Hypervelocity Aerodynamics and Control
Abstract
The research objective of this study of optimal aerodynamics and propulsive control at supercircular speeds is to develop methods for determining optimal guidance and control of earth launch kinetic energy weapons designed to intercept intercontinental ballistic missiles early in their ascent trajectory. Optimal control techniques are used to obtain multistage trajectories based on minimizing the mass ratio. Study parameters include time of flight, down range intercept distance and intercept altitude. Re-entry/skip trajectories are considered. Innovative means of attitude control of the final stage which intercepts the target are being studied. An investigation of the control of aerodynamic forces on hypersonic vehicles by boundary layer injection has also been started. Its goal is to determine optimal patterns of injection of a gas into a boundary layer on a hypersonic vehicle, to generate desired aerodynamic forces. Two directions of approach are being studied. In the first, analytical means are being used to study the effects of blowing on simple flow problems in the various flow regimes; a combination of asymptotic and numerical methods are used. In the second, numerical methods are being used, with particular emphasis on obtaining efficient codes which result in the computation of crisp shock waves and which can handle blowing in the boundary layer. Both distributed and strip blowing are under consideration. Preliminary results are presented.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1987
- Accession Number
- ADA241514
Entities
People
- R. M. Howe
- T. C. Adamson Jr.
Organizations
- University of Michigan