A rational method for predicting alighting gear dynamic loads.
Volume 1,
General methods /
T.R. Ferguson, J. Mollick, and W.W. Kitts.

Description

Main Author

Ferguson, T. R.

Related Names

Kitts, W. W., author.
Mollick, J., author.
Air Force Flight Dynamics Laboratory (U.S.)
United States. Air Force.

Language(s)

English

Published

Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Aeronautical Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1963.

Subjects

Mathematical analysis.
Materials > Materials / Dynamic testing.
Airplanes > Airplanes / Landing gear.
Airframes.
Mathematical analysis.
Materials > Materials / Dynamic testing.
Airframes.
Airplanes > Airplanes / Landing gear.

Summary

A rational method for predicting alighting gear loads during landing impact is discussed. The equations describing the motions of a vehicle during landing impact are developed for an arbitrary vehicle configuration. The method is of sufficient generality and accuracy to allow the formulation of alighting gear dynamics problems in flight vehicles including V/STOL aircraft, high gross weight logistic vehicles, recoverable booster vehicles, advanced tactical and defense vehicles operating out of remote areas, and lunar vehicles. It allows for the effects of varying coefficients of friction and damping, combinations of initial conditions of pitch, roll, yaw angles and rates, vertical, longitudinal and lateral motion, slippage of the gear relative to the alighting surface, flexible alighting gear and vehicle structure, simultaneously applied triaxial ground loads, and various types and number of alighting elements. The formulation is intended for the cantilevered type of gear, although the articulated type may be handled through some extensions of the formulation.

Note

AD0428027 (from http://www.dtic.mil).
"December 1963."

Physical Description

xxvi, 160 pages : illustrations ; 28 cm.

Locate a Print Version

Find in a library

Viewability