Study on reliability simulation for missile's flight control system

An approach of integrated analysis of performance and reliability for missile flight control system is proposed. The disturbance models of wind, structural errors (including missile mass asymmetry, body un-coaxial, airfoil installation angle error and rudder null position), thrust deviation and hardware failure are established. The method of reliability simulation, approach of implementation, the algorithm process and the formulas of computing reliability are given and the effects of these factors on the missile's reliability are analyzed by plenty of simulations. The X-missile flight control system is taken as an example.