Design of Optimal Flight Controller for Generic Linearised Missile Model in Hypersonic Regime

Abstract

This report presents a multivariable controller design for a generic missile travelling at hypersonic speed. The controller is based on the theory of optimal control, and the solution is provided by a feedback controller known as a Linear Quadratic Regulator (LQR) for tracking the demands (lateral acceleration and roll rate) as closely as possible while keeping the actuator efforts (for deflecting aileron, elevator and rudder) small. In the computer simulation, the missile model is subject to various hypersonic flight conditions and gain scheduling is exercised as a function of dynamic pressure. The initial study assumes perfect knowledge of all the states for the controller design. Subsequently, a state observer (kalman filter) is introduced into the design to reflect a more practical synthesis where some of the states need to be estimated.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 2010
Accession Number
ADA527797

Entities

People

  • Farhan A. Faruqi
  • Jijoong Kim

Organizations

  • Defence Science and Technology Group

Tags

Communities of Interest

  • Materials and Manufacturing Processes
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Automatic Pilots
  • Closed Loop Systems
  • Computer Simulations
  • Control Systems
  • Control Systems Engineering
  • Differential Equations
  • Dynamic Pressure
  • Engineers
  • Feedback
  • Filters
  • Guidance
  • Inertial Measurement Units
  • Inertial Navigation
  • Measurement
  • Multiple Input Multiple Output
  • Navigation
  • Simulations

Readers

  • Adaptive Control and Estimation with Uncertainty in Dynamic Systems.
  • Aerodynamics/Aeronautics.
  • Robotics and Automation.

Technology Areas

  • Hypersonics