运载器起飞段姿态控制性能仿真(英文)  

Simulation of Launch Vehicle Attitude Control System Performance During Ascending Stage

作　　者：孙平[1] 刘昆[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《系统仿真学报》2008年第19期5297-5300,共4页Journal of System Simulation

摘　　要：姿态控制系统是运载器重要的子系统之一。建立了运载器起飞段侧喷流直接力姿态控制模型。运载器起飞段姿态受到诸多因素干扰,如:侧喷流干扰、姿控发动机启动延时、风干扰、结构干扰以及初始状态干扰等。衡量姿态控制系统性能的指标主要有:姿态控制精度及稳定度、侧喷流发动机燃料消耗及开机次数等。在Matlab/Simulink仿真环境下建立并综合了各种模型,根据实验数据进行了数值仿真。结果表明:在起飞段马赫数较小的情况下,侧喷流发动机能够满足运载器姿态控制的需求。The launch vehicle attitude control system is the most important subsystem to ensure launch vehicle flying with the scheduled trajectories. A launch vehicle with lateral jet as its attitude control mechanism during ascending stage was proposed The attitude of the launcher is affected by a lot of factors such as lateral jet interaction, the switch delay of the attitude control motors, the variation in normal wind conditions, the configuration error of the main thruster and the initial states of the attitude parameters. The main index to describe the system performance includes the accuracy of the attitude control system, the fuel consumption and the switching conditions of the motors. To simulate the performance of the attitude control system, separate models were established and integrated in Matlab/Simulink environment. Numerical simulation was performed based on the actual design parameters and disturbance data to evaluate the system performance. Simulation results are presented to validate the control effectiveness of the lateral jet on low Maeh condition.

关 键 词：运载器 姿态控制系统 侧喷流 仿真 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]