DESIGN METHOD OF ATTITUDE CONTROL SYSTEM FOR FLIGHT VEHICLE AND COMPUTER PROGRAM

摘要

According to an embodiment of the present invention, a method of designing a system for controlling a posture of a flight vehicle comprises the following steps of: setting a system natural frequency and a system attenuation coefficient to obtain a proportional gain and a differential gain; analyzing posture stability of a flight vehicle based on the proportional gain and the differential gain to obtain a gain margin and a phase margin; analyzing a relationship between the proportional gain and the differential gain, and the gain margin and the phase margin to define a gain-phase margin grid on a control gain design area having the gain margin as one of a horizontal coordinate axis and a vertical coordinate axis, and the phase margin as the other of the horizontal coordinate axis and the vertical coordinate axis; defining a lower limit of each of the gain margin and the phase margin on the control gain design area; defining an upper limit of a bending mode vibration transfer rate on the control gain design area; defining an upper limit and a lower limit of each of the system natural frequency and the system attenuation coefficient on the control gain design area; and selecting a control gain point satisfying the lower limit of the gain margin and the phase margin, the upper limit of the bending mode vibration transfer rate, and the upper limit and the lower limit of each of the system natural frequency and the system attenuation coefficient at the same time on the gain-phase margin grid.