Saturday, July 5, 2008
Ulysses
1990-090B
The Out of Ecliptic project, later the International Solar Polar Mission, was to have consisted of a US and a European probe in complementary solar polar orbits, but the US cancelled its portion and ISPM became ESA's single Ulysses probe. Ulysses rode into orbit aboard Space Shuttle Discovery on 1990 Oct 6. It was deployed into a 296 x 302 km orbit on the first day of the mission. An hour after deployment, the first stage of the IUS upper stage ignited and placed the stack in an intermediate orbit similar to geostationary transfer orbit, with a velocity of 10.08 km/s (compared to an escape velocity of 10.93 km/s). A few minutes later the IUS second stage, SRM-2, fired to increase the probe's velocity to 11.43 km/s, placing it on an escape trajectory. The cooling line to the RTGs was then separated from ULS (but remained attached to the PAM-S aft adapter on SRM-2?). Then the SRM-2 and its attached adapter separated. The PAM-S kick stage was spun up, the PAM-S 1.3m dia 0.3m long motor support assembly separated, and the PAM-S ignited to increase the probe's speed to 15.25 km/s. The combination was then despun with the release of two small weights and their attached cables, and the PAM-S was discarded one hour and 23 minutes after deployment, with Ulysses now flying free at an altitude of 5247 km, on its way to Jupiter.
C3 is about 130.0 for ULS and PAM-S. It is about 12.9 for IUS-2; this would put IUS-2 in a solar orbit of about 1.0 x 1.65 AU.
PAM-S separates from IUS at 1.7 m/s; the MSA is separated at 1.3m/s.
| Ulysses (ULS) | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1990 Oct 6 | 1147:16 | Discovery launch | KSC LC39B |
| 1748:15 | ULS/PAM-S/IUS deploy | 296 x 302 | |
| 1853 | IUS SRM-1 burn, 291 km, 148s burn | ||
| 1857 | IUS SRM-1 sep, RCS spacing | ||
| 1857 | 125s coast | 564.19 310 x 32168 x 28.47 | |
| 1858 | IUS SRM-2, alt 493 km, 91s coast | ||
| 1900 | RTG ACS cooling line sep | ||
| 1901 | SRM-2/Adapter sep (P-10s) | ||
| 1901 | ARC 3s spinup burn (P-10s) | ||
| 1901 | Motor support assembly sep | ||
| 1901 | PAM-S burn, 1007 km, 87s (P-00s) | ||
| 1902 | PAM-S shutdown, despin wt. deploy (P+97s) | ||
| 1902 | Despin weights/cables sep (P+102s) | ||
| 1911 | PAM-S sep, P+596s 5247 km | 310 x -19198 | |
| Trajectory interface, 24100 km | |||
| Jupiter transfer orbit | |||
| 2228 | ULS pass EL1:4 | ||
| 1990 Oct 7 | 0200 | Passed orbit of Moon | |
| 1990 Oct 7 | 0322 | IUS stage pass EL1:4 | |
| 1990 Oct 8 | 0713 | ULS leave Earth sphere | 0.996 x 17.15 AU x 2.00 |
| 0723 | ULS leave Earth sphere (Horizons) | ||
| 1990 Oct 11 | 0709 | IUS leave Earth sphere | 0.9804 x 1.5438 AU x 1.12 |
| 1990 Oct 16 | 1600 | TCM-1 99m/s pulses; Delta Tarr-60hr | |
| 1990 Oct 17 | 1000 | TCM-1 complete | |
| 1990 Oct 18 | Axial jets, adjust aimpoint. 48 min burn | ||
| 6 min touchup burn | |||
| 1990 Oct 19 | Eject DUST experiment cover 0.131kg | ||
| 1990 Nov 2 | TCM-2 3.8m/s | ||
| 1990 Nov 4 | Wire booms deployed | ||
| Nutation problem developed | |||
| 1990 Nov 16 | Experiment checkout complete | ||
| 1991 Jul 8 | 1324 | TCM-3, 8.5min 0.3m/s, Delta Tarr -4 min | |
| 1991 Dec 28 | 1500? | Enter J sphere at 51.9M km | |
| 1992 Jan 31 | Begin Jupiter encounter phase | ||
| 1992 Feb 2 | 1733 | 113 RJ, bow shock | |
| 1992 Feb 6 | 0630 | 67RJ | |
| 1992 Feb 8 | 1202 | 6.31RJ, Jupiter encounter 450000 km | |
| 378950 x -1878034 x 140.1 | |||
| 1992 Feb 8 | 1445 | Center of plasma torus | |
| 1992 Feb 8 | 1815 | Exit plasma torus | |
| 1992 Feb 11 | 0030? | PAM-S Jupiter flyby | |
| 1992 Feb 15 | Exit Jovian magnetosphere | ||
| 1992 Feb 15 | Aphelion 5.4 AU | ||
| 1992 Feb 16 | 0752 | Last bow shock crossing, 149RJ | |
| 1992 Feb 17 | 1700 | 12.35 Mkm from Jupiter | |
| 1992 Mar 12 | 1.5 x 5.0 AU x 80 | ||
| 1992 Mar 21 | 1000 | 51.9M km from J, exit sphere | |
| 1994 May 29 | Begin solar S pole pass | ||
| 1994 Sep 13 | S polar pass -80.2 | ||
| 1994 Nov 4 | End solar S pole pass | ||
| 1995 Feb 5 | Perihelion at solar equator | ||
| 1995 May 29 | Begin N solar pole pass | ||
| 1995 Jul 31 | Max lat 80.2 | ||
| 1995 Sep 11 | End N solar pole pass | ||
| 1995 Sep 30 | End of nominal mission | ||
| 1996 May 1 | Pass through Hyakutake tail at 0.5Tm from nucleus | ||
| 1998 Apr 17 | First orbit complete | ||
| 1998 Apr 17 | Aphelion 2, 5.4AU | ||
| 1998 May 9 | Ecliptic plane crossing | ||
| 2000 Sep 6 | Start S Polar 2 | ||
| 2000 Nov 27 | Solar pole pass -80.2 | ||
| 2001 Jan 16 | End S Polar 2 | ||
| 2001 May 23 | Perihelion 2 at 1.34AU | ||
| 2001 May 25 | Ecliptic plane crossing | ||
| 2001 Jul 19 | Pass 1.34 AU from Earth | ||
| 2001 Aug 31 | Start N Polar 2 | ||
| 2001 Oct 13 | N Polar pass 80.2 deg | ||
| 2001 Dec 10 | End N Polar 2 | ||
| 2004 Jan | Jupiter Distant Encounter | ||
| 2004 Feb 4 | Jupiter closest approach, 120.4Mkm | ||
| 2004 Apr 1 | End encounter | ||
| 2004 Jun 30 | Aphelion 3 at 5.41AU | ||
| 2006 Feb | ULS through tail of McNaught | ||
| 2006 Nov 17 | Begin S Polar 3 | ||
| 2007 Apr | End S Polar 3 | ||
| 2007 Aug | Perihelion 3 | ||
| 2007 Nov | Begin N Polar 3 | ||
| 2008 Mar | End N Polar 3 | ||
Payload:
- Scalar magnetometer
- VHM/FGM Vector He magnetometer (ICL/Balogh) (Code HED)
- SWOOPS Solar wind plasma experiment, axial boom (LANL/Bame) (Code BAM)
- SWICS Solar wind ion composition spectrometer (Bern/UMD/Geiss,Gloeckler) (Code GLG)
- EPAC/GAS Energetic particle composition experiment, Interstellar neutral gas (MPAe-Lindau/Keppler) (Code KEP)
- HI-SCALE Low energy ion/electrons (Bell Labs/Lanzerotti) (Code LAN)
- COSPIN Cosmic ray and solar particle instrument (Chicago/Simpson) (Code SIM)
Friday, July 4, 2008
AMC-9
2003-024A
SES Americom's AMC 9 was an Alcatel Spacebus 3000B3, C/Ku N American comms from 72W. Mass 4100 kg,launch by ILS Proton.
| AMC 9 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2003 Jun 6 | 2215 | Launch by Proton-K/Briz-M | KB LC200/39 |
| T+2:03 St 1 sep | |||
| T+5:31 St 2 sep | |||
| T+5:43 GO sep | |||
| T+9:33 St 3 MECO | -1000? x 170 x 51.6 | ||
| 2224 | T+9:43 St 3 sep 159 km | ||
| 2226 | T+11:19 Briz-M MES-1 | ||
| 2234 | T+19:32 Briz-M MECO-1 | 180 x 180 x 51.6 | |
| 2324 | T+1:09:26 Briz-M MES-2 | ||
| 2339 | T+1:24:56 Briz-M MECO-2 | 275 x 5000 x 50.3 | |
| 2003 Jun 7 | 0145 | T+3:30:56 Briz-M MES-3 | |
| 0155 | T+3:40:55 Briz-M MECO-3 | ||
| 0156 | T+3:41:40 DTB sep | 276.44 296 x 15061 x 49.60 | |
| 0157 | T+3:42:51 Briz-M MES-4 | ||
| 0202 | T+3:47:52 Briz-M MECO-4 | 375 x 35786 x 49.1 | |
| 0643 | T+8:28:16 Briz-M MES-5 | ||
| 0649 | T+8:34:53 Briz-M MECO-5 | ||
| 0709 | T+8:54:45 Briz-M sep | 760.6 6668 x 35793 x 17.5 | |
| 2003 Jun 8 | 753.87 6445 x 35674 x 17.2 | ||
| 2003 Jun 10 | LAM-1? | 1334.28 31848 x 35689 x 0.8 | |
| 2003 Jun 11 | 1615? | LAM-2 | 1432.59 35694 x 35740 x 0.0 |
| 2003 Jun 19 | 1436.03 35779 x 35791 x 0.0 GEO 82W | ||
| 2003 Jun 20 | 1438.23 35783 x 35873 x 0.1 GEO 82W+0.5W | ||
| 2003 Jul 13 | 1436.13 35780 x 35794 x 0.0 GEO 85.0W | ||
| 2005 Feb 10 | Relocate from 85W to 83W | ||
| 2006 Aug 7 | 1436.11 35775 x 35798 x 0.0 GEO 83.0W | ||
Wednesday, July 2, 2008
JCSat 8
2002-015A
JCSAT 8 is a Hughes HS-601 launched by Ariane 4/5 to replace JCSAT-2 at 154E. It has only 3 panels per solar wing. The satellite is also known as JCSAT-2A.
Launch mass is 2600 kg. BSS 601 with 3.6 x 2.7 x 4.3m and 21m span.
| JCSAT 8 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2002 Mar 29 | 0129 | Launch by Ariane 44L | |
| T+2:30 PAL sep | |||
| T+3:30 St 1 sep | |||
| T+3:32 St 2 MES | |||
| T+4:16 Fairing sep | |||
| T+5:42 St 2 sep | |||
| T+5:46 St 3 MES | |||
| 0141 | -500? x 240? | ||
| 0142? | Perigee positive | ||
| 0143 | 230? x 1000? | ||
| 0147 | T+18:51 St 3 MECO | ||
| 0150 | T+21:27 JCSAT sep | ||
| 0154 | T+25:00? Mini-Spelda sep | ||
| 0156 | T+26:59 Astra sep | ||
| 0156 | T+27:22 avoidance burn | ||
| 2002 Mar 29 | 632.06 272 x 35764 x 4.0 | ||
| 2002 Apr 1 | LAM-1 | 1111.78 22596 x 35757 x 0.7 | |
| 2002 Apr 4? | LAM-2 | ||
| 2002 Apr 7? | LAM-3 | 1435.94 35779 x 35787 x 0.0 GEO 139.4E | |
| 2002 Apr 19 | mv out | ||
| 2002 Apr 26 | 1436.31 35775 x 35805 x 0.0 GEO 154.0E | ||
| 2002 Jul 19 | 1436.10 35777 x 35795 x 0.0 GEO 154.0E | ||
| 2006 Aug 7 | 1436.10 35774 x 35798 x 0.0 GEO 154.0E | ||
Sunday, June 29, 2008
Meteor-3M
2001-056A
Meteor-3M 17F45 No. 101 Originally planned for 1998, funding problems delayed it to 2001.
Mass is 2476 kg. Control from TsUP-M, Korolev.
It carried Badr B, Maroc-Tubsat, Kompass and Reflektor The SAGE 3 instrument studies aerosols and the ozone layer.
Launch was southbound from Baykonur; after stage 2 main engine cutoff, low thrust engines continued firing to insert the vehicle into orbit by around 17 min after launch (representing about an equivalent 250 m/s apogee burn).
| Meteor-3M | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2001 Dec 10 | 1718:57 | Launch by Zenit-2 No. 19K | KB PL45 |
| 1721:20 | T+2:23 Stage 1 MECO | ||
| 1721:22 | T+2:25 Stage 1 sep | ||
| 1721 | T+2:25 Stage 2 burn | ||
| 1721:37 | T+2:40 GO sep | ||
| 1725:39 | T+6:42 Stage 2 MECO | 180? x 996? x 99.7 | |
| 1736:29 | T+17:31 Stage 2 VECO | ||
| 1736:29 | Meteor-3M sep | ||
| 1736:31 | Satellites separate | ||
| 2202 | 105.25 996 x 1015 x 99.7 | ||
Payload:
- VIK-M1 Vis/IR imager with MSU-E visible and MSU-SM red channels, 30m
- BKNA Comprises MTVSZ, MIVZA, KGI-4S, MSGI-5EI?
- MR-700M Meteo instrument package, with MR-2000M1 TV camera and Klimat
- KGI-4S Particles: electron and proton spectra
- MSGI-5EI Electron and proton fluxes
- MTVZA Microwave sounder 18-36 GHz, 2600 km swath 30m res
- MIVZA Microwave sounder 42-94 GHz, 1700 km swath 12m res
- Cloud top heights
- Sea surface temperature measurements
- Temperature and humidity profiles
- SAGE 3 Stratospheric aerosol and gas profiles