This paper outlines the main design considerations of a CubeSat-like, miniature re-entry vehicle, HyCUBE. that will serve as a versatile hypersonic flight test platform. HyCUBE’s proposed first mission aims to collect experimental measurements of the aerothermodynamic environment that vehicles moving at hypersonic speeds encounter during re-entry from low Earth orbit. The data to be collected will contribute to the improvement and validation of computational models. Numerical simulations were used to establish the aerodynamic characteristics of the proposed vehicle, to evaluate the heat-load such that the thermal protection system can be sized, and to guide sensor placement and selection. The direct Simulation Monte Carlo (DSMC) method and computational fluid dynamics (CFD) were used where applicable, as well as analytical tools for the vehicle’s computed trajectory. Preliminary designs for the form factor and sensor suite are proposed and discussed.
|Original language||English (US)|
|Title of host publication||AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021|
|Publisher||American Institute of Aeronautics and Astronautics Inc, AIAA|
|State||Published - 2021|
|Event||AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021 - Virtual, Online|
Duration: Aug 2 2021 → Aug 6 2021
|Name||AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021|
|Conference||AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021|
|Period||8/2/21 → 8/6/21|
Bibliographical noteFunding Information:
This research is supported by the Air Force Office of Scientific Research (AFOSR) under Grant No. FA9550-19-1-0308. The views and conclusions contained herein are those of the authors and should not be interpreted as necessarily representing the official policies or endorsements, either expressed or implied, of the AFOSR or the U.S. Government.
© 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.