The Ivy League

 https://welib.org/md5/055effaee2d0789315af3b3350138825

People: July 27,2015

 https://welib.org/md5/4b122519639047df4248e7f64729796e

Reference Guide to the International Space Station - Utilization Edition - September 2015

 https://welib.org/md5/04305c17b6f9e023f39f56f7cecde44e

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

China Rich Girlfriend

 https://welib.org/md5/730a0cc1d6e44a3e97678781f8129b57

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

Progress M-15M

 2012-015A

---

Vehicle 11F615A60 415, mission 47P, Upgraded with improved MMOD shields and a new Kurs-NA rendezvous system which will be tested in a redocking exercise. Kurs-NA is lower mass, uses less power and does not require retraction during docking.

Carries Sfera-53 satellite support structure and satellite. Sfera-53 was to be stowed in Pirs and then deployed on EVA 31. 17KS.300Yu9220-0.

Mass 7287 kg, with 880 kg prop. Cargo 2356 kg

 

PM15M
Date	Time	Event	Orbit
2012 Apr 20	1250:24	Launch by Soyuz-U	KB
	1255	Blok A sep
	1259	Blok I MECO
	1259:13	Blok-I sep	88.67 187 x 230 x 51.6
	1332:26	DV1 69s 27.4m/s	89.71 223 x 296 x 51.6
	1408:33	DV2 19s 7.2m/s	89.96 247 x 296 x 51.6
	1638:59	DV3 SKD 20s 7.2m/s	90.02 255 x 295 x 51.7
	1723:36	DV4 SKD 10s 3.9m/s	90.03 246 x 305 x 51.7
2012 Apr 21	1412:24	DV5 24s 1.6m/s	90.07 252 x 302 x 51.7
2012 Apr 22	0400		90.07 250 x 304 x 51.6
2012 Apr 22	1439:32	Docked with Pirs
		HO to ISS
2012 Apr 23			92.39 386 x 396 x 51.6
2012 Jul 20		HC
2012 Jul 22	2026:00	Undock from Pirs
	2028	Sep burn
2012 Jul 23	0500s	Retro burn
2012 Jul 29
		Rendezvous with ISS for Kurs-NA test
	0032	Braking
	0038	Begin flyaround at 600m
	0051	Complete flyaround
	0051	150m? Begin final approach
	0053	100m and closing
	0058	20m to Pirs
	0100	2m range
	0101	Docking with Pirs
	0111	Hard dock
		HO
2012 Jul 6		Remove Kurs-NA avionics box for Soyuz return
2012 Jul 30		HC
	2119	Undocked
	2122	Sep-1 burn
2012 Aug 2		Radar-Progress experiments
2012 Aug 6	2020	30s burn 5m/s
2012 Aug 7	2029	15s burn 2.5m/s
2012 Aug 8	1850:50	29s 5m/s
2012 Aug 9	1900:50	29s 5m/s
2012 Aug 10	1812:20	6s 1.2m/s
2012 Aug 11	1650:30	29s 5m/s
2012 Aug 11	1720:30	29s 5m/s
2012 Aug 12	1710:20	29s 5m/s
2012 Aug 12	1715:20	29s 5m/s
2012 Aug 20	1517	Go for deorbit
	1522:00	DO burn 167.1s 89.3 m/s
	1524:47	DO CO
	1612	Impact Pacific 51 00 S 127 48W

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

Sicral 2

 2015-022B

---

Thales Alenia Space/Cannes and Telespazio/Roma Spacebus 4000 satellite for Italian MoD (Ministero della Difesa italiano) and DGA/France. 37E. Telespazio will operate the ground network. TAS/F builds the platform and the French SHF payload; TAS/I builds the overall satellite system.

TAS/I and Telespazio formed TGC (Temporary Group of Companies, RTI: Raggruppamento Temporaneo di Imprese) to develop the system, with TAS/I as the headquarters.

Sicral 2
Date	Time	Event	Orbit
2015 Apr 26	2000:07	Launch by Ariane 5	CSG ELA3
		T+2:15 EAP sep
		T+3:13 Fairing sep
	2008:50	T+8:43 EPC MECO
	2008:56	T+8:49 EPC sep	-1041 x 158 x 6.9
	2009:00	T+8:53 ESC-A burn
	2024:49	T+24:42 ESC-A burnout
	2028:00	Thor sep
	2032:31	Sylda sep
	2034:20	Sicral 2 sep
	2047	Passivation

Human Spaceflight and Exploration

 https://welib.org/md5/83ba3d102494cae742d2fa75d6130e66

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

Panamsat 5

 1997-046A

---

PAS 5 was launched by ILS Proton in Aug 1997. The first HS-601HP high power satellite in the PAS system, it is an AOR satellite at 58W. The C-band Americas beam provides coverage of Latin America, the US and Canada. The satellite also provides European coverage.

Panamsat/Greenwich,CT and Hughes Galaxy/LA merged 1997 May 16.

Mass of PAS 5 is 3600 kg. PAS 5 suffered power loss in 1999, and also had trouble with its XIPS engine.

PAS 5 capacity was leased to Arabsat in 2002 as Arabsat 2C (Badr C), with the ownership remaining with Panamsat. The satellite was renamed Intelsat IS-5 in 2007.

In 2013 the satellite was moved to 50E.

PAS 5
Date	Time	Event	Orbit
1997 Aug 28	0033:30	Launch by Proton 387-02/DM3 No 2L	KB
	0035:36	T+2:06 St 1 sep
	0035:42	T+2:12 Stage 2 burn
	0039:05	T+5:35 Stage 2 sep
	0039:14	T+5:44 GO sep
	0043:19	T+9:49 stage 3 sep
	0044:14	T+10:44 DM fairing sep
	0147:50	T+1:14:20 DM-3 burn 1
	0154:25	T+1:20:55 DM-3 MECO
1997 Aug 28			635.87 214 x 36018 x 51.6
		Coast for 5:05
	0652:12	T+ 6:18:42 DM-3 burn 2
	0714:02	T+6:40:32 DM-3 sep
	0837	DM-3 depletion
1997 Aug 28			804.60 8588 x 35966 x 14.6
1997 Sep 2	2100?	LAM-1
1997 Sep 2			973.94 16347 x 35990 x 7.0
1997 Sep 4	2200?	LAM-2
1997 Sep 5			1339.15 31748 x 35985 x 0.9
1997 Sep 6	1800?	LAM-3
1997 Sep 6			1364.24 32750 x 35985 x 0.4
1997 Sep 8	0700?	LAM-4
1997 Sep 9			1436.15 35745 x 35830 x 0.1 GEO 57.8W
1997 Nov 14			1436.13 35782 x 35791 x 0.0 GEO 58.0W
1999 Oct 17			1436.12 35782 x 35792 x 0.0 GEO 58.0W
2001 Jun 11			1436.14 35769 x 35805 x 0.1 GEO 58.1W
2001 Jun 15		mv out	1440.77 35870 x 35885 x 0.1
2001 Sep 9		mv in	1436.99 35787 x 35820 x 0.0 GEO 155.5W
2002 Mar 8			1436.02 35778 x 35791 x 0.1 GEO 155.5W
2002 Jun 2		mv out 156W
2002 Aug 23		mv in 46W
2002 Sep 25			1436.10 35782 x 35790 x 0.1 GEO 45.1W
2002 Dec 5		mv out
2002 Dec 29		mv in 25E
2003 Jul 5			1436.12 35767 x 35806 x 0.0 GEO 26.1E
2006 Aug 1			1436.07 35778 x 35794 x 0.0 GEO 26.1E
2008 Oct 18		Mv out of 26E
2009 Jan 12		Move in	1436.13 35783 x 35790 x 0.0 GEO 169.0E
2012 Oct 16			1436.12 35775 x 35798 x 0.1 GEO 169.0E

Suddenly, Tomorrow Came: The NASA History of the Johnson Space Center

 https://welib.org/md5/a4d55b97b2f12be8097b983a43987c5b

To Orbit and Back Again: How the Space Shuttle Flew in Space

 https://welib.org/md5/efddb7bf386df0b86a2b2176fa6acb80

University of Massachusetts Amherst : an architectural tour

 https://welib.org/md5/228eda3555af9c7ccb554d810f7522bb

Edusat

 2004-036A

---

Edusat (GSAT-3) launch in 2004 Sep. Launch mass 1950 kg, 820 kg dry; 1120 kg BOL.

440N ISRO LAM. 2.4 x 1.6 x 1.15m bus with 10.9m solar panel span.

Stationed at 74E with Insat 3C and Kalpana 1.

\imps{2.5}{images/04036A}

EDUSAT
Date	Time	Event	Orbit
2004 Sep 20	1031	Launch by GSLV-F01	SDSC
		T+1:44 Stage 1 burnout
		T+2:30 SOM burnout
		T+2:30 Stage 2 burn
		T+3:47 Fairing sep 115 km
		T+4:48 Stage 2 burnout
		T+5:04 Stage 3 MES
	1047	T+16:39 Stage 3 MECO
	1047	T+16:54 Stage 3 separation	162 x 35814 x 19.3
2004 Sep 20	1615		630.88 162 x 35814 x 19.3
2004 Sep 21	0218	LAM-1 49:56	804.79 8784 x 35780 x 7.0
2004 Sep 22	0509	LAM-2 42:00	32800 x 36000 x 0.25
2004 Sep 24	0451	LAM-3 26:15	GEO61E+2.5/d
2004 Sep 25		Deploy antenna, 3-axis stabilized
2004 Sep 29	1643		1426.61 35590 x 35610 x 0.1 GEO 69.7E+2.4E/d
2004 Oct 6			1436.07 35745 x 35826 x 0.1 GEO 70.8E
2004 Oct 14		Drifting	1434.25 35748 x 35752 x 0.1 GEO 72.3E+0.5E/d
2004 Nov 18			1436.09 35770 x 35802 x 0.0 GEO 74.0E
2006 Aug 8			35772 x 35800 x 0.0 GEO 74.0E
2011 Mar 10			1436.14 35757 x 35817 x 1.8 GEO 74.0E

Ayame 1

 1979-009A

---

The ECS (Experimental Communications Satellite) was built by Mitsubishi and Ford to carry out communications experiments in the UHF, SHF, submillimeter and millimeter bands. It was a spin stabilized cylinder with a mass of 130 kg (260 kg at launch), 0.93 m long (1.96m with antennas) and 1.41 m diameter. After launch ECS was named Ayame (`Iris'). Planned location was 145E.

ECS was based on the ETS-2 bus. Total mass of 260 kg was 139 kg ABM, 10 kg prop, and 111 kg dry satellite. Unfortunately, contact with ECS was lost 12 seconds into the apogee motor burn. The yaw weight (a 0.7 kg mass on a 1.8m wire) meant to tumble stage 3 did not deploy from stage 3, and stage 3 collided with ECS 37s after separation.

Element sets assigned to Ayame are misidentifications until 2005, when it was found in a 12669 x 34219 km x 9.9 deg orbit.

The Star 37 final stage was cataloged 20 years later, in 1999. The decayed second stage was retrospectively cataloged in 2000 but assigned to an old catalog number originally belonging to debris from the Magsat satellite; no TLEs are available.

A debris object in near-GTO was cataloged in 2008.

N-1 Stage 2 is 5860 kg full with 4740 kg prop, 1120 kg em, 53.35 kN thrust. (ISTS10-47), or 6032 kg full 5376 kg prop, 656 kg em (ActaAst7,967). Isp 285s or 290.2s (both values in AstraAc7,967). 250s burn time or: 4706f 1015 kg empty 5722 f (ISTS11-267). I take the latter, since it's a post-flight report of an actual mission.

Mass estimate: post stage 2 burn, 1015 kg + 669 + 260 = 1944 kg; 6645 kg f; if 290s then dV = 2844 ln ( 6645 / 1944) = 3500 m/s; for stage 3 burn 260 + (669/105).

Ayame
Date	Time	Event	Orbit
1979 Feb 6	0846	Launch by N-I	TNSC
		T+3:45 St 1 MECO
		T+3:54 Stage 1 sep
		T+3:56 Stage 2 MES
	0850	T+4? Fairing sep
	0854	T+8:04 SECO Stage 2 cutoff, parking orbit	200 x 300 x 30.4?
		Stage 2	171 x 192 x 30.43 (SSR)
	0911?	T+25m? Star 37 burn 37s	606.8 191 x 34590 x 24.1
	0913	Star 37 sep, failed to despin
	0914	Star 37 collided with Ayame
	0914	Ayame AKM and antennae damaged
1979 Feb 6	1420?	Apo 1
	1930?	Peri 1
1979 Feb 7	0100?	Apo 2
	0530?	Peri 2
	1130?	Apo 3
	1530?	Peri 3
	2100?	Apo 4
1979 Feb 8	0150?	Peri 4
	0800?	Apo 5
	1130?	Peri 5
	1800?	Apo 6
	2200?	Peri 6
1979 Feb 9	0400?	Apo 7
1979 Feb 9?	0400?	AKM burn
		T+12s contact lost
1979 Feb 9	0238	Misid	1500.01 36259 x 37797 x 0.5
1979 Jul 2		Misid	1351.28 31411 x 36808 x 0.5
1979 Nov 19		Misid	1348.81 29749 x 38371 x 0.1
1983 Dec 9		Misid	1314.48 28448 x 38293 x 0.3
1990 Nov 18		Misid	1312.72 29268 x 37403 x 2.0
1993 Dec 30		Misid	1312.99 29258 x 37423 x 4.9
2005 Jan 12		Found	854.23 12669 x 34129 x 9.9
2013 Aug 7			854.20 12673 x 34213 x 8.0