High-Gain Error Actuated Flight Control Systems for Continuous Linear Multivariable Plants.
Abstract
The theory of high-gain error actuated feedback control, developed by Porter and Bradshaw, is applied to the design of various lateral-directional decoupling flight control systems for an advanced aircraft. The controllers developed in this report utilize output feedback with proportional plus integral control to produce desirable closed-loop responses with minimal interactions between outputs. Because of the structure of the system, measurement variables in addition to the outputs are necessary to apply this method. The report examines controller design robustness by varying the flight conditions or maneuver commands from the ones the controller is specifically designed for, and then judges system performance. The results show that the controller is robust with respect to varying flight conditions, but is not robust with respect to varying maneuver commands. This report also examines the effect of first-order actuator dynamics in the system model. Actuator dynamics are shown to significantly effect the control system response, indicating that a simplified model, without actuators, is not desireable in one's control design scheme. Also a computer program to determine transmission zeros and decoupling zeros is developed. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1982
- Accession Number
- ADA124871
Entities
People
- Thomas Lewis
Organizations
- Air Force Institute of Technology