变后掠变展长飞行器动力学建模与动态响应分析

飞行器机翼后掠角和展长动态变化时，气动力、转动惯量、压力中心和质心等关键参数都发生剧烈变化。基于Newton-Euler方法建立了包含5个刚体的变后掠变展长飞行器的动力学模型，推导了由于变形所产生的附加气动力和气动力矩。在纵向上解耦简化了动力学方程，基于准定常气动力模型，分析了不同变形形式和变形速度下的纵向动态响应。研究结果表明，后掠角和展长的变化对动力学特性影响较大，但不同的变化速度对结果影响不大。通过合适的变形方式和变形速度的结合可以弱化变形过程中的动力学参数波动，减小控制系统的负担。

Dynamic Modeling and Response of a Morphing UAV with Variable Sweep and Variable Span

For morphing flight vehicles, the changes of sweep angle and span have great influence on key parameters such as aerodynamic forces, inertial moments, pressure center and gravity center. A dynamic model of morphing vehicle with variable sweep and span is established based on Newton-Euler method. The additional force and moment generalized by morphing are deduced. The dynamic response aroused by morphing is studied using decoupled longitudinal equations and quasi-steady aerodynamic model. The results indicate that the changes of sweep and span influence the dynamic characteristics severely; however, the effect of different morphing speed is not remarkable. Appropriate strategy of morphing could weaken the fluctuation of dynamic parameters and relieve the burden of control system.