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Six-Degree-of-Freedom Flight-Path Study Generalized Computer Program: Part I. Volume II. - Structral Loads Formulation

Report Number: FDL TDR 64-1 Part 1 Volume 2
Author: Mann, C. D.
Corporate Author: McDonnell Aircraft Corporation
Laboratory: AF Flight Dynamics Laboratory
Date of Publication: 1964-08
Pages: 166
Contract: AF 33(657)-8829
Project: 1431
Task: 143103
AD Number: AD0449828

Abstract:
The equations of motion applicable to the Six-Degree-of-Freedom Structural Loads Program (SLP) are derived in this report. These equations are written for the determination of vehicle structural loads and response due to aerodynamic loads, loads due to control surface deflections, and environmental disturbances. Arbitrary elastic degrees of freedom (wing bending, wing torsion, body bending, etc.) and fuel slosh equations are incorporated into the overall analysis. Newtonian flow theory is used for obtaining idealized aerodynamic pressure distributions since it is the simplest aerodynamic theory that offers sufficient generality. Accelerations, deflections, shear forces and bending moments at arbitrary stations can be computed.


Provenance:
AFRL/VACA
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