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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.
Based on the Kane method, the variant motion is assumed to be a known controllable input, and the constraint equations are used to represent the deformation of the wing. The selection of the physical model of a variant aircraft with variable length and variable sweep angle is simplified. The displacement velocity of the aircraft and the six components of the angular velocity in the body coordinate system are taken as the generalized velocity and the six-degree-of-freedom dynamics model of the variant aircraft is established. The concepts of additional force and additional torque are defined to describe the effect of the variant motion on the aircraft The simulation results show that under steady flight conditions, the additional force and additional moment generated by the wing deformation are smaller than the aerodynamic changes caused by the deformation.At different speeds of deformation, The simulation results show that the aircraft altitude, velocity and pitch angle will change greatly during the variant process.