Aeroelastic Analysis of a Composite Wing Designed for the BQM-34E Supersonic Aerial Target Vehicle.
Abstract
The BQM-34E with composite wings is found to be free from flutter within the sea level, subsonic regime provided three pounds of mass balance is installed in the tip of each antenna pod. although no analysis has been made at altitude, it is believed that freedom from flutter exists througout the subsonic regime at all altitudes. A high frequency fourth wing bending mode is predicted to be unstable above Mach 1 based on the subsonic analysis. However, it is reasonable to assume that this mode would not be unstable if a supersonic analysis were to be conducted. The most critical regime will be the transonic regime for which no adequate theory exists for flutter prediction. Due to the speed margin shown for the subsonic case at sea level, Mach .85, the mode is believed to be stable throughout the transonic regime. The wing will not diverge due to static aeroelastic loads; however, there is significant air load redistribution for the critical subsonic design condition due to elastic twist. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 28, 1972
- Accession Number
- AD0907529