Navstar 50

 2009-043A

---

GPS IIR-21 (IIRM-8) is SVN 50 (PRN 5) in slot E3, replacing IIA-26. Mass 2059 kg at launch

GPS 49
Date	Time	Event	Orbit
2009 Aug 17	1035:00	Launch by Delta	CC SLC17A
		T+1:03 GEM 1-6 out
		T+1:05 GEM 7-9 on
		T+1:06 GEM 1-6 sep
		T+2:09 GEM 7-9 out
		T+2:11 GEM 7-9 sep
	1039	T+4:23 MECO
		T+4:31 St 1 sep
		T+4:36 St 2 SEIG
		T+4:57 Fairing sep
	1045	T+10:48 SECO-1	174 x 206 x 37.50
		T+1:02:29 SEIG-2
	1138	T+1:03:11 SECO-2	191 x 1241 x 37.95
	1139	T+1:04:04 St 2 sep
	1139	T+1:04:41 TES
	1141	T+1:06:08 TECO
	1141	T+1:06:52 NCS blowdown
	1143	T+1:08:01 St 3 sep	354.77 188 x 20256 x 40.1
	1143	T+1:08:03 St 3 yo deploy
	1221	T+1:46:40 SEIG-3 depletion 32s
	1222	T+1:47:12 SECO-3	204 x 1224 x 32.91
2009 Aug 19	1952	AKM burn	356.86 189 x 20386 x 40.1
	1953	AKM burnout	718.08 20160 x 20209 x 55.12
2009 Sep 4			719.43 20160 x 20275 x 55.11

Salyut - The First Space Station: Triumph and Tragedy

 https://welib.org/md5/1d9765f4fe5b36983a19f3d899b20514

Intelsat 902

 2001-039A

---

SS/Loral FS-1300 Extended satellite. Launch by Ariane 4. (also 903, 904). Mass 4723 kg. At 60.0E Dry mass 1978 kg. Size 2.8 x 3.5 x 5.6m with 31m span.

Intelsat 902
Date	Time	Event	Orbit
2001 Aug 30	0646	Launch by Ariane 44L	CSG ELA2
		T+2:30 PAL sep
		T+3:31 St 1 sep
		T+3:34 St 2 MES
		T+4:22 Fairing sep
		T+5:43 St 2 sep
	0651	T+5:48 St 3 MES
	0704	T+18:42 St 3 MECO
	0706	T+20:49 St 3 sep
		T+21:00 St 3 avoidance maneuver
2001 Aug 30			630.97 179 x 35801 x 7.0
2001 Sep 1	1200	LAM-1
2001 Sep 2	0845	LAM-2	1201.86 26368 x 35765 x 0.7
2001 Sep 4	1540	LAM-3	1435.60 35757 x 35796 x 0.1 GEO 56.5E+0.1E
2001 Oct 20			1436.09 35760 x 35812 x 0.1 GEO 62.0E
2002 Jan 15			1436.06 35773 x 35798 x 0.0 GEO 62.0E
2006 Aug 3			1436.08 35774 x 35797 x 0.0 GEO 62.0E

Iridium 62

 1998-021A

---

Iridium SV62 was launched on the third Iridium Proton mission. 

Iridium 62
Date	Time	Event	Orbit
1998 Apr 7	0213:03	Launch by Proton-K	KB
	0214	Stage 1 sep
	0217	Stage 2 sep
	0217	Fairing sep
	0221	Stage 3 sep	140 x 140 km x 73 ?
	0250:07	T+37:04 DM2 burn 1
	0250:32	T+37:29 DM2 MECO-1
	0333	DM2 burn 2
	0338	DM2 MECO-2
	0341	Iridium deployment begins
	0410?	T+1:57? DM2 MES-3 deorbit
	0438?	T+2:25? DM2 reentry
1998 Apr 7			94.83 498 x 522 x 86.7
1998 Apr 9			94.85 501 x 521 x 86.7
1998 Apr 16			95.76 552 x 558 x 86.7
1998 Apr 18			96.77 601 x 606 x 86.7
1998 Apr 26			100.36 772 x 778 x 86.4
1998 May 3			100.40 777 x 777 x 86.4
2004 Jun 29			100.40 775 x 779 x 86.4
2009 Apr 27			100.40 776 x 779 x 86.4

Town and Country: May 2009

 https://welib.org/md5/ab5b7c365fd252be324b898e7ba9d553

The Planets

 https://welib.org/md5/77a753a4686e8ebaa508d42ff2a2fa60

The rough guide to the iPhone

 https://welib.org/md5/78dee77bd321fe8f170708a5c003cb77

Meridian 2

 2009-029A

---

The second Meridian flew in 2009. Due to a programming error the Fregat shut down during its second burn, and the small third burn did not take place.

Meridian 2
Date	Time	Event	Orbit
2009 May 21	2153:33	Launch by Soyuz-2-1A/Fregat	PL 43/4
	2156:30	Control to Titov center
	2157	Blok A sep
	2201	Blok I MECO	-100? x 204 x 62.8
	2202	Blok I sep
	2203?	Fregat MES-1
	2205?	Fregat MECO-1	200? x 204? x 62.8
	2243?	Fregat MES-2
	2247	Meridian perigee
	2252?	Fregat MECO-2 early shutdown
2009 May 22		Fregat MES-3 aborted
	0013	Fregat sep	275 x 36483 x 62.8
	0425	First apogee

Progress M-66

 2009-006A

---

Mass 7088 kg launch, 6778 kg docking, 6078 kg undocking. Carried Orlan MK-5 (109 kg). Cargo 2407 kg, GO 1238 kg.

Date	Time	Event	Orbit
2009 Feb 10	0549:46	Launch by Soyuz-U	LC31
		T+1:59 BVGD sep
		T+2:42 GO sep
		T+4:45 Blok A MECO
		T+4:47 Blok A sep
		T+4:57 KhO Sep
	0558:31	T+8:45 MECO
	0558:35	T+8:49 Blok I sep
2009 Feb 10	0538		89.67 186 x 230 x 51.6
	1330		89.77 243 x 282 x 51.6
2009 Feb 11			89.76 243 x 282 x 51.6
2009 Feb 13	0520		89.79 245 x 282 x 51.6
2009 Feb 13	0719	M-66 docked with Pirs
2009 Feb 13	1747		91.67 350 x 362 x 51.64
2009 May 6	1517:58	Undocked from Pirs
	1520:58	DV 0.7m/s 15s
	1824:37	DV SKD 4.8m/s 10s
		KPT-13 Plazma-Progress experiment
2009 May 14	1557:05	Plazma-Progress engine burn, 2.4m/s 6s
2009 May 15	1450:23	Plazma-Progress engine burn, 6.0m/s 12s
2009 May 16	1518:38	Plazma-Progress engine burn, 3.0m/s 7s
2009 May 17	1410:12	Plazma-Progress engine burn, 3.0m/s 7s
2009 May 18	1428:30	Deorbit 162s 89.68m/s
	1514	Debris impact 42 34S 139 24W

Natural Science in Western History (Complete) (v. 1 & 2)

 https://welib.org/md5/d6fc51b66438cafa1cddbd8e760733b0

Malory's Contemporary Audience: The Social Reading of Romance in Late Medieval England

 https://welib.org/md5/eea0aebde1f1834680efd6f2b8f8107f

Cloudsat

 2006-016A

---

An ESSP with a BCP RS-2000. Launch by Delta 7420-10 with Calipso under a DPAF fairing.

Size 2.5 x 2.3 x 2.0 m mass 848 kg full (773 kg dry?). 5.1m span. Cloudsat flies in formation with Picasso-Cena and carry a 94 GHz nadir-looking radar. Both satellites will also fly in looser formation with Aqua as part of the A-Train Constellation: Aqua, Cloudsat, CALIPSO, PARASOL and Aura. Combined launch mass 1295 kg.

Orbit 717 x 734 x 98.08. A-Train 1:31PM.

Joint NASA/Canada. Carries a cloud profile radar. an IR O2 spectrometer, and a visible imager. It uses the data from the Picasso lidar in combination with its own radar. Launch 2003.

Ground control by RSC/Kirtland, using AFSCN; mission management by JPL.

Now STP P00-4 SMC-801, Cloud and Aerosol Vertical Profiler.

Calipso is mounted on the upper DPAF cone-cylinder. The lower DPAF cone remains attached to the Delta second stage.

Cloudsat
Date	Time	Event	Orbit
2006 Apr 28	1002:16	Launch by Delta 7420-10C
		T+1:04 SRM 1-4 out
		T+1:22 SRM 1-4 sep 29 km
		T+4:24 MECO 112 km
		T+4:40 SES-1
		T+4:45 Fairing sep
	1013:32	T+11:16 SECO-1	173 x 684 x 98.1
	1102:16	T+1:00:00 SES-2 12s
		T+1:00:12 SECO-2
	1104:18	T+1:02:02 Calipso sep 690 km
	1137:31	T+1:35:15 Upper DPAF sep
	1138:51	T+1:36:35 Cloudsat sep
2007 Jul 4		burn to adjust orbital lifetime

Payload:

• PASBI Profiling A-band Spectrometer/Visible Imager 7500A, 1.3mu

• CPR Cloud Profiling Radar, mm-wave radar

• Propulsion system, 200m/s capability mono hydrazine, 4 x 4.5N, Isp 220s

USA-181

 2004-050A

---

The HLV-OLDSP Heavy Lift Vehicle Operational Launch Service Demonstration Payload (DemoSat) is a 5993 kg 1.95m high x 1.38m dia cylindrical test payload to record launch environment.

The Delta IVH has three LOX/LH2 RS-68 powered CBC stages in tandem and a 5-m D4HSS and 5m fairing. The vehicle is 71.6m tall and has a launch mass of 720t. Cargo capacity is 23t to LEO. Launch thrust is 8700 kN. This was the first flight of the 5-meter diameter upper stage. The CBCs cut off 8s early leading to long SES-1 and SES-2 burns, and the second stage ran out of fuel in the third burn. The post-SECO-1 orbit was marginal, with an apogee of around 105 km,

The Demosat carried USAF-STP's University Nanosat-2, two separating payloads built by ASU and UCoBoulder and integrated by AFRL/VS, and was to have tested low shock satellite separation systems. The satellites were dispensed afte SECO-1 and reentered in less than one orbit.

Delta 4H
Date	Time	Event	Orbit
2004 Dec 21	2150:00	Launch	SLC37B
		T+0:50 Center RS-68 to 57 percent thrust
		T+3:55 Outboard RS-68 to 57 percent
		T+4:00 Outboard CBCs MECO (8s early?)
		T+4:08 Outboard CBCs sep 75 km
		T+4:08? Center RS-68 to 102 percent
		T+4:50? 101 km
		T+5:30 Center CBC MECO 149 km
	2155	CBC sep
	2155:53	T+5:53 RL10B-2 SES-1 129 km
	2156:03	T+6:03 5-m fairing sep 134 km
	2203:17?	RL10B-2 SECO-1
	2206:52	T+16:52 Nanosat stack sep in low orbit	105 x 196 km
	2210:29	T+20:29 RL10B-2 SES-2
	2218:32	T+28:32 RL10B-2 SECO-2	185 x 35788 x 27
			645.30 288 x 36428 x 27.2
	2235	Nanosats at 120 km
	2246?	Nanosat perigee?
2004 Dec 22	0327:13	T+5:37:13 RL10B-2 SES-3
	0330:28	T+5:40:28 RL10B-2 SECO-3
	0339:37	T+5:49:37 Demosat sep
	0345:45	T+5:55:45 CCAM
		T+5:57:55 CCAM end
2005 Jan 7			1044.67 19032 x 36420 x 13.5

Optus C1

 2003-028B

---

Optus C1/D will also carry a military payload for the Australian Defense Force. Contractor is Mitsubishi Electric with a Space Systems/Loral bus. Launch to 156E. Mass 4725 kg. Box + 2 cruciform panels. dry is 1978 kg, 8.2 x 7.8 x 24.9m deployed. Owner is Singtel Optus Pty (formerly Cable and Wireless Optus Ltd (CWO)), Sydney. Control from CWO/Belrose.

Optus C1 was on an 1194H adapter. The 5.2m Sylda E (+300mm) adapter was used, with a medium fairing with one 0.5m model 5400 extension shell.

Optus C1/D
Date	Time	Event	Orbit
2003 Jun 11	2238:15	Launch by Ariane 5G	CSG ELA3
		T+2:22 EAP sep
		T+3:20 Fairing sep
		T+9:45 EPC MECO
	2248:07	T+9:52 EPC sep	55 x 1972 x 7.5
	2248:14	T+9:59 EPS MES
	2305:07	T+26:52 EPS MECO
	2306:22	T+28:07 Optus sep from 1194H adapter
	2310:14	T+31:59 Sylda 5E sep
	2313:17	T+35:02 BSAT 2 sep from 937V5 adapter
		T+51:21 end of V161 mission
2003 Jun 12	0005?	EPC reentry
2003 Jun 12			637.42 604 x 35707 x 7.03
2003 Jun 14		LAM-1	926.83 14600 x 35621 x 1.8
2003 Jun 16	0130?	LAM-2
2003 Jun 18			1403.73 34687 x 35613 x 0.04 GEO 143E+8E/d
2003 Jul 8		GEO 151E
2003 Jul 12		GEO 156E
2006 Aug 8			1436.10 35772 x 35800 x 0.0 GEO 156.0E

May 11,2005

 https://en.wikipedia.org/wiki/Diamond

Superbird 4

 2000-012A

---

Space Communications Corp of Tokyo ordered an HS-601HP in 1998. HS-601HP Superbird 4 launch by Ariane in 2000. Operational position 162E. The satellite was known as Superbird B2 when in operation.

Launch mass is 4057 kg. Dry mass is 1657 kg. Size is 2.8 x 2.3 x 2.6 m with 26m span.

Superbird 4
Date	Time	Event	Orbit
2000 Feb 18	0104	Launch by Ariane 44LP V127	CSG ELA2
		T+1:09 PAP sep
		T+2:27 PAL sep
		T+3:32 St 1 sep
		T+3:33 St 2 burn
		T+4:37 Fairing 01 sep
		T+5:44 St 2 sep
		T+5:48 St 3 burn
	0122	T+18:51 St 3 MECO
	0125	T+21:09 St 3 sep
2000 Feb 18			630.76 223 x 35747 x 5.0
2000 Feb 22?		LAM-1
2000 Feb 22			857.45 11282 x 35755 x 1.9
2000 Feb 26?		LAM-2
2000 Feb 29			1436.19 35777 x 35799 x 0.1 GEO 139.2E
2000 Mar 30		mv out
2000 Apr 18			1436.07 35774 x 35797 x 0.1 GEO 162.3E
2000 May 27			1436.07 35773 x 35798 x 0.1 GEO 162.4E
2006 Aug 4			1436.09 35784 x 35788 x 0.0 GEO 162.0E

Talent

https://welib.org/md5/b8cdf6280b5af39d1f4d72ae7b29ffbd

March 8,2001

 https://web.archive.org/web/20080504032246/http://digest-archive.degrassi.ca/DD126.htm

The Luxe

 https://welib.org/md5/69d3dcd941670d591f447e85ee6068c5

March 13,2006

 https://en.wikipedia.org/wiki/Theodore_Roosevelt

STS-103 (Discovery)

 1999-069A

---

Launch mass is 113881.9 (112563 in retrospective data). Sep mass of ET is 109965.3 kg. 3 EMUs carried. TCS. One HST-PFR in 13P and one on the FSS.

EVAs were carried out through the axial (longitudinal) hatch on the EAL. On the first EVA, the astronauts replaced HST's 6 gyros, the crucial mission task. Next, they fought with the valve covers on the NICMOS vents; they had planned to open the valves by hand and with a power ratchet tool, but in the end they had to go and get a pistol grip tool to remove the covers. The vents open, any remaining N2 will be vented by the time the new neon cooling system is installed on SM-3B. One of the old gyros wouldn't fit properly in the COPE at first, but eventually the crew managed to shove it in. The third task on EVA 1 was installation of Voltage Improvement Kits intended to prolong the life of the spacecraft's batteries. The walk was extended to allow the crew to install all six kits.

EVA-2 saw the installation of an Intel-486 based computer in the spacecraft.

During prep for EVA-3, Grunsfeld's suit had a problem, so he wore Foale's suit instead. On EVA-3, two bays were covered with the new outer blanket layers. There wasn't time to cover four more bays, so that was left for SM-3B.

 

STS-103
Date	Time	Event	Orbit
1999 Nov 4	1500	Roll from OPF/1 to VAB/1
1999 Nov 5		Mate to ET in VAB/1
1999 Nov 13	1227	Roll to LC39B
1999 Dec 16		Scrub at T-11h
1999 Dec 17		Scrub
1999 Dec 20	0050:00	Launch	KSC LC39B
	0052:04	SRB sep
	0058:26	MECO	90.89 56 x 587 x 28.5
	0058:45	ET-101 sep
	0134:08	T+44:00 OMS-2 2:33 75.2m/s	313 x 579 x 28.5
	0136:41	OMS 2 CO
	0149		93.63 320 x 583 x 28.5
	0230	PLBD open
	0615:30	OMS-3 NC-1 91s 46m/s
	0617:02	OMS-3 CO
	1400		95.32 484 x 583 x 28.5
	1930s	RMS tests
1999 Dec 21	0431:20	OMS-4 NSR 47s 24m/s
	0432:08	OMS-4 CO
	0432:23	RCS NC-1 trim	0.4s
	0526:49	RCS NC-2 31s 2m/s
	0527		96.28 570 x 589 x 28.5
	1826:22	OMS-5 R NC-3 20s 5m/s
	1826:42	OMS-5 CO
	1826:55	NSR trim 0.2s
	1914:34	OMS-6 L NH 17s 4m/s
	1914:51	OMS-6 CO
	2128:00	RCS NCC 1s
	2228:06	TI 9s, 1.3m/s, mass 104144 kg
	2248:06	MC-1 2s
	2322:58	MC-2 5s
	2339:58	MC-3 2s
	2349:58	MC-4 7s
1999 Dec 22	0002	On -Rbar at 207m
	0034:01	Grapple	591 x 610 x 28.5
	0133	Berth on FSS
	0142:00	Latched
	0203	On external power
	0208	RMS ungrapple
	0600		96.71 591 x 610 x 28.5
	1838	Depress at 1psi
	1841:37	EVA depress end
	1852?	HO (TC closed), axial hatch
	1854	EVA-1 on battery (Smith, Grunsfeld)
	1901	Thermal cover open
	1902	Egress EV1
		Grunsfeld on RMS
	2018	Prep to change RSU2
	2050?	RSU-2R out of ORUC
	2119	RSU-2 removed
	2130?	RSU-2R installed
	2135?	RSU-2 in ORUC
	2135	RSU-3R out of ORUC
	2156	RSU-3 removed
	2210?	RSU-3R installed
	2215?	RSU-3 in ORUC
	2215?	RSU-1R out of ORUC
	2235	RSU-1 removed
	2243	RSU-1R installed
	2250?	RSU-1 in ORUC
		Difficulty closing RSU-1 in box
	2250	Attempt to open NICMOS valves
	2333	Second attempt
1999 Dec 23
	0006	NICMOS cooling valves opened
	0108	Begin Voltage Improvement Kit work
	0129	VIK 1-3 into Bay 3
	0150	Begin VIK 4-6 into Bay 2
	0208	VIK install complete
	0252	Ingress
	0258	Thermal cover closed
	0302	Hatch closed
	0306	Repress begins
	0309:28 Begin repress (STS MR)
	0310	EVA-1 off battery, 8:15
	0310	Repress, NASA dur 8:15:10, JCM dur 8:32
		EVA-2 Foale, Nicollier
	1828	Depress begins
	1845	Airlock at 2psi : DEPRESS?
	1852:33	Depress complete (MR)
	1855	Depressurized at 0.2psi
	1900	Hatch open
	1905:56	EVA-2 on battery
	1913	Thermal cover open, egress
	1938	Foale on RMS
	2015	DF-224 computer removed
	2045?	DF-224 stowed
	2050?	HST-486 out of ORUC
	2120	HST-486 computer installed
	2200?	Foale off RMS, Nicollier on RMS
	2341	FGS-2R removed from HST
	2357	FGS-2 out of ORUC
1999 Dec 24	0043	FGS-2 installed in HST
	0140?	FGS-2R stowed in ORUC
	0303	Ingress; dur 7:50
	0307	HC; dur 8:07
	0311	Begin repress, on orbiter power
	0316:19	Repress : NASA dur 8:10 JCM depress dur 8:31
		EVA-3 Grunsfeld, Smith
	1848	Go for depress
	1909:51	Depressurized (MR)
	1915?	Inner hatch open
	1917	Depress complete
	1917	On battery EVA-3
	1926	Thermal cover open
	1927	Egress
		Grunsfeld on RMS
	2200		96.71 590 x 610 x 28.5
		NOBL layers added
1999 Dec 25	0202	Off RMS
		Rotate telescope
	0255	Ingress
	0301	Thermal cover closed
	0307	Hatch closed
	0318	Grunsfeld EMU failed to switch to OV power
	0325:48	Repress 8:08 NASA; JCM 8:15
	2000:30	RMS grapple HST
	2118:41	HST unberth
	2303:01	Release T+6:21:28
	2303:45	Sep-1 RCS 5s 0.4m/s
	2338:54	Sep-2 RCS 5s 0.4m/s
1999 Dec 26	2108:30	RCS adjust 95s 7m/s lower peri 28km
1999 Dec 27	0600		96.40 562 x 609 x 28.5
	1827	PLBD closed
	2248:26	Deorbit 4:49 157m/s	50 x 616 x 28.4
	2253:15	OMS DO CO
	2329:41	Entry Interface
1999 Dec 28	0000:47	MGTD KSC RW33 7:23:10:47
	0000:58	NGTD
	0001:34	WS

Terra

 1999-068A

---

Terra (EOS AM-1) was the first large EOS satellite. Earth Observing System AM-1 is built by LMT (formerly Astro Space) Valley Forge. Terra is the first NPOESS satellite. Launch of the spacecraft into 705 km 98.2 deg 10:30am SSO is by ILS Atlas 2AS AC-141 from V SLC3E in 1998 Dec. The stretched 14' EPF fairing was used for the first time. Launch mass 4854 kg full, with 328 kg hydrazine.Total 4765 kg at separation.

Control will be from the GSFC EOS Control Center. Launch was delayed due to problems with the ground ops software. 6.8m long 3.5m dia. box + 10m solar array. Box + 1 panel; bus has heritage from UARS.

The plan was to fly Terra in the same orbit as Landsat 7, but that was delayed when the first orbit raise burn was aborted due to a roll problem.

Terra
Date	Time	Event	Orbit
1999 Dec 18	1857:39	Launch by Atlas IIAS	V SLC3E
		T+00:59 SRB 3-4 burn
		T+1:44 SRB1-2 sep
		T+1:58 SRB3-4 sep
		T+2:46 BECO
		T+2:49 Booster sep
		T+3:11 Fairing
		T+4:42 Atlas MECO
		T+4:44 Atlas sep
	1902:40	T+5:01 Centaur MES
	1908:49	T+11:10 Centaur MECO	98.01 653 x 673 x 98.3
	1911:19	T+13:40 Centaur sep	98.26 655 x 695 x 98.3
	1925	Centaur depletion	355 x 654 x 98.3
1999 Dec 18			98.14 654 x 684 x 98.2
2000 Jan 11		AOCS-1 burn
2000 Jan 31			98.16 655 x 686 x 98.2
2000 Feb 17			98.48 684 x 687 x 98.2
2000 Feb 23		Final AOCS-8 burn
2000 Mar 30			98.83 701 x 703 x 98.2
2000 May 25			98.83 699 x 705 x 98.2
2002 Aug 4			98.82 701 x 703 x 98.20
2003 Jul 6			98.82 701 x 703 x 98.18
2005 Oct 21		small collision avoidance burn
2007 Jun 22		COLA to avoid FY1C deb, 1.3 km raise

Payload:

• CERES Clouds and the Earth's Radiant Energy System

• MODIS-N Moderate Res Imaging Spectrometer

• MISR Multi Angle Imaging Spectroradiometer

• ASTER Adv Spaceborne Thermal Emision and Reflection Radiometer

Strengthening U.S. Exploration Policy via Human Expeditions to Near-Earth Objects

 https://www.lpi.usra.edu/decadal/sbag/topical_wp/ThomasDJones.pdf

Sirius 5

 2000-077A

---

The third Sirius CD Radio satellite was launched on 2000 Nov 30.

Sirius 3
Date	Time	Event	Orbit
2000 Nov 30	1959:47	Launch by Proton-K/DM3 17L	KB LC81/23
		T+2:00 St 2 MES
		T+2:06 St 1 sep
		T+5:30 St 2 MECO
		T+5:32 St 3 sep
		T+5:35 St 3 MES
		T+5:44 Fairing sep
	2009	T+9:30 St 3 MECO
	2009:37	T+9:49 St 3 sep
	2009	Adapter sep
	2043:27	T+43:40 DM MES-1 375s
	2049:42	T+49:55 DM MECO-1	200? x 24400? x 63.4
	2203:04	T+2:03:17 DM MES-2 113s
	2205	T+2:05:10 DM MECO-2
	2225	T+2:25:10 DM sep
2000 Dec 2			994.81 6177 x 47087 x 63.4
2000 Dec 4		LAM-1	1142.07 12539 x 47089 x 63.4
2000 Dec 6	1100?	LAM-2	1417.13 23749 x 47049 x 63.4
2000 Dec 13			1435.89 24491 x 47073 x 63.4
2000 Dec 20			1435.89 24486 x 47078 x 63.4 GSO 66.0W
2006 Aug 2			1435.96 24363 x 47204 x 63.6 GSO 64.9W

Progress M-02M

 2009-024A

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Progress 11F615A60 No. 402, flight 33P. Carried Orlan-MK No. 6. Mass 7119 kg. Cargo mass 2510 kg including 109 kg Orlan-MK.

Progress undocked on Jun 30, but was kept on orbit and made a return visit to the Station to test out the newly active zenith docking port on Zvezda. The cargo ship approached to 10 meters to test the rendezvous equipment and was then commanded to depart the station without redocking.

It carried Orlan M-26 and M-27 on its departure.

Progress M-02M
Date	Time	Event	Orbit
2009 May 7	1837:09	Launch by Soyuz-U	KB LC1/5
	1841	Blok A sep
	1845:58	Blok I MECO
	1846	Blok I sep
	1954		88.71 187 x 234 x 51.6
	2315	DV 5 m/s 13s 21 kg
2009 May 8	0044		88.90 187 x 252 x 51.6
	1739:55	DV2 79s 32m/s SKD
	1823:03	DV3 180s 25m/s DPO
2009 May 9	1249		90.81 291 x 336 x 51.6
2009 May 11			90.80 291 x 336 x 51.6
	1646:27	DV4 DPO 30s 2.1 m/s
2009 May 12	1741	Kurs on
	1808	SKD burn
	1842	6m/s burn
	1847	TCM
	1849	TCM
	1920?	Rendezvous
	1924:23	Docked with Pirs
			91.56 344 x 357 x 51.64
2009 Jun 30	1829:43	Undocked from Pirs
	1833	Sep burn 15s DPO 0.7m/s	342 x 368
2009 Jul 3			91.50 342 x 353 x 51.6
	2110:15	DPO burn 8s 0.8m/s range 500 km	341 x 364
2009 Jul 11	1739:24	DPO 20s 1.7m/s
2009 Jul 12	1443	Begin rendezvous
	1545?	Progress rerendezvous with ISS
	1636	DPO burn, 9 minute flyby
	1655	Stationkeep with Zvezda zenith port at 150m
		Begin approach
	1704	At 10m from PkhO
1704:27	Braking for sep from MKS
	1707	Stationkeep at 10 m
		Approach cancelled as planned
	1708	Sep-1 burn
	1709	Progress at 150 m
	1715	Progress departs station
2009 Jul 13	1543:00	mass 5721 kg, Deorbit burn 163s 85.0m/s
	1546	Deorbit cutoff
	1628	Impact Pacific at 42 37S 140 34 W