Multivariable Control Law Design for the AFTI/F-16 with a Failed Control Surface.
Abstract
Two linearized models containing coupled aircraft equations are developed for the AFTI/F-16. The first is a model of the healthy aircraft with all control surface intact, and the second is a model of the aircraft with a free-floating right horizontal tail and all other surfaces operational. The multivariable design technique of Professor Brian Porter and the computer program MULTI are first used to design control laws for the healthy model. The control laws are tailored to perform seven maneuvers at four flight conditions. Maximum maneuvers are commanded to yield maximum control surface deflections. The same control law designs are then applied to the model with a failed right horizontal tail, and the performance is evaluated. Some maneuvers require modifications to the designs or lowered maximum maneuver requirements to avoid overshooting the deflection limits of the operational control surfaces. Simulation responses are presented for both the healthy and failure aircraft models. Generally, when the right horizontal tail fails, the left horizontal tail fails, the left horizontal tail assumes primary pitch control and the flaperons take over complete roll control. The flaperons, rudder, and canards deflect to counter the rolling and yawing moments produced by the left horizontal tail deflection. Originator-Supplied Keywords include: Flight Control Systems, Failure, Control theory, Damage Control, Fly By wire Control, and Self Organizing Systems, (Thesis).
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1984
- Accession Number
- ADA151908
Entities
People
- R. A. Eslinger
Organizations
- Air Force Institute of Technology