The disturbance effect of random wind on missile is analyzed. A proportional navigation guidance system model with random wind disturbance is built and then simplified．The analytic solution is obtained by using adjoint method. Finally, the original proportional navigation guidance system is analyzed in detail. The analytic solutionof the simplified model demonstrates that the miss distance caused by random wind varies as the standard deviation of random wind velocity and trends towards a constant value with the guidance time increase. Simulation results show that the increase of proportion navigation coefficient is beneficial to inhibit the harmful influence of random wind on the guidance precision，either improving autopilot response or reducing the damping coefficient have the same effect.
Key words
control and navigation technology of aerocraft /
random wind /
proportional navigation /
guidance precision /
adjoint method
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