III. HISTORY OF THE MISSION 2011 Development phase 2014 Dec 3 Launch 5 Critical operations Launch 6 Initial function check Rocket - H-IIA-26 (type 202) Planned launch date - 30 Nov 2014 13:24:48 (Delayed due to weather) 2015 Actual launch date - 3 Dec 2014 13:22:04 Possible launch window - 30 Nov~9 Dec 2014 Mar Cruising phase Launch location - Tanegashima Space Center 2 Sub-payloads accompanying launch Dec Earth swing-by - Shin‘en 2 (Kyushu Institute of Technology) 3 - ARTSAT2-DESPATCH (Tama Art University) Southern hemisphere 4 - PROCYON (co-research by University of Tokyo and JAXA） station operations 2016 Critical operations - Solar array panel deployment, sun acquisition control - Sampling device horn extension Mar - Release launch lock on the retaining mechanism 22 Phase-1 Apr ion engine operation for the gimbal that controls ion engine direction - Confirm spacecraft tri-axial attitude control functions May 21 - Ground-based confirmation of functions for Nov precise trajectory determination system 22 Phase-2 ion engine operation Initial functional confirmation 2017 - Confirmation of ion engine, communications, power supply, attitude control, observation devices, etc. - Precise trajectory determination Apr 26 2018 Jan 10 Phase-3 Jun ion engine operation 3 27 Asteroid arrival HISTORY OF THE MISSION 23 H-IIA LAuNcH VEHIcLE H2A202 [Standard] 50m Satellite fairing (type 4S) H-IIA naming: H2A 1st/2nd stage / number of LRB / number of SRB-A Length - 53 m Mass - 289 ton Satellite fairing 2nd Stage - 1 SRB-A - 2 12m Hayabusa 2 1st Stage - 1 SSB - ｜ 40m Co-payloads (3) Rocket flight plan Altitude Inertial (km) velocity(km/s) 0:0:0 Liftoff 0 0.4 Stage 2 Stage 2 liquid hydrogen tank #1 11m 0:1:39 Solid rocket booster burn completes 46 1.6 Stage 2 liquid oxygen tank #2 0:1:48 separates 53 30m Stage 2 engine 0:4:10 Satellite fairing separation 137 2.8 0:6:36 Stage 1 engine burn stop (MEC0) 202 5.6 Stage 1 liquid oxygen tank 0:6:44 Stage 1/2 separation 207 Stage 1 0:6:50 Stage 2 primary engine start (SEIG1) 210 37m 0:11:18 stop (SEC01) 254 7.8 20m 1:39:23 Stage 2 secondary engine start (SEIG2) 250 Solid fuel 1:43:24 stop (SEC02) 313 11.8 rocket boosters Stage 1 liquid Hayabusa 2 separation 15m hydrogen tank 1:47:15 889 11.4 1:53:55 Shin’en 2 separation 2867 10.4 1:58:5 ARTSAT2-DESPATCH separation 4418 9.7 10m 2:2:15 PROCYON separation 6068 9.2 Solid rocket booster #1At burn chamber max. pressure 2% #2 Thrust strut cutoff 0m Stage 1 engine 1 Satellite fairing separation 2 Primary engine burn stops (MEC0) 3 -90 Stage 2 primary engine stop (SEC01) 4 Stage 2 secondary engine start (SEIG2) Geodetic latitude [northern latitude, deg] [northern latitude, Geodetic latitude 5 -60 Stage 2 secondary engine stop (SEC02) 6 Hayabusa2 separation 7 Shin’en 2 separation 1 30 4 2 3 5 8 ARTSAT2-DESPATCH separation 6 9 PROCYON separation 0 7 8 9 -30 -60 -90 0 30 60 90 120 150 180 210 240 270 300 330 360 Geodetic longitude [eastern longitude, deg] HISTORY OF THE MISSION 24 INITIAL FuNcTION cHEck (details) 2014 12 7·8 - Functional confirmation of X-band mid-gain antenna beam pattern measurements, acquisition of actual data, and X-band communication equipment 9 - Power system (battery) function check 10 - Near-infrared spectrometer (NIRS3) inspection 11 - Inspection of thermal infrared camera (TIR), deployable camera (DCAM3), Optical Navigation Camera (ONC) 12-15 - Function check for attitude and trajectory system (all devices) 16 - Inspection of miniature rover (MINERVA-II) and lander (MASOT) 17 - Inspection of re-entry capsule and impactor (SCI) 18 - 5-point pointing test of X-band high-gain antenna (XHGA), pre-operation of ion engine 19-22 - Ion engine baking 23-26 - Ion engine test operation (ignition) *performed for each engine [12/23 : ion engine A; 12/24 ion engine B; 12/25 : ion engine C; 12/26 : ion engine D] 27 - Precise trajectory determination, Delta Differential One-way Ranging (DDOR) 2015 [No operations on 12/28, 1/1–2] Jan 4 5-7 - Ka-band communications device actual data acquisition, antenna pattern measurements 9-10 - Ka-band DSN station DOR, lensing tests 11 - Ion engine pre-operations 12-15 - Ion engine paired test operations [1/12: A+C; 1/13: C+D; 1/14: A+D; 1/15: A+C] 16 - Ion engine tri-set testing: A+C+D 19-20 - Paired engine 24-hour continuous autonomous operation: A+D 23 - Function check of laser altimeter (LIDAR), laser range-finder (LRF), flash lamp (FLA) 20-3/2 - Confirming functions such as coordinated operation of multiple devices for transition to cruising phase (regular operations) Function check of linked operations, such as solar light pressure effects evaluation, data acquisition from sun tracking movement behavior, solar light pressure and attitude trajectory control equipment (reaction wheels, etc.), ion engine HISTORY OF FLIgHT Mar 2 Initial operations phase complete, followed by normal operations phase. 3 EDVEGA phase-1 IES operation 21 27 Solar sail mode operations May (maintains fuel-free solar orientation using only 1 RW out of 4. Other RWs are kept in the OFF state) 7 12 Three IES operate in 24-hour mode ( ITR-A+C+D ） 13 Jun 2 EDVEGA phase-2 IES operation 6 9 Solar sail mode operation starts Sep 1 IES-TCM ( precise trajectory control for swing-by ) 2 Oct 1 Precise guidance phase ( TCM by RCS twice ) Dec 3 Earth swing-by ~2016/4/E Southern hemisphere station operations 2016 ( by DSN Canberra and ESA Malargüe only ) HISTORY OF THE MISSION 25 Phase-3 ion engine operations 10 Jan 2018~3 Jun 2018 Phase-2 ion engine operations 22 Nov 2016~26 Apr 2017 Arrive at Ryugu Trajectory to Ryugu 27 Jun 2018 Hayabusa 2 orbit Launch Earth orbit 3 Dec 2014 Earth swing-by 3 Dec 2015 Phase-1 ion engine operations 22 Mar 2016~21 May (incl. added burns) 2016 2015 Accel. Time Before swing-by Units m/s H Mar Initial functioning IES operations testing Transfer phase-1 ion engine operations start 22 confirmation May Transfer phase-1 ion engine operations end 21 3/3~21 IES powered flight 1 2 44 409 24 Mars observations (–Z Mars orientation) Jun 5/12~13 IES max. thrust test 3 4 24 1 6/2~6 IES powered flight 2 2 11 102 9 IES powered flight 3 14 Light pressure confirmation operations 9/1~2 2 1.3 12 20 2016 22 DSN-DSN uplink transfer testing 23 After swing-by DSN Ka-band communication testing 3/2~5/21 Phase -1 ion engine 3 127 798 29 operations 2 at times Jul 3 11/22~4/26 Phase -2 ion engine 3 435 2593 5 ESA Ka-band compatibility testing operations 2 at times 8 Aug 3 Transition to attitude control solar sail mode Oct 8 Transition to 3-axis attitude control wheel 2018 STT Mars observations (OPNAV practice) 11 ➡ 16 1/10~6/3 Phase -3 ion engine 2 3 393 2475 operations 19 ONC fixed-star observations 22 Nov 2,4 DSN-UDSC uplink transfer testing 22 Transfer phase-2 ion engine operations start 2017 Apr 18 ONC-T imaging near L5 26 Transfer phase-2 ion engine operations end May 16 ONC imaging of Jupiter and fixed stars 28 30 RCS autonomous maneuvering tests Jun 20172018 1 Sep Jan 5 Reset internal clock (TI) to zero 10 Transfer phase-3 ion engine operations start Nov Feb 18 DSN-SSOC real-time Doppler 26 First Ryugu observations 28 transmission testing Jun Dec 3 Transfer phase-3 ion engine operations end 2 DSN-UDSC uplink transfer testing Asteroid approach navigation start 26 IES test maneuvers 27 Asteroid arrival 27 HISTORY OF THE MISSION 26 2015 dEScRIpTION OF 2016 pRIMARY Operations Solar sail mode ( 2015 ～ ) A new technology that requires only a single reaction wheel; no fuel needed ・A new technology for Hayabusa2 that utilizes findings from Hayabusa and IKAROS ・This technology (a type of “solar sail” technology for utilizing the power of sunlight) allows stable control of spacecraft attitude with only one of the four reaction wheels aboard Hayabusa 2 turned ON, others OFF. ・Realizes non-fueled, long-term maintenance of sunward orientation, which was not possible in earlier spacecraft. ⬆ Attitude maintenance realized by this technology for over 9 months of the 2.5-year flight. Utilizes force (pressure) from sunlight for batteries, etc. Only one reaction wheel (RW-Z1) left ON RW-X RW-Z1 RW-Z2 RW-Y Scientific results from the swing-by ( 3 dec 2015 ) ONC-T Intensity distribution TIR LIDAR Color Earth image of light reflected TIR thermal image ONC-T color image Successful laser reception at 6.7 million km (0.045 AU) from vegetation on 19 Dec 2015 NIRS3 Light absorption by water molecules in Earth's atmosphere Mars imaging ( May - Jun 2016 ) Near ・24 May, 1 – 9 Jun 2016 alignment ・We performed observations, taking advantage of an alignment of Hayabusa2, Earth, and Mars. (Observations by ONC-T, NIRS3, TIR) Distance (AU) Distance Venu Mercury Earth Hayabusa 2 Mars Ryugu ONC-T image of Mars 21:46 24 May 2016(JST) Distance (AU) HISTORY OF THE MISSION 27 uplink transfer ( Jun - Nov 2016 ) Uplink transfer technology testing Previous method Uplink transfer 22–23 Jun 2016 : between DSN stations 2–4 Nov 2016 : between Usuda–DSN Communications Communications Communications temporarily cut not cut not cut Station A Station B Station A Station A Station B Station B ka-band Communications ddOR ( Jun - Jul 2016 ) Ka-band technology testing : 29 Jun–8 Jul 2016 waves from the quasar ・29 Jun–3 Jul : Ka-band communications testing at DSN Stn (Goldstone) ⬆ Success from approx.