TY - JOUR
T1 - Longitudinal aerodynamic modeling and verification for air-launch-to-orbit system during stage separation
AU - Yang, Lei
AU - Ye, Zhengyin
AU - Li, Wenhao
AU - Sun, Quanhua
N1 - Publisher Copyright:
© 2021 Elsevier Masson SAS
PY - 2021/10
Y1 - 2021/10
N2 - The stage separation is one of key issues for air-launch-to-orbit system. In this process, the elastic deformation of carrier causes periodic pulsation in interference aerodynamics and may lead to modal coupling and dynamics instability of spacecraft. The dynamic responses and stability of the two vehicles should be considered carefully. The CFD-based dynamic simulation method has high accuracy but requires large computation cost. In this study, a new reduced-order modeling method is developed, which is for unsteady aerodynamics of the air-launch-to-orbit system with considering the elastic deformations of carrier. Based on the physical mechanism of interference aerodynamics factors, the model input parameters are decoupled and the modeling difficulty is reduced. By coupling the unsteady aerodynamic model, structural dynamics equations and rigid body dynamic equations, the longitudinal dynamic responses of air-launch-to-orbit system during stage separation are simulated. Through comparison, those results have good agreement with traditional CFD-based method, and the simulation efficiency of new method is improved greatly. The new modeling method is applicable to the air-launch-to-orbit system and can provide guidance for similar engineering issues.
AB - The stage separation is one of key issues for air-launch-to-orbit system. In this process, the elastic deformation of carrier causes periodic pulsation in interference aerodynamics and may lead to modal coupling and dynamics instability of spacecraft. The dynamic responses and stability of the two vehicles should be considered carefully. The CFD-based dynamic simulation method has high accuracy but requires large computation cost. In this study, a new reduced-order modeling method is developed, which is for unsteady aerodynamics of the air-launch-to-orbit system with considering the elastic deformations of carrier. Based on the physical mechanism of interference aerodynamics factors, the model input parameters are decoupled and the modeling difficulty is reduced. By coupling the unsteady aerodynamic model, structural dynamics equations and rigid body dynamic equations, the longitudinal dynamic responses of air-launch-to-orbit system during stage separation are simulated. Through comparison, those results have good agreement with traditional CFD-based method, and the simulation efficiency of new method is improved greatly. The new modeling method is applicable to the air-launch-to-orbit system and can provide guidance for similar engineering issues.
KW - Aerodynamic modeling
KW - Air-launch-to-orbit
KW - Dynamic simulation
KW - Interference aerodynamics
KW - Store separation
UR - http://www.scopus.com/inward/record.url?scp=85110088669&partnerID=8YFLogxK
U2 - 10.1016/j.ast.2021.106915
DO - 10.1016/j.ast.2021.106915
M3 - 文章
AN - SCOPUS:85110088669
SN - 1270-9638
VL - 117
JO - Aerospace Science and Technology
JF - Aerospace Science and Technology
M1 - 106915
ER -