Validation of High Angle-of-Attack Analysis Methods
Abstract
This report extends, applies, and validates the aircraft stability and control methodologies developed by TASC and reported in ONR-CR-215-237-2. These methodologies enable the prediction of airframe stability boundaries, control and power difficulties, and stability boundaries of the combined pilot, control system, and aircraft. In the realm of control system design, these methods enable the construction of digital command augmentation systems which provide precise command response over the entire flight regime while augmenting the airframe stability characteristics. The design of an air combat digital flight control system for the F-14A is described in this report, and its performance is verified by the use of a nonlinear six-degree-of-freedom aircraft simulation and an air combat pilot model. Comparison of the tracking accuracy of the DFCS-aircraft to that of a conventionally controlled aircraft indicates that the DFCS provides better tracking and reduces the likelihood of control-induced departure. In the realm of pilot model validation, a method of choosing the best model among those hypothesized is described and its operation demonstrated. Piloted simulation data are processed which indicate that the pilot does not change his control strategy to correspond to changes in the aircraft flight condition.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 20, 1979
- Accession Number
- ADA087621
Entities
People
- John R. Broussard
- Paul W. Berry
- Sol W. Gully
Organizations
- TASC, Inc