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Asteroid Explorer, Hayabusa2, Reporter Briefing

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Asteroid Explorer, Hayabusa2, Reporter Briefing Asteroid explorer, Hayabusa2, reporter briefing September 15, 2020 JAXA Hayabusa2 Project Topics Regarding Hayabusa2, Extended mission selection 2020/9/15 Hayabusa2 reporter briefing 2 Contents 0. Hayabusa2 and mission flow outline 1. Current status and overall schedule of the project 2. Extended mission selection 3. Scientific significance of extended mission 4. Future plans 2020/9/15 Hayabusa2 reporter briefing 3 Overview of Hayabusa2 Objective We will explore and sample the C-type asteroid Ryugu, which is a more primitive type than the S-type asteroid Itokawa that Hayabusa explored, and elucidate interactions between minerals, water, and organic matter in the primitive solar system. By doing so, we will learn about the origin and evolution of Earth, the oceans, and life, and maintain and develop the technologies for deep-space return exploration (as demonstrated with Hayabusa), a field in which Japan leads the world. Expected results and effects By exploring a C-type asteroid, which is rich in water and organic materials, we will clarify interactions between the building blocks of Earth and the evolution of its oceans and life, thereby developing solar system science. Japan will further its worldwide lead in this field by taking on the new challenge of obtaining samples from a crater produced by an impacting device. We will establish stable technologies for return exploration of solar-system bodies. Features: World’s first sample return mission to a C-type asteroid. (Illustration: Akihiro Ikeshita) World’s first attempt at a rendezvous with an asteroid and performance of observation before and after projectile Hayabusa 2 primary specifications impact from an impactor. Mass Approx. 609 kg Comparison with results from Hayabusa will allow deeper understanding of the distribution, origins, and Launch 3 Dec 2014 evolution of materials in the solar system. Mission Asteroid return International positioning Arrival 27 June 2018 Japan is a leader in the field of primitive body exploration, and visiting a type-C asteroid marks a new Earth return 2020 accomplishment. Stay at asteroid Approx. 18 months This mission builds on the originality and successes of the Hayabusa mission. In addition to developing planetary Target body Near-Earth asteroid Ryugu science and solar system exploration technologies in Japan, this mission develops new frontiers in exploration of primitive heavenly bodies. Primary instruments NASA too is conducting an asteroid sample return mission, OSIRIS-REx (launch: 2016; asteroid arrival: 2018; Sampling mechanism, re-entry capsule, optical cameras, laser Earth return: 2023). We will exchange samples and otherwise promote scientific exchange, and expect further range-finder, scientific observation equipment (near-infrared, scientific findings through comparison and investigation of the results from both missions. thermal infrared), impactor, miniature rovers. 2020/9/15 Hayabusa2 reporter briefing 4 Mission flow Launch Earth swing-by Ryugu arrival MI NE RVA-II1 separation MASCOT Sep 21, 2018 Dec 3, 2014 Dec 3, 2015 June 27, 2018 separation Oct 3, 2018 Target marker Ryugu separation departure Oct 25, 2018 Nov 13, 2019 Target Target marker Earth return complete marker separation Impactor (SCI) Dec. 6, 2020 MI NE RVA-II2 separation Second May 30, 5 April, 2019 separation Sept. 17, touchdown 2019 First touchdown (image credit: illustrations including spacecraft July 11, 2019 by Akihiro Ikeshita, others by JAXA) Oct. 3, 2019 2019 Feb 22, 2019 2020/9/15 Hayabusa2 reporter briefing 5 1. Current project status & schedule overview Current – Precise estimate of the orbit of the spacecraft was made and from today (September 15), status< the fine correction (TCM-0) of the orbit by the ion engine is planned. – Narrowed down the extended mission – Continue preparation for recovery work 2015 2016 2017 2018 2019 2020 Schedule overview 12 3 10 12 4 6 7"001/"$) 12 &&.31128 .*3*", 6*.(#8 /41.&83/"23&1/*% 23&1/*%01/7*-*38/0&1"3*/.2 "13)1&341. Event /0&1"3*/. ,"4.$) "13)26*.(#8 11*5","384(4 &0"1341&'1/-84(4 "024,&1&&.318 &$ &$ 4.& /5 &$ : ; 3&23/0&1"3*/.2 /43)&1.)&-*20)&1&23"3*/. "8 /0&1"3*/.2 03*$",."5*("3*/. /,"1 $/.+4.$3*/. $3 "8 "8 4, /5 &$ &03 /.&.(*.&/0&1"3*/.29 "1 4. "1 "8 /5 01 ". 4. &$ &# "8 :*-"(&$1&%*3<!; 2020/9/15 Hayabusa2 reporter briefing 6 2. Extended mission selection Scenario selection result • There were 2 candidates for the Hayabusa2 extended mission and we planned to select one scenario after confirming the technical feasibility • After examination, the EAEEA scenario has been selected. -The final target celestial body is 1998 KY26. Mission significance/ (1) Advancement in long-term navigation within the Solar System (2) fast-rotating small asteroid exploration (3) Acquisition of science and technology for planetary defense. "!&$ '%(!"$%(! %&$""$& %&$"%'#$"%**, 01998 KY26 properties1 $'%"#$&"!' '&"!" "$& "!&$ "#$&"!$%'&%"$ %&$""$& $&"$& Spherical (from radar obs.) , About 30 m 10.7 min (0.178hr) 2 Tumbling No short-term variability motion detected !'%"$& Spectral type Possible carbonaceous asteroid %&$"&&!% %&$"##$" '& $&%)!*, %&$"&&!% %&$"$!+("'% %!&, , Accumulation2 Monolithic? Centrifugal force is superior to gravity Target marker - $&/ ''$!!($%&* . - $&/ . 2020/9/15 Hayabusa2 reporter briefing 7 2. Extended mission selection Background • Originally, the spacecraft was designed on the assumption that the solar distance is in the range 0.85 – 1.41 au. But in both scenarios, the solar distance will deviate from the design premise. Ø EVEEA Sun distance range/ 0.711.64au Ø EAEEA Sun distance range/ 0.771.52au • Further analysis and the conducted examination highlighted further specific issues: Ø Deviation from the allowable temperature range of the onboard equipment near the Venus orbit (0.71 au) (0.77 au is no problem) Ø Operation restrictions for the ion engines in a high temperature environment (3 engines can be operated up to 0.85 au but even 1 engine is difficult to operate at 0.77 au) ,#%!&$#%#%$%#"- ,#%$%#"#%#%$%#"- 1 Venus 2001CC21 Earth Earth 2001AV43 Venus )%! $$"!$%#% )%! $$"!$%#% S/C 1998KY26 0.5 . 1 S/C #% $(!* #%$(!* 0 0.5 Ion engine prohibited Ion engine prohibited period abefore/after period before/after Venus CC21 fly-by : 97day #!+'"&$ -0.5 swing-by : 144day 0 Y(J2000EC) [AU] #!+'"&$ Y(J2000EC) [AU] $(!* -1 -0.5 $(!* -1.5 !&$ $(!* -1 -1.5 -1 -0.5 0 0.5 1 -1.5 -1 -0.5 0 0.5 1 1.5 , #%/- X(J2000EC) [AU] X(J2000EC) [AU] 2020/9/15 Hayabusa2 reporter briefing 8 2. Extended mission selection Scenario comparison and selection Evaluation EVEEA Eval. EAEEA When attitude is changed for observing Venus, the Even at minimum solar distance (0.77 au), the Thermal temperature range for onboard eqipnebts exceed temperature range for onboard equipment does not feasibility the nomal range. (Max. Sun distance: 1.64 au) exceed the mormal range. (Max. Sun distance: 1.52 au) ≪ Ion engine Ion engine cannot be used for about 140 days Ion engine cannot be used for about 100 days conditions before/after Venus swing-by (0.71 au) before/after asteroid fly-by (0.77 au) If trouble occurs during the Venus swing-by, the orbit Even if the asteroid fly-by cannot be implemented, there Scenario plan for the asteroid cannot be achieved (critical is no problem with the subsequent Earth swing-by and feasibility operation required in a high-risk environment) no major changes to the orbit plan are required. ≪ • The difference between the minimum solar distance of 0.71au and 0.77au, as well as the timing of the mission implementation make a big difference to the mission feasibility, and EAEEA is generally more feasible. • In addition to the thermal analysis here, the model uncertainty cannot be determined because we have no experiences. This results in a latent risk that should be supressed by minimising the deviation from the initial solar distance range. • Conclusion From a comprehensive judgement and evaluation from these situations, the EAEEA scenario with less deviation from the design premise for the solar distance range was selected in order to reduce risk. 2020/9/15 Hayabusa2 reporter briefing 9 2. Extended mission selection EAEEA scenario orbit sequence 1.5 1.5 2001CC21 Earth +'# Earth Venus 1 " && $#&'%' Venus 1 S/C 0.85AU S/C %'&* #, 0.5 0.5 ! $% ' 0 0 $% '& Y(J2000EC) [AU] -0.5 %'&* #, Y(J2000EC) [AU] -0.5 1.5 -1 Earth -1 1.5 !,, Venus Earth 1 0.85AU $% '& Venus -1.5 S/C 1998KY26 -1.5 1 -1.5 -1 -0.5 0 0.5 1 1.5 -1.5 -1 -0.5 0 0.5 1 1.5 1.41AU X(J2000EC) [AU] S/C 0.5 X(J2000EC) [AU] 0.5 0 %'&* #, 0 Y(J2000EC) [AU] -0.5 $% ' Y(J2000EC) [AU] -0.5 %'&* #, -1 -1 !,, %#-)$(& -1.5 -1.5 . "% '0/ -1.5 -1 -0.5 0 0.5 1 1.5 -1.5 -1 -0.5 0 0.5 1 1.5 X(J2000EC) [AU] X(J2000EC) [AU] 2020/9/15 Hayabusa2 reporter briefing 10 2. Extended mission selection EAEEA scenario mission sequence time Event Engineering achievements Science achievements Acquisition of long-term fuel saving / labor Zodiacal light observation 202126/7 Cruise operation saving cruise operation technology Exoplanet observation Acquisition of asteroid proximity high-speed Asteroid2001 CC21 flyby technology Observation of L-type asteroids by close- 2026/7 Fly-by Acquisition of technology that contributes to range high-speed flyby. Planetary Defense Calibration of on-board equipment 2027/12 Earth swing-by 1 Multi (3rd) Earth swing-by achieved through lunar observations during Earth swing-by Calibration of on-board equipment 2028/6 Earth swing-by 2 Multi (4th) Earth swing-by achieved through lunar observations during Earth swing-by Progress of long-term deep space navigation (completion of the final phase) Elucidation of the formation and Target body 1998 Acquisition of fast rotator exploration evolution of fast rotating asteroids 2031/7 KY26 rendezvous technology Acquisition of science that contributes to Acquisition of knowledge contributing to Planetary Defense Planetary Defense technology 2020/9/15 Hayabusa2 reporter briefing 11 3.
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