Application of Aeroelastic Modeling Techniques to the Determination of Strctural Loads and Stability and Control Dynamic Characteristics
Report Number: RTD-TDR-63-4197 Part I, p. 129
Author(s): Hill, J. A., Gikas, X. A.
Corporate Author(s): Astromechanics Research Division, Giannini Controls Corporation
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1964-03
Pages: 30
DoD Task:
Abstract:
This paper considers the application of aeroelastic modeling techniques to the determination of structural loads and stability and control characteristics. Specifically, the paper deals with considerations for development of static and dynamic flexible wind tunnel models to be used to measure structural loads and stability and control characteristics. The need for development in these facets of modeling is indicated by reviewing the present technological status of aerodynamic wind tunnel simulation and testing. It is emphasized that these modeling extensions provide another, but significant, "development tool" for the vehicle designer and a means, whereby, a significant cost savings can be realized during prototype flight test. The technical considerations required for these modeling extensions are divided into seven areas: similitude, model, mounting system, control system, sensors, data transmission, and data handling. The requirements and problems pertinent to each of these areas are defined. It is concluded that these extensions of aeroelastic modeling techniques are feasible and desirable from both technical and economic points of view.
Provenance: Bombardier/Aero
Author(s): Hill, J. A., Gikas, X. A.
Corporate Author(s): Astromechanics Research Division, Giannini Controls Corporation
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1964-03
Pages: 30
DoD Task:
Abstract:
This paper considers the application of aeroelastic modeling techniques to the determination of structural loads and stability and control characteristics. Specifically, the paper deals with considerations for development of static and dynamic flexible wind tunnel models to be used to measure structural loads and stability and control characteristics. The need for development in these facets of modeling is indicated by reviewing the present technological status of aerodynamic wind tunnel simulation and testing. It is emphasized that these modeling extensions provide another, but significant, "development tool" for the vehicle designer and a means, whereby, a significant cost savings can be realized during prototype flight test. The technical considerations required for these modeling extensions are divided into seven areas: similitude, model, mounting system, control system, sensors, data transmission, and data handling. The requirements and problems pertinent to each of these areas are defined. It is concluded that these extensions of aeroelastic modeling techniques are feasible and desirable from both technical and economic points of view.
Provenance: Bombardier/Aero
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This report is part of the following conference:
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Proceedings of Symposium on Aeroelastic & Dynamic Modeling Technology
RTD TDR 63-4197 Part I