The Dynamic Response of Advanced Vehicles

Item

Title
The Dynamic Response of Advanced Vehicles
Description
An analytical study program has been conducted in order to determine dynamic load conditions and governing parameters for the flight of advanced vehicles; and an assessment of the adequacy and the applicability of existing dynamic loads prediction methods has been made.

A typical two stage liquid fuel boost-glide configuration is assumed for the study, thus allowing for the interaction of such variables as fuel slosh, structural flexibility, aerodynamic forces and control system forces. The report is divided into sections which discuss dynamic loads in the following areas: pre-launch, launch, boosted flight, staging, re-entry and landing or recovery. Included in the Appendices are discussions of modal determination, simplified methods of analysis, computational techniques, and ground wind criteria. Also included is a development of flight equations of motion and an extensive bibliography of reference material.

As a general conclusion it might be stated that the most formidable problems associated with dynamic loads determination result from man's inability to define aerodynamic forces accurately. Although mathematical models are becoming more complex, involving time-varying coefficients and nonlinear terms, their solutions can be obtained by the use of digital and analog computers.
Date
1960
Index Abstract
Contrails and DTIC truncated
Photo Quality
Not Needed
Report Number
WADD TR 60-518
Creator
Bohne, Q. R.
Clingan, B. E.
DeCeault, C. W.
Deutschle, P. C
Corporate Author
Boeing Airplane Company
Laboratory
Flight Dynamics Laboratory
Extent
230
Identifier
AD0261041
Access Rights
ASTIA
Distribution Classification
1
Contract
AF 33(616)-6597
DoD Project
1370
DoD Task
14000
DTIC Record Exists
No
Distribution Change Authority Correspondence
None
Report Availability
Full text available by request
Date Issued
1960-09
Abstract
An analytical study program has been conducted in order to determine dynamic load conditions and governing parameters for the flight of advanced vehicles; and an assessment of the adequacy and the applicability of existing dynamic loads prediction methods has been made.

A typical two stage liquid fuel boost-glide configuration is assumed for the study, thus allowing for the interaction of such variables as fuel slosh, structural flexibility, aerodynamic forces and control system forces. The report is divided into sections which discuss dynamic loads in the following areas: pre-launch, launch, boosted flight, staging, re-entry and landing or recovery. Included in the Appendices are discussions of modal determination, simplified methods of analysis, computational techniques, and ground wind criteria. Also included is a development of flight equations of motion and an extensive bibliography of reference material.

As a general conclusion it might be stated that the most formidable problems associated with dynamic loads determination result from man's inability to define aerodynamic forces accurately. Although mathematical models are becoming more complex, involving time-varying coefficients and nonlinear terms, their solutions can be obtained by the use of digital and analog computers.
Provenance
AFRL/VACA
Type
report
Subject
Supersonic Flow
Gliders
Hypersonic Vehicles
Hypersonic Characteristics
Aerodynamic Characteristics
Dynamics
Matrices (Mathematics)
Load Distribution
Vortices
Mathematical Analysis
Digital Computers
Airframes
Launching
Differential Equations
Parachutes
Fuel Tanks
Analog Computers
Earthquakes
Gust Loads
Drag
Wings
Integral Equations
Lift
Booster Rocket Engines
Staging
Aerodynamic Heating
Aircraft Landings
Manned
Atmosphere Entry
Control Systems
Recovery
Maneuverability
Bibliographies
Publisher
Wright-Patterson Air Force Base, OH : Flight Dynamics Laboratory, Wright Air Development Division, Air Research and Development Command, United States Air Force