Implications of Practical Re-entry Structures for Dynamic Model Simulation
Report Number: RTD-TDR 63-4197 Part I, p. 673
Author(s): LaFavor, S. A., Lemley, C. E., Tucker, P. B.
Corporate Author(s): System Technology Division, McDonnell Aircraft Corporation
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1964-03
Pages: 29
Contract: AF33(616)-8106
DoD Project: 1466
DoD Task: 1466
Abstract:
The unique considerations associated with the application of aerothermoelastic scaling laws in the design, construction, and testing of flutter models for re-entry glide vehicles are discussed. A brief review of the scaling laws is presented in order to re-emphasize the point that they cannot be completely satisfied for other than the case of full scale testing of flight type hardware. This is followed by a discussion of four structural concepts that have been devised to provide acceptable structures for use in the re-entry environment. These concepts are reviewed with respect to predicting the mechanism of potential aerothermoelastic problems, and establishing the possibility of relaxing some of the restrictions of the aerothermoelastic scaling laws. It is concluded that the aerothermoelastic problem can generally be reduced to separate thermoelastic and aeroelastic problems for these structural concepts and that the testing of small scale "artificially reduced stiffness" aeroelastic models, in conjunction with "restricted purpose" heat transfer models, will yield meaningful and useful flutter data for re-entry vehicle structural approaches that presently appear feasible. The use of this type of approach in performing wind tunnel tests on a scaled model of the ASSET re-entry glide vehicle is described.
Provenance: Bombardier/Aero
Author(s): LaFavor, S. A., Lemley, C. E., Tucker, P. B.
Corporate Author(s): System Technology Division, McDonnell Aircraft Corporation
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1964-03
Pages: 29
Contract: AF33(616)-8106
DoD Project: 1466
DoD Task: 1466
Abstract:
The unique considerations associated with the application of aerothermoelastic scaling laws in the design, construction, and testing of flutter models for re-entry glide vehicles are discussed. A brief review of the scaling laws is presented in order to re-emphasize the point that they cannot be completely satisfied for other than the case of full scale testing of flight type hardware. This is followed by a discussion of four structural concepts that have been devised to provide acceptable structures for use in the re-entry environment. These concepts are reviewed with respect to predicting the mechanism of potential aerothermoelastic problems, and establishing the possibility of relaxing some of the restrictions of the aerothermoelastic scaling laws. It is concluded that the aerothermoelastic problem can generally be reduced to separate thermoelastic and aeroelastic problems for these structural concepts and that the testing of small scale "artificially reduced stiffness" aeroelastic models, in conjunction with "restricted purpose" heat transfer models, will yield meaningful and useful flutter data for re-entry vehicle structural approaches that presently appear feasible. The use of this type of approach in performing wind tunnel tests on a scaled model of the ASSET re-entry glide vehicle is described.
Provenance: Bombardier/Aero
Other options for obtaining this report:
Via the Defense Technical Information Center (DTIC): Via National Technical Report Library: This report may be available for download from NTRL. Use the Title from this record to locate the item in DTIC Online 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 statementRelated report(s)
This report is part of the following conference:
-
Proceedings of Symposium on Aeroelastic & Dynamic Modeling Technology
RTD TDR 63-4197 Part I