2014-076A
\uni{ はやぶさ２}{ }
Size 1.25 x 1.00 x 1.60m with 6.00m span RV is 0.40m dia Minerva about 0.25l 0.15m dia each SCI about 0.3m x 0.21m cyl, 9.5 kg mass of which 4.7 kg is explosive, 2.5 kg liner 5 mm thick.
to 1999JU3 (162173) Ryugu, 0.98 km dia, a = 1.19 e = 0.19 i = 5.8 0.96 x 1.42 x 5.88, T = 1.30 yr The asteroid was discovered by the LINEAR telescope. Similar spacecraft to Hayabusa-1. Mass around 600 kg
Ryugu estimated mass 0.0036 Tt, Hill sphere 150 km at SMA, 122 km at encounter. If density is 2 g/cm3, dia is 0.92 km, then mass is 8E11 kg or 8E-4 Tt; Rg = 6E-16m = 0.6fm. So orbital velocity at 20 km is 0.05m/s, at 45 km is 0.035m/s Helio distance at encounter is 0.98AU.
Launch by H-IIA-26 with 4S fairing. Azimuth 97 deg (cf 96 deg for 25). C3 = 21 km**2/s**2. Reentry vel 11.6 km/s. Registered with the UN in a 137.1 x 163.4 Mkm x 22.1 deg heliocentric orbit, i.e. 0.916 x 1.092 AU.
Total mass of deployables 14.1 + 9.5 + 6 + 16 = 45.6 Total prop 108 H2 mass 554 full 446 dry.
| H2 | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 2014 Dec 3 | 0422:04 | Launch by H-IIA-202 F26 | TNSC |
| T+1:39 SRB burnout 46 km | |||
| T+1:48 SRB sep 53 km 1.6 km/s | |||
| T+4:10 Fairing sep 137 km 2.8km | |||
| 0428 | T+6:36 MECO 202 km 5.6km/s | ||
| T+6:44 St 1 sep 207 km 5.6 km/s | |||
| 0428 | T+6:50 SEIG 210 km 5.6 km/s | ||
| 0433 | T+11:18 SECO-1 254 km 7.8 km/s | ||
| 0601 | T+1:39:23 SEIG-2 250 km 7.8 km/s | 250 x 254 x 30.0 | |
| 0605 | T+1:43:24 SECO-2 313 km 11.8 km/s | ||
| 0609 | T+1:47:15 Haya 2 sep 889 km 11.4 km/s | 245 x -50902 x 29.89 C3=21.03 | |
| 0615 | T+1:53:55 Shin'en 2 sep 2867 km | ||
| 0620 | T+1:58:05 ARTSAT2 sep | ||
| 0624 | T+2:02:15 PROCYON sep | ||
| 2014 Dec 3 | 1322 | H2 pass EL1:4 | |
| 2014 Dec 5 | 1030 | Exit Earth sphere | |
| 2014 Dec 6 | 2034 | Pass L1 distance | |
| 2014 Dec 31 | 366.34d 0.915 x 1.089AU x 6.8 | ||
| 2015 Sep 1 | Ion engine on, 12 hr, tweak flyby | ||
| 2015 Sep 2 | Ion engine off | ||
| 2015 Nov-Dec | Earth swingby | ||
| 2015 Nov 3 | TCM-1 | ||
| 2015 Nov 26 | TCM-2 | ||
| 2015 Nov 29 | 2008 | Enter Earth sphere | |
| 2015 Dec 3 | 1007 | Swingby 3100 km alt., 10.3 km/s, 80 deg deflection | |
| Perigee over Pacific | |||
| HCO vel 30.3 to 31.9 km/s | |||
| 2015 Dec 7 | 0014 | Leave Earth sphere | |
| 2016 Mar 22 | IES-1 Start | ||
| 2016 May 20 | IES-1 Stop | ||
| 2016 Nov | IES-2 Start | ||
| 2017 Apr 15 | IES-2 Stop | ||
| 2017 Apr 25 | IES-2 Trim | ||
| 2017 Apr 26 | IES-2 Trim stop | ||
| 2017 May 30 | RCS test burn | ||
| 2017 Dec 26 | IES Test | ||
| 2017 Dec 27 | IES Test stop | ||
| 2018 Jan 10 | IES-3 Start | ||
| 2018 Jun 3 | 0559 | IES-3 Stop, dv=393m/s | |
| 24 kg Xe used up to now | |||
| 2018 Jun 5 | OpNav start 2500 km | ||
| 2018 Jun 8 | 0330 | TCM-01 | |
| 0440 | TCM-01 complete | ||
| 2018 Jun 11 | 0030 | TCM-02 (13,01,26) cm/s at 1320 km | |
| 0140 | Complete | ||
| 2018 Jun 14 | 0340 | TCM-03 dV 0.4m/s, Vrel 1.7m/s | |
| 0450 | End of TCM | ||
| 2018 Jun 16 | 0030 | TCM-04 | |
| 0140 | End of TCM, (-10,1,44) cm/s, range 470 km | ||
| 2018 Jun 18 | 0200 | TCM-05 | |
| 0210 | End of TCM (-8,1,61) cm/s, 220 km, Vrel 0.7 m/s | ||
| 2018 Jun 20 | 0340 | TCM-06 (3,1,35) cm/s 110 km, Vrel 0.4m/s | |
| 0450 | End of TCM | ||
| 2018 Jun 22 | 0030 | TCM-07 | |
| 0040 | End of TCM. (-2,1,31) cm/s, 45 km | ||
| 2018 Jun 24 | 0030 | TCM-08 dV 2cm/s 38 km VRel 0.08m/s | |
| 0040 | end of TCM | ||
| 2018 Jun 26 | 0110 | TCM-09 | |
| 0120 | End of TCM (0.008, 0.003, 0.1)m/s, 23 km range, Vrel= 0.02m/s | ||
| 2018 Jun 27 | 0030 | TCM-10, range 20.7 km | |
| 0035 | end of TCM (0.007,0.0,0.028)m/s; vrel 0.01m/s | ||
| 2018 Jun 27 | Asteroid arrival 20 km | ||
\uni{ 小型ローバ・ランダの投下}{ }
| |||
| Remote sensing | |||
| At 20 km, leave HP | |||
| 2018 Jul | Mid Alt Obs Descent 1 (5km) | ||
| 2018 Aug | Gravity Measurement Descent (1 km) | ||
| 2018 Sep | TD1 Rehearsal 1 100m | ||
| 2018 Sep | MINERVA-II deploy 50m | ||
| MASCOT deploy 50m | |||
| 2018 Oct | TD1 Rehearsal 2 (50m) | ||
| TD1 | |||
| Deploy target marker | |||
| At 30m align attitude | |||
| Drop small rover | |||
| Touchdown sample acquisition attempts | |||
| DCAM3 ejected? | |||
| Impact device, make artificial crater | |||
| Acquire sample from artificial crater | |||
| 2018 Nov | Begin Conjunction | ||
| 2019 Jan | End Conjunction | ||
| 2019 Jan | Mid Alt Obs Descent 2 (5km) | ||
| 2019 Feb | TD2 rehearsal 2 50mm | ||
| 2019 Mar | Pre-Impact Descent 1 km | ||
| Kinetic Impact 500m | |||
| 2019 Apr | Crater Search Descent 1 km | ||
| 2019 Apr | Pinpoint TD Campaign, 4 descents | ||
| 2019 Jul | MINERVA-II deploy 50m | ||
| 2019 Nov -Dec | Depart asteroid | ||
| 2020 Nov -Dec | Earth reentry at Woomera, 12 km/s | ||
| 10 km alt, deploy para | |||
Payload:
- Reentry capsule (Sai totsunyu kapuseru)
\uni{ 再突入カプセル}{ }with parachute cover, aeroshell (both sep on entry at 11.6 km/s) 16 kg, diam 0.40m ht 0.20m, spin 0.3rev per s - Sample acquisition device
- Minerva-II1 Micro/Nano Experimental Robot Vehicle Asteroid., with Rover 1A and Rover1B Mass 2.5 kg. ISAS, Aizu U
- Minerva-II2 with Rover 2.
- Active Target Marker (akutibu tagettomaka,
\uni{ アクティブ・ターゲットマーカ}{ }) - 5 target markers on H2.10 cm dia. less than 1 kg - camera, accelerometer for imaging ,gravity measuremnet, outreach to university commmunity - DLR MASCOT lander (Mobile Asteroid Surface Scout) 10 kg, 0.30 x 0.30 x 0.20m
- DCAM-3 camera
- Ka-band comms 32 GHz
- X-band comms 8 GHz
- ONC Optical Navigation Camera (telephoto and 2 wide angle lens; ONC-T, ONC-W1, ONC-W2 wiht 6.4 and 65 deg FOV; at0.4-1.0 mu)
- NIRS3 NIR Spectrometer (1.8-3.2mu)
- TIR Thermal IR Imager(8 - 12 micron band)
- LIDAR - altimeter and albedro, 10m to 10 km range, 1.06mu laser
- SMP Sampler Device
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