This paper presents a methodology to combine a rigid-body and non-linear aerodynamic model of a hypersonic entry vehicle and provide bounds on the entry conditions required to ensure the vehicle maintains its attitude within prescribed limits. The non-linear aerodynamic model is based on parametric fits of the vehicle’s aerodynamic coefficients found using the computation tools US3D and MGDS. The vehicle’s equations of motion are separated into a nominal, linear time-invariant portion and a sector-bounded static memoryless non-linearity. Properties of the non-linearity are exploited to quantify the vehicle’s dynamic stability using integral quadratic constraint theory. Numerical results demonstrate that the non-linear aerodynamic model can be accounted for when assessing dynamic stability.
|Original language||English (US)|
|Title of host publication||AIAA AVIATION 2020 FORUM|
|Publisher||American Institute of Aeronautics and Astronautics Inc, AIAA|
|Number of pages||19|
|State||Published - 2020|
|Event||AIAA AVIATION 2020 FORUM - Virtual, Online|
Duration: Jun 15 2020 → Jun 19 2020
|Name||AIAA AVIATION 2020 FORUM|
|Conference||AIAA AVIATION 2020 FORUM|
|Period||6/15/20 → 6/19/20|
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.
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