2009.3.1

9 1 Institute of Fluid Science, Tohoku University

Spacecraft Thermal and Fluids Systems Laboratory, Institute of Fluid Science

Nagai∙Fujita Lab.

Lab HP: http://www.ifs.tohoku.ac.jp/space/ E-mail: nagai.hiroki@tohoku.ac.jp

Study of aerodynamic characteristics and heating phenomena when a space vehicle enters into planet atmosphere

Development of thermal control device and innovative thermal system for next-generation spacecraft

Study and Development of Mars airplane / helicopter

Progressive visualization, measurement technique challenge under extreme environment

Aerodynamic heating of Hypersonic airplane

HIFiRE-1 model in JAXA-HIEST

Study of Mars airplane

Martian hole and lava tube exploration using rotorcraft

Thermal control of spacecraft (Understand and manage the heat)

Aerospike Model

Loop Heat Pipe Oscillating Heat Pipe

Aerodynamic heating (Database for spacecraft design)

Compression Corner Model

N

N

N

NM

FF

F

F

F

FF

F

F F

F

FF

F

F

F F

F

FF

N

N

N

NM

FF

F

F

F

FF

F

F F

F

FF

F

F

F F

F

FF

Re-entry Capsule

Micro-nozzle

Thermal / aerodynamic measurement in extreme conditions （High / low temperature, Reynolds number, Mach number, Knudsen number）

NN

NN

N

NRu

2+CH3

Si(CH3)3

n

Thermal Analysis of Mars Airplane

groove

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