Patch module method for flight simulation of flexible aircraft

被引：0
作者：
Wang P. [1 ]
Wu Z. [1 ]
Yang C. [1 ]
Sun X. [2 ]
机构：
[1] School of Aeronautic Science and Engineering, Beihang University, Beijing
[2] Seahawk Aviation General Equipment Co. ，Ltd., Beijing
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2023年 / 44卷 / 06期
关键词：
aeroelasticity; flexible aircraft; flight dynamics; flight simulation; nonlinear aerodynamics; rigid-elastic coupling;
D O I：
10.7527/S1000-6893.2022.27038
中图分类号：
学科分类号：
摘要：
Modern aircrafts increasingly exhibit characteristics of light structure，large flexibility，and low damping，while the aeroelastic effect has become an important factor，enabling significantly different motion responses of flexible aircraft from those of rigid aircraft. However，the demand to solve rigid-elastic coupling equations increases the difficulty in modeling and validation of flexible aircraft. This paper proposes a patch module method suitable for flight simulations of flexible aircraft. This patch module" consists of decomposition of generalized aerodynamic forces and superposition of incremental measurement signals of elastic vibrations. Then it is embedded into flight simulations of six-degree-of-freedom full equations of rigid aircraft to transform them into those of flexible aircraft. This method fully utilizes the original model of rigid aircraft，simplifies the modeling process of flexible aircraft，and contributes to the development of subsequent projects. Numerical results of an unmanned aerial vehicle with a large aspect ratio are obtained through flight simulations of flexible aircraft based on the patch module method，and the corresponding trim methods are introduced. The feasibility and accuracy of the flight simulation method are validated during the study of maneuvering response，aerodynamic nonlinearity and aeroservoelastic stability. © 2023 AAAS Press of Chinese Society of Aeronautics and Astronautics. All rights reserved."
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