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Planetary Protection of Hayabusa-2 Mission, a Sample Return from 1999 JU3, C-Type NEO

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Planetary Protection of Hayabusa-2 Mission, a Sample Return from 1999 JU3, C-Type NEO NASA Planetary Protection Subcommittee 2012 Planetary Protection of Hayabusa-2 Mission, a Sample Return from 1999 JU3, C-type NEO May 1-2, 2012 NASA Headquarters, Room 3H46, Washington, D.C., USA (via Teleconf/WebEx) Presented by Hajime YANO (JAXA/ISAS & JSPEC) and the Hayabusa-2 Project Team (PM: Makoto YOSHIKAWA) Motivation of This Presentation: To Receive Kind Understanding from International Partners and COSPAR PPP Resolution in 2012 for Hayabusa-2 USA NASA (e.g., DSN support, Airborne observation of the re- entry, Collaboration with OSIRIS-Rex, etc.) Australia SLASO/DIISR DoD/AOSG AQIS/AC (e.g., ERC recovery operation at Woomera, etc.) Europe DLR (e.g., Provision of the lander, Microgravity test facilities, etc.) Agenda (1) Hayabusa-2 Mission Description (2) Observed Nature of 1999 JU3 (3) COSPAR Six Questions for the 1999 JU3 Sample Return Mission Hayabusa-2 Mission Description Japan’s Primitive Body Exploration Program: Sample Return Strategy for “Further, Smaller, More Primitive” Objects Post Hayabusa Series Hayabusa Hayabusa-2 Hayabusa Mk-II (plan) Itokawa = S type 1999 JU3 = C type D type, Dormant comet (1996~/2003-10) Lessons Learned from Hayabusa Advanced, Full Model-change (2010~/2014-20) (Early 2020’s) Carbonaceous Ordinary Chondrites Chondrites C type S type D type Main Asteroid Belt IDP, Micrometeorites, Tagish Lake? 5 Major Spectral Types of Asteroids Related to Heliocentric Distances D-type ・Richer in organic materials ・Tagish Lake? S-type like objects S-type (Itokawa) ・Rock and metals ・Ordinary chondrites C-type like objects Distance from the Sun C-type ・Organic, hydrated minerals ・Carbonaceous chondrites (1999 JU3) Asteroid classification by spectral types 6 Hayabusa-2 Mission Outline: Follows the Hayabusa-1’s Path with Some New Additions June, 2018 : Arrival at 1999 JU3 The spacecraft observes the asteroid, Launch deploys multiple small landers/rovers, Dec. 2014 and conducts multiple samplings. (back-up 2015) The spacecraft carries Sample Analysis an impactor. New Challenges Earth Return Dec. 2020 Dec. 2019 : Departure The impactor reaches to the 2019 surface of the asteroid. Sampling will be attempted to a newly created crater if proven to be safe. 7 Purposes of Hayabusa-2 Project 1. Science Investigate “where we came from" • The origin and evolution of the Solar System • Life Precursor • The origin of the ocean water 2. Engineering Develop technology needed for the Solar System exploration • Improve technology heritage from Hayabusa for being more reliable and robust • New challenges, e.g., the impactor and the lander/rover(s) 3. Exploration Extend the area where humanbeings can reach • Deep space round trip • Spaceguard, resources, precursor for human mission, etc. 8 Approach to Scientific Objectives Thermal metamorphism Formation temperature, Target #1 from planetesimals to an experienced temperature, and present temperature Material asteroid environment characteristics of a C-type Processes of impact Density, porosity, crater, asteroid destruction and impact ejecta (boulders) accumulation Low temperature Target #2 Interaction between products, volatile Formation materials, water and hydrated mineral and process of the organics organics asteroid High temperature Material cycle in the products, refractory primitive solar system substances, and minerals 9 Hayabusa-2 Mission Schedule year 2014 2015 2016 2017 2018 2019 2020 month 12 06 12 06 08 12 12 Spacecraft IES operation Launch windows Earth Swing-by Departure Earth Arrival at Science from 1999 return 1999JU3 observation, JU3 Sampling IES operation Impactor 10 Hayabusa-2 Spacecraft Design Wet Mass：~600 kg cf. Hayabusa (510 kg) Size Comparison with OSIRIS-REx 11 Planned Payloads for Scientific Outcomes Payloads Specifications Multiband Imager Wavelength: 0.4 – 1.0 mm, FOV: 5.7 deg x 5.7 deg, (ONC-T) Pixel Number: 1024 x 1024 px; filter (ul, b, v, w, x, p) (Heritage of Hayabusa) Near IR Spectrometer Wavelength: 1.8 – 3.2 mm, FOV: 0.1 deg x 0.1 deg (NIRS3) (Heritage of Hayabusa except 3mm range, which is new) Thermal IR Imager Wavelength: 8 – 12 mm, FOV: 12 deg x 16 deg, (TIR) Pixel Number: 320 x 240 px (Heritage of Akatsuki) Laser Altimeter (LIDAR) Measurement Range: 50 m – 50 km (Heritage of Hayabusa) Sampler Minor modifications from Hayabusa-1 (Heritage of Hayabusa) Small Carry-on Impactor Small, deployable system to form an artificial crater on the surface (SCI) (New) Separation Cameras Small, deployable camera to observe the SCI operation (DCAM) (Heritage of IKAROS) Small Rovers Almost the same as MINERVA of Hayabusa-1 (MINERVA II-1, II-2) (Possible payloads: Cameras and thermometers) (Heritage of Hayabusa) Small Rover Contirbution from DLR (New): (MASCOT) MicrOmega, MAG, CAM, MARA (Heritage from PhobosGrunt, etc.) 12 Heritage from Hayabusa: Impact Sampling System Spacecraft Return Capsule (Sample Catcher & Container inside) Projectors (Up to three) • Collect sufficient amount of samples (>several 100 mg) Conical compliant with both monolithic Horn bed rock and regolith targets (Concentrator) • Projectors designed to fire a 5-g Extendable metal projectile at 300 m/s Fabric Horn • Powder cartridge and sabot to conceal residual gas during Metal (Al) sampling Horn with Dust Protection •“Ta” projectile not to spoil Skirt and LRF sample analysis with enough Trigger Target material strength Heritage from Hayabusa: Sample Collection Performance T = 1 msec T = 2 msec T = 4 msec T = 6 msec T = 10 msec T = 14 msec T = 22 msec T = 28 msec T = 37 msec T = 50 msec T = 58 msec T = 70 msec 100 1G-Monolith 1G-Gravels (0.1%) Double Impacts 1G-Gravels (1%) Double Impacts (1G 10mm Glass Balls) (1G 8mm Gravels) ) 1G-Regolith g ( Micro-G Monolith r 10 e l Micro-G Regolith p m a S e =Double Impacts h t (1G Monolith) n i 1 s s =30° a M =55° n o 55°= i t c e l 0.1 l o C =55° =55° (Yano, et al., Science, 2006) 45° = =55° =55° 55°= 0.01 1 10 100 1000 10000 ○：Monolith（>>10 mm） Ejected Mass from Target (g) □：Gravels（3~10mm） △：Regolith（<< 1mm） Heritage from Hayabusa: Direct Sampling Site Investigation by the Spacecraft * From experiences of the Hayabusa operation, physical properties, thermal inertia, close-up images of the sampling site can be measured by the Hayabysa-2 spacecraft 5m 35 30 XRS Radiator ] 25 20:53~57 ℃ [ ∙∙∙∙∙∙∙∙ 20 ± e 310 10 K k = 500 r u t 15 k = a ¾¾ r e 10 7000 p ´ ------- k = m 5 e T 20000 T 0 -5 (1)(2) (3) (4) -10 20:00:00 21:00:00 22:00:00 23:00:00 0:00:00 Time [UTC] Yano, et al., Science (2006) ＜Retrieval, Transport, Heritage from Hayabusa: Cleaning, Storing, Purging＞ ＜Soil Sampling＞ Landing of the ERC at Woomera in Australia in December, 2020 ＜International Witness＞ ＜Arrival to Curation Facility＞ ＜XCT Scanning＞ (From examples of the Hayabusa-1 ERC recovery) Heritage from Hayabusa: Curation Facility for Initial Sample Handling, Description and Storage like Itokawa Samples A New Challenge: Observe and Sample Excavated, Sub-Surface Materials by a Small Carry-on Impactor •~2 kg Cupper Projectile •Impact Velocity~ 2 km/s • Spin separation Impactor EFP（Explosively Formed Projectile） Demonstration Expected Crater Size: D~2-3m: Autodyn Simulation D~4 m: Takagi et al. D~7.4 m: Housen & Holsapple Hayabusa vs. Hayabusa-2 at a Glance: From Technological Challenges to Programmatic Sample Return Missions Hayabusa Hyabusa-2 Objectives C-type asteroid Verify key sample return technology needed and improvement for deep space round of the deep space trip exploration round trip exploration technology Mission Target Itokawa: S-type, sub-km NEO 1999 JU: C-type, 1-km NEO Major Payload •Sampling System •Sampling System Instruments •Earth Return Capsule •Earth Return Capsule •Multi-band Optical Camera •Small Carry-on Impactor with •LIDAR DCAM •Near Infrared Spectrometer •Multi-band Optical Camera •X-ray Fluorescence Spectrometer •LIDAR •Micro-Rover •3 mm Near Infrared Spectrometer •Thermal Imaging Camera •Micro-Rover •Micro-Lander Mission Epoch 2003-2010 2014-2020 19 Observed Nature of 1999 JU3 Near Earth Objects: Itokawa vs. 1999 JU3 at a Glance Earth Crossing Orbits Itokawa Mars Earth 1999 JU3 (162723) 1999 JU3 (C) (25143) Itokawa (CollageInternational (S) Courtesy:Space P.Station Lee, 2006) (Model Courtesy: Kaasalainen, et al., 2008) (Collage Courtesy: ~922 m P. Lee, 2006) Remote Sensing Studies: 1999 JU3, Hayabusa-2’s Target (1) Rotational Period Defined from Ground Observations P= 0.3178 days (~7.6 hours) (Kawakami, et al., 2008) Remote Sensing Studies: 1999 JU3, Hayabusa-2’s Target (2) Geometric Albedo and Size Estimated from Space and Ground Observations Albedo = 0.037, Diameter = ~980 m (Hasegawa, et al., 2008) Remote Sensing Studies: 1999 JU3, Hayabusa-2’s Target (3) Internal Structure Implied by Rotational Periods and Sizes Barrier at the rotation rate where a strengthless body would fling itself apart Itokawa 1999 JU3 (Pravec et al. 2002) Remote Sensing Studies: 1999 JU3, Hayabusa-2’s Target (4) Spectral Type Defined from Ground Observations Cg Type = SMASS classification for the absence (Kawakami, et al., 2008) of the absorption feature at 0.7 μm) Remote Sensing Studies: 1999 JU3, Hayabusa-2’s Target (5) Surface Dichotomy Expected from Ground Observations * Exhibits both absence and presence of C-type Asteroid absorption features similar to CM2 chondrites, implying two geological Iron-bearing units (weathered and fresh?) Phyllosilicates Jul ‘07 CM2 Sep ‘07 Carbonaceous Chondrites (Vilas, 2008) Meteoritic Studies: 1999 JU3, Hayabusa-2’s Target (6) Compressive Strength of Carbonaceous Meteorite Samples 5x10 mm Compressive Strength TL: Tagish Lake carb -r:
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