SDRE AUTOPILOT FOR DUAL CONTROLLED MISSILES

Abstract The SDRE technique is used to develop an autopilot design for a dual controlled (tail and canard) missile. Dual control missiles can have difficulty achieving high angles of attack and thus high levels of lateral acceleration because the control surfaces move together to achieve quick responses but in steady state the deflections can be significantly larger than with only one control. The unique contribution of this paper is examining the effects of scheduling the design weights on state variables to solve this specific problem with dual controlled missiles. Output and control weights having dependence on the state variables are examined to overcome this problem.