https://web.archive.org/web/20080504033305/http://digest-archive.degrassi.ca/DD4.htm
Friday, June 26, 2009
Thursday, June 25, 2009
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 | ||
Sunday, June 21, 2009
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 | ||
Saturday, June 20, 2009
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
Thursday, June 18, 2009
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 | ||
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
Friday, June 12, 2009
TDRS-8
2000-034A
The HS-601 TDRS-H was the first of the new series TDRS, carrying S, Ku and Ka-band but omitting the C-band payload of the earlier models. Size is 21.0m span across solar panels, 13 m across antennas. Stowed 8.4m x 3.4m. Mass is 3180 kg launch, 1777 kg BOL. Will test at 150W and move to 171W for TDRS-West duties. The dish antennas provide single access S, Ku and Ka band capability; a phased array antenna supplies S-band multiple access.
In mid-2001 it was revealed that the phased-array antenna had been disappointing in checkout, and did not meet the spec performance. TDRS H was finally accepted by NASA-GSFC in Aug 2001.
| TDRS H | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2000 Jun 30 | 1256 | Launch by Atlas 2A AC-139 | CC SLC36A |
| T+2:45 BECO | |||
| T+2:48 Booster sep | |||
| T+3:37 Fairing sep | |||
| T+4:35 SECO | |||
| T+4:37 Atlas sep | |||
| T+4:53 MES-1 | |||
| T+6:00 156 km 3.93 km/s | |||
| 1305 | T+9:46 MECO-1 | 167 x 577 x 28.3 | |
| 1321 | T+24:48 MES-2 | ||
| 1322 | T+26:08 MECO-2 | ||
| 1326 | T+29:55 Centaur sep | ||
| 1751 | Antenna deploy | 480.66 230 x 27665 x 27.1 | |
| 2000 Jul 3 | 2130? | LAM-1 | 638.04 389 x 35954 x 26.9 |
| 2000 Jul 4 | 1330? | LAM-2 | 752.16 6066 x 35971 x 17.4 |
| 2000 Jul 5 | 1700? | LAM-3 | 20307 x 35922 x 9? |
| 2000 Jul 7 | 1400s | LAM-3 | 1247.91 28061 x 35973 x 8.2 |
| 2000 Jul 8 | 1100s | LAM-4 | 1407.60 34396 x 36057 x 7.6 |
| 2000 Jul 9 | 0700s | Trim burn | |
| 2000 Jul 18 | 1435.88 35617 x 35947 x 7.0 GEO 150.3W | ||
| 2000 Oct 15 | 1436.04 35646 x 35924 x 6.9 GEO 150.4W | ||
| 2001 Dec 13 | 1436.03 35713 x 35856 x 5.9 GEO 150.4W | ||
| 2002 Jan 3 | Relocating from 150W | ||
| 2002 Jan 22 | Move in at 171W | ||
| 2002 Mar 22 | 1436.13 35773 x 35800 x 5.6 GEO 170.7W | ||
| 2004 Jan 2 | 1436.22 35775 x 35802 x 4.0 GEO 171.1W | ||
| 2004 May | Move to 174.5W | ||
| 2004 May 12 | 1436.06 35768 x 35803 x 3.7 GEO 174.5W | ||
Saturday, June 6, 2009
Thursday, June 4, 2009
Panamsat 9
2000-043A
A new PAS 9, an HS-601HP satellite, was ordered in 1998 for launch in 2000. Launch by Sea Launch in Jul 2000 2000 Jul 28 2242 UTC sched. 3650 kg launch, 2389 kg BOL, 26m span 7m w. Two dishes, two panels. C and Ku band replacing PAS 5 at 58W.
| PAS 9 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2000 Jul 28 | 2242:00 | Launch by Zenit-3SL | |
| T+2:23 St 1 MECO | |||
| T+2:26 St 1 sep | |||
| T+2:29 St 2 MES | |||
| T+3:10 Fairing sep, 124 km | |||
| 2251 | T+9:05 St 2 MECO, sep | -2220 x 264 x 1.2 | |
| Lower fairing sep | |||
| T+9:15 DM-SL MES-1 | |||
| 2256 | T+14:40 MECO-1 | 110.07 200 x 2260 x 1.2 | |
| T+53:57 MES-2 | |||
| T+59:40 MECO-2 | |||
| 2352 | T+1:09:54 DM-SL sep | 664.64 1928 x 35772 x 1.2 | |
| T+3h50m DM-SL disposal burn | |||
| 2000 Jul 29 | 664.64 1928 x 35772 x 1.2 | ||
| 2000 Jul 31 | 0100? | LAM1 | 765.41 6919 x 35759 x 0.1 |
| 2000 Aug 1 | 1550? | LAM2 | 998.61 17672 x 35760 x 0.1 |
| 2000 Aug 3 | 1730? | LAM3 | 1427.35 35444 x 35786 x 0.1 |
| 2000 Aug 9 | 1436.08 35778 x 35794 x 0.1 GEO 61.5W | ||
| 2000 Aug 30 | mv out | ||
| 2000 Sep 4 | mv in | 1436.18 35786 x 35790 x 0.0 GEO 58.0W | |
| 2006 Jul 31 | 1436.10 35780 x 35792 x 0.0 GEO 58.0W | ||
Monday, June 1, 2009
ATV-1 (Jules Verne)
2008-008A
Launch by Ariane 5ES, a version with the Vulcain 2 based EPC and uprated EAP combined with the Ariane 5G's P2000 EPS, uprated for a second short burn but with a short fuel load of only 5200 kg (formerly known as EPS-V, Versatile EPS). The ATV itself uses R4D engines, already ISS-qualified.
Launch mass 19400 kg. Ariane launch mass 775t. EPS is 1300 kg dry 7500 kg full not including VEB (usually 1370 kg full 1300 kg dry) and 345 kg, 3.94m dia SDM (Separation and Distancing Module) adapter.
Later flights will have a 20750 kg mass and will be delivered to 300 x 300 km. Jules Vernes is spacecraft M8002MS to the TDRS nework.
Propulsion module is EADS-ST/Bremen; Avionics module is EADS-Astrium/Toulouse; cargo module is Thales Alenia/Torino. Overall management is EADS-ST/Les Mureaux. Integration was in Bremen. ATV-CC at CNES Toulouse.
The Automated Transfer Vehicle will fly on a single-stage Ariane 5E. Lead design is Aerospatiale/Les Mureaux (Ae Matra Lanceurs) with DASA/Bremen (Astrium Space Infrastructure) for production. Now EADS LV/ATV Les Mureaux; Arianespace/Evry. Mangement by ESA/MSM. Shell by Alenia Spazio/Torino.
The ATV will fly every 1.5 yr for supply and reboost.
Size is 10.3m long 4.5m dia.Span 22m. Four R-4D-11 490N main engines and 28 (span 18.5 in another source)
On deorbit, ATV can carry 6500 kg of garbage to reentry over the Pacific.
At Feb 2008:
| ATV dry w SDM | 10470 kg | |
| ATV dry no SDM | 10075 kg | |
| ATV prop | 6475 kg | |
| ATV wet no SDM | 16550 kg | |
| JV dry cargo | 1300 kg | |
| JV Water/O2 | 302 kg | |
| JV ISS prop | 860 kg | |
| JV total cargo | 2462 | |
| ATV w/cargo | 19012 kg | |
| SDM | 345 | |
| Reserve? | 50 | |
| ATV w/cargo and SDM | 19407 |
Size 9.79m long 4.48m dia 22.3m span.
Propulsion module by Astrium SI/Bremen includes MON (mixed oxides of Nitrogen)/MMH with 4 x 490N Marquardt R4D engines and RCS with 20 x 220N. Astrium/Lampoldshausen 220N thrusters. Spacecraft structure by Oerlikon Cotraves, integrated cargo carrier by Alenia Spazio.
The Automated Transfer Vehicle is built by DASA/Astrium in production. The first ATV, the Jules Verne ATV, is built at EADS-LV/Les Mureaux. It has 5 R-4D engines.
During phasing, ATV will demo attitude control, GPS navigation, orbit control, and a collision avoidance manuever (CAM).
The EPS deorbit burn occured at 06:28:31 UTC and lasted 16 seconds. It was followed 8 seconds later by a propellant dump. It was then in a direct reentry trajectory that was followed by the Awarua tracking station. Contatc was lost at an altitude of 120 km. The crash into the ocean came a few minutes later. (ESA info via Dan Deak)
At undocking in Sep, ATV arried 900 kg dry waste and 254 kg liquid waste.
| Jules Verne | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2008 Mar 9 | 0403:04 | Vulcain 2 ignition | |
| 0403:11 | T+0:07 Launch by Ariane 5ES-ATV L528 | CSG ELA3 | |
| T+2:19 EAP sep 60.8 km Vrel=2.007 km/s | |||
| T+3:29 Fairing sep, 106.3 km | |||
| 0411:59 | T+8:55 EPC MECO 132 km | -1304 x 139 x 51.24 | |
| 0412:04 | T+9:00 EPC sep 133 km | ||
| 0412:12 | T+9:08 EPS MES-1 9m, 134 km | ||
| 0417? | EPC reentry | ||
| 0420? | EPC impact off coast of Portugal 14.7W | ||
| 0420:17 | T+17:13 EPS MECO-1 146 km | 137 x 260 x 51.6 | |
| 45 min coast | |||
| 0505:14 | T+1:02:10 EPS MES-2 30s 270 km | ||
| 0505:44 | T+1:02:40 EPS MECO-2 | 260 x 260 x 51.6 | |
| 0509:43 | T+1:06:39 EPS sep | ||
| 0509:53 | T+1:06:49 Avoidance burns | ||
| ATV arrays deploy | |||
| 0628:31 | T+2:24:27 EPS MES-3 deorbit | ||
| 0628:47 | T+2:24:43 EPS MECO-3 | ||
| 0648? | EPS reentry over S Pacific | ||
| 0651 | T+2:48 EPS end of mission | ||
| 2008 Mar 11 | 0537 | 89.77 253 x 272 x 51.6 | |
| 2008 Mar 11 | 1501:09 | Main engine burn TE1 6m/s | |
| 1612:39 | Main engine burn TE2 6m/s | ||
| 2052 | 90.18 275 x 291 x 51.6 | ||
| 2008 Mar 12 | 1312:23 | TP1 dV 6m/s | |
| 1401:29 | TP2 dV 6m/s | 90.72 302 x 316 x 51.7 | |
| 2008 Mar 14 | 0757:35 | Collision avoidance test burn CAM, 5.3m/s | |
| burn 2 | |||
| 2008 Mar 18 | Height adjust burn 1 | 90.71 306 x 311 x 51.6 | |
| 2008 Mar 18 | Height adjust burn 2 | ||
| Flyby under ISS at 30 km | 91.16 327 x 335 x 51.6 | ||
| 2008 Mar 19 | 0530:03 | TV2-1 Orbit adjust 2.1m/s | |
| 0615:41 | TV2-2 Orbit adjust 2.1m/s | ||
| 1021:02 | IF1 0.14m/s burn to enter parking pos | ||
| 1106:48 | IF2 0.02m/s | ||
| 1151:04 | IF3 1.32m/s | 91.35 339 x 341 x 51.6 | |
| Parking position 2000 km ahead of ISS | |||
| 2008 Mar 20 | 1313:50s | SK1-1 stationkeeping | |
| 1404:41s | SK1-2 stationkeeping | ||
| 2008 Mar 25 | 91.35 340 x 341 x 51.6 | ||
| 2008 Mar 27 | Move to prep for D-0 | ||
| 2008 Mar 27 | 91.35 340 x 341 x 51.6 | ||
| 2008 Mar 29 | D+0 Demo Day 1 | ||
| 1419 | Prox ops begin at 39km range, 5 km below | ||
| 1557 | At S2 hold point, 3.5km | ||
| Flyby 3.5 km from ISS above Vbar using rel GPS | |||
| 1730 | Escape mvr | ||
| 2008 Mar 29 | 91.00 321 x 325 x 51.6 | ||
| 2008 Mar 31 | Demo day 2 | ||
| D+2d Demo Day 2 | |||
| Begin prox ops at 39 km range, 5 km below | |||
| On Vbar at 250m | |||
| 1550? | Approach at 150 m | ||
| Retreat to 180m | |||
| 1617 | Hold at 19m, S4 hold | ||
| 1638 | Approach to 11m of ISS on Vbar, S41 hold | ||
| 1643 | Retreat to 20m, S4 hold | ||
| 1652 | Escape mvr | ||
| 1702? | Hold at 800m | ||
| 2008 Apr 1 | 0000? | E+7hr TA burn, transfer above ISS | |
| 2008 Apr 1 | 0224 | 91.18 325 x 339 x 51.6 | |
| 1900 | 91.53 348 x 351 x 51.6 | ||
| 2000? | E+27hr TB burn, transfer below ISS | ||
| 2008 Apr 3 | 1119s | S1 hold point, 15.5km | |
| 1205s | S2 hold point, 3.5km | ||
| 1237s | Leave S2 | ||
| 1317s | Arrive at 250m S3 hold | ||
| 1333 | Optical tracking on, 250m range | ||
| 1354s | Resume approach from S3 | ||
| 1415 | 19m, begin hold at S4 | ||
| 1435 | Resume approach from S4 | ||
| 1438 | 11m, S41 hold, final approach | ||
| 1445 | Docking with Zvezda | ||
| 2008 Apr 4 | 1100 | 91.31 338 x 339 x 51.6 | |
| 2008 Apr 21 | ISS orbit raise | ||
| 2008 Jun 19 | 0641 | ISS orbit raise with OCS engines | |
| 2008 Jul 22 | 91.42 337 x 351 x 51.6 | ||
| 2008 Jul 23 | 1618s | ATV burn 1237s | 91.56 344 x 358 x 51.6 |
| 2008 Aug 13 | 0758 | ISS orbit raise with OCS engines | |
| 2008 Aug 27 | 1611 | DAM Burn to avoid K2426 deb, 1m/s | |
| 2008 Sep 5 | 2129 | Undocking | |
| 2130s | Sep-1 burn 4m/s 316s | ||
| 2008 Sep 15 | 91.40 338 x 347 x 51.6 | ||
| 2008 Sep 18 | Orbit lower | 90.74 300 x 321 x 51.6 | |
| 2008 Sep 28 | Orbit raise | ||
| 2008 Sep 29 | 0100 | 91.13 322 x 337 x 51.6 | |
| 2008 Sep 29 | 1000:27 | DO-1 29.8m/s? 6 min | |
| 1258:18 | DO-2 70.3m/s 14:20 | ||
| 1312:38 | DO-2 CO | -11? x 334 x 51.6 | |
| 1331 | Reentry over approx 130W 45S at 120km | ||
| 1335? | Breakup at 75 km | ||
| 1346? | Debris impact Pacific | ||
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