Aircraft Landing Dynamic Analysis. Volume 1. Equations of Motion

Abstract

This report is Volume 1 of a two volume report. The first volume provides the derivation of the equations of motion and the second volume documents the computer program. The equations of motion are derived for the general case of a flexible aircraft with rigid body motion permitted in six degrees of freedom. The shock strut force equations are derived based on the assumption that a gas-fluid shock is used. The hydraulic fluid is assumed to be compressible in the shock strut. The arresting forces are derived for a cable arrestment system. The equations permit landings to be made with unsymmetrical arresting forces. The friction between the cable and arresting hook is accounted for in the derivation of the arresting forces. The equations of motion for the aircraft are developed from Lagrange's equations with the modifications included to use the body axis components of the airframe velocity vector and angular velocity vector as quasi-coordinates.

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Document Details

Document Type
Technical Report
Publication Date
Nov 09, 1987
Accession Number
ADA240123

Entities

People

  • John W. Lincoln

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Accuracy
  • Aerodynamic Forces
  • Air Force
  • Aircrafts
  • Airframes
  • Compressive Properties
  • Differential Equations
  • Dynamic Response
  • Engineering
  • Equations
  • Equations Of Motion
  • Geometry
  • Landing Gear
  • Mechanics
  • Plastic Explosives
  • Systems Engineering
  • Three Dimensional

Fields of Study

  • Engineering

Readers

  • Aerospace Engineering
  • Control Systems Engineering.
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)