高超声速飞行器面向控制一体化迭代设计的参数化模型

A parametric model for control integrated design of hypersonic vehicles

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 to the complex operation condition and strong coupling dynamic characteristics of hypersonic vehicles, this paper develops a parametric model which is suitable to the control integrated design. First, the necessities and research status of the control integrated design of hypersonic vehicles are discussed. Then, the typical hypersonic waverider shape is geometrically parametrized using the quadratic curve and class/shape function methods. After that, the forces and moments of the hypersonic vehicle are estimated based on the surface element method in combination with the engineering estimation formulas, and the nonlinear dynamic parametrization model is built. Furthermore, the analytical expressions of forces and moments are obtained by means of the sensitive analysis strategies as a result that the complicated nonlinear dynamics model is changed to the iterative design model. Finally, an illustrative example is provided to verify the feasibility of this proposed method, and the according results show that the developed parametrization model enables to meet the requirements of the control integrated design.