Sunday, December 27, 2009
Thursday, December 24, 2009
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 | ||
Tuesday, December 22, 2009
Monday, December 21, 2009
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 | ||
Sunday, December 20, 2009
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 | ||
Saturday, December 19, 2009
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 | ||
Friday, December 18, 2009
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
Tuesday, December 15, 2009
Monday, December 14, 2009
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 | ||
Saturday, December 5, 2009
Friday, December 4, 2009
DFH-45
1997-029A
The FY-2 weather satellite was launched in Jun 1997 after a long delay caused by the explosion of the first flight model during testing.
The spin-stabilized FY-2 was built by the Shanghai Aerospace Technology Research Institute and had a mass of 1380 kg. It will be stationed at 105E and controlled from the Xi'an control center. The satellite is a 2.1m dia 4.5m high cylinder with antenna deployed and AKM attached. The main bus is 2.1 dia 1.6m high, with antenna but without AKM it is 3.0m high. The FG-36 AKM is a cylinder-cone 1.5m high 1.0m dia and 729 kg full 70? empty, leaving a BOL mass for FY-2 of 651 kg. AKM Burn time is 43s, Isp 289.0. After the AKM fires and is ejected, an imager cover is also ejected into near-GEO.
| FY2 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1997 Jun 10 | 1201 | Launch by CZ-3 | XSC |
| T+2:06 St 1 MECO | |||
| T+2:07 St 2 burn | |||
| T+4:15 St 2 MECO | |||
| T+4:19 Fairing sep | |||
| T+4:22 St 2 VECO | |||
| T+4:23 Stage 3 burn | |||
| 1212 | T+11:08 MECO-1 | ||
| 1216 | T+15:35 MES-1 | ||
| 1221 | T+20:53 Stage 3 MECO-2 | ||
| 1222 | T+21:32 Stage 3 sep | ||
| 1997 Jun 10 | 635.12 206 x 35987 x 28.5 | ||
| 1997 Jun 10 | 141 x 36043 x 27.8 (R/B?) | ||
| 1997 Jun 11 | 0418? | AKM burn | |
| 1997 Jun 11 | 0430? | AKM separated | 1399.72 34099 x 36044 x 0.3 |
| 1997 Jun 11 | 1396.45 34015 x 35998 x 1.3 | ||
| 1997 Jun 11 | 1403.34 34069 x 36216 x 1.3 GEO 114.9E+8.4E | ||
| 1997 Jun 17 | 1436.08 35780 x 35792 x 1.2 GEO 105.0E | ||
| 1997 Jul 10 | 1436.01 35781 x 35788 x 1.1 GEO 104.1E | ||
| 1999 Oct 13 | 1436.09 35784 x 35788 x 0.7 GEO 104.8E | ||
| 2000 Apr 23 | Moved out | 1548.33 35773 x 36278 x 0.1 GEO 104E dr | |
| 2000 May 10 | mv in | GEO 85.5E | |
| 2000 Jun 11 | 1436.15 35767 x 35807 x 0.3 GEO 85.6E | ||
| 2004 Feb 14 | 1436.07 35784 x 35787 x 3.5 GEO 87.2E | ||
Tuesday, December 1, 2009
USA-194
2007-027A
AV-009 Atlas V 401 from SLC41.
3250 kg each?
NOSS launch codenamed 'PYXIS'. The Centaur second burn had a problem and the payload was delivered to a lower than planned orbit; it was expected that on board propulsion would let the mission reach its planned orbit, assumed to be 1150 km x 63 deg.
After the first Centaur burn, a valve failed to close and fuel leaked out during the coast phase, leading to early fuel depletion during the second burn.
The UN-released orbit was 714 x 953 km x 63.3 deg. The 2009 EELV Cape history by M. Cleary spun the issue as 'there was some loss in performance during the second stage burn, but the payload was launched successfully'. Nevertheless the orbit achieved was signicicantly different from the desired one and I count this flight as a launch failure for statistical purposes.
| NROL-30 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2007 Jun 15 | 1512:00 | Launch by Atlas AV-009 | CC SLC41 |
| Ascent on Az 46.85 | |||
| Atlas MECO | |||
| T+4:15? Atlas sep | |||
| T+4:23? Centaur MES-1 | |||
| T+4:38? Fairing | |||
| 1530? | T+18 min? Centaur MECO-1 | ||
| 1629? | T+1:17? Centaur MES-2 | ||
| Centaur premature shutdown | |||
| 1630? | T+1:18? Centaur MECO-2 | 105.22 783 x 1225 x 63.6 | |
| 1634? | T+1:22? Payload sep | ||
| Centaur blowdown | 101.57 715 x 951 63.4 | ||
| 2007 Jun 18 | 105.45 847 x 1183 x 62.7 | ||
| 2007 Aug 11 | 106.08 904 x 1186 x 63.4 | ||
| 2008 Feb 17 | 107.36 997 x 1211 x 63.4 | ||
| 2008 Jun 10 | Orbit raise to operational alt | 107.41 1014 x 1198 x 63.4 | |
| 2009 Apr 26 | 107.42 1033 x 1181 x 63.4 | ||