 41346 x 34.5 57.4W
1994 Feb 15		Orbit correction	1435.67 30243 x 41312 x 34.5 57.4W
1994 Sep 20			1436.60 30235 x 41357 x 34.8 55.4W
1994 Sep 20		Orbit correction	1435.55 30243 x 41308 x 34.8 52.9W
1995 Apr 30			1436.58 30207 x 41384 x 35.1 48.4W
1995 May 3		Orbit correction	1435.85 30183 x 41380 x 35.1 48.1W
1995 Jun 5			1435.98 30178 x 41389 x 35.2
1995 Jun 6		Orbit correction	1435.19 30162 x 41374 x 35.2
1996 Mar 5			1436.21 30095 x 41482 x 35.6 35.8W
1996 Mar 6		Command error, control lost
1996 Mar 11		One-gyro control enabled
1996 Sep 29			1437.04 29992 x 41617 x 35.9 65.5W
1996 Sep 30	1357	Science cameras off
	1730	Propellant drained (18 kg)
	1842	Spacecraft deactivated
1996 Oct 10			1439.04 30216 x 41472 x 35.6
1999 Apr 27			1438.85 29739 x 41941 x 37.2

Payload:

• Telescope 45 cm Ritchey-Chretien telescope

Town and Country: January 2004

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Progress M1-6

 2001-021A

---

The next ferry, spacecraft 11F655 No. 255, carried food and equipment to ISS including backup parts for the Destiny C+C computers. Launch of ISS supply flight 4P was by the first Soyuz-FG, a Soyuz-U with uprated engines featuring improved fuel injection.

The vehicle carried 2478 kg of cargo including 900 kg of fuel for Zvezda and 1300 kg dry cargo.

Progress M1-6
Date	Time	Event	Orbit
2001 May 20	2232:40	Launch by Soyuz-FG	KB PU5
		T+1:58 St 1 sep
		T+2:32 GO sep
		T+4:47 St 2 sep
		T+4:57 KhO sep
		T+8:44 St 3 MECO
	2241:29	Blok I sep
2001 May 23		Rendezvous with ISS
	0023:57	Docked with Zvezda -Y
	0210	HO to ISS
2001 Aug 22	0601	Undocked from Zvezda -Y
	0900?	Deorbit

Spaceflight: May 2004

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