The feasibility of using an active control in the landing gear system of an aircraft to reduce wing fatigue damage resulting from ground induced vibrations during taxiing is considered. The characteristics of three vehicle models are discussed: a single landing gear system, a tricycle landing gear system and a system of five landing gears. Mathematical expressions for the runway inputs to each vehicle model are obtained in the form of random inputs represented by Gauss-Markov processes. The model for a linear hydraulic actuator which is used as the active control element in the landing gear system is presented. The results indicate that the combined optimal active control and landing gear system can provide a substantial improvement in reducing wing fatigue over that of the landing gear system alone. Also, the control parameters that are necessary and desirable in the optimal system, together with the physical demands placed on the actuator, are determined. (Author).

The feasibility of using an active control in the landing gear system of an aircraft to reduce wing fatigue damage resulting from ground induced bibrations during taxiing is considered. The characteristics of three vehicle models are discussed: a single landing gear system, a tricycle landing gear system and a system of five landing gears. Mathematical expressions for the runway inputs to each vehicle model are obtained in the form of random inputs represented by Gauss-Markov processes. The model for a linear hydraulic actuator which is used as the active control element in the landing gear system is presented. (Author).