一种适用于弹性飞机飞行仿真的补丁方法  

Patch module method for flight simulation of flexible aircraft

作　　者：王培涵 吴志刚[1] 杨超[1] 孙晓旭 Peihan WANG;Zhigang WU;Chao YANG;Xiaoxu SUN(School of Aeronautic Science and Engineering,Beihang University,Beijing100191,China;Seahawk Aviation General Equipment Co.,Ltd.,Beijing 100070,China)

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191 [2]海鹰航空通用装备有限责任公司,北京100070

出　　处：《航空学报》2023年第6期80-96,共17页Acta Aeronautica et Astronautica Sinica

摘　　要：现代飞行器呈现轻结构、大柔性和低阻尼等特点,气动弹性效应成为不可忽视的因素,使得弹性飞机存在明显区别于刚性飞机的运动响应。由于弹性飞机飞行仿真需研究刚弹耦合方程,增加了建模和验证的难度。针对该问题,提出了一种适用于弹性飞机飞行仿真的补丁方法,通过广义气动力的拆分和测量信号弹性增量的叠加构成“补丁模块”,将该模块置入6自由度全量方程的刚性飞机飞行仿真中,实现弹性飞机的飞行仿真。该方法充分利用了原有刚性飞机的飞行仿真模型,简化了弹性飞机的建模过程,有利于开展后续工作。以某大展弦比无人机为例,基于“补丁模块”的弹性飞机飞行仿真分析给出了对应的配平方法,并在机动响应、气动力非线性和气动伺服弹性稳定性研究中验证了该飞行仿真方法的可行性和准确性。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.

关 键 词：弹性飞机 飞行仿真 飞行力学 气动弹性 刚弹耦合 非线性气动力 

分 类 号：V212.12[航空宇航科学与技术—航空宇航推进理论与工程]