高超声速飞行器姿态大偏离下的耦合动力学建模与控制研究

项目名称： 高超声速飞行器姿态大偏离下的耦合动力学建模与控制研究

项目编号： No.91216102

项目类型： 重大研究计划

立项/批准年度： 2013

项目学科： 数理科学和化学

项目作者： 向锦武

作者单位： 北京航空航天大学

项目金额： 75万元

中文摘要： 乘波体构型高超声速飞行器可用于天地往返系统及高速导弹，应用前景广阔。由于飞行动力学稳定性差，超燃冲压发动机工作条件苛刻等原因，飞行器容易发生工作状态大偏离，进而表现出与正常工作状态不同的耦合动力学行为。本项目在前期研究的基础上，采用理论、数值和半物理仿真相结合的研究方法，通过对大偏离下乘波构型高超声速飞行器以控制为目标的气动/热/推进/结构建模方法、非线性系统动力学特性分析、非线性系统不确定分析方法三方面的研究，建立一种能够反映乘波构型高超声速飞行器在飞行状态偏离设计工作状态下的气动/热/结构/推进耦合系统非线性动力学模型，展开对高超声速动力学耦合机理及系统稳定性的研究，给出大偏离飞行状态下恢复正常工作状态的控制策略。在此基础上，研究线性不确定分析方法对高超声速飞行器飞行动力学的适用度，以服务于高超声速飞行器总体设计和控制系统设计。

中文关键词： 高超声速飞行器；大迎角；气动力；全动尾翼；气动弹性

英文摘要： Near space air-breathing hypersonic waverider can be used as a solution to affordable space access or hypersonic missiles. At present, most researches are conducted on the coupling dynamics of hypersonic vehicles at design condition. But the vehicle would exhibit totally different property of dynamical behavior at off-design conditions, which are easy to happen due to the poor stability of flight dynamics and intractable uncertainties of Scramjet. The project is based on the previous studies and the research method combined with theoretical analysis and numerical simulations are still adopted. Three control-oriented aspects of hypersonic waverider at off-design conditions are investigated, including modeling method for aerodynamics/thermodynamics/structural dynamics/propulsion coupled dynamic system, global characteristics of nonlinear flight mechanics and method for nonlinear system with uncertainties. The dynamical model is developed for the airframe/propulsion integrated hypersonic waverider for the off-design conditions as large angle of attack or high speed roll. The coupling mechanism of subsystems and stability is revealed, and control strategies for recovering from the off-design conditions are purposed. The quantitative analysis are conducted and the adaptability of methods for uncertainty propagation i

英文关键词： hypersonic vehicle；high angle of attack；aerodynamic；all-movable tail；aeroelastic