Simulation design method for flight path flight control system of patrol bomb and control system

Abstract

The invention discloses a simulation design method for a flight path flight control system of a patrol bomb and the control system. The method comprises the following steps: establishing a trajectorysimulation mathematical model of the patrol bomb; designing control parameters of the patrol bomb track flight control system based on the L1 nonlinear track guidance law, the STT stability control law and the rolling stability control law; obtaining a six-degree-of-freedom controlled trajectory simulation program of the patrol bomb; adding the interference factors and the deviation coefficient table into a six-degree-of-freedom controlled trajectory simulation program of the patrol bomb; developing a six-degree-of-freedom controlled ballistic simulation test of the patrol bomb according to the deviation coefficient table, and outputting a simulation result; judging whether the simulation result meets the expected requirement or not, and if not, skipping to the step 2 and redesigning the control parameters; and if so, ending the design process. The problems of pneumatic and control coupling, projectile body motion dynamic noise, seeker image rotation and the like caused by projectile body rotation can be solved, and the flight path flight combat efficiency of the pneumatic layout patrol projectile can be effectively improved.

Description

technical field [0001] The invention belongs to the field of loiter bomb track flight control, in particular to a simulation design method of a loiter bomb track flight control system and the control system. Background technique [0002] Based on the demand for the improvement and optimization of the flight combat effectiveness of the aerodynamic layout cruise missile trajectory, it is necessary to optimize the design and simulation verification of the cruise missile trajectory flight control system. At present, the trajectory flight control system of the cruise missile is mainly designed based on the BTT (bank and turn) control law, which has the following disadvantages: [0003] 1. The BTT control method is used to control the trajectory flight of the loitering bomb, and the loitering bomb needs to rotate around the longitudinal axis at any time. [0004] 2. The rotation of the missile body is easy to produce aerodynamic and control coupling, and at the same time, it will...

AI Technical Summary

Problems solved by technology

[0008] The object of the present invention is to provide a simulation design method of a flight control system for loitering missiles and the control system, which can solve the problem of aerodynamic and control coupling and the dynamics of missile movement brought about by the rotation of the missile body. Problems such as noise and seeker image rotation can effectively improve the combat effectiveness of the aerodynamic layout cruise missile track flight

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