Missile

About: Missile is a research topic. Over the lifetime, 12829 publications have been published within this topic receiving 94307 citations. The topic is also known as: guided missile & missiles.

Integrated Guidance and Control of Missiles With $theta hbox - D$ Method

Abstract: A new suboptimal control method is proposed in this study to effectively design an integrated guidance and control system for missiles. Optimal formulations allow designers to bring together concerns about guidance law performance and autopilot responses under one unified framework. They lead to a natural integration of these different functions. By modifying the appropriate cost functions, different responses, control saturations (autopilot related), miss distance (guidance related), etc., which are of primary concern to a missile system designer, can be easily studied. A new suboptimal control method, called the thetas-D method, is employed to obtain an approximate closed-form solution to this nonlinear guidance problem based on approximations to the Hamilton-Jacobi-Bellman equation. Missile guidance law and autopilot design are formulated into a single unified state space framework. The cost function is chosen to reflect both guidance and control concerns. The ultimate control input is the missile fin deflections. A nonlinear six-degree-of-freedom (6-DOF) missile simulation is used to demonstrate the potential of this new integrated guidance and control approach

Dynamic scheduling of modern-robust-control autopilot designs for missiles

Abstract: The dynamic scheduling of multiple linear-time-invariant (LTI) controllers, designed using H/sub infinity // mu techniques, for systems with widely varying plant dynamics is examined. The observer/full-state feedback structure of the LTI H/sub infinity / controller is extended to accommodate the time-varying, nonlinear dynamics problem. A procedure for handling the variations that occur between fixed operating points, in the two-Riccati equation solutions, is proposed. An example missile control problem that contains realistic and necessary performance goals and robustness constraints is included to demonstrate the viability of the approach. >

Back-stepping sliding mode control for missile systems based on an extended state observer

Abstract: A novel approach combining the sliding mode control and extended state observer (ESO) is proposed for attitude control of a missile model which is non-linear in aerodynamics. Combining the back-stepping technique, the corresponding sliding mode controller is designed to guarantee the state variables of the closed-loop system to converge to the reference state with the help of the ESO by estimating the unknown variable. Also, simulation results are presented to illustrate the effectiveness of the control strategy.

Integrated Higher-Order Sliding Mode Guidance and Autopilot for Dual Control Missiles

Abstract: 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.