Abstract:

The problem of autopilot design during agile turn phase of over the shoulder launch is investigated, for air-to-air missile with blended actuators. A fourorder dynamics is established for a missile under both low angle of attack condition and high angle of attack condition. Sliding mode control based on nonsmooth Lipschitz continuous surface is introduced, and the stability proof of piecewise linear sliding mode is presented by using non-smooth analysis. Elevator control and lateral force control are designed separately based on the idea of equivalent control and switch control. The numerical simulation results verify that compared with regular linear sliding mode control, piecewise linear sliding mode control has good performance in improving dynamic and reducing error, and is especially efficient for blended control.