open access

https://hdl.handle.net/2115/71226

Aerodynamic-Heating Analysis of Sample-Return Capsule in Future Trojan-Asteroid Exploration

英語

2018-07

The American Institute of Aeronautics and Astronautics

Journal of thermophysics and heat transfer

32(3)

547-559

In sample-return missions, the reentry velocity of a sample-return capsule is expected to be approximately 15km/s; however, the reentry velocity of the Hayabusa sample-return capsule was 11.8km/s. Strong aerodynamic heating caused by a high velocity can damage the capsule during reentry. To overcome this, two designs of high-velocity reentry capsules were proposed. In one design, a rigid flare was attached to decrease the ballistic coefficient by increasing the front projected area. In the other design, the conventional Hayabusa sample-return capsule was used with no modifications. In this study, the aerodynamic heating of the high-velocity reentry capsules and the Hayabusa sample-return capsule was analyzed using numerical simulations. Plasma flow in the shock layer at the front of the capsules and expansion flow in the wake region around the capsules were investigated. The profiles of convective and radiative heat fluxes on the surfaces of these capsules were predicted. The heat fluxes at the stagnation points predicted by the present numerical simulation were in good agreement with that of the empirical models. At the strongest aerodynamic-heating altitude, the total heat fluxes at the rear of the high-velocity reentry capsules and the Hayabusa sample-return capsule were approximately 2% of those in front of the capsules.

学術雑誌論文

Accepted Manuscript

© 2018 American Institute of Aeronautics and Astronautics

0887-8722