Tuesday, July 26, 2011
Galaxy 17
2007-016B
By the time of launch, Galaxy 17 was owned by Intelsat. Thales Alenia Space (formerly Alcatel/Cannes) Spacebus 3000B3. Launch 2007; was to replace Galaxy 11 at 91W for video and voice comms in N America. In the event, it was stationed at 74W from 2007 Jul to 2008 Mar, and then moved to 123W.
Mass 4107 kg launch, 1750 kg dry. Size 3.8 x 1.8 x 2.3m with 36.9m span.
| Ariane | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2007 May 5 | 2229 | Launch by Ariane 5ECA L536 | CSG ELA3 |
| T+0:07 Takeoff | |||
| T+2:20 EAP sep 67 km | |||
| T+3:10 Fairing sep, 105 km | |||
| 2237 | T+8:53 EPC MECO 167 km | -1097 x 167 x 6.37 | |
| 2237 | T+8:59 EPC sep | ||
| 2238 | T+9:03 ESC-A burn 167 km | ||
| 2253 | T+24:41 ESC-A MECO, 596 km | ||
| 2256 | T+27:00 Astra 1L sep | ||
| 2258 | T+29:21 Sylda sep | ||
| 2301 | T+32:39 Galaxy 17 sep | ||
| T+44:41 ESC-A passivation | |||
| 2007 May 9 | 631.88 264 x 35763 x 6.0 | ||
| 2007 May 9 | LAM | 1330.67 31579 x 35814 x 0.2 | |
| 2007 May 10 | 1630? | LAM | 1430.68 35540 x 35820 x 0.0 GEO 88.6W+1.4E/d |
| 2007 May 17 | 1435.97 35782 x 35785 x 0.1 | ||
| 2007 May 22 | 1436.15 35786 x 35788 x 0.1 GEO 81.0W | ||
| 2007 Jun 9 | 1436.31 35788 x 35793 x 0.1 GEO 75.5W+0.06/d | ||
| 2007 Jul 13 | 1436.07 35780 x 35791 x 0.1 GEO 74.0W | ||
| 2008 Feb 28 | 1436.12 35775 x 35798 x 0.0 GEO 74.0W | ||
| 2008 Mar 20 | Move out from 74.0W | ||
| 2008 May 7 | Move in at 123W | ||
| 2008 May 14 | 1436.04 35771 x 35799 x 0.05 GEO 122.9W | ||
Thursday, July 21, 2011
SAMPEX
1992-038A
The first SMEX was SAMPEX, the Solar and Anomalous Magnetospheric Particles Explorer. It carried a set of experiments from a team lead by the University of Maryland, and was built in-house at NASA-GSFC.
The 158 kg satellite was a box + 2 panels 0.86m in diameter and 1.5m long. It studied trapped radiation in the magnetosphere, solar flare composition, cosmic rays, and precipitating electrons.
LEICA is a high resolution mass spectrometer for low energy particles in an approximate range of 0.2-10 MeV/nucleon. MAST measures isotopic composition with a mass resolution of 0.3 amu in the 15-300 MeV/nucleon range; PET measures H and alpha in the same range and electrons in 0.4-30 MeV. HILT detects particles in the 10-200 MeV/nucleon range.
Launch was at 1419 on 1992 Jul 3 by Scout S215C from Space Launch Complex 5 at Vandenberg AFB into a 550 x 657 km x 82 deg orbit. SAMPEX was still operating in 1994. POCC was at GSFC with a Science Ops Center at Maryland. In 2010, SAMPEX was being operated by the Bowie State control center in Maryland.
| SAMPEX | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1992 Jul 3 | 1419 | Launch by Scout | SLC5 |
| T+1:24 Stage 1 burnout | |||
| T+1:28 St 1 sep | |||
| T+1:28 St 2 burn | |||
| T+2:09 St 2 burnout | |||
| T+2:20 Fairing sep | |||
| T+2:22 St 2 sep, St 3 burn | |||
| T+3:10 St 3 burnout | |||
| T+9:54 St 3 sep | |||
| 1429 | T+9:59 St 4 burn | ||
| 1429 | T+10:32 Stage 4 burnout | ||
| 1430 | T+11:36 Stage 4 sep | ||
| 1434 | T+14:56 SAMPEX Yo-yo despin | ||
| 1997 Oct | SAMPEX control to Bowie, MD | ||
| 2004 Jun 30 | end of sci ops | ||
| 2004 Dec 27 | Observed large X-ray flare | ||
| 2005 Jan 20 | Observed GLE event | ||
| 2005 Mar | Still operational | ||
| 2010 Aug | Still operational | ||
Wednesday, July 20, 2011
Galaxy 4R
2000-020A
HS-601HP satellite to replace Galaxy 4 at 99W. Distribute video and comms and broadband internet pipe. Galaxy 6, 7 and 11 will relocate.
Galaxy 4R developed XIPS engine problems in June 2003. It was retired in 2009.
Launch mass is 3668 kg, BOL 2216, dry mass 1895 kg. Size is 4.0 x 3.6 x 2.7m, 26m span.
| Galaxy IV-R | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2000 Apr 19 | 0029 | Launch by Ariane 42L V129 | CSG ELA2 |
| T+2:20 PAL sep | |||
| T+3:14 St 1 sep | |||
| T+3:17 St 2 burn | |||
| T+4:05 Fairing sep | |||
| T+5:26 St 2 sep | |||
| T+5:31 St 3 burn | |||
| 0047 | T+18:40 St 3 MECO | ||
| 0050 | T+20:48 St 3 sep | ||
| T+20:52 St 3 avoidance maneuver | |||
| T+22:37 end of V129 mission | |||
| 219 x 32007 x 7.0 | |||
| 2000 Apr 19 | 559.49 219 x 32007 x 7.0 | ||
| 2000 Apr 20? | LAM-1 | ||
| 2000 Apr 21 | 566.40 587 x 32009 x 7.0 | ||
| 2000 Apr 23? | LAM-2 | ||
| 2000 Apr 24 | 740.30 5683 x 35776 x 4.2 | ||
| 2000 Apr 25 | 1600? | LAM-3 | |
| 2000 Apr 27 | 1435.70 35765 x 35792 x 0.1 GEO 67.4W+0.05W | ||
| 2000 May 1 | GEO 67W | ||
| 2000 May 26 | 1436.09 35785 x 35787 x 0.0 GEO 73.0W | ||
| 2000 Jun | Move to 99W | ||
| 2000 Jun 25 | 1436.09 35785 x 35787 x 0.0 GEO 99.0W | ||
| 2000 Oct 18 | 1436.10 35785 x 35787 x 0.0 GEO 99.0W | ||
| 2003 Jul 3 | 1436.11 35773 x 35799 x 0.0 GEO 99.0W | ||
| 2006 Aug 4 | 1436.04 35780 x 35790 x 0.0 GEO 99.0W | ||
| 2006 Sep | Move to 77W | ||
| 2006 Oct 2 | 1436.06 35777 x 35794 x 0.1 GEO 76.8W | ||
| 2009 Mar 29 | 1436.11 35773 x 35799 x 2.5 GEO 76.9W | ||
Radarsat 1
1995-059A
The CSA's Radarsat was built by Spar Aerospace. The 4.2m long, 2.8m wide spacecraft bus, built by Ball and based on the RME satellite, carried a large solar array and a 15 x 1.5m C-band synthetic aperture radar. It had a mass of 2750 kg. The radar has a 500 km swath width and can be steered electronically, with a fine (8-m resolution) 50 x 50 km area mode and a scan (100 m resolution) 500 x 500 km mode. It is intended to image the Arctic region and Canada, and will also improve maps of the Antarctic. 15 percent of the observing time is allocated to the US in return for the launch. Radarsat is to be operated by the Canadian Space Agency from the Radarsat Control Center at St Hubert, Quebec. Radarsat was launched into a 6am/6pm sun-synchronous orbit for continuous solar array illumination.
In Sep 1997 the satellite was flipped in orientation (yaw) to begin the Antarctic-1 mapping mission, imaging to the left of the satellite track.
The MDA company operates Radarsat. The Dept. Foreign Affairs and the military DND does tasking for surveillance to MDA; commercial tasking is done directly by MDA, while civil tasking is sent to MDA by CSA.
Payload:
- C-band 1.5 x 15m SAR radar, 5.3 GHz
| Radarsat | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1995 Nov 4 | 1422 | Launch by Delta 7920-10 | V SLC2W |
| SRM 1-9 sep | |||
| 1426 | Stage 1 sep | ||
| 1426 | Delta stage 2 burn | ||
| 1427 | Type 10 fairing sep | ||
| 1432? | Delta stage 2 cutoff | 190? x 784 x 98.6 | |
| 1523? | Delta stage 2 MES2 | ||
| Delta stage 2 MECO2 | |||
| 1526 | Delta stage 2 sep | ||
| 1552 | Solar array deploy | ||
| 1615 | SAR begin deploy | ||
| 1995 Nov 4 | 100.57 783 x 787 x 98.6 | ||
| 1995 Nov 4 | 1540? | Delta SES-3 | |
| SECO-3 | 786 x 1462 x 98.6 | ||
| 1995 Nov 4 | 1608? | Delta SES-4 | |
| Delta/SURFSAT SECO-4 | 934 x 1494 x 100.64 | ||
| 1995 Nov 7 | 100.57 783 x 787x 98.6 | ||
| 1995 Nov 15 | Begin orbit adjust | ||
| 1995 Dec 16 | In operational orbit | ||
| 1995 Dec 16 | 100.70 791 x 792 x 98.6 | ||
| 1997 Sep 9 | Reorient satellite | ||
| 1997 Sep 11 | Begin Antarctic-1 mission (AMM) | ||
| 2002 Nov | safemode, AOCS problem | ||
| 2002 Dec 24 | Resume ops | ||
| 2011 Mar 31 | 100.70 791 x 792 x 98.6 | ||
Tuesday, July 19, 2011
GSAT-2
2003-018A
GSAT-2 launch mass was 1823 kg, 840 kg dry. Prop was MMH/MON-3. Size 2.4 x 1.6 x 1.5m with 9.6m span. Launch 2003 May by GSLV-D2 into GTO; LAM to GEO at 48E.
D2 had 10t of extra prop in stage 1, and improved strapon and stage 2 engines. Mass 414t at launch. The S139 first stage has four L40H strapons. GS2 is 11.6l 2.8d with 39.3t prop of UH25/N2O4 and 804 kN thrust. GS3 is cryo, 8.7l 2.9dia. The payload adapter was also made lighter, for a total gain of 485 kg; the lower-than-design Isp of the 12KRB represented a loss of 200 kg.
Launch from SDSC-SHAR (Satish Dhawan Space Center). Azimuth 104 deg.
The satellite carried SOXS, a solar X-ray spectrometer.
| GSAT 2 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2003 May 8 | 1128 | Launch by GSLV D2 | |
| T-4.8s L40H ignite | |||
| T+0:0 S139 ignite | |||
| T+1:47 S139 burnout | |||
| T+2:29 L40H burnout 69km | |||
| T+2:30? GS-2 MES | |||
| T+2:33? S139 sep | |||
| T+3:48? Fairing sep | |||
| T+4:46? GS-2 MECO | |||
| T+4:50 GS-2 sep 131 km | |||
| 1132 | T+4:50 GS-3 burn 11:45 5.4 km/s | ||
| 1144 | T+16:35? GS-3 MECO | ||
| 1144 | T+16:37 GS3 sep 198 km | 180 x 36000 | |
| 2003 May 9 | LAM-1 | 8850 x 36000 x 7.4 | |
| 2003 May 9 | 801.1 8826 x 35562 x 7.4 | ||
| 2003 May 10 | 0600 | LAM-2 41min | 1384.0 34000 x 36000 x 0.3 |
| 2003 May 11 | 0520 | LAM 79s | |
| 2003 May 11 | 1436.81 33601 x 37999 x 0.3 | ||
| 2003 May 12 | Solar array deploy | ||
| 2003 May 23 | 1436.13 35782 x 35791 x 0.0 GEO 48.0E | ||
| 2003 May 27 | 1436.11 35783 x 35790 x 0.0 GEO 48.0E | ||
| 2003 Dec 19 | 1436.15 35713 x 35861 x 0.1 GEO 48.0E | ||
| 2004 Feb 11 | 1436.08 35775 x 35797 x 0.0 GEO 48.0E | ||
| 2011 May 4 | 1436.00 35767 x 35802 x 0.4 GEO 48.1E | ||
Monday, July 18, 2011
IceSat
2003-002A
EOS Laser ALT-1, or ICESAT (Ice, Cloud and Land Elevation Satellite), launched to 705 x 705 x 94. ICESAT is built by Ball Aerospace/Boulder under an IDIQ contract with the BCP-2000 (Ball Commercial Platform) bus. ICESAT will study the Greenland and Antarctice ice sheets.
The 300 kg ICESAT is mounted on the RH-DPAF (Reduced Height Dual Payload Attach Fitting) containing CHIPSAT. RH-DPAF consists of an upper cone/cylinder and a lower cone.
The GLAS lidar instrument is a 1-m telescope with a ND-YAG 0.5 and 1 micron laser. ICESAT is 3.1m tall, 1.9m in dia, with two 2.1 x 2.3m solar panels for an approx 6.5m span.
The first of ICESAT's 3 lasers failed after only 36 days due to a solder contamination problem. A second laser was activated in Sep 2003.
| ICESAT | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2003 Jan 13 | 0045:00 | Launch by Delta 7320-10 | V SLC2W |
| T+1:04 SRM1-3 burnout | |||
| T+1:39 SRM 1-3 sep 32 km | -6350 x 35? | ||
| T+4:24 MECO | |||
| T+4:32 St 1 sep | |||
| T+4:37 SES-1 121 km 4.830 km/s | -4900 x 150? | ||
| T+4:57 Fairing 135 km 4.892 km/s | -4830 x 170 ? | ||
| 0056:05 | T+11:05 SECO-1 | 185 x 597 x 93.96 | |
| 0144:50 | T+59:50 SES-2 | ||
| 0144:58 | T+59:58 SECO-2 | ||
| 0149:00 | T+1:04:00 Icesat sep | 585 x 591 x 94.0 | |
| 0205:00 | T+1:20:00 RH DPAF sep | 559 x 585 x 94.0 | |
| 0208:20 | T+1:23:20 Chipsat sep | 559 x 585 x 94.0 | |
| T+1:26:40 Stage 2 retro | |||
| T+1:46:40 SES-3 evasive | 561 x 583 x 94.0 | ||
| T+1:46:45 SECO-3 | 498 x 585 x 94.84 | ||
| T+2:06:40 SES-4 depletion | |||
| T+2:07:16 SECO-4 depletion | 198 x 546 x 97.30 | ||
| 2003 Jan 13 | 96.40 578 x 593 x 94.0 | ||
| 2003 Jan 20 | 96.39 577 x 593 x 94.0 | ||
| 2003 Jan 23 | 96.40 578 x 593 x 94.0 | ||
| 2214 | orbit raise | 96.50 584 x 598 x 94.0 | |
| 2003 Jan 26 | orbit raise | 96.59 588 x 602 x 94.0 | |
| 2003 Feb 8 | 96.61 590 x 601 x 94.0 | ||
| 2003 Feb 20 | GLAS turned on | ||
| 2003 Mar 12 | 96.61 594 x 598 x 94.0 | ||
| 2003 Mar 28 | GLAS laser failed (1 of 3), science suspended | ||
| 2003 Jul 2 | 96.61 594 x 598 x 94.0 | ||
| 2003 Sep 25 | Laser 2 activated | ||
| 2009 Apr | End of primary mission? | ||
| 2009 Oct 11 | Laser 3 failed, end of science data | ||
| 2010 Feb 24 | Attempts to restart lasers abandoned | ||
| 2010 Feb 24 | Decommissioning phase | ||
| 2010 Jun 23 | 96.59 592 x 597 x 94.0 | ||
| 2010 Jun 24 | Lower orbit | 96.33 572 x 593 x 94.0 | |
| 2010 Jul 1 | 96.33 572 x 593 x 94.0 | ||
| 2010 Jul 7 | 95.65 509 x 591 x 94.0 | ||
| 2010 Jul 8 | Lower orbit | 94.32 410 x 561 x 94.1 | |
| 2010 Jul 12 | Lower orbit | 93.08 265 x 584 x 94.0 | |
| 2010 Jul 15 | Lower orbit | 92.38 200 x 581 x 94.0 | |
| 2010 Aug 12 | 90.81 192 x 436 x 94.0 | ||
| 2010 Aug 30 | 87.16 128 x 139 x 94.0 | ||
| 2010 Aug 30 | Reentered over Barents Sea | ||
Payload:
- GLAS Geoscience Laser altimeter System, GSFC
Friday, July 15, 2011
Thor 3
1998-035A
Thor III is an HS376HP to be colocated at the Nordic Hot Bird position of 1W with other Thor satellites belonging to Telenor AS/Oslo. Launch was Jun 1998 by Delta 7925 with a 9.5 foot fairing. It will broadcast DTH to Nordic countries, and central and eastern Europe. The satellite has 1400W generated by GaAs solar cells. Hughes delivered the satellite on orbit to Telenor.
Launch mass was 1451 kg. Size is 2.16m dia, 3.32m high stowed, 7.76m high deployed. The mission used a 'Thor 2A DTO' boost trajectory, with three Delta stage 2 burns to a high perigee geostationary transfer orbit.
| Thor 3 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1998 Jun 10 | 0035:00 | Launch by Delta 7925 (D258) | CC LC17A |
| 0036 | T+1:06 SRM 1-6 sep | ||
| 0037 | T+2:11 SRM 7-9 sep 52 km | ||
| 0039 | T+4:23 MECO 113 km | ||
| 0039 | T+4:36 Stage 2 burn 123 km | ||
| 0039 | T+4:57 Fairing sep | ||
| 0044 | T+9:57 SECO-1 | 87.81 157 x 174 x 29.21 | |
| 0057 | T+22:12 Stage 2 burn | ||
| 0058 | T+23:02 SECO-2 | 100.86 157 x 1440 x 28.17 | |
| 0144 | T+1:09:30 Stage 2 burn | ||
| 0145 | T+1:10:22 SECO-3 | 116.18 1365 x 1652 x 26.68 | |
| 0146 | T+1:11:15 Stage 2 sep | ||
| 0146 | T+1:11:52 Stage 3 burn | ||
| 0148 | T+1:13:19 TECO | 680.11 1426 x 37053 x 20.29 | |
| 0150 | T+1:15:12 Stage 3 sep | 680.05 1426 x 37049 x 20.29 | |
| 0221 | Stage 2 depletion burn | ||
| 0224 | SECO-4 | 111.28 891 x 1680 x 26.4 | |
| 1998 Jun 10 | 683.65 1416 x 37241 x 19.2 | ||
| 1998 Jun 12 | 0440? | Star 30 burn | |
| 1998 Jun 15 | 1422.29 34863 x 36168 x 0.1 GEO 60.2W+3.4E | ||
| 1998 Jun 20 | 1422.36 34869 x 36165 x 0.1 GEO 45.0W+3.4E | ||
| 1998 Jul 8 | 1426.67 35413 x 35790 x 0.2 GEO 1.0W+2.4E | ||
| 1998 Jul 17 | 1436.07 35753 x 35818 x 0.1 GEO 0.9W | ||
| 1999 Mar 9 | 1436.07 35778 x 35793 x 0.0 GEO 0.9W | ||
| 1999 Oct 14 | 1436.07 35780 x 35791 x 0.0 GEO 0.8W | ||
| 2006 Aug 1 | 1436.07 35777 x 35794 x 0.0 GEO 0.9W | ||
| 2010 Jun 7 | 1436.08 35776 x 35795 x 0.2 GEO 0.6W | ||
Tuesday, July 12, 2011
STS-104 (Atlantis)
2001-028A
Transfer of Atlantis to the VAB was delayed while the tiles were dried out; they had been soaked while at Edwards and moisture was still trapped almost three months later. Problems on orbit with the SSRMS delayed the launch further.
Launch mass is 117127 kg (press kit). OMS 2 mass is 116074 kg. Pre docking mass is 111066 kg. Docked mass with ISS is 231515 kg. Post undocking mass is 100606 kg, post sep 100572 kg. OV launch mass 117127 kg. Airlock 6063 kg. Landing mass 94007 kg.
The astronauts removed thermal covers from Quest. They returned to the airlock briefly while it was unberthed, but then emerged again to go to Unity to monitor its installation.
| STS-104 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2001 May 28 | Transfer from OPF/3 to VAB | ||
| 2001 Jun 4 | Mate to ET in VAB/1 | ||
| 2001 Jun 20 | Rollout aborted | ||
| 2001 Jun 21 | Rollout to LC39B | ||
| 2001 Jul 12 | 0903:59 | Launch from KSC | |
| 0906:02 | SRB sep | ||
| 0912:25 | MECO | ||
| 0912:44 | ET sep | 87.44 59 x 235 x 51.6 | |
| 0942:31 | T+38:29 OMS-2 1:05 29m/s | 88.41 155 x 235 x 51.6 | |
| 0943:36 | OMS-2 CO | ||
| 1045:12 | PLBD open | ||
| 1238:59 | OMS-3 NC1 burn 93s 43.2m/s | ||
| 1240:33 | OMS-3 CO | ||
| 1755 | 232 x 305 x 51.6 | ||
| 2001 Jul 13 | 0015:02 | OMS-4 R NC2 burn 2.4m/s 10.4s | 89.89 232 x 305 x 51.6 |
| 0015:12 | OMS-4 CO | ||
| 0159 | RMS checkout | ||
| 0612s | NPC burn? | 89.96 237 x 307 x 51.6 | |
| 1012:50 | OMS-5 NC3 burn 77s 37.0m/s | 91.27 288 x 385 x 51.6 | |
| 1014:08 | OMS-5 CO | ||
| 2216 | NH burn | ||
| 2301:22 | OMS-6 NC4 burn 112058 kg 39s 18m/s | ||
| 2302:00 | OMS-6 CO | ||
| 2335:37 | tweak 3.5s 0.2m/s | ||
| 2001 Jul 14 | 0033:18 | OMS-7 L TI burn 13s 3m/s | 349 x 385 x 51.6 |
| 0033:31 | OMS-7 CO | ||
| 0053:07 | MC1 0.4s 0.03m/s | ||
| 0123:12 | MC2 1.0s 0.06m/s | ||
| 0140:14 | MC3 0.5s 0.06m/s | ||
| 0150:11 | MC4 11.6s 0.8m/s | 363 x 386 x 51.6 | |
| 0205 | 180m on -Rbar | ||
| 0218 | On V-bar at 116m | ||
| 0226 | Approaching at 85m | ||
| 0303 | 10m approach | ||
| 0308 | Docking with PMA-2 | ||
| 0323 | Hard dock | ||
| 0500 | Hatch open to ISS | 92.04 363 x 386 x 51.6 | |
| 1000? | RMS and SSRMS joint rehearsal | ||
| 2001 Jul 15 | EVA-1 EV1 Gernhardt, EV2 Reilly | ||
| 0113? | RMS uncradle | ||
| 0149? | RMS near EAL (PAD install pos) | ||
| 0257? | Begin depress | ||
| 0300 | Leak check | ||
| 0302 | Resume depress | ||
| 0305 | Almost at vacuum | ||
| 0306? | Depress complete | ||
| 0307 | Go for Open hatch | ||
| 0310 | Battery power | ||
| 0318 | TC open | ||
| 0319 | Egress EV1 | ||
| 0324 | Egress EV2 | ||
| 0449 | SSRMS grapple Quest | ||
| 0500? | Ingress | ||
| 0510 | SSRMS unberth Quest | ||
| 0512 | TC closed | ||
| 0520? | Egress | ||
| 0622 | Quest at preinstall position | ||
| 0720 | Quest contact with Unity | ||
| 0731 | Quest ready-to-latch on Unity CBM | ||
| 0734 | First-stage capture | ||
| 0740 | Second stage capture; Bolted to Unity | ||
| 0750 | Bolt loading complete | ||
| 0814 | SSRMS Ungrapple Quest | ||
| 0848 | Near ingress? | ||
| 0853 | Ingress EV2? | ||
| 0858 | TC closed | ||
| 0859? | HC | ||
| 0912 | Repress | ||
| 1359 | 92.04 363 x 386 x 51.6 | ||
| 2001 Jul 16 | 0118 | Reboost-1 1hr 2.1m/s | |
| 2001 Jul 17 | 2200 | 92.10 366 x 388 x 51.6 | |
| 2001 Jul 18 | EVA-2 | ||
| SSRMS ready to grapple O2 Tank 1 (Port aft) | |||
| 0252 | Begin depress | ||
| 0302 | Depressurized | ||
| 0303 | HO | ||
| 0304 | Begin EVA | ||
| 0310 | Egress EV1 | ||
| 0317 | SSRMS grapple O2-1 | ||
| 0328 | O2-1 unberth | ||
| O2-1 on Quest nadir | |||
| 0419 | SSRMS ungrapple O2 Tank-0001, manual grasp by EV-1/EV-2 | ||
| 0421 | O2-1 installed on Quest | ||
| 0528 | SSRMS grapple N2 Tank-0004 (Stbd Aft) | ||
| 0539? | SSRMS unberth N2-0004. | ||
| 0635 | EV1/2 manual grapple N2-4 | ||
| 0638 | SSRMS ungrapple N2-4 | ||
| 0639 | N2-4 docked on Quest | ||
| O2 Tank-0002 (Port Fwd) | |||
| 0752 | SSRMS grapple O2-2 | ||
| 0800 | Unberth O2-2 | ||
| 0844 | SSRMS ungrapple O2-2 | ||
| 0845 | O2-2 docked on Quest | ||
| 0921 | Ingress | ||
| 0925 | TC closed | ||
| 0927 | HC | ||
| 0933 | Repress | ||
| 0959:12 | Reboost-2 1hr 2.1m/s | ||
| 2001 Jul 19 | 0735:04 | Reboost-3 1hr 4.5m/s | |
| 1028 | 92.34 379 x 398 x 51.6 | ||
| 2001 Jul 20 | EVA-3 | ||
| 0112 | Resume EL depress from 11.8psi to 10.2 psi | ||
| Crew in suits (EV1 on Safer 4) | |||
| Repress EL and open EL hatch to Unity | |||
| 0320 | Crew to CL | ||
| 0329 | Begin CL depress | ||
| 0340 | 5 psi | ||
| 0350 | SSRMS Ready to grapple N2-3 | ||
| 0355 | Resume CL depress | ||
| 0405 | SSRMS grapple N2-3 | ||
| 0414 | CL at 1 psi | ||
| 0427 | 0.53psi; TC is open already | ||
| 0433 | 0.51psi | ||
| 0434 | HO | ||
| 0435 | Battery power | ||
| 0440 | EV1 egress | ||
| 0441 | EV2 egress | ||
| 0500 | N2-3 unberth | ||
| 0606 | N2-3 ungrapple to manual | ||
| 0608 | N2-3 berth on Quest | ||
| 0730 | Climb P6 to inspect FPP, SAW | ||
| 0812 | Ingress EV2 | ||
| 0828 | Ingress EV1 | ||
| 0830 | TC closed | ||
| 0832 | HC | ||
| 0837 | Repress | ||
| 2001 Jul 22 | 0225 | Crew leaves ISS | |
| 0252 | Hatch closed to ISS | ||
| 0454:17 | Undocking on vbar | ||
| At 150m on +Vbar | |||
| 0510? | Flyaround | ||
| 0530 | On +Rbar | ||
| 0543 | On -Vbar | ||
| 0550? | On -Rbar | ||
| 0605? | On +Vbar | ||
| 0615:36 | Sep on +Rbar 1m/s 11s | 92.30 378 x 395 x 51.6 | |
| 2001 Jul 24 | 0055 | PLBD closed | |
| 0319 | DO waveoff of first opp | ||
| PLBD open | |||
| 92.29 378 x 395 x 51.6 | |||
| 2001 Jul 25 | 0001 | PLBD closed | |
| 0231:35 | OMS DO 4:17 142 m/s | ||
| 0235:46 | OMS DO complete | 87.45 -98 x 394 x 51.6 | |
| 0307:09 | Entry interface | ||
| 0338:55 | MGTD KSC RW15 | ||
| 0339:10 | NGTD | ||
| 0340:38 | Wheels stop | ||
| 0930 | Tow to OPF/2 | ||
Saturday, July 9, 2011
JCSAT-4
1997-007A
JCSAT 4 is an HS-601 satellite, for 124 E. By 2004 it was a backup spacecraft, JCSAT-R. It has four octagonal antennas and two solar panel wings. 12 C-band and 8 Ku-band/36 MHz,34W 16 Kuband /27MHz, 60W Control center Yokohama, backup station in Gunma. The satellite was built by HSCII Hughes Space and Comms Intl Inc, subsidiary of HSCS Hughes Space and Comms Co, unit of Hughes Electronics Corp.
| JCSAT 4 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1997 Feb 17 | 0142:02 | Launch by Atlas IIAS (AC-127) | CC LC36B |
| 0144:45 | BECO T+2:43 | ||
| 0144:48 | Booster sep T+2:46 | ||
| 0145:28 | Fairing sep T+3:26 | ||
| SECO | |||
| 0146:57 | Atlas sep T+4:55 | ||
| 0147:14 | Centaur TIG1 T+5:12 | ||
| 0151:40 | Centaur MECO1 T+9:38 | 155 x 374 x 28.0 (s) | |
| 0206:26 | Centaur TIG2 T+24:24 | ||
| 0208:14 | Centaur MECO2 T+26:12 | 224 x 94476 x 23.2 | |
| 0211:55 | Centaur sep T+29:53 | ||
| 0242:19 | Centaur depletion | 225 x 94483 x 23.2 | |
| 1997 Feb 16 | 2058.95 221 x 94244 x 23.5 | ||
| 1997 Feb 19 | 0530? | LAM-1 over 124E at apogee | |
| 1997 Feb 19 | 2473.56 14243 x 94173 x 6.3 | ||
| 1997 Feb 22 | 1700? | LAM-2 over 53W at apogee | |
| 1997 Feb 22 | 3148.37 34998 x 94559 x 1.4 | ||
| 1997 Mar 2 | 1100? | LAM-3 over 100W at perigee | |
| 1997 Mar 2 | 1664.20 35777 x 44504 x 0.4 | ||
| 1997 Mar 4 | 1500? | LAM-4 over 143E at perigee | |
| 1997 Mar 4 | 1458.68 35784 x 36670 x 0.1 GEO 143.7E+5.5W | ||
| 1997 Mar 7 | 1436.12 35770 x 35803 x 0.1 GEO 140.3E | ||
| 1997 Apr 21 | 1436.36 35779 x 35804 x 0.1 GEO 139.9E | ||
| 1997 Apr | Move to 150E | ||
| 1997 May 5 | 1436.11 35783 x 35790 x 0.1 GEO 150.0E | ||
| 1997 Jul 25 | 1436.22 35778 x 35800 x 0.2 GEO 149.4E | ||
| 1998 Jan | GEO 150E | ||
| 1998 Mar 18 | 1436.14 35786 x 35789 x 0.0 GEO 150.0E | ||
| 1998 Apr 28 | 1436.16 35775 x 35800 x 0.0 GEO 150.0E | ||
| 1998 May | Replace JCSAT 1 | GEO 124E | |
| 1998 Jun 2 | 1436.22 35781 x 35796 x 0.0 GEO 124.0E | ||
| 1998 Aug 19 | 1436.15 35777 x 35798 x 0.0 GEO 124.0E | ||
| 1999 Jun 14 | 1436.14 35783 x 35791 x 0.0 GEO 124.0E | ||
| 1999 Jun | Move to 127E | ||
| 1999 Jul 29 | 1436.13 35777 x 35797 x 0.0 GEO 127.0E | ||
| 1999 Oct 17 | 1436.10 35779 x 35794 x 0.0 GEO 127.1E | ||
| 2005 Jan 16 | 1436.11 35781 x 35792 x 0.0 GEO 127.5E | ||
| 2005 Jan 17 | mv out | ||
| 2005 Feb 2 | 1438.70 35834 x 35840 x 0.0 GEO 148.7E+0.6W/d | ||
| 2005 | Moved to replace JCSAT 1R | ||
| 2006 Aug 1 | 1436.13 35778 x 35795 x 0.0 GEO 150.0E | ||
| 2009 Aug 19 | 1436.13 35778 x 35795 x 0.0 GEO 150.0E | ||
| 2009 Aug 31? | Move out | ||
| 2009 Aug?? | Renamed Intelsat IS-26 | ||
| 2009 Sep 1 | move in at 127.5E | ||
| 2009 Sep 12 | 1436.11 35775 x 35798 x 1.7 GEO 127.5E | ||
| 2009 Dec 29 | 1436.18 35778 x 35798 x 2.0 GEO 127.4E | ||