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针对高超声速飞行器复杂的运行环境以及强耦合的动力学特性,提出了一种适合控制一体化迭代设计的参数化模型.首先,讨论高超声速飞行器控制一体化迭代设计的必要性和研究现状.然后,采用二次曲线和状态类型函数法将典型的高超声速乘波体外形进行几何参数化.接着,基于面元法结合工程估算公式获取高超声速飞行器力和力矩,构建参数化的非线性动力学模型.进而,采用灵敏度分析策略得到力和力矩的解析表达式,将复杂的非线性动力学模型简化成适合迭代设计的仿真模型.最后,通过仿真实例验证了本文所提方法的可行性,结果表明所发展的参数化模型能够满足高超声速飞行器控制一体化迭代设计的需要.
Aiming at the complex operating environment of hypersonic vehicle and the dynamic characteristics of hyperelastic vehicle, a parametric model suitable for controlling integrated iterative design is proposed.Firstly, the necessity and research status of integrated iterative design of hypersonic vehicle are discussed. Then , The shape of a typical hypersonic multiplicator body is geometrically parameterized by means of the quadratic curve and the state type function method.Finally, the hypersonic vehicle forces and moments are obtained based on the surface element method and the engineering estimation formula, and the parametric nonlinear dynamics Model.And then, the analytic expressions of force and moment are obtained by the sensitivity analysis method, and the complex nonlinear dynamic model is simplified to a simulation model suitable for iterative design.Finally, the feasibility of the method proposed in this paper is verified by the simulation example. The results It shows that the developed parametric model can meet the needs of hypersonic vehicle control integrated iterative design.