Town and Country: February 2014

 https://welib.org/md5/6c39093d35e7b9a509953b2e0bf1328c

Hot Bird 8

 2006-032A

---

HB8 is an EADS Astrium Eurostar 3000 satellite with a mass of 4875 kg. 

HB8
Date	Time	Event	Orbit
2006 Aug 4	2148:00	Launch by Proton	LC200/39
		T+2:04 St 1 sep
		T+5:31 St 2 sep
		T+5:45 Fairing sep
	2157:45	T+9:45 St 3 MECO,
	2157:45	T+9:45 St 3 sep	-932 x 163 x 51.50
	2159:19	T+11:19 Briz-M MES-1
	2206:56	T+18:56 MECO-1	173 x 173 x 51.49
	2256:20	T+1:08:20 MES-2
	2313:01	T+1:25:02 MECO-2	258 x 5000 x 50.30
2006 Aug 5	0117:09	T+3:29:09 MES-3
	0128:39	T+3:40:39 MECO-3
	0129:29	DTB sep	316 x 16438 x 49.5
	0130:44	T+3:42:44 MES-4
	0135:35	T+3:47:36 MECO-4	395 x 35820 x 49.10
	0640:12	T+8:52:12 MES-5
	0647:33	T+8:59:33 MECO-5	3801 x 35786 x 13.00
	0659:20	T+9:11:20 Briz-M sep	3746 x 35539 x 13.1
2006 Aug 6			703.77 3857 x 38504 x 13.0
2006 Aug		Apogee burns
2006 Aug 16			1435.65 35770 x 35784 x 0.1 GEO 1.7E+0.1E/d
2006 Aug 16		Move in at 1.7E
2006 Sep 18			1436.08 35775 x 35796 x 0.1 GEO 4.0E
2006 Sep 22		Move out of GEO 0.8E/d
2006 Sep 30			1432.75 35711 x 35730 x 0.1 GEO 11.9E+0.8E/d
2006 Oct 6		Move in at 13E
2006 Nov 28			1436.02 35769 x 35800 x 0.0 GEO 13.1E
2012 Mar 1		Renamed EUTELSAT HOT BIRD 13B
2012 Mar 2			1436.07 35761 x 35810 x 0.0 GEO 13.0E

IGS-1

 2003-009A

---

MELCO built the optical IGS. Mass of 850 kg. Operated by National Space Information Center.

Launch was by H2A 2024 with a 4/4D-LC adapter. IGS-R1 was in the upper position and IGS-O1 was in the lower position. The two satellites have a common box-shaped bus (possibly based on USERS) with two solar panels. IGS-O1's payload module has a box-shaped instrument section with two cameras.

Solar panel span around 16.5m.

Reportedly Optical-1 only achieved 2-3m instead of the planned 1m.

Name is Kougaku 1 gouki (Optical machine number 1).

IGS Optical-1
Date	Time	Event	Orbit
2003 Mar 28	0127	Launch by H2A 2024	TNSC
		T+1:40 SRB-A burnout
		T+1:47 SRB-A sep
		T+4:20 PLF sep
		T+6:35 St 1 MECO
		T+6:43 St 1 sep
		T+6:49? Stage 2 burn
	0142	T+15? SECO
	0143?	IGS-1a sep	94.37 484 x 491 x 97.31
	0145?	Upper fairing sep
	0145?	Fairing Side panels sep
	0150?	IGS-1b sep	94.36 483 x 491 x 97.31
2003 Apr 22			487 x 496 x 97.3
2014 Jul 18		Reentered

Payload:

• OPS-M optical sensors, 1-m res

2003-009B

---

NASDA's IGS will be its first spy satellite. Two radar and two optical sats will be launched. Radar sat mass is 1200 kg. The satellites are built by MELCO. The Radar sat payload module carries a deployable radar antenna.

Solar panel span probably about 22.5m.

Times based on ADEOS, with separation times pure guesswork. The satellite failed after 4 years of its planned 5 year mission.

Name is Re-da 1 gouki (Radar-1).

IGS Radar-1
Date	Time	Event	Orbit
2003 Mar 28	0127	Launch by H2A 2024	TNSC
		T+1:40 SRB-A burnout
		T+1:47 SRB-A sep
		T+4:20 5S PLF sep
		T+6:35 St 1 MECO
		T+6:43 St 1 sep
		T+6:49? Stage 2 burn
	0142	T+15? SECO
	0143?	IGS-1a sep	94.37 484 x 491 x 97.31
	0145?	Upper fairing sep
	0145?	Fairing Side panels sep
	0150?	IGS-1b sep	94.36 483 x 491 x 97.31
2003 Apr 22			497 x 511 x 97.3
	1030?	lower peri	488 x 512 x 97.3
2007 Mar 25		Power supply failed
2012 Jul 26	0952	Entry over Pacific

Payload:

• SAR, 3-m res

MER-2 (Spirit)

 2003-027A

---

Mars Exploration Rover-2 "Spirit".

Mass 150 kg. Launch 2003 May 22. Landing 2004 Jan 2.

Spirit launched with targeted B-plane (104184, 235634) km and achieved (292891,407923) with TCA 2004 Jan 6, 2317 UTC.

The landing sites for the Mars Exploration Rovers: the centers of the target ellipses are 14.640S, 184.702W in Gusev Crater and 2.060S 5.992W in Meridiani Planum (according to JPL; another source gives 14.64S 184.94W and 2.06S 6.23W).

Actual landing site 14.5692S 175.4729E, i.e. approx 184.5W

AIAA2004-4980 quotes actual as 14.57189S 175.47848E.

Cruise stage: 2.65m dia, 1.6m high; based on MPF. 193 kg dry plus 50 kg prop.

Backshell and parachute are 209 kg. Heatshield is 78 kg. Each around 2.6m dia 1.5 tall?

Lander is 348 kg not including Rover. but including airbags.

Rover is 1.4m long and 1.0m wide, mass 185 kg. Box + 6 wheels + panel + booms.

During approach to the atmosphere the gas generator heaters were running hot.

The lander platform was named Columbia Memorial Station on Jan 6. Landing site was 14.571892S 175.47848W.

On Jan 21 Spirit stopped communicating with Earth and went into a cycle of repeated computer reboots when its flash memory file system filled up. The software problem was eventually fixed by controllers and Spirit resumed operations on Jan 31.

Mars Re is 3397.5 km; landing site is at -5.2 km; entry at 124.7 km, Vi 5.628 km/s with theta = -11.4949 at az 70.925207 over 17.7420S 161.7765E. Entry mass was 827 kg including 90 kg heatshield; 14.1m parachute diameter.

Mass breakdown:

	PK	Older data
Rover	174 kg	185
Lander	365 kg	348
RAD x 3	15 kg	)
RAD prop	37 kg	)
Backshell	146 kg	)209	+ parachute
Heatshield	90 kg	78
Cruise	183 kg	193
Prop	52 kg	50
Total	1062 kg	1063
Payload adapter
PAM/Star 48 full	2213	2134 motor
PAM/Star 48 empty	191	111 motor

Three RAD - rocket assisted decleration, Star 8. Star 8 TE-M-1076-1 is 0.69m long 0.20m dia with 33 kNs impulse, 7.5kN for 4.3s at 272.9 eff Isp and 17.4 kg full 5.1kg dry.

Three TIRS - Tranverse Impulse Rocket System (Star 3, TE-M-1082-1) with 1 kg full 0.5kg prop.

ATK 0.20m dia 0.69m long 17 kg mass, 4.3s burn. TP-H-3062 CTPB prop. Enhanced derivative of MPF RAD. Impulse 31 kNs. Thrust 7.3 kN.

TIRS - transverse impulse rocket system

ATK 0.08m dia 0.29m long 1.2 kg, 0.62s burn.

Rover A
Date	Time	Event	Orbit
2003 Jun 10	1758:47	Launch by Delta 7925-9.5	CC SLC17A
		T+1:03 SRM 1-6 off
		T+1:05 SRM 7-9 on
		T+1:06 SRM sep 1-6
		T+2:11 SRM sep 7-9
		T+4:23 MECO
		T+4:31 St 1 sep
	1803:24	T+4:37 SES-1	-3400 x 120
	1803:29	T+4:42 Fairing sep	-3390 x 120
	1808:15	T+9:38 SECO-1	160 x 180 x 28.5
	1825:15	T+26:28 SES-2
	1827:21	T+28:34 SECO-2	163 x 4762 x 28.5
	1828:14	T+29:27 St 2 sep
	1828:51	T+30:04 TES 90s over 18E 20S ? 200 km?
	1830:19	T+31:32 TECO C3= 9.2510 at 182 km
	1835:01	T+36:14 Yo-yo despin released
	1835:06	T+36:19 Star 48 sep	182 x -99113 x 28.50
	2030?	SES-3
		SECO-3	162 x 4619 x 25.7
		Injection C3 = 8.822 RLA,DLA = 347.35, -2.32	184 x -103070 x 28.46
2003 Jun 11	0347	Pass EL1:4
2003 Jun 16	0127	Depart Earth sphere 1.5Mkm
2003 Jun 20	1700	TCM-A1 axial 28min; range 2.66Mkm
		TCM-A1 perpendicular 22 min; total
		Total 16.5m/s (or 14.3m/s?)
2003 Aug 1	1800	TCM-A2 6m/s 9m; Gusev targeting
2003 Nov 14	1830	TCM-3 0.6m/s 132s
2003 Nov		T-45d Approach phase
2003 Dec 27	0200	TCM-A4 3.4s 0.03m/s
2003 Dec 30	1545?	Enter Mars sphere 1.08Mkm
2004 Jan 4
	0255	Turn to entry, heat shield forward
	0311	Turn complete
	0326	Alt 10600 km at 3.4 km/s
	0345	Coolant venting
	0401	3200 km, 4.23 km/s
	0404:52	E-15:00 Cruise Stage sep	15 x Inf
	0408	2000 km
		E-3.0min 465 km 5.202 km/s 1731 km uprange
		E-2.5min 354 km alt
		E-2.0min 298 km alt
		E-1.5min 245 km
		E-1.0min 195 km 5.401 km/s
73 12192 437	0419:52	E-0 Entry at 128 km, 75 deg az, 5.4km/s/rel, -12 deg rel (-11.5 in.)
		Postflight: Entry 5.63 km/s -11.5 deg	13 x -18404
		117 km 5.449 km/s 703 km range
		E+60s 74 km 5.4415 km/s
		E+102s Peak heating
	0423:05	E+240s (actual was later) para deploy
		E+251s (actual) para deploy
	0424:15	E+271s Heatshield sep
	0424:25	E+272s Backshell release
		E+282s Bridle descent complete
		E+311s 34 km, radar on
		E+339s Airbags inflate
	0425:42	E+339s RAD/TIRS rockets fire at 115m
		RAD dV = 315 m/s at 100m alt. Three RAD, 4s burn, 10 kN?
	0425:44	E+348s Bridle cut (backshell sep) at 8m
	0425:48	E+350s Landing at Gusev at 24 m/s
		Bounces 57s to 100m?
		28 impacts for 300 m
	0436	Landing complete
	0444:09	Antenna tone
	0447	Airbags retract L+66m
	0521	Airbag retraction stops
	0521?	Petals open L+187m
2004 Jan 5		HGA deployed
2004 Jan 6	2317	PAM-D pass Mars at 502000 km
2004 Jan 8		Airbag retraction continues
2004 Jan 9		Front wheel deploy
2004 Jan 10		Standup sequence complete
2004 Jan 15	0821:30	Move command transmitted
	0840	Rover move off lander by 3m
	0841	Rover move complete
2004 Jan 18		Move to Adirondack rock
2009 May 7		Stuck at Home Plate
2010 Jan 26		Attempts to free from Home Plate abandoned
2010 Mar 30		LOS for Martian winter

Payload:

• Pathfinder landing system, airbags

• Pancam Panoramic camera

• Mini-TES Miniature Thermal Emission Spectrometer

• Mossbauer Spectrometer (on arm)

• APEX Alpha proton X-ray spectrometer (on arm)

• Microscopic imager (on arm)

• RAT Rock Abrasion Tool (on arm)

BSat 2B

 2001-029B

---

Orbital/Dulles Star 1. Launch mass 1298 kg, dry mass 535 kg. Size 3.7 x 2.2 x 2.1m, 15.7m span. Location at 110E. The satellite was decommissioned after it entered the wrong orbit; the apogee motor was never fired. Since the launch contract was for on-orbit delivery it presumably remained the property of Orbital and should have been registered by the US.

BSAT 2b
Date	Time	Event	Orbit
2001 Jul 12	2158:00	Launch by Ariane 5G	CSG ELA3
		T+0:07 Liftoff
		T+2:24 EAP sep
		T+3:25 Fairing
	2207:59	T+9:59 EPC cutoff
	2208:06	T+10:06 EPC sep	59 x 2026 x 6.6
	2208:28	T+10:28 EPS burn
	2208:31	T+10:31 Aestus problem, 80 percent thrust
	2223:28	T+25:28 Aestus cutoff early
		T+26:48 Aestus cutoff due
	2226	T+28:06 Artemis sep
	2228	T+29:58 Sylda 5 sep
	2233	T+35:35 BSAT-2b sep
	2344?	EPC entry
2001 Jul 14			317.26 589 x 17472 x 2.9
2001 Aug?		Decommissioned
2001 Aug 13			317.25 593 x 17467 x 3.0
2001 Sep 28			317.25 606 x 17454 x 3.0
2001 Oct 15			317.25 613 x 17447 x 3.0
2003 Sep 3			317.19 656 x 17400 x 2.9
2006 Aug 3			317.09 434 x 17616 x 2.9
2013 Aug 10			161.99 136 x 6794 x 3.0
2014 Jan 28	1121?	Reentry (+/- 3 hours)

Angara-1.2PP

 2014-S37

---

A special variant, 1.2PP (Perviy Polyot, first flight). Vehicle 14A125-01 No. 71601, was launched from Area 35's USK 14P211 pad.

A1.2PP
Date	Time	Event	Orbit
2014 Jul 8	1200:00	Launch by Angara-1.2PP	PL LC35
		T+3:42 St 1 MECO
	1203	T+3:44 St 2 burn RD-0124A
		T+3:52 Fairing sep
		St 1 impact Barents Sea
	1208:11	T+8:11 St 2 MECO	-1008 x 189 x 75.2
	1223:02	T+23:02 St 2 impact

Astronomica : galaxies, planets, stars, constellation charts, space exploration

 https://welib.org/md5/22d0f7489991c77634e7792ac67f134b

Ofeq 5

 2002-025A

---

'Ofeq-5 was launched in May 2002 and began military imaging operations by early June.

The satellite is 2.3m high and 1.2m dia. Mass is about 300 kg. The LK-A variant of Shavit was used.

The Ofeq's Rafael HPS (Hydrazine Propulsion System) has 12 5N thrusters and two 25N thrusters. The PEPT-420 tank carries 30l of hydrazine so at 1g/cc that's 30 kg.

'Ofeq-5
Date	Time	Event	Orbit
2002 May 28	1525	Launch by Shavit	Palmachim
		Stage 1 MECO at T+0:52
	1526?	Stage 1 sep
		Stage 2 MECO at T+1:44,
	1528?	Stage 2 sep, 110 km
	1532?	Fairing (2 pieces) sep, 250 km
	1532?	Main equipment compartment sep
	1534?	Stage 3 92s burn over W Med.	-5735 x 262 x 143.4
	1535?	Stage 3 sep	95.00 262 x 774 x 143.5
	1613	Orbit raise burn
	1620?	Ofeq apogee burn 33m/s
			96.07 369 x 771 x 143.5
2002 Jun 18			95.94 366 x 762 x 143.5
		Trim	95.99 369 x 763 x 143.5
2003 Apr 9			94.19 348 x 609 x 143.5
2003 Apr 9		Perigee raise	94.69 397 x 609 x 143.5
2004 Feb 3			93.66 376 x 530 x 143.4
2004 Feb 4		Perigee raise	93.97 407 x 530 x 143.4
2004 Oct 26			93.88 391 x 482 x 143.4
2004 Oct 27		Perigee raise	93.88 446 x 481 x 143.4
2004 Dec 13			93.78 441 x 477 x 143.4
2004 Dec 14		Perigee raise	94.16 474 x 481 x 143.5
2005 Nov 2			93.80 458 x 462 x 143.5
2005 Nov 3		Apogee raise	94.01 460 x 480 x 143.4
2005 Nov 17			94.00 461 x 478 x 143.4
2005 Nov 18		Orbit trim	94.21 477 x 483 x 143.4
2007 Oct 15			93.83 456 x 468 x 143.4
2007 Oct 16		Orbit raise	94.32 462 x 510 x 143.5
2007 Oct 18			95.07 509 x 535 x 143.5
2013 Mar 12			95.07 514 x 528 x 143.5