Abstract
At the time of re-entry modules entering into the atmosphere from space, a small perturbation introduces dynamic oscillations on the vehicle because of their extreme traveling speed. The dynamic stability characteristics of re-entry modules at hypersonic Mach numbers is of considerable relevance to their initial design. In the present paper, the dynamic stability of blunt cone model about [Formula: see text] is examined with wide range of design parameters such as nose bluntness, semi-vertex angle and center of rotation through theoretical and experimental methods. Theoretical approximations are made over a model based on the standard Newtonian theory. Experiments are conducted at [Formula: see text] hypersonic wind tunnel at [Formula: see text] and the following trends are observed from the experimental analysis. Interestingly, the incremental higher nose bluntness, semi-vertex angle and center of rotation reduce the dynamic stability. At higher hypersonic Mach numbers [Formula: see text], dynamic stability characteristics of the re-entry module are insensitive to the free stream Mach number. However, it is observed that the dynamic stability is increased in proportion to the vibration amplitude at hypersonic speeds.
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