A Classical Design Approach to a Normal Acceleration Stability Augmentation System for a High Performance Aerospace Vehicle.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING
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The thesis represents a response to the design challenge problem presented at the 1970 Joint Automatic Control Conference. The design entailed a stability augmentation system for a high speed, high performance aerospace vehicle, including consideration of the first two structure modes. A normal acceleration system with a pitch rate inner loop was designed. Root locus techniques were used exclusively in obtaining an appropriate filter and fixed compensation in the pitch rate and normal acceleration loops. Relatively simple, but not large, gain changes in both loops was necessary to achieve the desired time responses to a commanded input. Realistic gust responses proved to be well within prescribed tolerances. Author
- Research and Experimental Aircraft
- Unmanned Spacecraft