HAYABUSA MarkII Reentry Capsule

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HAYABUSA Mark-IIReentry Capsule

• Contents
• Japanase Experience in Reentry Capsule Missions
• Hayabusa Capsule
• What is different in Mark-II
• What is the Mark-II Reentry Capsule like?
• Japanese Reentry Technology Potential

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ISAS/JAXA Reentry Missions
Reentry Researchers in ISAS have been engaged
in...
Whats Next ? we would answer Planetary Entry
! Hi-Speed Reentry
USERS/REV dedicated to µG Experiment ISAS
cooperate with USEF on Research
Activities Launched Sept/2002 Recovered May/2003
HAYABUSA Asteroid Sample Return Launched
April/2003 Arrive at Asteroid Aug/2005 Return
June/2010
DASH Launched Mar/2002 -Hyperbolic
Velocity -Precursor for M-C
EXPRESS Launched Jan/1995 Reentry Tech.
Acquisition
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HAYABUSA Reentry Capsule
Heatshield Surface
with MLI attached
Exploded View
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Hayabusa Reentry Sequence
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HAYABUSA-2 Capsule
Same Size with Hayabusa-1 Weight 17kg Diamter
40cm
Flight Environment almost same as
Hayabusa-1 Maximum Heat Flux 16 MW/m2 Total
Heat Input 240 MJ/kg
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MK-II Capsule Development Issues

• Shape, Size
• Sampler?! Accomodation of Parachute Systems.
• ? Aerodynamic Heating,
• Flight Performance(Aero. Coeff.,Gravity
  Center,etc.)
• Parachute Systems, Recovery Systems?
• Supersonic Parachute?!
• Thermal Protection System
• Severe Aerodynamic Heating

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MK-II SRC Reentry Condition
Vinf 9 km/s V0, entry 14.2
km/s FlightPassAngle 11 deg
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Aerodynamic Heating of Mk-II
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Capsule TPS Designing
Heat flux should be within Ground Environment
Simulator Performance ?Shallow Entry
ASAP ?Increase in the Total Heat Input Q can be
covered by the Thickness of the Ablator
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Ablator Technology
Japanese Ablator Technology (labo., manufacture
level, flight-proven) High Heat Flux Ablator ? ?
1.3 g/cc for 3 MW/m2 (USERS) and 15 MW/m2
(hayabusa) Lite-weight Ablator ? ? 0.4-0.5 g/cc
for 3 MW/m2 (Manu.) Super-Lite-Weight Ablator ? ?
0.2-0.3 g/cc for 3 MW/m2 (labo)
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Numerical Analysis Technology
Nonequilibrium Reacting Flow Analysis Code with
multi-temperature model, ablation product,
radiation-coupled analysis considered. 2-D
Ablation Analysis Code with Internal Pressure of
Pyrolysis Gas, Mechanical Erosion
considered. Radiation Analysis Code SPRADIAN
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ISAS Arc Windtunnel Facility