Modeling Flexible Aircraft for Flight Control Design
Abstract
Trends to lower structural fraction of aircraft increase flexibility effects. Higher bandwidth control systems combined with these more flexible structures cause more aeroservoelastic interactions. Active, closed-loop control systems allow greater flexibility. To take advantage of this design possibility, an integrated ASE model is needed for conceptual and preliminary design stages of aircraft. This report seeks to define the equations of motion of a flexible aircraft from first principles to aid future discussions between experts in the specialties which make up ASE: aerodynamics, controls, and structures. This theoretical report documents the development of the equations, and states under what conditions the assumptions and approximations are accurate. It consists of 5 sections on different technical areas and a summary section: 1) Linearization of flexible aircraft hybrid-coordinate dynamic equations and inclusion of aerodynamic and gravitational loads; 2) Derivation of equations of motion and stability derivatives for a flexible aircraft vehicle; 3) Aerodynamics for aeroservoelasticity; 4) Model-order reduction for linear systems; and 5) Hydraulic actuator equations for aeroservoelastic modeling. Flight control systems; Servomechanisms.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1989
- Accession Number
- ADA219123
Entities
People
- A. Goforth
- E. C. Bekir
- E. J. Horowitz
- G. A. Watts
- H. Hassig
- R. N. Moon
- W. J. Davis
Organizations
- Lockheed Martin Aeronautics