Journal of Guidance Control and Dynamics · 2008 · 172 citations · 23 references
EngineeringAerospace EngineeringMechanical EngineeringFlight DynamicsFlight MechanicsRoboticsAttitude ControlManeuveringManeuvering ControlMissile ControlMissile Flight DynamicsTrajectory DynamicsAutopilot ControlAutopilot DesignGuidanceIntegrated GuidanceMissile Trajectory DynamicsNonlinear Missile DynamicsRobust Missile ControlSliding Mode Control
The study develops an integrated autopilot and guidance algorithm based on higher‑order sliding mode control that remains robust to target maneuvers and missile model uncertainties for interceptors using aerodynamic lift, sustainer thrust, and center‑of‑gravity divert thrusters. The algorithm employs a smooth higher‑order sliding mode guidance that generates flight‑path trajectory and attitude rate commands, uses attitude maneuvers to produce aerodynamic lift or orient sustainer thrust, treats lateral acceleration as a cooperative disturbance, incorporates a nonlinear dynamic sliding manifold autopilot, adds seeker/tracker bore‑sight stabilization and target lateral acceleration estimation, and is validated in computer simulations against a ballistic maneuvering target.
An integrated autopilot and guidance algorithm, robust to target maneuvers and missile’s model uncertainties, is developed using higher-order sliding mode control for interceptors steered by a combination of aerodynamic lift, sustainer thrust, and center-of-gravity divert thrusters. A smooth higher-order sliding mode guidance that is robust to target maneuvers generates flight-path trajectory angular rates and attitude rate commands. The attitude rate missilemaneuvers are aimed at producing desired aerodynamic lift and/or orienting the sustainer thrust. The lateral acceleration created by themissile attitudemaneuver is treated as a cooperative disturbance andaccounted for by the trajectory control. Robust to themissile’smodel uncertainties, higher-order (second-order) slidingmode autopilot is designed based on a nonlinear dynamic slidingmanifold. The proposed integrated autopilot and guidance algorithm also includes seeker/tracker bore-sight stabilization and estimation of target lateral acceleration. The algorithm is tested using computer simulations against a ballistic maneuvering target.
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