Adaptive block dynamic surface control for integrated missile guidance and autopilot
نویسندگان
چکیده
منابع مشابه
Integrated Design of Agile Missile Guidance and Autopilot Systems
By P. K. Menon and E. J. Ohlmeyer Abstract Recent threat assessments by the US Navy have indicated the need for improving the accuracy of defensive missiles. This objective can only be achieved by enhancing the performance of the missile subsystems and by finding methods to exploit the synergism existing between subsystems. As a first step towards the development of integrated design methodolog...
متن کاملA Blended Autopilot for Dual Control Missile Using Generalized Predictive and Adaptive Terminal Sliding Mode Control
A blended autopilot algorithm is developed using generalized predictive control and adaptive non-singular terminal sliding mode control, for dual control missile steered by combination of aerodynamic fins and reaction jets. The blended algorithm considers the reaction jets control design prior due to its inherent control error, and then treats the aerodynamic fin control on the basis of the rea...
متن کاملNumerical SDRE Approach for Missile Integrated Guidance - Control
Numerical state-dependent Riccati equation based integrated guidance-control formulation is developed for an internally actuated missile. The dynamic system under consideration is of tenth order, making it tedious to algebraically manipulate the equations of motion into the state-dependent coefficient form central to the design methodology. A numerical approach based on previous research is dev...
متن کاملL1 Adaptive Controller for a Missile Longitudinal Autopilot Design
This paper considers application of L1 adaptive output feedback controller to a missile longitudinal autopilot design. The proposed adaptive controller has satisfactory performance in the presence of parametric uncertainties and time-varying disturbances. Simulations demonstrate the benefits of the control method and compare the results to Linear Quadratic Regulator (LQR) and Linear Quadratic G...
متن کاملIntegrated Autopilot and Guidance for Dual Control Missiles Using Higher Order Sliding Mode Control and Observers
An integrated Autopilot-and Guidance Algorithm is developed using Higher Order Sliding Mode Control, for interceptors steered by combination of aerodynamic lift, sustainer thrust and center of gravity divert thrusters. A smooth HOSM guidance generates flight path trajectory angular rates and attitude rate commands. The attitude rate maneuvers are aimed at producing desired aerodynamic lift and ...
متن کاملذخیره در منابع من
با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید
ژورنال
عنوان ژورنال: Chinese Journal of Aeronautics
سال: 2013
ISSN: 1000-9361
DOI: 10.1016/j.cja.2013.04.035