2003-019A
The third mission in the MUSES series, MUSES-C was Japan's most ambitious interplanetary mission to date, the first attempt by any nation to return samples from an asteroid. MUSES-C featured a system to grapple onto the asteroid surface and fire explosive projectiles which would kick up debris into a fragment catcher in its sample return capsule.
The MUSES-C spacecraft consisted of a box-shaped main vehicle, with two solar panels and both bipropellant and Xe ion engines, together with the sample return capsule. It also carried a small 0.1m `hopper' lander, MINERVA, and three tiny `target markers' (TM) which would be jettisoned onto the asteroid. The capsule is 16kg, 0.404 m diameter and 0.202m high, and is similar to the DASH experimental reentry capsule.
The probe was launched by M-5 in 2003 May and renamed Hayabusa (Falcon). Its target was asteroid 1998 SF36; in the run up to the mission it was given the permanent number and name (25143) Itokawa after the ISAS pioneer. The asteroid's orbit is 0.953 x 1.692 AU x 1.7 deg, making it a member of the Apollo class of near-earth asteroids.
The M-V launch was by direct insertion to solar orbit, with a KM-V2 kick stage providing the final insertion. KM-V2 is probably Isp 300s, mass 1400f 120e, with 90s burn. MUSES/KM-V2 mass was then 1900 before, 620 after giving dV = 3.29 km/s.
Reentry trajectory 11.6 km/s at 200 km, 12-15 deg angle (nominal -12 deg inertial). (-59 to -203 x Inf).
By late 2004 Hayabusa had completed its first orbit of the Sun following launch in May 2003, with two or three of its cluster of four ion engines in operation over 50 percent of the time and increasing the probe's velocity by 4 meters per second per day - an acceleration of only five-millionths of an Earth `g', but enough to increase the spacecraft's orbital eccentricity from 0.0 to 0.13, keeping its orbital period constant, leading to a 13 percent increase in its aphelion. By 2003 December 22, after 120 total days of operating time, the engines were temporarily shut down; a further 40 days of operation let Hayabusa reach the target Earth flyby orbit by the end of 2004 February, with a total ion engine operation time of 10627 unit-hours. On 2004 May 19, it made an Earth swingby passing 3725 km above the surface and raising its orbit from 0.86 x 1.14 AU to 1.01 x 1.74 AU out close to that of Itokawa.
First orbit: in GSE coords, at (0.0,-0.3) in Oct 03, (-0.1,-0.5) AU in Dec 03, then back up to 0,0 for encounter in May 2004.
On 2005 Sep 28 Hayabusa made rendezvous 20 km from Itokawa.
After the touch-and-go landing, the probe lost hydrazine RCS capability and control was restored using the ion engine system. The spacecraft was out of control for some weeks; by Dec 6 Hayabusa was found to be 550 km from Itokawa, but its signal was again lost until January. Recovery planning consumed all of 2006, and Hayabusa remained near Itokawa until 2007 Feb, when the ion engines were used to begin the return to Earth. In 2010 April a complex sequence of targeting manuevers began to steer Hayabusa back to a precise Earth entry trajectory; the main spacecraft would burn up, but three hours before reentry the heat-shielded capsule separatedm oriented for an 11.4 km/s fiery plunge.. On 2010 Jun 13, the Hayabusa reentry capsule made a triumphant landing in the Australian desert near Woomera. It was recovered a few hours later, and analysis showed that it did indeed contain fragments of the asteroid.
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| MUSES C |
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| Date | Time | Event | Orbit |
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| 2003 May 9 | 0429:25 | Launch by M-V-5 | KASC |
| | | Launcher Az 90.2 |
| | 0430:40 | T+1:15 St 1 sep |
| | | T+1:15 St 2 burn |
| | | T+3:06 Fairing sep |
| | 0433:03 | T+3:20 St 2 sep |
| | | T+3:22 St 3 nozzle extend |
| | | T+3:25 St 3 burn |
| | | T+5:23? St 3 burnout |
| | | T+5:59 Spinup |
| | 0434:48? | T+6:10 St 3 sep | -100? x 500? x 30? |
| | | T+6:12 KM nozzle out |
| | 0435:37 | T+6:12 KM-V2 burn |
| | | KM-V2 cutoff |
| | 0435:48 | T+6:23 target interface |
| | | Target Hyperbola to RA DEC = 221, -29 C3 = 10.99202 | 204 x -85485 x 31 |
| | 0436:53 | Actual C3=10.8604 | 236 x -86397 x 31.08 |
| | 0439:35 | T+10:10 KM-V2 sep |
| | | T+10:12 KM-V2 yo weight |
| | | T+10:19 KM-V2 tumble motor |
| | 0443 | Solar panels deploy |
| 2003 May 9 | | Unreliable orbit | 0.93 x 1.74 AU x 1.3? deg (UN) |
| 2003 May 9 | 1025 | Pass EL1:4 |
| 2003 May 13 | 2200? | Depart Earth sphere 1.5Mkm |
| 2003 May | | Begin ion drive |
| 2003 Dec | | End ion drive |
| 2004 Jan | | Resume ion drive |
| 2004 Jan 9 | | | 0.859 x 1.137 AU x 1.21 deg |
| 2004 Apr? | | IES off |
| 2004 Apr 20 | | TCM |
| 2004 May 1 | | | 0.859 x 1.145 AU x 1.21 deg |
| 2004 May 12 | | TCM |
| 2004 May 15 | 0200? | In Earth sphere 1.5Mkm |
| 2004 May 16 | 1730? | Within Earth sphere SOI | 5012 x -70401 x 39.8 |
| 2004 May 18 | 0700? | Within lunar orbit |
| 2004 May 19 | 0435 | Within GEO |
| | 0621:42 | Earth flyby | 3725 x -69185 km x 38.14 |
| | 0810 | Beyond GEO |
| 2004 May 20 | 0600? | Beyond lunar orbit |
| 2004 May 21 | 1900? | Leave Earth sphere SOI | 3236 x -68863 x 38.4 |
| 2004 May 23 | 1100? | Leave Earth sphere 1.5Mkm |
| 2004 Jun 15 | | | 1.012 x 1.734 AU x 1.34 deg |
| 2004 Aug 10 | | | 583.82 1.010 x 1.724AU x 1.50 |
| 2004 Sep | | Engines throttled |
| 2004 Oct | | One of three engines turned off |
| 2004 Nov 1 | 0000 | 569.77d 0.9914 x 1.6987 x 1.50 |
| 2005 Apr 1 | 0000 | 561.08d 0.9672 x 1.6954 x 1.50 |
| 2005 Jun 1? | | 400000 km from Itokawa |
| 2005 Jul 3 | | Begin solar conjunction |
| 2005 Jul 7 | | 143098 km from Itokawa |
| 2005 Jul 8 | | 139888 km |
| 2005 Jul 13 | | 135712 km |
| 2005 Jul 21 | | 100000 km |
| 2005 Jul 29 | | End solar conjunction |
| 2005 Jul 29 | | Resume ion drive?; optical nav |
| 2005 Aug 4 | | 53998 km |
| 2005 Aug 10 | | 36695 km |
| 2005 Aug 11 | | 34058 km |
| 2005 Aug 14 | | 28750 km |
| 2005 Aug 17 | | 20199 km | 557.19d 0.9545 x 1.6958 AU x 1.61 |
| 2005 Aug 22 | | 11320 km |
| 2005 Aug 24 | | 8880 km |
| 2005 Aug 28 | | Ion thrusters off |
| 2005 Aug 28 | | Biprop thrusters on |
| 2005 Aug 29 | | 4040 km |
| 2005 Aug 30 | | 3220 km |
| 2005 Aug 31 | | 2500 km |
| 2005 Sep 2 | | 1550 km, 5m/s approach |
| 2005 Sep 5 | | 750 km |
| 2005 Sep 6 | 0000 | 500 km |
| 2005 Sep 9 | 0030 | 100 km |
| 2005 Sep 10 | 0500 | 47 km |
| 2005 Sep 11 | 0500 | 27 km Hill sphere entry |
| 2005 Sep 12 | 0117 | 20 km, stationkeep burn - arrival gate |
| 2005 Sep 19 | | 15 km |
| 2005 Sep 21 | | 19 km |
| 2005 Sep 29 | | 10 km, gate to home |
| 2005 Sep 30 | | Arrive Home position 6.8 km |
| | | Reaction wheel failure |
| | | Begin RCS 5cm/s, to 8 km |
| 2005 Oct 3 | 0000 | 8 km |
| 2005 Oct 18 | | Begin approach |
| 2005 Oct 21 | | At 4 km |
| 2005 Oct 28 | | 4 km |
| 2005 Nov 3 | 1917 | 3.5 km, begin descent |
| 2005 Nov 4 | 0330 | Descent aborted at 0.7 km |
| 2005 Nov 9 | | Descend to 70m |
| | | Return to 3 km? |
| | | Descend to 500m |
| | | Target marker 1 release |
| | | Return to 3 km |
| 2005 Nov 12 | | Touchdown test |
| | | MINERVA cover ejected |
| | 0624 SCET | MINERVA released at 55m |
2005 Nov 19 | | First touchdown attempt |
| | 1200 | Begin descent at 1 km |
| | 1800 | At 500m |
| | 2025 | Descending at 0.12m/s |
| | 2028 | TM2 release (Kawaguchi et al) at 54m |
| | 2030 SCET | SC DV -0.09m/s to sep from Target marker 2 |
| | 2030 | TCM, slow descent to 0.03m/s |
| | 2036 SCET | TM+6:40 Impact of TM |
| | 2040 | At 17m, begin free fall |
| | 2110 | Landed on asteroid, bounce |
| | 2110 | Bounce up to 22m |
| | 2130 | Landed |
| | 2150 | Another bounce |
| | 2200 | safemode, abort sent |
| | 2205 | Takeoff |
| 2005 Nov 19 | 2330? | (guess) Leave I sphere |
| 2005 Nov 20 | 0032 | Two-way comms |
| | | 100 km from Hayabusa |
| 2005 Nov 23 | | 77 km |
| 2005 Nov 24 | | 20 km - Enter I sphere |
| 2005 Nov 25 | | Second landing attempt |
| 2005 Nov 25 | 2055 | At 460m, begin descent |
| | 2140 | At 160m |
| | 2155 | At 40m |
| | 2207 | Touchdown |
| | 2207? | Two sampling bullets fired? |
| | 2207 | Takeoff |
| 2005 Nov 26 | 0000 | Thrusters to side B |
| | | Safemode |
| 2005 Dec 5 | | mid-gain Telemetry regained |
| 2005 Dec 6 | | Range 550 km to Itokawa, rdot 1.4m/s |
| 2005 Dec 8 | | Lost signal |
| 2006 Jan 23 | | Recovered beacon |
| 2007 Feb | | Leave Itokawa region |
| 2007 Jul | | Ion engine restart |
| 2007 Oct 18 | | Ion engine shut down |
| 2009 Feb 5 | 0235 | Ion engine restart |
| 2010 Mar 27 | | Ion engine adjust complete, range 27 Mkm |
| 2010 Apr 6 | | TCM-0, range 24Mkm | 0.9833 x 1.6543 AU x 1.68 |
| 2010 May 1 | 1200 | TCM-1 for 200 km flyby, duration 64 hours, range 17 Mkm |
| 2010 May 22 | | TCM-2 for 200 km flyby, range 9Mkm |
| 2010 May 26 | | TCM-2 completed |
| 2010 Jun 3 | 1310 | TCM-3 begins, 50 hr, guidance for Australia impact, range 4 Mkm |
| 2010 Jun 5 | 1110 | TCM-3 complete, on target to WPA, dist 3.6Mkm |
| 2010 Jun 9 | 0000 | Range 1989730 km J2000 = 131.0000 29.79 |
| 2010 Jun 9 | 0330 | TCM-4 begin |
| 2010 Jun 9 | 0600 | TCM-4 complete, range 2 Mkm |
| 2010 Jun 10 | 0000 | Range 1566720 km J2000 =131.1666 29.75 |
| | 0358 | Enter Earth sphere 1.5Mkm |
| 2010 Jun 11 | 0000 | Range 1142550 km J2000= 131.4167 29.69 |
| 2010 Jun 11 | 1200 | In Earth sphere (0.9Mkm) |
| 2010 Jun 12 | 0000 | Range 715930 km J2000= 121.9458 29.54 |
| 2010 Jun 12 | 0100 | | 504 x -47149 x 34.33 |
| 2010 Jun 12 | | Capsule heaters on |
| 2010 Jun 12 | | R-19h lunar range |
| 2010 Jun 13 | 0000 | 280000 km, above 128W 28N? |
| 2010 Jun 13 | 0400 | 200000 km above 174E? 29N? |
| 2010 Jun 13 | 0700 | Range 150000 km, over KASC |
| 2010 Jun 13 | 0900 | 110000 km 100E 27N? |
| 2010 Jun 13 | 1051 | R-3h Capsule sep, range 70000 km |
| 2010 Jun 13 | | Pre TCM orbit | 247 x -46866 x 34.5 |
| 2010 Jun 13 | | Actual orbit | (-100 to 50) x -46866 x 34.5 |
| 2010 Jun 13 | | Actual orbit | -64 x -46477 x 34.5 (Bill Gray) |
| 2010 Jun 13 | 1254 | Ground track inflection 60E 20N at 23000 km |
| 2010 Jun 13 | 1324 | 10000 km over 70E 11N |
| 2010 Jun 13 | 1344 | 2000 km over 95E 12S |
| 2010 Jun 13 | 1349 | 600 km over 112E 22S |
| 2010 Jun 13 | 1351 | Earth return entry 12.2 km/s 200 km -10 to -12 deg 125E 28S? | |
| | | 10 km alt, jettison shield, deploy para |
| | 1412? | Landing |
| 2010 Jun 14 | 0708 | Capsule recovered in desert |
Payload:
- AMICA Asteroid multiband imaging camera
- NIRS IR spectrometer
- XRS XR flourescence spectrometer
- LIDAR Laser altimeter
- Sample scoop
- TM Target marker (jettison prio to landing) cube
- 12 biprop thrusters 22mN
- IES 4 ion thrusters 23mN total (3 running)
