Dual Control Analysis of an Air to Ground Missile.
Abstract
Many errors are known to exist in Inertial Navigation Systems of modern air-to-ground missiles. These error sources, if undetected, contribute to navigation errors of position and velocity. This study analyses one source of INS errors -- the misalignment of the accelerometer reference frame. By maneuvering a missile, the error source becomes more observable. Thus, a better estimate can be made of the error source. This directly influences the estimate of position. Hence, in order to minimize the terminal navigation error, some control energy must be expended to identify the error source. This dual control problem may be viewed as an optimization problem. By formulating a performance index of the terminal error and control energy appropriate mathematical techniques should yield an optimal flight trajectory. This thesis seeks to analyze the dual control nature of an air-to-ground missile. Two methods are used. The first uses a predetermined flight path which is incremented until a minimum is reached. The second is a first-order gradient which allows greater freedom in the control law. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1978
- Accession Number
- ADA058515
Entities
People
- James P. Kauppila
Organizations
- Air Force Institute of Technology