Skid-to-turn missile autopilot design using scheduled eigenstructure assignment technique

Abstract

This paper presents an application of adaptive control techniques to the design of skid-to-turn missile autopilot. The involved simplified adaptive controller is developed by combining gain scheduling approach with the eigenstructure assignment control design. A linear interpolation method is proposed to generate linear parameter-varying controller from a finite set of linear time-invariant controllers. Results of simulations are reported to demonstrate the performance, stability, and robustness of the considered autopilot.

Dynamic Sliding Mode Autopilot for Nonlinear Non-Minimum Phase Flight Vehicle

“…[8][9][10][11] The control objective is to force the air vehicle to track a desired motion path generated by the guidancenavigation system as the reference acceleration commands for the center of mass. The problem is first formulated and performance objectives are specified.…”

“…The classical approach being to design a controller for a certain point and then to schedule the controller's gain to place eigenvalues deep in the left half plane and the near real-axis according to measured or derived parameters that represent flight conditions, such as angle of attack or Mach number. 8) In another method, H 1 methods are invoked to design a collection of controllers, where, for each operating point in the flight envelope grid, a controller with a fixed structure results.…”

Multi-Mode Electric Actuator Dynamic Modelling for Missile Fin Control

“…Mehrabian et al [11] have modelled an actuator with second-order dynamics for a tail-controlled missile to study a STT missile autopilot design using adaptive control methodology based on eigen-structure assignment wherein the response of the missile is assessed by tail fin deflection and pitching rate. Reichert [12] has designed an autopilot for a tail-fin controlled missile using dynamic scheduling in which the actuator is modelled with second-order dynamics and has analysed the system performance for a series of commanded manoeuvres at varying speeds in terms of missile angle of attack only.…”

Sliding Mode Observer and Control Design with Adaptive Parameter Estimation for a Supersonic Flight Vehicle

“…There are many possible ways of dealing with the control of such linear and time varying plants. The classical approach is to design a controller for a certain point and then to schedule the controller's gain to place eigenvalues deep in the left half plane and the near real-axis according to a measured or derived parameters that represent flight conditions, such as angle of attack or Mach number [1]. In another method, H ∞ methods are invoked to design a collection of controllers, where, for each operating point in the flight envelope grid, a controller with a fixed structure results [2].…”