Saturday, December 2, 2000
Friday, December 1, 2000
Thursday, November 30, 2000
Mars Polar Lander
1999-001A
The MS 1998 Lander (Mars Polar Lander) is built by Lockheed Martin Astronautics and was launched on 1999 Jan 3 by Delta 7425. It was to land near the south pole at 195W 76S.
in Dec 1999. (the ice-free safe zone is 170 to 230W, 75 to 76S). It is 1.0m wide and 0.5m high. The aeroshell is based on the MPF aeroshell, but the lander uses a Viking-type rocket descent system. Attached to the aeroshell is a cruise stage with solar panels. The lander uses solar arrays for power, and will terminate operations as the winter begins. The Lander has four 22N REM engines used during cruise, using the same 64 kg hydrazine propellant tanks as the descent engines.
Aeroshell ejection is followed by propulsive terminal descent. The MARDI imager, mounted on the lander underside, operates during descent. The SSI imager, used on the surface, is similar to the MPF lander's.
Landing near the south pole is during local spring. MPL will dig a trench and collect soil samples for analysis. It will search for near surface ice and look for evidence of climatic changes: however,nothing was heard from the lander after scheduled Cruise Stage separation. A review board suggested the most likely cause was a design flaw in a touchdown sensor causing the engines to shut of at 40m altitude and impact at 55 kph; however, when the successor Phoenix mission was being ground-tested, it was discovered that the Cruise separation itself probably did not occur. A design error exposed critical parts of the separation system to excessively low temperatures which would have stopped them working. The aeroshell entered the atmosphere with the cruise stage still attached, and the spacecraft was probably destroyed and burnt up during entry.
Estimated impact location was 76.1S 195.3W.
Planned B-plane miss at injection (+60000,-20000) km. Mass injected: 583 kg, with PAM-D 2141 kg full 132 kg empty. 1997 planned injection data: 11.165 km2/s2, RLA DLA =235.35, 0.92. Arival data at 125 km: 143.37 -62.57 az 173.69, fpa -13.25, V 6.91, for landing at 210,-76.
| MPL | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1999 Jan 3 | 2021:10 | Launch Delta 7425 | CC LC17B |
| T+4:24 MECO | |||
| T+4:32 Stage 1 sep | |||
| T+4:37 Stage 2 burn | |||
| T+4:42 Fairing sep | |||
| 2032:32 | T+11:22 SECO-1 | 157 x 246 x 28.4 | |
| 2055:21 | T+34:11 Stage 2 restart | ||
| 2055:40 | T+34:30 SECO-2 | 237 x 770 x 28.4 | |
| 2056:33 | T+35:23 Stage 2 sep | ||
| 2057:10 | T+36:00 Stage 3 burn | ||
| 2058:38 | T+37:28 TECO 293 km 11.434 km/s | 0.97 x 1.45 AU | |
| T+42:10 Yo-yo deploy | |||
| 2103:25 | T+42:15 Stage 3 sep | 185 x -84447 x 28.43 | |
| Deploy solar panels | |||
| 1999 Jan 4 | 0543 | Pass EL1:4 | |
| 1999 Jan 8 | 1548? | Exit Earth sphere 1.5Mkm | |
| 1999 Jan 21 | 1227 | TCM-1, 3min 16m/s | |
| 1999 Mar 16 | 1305 | TCM-2, 10s, 0.9m/s | |
| 1999 Sep 1 | 1700s | TCM-3, site adjust 2.3m/s | |
| 1999 Oct 30 | 1728 | TCM-4 site adjust 12s | |
| 1999 Nov 30 | 1800 | TCM-5 0.1m/s 3.5 Mkm from Mars | |
| 1999 Dec 1 | 0615 | Enter Mars sphere | |
| 1999 Dec 2 | 0000? | PAM-D enter Mars sphere | |
| 1999 Dec 3 | 1339 | TCM-6, 8s | |
| 1999 Dec 3 | Mars arrival OWLT = 14m | ||
| 1949 | Transmitter off | ||
| E-7h TCM-5 at 125000 km | |||
| 1951:00 | E-5min L-10 min Cruise stage sep | ||
| 1951:18 | DS2 sep | ||
| 1955 | DS2 entry | ||
| 1956 | E-0 L-5 Entry 6.91 km/s, 125 km, -13.1 deg | ||
| E+0:33 Hypersonic ops begin | |||
| 1958 | E+2:30 Parachute deploy 7.3 km | ||
| E+2:37 MARDI imaging begins | |||
| E+2:37 Aeroshell sep | |||
| E+2:39 Landing legs deployed | |||
| E+2:40 Landing radar on | |||
| E+4:00 Radar lock, 2.5 km | |||
| 2000 | E+4:00 Backshell sep 1.8 km | ||
| E+4:01 Landing engines on | |||
| 1999 Dec 3 | 1959 | DS2 impact | |
| 2001 | Landing | ||
| 2000 | PAM-D pass at 63000 km | ||
| 1999 Dec 5 | 1600? | PAM-D leave Mars sphere | |
| 2000 Feb 29 | End primary mission | ||
Payload:
- MARDI Mars Descent Imager
- LIDAR Lidar (light detection and ranging) for dust and aerosols, IKI/RKA
- MVACS Mars Volatile and Climate Surveyor
- SSI Stereo surface imager
- RA Robotic arm (2m)
- RAC Robotic arm camera
- TEGA Thermal and evolved gas analyzer
- MET Meteorological package
STS-46 (Atlantis)
1992-049A
The EURECA deploy was delayed one day because of intermittent data problems. After deploy, Atlantis separated to 290m and remained there an extra orbit. Five hours after the 12m boom was extended, the subsatellite was released for the first flyaway. However, the release was aborted after only 10 cm of tether was deployed, and after 13 minutes the satellite was reeled back in to the docking clamp. On the next orbit, the flyaway began again. This time the tether snagged at a distance of 220m, on a bolt in the deployer mechanism.
| STS-46 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1992 Jun 4 | Tow to VAB | ||
| 1992 Jun 6 | ET mate | VAB/1 | |
| 1992 Jun 11 | Rollout | LC39B | |
| 1992 Jul 31 | 1356:48 | Launch from LC39B | |
| 1358:53 | SRB sep | ||
| 1405:16 | MECO | 89.36 65 x 420 x 28.5 (OMS dV) | |
| 1405:35 | ET sep | ||
| 1438:11 | OMS-2 3:44 107m/s | ||
| 1441:54 | OMS-2 CO | ||
| 1511 | 93.11 420 x 433 x 28.5 | ||
| 1535 | PLBD open | ||
| 1945 | RMS checkout | ||
| 1992 Aug 1 | 0130 | Eureca grappled | |
| 0225? | Eureca unberth by RMS | ||
| Deploy delayed | |||
| 1859 | 93.12 422 x 432 x 28.5 | ||
| 1992 Aug 2 | 0707 | RMS deploy EURECA | |
| 0708? | RCS sep | ||
| 1700? | 93.11 422 x 431 x 28.5 | ||
| 1992 Aug 3 | 1054:13 | OMS-3 1:10 36m/s Orbit lowered for TSS | |
| 1055:23 | OMS-3 CO | ||
| 1139:22 | OMS-4 1:10 37m/s Orbit lowered | ||
| 1140:32 | OMS-4 CO | ||
| 2322 | 90.48 294 x 301 x 28.5 | ||
| 1992 Aug 4 | 1600? | TSS boom extend begins | |
| 1630 | Boom extended | ||
| 2001 | U2 umbilical disconnect | ||
| 2115 | TSS flyaway 1, abort at 10cm | ||
| 2134 | TSS reeled back | ||
| 2250:47 | TSS flyaway 2 | 90.49 295 x 301 x 28.5 | |
| 2347 | Snag at 179m | ||
| 1992 Aug 5 | Snag at 256m | ||
| 0100? | 90.48 295 x 301 x 28.5 | ||
| 1301 | Reel in to 224m | ||
| 2155 | TSS reel in begins | ||
| 2252:47 | TSS docked on boom | ||
| 2326 | TSS power down | ||
| 2337 | TSS boom retract | ||
| 1992 Aug 6 | 0003 | TSS retracted and latched | |
| 0939:06 | OMS-5 to lower orbit for EOIM ops, 33s 18m/s | ||
| 0939:40 | OMS-5 CO | 89.21 234 x 236 x 28.5 | |
| 1023:14 | OMS-6 35s 20m/s | ||
| 1023:51 | OMS-6 CO | 89.13 227 x 235 x 28.5 | |
| 1992 Aug 7 | 0126 | 89.12 227 x 234 x 28.5 | |
| 2200 | 89.09 225 x 232 x 28.5 | ||
| 1992 Aug 8 | 0935 | PLBD closed | |
| 1217:09 | OMS DO (2:03) 68m/s | ||
| 1219:13 | OMS DO CO | ||
| 1239:53 | Entry interface 120 km | ||
| 1311:50 | Landed KSC RW33 | ||
| 1312:05 | NGTD | ||
| 1312:55 | Wheels stop | ||
| 1530 | Tow to OPF | OPF/2 | |
Zond 3
1965-056A
3MV-4 No. 3 was launched on 1965 Jul 18 on a mission to test out the reliability of planetary probes. The modified Mars probe made a lunar flyby and returned pictures of the lunar surface. It was named Zond-3.
| Zond-3 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1965 Jul 18 | 1432:05 | Launch by 8K78 | KB |
| 1437? | Blok A sep | ||
| 1437? | Blok I burn | ||
| 1441? | Blok I sep | ||
| 1552? | BOZ burn | ||
| 1553? | Blok L burn | ||
| 1557? | Blok L sep | ||
| 1965 Jul 20 | 0124 | Start lunar photos at 11600 km ht | |
| 0224? | Perilune, 9220 km | ||
| 0232 | End lunar photos at 10000 km ht | ||
| 1965 Sep 15 | TCM in solar orbit | ||
| 1966 Mar | End of ops | ||
| 1966 Dec | Reactivated for test transmission | ||
Payload:
- Lunar mapping camera
STS-84 (Atlantis)
1997-023A
STS-84 was another Spacehab-DM flight to Mir. A late addition to the Spacehab, in April, was a replacement Elektron oxygen generator. Although the plan was for MS Foale to replace Linenger aboard Mir, after the space station's equipment failures preparations were made in case both Foale and Linenger would return to Earth after the docking. In the event, the Mir troubles were deemed to be resolved and British-born Foale took his place aboard Mir.
STS-84's crew was remarkably international. The US-born crew members were commander Precourt, pilot Collins, and mission specialist Lu; Foale and Peruvian-born Carlos Noriega were also US citizens. They were joined by Elena Kondakova of the Russian Space Agency and French citizen Jean-Francois Clervoy of the European Space Agency.
Atlantis was launched on 1997 May 15 and docked with Mir early on May 17. Undocking on May 22 was a direct R-bar separation. In contrast to earlier missions, no flyaround of Mir was performed due to software modifications.
| STS-84 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1997 Apr 19 | 2130 | Roll to VAB | |
| Mate to ET | |||
| 1997 Apr 24 | 1230 | Rollout to LC39A | |
| 1997 May 15 | 0807:48 | Launch | |
| 0809:52 | SRB sep T+2:04 | ||
| 0816:20 | MECO T+8:32 | 82 x 296 x 51.65 | |
| 0816:30 | ET sep | ||
| 0851:52 | OMS-2 23m/s 48s | 89.04 158 x 296 x 51.65 | |
| 0945:56 | PLBD open | ||
| 1147 | NC1 OMS-3 33m/s 68s | ||
| 1200 | 90.18 270 x 296 x 51.65 | ||
| 2347 | NC2 OMS-4 3m/s 11s | ||
| 2350 | 90.26 277 x 296 x 51.65 | ||
| 1997 May 16 | 0600 | 90.26 277 x 296 x 51.65 | |
| 1056 | NC3 OMS-5 28m/s 58s | ||
| 1200 | 91.26 277 x 395 x 51.65 | ||
| 2220 | NC4 OMS-6 27m/s 54s | ||
| 2255 | NCC RCS 0.4m/s 5s | ||
| 2353 | TI burn OMS-7 2m/s 9s | 92.31 379 x 396 x 51.66 | |
| 1997 May 17 | 0015 | MC1 RCS 0.1m/s 1s | |
| 0047 | MC2 RCS 0.6m/s 8s | ||
| 0057 | MC3 RCS 0.1m/s 1s | ||
| 0107 | MC4 RCS 0.3m/s 1s | ||
| 0233 | Docking with Mir | ||
| 0241 | Hard dock | ||
| 0425 | Hatch open | ||
| 1000 | 92.34 382 x 396 x 51.66 | ||
| 1415 | Foale to Mir 23 crew | ||
| 1415 | Linenger to STS-84 (122:04:30 as Mir crew) | ||
| Elektron O2 generator transferred | |||
| 1997 May 18 | 1200 | 92.34 383 x 395 x 51.66 | |
| 1997 May 21 | 1240 | Hatch closed | |
| 1997 May 22 | 0103:56 | Undocked | 92.34 384 x 393 x 51.7 |
| 0109 | Stationkeep at 27m | ||
| 0113 | Resume sep | ||
| 0117 | Stationkeep at 90 m | ||
| 0121 | Resume sep | ||
| 0134 | Stationkeep at 450 m | ||
| 0141 | Resume sep | ||
| 0152 | Leave corridor at 1 km | ||
| 0330 | 92.25 376 x 393 x 51.7 | ||
| 1997 May 24 | 0815 | PLBD closed | 376 x 392 x 51.6 |
| 1223:33 | OMS DO 3:09 101m/s | ||
| 1226:42 | OMS cutoff | 33 x 394 x 51.6 | |
| 1256 | Entry interface 115 km | ||
| 1327:44 | MGTD KSC RW33 9:05:19:56 | ||
| 1327:52 | NGTD | ||
| 1328:35 | Wheels stop | ||
Wednesday, November 29, 2000
Soyuz TM-27 (Crystal)
1998-004A
Soyuz TM-27 was launched in Jan 1998 with a new EO-25 Mir crew. Commander was Talgat Musabaev, flight engineer Budarin and Leopold Eyharts, cosmonaut-researcher. Eyharts's flight was the CNES Pegase mission.
| Soyuz TM-27 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1998 Jan 29 | 1633:42 | Launch by Soyuz-U | |
| T+1:59 Strapons sep | |||
| T+2:42 Fairing sep | |||
| T+4:47 Blok A sep | |||
| T+5:00 Interstage sep | |||
| 1642:31 | T+8:49 Blok I sep | ||
| 2009:24s | TCM1 | ||
| 2059:12s | TCM2 | ||
| 1998 Jan 30 | 1732:29s | TCM3 | |
| 1998 Jan 31 | 1602:41s | TCM4 | |
| 1648:05s | TCM5 | ||
| 1754:30 | Docking with Kvant +X | ||
Payload:
- Physiolab, cardiovascular study
- Congeal, central nervous system
- Fertile Bio payload: salamanders
- Alice II (fluids at critical point)
- Castor (microvibration and structures)
Soyuz TM-27 was redocked to another port. Mir rotated 180 degrees in the horizontal plane.
| Soyuz TM-27 flight 2 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1998 Feb 20 | 0848:20 | Undocked Kvant +X | |
| back off to 30-70m | |||
| Mir rotation | |||
| reapproach | |||
| 0932:21 | Docked Mir -X | ||
In Aug 1998, the Kristall crew, Musabaev, Budarin and Baturin boarded the craft for the return to Earth. At undocking, mass was 6740 kg (BO 1204 kg, SA 2867 kg). Landing was at 47 57 07N 69 37 50E. Flight duration was 207d 12h 51m02s.
| Soyuz TM-27 flight 3 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1998 Aug 24 | 2258s | Hatch closed | |
| 1998 Aug 25 | 0204:55 | Undocked Mir -X | |
| 0211:00 | DPO burn, 8s | 363 x 372 x 51.7 | |
| 0431:18 | Deorbit, 4:21 | ||
| 0435:39 | DO CO | -17? x 364 x 51.6 | |
| 0456? | Modules sep | ||
| 0459? | Entry | ||
| 0524:44 | Landed | ||
Tuesday, November 28, 2000
Progress M-41
1999-015A
Progress M-41 was launched in Apr 1999 amid continuing uncertainty about Mir's financial future. It carried 2438 kg of cargo. Launch mass was 7180 kg.
| Progress M-41 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1999 Apr 2 | 1128:43 | Launch by Soyuz-U | KB LC1 |
| 1137:32 | Sep from Blok-I | ||
| 1999 Apr 4 | 1246:49 | Docked with Kvant | |
| 1999 Jul 17 | 1120 | Undocked | |
| 1918 | Deorbit | ||
| 1951 | Reentered | ||