The goal of the Contrails project is to help preserve and disseminate the technical record of 20th century aerospace research, highlighting in particular the research endeavors of the Illinois Tech community.

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

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.

Download this report

(PDF, 2.57 MB, 166 pages)

Other options for obtaining this report

Via the Defense Technical Information Center (DTIC):
A record for this report, and possibly a full-image download of the report, exists at DTIC

Via National Technical Information Service:
This report may have been digitized and made freely available for public download, or made publicly available for purchase by the National Technical Information Service through their online database, the National Technical Reports Library

Indications of Public Availability
No digital image of an index entry indicating public availability is currently available
There has been no verification of an indication of public availability from an inside cover statement

Related Reports

This report has the following parts/volumes: