高超音速飞机总能量控制系统的设计和应用  

Design and Application of Total Energy Control System for Hypersonic Vehicle

作　　者：刘燕斌[1] 陆宇平[1] 何真[2] 

机构地区：[1]南京航空航天大学航天学院,江苏南京210016 [2]南京航空航天大学自动化学院,江苏南京210016

出　　处：《应用基础与工程科学学报》2008年第1期128-135,共8页Journal of Basic Science and Engineering

基　　金：国家863计划资助项目(2003AA755021)

摘　　要：为了解除高超音速飞机飞行速度与航迹角之间的强耦合,设计了基于总能量原理的飞行控制系统,该原理的核心思想是采用高超音速飞机发动机的推力来控制总能量,而升降舵用于调节总能量的分配,通过协调升降舵和发动机节流阀调定指令,达到合理增加和分配能量的目的,确保其具有良好的非线性解耦控制能力及强鲁棒性能.仿真结果表明,本文所设计的控制系统对于高超音速飞机是可行的.In order to relieve the decoupling on flight velocity and flight path angle for hypersonic vehicle, this paper designs fight control system based on total energy theory. Its core ideas are to use the thrust of hypersonic vehicle engine to control the total energy and the elevator to adjust the distribution of the total energy. By coordinating the elevator and the engine throttle setting commands, the goal about increasing and assigning the energy reasonably can be achieved, which will ensure the good nonlinear decoupling ability and the strong robustness for hypersonic vehicle. The simulation studies demonstrate the control system in this paper is feasible for hypersonic vehicle.

关 键 词：纵向飞行控制 高超音速飞机 总能量控制理论 非线性解耦控制 

分 类 号：V271.9[航空宇航科学与技术—飞行器设计]