运载火箭姿态控制速率陀螺自适应加权方法  

Rate gyro adaptive weighting method for launch vehicle attitude control

作　　者：江星宇 师鹏[1] 龚胜平 JIANG Xing‑yu;SHI Peng;GONG Sheng‑ping(School of Astronautics,Beihang University,Beijing 102206,China)

机构地区：[1]北京航空航天大学宇航学院,北京102206

出　　处：《振动工程学报》2024年第10期1758-1766,共9页Journal of Vibration Engineering

摘　　要：针对运载火箭反馈控制回路中弹性振动信号与刚体信号存在耦合,会明显降低姿控系统稳定性的问题,提出了一种速率陀螺自适应加权方法,该方法适用于弹性振动的模态振型斜率和频率存在偏差的情况。将速率陀螺观测信号转换为频域表达,采用插值离散傅里叶变换方法辨识弹性频率;基于频域信号提出了速率陀螺加权系数矩阵自适应更新算法,分步抑制了各阶弹性振动信号;开展了不同偏差情况下的仿真校验工作。仿真结果表明,速率陀螺自适应加权方法可实现对速率陀螺测量信号中弹性振动信号的显著抑制,从源头上减小弹性振动信号对姿控系统稳定性的不利影响,从而提高运载火箭姿态控制器的性能,降低控制器的设计难度。A rate gyro adaptive weighting method is proposed for the problem that the serious coupling of elastic vibration signals and rigid-body signals in the feedback control loop of flexible launch vehicles will significantly reduce the stability of the attitude control system.The method can be applied to the cases where there are deviations in the shape slope and frequency of elastic vibration.The rate gyro observation signal is converted into a frequency domain expression,and the interpolated discrete Fourier transform method is used to identify the elastic frequency.An adaptive updating algorithm for the rate gyro weighting coefficient matrix is derived based on the frequency domain,which eliminates the elastic vibration signals of each order in a stepwise manner.A simulation calibration is carried out under different cases of deviation.Simulation results indicate that the rate gyro adaptive weighting method can realize significant suppression of elastic vibration signals in the rate gyro measurement signals and reduce the adverse effect of elastic vibration signals on the stability of the attitude control system from the source.Thus the performance of the launch vehicle attitude controller is improved and the difficulty in the controller design is reduced.

关 键 词：运载火箭 姿态控制 刚-弹耦合 速率陀螺 模态振型斜率 

分 类 号：V448.1[航空宇航科学与技术—飞行器设计]