摘要
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.
作者
刘燕斌
陈柏屹
肖地波
沈海东
陆宇平
LIU YanBin CHEN BoYi XIAO DiBo SHEN HaiDong LU YuPing(College of Astronautics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China College of Automation Engineering, Nanjing University of Aeronautics andAstronauties, Nanjing 210016, China)
出处
《中国科学：技术科学》
EI
CSCD
北大核心
2016年第10期1024-1038,共15页
Scientia Sinica(Technologica)
基金
国家自然科学基金(批准号:61403191,11572149)
江苏省自然科学基金(编号:BK20130817)
中央高校基本科研业务费专项资金(编号:NJ20160052)
江苏省研究生科研创新基金(编号:KYLX_0281)资助项目
关键词
高超声速飞行器
参数化建模
控制一体化
迭代设计
稳定性
hypersonic vehicles, parametric modeling, control integration, iterative design, stability
