A pitch autopilot design for blended aero and reaction-jet air-to-air missile via piecewise sliding mode control

摘要

In this paper, the problem of blended aerodynamic and reaction-jet autopilot design for air-to-air missile with over-the-shoulder (OTS) launch capability is investigated, and a novel sliding mode control (SMC) approach with piecewise smooth sliding surface is applied to solve the problem. Considering the multi-actuator configuration of the agile missile, a four-order dynamical model is established where the reaction-jet control system (RCS) is arranged at the tail of the missile. By introducing piecewise sliding mode control (PSMC), elevator control and lateral force control are designed separately based on the idea of equivalent control and switched control. By the means of Gauss pseudospectral method (GPM), a minimum time optimal pitch command is obtained for numerical simulation. The simulation result verifies the effectiveness of PSMC for the blended control system.