Columbus

 2008-005

---

The ESA COF lab module was built by EADS/Bremen, formerly DaimlerChrysler Aerospace (DASA) Space Infrastructure of Munchen, with an outer shell by Alenia/Torino based on the MPLM. It will be 6.7m long and 4.5m in diameter with a mass of 9500 kg empty. Columbus is named after Cristoforo Colon (1451-1506), the explorer. The full COF is 8m long 4.5m dia. Mass is 10230 kg (or 9900 kg) empty; it is launched with 2500 kg of payload, for a launch mass of 12077 kg (FRR; 12730 kg or 12250 kg, AWST Aug 06) with a further 7660 kg to be added on orbit.

The ETC (European Transport Carrier) ISPR-class rack is used for transport of payload items to orbit using CTBs (Cargo Transfer Bags) and as a workbench and stowage on orbit. It will eventually be replaced by another rack and be returned and reused aboard MPLM flights.

Early suggested CEPF payloads include: ACES (Atomic Clock Ensemble in Space); Solar (solar irradiance measurements on coarse pointing device); EXPOSE (life sciences exposure), SPORt (Sky Polarization Observatory, all sky polarization in 20-90GHz range), EuTEF (technology experiments)

Payload:

• FSL Fluid Science Lab; Rack location O1 (Overhead) (launch on COF) *

• ETC European Transport Carrier; Rack location O2 (launch on COF at D4; stay at D4?)

• ZSR Stowage Rack location O3

• ZSR Stowage Rack location O4 (EDR is at O4 at launch)

• ER6 Express Rack 6; Rack location A1 (Aft) (launch on UNK)

• Biolab Rack location A2 (launch on COF in O2 pos, moved) *

• ZSR Stowage rack, launch at A2 then moved

• EPM European Physiology Modules, Rack Location A3; launch on COF at O4 *

• HRF-2 Human Research Facility, Rack Location A4; launched on STS-114

• System rack Life support; Rack location D1 (Deck)

• System rack Rack location D2

• System rack Rack location D3

• Stowage rack Rack location D4

• EDR European Drawer Rack; Rack location F1(Fwd) (Launch on COF at O4) *

• MSG Micogravity Science Glovebox; Rack location F2; launched UF2 MPLM

• MARES Muscle Atrophy Research Exercise System; Rack location F3 (launch UF-3 MPLM)

• HRF-1 Human Research Facility-1; Rack location F4 (launched on Destiny)

• CEPF Columbus External Payload Facility (on end cone)

DSP-20

 2000-024A

---

DSP 20 stepped in to fill the gap caused by the loss of DSP 19. It probably was stationed over the Pacific.

DSP 20
Date	Time	Event	Orbit
2000 May 8	1601	Launch by Titan 4B-29	CC LC40
		T+2:11 Stage 1 burn
		T+2:26 SRMU sep
		T+3:26 56' Fairing sep
		T+5:21 St 1 sep
	1609	T+8:47 St 2 MECO	92.3 199 x 582 x 28.6 (UN)
	1610	T+8:54 St 2 sep
	1713	T+1:13:22 IUS-22 SRM-1
	2229	T+6:28:57 SRM-1 sep	637.2 332 x 35972 x 28.6 (UN)
	2233	T+6:32:32 SRM-2 burn
	2255	T+6:54:23 SRM-2 sep	1444.3 35924 x 35971 x 2.9? (UN)
2000 May 9?		Cover sep
2000 May 9			1443.9 35911 x 35970 x 2.9 (UN)
2000 Oct		Reach 8.5E
2003 Nov			GEO 8.5E
2008 Feb		DSP Europe	GEO 7.0E
2008 Mar		Move out
2009 Jun		DSP Pacific	GEO 164.9W
2011 Jan		DSP Pacific	GEO 165.9W

Pujiang

 2015-051A

---

SAST/SISE satellite, Main payload of first CZ-11 launch. Technology sat to test heat pumps, microprocessors, other components.

CZ-11 has four solid stages; the fourth stage has some kind of additional propulsion to allow a perigee lowering burn, which caused it to reenter a few days after launch.

PJ1
Date	Time	Event	Orbit
2015 Sep 25	0141	Launch by CZ-11	JQ SLS-E
	0142?	Stage 1 sep
	0144?	Stage 2 sep
	0148?	Stage 3 burn
	0149?	Stage 3 burnout
	0150?	Stage 3 sep	94.12 466 x 485 x 97.3
	0153?	Stage 3 RCS burn, lower perigee
		91.69 145 x 570 x 97.3 (Stage 4)
2015 Oct 2			94.15 468 x 486 x 97.3

Telstar 6

 1999-005A

---

FS-1300 SS/Loral Telstar 6 launched by Proton. Owned by Loral Skynet, it will provide broadcast and distribution services for the US and the Caribbean. Launch mass 3763 kg, 1469 kg dry, 2421 kg BOL. Size 3.1 x 3.0 x 5.5m, Span 31m with 8.6m antenna span.

DM3 No. 8L was replaced by No. 4L at a late date.

Telstar 6 was sold to Intelsat in 2004 as Intelsat Americas 6 or Intelsat 3006. In 2007 it was renamed Galaxy 26. In 2009 its commercial traffic was routed to Galaxy 25 and it mas moved to support US DoD UAV data traffic in Iraq and Afghanistan.

Telstar 6
Date	Time	Event	Orbit
1999 Feb 15	0512:00	Launch by Proton/DM3 No 4L	KB
	0514:07	T+2:07 St 1 sep
	0517:35	T+5:35 St 2 sep
	0517:44	T+5:44 Fairing sep
	0521:48	T+9:48 St 3 sep	88.44 179 x 215 x 51.6
	0625:49	T+1:13:49 Blok DM3 burn
	0632:59	T+1:20:59 MECO-1	643.13 201 x 35942 x 51.6
	1133:25	T+6:21:25 Blok DM3 burn
	1136:14	T+6:24:14 MECO-2
	1154:01	T+6:42:01 Blok DM3 sep	6638 x 35756 x 17.4
1999 Feb 15			757.92 6716 x 35600 x 16.9
1999 Feb 16	0230?	AMF-1
1999 Feb 17			940.49 15037 x 35801 x 7.9
1999 Feb 19	0100?	AMF-2
1999 Feb 20			1403.78 34509 x 35793 x 0.3
1999 Feb 21	0000?	AMF-3
1999 Feb 24			1435.68 35714 x 35842 x 0.1 GEO 94.0W+0.1E
1999 Mar 9			1436.09 35775 x 35797 x 0.1 GEO 93.0W
1999 Nov 3			1436.11 35764 x 35809 x 0.0 GEO 93.0W
2000 Jun 9			1436.12 35774 x 35800 x 0.0 GEO 93.1W
2001 Apr 23		Primary CPU failed
2004 Mar		Renamed IA-6
2006 Aug 3			1436.10 35774 x 35798 x 0.0 GEO 93.0W
2008 Jun 29		Power loss, half capacity
2009 Feb 19			1436.10 35774 x 35799 x 0.02 GEO 93.0W
2009 Feb 21		Moved to IOR for DoD comm support
2009 Mar 16		Move in	1436.42 35759 x 35826 x 0.0 GEO 50.8E
2014 Mar 25			1436.06 35772 x 35799 x 0.0 GEO 50.0E

A Tale of Two Besties : A Hello Giggles Novel

 https://welib.org/md5/31bb5eaac97ab63f2cf0422ab90be7c4

Amos 1

 1996-030B

---

The Israeli Aircraft Industries Amos communications satellite was launched by an Ariane 4. It will provide telephone, telex, fax, and TV relay services to the Middle East and Eastern Europe. Amos is presumably named after Amos of Tekoa (c. 750BC?), the Hebrew prophet.

The IAI-built spacecraft is a 2.4 x 2.0 x 2.3 m box with two solar array panels of 10.6m span. Launch mass is 996 kg; BOL mass 580 kg, dry mass 479 kg. Alcatel provided the comms payload. Amos was launched as the lower payload beneath a SPELDA 30 structure. The upper satellite was Palapa C-2, interestingly enough owned by an Islamic nation, Indonesia. AMOS was stationed over 4 deg W. The Mabat Company operated the satellite in conjunction with its Spacecom subsidiary, and supervised initial on orbit communications tests in July.

AMOS 1
Date	Time	Event	Orbit
1996 May 16	0156	Launch by Ariane 44L (V86)	CSG ELA2
	0159	Stage 2 TIG
	0201	Stage 2 sep
	0201	Stage 3 TIG
	0214	Stage 3 MECO
	0216?	Palapa C-2 sep
	0218?	SPELDA sep
	0220?	Amos sep
1996 May 16			633.25 310 x 35788 x 4.0
1996 May 16?		LAM-1
1996 May 17?		LAM-2
1996 May 19			1374.81 33326 x 35829 x 0.1
1996 May 21	1130?	LAM-3
1996 May 23			1433.83 35724 x 35760 x 0.1 GEO 9.0W+0.5E
1996 May 31			1435.27 35748 x 35792 x 0.1 GEO 4.4W
1996 Jul 7		Test transmissions carried out
1996 Aug 3			1436.11 35772 x 35801 x 0.1 GEO 4.0W
1999 Oct 15			1436.09 35772 x 35800 x 0.0 GEO 4.0W
2006 Aug 1			1436.08 35768 x 35804 x 0.1 GEO 4.1W
2008 Sep 14			1436.02 35780 x 35790 x 0.1 GEO 3.9W
2008 Sep 29		Move out
2008 Nov 7		Move in	1436.02 35764 x 35805 x 0.3 GEO 1.5W
2009 Jul?		Bought by Intelsat
2009 Jul?		Renamed IS-24
2009 Jul 28			1436.03 35771 x 35799 x 1.0 GEO 1.3W
2009 Aug 18		Move out
2009 Nov 23		Move in at 47E
2009 Dec 9			1436.10 35770 x 35803 x 1.3 GEO 47.3E
2011 Jun 14			1436.03 35767 x 35802 x 2.7 GEO 47.3E
2011 Jun 15		Move out
2011 Aug 28		Move in at 31E	1436.16 35776 x 35799 x 2.8 GEO 31.0E
2012 Jul 3			1436.07 35772 x 35800 x 3.5 GEO 31.0E

Venus Express

 2005-045A

---

VEX uses the Astrium Mars Express bus, with the S400 propulsion system. Soyuz-ST/Fregat by KB. Mass 1240 kg including 570 kg prop. Fregat mass at Blok I sep is 6270 kg.

Ops from Cebreros, Spain and ESOC.

Box 1.5 x 1.8 x 1.4m + 2 panels, span 8.0m.

Launch by Soyuz-FG No. 010 (ST14) and Fregat 1010.

At injection, altitude is 334 km and velocity is 2.78 km/s, inclination 51.57 deg.

Injection was Vinf= 2.7968 km/s, Ra, Dec 309.52 -21.01.

VEX
Date	Time	Event	Orbit
2005 Nov 9	0333:34	Launch by Soyuz-ST/Fregat	KB LC31
		T+1:58 St 1 sep
	0337	T+4:14 GO sep
		T+4:47 St 2 sep 150km 4.5 km/s
		T+4:58 KhO sep
	0342	T+8:45 Blok I MECO
	0342	T+8:48 Blok I sep 190 km. 7.750km/s	30? x 190 x 51.8
		T+8:53 Fregat ullage
	0343:23	T+9:48 Fregat MES-1 20s 50m/s
	0343:43	T+10:08 Fregat MECO-1 EOI 185.9 x 188.5 x 51.7
	0410?	Stage 3 reenter over Pacific 165W 15S?
	0453	T+1:22:00 Fregat MES-2 escape burn
	0509	T+1:36:10 Fregat MECO-2
	0511	T+1:36:30 Fregat sep	334 x -114954 x 51.6
	1439	Pass EL1:4
2005 Nov 10	0638:52	TCM-0 0.5m/s 48s, test
2005 Nov 10	1010	Pass lunar orbit
2005 Nov 11	0614:33	TCM-1 3.4m/s 209s
2005 Nov 12	1230	Leave Earth sphere SOI
2005 Nov 14	1857	Depart Earth sphere 1.5Mkm
2005 Nov 25			285.01d 0.7020 x 0.9931 AU x 0.26
2006 Feb 17		3s TCM 2.8m/s, 400N engine
2006 Mar 29		TCM 0.13m/s
2006 Apr 8	2238	Enter Venus sphere 1.01Mkm
2006 Apr 9	2150	Enter Venus sphere SOI
2006 Apr 11	0000		374 x -43251 x 89.61
2006 Apr 11	0710:29s	VOI 1.252 km/s (1.31 km/s) 53min
	0736:37s	Periapsis 250 km ?
	0755:13	End of eclipse
	0800:42s	VOI MECO
	0840		-19 x 324447 x 89.65 (HOR)
		VOI CO	250 x 220000 x 90?
			662 x 330685 km x 90
2006 Apr 15	1830	Apoapasis 1	114 x 326550 x 89.71
2006 Apr 15	1830	PCM-1 5.1 m/s
		-108 x 326550 x 89.70 (HOR)
		257 x 330685 x 90 (ESA Bul)
2006 Apr 20	0450	Periapsis 2, VOI-2 257 km
	1830	ALM-1 200.3 m/s 379s
			259 x 99108 x 90.0
2006 Apr 23	1730	VOI-3 ALM-2 105.3m/s main eng.	266 x 70463 x 89.99
2006 Apr 26	2300	VOI-4 ALM-3 9.2m/s, 10N thrusters	1491.255 274 x 68408 x 90.00
2006 Apr 28		Periapsis
2006 Apr 30	0300	VOI-5 ALM-4 8.0m/s 603s	1450.245 282 x 66911 x 90.00
			268 x 67000 x 90.0 (ESABul)
2006 May 3	1323?	ALM-5 2.0m/s 233s	268 x 66582 x 90
2006 May 6		PCM-2 at apoapsis
2006 May 7			1438.368 247 x 66513 x 90.00
		Pericenter at 84N
2008 Jul		Orbit adjust burns
2008 Aug 4	s	Orbit adjust complete	185? x
2009		Fregat stage in 0.7 x 1.3 AU orbit
2010 Jan 13	1246	Fregat stage passes 131023 km from Earth
2012 Mar 8		Star tracker failure after solar storm
2012 Mar 9		Star trackers operating again
2014 May 17		Begin walk-in phase, natural pericenter decrease	190 km
2014 Jun 18		Begin EOM aerobraking phase, 137 km
2014 Jun 23	1042	OCM, lower peri 2.8 km to circa 135 km
2014 Jun 23	2231	Periapsis
2014 Jul 2		OCM lower by 0.8 km	130 km Peri
2014 Jul 12		Dip to 129.1 km
2014 Jul 12	s	End aerobraking, peri raise burns
2014 Jul 18		Peri raise burn 8, 300 km peri
2014 Jul 26		Peri raise burn 15, 460 km	460 x 63000
2014 Nov 23		Begin peri raise burns
2014 Nov 28		Loss of attitude control
		Loss of contact (some telem packets)
		In safemode
2015 Jan 19		last detection of carrier signal	120 x
2015 mid?		reentry

Payload:

• ASPERA Analyser of Space Plasmas and Energetic Atoms

• PFS High resolution IR Fourier Spectrometer

• SPICAV UV and IR spectrometer for solar/stellar occultation and nadir observations

• VeRa Venus Radio Science instrument

• VIRTIS UV-Visible-IR imaging spectrometer

• VMC Venus Monitoring Camera

• MAG Magnetometer