Wednesday, September 29, 2010
Saturday, September 25, 2010
Wednesday, September 22, 2010
Friday, September 17, 2010
GOES-10
1997-019A
GOES K was launched in Apr 1997 on the final Atlas I Centaur and renamed NOAA GOES 10. Mass was 2100 kg. GOES 10 was placed in on orbit storage as an operational spare. The plan was to spin-stabilize it while in storage. A solar panel drive failure in Jun 1997 threatened the mission, but operating it in reverse (and flipping the whole satellite) fixed the problem, at the cost of rewriting the ground analysis software.
| GOES 10 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1997 Apr 25 | 0549 | Launch by AC-79 | CC LC36B |
| 0551 | BECO T+2:36 | ||
| 0551 | Booster sep T+2:39 | ||
| 0552 | Fairing sep T+3:36 | ||
| Atlas SECO | |||
| 0553 | Atlas sep T+4:27 | ||
| 0553 | Centaur TIG1 T+4:49 | ||
| 0559 | Centaur MECO1 T+10:03 | 148 x 407 x 28.4 (s) | |
| 0613 | Centaur TIG2 | ||
| 0614 | Centaur MECO2 | ||
| 0618 | Centaur sep | 757.57 167 x 42131 x 27.0 (A) | |
| 0642 | Centaur depletion | 751.80 136 x 41883 x 27.1 (B) | |
| 0710 | Solar panel deploy begins | ||
| 1997 Apr 25 | 757.9 140 x 42175 x 27.1 | ||
| 1997 Apr 27 | 0200? | LAM1 | |
| 1997 Apr 27 | Intermediate? | 850.38 4503 x 42205 x 27.6 | |
| 1997 Apr 27 | 991.84 10909 x 42224 x 8.1 | ||
| 1997 Apr 29 | 2030? | LAM2 over 44W | |
| 1997 Apr 30 | 1409.68 28230 x 42305 x 1.1 | ||
| 1997 May 1 | 1930? | LAM3 over 30W | |
| 1997 May 1 | 1607.36 35593 x 42257 x 0.5 | ||
| 1997 May 3 | 1330? | LAM4 over 103W | |
| 1997 May 4 | 1436.94 35596 x 36010 x 0.5 | ||
| 1997 May 8 | 1437.70 35615 x 36020 x 0.4 GEO 104.4W+0.4W | ||
| 1997 May 13 | 1436.16 35772 x 35803 x 0.4 GEO 105.1W | ||
| 1997 Jun | Solar panel drive failed | ||
| 1997 Jul 31 | Spacecraft rotated 180 deg | ||
| 1998 May 2 | 1436.00 35769 x 35800 x 0.3 GEO 104.6W | ||
| 1998 Jun 5 | GOES 10 turned over to NOAA | ||
| 1998 Jul 9 | Activated | GEO 105W | |
| 1998 Jul 20 | 1435.93 35772 x 35794 x 0.4 GEO 103.8W | ||
| 1998 Jul 26 | mv out | 1440.03 35794 x 35932 x 0.4 | |
| 1998 Sep 14 | mv in | 1436.20 35778 x 35799 x 0.3 GEO 135.1W | |
| 1999 Oct 17 | 1436.00 35774 x 35794 x 0.2 GEO 135.2W | ||
| 2006 Jun 29 | 1435.95 35774 x 35793 x 0.9 GEO 134.5W | ||
| 2006 Jun 30 | move out | ||
| 2006 Aug 4 | 1435.01 35759 x 35771 x 1.0 GEO 125.5W+0.3E/d | ||
| 2006 Dec 4 | Arrived at 60W | ||
| 2007 Oct 11 | 1436.18 35764 x 35812 x 2.1 GEO 59.6W | ||
| 2009 Jun | S American imaging support | ||
| 2009 Nov 30 | 1436.25 35772 x 35806 x 4.0 GEO 60.4W | ||
Thursday, September 16, 2010
HETE-2
2000-061A
The HETE-2 gamma ray burst locator satellite was funded to replace the original HETE lost in a launch failure. It replaced the UV sensor with an extra soft X-ray imager, following the discovery by BeppoSAX of X-ray afterglows to gamma ray bursts. HETE-2 is built by MIT rather than AeroAstro, using left over HETE parts. The ground network is a series of small terminals across the world, which relay data back to MIT. MIT operates the satellite; management is GSFC.
HETE-2 was staged from KMR on Pegasus mission P-35. The Pegasus H (Hybrid) has standard stages 1 and 2, with XL's stage 3 and avionics. Takeoff from PKWA (Bucholz Army Airfield) RW 06/24, at 08 42.9N 167 43.6E. Drop point is 7.65N 167.7E; azimuth is 118.45 deg, altitude 11.9km.
Launch control was remotely from CCAFS Hangar AE.
Mass is 124 kg. Size is about 1.0h 0.5d 2.5 span. Resolution 10' to 10".
In Dec 2005 NASA stopped funding but MIT continued operating the satellite.
| HETE 2 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2000 Oct 9 | 0440 | TO from PKWA | |
| 0538:18 | Drop Pegasus P-35 | ||
| 0538:23 | Ignition | ||
| T+1:21 St 1 burnout | |||
| T+1:30 St 1 sep | |||
| T+2:10 fairing sep | |||
| T+2:49 St 2 burnout | |||
| 527 s coast | |||
| T+8:58 St 2 sep | |||
| 0547:32 | T+9:09 St 3 burn | ||
| 0548:39 | T+10:16 St 3 burnout | ||
| 0550:34 | T+11:16 Stage 3 sep | ||
| Orbit | 600 x 600 x 2 | ||
| 2000 Oct 10 | 97.02 595 x 636 x 1.95 | ||
| 2005 Dec | Control transfer to NASA | ||
| 2007 Mar 28 | Still operational, sporadic ops | ||
| 2009? | end of operations | ||
| 2010 Aug 30 | 96.24 561 x 594 x 1.95 | ||
Payload:
- FREGATE French Gamma Telescope, Lilas-derived Omnidirectional gamma ray spectrometer, 2 sr resolution, 6-400 keV
- WFXM Wide field X-ray monitor, coded mask 2-25 keV
- SXC Soft XR imagers, 2; 33" resolution
Wednesday, September 8, 2010
STS-106 (Atlantis)
2000-053A
STS-106 launch mass is 115257 kg; landing mass is 100366 kg. At TI, orbiter mass was 112261 kg; after undocking 105536 kg. The loaded ICC is 2054 kg (1300 kg of cargo) and the Spacehab is 8200 kg.
2449 kg of cargo including 354 kg of water were transferred to ISS. 430 kg were returned from ISS. Of this, 1995 kg up and 358 kg down were in Spacehab, so 364 kg + 90 kg EVA from STS to ISS, 72 from ISS to STS. 590 kg of cargo were transferred from Progress to ISS. About 90 kg of equipment was installed by EVA, Spacehab mass without up cargo is then 6205.
The main purpose of the 2A.2b flight was to kit out the newly arrived Zvezda module with basic equipment so that it can serve as living quarters for Expedition One. Fire extinguishers and gas masks will be activated. Lu and Malenchenko made a spacewalk to hook up cables from Zvezda to Zarya, and to install a magnetometer on Zvezda. They would reach 33m from the airlock, a record distance for a US tethered spacewalk. Morukov will unload supplies from Progress M1-3. The crew will install three batteries in Zvezda and replace two in Zarya, and install power conversion units to enable the Russian segment to use power from the US solar arrays.
Delivered aboard the Spacehab will be part of the CheCS (Crew Health Care System), a treadmill and a bicycle ergometer, as well as water and supplies. A toilet will also be added to Zvezda. An experimental PCG dewar will be placed on the ISS for later retrieval.
The ICC carries the SHOSS box and the SOAR (DTO700-21) GPS attitude determination system.
The Bay 13S GABA carries two GAS canisters with high school experiments, SEM-8 and G-782.
Orbiter OV-104 Atlantis was launched from Kennedy Space Center's Launch Complex 39B on 2000 Sep 8 at 1245:47 UTC. The solid rocket boosters, serial RSRM-75, were jettisoned at about 2 minutes after launch at an altitude of around 50 km. The orbiter, still connected to the external tank, flew up the east coast of the US.
At 1253 UTC the main engines shut down (MECO) and ten seconds later external tank ET-103 separated. The Shuttle and ET-103 were then in a 72 x 328 km x 51.6 deg transfer orbit. ET-103 will reenter over the Pacific after one orbit; the Shuttle fired its OMS engines at apogee to circularize its own orbit.
One of two star trackers on Atlantis failed, making navigation slightly trickier, but the docking was carried off flawlessly over Kazakstan.
Following the EVA, the crew installed equipment in Zvezda including the toilet and the TVIS treadmill.
| STS-106 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2000 Aug 7 | Move to VAB/HB1 | ||
| 2000 Aug 8 | Mate to ET | ||
| 2000 Aug 12 | Move to VAB/HB2; Safe Haven fit check | ||
| 2000 Aug 14 | Rollout to LC39B | ||
| 2000 Sep 8 | 1245:47 | Launch | |
| 1247:50 | SRM sep | ||
| 1248:00 | OMS assist burn 15s | ||
| 1248:15 | OMS CO | ||
| 1254:13 | MECO | ||
| 1254:32 | ET Sep | 72 x 328 x 51.6 | |
| 1329:47 | OMS-2 54s 24.7m/s | 89.34 158 x 324 x 51.6 | |
| 1330:41 | OMS 2 CO | ||
| 1400? | ET reentry | ||
| 1422 | PLBD open | ||
| 1630:22 | OMS-3 NC1 79s 37m/s | 90.63 279 x 331 x 51.6 | |
| 1631:47 | OMS-3 CO | ||
| 2000 Sep 9 | 0445:56 | OMS-4 NC2 39s 7.5m/s | |
| 0446:22 | OMS 4 CO | ||
| 0630 | RMS checkout | ||
| 0700 | RMS complete | ||
| 1136:53 | NC3 RCS 13s 1m/s | 91.08 296 x 358 x 51.6 | |
| 2000 Sep 10 | 0126:31 | OMS-5 NC4 32s 15m/s | |
| 0127:03 | OMS-5 CO | ||
| 0200:52 | RCS NCC 0.3m/s 1s | ||
| 0258:33 | OMS-6 L TI burn 15 km; 10s, 2.5m/s | 344 x 369 x 51.6 | |
| 0258:44 | OMS-6 CO | ||
| 0318:32 | MC1 | ||
| 0351:14 | MC2 | ||
| 0408:15 | MC3 | ||
| 0418:14 | MC4 7s 0.8m/s | 91.73 352 x 365 x 51.6 | |
| 0425 | 300m | ||
| 0429 | +Rbar 180m | ||
| 0442 | +Vbar 120m | ||
| 0456 | -Rbar 75m | ||
| 0458s | 52m, skeep | ||
| 0502 | Go for docking | ||
| 0517 | 52m, approach | ||
| 0532 | 15m | ||
| 0551:37 | Dock with PMA-2 | ||
| 0604:53 | Hard dock | ||
| 0818 | Open PMA-2 for air sample | ||
| 0830? | Close PMA-2 | ||
| 2000 Sep 11 | 0441 | Depress EVA-1 Lu, Malenchenko | |
| 0442:45 | Depress (MR) | ||
| 0447 | Battery power | ||
| 0452 | Thermal cover open | ||
| 0453 | HO | ||
| 0459 | Egress Lu (Safer 3) | ||
| 0504 | Egress Malenchenko (Safer 5) | ||
| On RMS, to ICC | |||
| 0532 | To Zarya on RMS | ||
| 0639s | Docking target deploy | ||
| 0656 | Install and deploy 2m magnetometer boom | ||
| 0900? | Install cables from FGB to SM | ||
| 1020 | Return to Atlantis | ||
| 1023 | Storage on ICC | ||
| 1051 | Entry | ||
| 1054 | HC | ||
| 1100 | RMS reberth | ||
| 1100:47 | Repress | ||
| 1106 | At5 psi | ||
| 1223:49 | RCS reboost, 36 pulses | ||
| 1329:21 | RCS reboost complete | ||
| 2000 Sep 12 | 0240 | HO to PMA-2 | |
| 0415 | HO to Zarya | ||
| 0520 | HO to Zvezda | ||
| 0622 | HO to Progress | ||
| 2000 Sep 14 | 0611:56 | RCS reboost 2 3.5m/s | |
| 0714:57 | Reboost off | ||
| 2000 Sep 15 | 0642:33 | RCS reboost 3 | |
| 0745:42 | Reboost off | ||
| 2000 Sep 17 | 0323:12 | RCS reboost 4 | |
| 0424:12 | Reboost off | ||
| 1120 | HC to Zvezda | ||
| 1200 | HC to PMA-2 | ||
| 2000 Sep 18 | 0345:58 | Undocking | |
| 0346:05 | RCS Sep | ||
| 0400 | Sep to 120m at -Rbar | ||
| 0402 | Begin Flyaround 1 at -Rbar | ||
| 0448 | Begin Flyaround 2 at -Rbar | ||
| 0534:26 | Sep burn at -Rbar 1m/s 1.5s RCS | ||
| 2000 Sep 20 | 0414 | PLBD closed | |
| 0650:07 | DO TIG 3:18 0.104km/s at 380 km | ||
| 0653:25 | DO CO | 22 x 380 x 51.6 | |
| 0725:01 | Entry interface | ||
| 0756:44 | Landing KSC RW15 | ||
| 0758:01 | Wheels stop | ||
| 1230 | Tow to OPF/3 | ||
Sirius 1
1997-071A
Sirius 2 is the first Aerospatiale Spacebus 3000-B satellite, with a redesigned propulsion system, built for NSAB (Nordiska Satellitaktiebolaget) of Sweden as a follow-on to Sirius 1 and Tele-X. It will be stationed at 5 deg E. NSAB will market half the transponders and GE Americom (later SES Americom) the rest. GE Americom called the satellite GE-1E (E for Europe). Mass is 2920 kg full, 1760 kg BOL, 1245 kg dry. Satellite is 2.3 x 3.4 x 3.5m with 29m solar panel span and 7 kW power.
In 2003 Sirius 2's pan-European beam was transferred to NSAB by SES Americom. By 1998 Sirius 2 was owned by SES Sirius, and was renamed Astra 5A. It was moved from 5E to 31.5E.
| Sirius 2 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1997 Nov 12 | 2148 | Launch by Ariane 44L | |
| T+2:31 PAL sep | |||
| T+3:35 Stage 1 sep | |||
| T+4:25 Fairing 01 sep | |||
| T+5:46 St 2 sep | |||
| T+5:51 St 3 burn | |||
| 2206 | T+18:53 St 3 MECO | ||
| 2209 | T+21:50 Sirius 2 sep | ||
| 2212 | T+24:10 SPELDA sep | ||
| 2214 | T+26:20 Cakrawarta sep | ||
| 1997 Nov 13 | 631.81 209 x 35815 x 7.0 | ||
| 1997 Nov 16 | 630.66 209 x 35755 x 7.0 | ||
| 1997 Nov 16 | 1338.92 31992 x 35732 x 0.2 | ||
| 1997 Nov 18 | 0900? | Apogee burn over 1W? | |
| 1997 Nov 18 | 1440.21 35465 x 36268 x 0.1 | ||
| 1997 Nov 20 | 1426.65 35418 x 35779 x 0.1 GEO 5.1E+2.4E | ||
| 1998 Apr 1 | 1436.04 35784 x 35786 x 0.1 GEO 4.9E | ||
| 1999 Oct 18 | 1436.07 35779 x 35792 x 0.0 GEO 4.8E | ||
| 2006 Aug 1 | 1436.07 35783 x 35788 x 0.0 GEO 4.8E | ||