Optimal Aerodynamic and Thrust Magnitude Control of Maneuvering Rockets
Abstract
The report presents the results of a study to evaluate thrust magnitude control in Air Force missions. In this study modern control theory was applied to determine the time history of the thrust profile to achieve optimal maneuvers of aerospace lifting vehicles. Following formulation of a mathematical model with a very general propulsion system, optimal control laws for the thrust direction and magnitude were obtained. It was shown that coast, boost, and sustaining thrust could all be optimal. For the particular case of the sustaining flight it was shown that the position vector, the velocity vector, and the mass of the rocket vehicle must satisfy a certain explicitly obtained relationship, and that the variable thrust magnitude depends strongly on the aerodynamic characteristics of the vehicle and the optimal trajectory flown.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1972
- Accession Number
- AD0751281
Entities
People
- C. J. Shieh
- N. X. Vinh
- W. F. Powers
Organizations
- University of Michigan