Equations of Motion of the F-80 Aileron Boost

Abstract

Equations and non-linear expressions defining the dynamic control performance of the F-80 aircraft aileron boost are derived. The complete equations and expressions define the non-linear nature of the device, and relate the instantaneous input and output moments to the input and output positions repsectively, as determined by the boost design. Methods of solution by analogue machine methods are indicated for further investigation and study. These equations and expressions may be of use also in analysis of F-94 roll performance, since the boost design (with the exception of the hydraulic system pressure) is similar. The operation of the F-80 aileron differential mechanism is described as a related factor in the overall roll system control by a human pilot.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1952
Accession Number
ADA075871

Entities

People

  • Samuel P. Altman

Organizations

  • Wright Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Aircrafts
  • Altitude
  • Analogs
  • Automatic Pilots
  • Closed Loop Systems
  • Control Sticks
  • Control Systems
  • Dynamics
  • Engineering
  • Equations
  • Equations Of Motion
  • Feedback
  • Hydraulic Pressure
  • New York
  • Schematic Diagrams
  • Transfer Functions

Readers

  • Aerodynamics/Aeronautics.
  • Aerospace Engineering
  • Calculus or Mathematical Analysis