Spaceflight: July 2004

 https://welib.org/md5/a33b3bc53b4231a7864ddd9c64623aba

Blonde Ambition: An A-List Novel

 https://welib.org/md5/6c4a4bd685702a5ef9113ec2b8b8af8e

Haruka

 1997-005A

---

The VSOP (VLBI Space Observatory Program) was a project to do radio astronomy using spaceborne Very Long Baseline Interferometry. The space segment of VSOP was the MUSES-B satellite, named Haruka (`far-away') after launch. Mass of Haruka was 830 kg including 62 kg of RCS prop and 246 kg dish antenna. It has a 10m (8m effective) deployable dish with a central boom carring the subrelector. The main spacecraft is a 1.5m dia, 1.0m high box with 2 solar panels. MUSES B was built by NEC.

The second Mu Space Experiment System (MUSES B) was the 16th ISAS scientific satellite, to test large space structures and provide the first orbiting VLBI radio observatory. Initial orbit is 200 x 20000 km, with perigee raising maneuvers into a 1000 x 20000 km. The spacecraft has a box shaped bus, with 2 solar panels and the antenna. Haruka has also been assigned the English homonym HALCA (Highly Advanced Laboratory for Communications and Astronomy).

This was the first launch of the M-V rocket. A KM-V1 fourth stage kick motor was added. The third stage was not cataloged until 1999, when two objects were found in orbits with apogees of 1263 and 1674 km.

Haruka VSOP
Date	Time	Event	Orbit
1997 Feb 12	0450:00	Launch by M-V-1	Kagoshima
		Stage 1 burnout
	0451:15	Stage 1 sep T+1:15s
	0452:37	Stage 2 burnout T+2:37
	0453:17	Fairing T+3:17s
	0453:31		-4962 x 224 x 31.1
	0453:33	Stage 2 sep T+3:33s
	0453:39	Stage 3 burn T+3:39
	0455:33	T+5:33 St 3 burnout
	0455:33	Spinup T+333s
	0455:39	Stage 3 sep T+5:39s	233 x ? x 31.2
	0455:43	KM-V1 burn T+5:43s 71s?
		KM-V1 burnout
	0457:57	KM-V1 sep T+7:57s	233 x 21527 x 31.2
		Yo-yo deploy T+8:00
		Solar panel deploy T+90min
		Orbit raise
1997 Feb 14		TCM1
1997 Feb 16		TCM2
1997 Feb 21		TCM3
1997 Feb 24		Sub-reflector deployed
1997 Feb 27		Main antenna deploy begins
1997 Feb 28		Antenna deploy complete
1997 Mar 30		Eclipse period begins
1997 Apr		First fringes at 1.6 GHz
1998 Aug 30		Computer problem, observing halted
1998 Dec 10		Computer rebooted
1999 Oct		Gyro problem,
1999 Dec		Resume observing
1999 Dec		Orbit lower
2000 Feb		Resume attitude control
2000 Mar 8		Resume observing
2003 Oct		end of VSOP observations

Hexagon 5

  1973-014A

---

It has been claimed that the short lifetime of KH-9 no. 5 was due to the fact that preparations for its launch were rushed. HEXAGON 5 carried the first mapping camera in the series, as well as a related secondary payload, the Doppler Beacon 7 transponder which was used in an APL geodetic program. Earlier Doppler Beacon payloads had been carried on the Agena D aft rack of CORONA missions. The doppler system was used to track the orbit of the satellite from sensors around the periphery of the USSR, providing a geodetic control net for the area. The mapping SRV, mission 1205-5, was recovered after 42 days. The mission was used in a deorbit experiment over a broad ocean area (over Shemya according to The HEXAGON Story).

HEXAGON 5
Date	Time	Event	Orbit
1973 Mar 9	2100	Launch by Titan IIID	V SLC4E
		T+1:54 Stage 1 burn 2:27
		T+1:55 SRM burnout
		T+2:05 SRM sep
		T+4:22 Stage 1 MECO
		T+4:22 Stage 1 sep
		T+4:22 Stage 2 burn
		T+4:36 Fairing
	2107	T+7:40 Stage 2 MECO
	2108	T+7:52 Stage 2 sep
		Solar arrays deployed, rev 1
		Payload ops begin, rev 5
1973 Mar 9			88.60 146 x 264 x 95.72
1973 Mar 10			88.75 153 x 271 x 95.72
1973 Mar 19	1834		88.73 161 x 261 x 95.69
1973 Mar 21	2250?	SRV-1 deorbit
1973 Mar 31			88.6 152 x 263 x 95.7 (SSR)
1973 Apr 4	2325?	SRV-2 deorbit
1973 Apr 7		op 121	88.64 152 x 261 x 95.7
1973 Apr 9		op 138
1973 Apr 10		op 140
1973 Apr 11		op 149
1973 Apr 16		op 173
1973 Apr 18	2250?	SRV-3 deorbit
1973 Apr 19		op 194
	0600?	Orbit adjust
1973 Apr 20	2300?	SRV-5 deorbit opp	151 x 268 x 95.7
		T+0:00 SRV sep
		T+0:03 Spinup 57 rpm
		TE-M-236B deboost
		Despin
		T+0:21? Thrust cone separation
		E+0:00 = T+5:51? Entry
		E+2:26 Cover sep
		E+2:36 Chute deploy
		E+22-25 min? Recovery at 5 km
	2335?	SRV-5 recovered
1973 Apr 28		DB-7 turned off	88.63 151 x 262 x 95.7
1973 May 6			88.85 169 x 265 x 95.6
1973 May 11			88.66 151 x 264 x 95.6
1973 May 11	2220?	SRV-4 deorbit
1973 May 12	0608	Raise perigee	88.96 179 x 266 x 95.6
	1502		88.94 169 x 274 x 95.6
1973 May 16	1344		88.39 155 x 233 x 95.6
1973 May 16	1809	Orbit raise	88.53 156 x 246 x 95.6
1973 May 17	1746		88.42 155 x 237 x 95.7
1973 May 18	1126	Lower perigee	88.13 143 x 220 x 95.7
1973 May 19		Reentered after 71d
	0000?	Deboost rev 1139, day 70	80? x 176 x 95.7
		VASP 1 reentry experiment over BOA (Shemya)
		Deboost (OAM burn along horizontal, vel vector)
		S+1:05:56 Alt 129 km
		S+1:09:52 Loss of signal 92 km
	0110	S+1:10:40 Solar panels break off 84 km
		S+1:11:15 Vehicle breakup 78 km

STS-110 (Atlantis)

 2002-018A

---

The first mission of Phase 3. S0 fills the bay. MT is underneath the S0 in the bay.

Smith, Walheim, Ross and Morin are EV1,2,3,4.

MT is attached to S0 prior to launch. Launch mass 116609 kg. Landing mass 91016 kg.

In addition, Atlantis will carry water supplies, and CETA lights (1 on Destiny and one on Unity).

On EVA-1, the SSRMS installed S0 to the Destiny LCA claw, and the first two MTS structs were installed. EVA-2 bolted the remaining two MTS attachment struts for S0 and connected cables.

On EVA-3, Smith and Walheim released the Destiny claw and set up the MT, releasing the launch restraints. They also rewired the SSRMS to allow it to get power while moving onto the truss. Airlock Spur installation was delayed until EVA-4.

EVA-4 will see Ross and Morin install handrails, a platform and floodlights on the truss. They will also install the Airlock Spur beam between Quest and S0, used as an EVA path from the AL to the truss and installed with multiple handrails. The Spur is installed on the starboard aft side of S0 and hinges out to attach to the AL. It is 4.2m long.

S0 is 13.4m long 4.6m dia and 12118 kg.

The crew transferred 66 kg O2 and 20 kg N2, and 664 kg of H2O to the ISS as well as 1021 kg of supplies and equipment. 1111 kg of logistics were taken from ISS to Atlantis. 104 kg of condensate were vented, and the station's orbit was raised by 9 km.

The MT was later moved from WS3 to WS4, the first MT move across a truss segment.

STS-110
Date	Time	Event	Orbit
2002 Mar 6		Tow to VAB/1
2002 Mar 7		ET mate
2002 Mar 12	1330	Rollout to LC39B
2002 Apr 8	2044:19	Launch by STS from LC39B
	2046:22	SRB sep
	2046:32	OMS ASS
	2047:49	OMS ASS CO
	2052:42	MECO
	2053:05	ET-114 sep	58 x 229 x 51.64
	2122	ET apogee
	2123:04	OMS-2 60s? 29m/s
	2124:07	OMS-2 CO
	2122		88.35 155 x 230 x 51.64
	2150?	ET reentry
	2239:14	PLBD open
2002 Apr 9	0019s	NC1
	0925:36	Mass 114931 kg	155 x 227 x 51.6
	1315	NC2 cancelled
	2120	NC3 2m/s
2002 Apr 10	0600		88.29 154 x 224 x 51.6
	1128:12	OMS 3 NH
	1130:32	OMS 3 CO
	1136	Mass 112415 kg
	1211:48	OMS 4
	1213:22	OMS 4 CO
	1314s	NC4
	1345:38	TI OMS 5 L
	1345:51	OMS 5 CO
	1351	Mass 110688 kg
	1505	At 0.5km
	1516	On -Rbar at 200m
	1529	On V-bar at 100m
	1601	Final approach 10m
	1604:30	Docking
	1619:24	Hard dock	92.29 384 x 388 x 51.64
	1808	HO
2002 Apr 11		EVA-1 Smith, Walheim
	1000?	SSRMS Grapple S0
	1030	Uncradle S0
	1325	First stage capture of S0 with LCA	92.27 383 x 388 x 51.64
	1346	S0 attached (LCA closed)
	1353	Begin depress in Quest module
	1404	At 5 psi
	1415	SSRMS ungrapple S0
	1419	Resume
	1419	TC open
	1424	Pump power switch off
	1433	Depress complete 0.1psi
	1434	HO
	1436	Batt power
	1444	Egress Smith
	1447	Egress Walheim
		Walheim on SSRMS
	1611	Forward stbd strut bolted
	1656	Forward port strut bolted
	1743	Stbd UT removed from S0
	1752	Stbd umbil tray installed on Destiny
	2000	Umbil tray installs, connections
	2115	Smith recharges O2 tank
		Unreel TUS
	2219?	Ingress
	2220	HC
	2224	Repress
2002 Apr 13		EVA-2 Ross, Morin
	1353	TC open
	1353	In depress	92.27 383 x 388 x 51.64
	1405	Depress
	1407	HO
	1409	Battery
	1420	Egress Ross
	1430	Egress Morin
		Morin on SSRMS
	1455	Releasing MTS strut
	1606	Aft Stbd MTS strut install compelete
	1818	Aft Port MTS strut complete
	1930	second TUS installation
	2120?	Ingress
	2133	TC closed
	2135	HC
	2139	Repress
2002 Apr 14		Reboost?	92.29 384 x 389 x 51.64
2002 Apr 14		EVA-3 Walheim, Smith
	1330?	Resume depress of Quest
	1334	3.5psi
	1344	Depress complete?
	1346	HO
	1348	Batt
	1358	Walheim egress
	1405?	Smith egress
		Rewiring SSRMS	92.28 383 x 389 x 51.6
	1700	MT launch restraint bolts removed
	1730	Rewired SSRMS
		AL spur deferred
	1947	Ingress Smith
	2007	Ingress Walheim
	2010	TC closed
	2011	HC
	2015	Repress
2002 Apr 15	0139	Reboost?	92.32 385 x 390 x 51.64
2002 Apr 16		EVA-4: Ross,Morin
	1355	Begin dp
	1426?	Depress	92.31 384 x 390 x 51.64
	1428	HO
	1429	Batt
	1515	Spur deployed
		Ingress
	2100?	HC
	2106	Repress NASA 6:37
2002 Apr 17	1604 HC to ISS	92.30 384 x 390 x 51.64
	1831:13	Undocked
	1917	+V flyaround 120m
	1926	+R
	1939	-V
	1952	-R
	2004	+V
	2016	+R, sep	92.41 385 x 399 x 51.64
2002 Apr 18	1726:19	OMS 6 attitude control test
	1726:29	OMS 6 CO
	1804:19	OMS ADJ Orbit lower	91.62 308 x 399 x 51.64
	1804:57	OMS ADJ CO
2002 Apr 19	1249:49	PLBD close	91.65 308 x 401 x 51.63
	1518:59	OMS DO 2:19 76 m/s?
	1521:17	OMS DO CO	53 x 399 x 51.6
	1555:25	EI
	1626:58	MGTD KSC RW33
	1627:09	NGTD
	1628:07	WS KSC RW33
	2230	OPF

Aviation Week: August 9,2004

 https://welib.org/md5/13118d97f0522295d7f39424a40d843d

GOES-8

 1994-022A

---

The first Space Systems/Loral GOES Next weather satellite wasGOES I. The three axis stabilized satellite was a 2.3 x 2.1 x 2.0 m box together with a solar array wing on one side and a solar sail for attitude control on the other, with an overall 28.2 m span. Dry mass was 977 kg. Launch mass was 2105 kg. The spacecraft was based on the FS-1300 bus.

GOES I (Geostationary Operational Environmental Satellite 08 was launched on 1994 Apr 13 at 0604 by Atlas I Centaur AC-73 from Launch Complex 36B at Cape Canaveral. At T+4:50 the Centaur ignited for a 5 minute burn, placing itself in a 52 x 148 km parking orbit at 0614. After a 14 minute coast, the Centaur ignited again at 0628 for a 1 minute 35 sec burn to a 167 x 42831 km transfer orbit. An initial burn of the liquid apogee engine was terminated early on Apr 14 after high temperatures were noticed. A small verification burn was made on Apr 18, a larger one a few days later, and a final burn at 0045 on Apr 28. In early 1995, GOES 8 was moved from the testing location at 90W to the 75W GOES-E operational location.

GOES 8
Date	Time	Event	Orbit
1994 Apr 13	0604	Launch by Atlas I (AC-73)	CC LC36
		BECO
		Booster sep
		SECO
		Atlas sep
	0608	T+4:50 Centaur MES-1
	0614	Centaur MECO-1	52 x 148 x 27.4?
	0628	Centaur MES-2
	0629	Centaur MECO-2
	0631?	Centaur sep
1994 Apr 14			767.59 168 x 42615 x 27.0
1994 Apr 14		LAM-1, aborted
1994 Apr 15			785.34 987 x 42649 x 23.5
1994 Apr 18	2250?	LAM-2 verification burn over 75W
1994 Apr 20			830.70 3128 x 42659 x 17.7
1994 Apr 21	1950?	LAM-3 over 38W
1994 Apr 21			919.69 7237 x 42660 x 11.2
1994 Apr 23	1745?	LAM-4 over 10W
1994 Apr 24			1466.56 30022 x 42739 x 0.8
1994 Apr 25?		LAM-5
1994 Apr 27			1434.00 35297 x 36193 x 0.5 GEO 93.4W+0.5E
1994 Apr 28	0045	LAM-6?
1994 May 1			1433.86 35288 x 36197 x 0.5 GEO 92.6W+0.6E
1994 May 11			1435.89 35633 x 35931 x 0.4 GEO 91.0W
1994 Aug 7			1436.03 35776 x 35794 x 0.3 GEO 89.9W
1994 Nov 19			1436.00 35767 x 35801 x 0.1 GEO 89.5W
1995 Feb 2			1436.10 35778 x 35795 x 0.3 GEO 91.1W
1995 Feb 3		mv out
1995 Mar 19		mv in	1435.89 35781 x 35784 x 0.2 GEO 75.1W+0.05E
1995 Apr 11			1436.01 35781 x 35788 x 0.1 GEO 74.4W
1995 Oct 17			1436.13 35771 x 35803 x 0.3 GEO 74.3W
1995 Dec 1		GOES East	GEO 75.8W+0.05E
1996 Oct 10			1436.09 35767 x 35806 x 0.3 GEO 74.3W
1997 Jan		Temporary loss of attitude control
1999 Oct 18			1436.29 35771 x 35809 x 0.3 GEO 75.3W
2003 Mar 6			1436.09 35780 x 35792 x 0.3 GEO 74.6W

Radio-ROSTO

 1994-085A

---

RS-15 (Radio-ROSTO) was launched on 1994 Dec 26 as a test payload for the Rokot launch vehicle. The unstablized 1m diameter polyhedron had a mass of 70 kg and carried two CW beacons. It was based on the Strela-1M bus.

Radio-ROSTO
Date	Time	Event	Orbit
1994 Dec 26	0301	Launch by Rokot	KB
		T+2:01? St 1 sep
		T+2:50? Fairing sep
		T+5:04? St 2 sep
		T+5:04? Briz-K MES-1
	0315?	T+14m? Briz-K MECO-1	180? x 1884 x 64.9
	0407?	Briz-K MES-2
	0407?	Briz-K MECO-2
		Briz-K sep
1994 Dec 26			127.72 1861 x 2184 x 64.9
1997		Still operating
2004 Feb		still operating

GE-3

 1997-050A

---

GE Americom's GE 3 (later AMC 3) is an LMT Series A2100 satellite for video and data services. It replaces Satcom K-2. Coverage includes CONUS, S Canada, Caribbean and Greenland. It was launched by AC-146 (IIAS with RL10A-4-1 engines) in Sep 1997 and was stationed at 87W. Mass was 2845 kg. In 1999, the satellite failed briefly but was recovered after only a few hours, with minor impact on AP services.

GE 3
Date	Time	Event	Orbit
1997 Sep 4	1203	Launch by Atlas IIAS	CC LC36A
	1203	Castor 4A x 2 burn
	1204	Castor 4A x 2 burn, T+0:55
	1204	Castor 4A x 2 sep
	1205	Castor 4A x 2 sep
		T+2:43? Atlas BECO
		T+2:46? Atlas booster sep
		T+3:25? Atlas fairing
	1208	T+5:00?? Atlas SECO
	1208	T+5:20?? Centaur AC-146 MES1
	1212?	T+9:40? Centaur MECO	158? x ? x 28.0
	1225?	Centaur burn 2
	1226?	Centaur MECO-2
	1226	Eq crossing/perigee (TLE)
	1233?	Centaur sep T+30?
			303 x 43913 x 19.1
1997 Sep 5			797.79 312 x 43919 x 19.1
1997 Sep 7	1330?	LAM-1
1997 Sep 7			834.73 2077 x 43899 x 14.3
1997 Sep 8	1730?	LAM-2
1997 Sep 8			963.23 7928 x 43931 x 8.4
1997 Sep 10	0100?	LAM-3
1997 Sep 10			1588.34 33557 x 43875 x 0.7
1997 Sep 11	1750?	LAM-4
1997 Sep 11			1379.37 33530 x 35807 x 0.0
1997 Sep 12	0500?	LAM-5
1997 Sep 13			1438.97 35717 x 35967 x 0.1 GEO 82.9W+0.7W
1997 Sep 16			1435.88 35736 x 35828 x 0.1 GEO 83.0W
1997 Sep 28			1439.41 35753 x 35949 x 0.0 GEO 87.4W+0.8W
1997 Oct 3			1436.13 35783 x 35791 x 0.0 GEO 87.1W
1999 Mar 12	0900	Gyro failed, tumbled
	1400	S/C recovered
1999 Oct 15			1436.12 35783 x 35790 x 0.0 GEO 87.1W
2003 Jul 12			1436.10 35781 x 35791 x 0.0 GEO 87.0W