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

摘要

According to an embodiment of the present invention, in the method of designing a system for controlling the attitude of a vehicle, setting a system natural frequency and a system attenuation coefficient to obtain a proportional gain and derivative gain, and based on the proportional gain and differential gain, Analyze attitude stability to obtain gain and phase margins, and analyze the relationship between proportional and differential gains and gain and phase margins.The gain margin is one of the horizontal and vertical axes, and the phase margin is the horizontal and Defining a gain-phase margin grating on the control gain design region of the other one of the vertical coordinate axes, defining a lower limit of each of the gain margin and phase margin on the control gain design region; Defining an upper limit specification of the bending mode vibration transfer rate, the system natural frequency and the system on the control gain design area. Defining the upper and lower limits of each of the damping coefficients, the lower limit of the gain margin and phase margin on the gain-phase margin grid, the upper limit specification of the bending mode vibration transfer rate, and the system natural frequency and system damping coefficient, respectively. Disclosed is a method for designing a vehicle attitude control system including selecting a control gain point that simultaneously satisfies an upper limit specification and a lower limit specification.