Six-Degree-of-Freedom Flight-Path Study Generalized Computer Program: Part I. Volume II. - Structral Loads Formulation
Item
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Title
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Six-Degree-of-Freedom Flight-Path Study Generalized Computer Program: Part I. Volume II. - Structral Loads Formulation
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Date
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1964
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Index Abstract
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Not Available
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Photo Quality
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Not Needed
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Report Number
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FDL TDR 64-1 Part 1 Volume 2
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Creator
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Mann, C. D.
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Corporate Author
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McDonnell Aircraft Corporation
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Extent
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166
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Identifier
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AD0449828
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Access Rights
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DDC release to OTS not authorized
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Distribution Classification
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1
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Contract
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AF 33(657)-8829
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DoD Project
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1431
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DoD Task
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143103
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DTIC Record Exists
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Yes
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Distribution Change Authority Correspondence
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AFFDL LTR
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Abstract
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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.
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Report Availability
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Full text available
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Date Issued
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1964-08
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Laboratory
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AF Flight Dynamics Laboratory
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Provenance
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AFRL/VACA
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Type
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report
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Format
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1 online resource
