The invention provides a control surface distribution scheme adjustment method for dynamically adjusting the maneuverability of an aircraft. The method comprises the following steps: acquiring a high-maneuverability first control surface distribution scheme under an X-shaped rudder sheet layout; obtaining a low-maneuverability second control surface distribution scheme under the X-shaped rudder sheet layout; designing a transition algorithm during dynamic switching of the control surface distribution scheme; and based on a transition algorithm, dynamically switching the first control surface distribution scheme and the second control surface distribution scheme by utilizing the change of the dynamic pressure. According to the invention, the control surface distribution scheme is adjusted on line, so that moderate control surface control capability in the flight process is ensured.
本发明提供了一种动态调节飞行器操纵性能的舵面分配方案调整方法,获取X字型舵片布局下高操纵性的第一舵面分配方案;获取X字型舵片布局下低操纵性的第二舵面分配方案;设计舵面分配方案动态切换时的过渡算法;基于过渡算法,利用动压的变化,对第一舵面分配方案和第二舵面分配方案进行动态切换。本发明通过在线调整舵面分配方案,确保飞行过程中舵面操纵能力适中。
Control surface distribution scheme adjusting method for dynamically adjusting maneuvering performance of aircraft
一种动态调节飞行器操纵性能的舵面分配方案调整方法
2024-09-20
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
Aircraft control surface static balance moment adjusting device and adjusting method
European Patent Office | 2021
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