Modification of classical two loop lateral missile autopilot design using reduced order observer (DGO) and LQR

Parijat Bhowmick, Gourhari Das

Research output: Contribution to conferencePaperpeer-review

Abstract

A flight path rate demand modified two-loop lateral missile autopilot design methodology for a class of guided missile, based on state feedback, reduced order Das & Ghosal observer (DGO) and Linear Quadratic Regulator (LQR), is proposed. The open loop undamped model of two-loop autopilot has been stabilized by using pole placement and state feedback. The non-minimum phase feature of rear controlled missile airframes is analyzed. The LQR technique is adopted to ensure optimal pole placement such that the adverse effect of non-minimum phase property on the response of missile autopilot can be reduced considerably and also the system stability can be made better. The overall response of the two-loop autopilot has been significantly improved over the previous ones. Performance (both transient and steady state) comparisons among the classical two loop design, two-loop design using state feedback & Ackermann approach and the present one, are made. Reduced order Das & Ghosal observer (using Generalized Matrix Inverse) is implemented successfully in this design. A program has been developed to find out the appropriate state vector & control input weightage matrices which will give the optimal pole positions and feedback gains according to the desired time domain performance specifications. Finally a numerical example has been considered and the simulated results are discussed in details.

Original languageEnglish
DOIs
Publication statusPublished - 2012
Event2012 3rd International Conference on Computing, Communication and Networking Technologies, ICCCNT 2012 - Coimbatore, Tamilnadu, India
Duration: 26 Jul 201228 Jul 2012

Conference

Conference2012 3rd International Conference on Computing, Communication and Networking Technologies, ICCCNT 2012
Country/TerritoryIndia
CityCoimbatore, Tamilnadu
Period26/07/1228/07/12

Keywords

  • Accelerometers
  • Ackermann
  • Aerodynamic control
  • Das & Ghosal Observer
  • Flight path rate demand loop
  • Generalized Matrix Inverse
  • LQR
  • Luenberger Observer
  • Non-minimum phase system
  • Rate Gyro
  • Two Loop Pitch Missile Autopilot

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