Optimal Design of Helicopter Precision Hover Control Systems.

Abstract

1-F-162202-AA-9713(*helicopters, hovering), (*flight control systems, helicopters), stability, equations of motion, accuracy, optimizationcomputer aided analysisModern Control Theory is employed to analytically determine the limit of positional precision with which a helicopter can be hovered. Approaches based on Liapunov's Second Method and a Squared Root Locus Method are formulated to this optimal control problem. Both of these methods avoid iterative solution of the Matrix Riccati Equation. The Squared Root Locus Method is developed as a computer algorithm which generates optimal control designs as a function of performance index and helicopter stability/control derivatives. Practical design constraints can readily be interpreted from the results of this formulation. (Author)

Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1973
Accession Number
AD0759919

Entities

People

  • N. N. Purl
  • R. J. Niemela

Organizations

  • United States Army Communications-Electronics Command

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Accuracy
  • Control Systems
  • Control Theory
  • Differential Equations
  • Equations
  • Equations Of Motion
  • Flight Control Systems
  • Helicopters
  • Precision
  • Riccati Equation

Fields of Study

  • Physics

Readers

  • Adaptive Control and Estimation with Uncertainty in Dynamic Systems.
  • Aviation Science / Aeronautics.
  • Control Systems Engineering.