Palapa C1

 1996-006A

---

The Palapa C-1 satellite was owned by PT Satelindo (PT Satelit Palapa Indonesia), a regional company which replaced PT Telekomunkasi as the operator of the Palapa system. It was located at 113E and will cover Indonesia, SE Asia, and parts of China, Japan, India and Australia. Launch mass was 2989 kg, on orbit mass is 1775 kg.

By 1998 Palapa C-1 was owned jointly by PT Satelindo and PT Pasifik Satelite Nusantara (PSN). The satellite lost the ability to charge its batteries in late 1998.

In Nov 2000 the satellite was reowned by Hughes Global Services, which renamed it HGS-3 and then leased the satellite to Kalitel/San Diego, who in turn leased capacity to Turk Telecom as Anatolia 1. It was then moved to 50E.

In late 2002 it was leased by Pakistan's Ministry of Information Technology and Telecommunications, which called it Paksat 1, and moved to 38E.

The national Perumtel/Telkom organization handed over the Palapa C satellites to Satelindo in 1996; Telkom then began to launch 'Telkom' satellites.

Palapa C-1
Date	Time	Event	Orbit
1996 Feb 1	0115:01	Launch by Atlas Centaur (AC-126)	CC LC36B
	0117	BECO
	0117	Booster sep
	0118	Fairing sep
	0119	SECO
	0119	Atlas sep
	0120	Centaur MES1
	0125	Centaur MECO-1	160? x 400? x 28.2?
	0137?	Centaur MES2
	0139?	Centaur MECO2
	0143:47	Centaur sep	1923.25 240 x 89462 x 21.9
			1935.12 255 x 89869 x 21.8 (TLE)
		167 x 90327 x 21.8 (AWST)
	1714	First apogee eq crossing at 60.6W 0.0N
1996 Feb 4	0530?	LAM-1
1996 Feb 6			2811.95 29234 x 89996 x 2.26
1996 Feb			LAM-2
1996 Feb			LAM-3
1996 Feb 12			1509.96 35521 x 38920 x 0.22
1996 Feb 13	1600?	LAM-4
1996 Feb 13			1436.57 35493 x 36099 x 0.14
1996 Feb 13			1435.97 35495 x 36074 x 0.11
1996 Feb 19			1435.66 35481 x 36074 x 0.1 GEO 125.0E+0.1E
1996 Feb 27			1436.18 35493 x 36083 x 0.1 GEO 124.3E+0.03W
1996 Mar 3		Drift
1996 Mar 16		Move in	GEO 113E
1996 May 30			1436.12 35779 x 35795 x 0.0 GEO 113.2E+0.01W
1996 Aug 14			1436.14 35776 x 35798 x 0.0 GEO 112.9E
1996 Aug 15		Move out
1996 Sep 12		Move in	GEO 150E
1996 Sep 19			1436.13 35767 x 35806 x 0.1 GEO 150.5E
1999 Oct 15			1436.11 35778 x 35795 x 0.5 GEO 150.9E
2000 Nov		Renamed HGS-3
2000 Nov 24			1436.15 35771 x 35803 x 1.4 GEO 151.3E
2000 Dec		Reloc to 49E	1448.05 36008 x 36032 x 1.4
2001 Jan 25			1436.10 35688 x 35885 x 1.5 GEO 49.8E
2001 Jun 5			1436.11 35773 x 35800 x 0.1 GEO 50.0E
2002 Nov 28			1436.06 35771 x 35799 x 0.0 GEO 50.0E
2002 Dec 5		mv out	1440.50 35867 x 35878 x 0.0
2003 Jan 23		mv in as PAKSAT
2003 Feb 7			1436.04 35778 x 35792 x 0.0 GEO 38.0E
2004 Feb 10			1432.10 35773 x 35800 x 0.0 GEO 38.0E
2006 Aug 1			1436.05 35772 x 35798 x 0.0 GEO 38.0E

NOAA-17

 2002-032A

---

NOAA M was launched by Titan II in 2002, becoming NOAA 17. It wil go to a 1000LT southbound equator crossing to optimize vegetation mapping, instead of the 0730LT used by earlier NOAA morning satellite.

NOAA M is 4.2m long 1.9m dia with a 6.1m solar panel array. Mass is 2232 kg launch, including 757 kg of fuel in the 42.38 kN Star XFP, which burns for 51s.

NOAA M was the last NOAA to be completed at East Windsor before the transfer to Sunnyvale in 1998.

NOAA M
Date	Time	Event	Orbit
2002 Jun 24	1823:04	Launch by Titan II	V SLC4W
		T+2:31 St 1 MECO
		T+2:32 St 1 sep, St 2 burn
		T+3:38 Fairing sep
	1828:33	T+5:29 St 2 MECO
	1829:35	T+6:31 Stage 2 sep	-2500? x 820
	1837:44	T+14:40 Star 37XFP AKM burn
	1838:35	T+15:31 AKM burnout
	1838:40	T+15:36 AOCS trim burn
	1839:04	T+16:00 end AOCS burn	101.19 807 x 822 x 98.8
		T+20:43 Solar array deploy
		T+22:13 Boom deploy
2006 Aug		AM Primary

Payload:

• AVHRR/3 Advanced Very High Resolution Radiometer

• HRPT/3 High Resolution Picture Transmission

• AMSU-A1 Advanced Microwave Sounding Unit

• AMSU-A2 Advanced Microwave Sounding Unit

• AMSU-B Advanced Microwave Sounding Unit

• SBUV/2 Solar Backscatter UV Radiometer 2

• SEM/2 Solar Environment Monitor

• DCS/2 Data Collection System

• HRIRS High Res IR Sounder

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Chang’e 1

 2007-051A

---

Chang'e is the Chinese moon goddess.

Chang'e-1 (chang'e yihao weixing) lunar probe. Based on its DFH-3 communication satellite, Chang'e-1 will be launched into geostationary transfer orbit by the Long March 3A rocket from the Xichang spaceport and then use its own engine to head out to the Moon and enter a 200 kilometer polar orbit around it. According to Chinese astronomer Renjiang Xie, the launch of Chang'e-1 is now set for April 2007, and a 50-meter deep space network antenna has been inaugurated in Beijing to support the mission. The probe will have a low-resolution imager, a gamma-ray spectrometer and microwave radiometer to study surface composition and temperature, and a laser altimeter to measure the height of topographical features. Although Chang'e-1 is just a test mission, the altimeter will be competitive with those flown on previous missions.

Leading the Chinese lunar program is Ouyang Ziyuan, seen here in front of the new Beijing deep space antenna.

Notes: the mass of Chang'e is about 2350 kg full 1000 kg empty; it is probably a box 2.2 x 1.7 x 2.0m in size with solar panel span 18m. It most likely uses the FY-25 engine with 490N thrust for course corrections and lunar orbit insertion.

- A stereo camera and integrated spectrometer with three CCDs. Its ground resolution will be a rather low 120 m (compare to about 1 meter for Lunar Orbiter and 13 m for Clementine) - A laser altimeter with 120 m accuracy - A gamma and X-ray spectrometer. This particular instrument will be mounted inside the body of the probe, which in my opininion could create some problem since measures will be contaminated by the presence of the spacecraft structure. Gamma-ray spectrometers are usually carried at the end of long booms for this reason. - A 4 band microwave radiometer to measure the temperature of the regolith and infer its depth. - Various deep space environment monitors (particle detectors etc.)

Control from BACC - Beijing Aerospace control center.

China's lunar probe, Chang'e-1, was deorbited at 0736 UTC on Mar 1 and impacted the lunar surface at 1.50S 52.36E at 0813 UTC. The impact site in Mare Fecunditatis is south-east of the crater Taruntius P and west of the Luna-16 landing site.

CE-1
Date	Time	Event	Orbit
2007 Oct 24	1005:04	Launch by CZ-3A	XSC
		T+2:25 Stage 1 MECO
	1007:40	T+2:27 Stage 2 MES, Stage 1 sep
	1009:09	T+3:52 Fairing sep
		T+4:15 St 2 MECO
		T+4:20 St 2 VECO
	1009:40	T+4:21 St 2 sep, St 3 MES
	1015:05?	T+10:00? St 3 MECO-1	200 x 212 x 30.9?
	1026	MES-2
	1028:04	T+23:00 MECO-2
	1029:39	T+24:34 St 3 sep	212 x 50584 x 30.9
	1955		173 x 50432 x 30.9
2007 Oct 25	0955	OTM-1 130s raise peri	600 x
2007 Oct 26	0944	OTM-2	24h x 70000
2007 Oct 29	1001	OTM-3	48h x 120000
2007 Oct 30	1000	At apogee
2007 Oct 31	0915	OTM-4 10.916 km/s	600? x 380000
	0928	OTM-4 complete
2007 Nov 1	0042?	Pass EL1:4
2007 Nov 2		MCC-1
2007 Nov 4	2205?	Enter L sphere
2007 Nov 5	0100	Despin
	0145	Attitude control for LOI
	0315	LOI burn begins, 300 km alt
	0337	LOI 1.948 km/s	210 x 8600
2007 Nov 6	0300s	LOI-2 1.80 km/s	200 x 1700
2007 Nov 7	0000s	LOI-3 1.59 km/s 127 min circ	200 x 200
2008 Jan 27	1550:48	Orbit raise 2 km to shorten eclipse
2008 Feb 21		Eclipse 2 hr
2008 Oct 24		Primary mission complete
2008 Dec 5		200 x 200 km
2008 Dec 6		OTM	100 x 200
		OTM	100 x 100
2008 Dec 18	1800	OTM	17 x 100
2008 Dec 19	0400	After mascon drift	15 x 100
2008 Dec 20	0000	OTM	100 x 100
2008 Dec?		Inclination change
2009 Mar 1	0736	Deorbit burn
	0813	Impact at 1.50S 52.36E

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GOES-12

 2001-031A

---

GOES M is an FS-1300 based GOES I series craft. It carries a new solar X-ray imager. Like the XRS detector, SXI is mounted on the solar array yoke of GOES. Launch Jun 2001

NOAA ground stations at CDA/Wallops and control center SOCC FB-4/Suitland, MD operate the spacecraft. The SEM is operated by the SEL at Boulder.

Mass is 2279 kg at separation, 1042 kg dry. Centaur mass is 2095 kg at separation; at MECO1 Centaur mass is 6165 kg. Uses 14' fairing and 47" adapter.

Size is 2.0 x 2.2 x 2.4m packed, 5.9 x 4.9 x 26.9m span deployed. from solar array to tip of solar sail.

GOES M
Date	Time	Event	Orbit
2001 Jul 23	0723	Launch by Atlas IIA AC-142	CC SLC36A
		T+2:44 BECO
		T+2:47 Booster sep
		T+3:39 Fairing sep
		T+4:42 SECO
		T+4:44 Atlas sep
		T+5:00 MES-1
	0732:40	T+9:40 MECO-1	164 x 505
	0745:02	T+22:02 MES-2
		T+23:33 MECO-2
	0750:00	T+27:00 Centaur sep	274 x 42275 x 20.5
		T+45:10 Centaur blowdown
		T+54:20 Centaur hydrazine depletion
		T+58:47 Centaur depleted
2001 Jul 23			763.28 274 x 42301 x 20.5
		AMF-1 T+1d20h, 54m
2001 Jul 25			792.38 1848 x 42125 x 16.6
		AMF-2 28m L+4d14h27m
2001 Jul 27			832.37 3737 x 42129 x 13.2
2001 Jul 29?		AMF-3 10min L+6d12h
2001 Jul 29			881.06 6035 x 42095 x 10.4
2001 Aug 3		AMF-4	1139.20 17334 x 42173 x 3.9
2001 Aug 5		AMF-5	1271.89 22748 x 42267 x 2.4
2001 Aug 7		AMF-6	1444.34 29489 x 42406 x 1.0 GEO 6.0W+2.1W
2001 Aug 9		AMF-7	1615.77 35628 x 42839 x 0.4
2001 Aug 11			1616.33 35643 x 42844 x 0.3
2001 Aug 12		AAM (apo adjust) 5min T+8d6h
2001 Aug 12			1435.42 35648 x 35894 x 0.3 GEO 91W+0.2E
2001 Aug 12		Redesignated GOES 12
2001 Oct 2			1436.16 35774 x 35800 x 0.2 GEO 90.1W
2001 Dec 21		To NOAA
2001 Dec 21		Drifting in 90-105W band
2002 Jan 1			1436.36 35782 x 35801 x 0.0 GEO 94.2W
2002 Nov 2			1436.51 35781 x 35807 x 0.3 GEO 102.6W
2003 Jan 12			1436.00 35780 x 35793 x 0.4 GEO 105.2W
2003 Jan 23		Relocate
2003 May 11			1436.13 35771 x 35802 x 0.1 GEO 74.7W
2006 May			75W
2006 Aug 4			1436.16 35774 x 35801 x 0.1 GEO 75.1W
2007 Apr 12		SXI end of operations
2007 Nov 28			1436.18 35777 x 35799 x 0.4 GEO 75.5W

Arabsat 4B

 2006-051A

---

Badr-4, EADS Astrium Eurostar 2000+ satellite

3304 kg launch and 1487 kg dry. 2.5 x 1.8 x 2.9m in size, 7.5 x 4.5m x 32m deployed.

Launch by Proton 53515/Briz 88517.

Badr 4
Date	Time	Event	Orbit
2006 Nov 8	2001	Launch by Proton-Briz	KB LC200/39
		T+2:03 St 1 sep
		T+5:33 St 2 sep
		T+5:44 Fairing sep
	2010	T+9:46 St 3 sep	-390 x 173 x 51.53
	2012	T+11:21 Briz MES-1
	2015	T+14:45 Briz MECO-1	173 x 174 x 51.6
	2106	T+1:05:23 MES-2
	2137	T+1:36:14 MECO-2
	2138	T+1:37:04 DTB sep	672 x 22255 x 51.5
	2139	T+1:38:34 MES-3
	2142	T+1:41:30 MECO-3	867 x 35837 x 51.5
		T+3:39:06 MES-4
		T+3:47:49 MECO-4	3127 x 35802 x 14.1
2006 Nov 9	0001	T+4:00:00 Briz sep
2006 Nov 14			687.64 3158 x 35698 x 14.0
2006 Nov 15?		LAM
2006 Nov 16			1431.08 35573 x 35803 x 0.1 GEO 25.2E+1.2E/d
2006 Dec 22			1436.10 35764 x 35808 x 0.1 GEO 26.0E

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Orbital Express

 2007-006A

---

Autonomous Space Transporter and Robotic Orbiter (ASTRO).

STP DARPA-0001 Orbital Express Adv Tech Demo, STP 2000. Launch in 2006 Sep by Atlas V 401 AV-013 from CC

2 sats launched in 2006 for auto docking and fuel transfer. Astro is the servicing and 'chase' spacecraft.

Orbit 492 x 492 x 46.

Mass 1100 kg, length 1.8m dia 1.8m and span 5.6m. Boeing Phantom Works, Advanced Systems is prime, DARPA is lead. Oct prism + 2 panels + manipulator arm.

After launch, ASTRO had some control problems and Nextsat managed the stack; the problems were sorted out by a software update on Mar 23.

After initial experiments culminating in undock and redock, there will be more tests with grapple capture of Nextsat and then seven rendezvous and capture tests and ranges up to 7 km, with further propellant transfers.

Date	Time	Event	Orbit
2007 Mar 9	0310	Launch by Atlas V
		T+4:04 Atlas MECO
		T+4:10 Atlas sep
	0314	T+4:20 Centaur MES-1
		T+4:28 Fairing sep
	0324	T+14:23 Centaur MECO-1	492 x 496 x 46
	0328	T+18:02 Orbital Express sep
2007 Mar		1 week checkout phase
2007 Mar 14		Checkout and initialization complete
2007 Mar 23		Software update solves GNC issue
2007 Mar 28		MDA checkout
2007 Apr 1		Propellant transfer expt
2007 Apr 2		Propellant transfer expt
2007 Apr 5		Prop transfer back from Nextsat
2007 Apr 6		Battery transfer via arm
		Battery installed on NextSat
2007 Apr 9		Prop transfer to N
2007 Apr 11		Prop transfer to N
2007 Apr 13		Prop transfer from N
		Prop coupler demate
2007 Apr 17
		MDA unberth Nextsat, position at 2m distance
	1754	Separation ring ejected
		Reberth Nextsat
2007 May 6
	0522	Undock from Nextsat
		Sep to 10-m
	0630?	Redock Nextsat after 1 hr
2007 May 11		Undock from Nextsat
		Scenario 3-1
		Stationkeep at 10m on way to 30m
		At 30 m
		Return to 10m
		Computer problem, guidance abort
		Retreat towards 120m
		Guidance issues, drift to 2.5km behind for 24 h
2007 May 12		Software issue, burn incorrect
		End up 6 km ahead of NextSat
2007 May 19		Redock with Nextsat
2007 Jun 16	0950	Undock, sep to 120m
		Flyaround; Scenario 5
		Stationkeep for 17 min
		-R-bar approach
		Redocked after 5 hr?
2007 Jun 23		Undock; Scenario 7
		Stationkeep at 4 km
2007 Jun 23		Capture Nextsat with MDA arm
2007 Jun 29?		Undock to 7 km; Scenario 8
2007 Jun 29		Redock
2007 Jul 2		Propellant transfer; complete Sc. 8
2007 Jul 16		EOL scenario: undock
		Separate to 310 km range
		Begin re-rendezvous
2007 Jul 19		Rendezvous with Nextsat
		Stationkeep at 1 km
2007 Jul 20		Separation burn
2007 Jul 21		Nextsat turned off
2007 Jul 22		Astro fuel jettison
		Astro deactivated

Payload:

• Manipulator arm (MDA)

• AVGS guidance sensor (MSFC) for capture

• ARCSS (Autonomous Rendezvous and Capture Sensor System) for acquisition and approach; Laser rangefinder, vis, LWIR sensors, spotlight

• Docking capture system

• Crosslink antenna

• Battery ORU, 24 kg, for transfer to NS

• Computer ORU with firewire connection

2007-006C

---

Ball STP Orbital Express target satellite, to be serviced by the Astro refuelling satellite. Mass 250 kg (or 400 kg?).

Oct Cyl + 1 panel.

Ball Aerospace provided the Next Generation Satellite and Commodities spacecraft (NextSat/CSC) and ground support equipment, and participated in launch and mission operations.

Payload:

• Servicable propellant system with hydrazine (no propulsion system)

• Crosslink antenna

• Docking targets

• ORU fixture

• Grapple fixture

IRS-1C

 1995-072A

---

IRS-1C was the first of an improved generation of IRS satellites, placed in a 10:30 local time sun-synchronous orbit. Mass was 1350 kg launch, 1250 kg on orbit. This was the first launch by a Molniya 8K78M into sun-synchronous orbit; the Blok-I stage was suborbital and the Blok-2BL fourth stage fired to circularize the orbit. Bus was 1.6 x 1.6 x 1.1m with solar panel span about 12m?

IRS-1C
Date	Time	Event	Orbit
1995 Dec 28	0645:18	Launch by Molniya 8K78M	KB LC31
	0647:18	Blok-BVGD sep. 60 km (T+2:00)
	0648:57	Fairing sep, 210 km (T+3:39)
	0649:21	Blok A sep, 252 km (T+4:02)
	0653:24	Blok I sep, 604 km (T+8:05)	-4487 x 803 x 97.94
	0656:40	BOZ ignition, (T+11:21)
	0657	Blok 2BL ignition
	0657:20	BOZ separation, 2BL at 0.75 thrust, 798 km (T+12:01)
	0700:12	Blok 2BL cutoff (T+14:53), 804 km
	0700:19	Blok 2BL sep (T+15:01)	101.1 805 x 817 x 98.6
	0707?	Blok I reentry, Arabian Sea off Somali coast?
	0710:20	Blok 2BL deorbit
1996 Jan 1		Orbit raise	816 x 818 km x 98.6
1996 Jan 5		Cameras switched on
2009 Sep 21		End of operations

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WIRE

 1999-011A

---

The Wide Field IR Explorer (WIRE) is SMEX 5. PI was Perry Hacking of JPL. The cryogenically cooled satellite would carry out IR studies of galaxy formation. The telescope had a 33 arcmin FOV and 12 and 25 micron detectors, with 20 arcsec resolution. It will survey 1000 square deg. Spacecraft mass is 187 kg. The Lockheed Martin cryostat is cooled to 6.5K by solid hydrogen. The spacecraft uses the GSFC SMEX bus with an octagonal structure.

WIRE was launched by a Pegasus rocket from Vandenberg. The Pegasus was successful, although a guidance anomaly caused delays to the next Pegasus flight. WIRE was deployed in a 539 x 593 km x 97.5 deg sun-synchronous orbit.

Unfortunately, the telescope cover was ejected shortly after orbit injection (instead of 3 days later), before the satellite was stabilized. Earthlight entering the aperture boiled off hydrogen, sending the spacecraft tumbling at 1 rev per second. For several days battery power decreased and the hydrogen vented, with the last hydrogen depleted in a few days. The spin was controlled by Mar 12.

The failure investigation reported that a circuit in the satellite's power system surged when it was switched on, and triggered the explosive bolts on the cover.

After the tumbling craft was brought back under control it seemed that it could only be used for engineering tests. Then Derek Buzasi of Berkeley realized that WIRE's star tracker, designed to point the observatory at its targets, was itself a useful optical space telescope. With only a 2-inch aperture, the F/1.8 telescope poses no challenge to Hubble, but its CCD detector can take low resolution images ten times a second and has remarkable photometric accuracy. WIRE's star tracker can measure a bright (0-2mag) star to within a millimagnitude in each exposure, and Buzasi is interested in studying small amplitude oscillations in convective stars, something WIRE's tiny space telescope can do more efficiently than a large ground based telescope like Keck. On April 30 WIRE was turned to observe Procyon as a test target, and followed up with the Ap star Gamma Aquilae, confirming its known variations. A long look at Regulus confirmed its constancy to a few micromagnitudes, showing that WIRE's observations were reliable. The main science program started in May with the target Alpha Ursae Majoris. Operations continued until funding ended in Sep 2000; a second cycle of observations began in 2003 and was concluded in 2008.

WIRE
Date	Time	Event	Orbit
1999 Mar 1	0155	L-1011 T/O from VAFB
	0256	Abort at T-45s, fin pin problem
	0324	L-1011 landed at VAFB
1999 Mar 5	0155	L-1011 T/O from VAFB
	0255:55	Launch from L-1011
		T+0:05 St 1 burn
		T+1:15 St 1 burnout
		T+1:31 St 2 burn
		T+2:06 Fairing
		T+2:43 St 2 burnout
	0307:29	T+7:34 St 3 burn 68s
	0308:37	T+8:42? St 3 burnout
	0309:37?	T+9:42? St 3 sep
	0327	Cryo cover ejected prematurely
		Venting H
1999 Mar 8		Cryo depleted	95.99 539 x 593 x 97.5
1999 Mar 12		Spacecraft stable in safemode
1999 Apr 30		Star camera observations begin
2000 Sep 30		Star camera operations suspended
2003 Nov 26		Star camera operations resume
2003 Dec 16		Observing program begins
2004 Jan		Control to Bowie State, MD
2008 Mar?		End of operations

Payload:

• Solid hydrogen cryostat.

• Telescope, Ritchey-Chretien 0.30m.

• Focal plane arrays, 12 and 25 mu, 128 x 128 pixels

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