Flutter analysis of a rocket fin at high mach numbers

Title

Flutter analysis of a rocket fin at high mach numbers

 Author

Ohman, L.H.
Dixon, R.C.

Institution

Natioanl Resaerch Council Canada, National Aeronautical Establishment

 Date

1963-05-31

 Abstract

Flutter analysis of a rocket fin at Mach numbers from 2 to 7 has been performed. The analysis is based on a number of preassigned mode shapes with piston theory representing the aerodynamic forces. Various mode combinations, effects of reduced stiffness due to kinetic heating, effects of structural damping and thickness effects as given by 2nd order piston theory, have been considered. In the analysis the eigenvalues of the various dynamic systems have been determined for flight cases along a given trajectory and for hypothetical flight cases to establish the flutter boundary. For 2-mode systems the eigenvalues have been determined analytically. For systems with more than two modes an iterative procedure has been developed to determine the eigenvalues.

 To reference this document use:

http://resolver.tudelft.nl/uuid:3e9027ec-589f-4949-88b2-97d1f3929a2a

 Publisher

National Research Council Canada

 Access restriction

Campus only

 Source

National Research Council Aeronautical Report LR 377; NRC No. 7522

 Part of collection

Aerospace Engineering Reports

 Document type

report

 Rights

(c) 1963 National Research Council
Files
PDF LR-377.pdf 4.45 MB
Close viewer