Analytical-Solution-Based Autopilot Design for Airdrop of Cruise Missile Equiped with Parachute

Abstract

after being delivered from aircraft, a cruise missile needs to decelerate by parachute to meet the requirements for engine ignition, especially on altitude, speed, and angle of attack (AOA). Thus, a new autopilot design problem arises, where the effect of parachute should be taken into account. During the falling, the parachute exerts a huge force on the missile through the hinge point, which makes the traditional autopilot lose potency. In this paper, the analytical solution for hinge force is deduced and used to establish a new attitude dynamics model. By linearizing the new dynamics model and using pole placement method, a new three loop autopilot considering the effect of parachute is put forward. The superiority of the new autopilot is verified by conducting trajectory simulations.