高超声速机动飞行的复杂动力学建模与自主控制

项目名称： 高超声速机动飞行的复杂动力学建模与自主控制

项目编号： No.11332001

项目类型： 重点项目

立项/批准年度： 2014

项目学科： 数理科学和化学

项目作者： 黄琳

作者单位： 北京大学

项目金额： 300万元

中文摘要： 高超声速飞行器控制是近年来国内外动力学与控制领域研究的热点，研制相关飞行器是我国航空航天部门的重大战略方向，其中高超声速机动飞行又是特别重要而又难以分析和控制的飞行阶段。本项目拟借鉴国外飞行器失败经验，针对一大类机动运动，如大攻角快速下压、大滚转、高度与速度的快速变化等，深入开展高速机动飞行动力学建模与控制课题研究。研究由于机动运动带来的姿态多通道耦合、姿态与轨迹耦合问题，建立能准确反映耦合特征的动力学模型，明确耦合因素对动力学特征的影响，给出高速机动飞行时姿态与质心运动的交互作用机理，建立姿态多通道解耦与耦合动力学分析与控制理论、姿态与轨迹分离设计和一体化设计理论与方法。在此基础上，结合一类高超声速滑翔飞行器，给出再入机动、滑翔机动、快速下压机动下的动力学分析与优化控制方法，以及高速机动飞行参数大范围变化与模型不确定性状态下的鲁棒自适应控制方法，并通过仿真实验验证方法的可行性和适应性。

中文关键词： 高超声速机动飞行;复杂动力学建模;自主飞行控制;运动稳定性;

英文摘要： Control of hypersonic flight vehicles is a hot research topic in the dynamics and control community in recent years and developing hypersonic flight vehicles is a strategic direction of the aeronautics and astronautics department of China. For hypersonic flight vehicles, hypersonic maneuvering is a very important fight phase which is quite difficult to analyze and control. Based on the analysis of the foreign failure hypersonic vehicles, this project will study the modeling and control problems of hypersonic maneuvering flight dynamics for a large class of maneuvering motions, e.g., fast descending of high angles of attack, large-amplitude roll motions, and fast changing of both the height and speed. We will investigate the coupling problems of the multiple attitude channels, and the coupling of the attitude and trajectories induced by the supersonic maneuvering motions. We will establish dynamical models to precisely describe the characteristics of the aforementioned couplings, identify the effects of the couplings on the dynamics, give the interacting mechanisms of the attitude and the motion of center of mass during hypersonic flights, and establish the decoupled and coupled control methods for the multiple channels of the attitude dynamics and the separated and integrated design theory and methods of the attitude and the trajectory. Furthermore, based on a class of hypersonic gliding vehicles, we will present control methods for reentry maneuvering, gliding maneuvering, and fast descending maneuvering, and give robust and adaptive control laws in the presence of large-range varying parameters and model uncertainties. Finally, the feasibility and adaptability of the proposed methods will be verified by numerical simulations and experiments.

英文关键词： Hypersonic maneuvering flight ;Complex dynamics modeling ;Autonomous flight control;Motion Stability