Vibratory loads and response prediction for a high-speed flight vehicle during launch events

Abstract

High-speed flight vehicles (HSFVs) such as space launch vehicles and missiles undergo severe dynamic loads which are generated during the launch and in in-flight environments. A typical vehicle is composed of thin plate skin structures with high-performance electronic units sensitive to such vibratory loads. Such lightweight structures are then exposed to external dynamic loads which consist of random vibration, shock, and acoustic loads created under the operating environment. Three types of dynamic loads (acoustic loads, rocket motor self-induced excitation loads and aerodynamic fluctuating pressure loads) are considered as major components in this study. The estimation results are compared to the design specification (MIL-STD-810) to check the appropriateness. The objective of this paper is to study an estimation methodology which helps to establish design specification for the dynamic loads acting on both vehicle and electronic units at arbitrary locations inside the vehicle.

Development of a method for maximum structural response prediction of a store externally carried by a jet fighter

“…In these standards, 5 it is advised to avoid using these levels if there is any measurement data. Kin et al 6 examined the military standard levels, compared the vibration levels with the performed measurements and showed that levels given by the military standard were exaggerated. Following these standards may lead to overdesigning of the parts due to their large conservatism of the actual response levels.…”