2001-034A
Genesis is a Discovery mission. It will collect solar wind samples for 2 years at the L1 point, in a 800000 km radius halo orbit, and then return a capsule to Utah. The LMA/Denver craft is operated by JPL; PI is David Burnett at CalTech. Wafers of ultra pure silicon collect the material. Each L1 halo orbit takes 6 months; Genesis will make 4. Recovery at UTTR.
Launch by Delta 7326. Dry mass is 494, launch is 636 kg. Size is 7.9m span, 2.3h 2.0dia SRC has a 60-deg sphere-cone forebody. The 210 (225?) kg SRC is 1.52m dia 0.96m high. It uses an entry sequence derived from Stardust.
The gravity acceleration sensors were installed in the wrong orientation and failed to detect entry, preventing the parachute deployment sequence from operating. Genesis impacted the Utah desert at high speed, but shards of solar wind collector plates were recovered from the crash site.
Goals: Precision of isotope ratios; Broad range of elements. Compared to ALSEP SWC: Longer exposure, better collector Oxygen isotopic composition - why varies; Ar, Xe, Ne
1 percent isotope ratio abundance measurements
(1)
O isotopes
(2)
N isotopes (a)
(3)
Noble gas elements and isotopes (a)
(4)
Noble gas elements and isotopes, individual s.w. regimes
****** SCIENCE FLOOR ******
Radioactive nuclei in the solar wind (a)
For major ion species, in-situ instruments can now
determine: (1) Velocity distributions (density, velocity, temperature,
anisotropy) as a function of time and solar wind regime. (2) Charge
state distributions. (3) Elemental abundances for elements more abundant
than Cl. (4) A few favorable isotopic ratios e.g., 3He/4He,
24Mg/25Mg/26Mg, 20Ne/22Ne to within a few percent (1 sigma). The solar
wind samples returned by Genesis will extend the database acquired by
in-situ instruments by determining: (a) Elemental abundances for much of
the rest of the periodic table, including important low-abundance light
elements such as Li, Be, B, and F and elements heavier than Ni to which
the in-situ instruments are not sensitive because of the lower
abundances and inadequate instrumental mass resolution. (b) Isotopic
abundances at the precision required for addressing planetary science
objectives. For example, for planetary issues, it is necessary to
measure 17O/16O to a precision better than the difference between
3.70x10-4 and 3.71x10-4. This requirement is set to match differences
measured in different types of meteorites, but such precision is well
beyond the capability of in situ instruments.
The results obtained by the in situ measurements are essential to the
interpretation of Genesis data. The objectives of solar and heliospheric
physics as well as planetary science require both types of measurements
|
| Genesis |
| |
|
| Date | Time | Event | Orbit |
|---|
|
| 2001 Aug 8 | 1613:40 | Launch by Delta 7326 | CC SLC17A |
| | | T+1:03 SRB 1-3 sep | -6340 x 21 ? |
| | | T+4:24 MECO |
| | | T+4:38 SES-1 | -4378 x 110 |
| | | T+5:02 Fairing sep |
| | 1624:14 | T+10:34 SECO-1 | 185 x 197 x 28.5 |
| | 1710:20 | T+56:40 SES-2 |
| | 1711:30 | T+57:50 SECO-2 |
| | 1712:23 | T+58:43 Stage 2 sep | 182 x 3811 km x 28.5 |
| | 1713:00 | T+59:20 TES |
| | 1714:06 | T+1:00:26 TECO |
| | | Despin weights release |
| | 1717:52 | T+1:04:12 Star 37 sep | 180 x 1225640 km |
| | | SES-3 |
| | | SECO-3 depletion | 127.04 188 x 3797 x 26.88 |
| 2001 Aug 9 | 0650 | Pass EL1:4 |
| 2001 Aug 10 | 0521 | TCM-1 5s, 8m/s anti-sun |
| | | Thermal radiator problem |
| 2001 Aug 29 | 0100 | Pass 1.2M km in GSE X |
| 2001 Nov 8 | | Inside 1.2Mkm |
| 2001 Nov 16 | 1904 | L+3mo TCM-5, nominal HOI 268s burn 25m/s |
| | 1908 | Halo orbit insertion 300000 x 800000 km |
| 2001 Dec 3? | | Open canister cover backshell |
| 2001 Dec 3 | | Collector deploy |
| 2001 Dec 12 | | SKM-1A 1.1m/s |
| 2001 Dec 23 | | Outside 1.2Mkm |
| 2002 Jan 16 | 1900 | SKM-1B 282s 1.3m/s |
| 2002 Mar 20? | | SKM-1C |
| 2002 May 22 | | SKM-2A 0.79m/s |
| 2002 Jul 24 | | SKM-2B 1.5m/s 322s |
| 2002 Sep 25 | | SKM-2C No 6 1.5m/s |
| 2002 Nov 5 | | Inside 1.2Mkm |
| 2002 Dec 10 | | SKM-3A No 7 291s, 1.2m/s |
| 2002 Dec 15 | | Outside 1.2Mkm |
| 2003 Feb 6 | | SKM-3B |
| 2003 Apr 16 | | SKM-3C |
| 2003 Jun 11 | | SKM-4A 7min |
| 2003 Jul 30 | | SKM-4B |
| 2003 Sep 24 | | SKM-4C |
| 2003 Oct 29 | | Inside 1.2Mkm |
| 2003 Nov 19 | | SKM-5A |
| 2003 Dec 6 | | Outside 1.2Mkm |
| 2004 Jan 14 | | SKM-5B |
| 2004 Mar 10 | | SKM-5C |
| 2004 Mar 26 | | Inside 1.2Mkm |
| 2004 Apr 2 | | Close SRC |
| 2004 Apr 22 | | TCM-6 Return DV 2; 5 mo return leg |
| 2004 May 2 | 1000 | Earth flyby at 386000 km |
| 2004 May 25 | | TCM-7 |
| 2004 Jun 14 | | Enter L2 region GSEx -1.2Mkm |
| 2004 Jun 30 | | TCM-8 |
| 2004 Jul 25 | | Pass L2 region |
| 2004 Aug 9 | 1015 | TCM-9 50min burn, 1.4m/s, 0.5 kg | 1282 x 1515790 x 138.6 |
| 2004 Aug 15 | | Inside 1.2Mkm |
| 2004 Aug 28 | | | -1720 x 1394026 x 52.5 |
| 2004 Aug 29 | | TCM-10 | -1070 x 1402554 x 51.7 |
| 2004 Sep 5 | | | -16 x 1382143 x 51.9 |
| 2004 Sep 6 | | TCM-11 0.93m/s | -21 x 1380564 x 51.9 |
| | 0900 | Pass lunar orbit inbound |
| 2004 Sep 8 |
| | 1152:47 | SRC sep 59471 | -1 x 1376362 x 52.0 |
| | 1208 | Main bus divert burn to solar orbit |
| | 1555s | Entry 10.7 km/s (or 11.04 km/s) at -8.25 deg, 125 km |
| | 1552:47 | Entry at 135 km |
| | | | -1? x 1500000? x 52? |
| | | | 5 x Inf ? |
| | 1553:10 | Sensible atmosphere at 102 km |
| | 1554:53 | E+2:33 33 km Drogue chute fails to deploy |
| | 1556:10 | Tumble |
| | 1558:52 | Impact 86 m/s at UTTR 40 07 40 N 113 30 29 W |
2004 Sep 8 | 1558 | Bus orbit perigee | 242 x 1350949 x 52.3 |
| 2004 Sep 11 | 0000? | Pass lunar orbit |
| 2004 Sep 19 | 1200? | At 930000 km |
| 2004 Oct 7 | | Apogee at 1.28Mkm |
| 2004 Nov 6 | 0540 | Perigee | 60672 x 1454293 x 41.9 |
| | | TCM for heliocentric departure |
| 2004 Nov 9 | 0100 | Pass lunar orbit |
| 2004 Dec 1 | | Bus deactivated |
| 2004 Dec 5 | | Enter L1 region |
| 2005 Feb 27 | | Leave L1 region |
| 2005 Feb | | Earth-leading HCO |
| 2005 Dec 31 | | | 334.35 0.8960AU x 0.9896AU x 0.28 |
Payload:
- Pure hydrazine monoprop propulsion, 4 x 22N thruster
- Sample collection arrays
