Aircraft Landing Dynamic Analysis. Volume 2. Computer Program

Abstract

This report is Volume 2 of a two volume report. The first volume provides the derivation of the equations of motions and the second volume documents the computer program. In this volume the equations of motion are coded 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 strut 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 with unsymmetrical arresting forces. The equations were coded in FORTRAN 77. A sample input deck and run are provided.

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Document Details

Document Type
Technical Report
Publication Date
Nov 04, 1988
Accession Number
ADA240147

Entities

People

  • John W. Lincoln

Tags

Communities of Interest

  • Advanced Electronics
  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Forces
  • Air Force
  • Air Force Facilities
  • Aircrafts
  • Airframes
  • Classification
  • Computational Science
  • Computer Programs
  • Differential Equations
  • Engineering
  • Equations Of Motion
  • Fuselages
  • Landing Gear
  • Molecular Dynamics
  • Plastic Explosives
  • Security
  • Systems Engineering

Fields of Study

  • Engineering

Readers

  • Aerospace Engineering
  • Computer Science.
  • Fluid Dynamics.