Development of a Mathematical Model that Simulates the Longitudinal, and Lateral-Directional Response of the F/A-18 for the Study of Flight Control Reconfiguration
Abstract
A linearized mathematical model is developed which simulates the dynamic response of the Navy F/A-18 for the study of flight control reconfiguration. The aircraft is modeled as a multi-input multi-output, sampled data, closed system, which couples the dynamics of the flight control system to the aircraft linearized small perturbation equations. The discrete time, state variable equations for the system are then formulated. A computer program is developed which will compose the model matricies and compute the response of the aircraft to stick and rudder inputs. To study flight control reconfiguration, the model allows individual actuation of either a left or right control surface. Aircraft response to the actuation loss of either the left or right stabilator is simulated in the program. The program is designed to implement the reconfigurable control mixer, currently under study for the Self-Repairing Digital Flight Control System. The computer simulation was written in VS FORTRAN. A copy of the program and simulation results are included in the appendices.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1986
- Accession Number
- ADA176333
Entities
People
- Fredric W. Rojek
Organizations
- Naval Postgraduate School