Concepts and Studies of Flight Experiment Vehicles for Reusable Space Transportation System

Fujii, Kenji; Nakamura, Toshiya; Kawato, Hiroshi; Watanabe, Shigeya

doi:10.2514/6.2003-6984

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Piggyback Atmospheric Reentry Technology Testbed (Partt)1

Introduction1

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2006

2024

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Cited by 7 publications

(2 citation statements)

References 5 publications

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“…This section briefly overviews the PARTT system, while details have been given by Fujii et al [3,4].…”

Section: Piggyback Atmospheric Reentry Technology Testbed (Partt)mentioning

confidence: 99%

Probabilistic transient thermal analysis of an atmospheric reentry vehicle structure

Nakamura

Fujii

2006

Aerospace Science and Technology

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“…This section briefly overviews the PARTT system, while details have been given by Fujii et al [3,4].…”

Section: Piggyback Atmospheric Reentry Technology Testbed (Partt)mentioning

confidence: 99%

Probabilistic transient thermal analysis of an atmospheric reentry vehicle structure

Nakamura

Fujii

2006

Aerospace Science and Technology

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“…Therefore, numerous worldwide activities address the progress of supersonic and hypersonic airbreathing technology in the form of scramjets. [1][2][3][4][5][6][7][8] In Germany, the Research Training Group GRK1095 was initiated in 2005 9 to develop a sophisticated concept of a scramjet engine. This contribution deals with the analysis of the nozzle flow field including prediction and control of the thrust vector.…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation to Enhance the Thrust Vector of a Scramjet Nozzle

Meiss¹,

Schröder²,

Meinke³

2011

17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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Numerical investigations of the flow field of a supersonic single expansion ramp nozzle (SERN) and its interaction with a freestream of Ma=8 are conducted using Large-Eddy Simulations (LES) to allow accurate predictions of the high Reynolds number flow characterized by shocks and expansion waves, turbulent boundary and shear layers, and flow separation. The influence of selected parameters, i.e., boundary-layer thickness, wall temperature, gas composition, and flap angle on the thrust vector is determined to optimize the thrust vector. It will be shown that variations of boundary-layer thicknesses and wall cooling have inferior influence on the thrust compared to flap angle variations and change of the adiabatic exponent. A positive flap angle causes an increase of lift and drag, while a variation of the fluid, i.e., a gas at a lower adiabatic exponent than air, leads to a decrease of lift and drag.

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Inverse analysis for transient thermal load identification and application to aerodynamic heating on atmospheric reentry capsule

Nakamura

Kamimura

Igawa

et al. 2014

Aerospace Science and Technology

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Concepts and Studies of Flight Experiment Vehicles for Reusable Space Transportation System

Cited by 7 publications

References 5 publications

Probabilistic transient thermal analysis of an atmospheric reentry vehicle structure

Probabilistic transient thermal analysis of an atmospheric reentry vehicle structure

Numerical Investigation to Enhance the Thrust Vector of a Scramjet Nozzle

Inverse analysis for transient thermal load identification and application to aerodynamic heating on atmospheric reentry capsule

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