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

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

Opera for Libraries

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Rocsat 2

 2004-018A

---

Rocsat-2 was renamed Formosat-2 in Dec 2004. It was an Earth imaging satellite with a secondary science payload for imaging lightning.

Rocsat 2 prime contractor was originally DaimlerChrysler Aerospace but after political problems Matra Marconi Space (later EADS Astrium) got the work. Launch 2003. Mass 764 kg including 50 kg of hydrazine. Size 3?m dia 4?m high. hexagon + panel. First use of Astrosat-500 (Leostar 500XO) bus (Spot 5 derivative).

Initial delivery to 730 km orbit, then boost to operational 891 km orbit.

Launch by Taurus XL/3210 with 92" fairing. Control from NSPO MMC at Hsin-Chu in Taiwan.

ROCSat-2
Date	Time	Event	Orbit
2004 May 20	1747:03	Launch by Taurus XL 3210	V 576E
		T+1:24 Castor 120 sep
		T+2:43 Orion 50SXL burnout
		T+2:47 Orion 50SXL sep
		T+2:50 Orion 50XL burn
		T+2:55 Fairing
		T+4:06 Orion 50XL burnout
		T+5:10 Orion 50XL sep
		T+11:29 Orion 38 burn	-2836 x 714 x 99
	1759	T+12:42 Orion 38 burnout	728 x 740 x 99
	1801	T+14:37 Orion 38 sep
			730 x 743 x 99.1
		T+18:02 CCAM burn complete
		T+40:32 RCS depletion
2004 May 20			99.44 720 x 742 x 99.11
2004 May 23			99.50 725 x 743 x 99.10
2004 May 24			99.71 734 x 755 x 99.11
2004 May 25			100.14 763 x 766 x 99.10
2004 May 27			101.11 809 x 812 x 99.1
2004 May 28			101.54 829 x 833 x 99.1
2004 Jun 2			102.79 890 x 892 x 99.1

Kosmos 273

  1969-027A

---

Zenit-2 No. 77 was launched on the same day Zenit-4 No. 52 returned. It landed after 8 days 240 km E of Tselinograd at 51 20 N 75 00 E.

Kosmos-273
Date	Time	Event	Orbit
1969 Mar 22	1215	Launch by 11A57	PL
	1220	Blok-I burn
	1224	Blok-I sep	89.9 205 x 356 x 65.4 (TASS)
1969 Mar 22	1800		89.87 199 x 335 x 65.4
1969 Mar 28	1035	Blok-I reentered
1969 Mar 30	0403		89.67 196 x 319 x 65.4
	0530?	Retrofire
	0556	Landed

Pioneer 10

  1972-012A

---

The Pioneer F (Pioneer Jupiter) payload was an entirely new design. The central bus was dominated by a large communications antenna and two booms holding nuclear RTGs which supplied electrical power. The first spacecraft to head to the outer planets, the Pioneer F and G probes were built by TRW for NASA-Ames. Instead of solar panels, they carried 4 SNAP-19 radioisotope thermoelectric generators using plutonium decay to generate electrical power.

Pioneer 10 was launched at 0149:04 on 1972 Mar 3 by Atlas Centaur from Cape Kennedy, Launch Complex 36A. The Atlas separated at 0153:10 and the Centaur ignited at 0154 on a single burn, ending at 0200:39. Centaur AC-27 separated at 0201, leaving Pioneer 10 and its Star 37E kick motor in solar orbit. The kick motor fired for 45s at 0202 and separated at 0204. The experiments were switched on at 0215. Pioneer 10 passed lunar orbit at 1500 on Mar 3. Trajectory correction maneuvers were carried out to refine the orbit: TCM-1A and 1B at 1219 and 1930 on Mar 7, TCM-2A and 2B at 2202 on Mar 23 and 1202 on Mar 24, and TCMs on Sep 19 and 1973 Jun 20.

TCM-1 moved encounter earlier by 9 hr; TCM-2 moved it later by 2.5 hr and moved the path 6400 km closer to Jupiter.

The Jupiter encounter phase began on 1973 Nov 6, with the bow shock crossing coming on Nov 26. Pioneer 10 passed Callisto at 1390000 km on Dec 3 at 1226*, Ganymede at 446000 km on Dec 3 at 1356*, Europa at 599000 km at 1526*, and Io at 357000 km at 1956*. Closest approach to Jupiter was at 2325:05* on Dec 3, at a distance of 130400 km. On Dec 12-18, Pioneer 10 left the Jovian magnetosphere and headed out to the stars. It passed the orbit of Uranus on 1979 Jul 11, Neptune in 1983 Jun, and by 1992 Oct 9 was 55 AU from the Sun.

At the end of 1996, Pioneer 10 was still operating, with the charged particle instrument, Geiger Tube Telescope, and UV Photometer operating for part of each month. Funding for tracking the spacecraft was stopped and the last official science data was obtained on 1997 Mar 31, although the probe would still be used for deep space tracking training exercises by the Lunar Prospector control center, and some science data from the Iowa Geiger Tube, the Chicago particle instrument, and the doppler radio science experiment were returned into 1998. It was still being operated in early 1999 as part of the Lunar Prospector controller training program.

Pioneer 10
Date	Time	Event	Orbit
1972 Mar 3	0149:04	Launch by Atlas Centaur
	0153:10	Atlas sep
	0154	Centaur MES
	0200:39	Centaur MECO	1537.96 152 x 75361 x 31.48
	0201	Centaur sep
	0202	Star 37E burn, 45s
	0202	Star 37E burnout 13.896 km/s	200 x -22505? x 31.5
	0204	Star 37E sep	186 x -22379 x 31.48
	0215	Experiments on
	0307	Pass GEO
	1313	Pass lunar orbit
1972 Mar 4
	0536	Pass 929000 km sphere
	2245	Pass L1 distance
1972 Mar 7	1219	TCM-1A
	1930	TCM-1B tot 14m/s, B=140000 km
1972 Mar 23	2202	TCM-2A
1972 Mar 24	1202	TCM-2B
1972 Sep 19		TCM
1973 Jun 20		TCM
1973 Oct 1		Enter Jovian sphere
1973 Nov 6		Jupiter encounter
1973 Nov 26		Bow shock
1973 Dec 3	1441	Callisto, 1390000 km
	1611	Ganymede, 446000 km
	1741	Europa, 599000 km
	2211	Io, 357000 km
1973 Dec 4	0139:24	Jupiter, 130400 km
	0249	Max Earth-rel vel 72.27 km/s
1973 Dec 5	0000	1.6 M km from Jupiter
1973 Dec 14		10 Mkm from Jupiter
1973 Dec 18		Last magnetosphere exit
1974 Feb 12		Leave Jovian sphere
1979 Jul 11		Passed orbit of Uranus
1983 Jun		Passed orbit of Neptune
1992 Oct 9		55AU from Sun
1996 Nov 1		66.26AU from Sun
1997 Mar 31	1945	Science mission support ends
1997 Aug 9		Precession maneuver
1998 Feb 2		Precession maneuver
1999 Jul 10		Precession maneuver
2000 Mar 21		Contact
2000 Jul 8		Precession maneuver
2000 Aug 19		Contact
2001 Jan		End of contact
2001 Apr 28		Contact regained
2002 Mar 1		Contact
2003 Jan 22		Last signal
2003 Jan 25		Contact support ended

To Reach the High Frontier : A History of U.S. Launch Vehicles

https://welib.org/md5/ce0a24570eb1474f61a1549f22bdff5f

True wealth : an expert guide for high-net-worth individuals

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Aquacade 3

 1977-114A

---

The third Rhyolite, now renamed Aquacade, was launched at the end of 1977.

RH3
Date	Time	Event	Orbit
1977 Dec 11	2245:01	Launch by Atlas Agena D	CC
	2247	Atlas BECO
	2247	Atlas booster sep
	2248	Atlas SECO
	2251	Atlas sep
	2251	Agena burn 1
	2251?	Fairing
	2254?	Agena MECO-1	178 x 180 x 28.5 ?
	2338?	Agena MES-2
	2339?	Agena MECO-2	178 x 33700? x 28.2
	2340?	Agena sep
1977 Dec 12	0500?	LAM-1
1978			GEO 70E

A Tale of Four Houses : Opera at Covent Garden, LA Scala, Vienna and the Met Since 1945

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Progress M1-10

 2003-025A

---

Spacecraft 259 on mission 11P, resupplying Expedition 7. Launch mass 7270 kg. Total docked mass 6934 kg at Pirs nadir.

After undocking on Sep 4, 259 was left in orbit for a remote sensing mission using the Klest-M TV camera.

M1-10
Date	Time	Event	Orbit
2003 Jun 8	1034:19	Launch by Soyuz-U	KB LC1
		T+1:58 Strapons
		T+2:41 GO sep
		T+4:47 Blok A sep
		T+4:57 KhO sep
	1043:04	T+8:45 Blok I MECO
	1043:08	T+8:49 Blok I sep	88.78 186 x 241 x 51.7
	1409	DV1 34m/s
	1456	DV2 26m/s
			90.72 304 x 314 x 51.6
2003 Jun 10	1015:02	DV3 3 m/s
	1821	Blok I reentry
2003 Jun 11	0905:40	DV4 9m/s 23s
	0951:06	DV 21m/s 53s
2003 Jun 11	1114:43	Docked with Pirs
	1115:25	Docking time (NK)
2003 Sep 4	1941:44	Undock from Pirs
	2234:00	23s TCM
2003 Oct 2	1126	Deorbited 145.3s 78 m/s	247 x 340 x 51.6
		DO CO	69 x 253 x 51.6
	1158	Entry