一种变体飞行器的动力学建模与动态特性分析

对可变展长、可变后掠角的变体飞行器物理模型进行了简化,基于Kane方法,将变体运动假设为已知的可控输入,利用约束方程来表示机翼的变形运动,选取飞行器位移运动速度以及角速度在机体坐标系下的6个分量作为广义速率,建立了该变体飞行器的六自由度动力学模型.定义了附加力与附加力矩的概念用于描述变体运动对飞行器产生的动力学影响,仿真结果表明,在平稳飞行条件下,相对于变形引起的空气动力的变化,机翼变形产生的附加力和附加力矩都较小.在不同的变形速度下,对变体引起的飞行器纵向运动响应进行了仿真分析,仿真结果表明,变体过程中飞行器的高度、速度以及俯仰角等状态均会发生很大变化.

Dynamic modeling for a morphing aircraft and dynamic characteristics analysis

The physical model of a variable-span variable-sweep morphing aircraft was simplified. Based on Kane's method, the morphing movements were assumed to be controllable known input, and the wings' movements were expressed by constraint equations. The six components of the translational velocity and the angular velocity of the morphing aircraft's body in the body coordinate frame were selected as the generalized speeds. Six degree-of-freedom dynamic model was built. Additional forces and additional moments were defined to describe the dynamic influence imposed on the morphing aircraft by the morphing movement. The simulation results show that, in the condition of steady-state flight, the additional forces and moments cased by the wings' morphing are small compared to the variations of aerodynamic forces. The aircraft's longitudinal dynamic responses during the morphing process are simulated and analyzed at different morphing speeds. Results show that the aircraft's height, velocity and pitch angle will change considerably during morphing process.