| Article ID: | iaor1994171 |
| Country: | United Kingdom |
| Volume: | 20 |
| Issue: | 1 |
| Start Page Number: | 1 |
| End Page Number: | 19 |
| Publication Date: | Sep 1992 |
| Journal: | Engineering Optimization |
| Authors: | Grandhi R.V., Hankey W.L., Tiley Jaimie, Belcher P. |
| Keywords: | optimization, performance |
A performance synthesis method is developed to optimize flight operations of advanced hypersonic intercept vehicles. The control laws and guidance control method are evaluated to intercept a known penetrator in minimal time. Two cases of penetrator performance are investigated with the optimal switching point from optimal climb to intercept maneuvering defined. Evaluated are tradeoffs between control law parameters, missed distance, intercept time, and intercept guidance control range for a selected vehicle.