Abstract
The main control objective of an aircraft ABS(Anti-skid Brake System) is to continuously adjust brake pressure to maintain optimum brake torque. This optimum level should balance tire and runway friction at its peak value, which is conveniently done by controlling the wheel slip ratio around the peak of the friction coefflcient(µ)-slip ratio(s) curve during ABS maneuvers. It influences not only the taxing distance of an aircraft, but also the strength and the fatigue life of the landing gear system. Difficulties in designing an ABS controller are due to the nonlinear characteristics of braking system dynamics, the time-varying nature of the system components, and the unknown environmental parameters. Furthermore, as an optimal control problem, this is currently intractable because of the large uncertainty in the dynamics. In this paper, an ABS control algorithm is developed with a 5-D.O.F. aircraft dynamics model based on the landing dynamic equations and the ABS digital control unit(DCU) is designed to accommodate the anti-skid control algorithm. Also the design and implementation of real-time HILS system for development of the aircraft ABS DCU are presented. Developed ABS DCU is evaluated and tested with proposed HILS system on the several runway conditions.
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