Use of the Pseudo-Inverse for Design of a Reconfigurable Flight Control System.

Abstract

Reconfiguration of the flight control system is achieved using generic inputs and transformation matrices for single primary control surface failure. Pseudo-inverse is used to evaluate appropriate transformation matrices. Design is tested against non-linear six degree-of-freedom model of the A-7D by simulating failure flights. System was found to provide desirable flying qualities upon reconfiguration. (Author)

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1981
Accession Number
ADA111172

Entities

People

  • Syed Javed Raza

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Aerodynamic Control Surfaces
  • Aeronautical Engineering
  • Air Force
  • Aircraft Models
  • Aircrafts
  • Airplanes
  • Closed Loop Systems
  • Control Surfaces
  • Control Systems
  • Control Systems Engineering
  • Differential Equations
  • Engineering
  • Engineers
  • Failure Mode And Effect Analysis
  • Flight Control Systems
  • Frequency Response
  • Surfaces

Fields of Study

  • Physics

Readers

  • Aviation Science / Aeronautics.
  • Robotics and Automation.
  • Statistical inference.