Abstract: A system and a method for generating a signal to control a steering mechanism and an aircraft using the system are disclosed. A tiller module includes a moveable tiller base configured to moveably respond to a steering signal. The tiller module also includes a tiller coupling configured to couple the tiller with the moveable tiller base and further configured to generate a tiller differential signal indicative of a steering force applied to the tiller relative to a position of the moveable tiller base. A tiller controller is configured to receive the tiller differential signal and a steering mechanism position signal. The tiller controller is further configured to generate the steering signal to direct a steering mechanism to conform with the steering force and to direct the moveable tiller base of each tiller module to a feedback position representative of a current position of the steering mechanism.

Abstract: A control system for controlling a tiltable wheel truck of a main landing gear includes an auxiliary strut, a ground mode system operably connected with the aircraft for detecting and providing signals indicative of when the aircraft is on the ground; a takeoff mode system operably connected with the aircraft for detecting and providing signals indicative of when the aircraft is operating in a throttled-up mode; and an auxiliary strut control unit operably connected with the ground mode system, takeoff mode system, and auxiliary strut. The auxiliary strut control unit is operable to issue a lock-up command signal to the auxiliary strut upon detecting signals from the systems indicating that the aircraft is on the ground and that the aircraft is operating in a throttled-up mode, whereby the auxiliary strut is caused to lock up during a takeoff roll but is unlocked during other operating modes of the aircraft.

Abstract: A control system for controlling a tiltable wheel truck of a main landing gear includes an auxiliary strut, a ground mode system operably connected with the aircraft for detecting and providing signals indicative of when the aircraft is on the ground; a takeoff mode system operably connected with the aircraft for detecting and providing signals indicative of when the aircraft is operating in a throttled-up mode; and an auxiliary strut control unit operably connected with the ground mode sensor, takeoff mode sensor, and auxiliary strut. The auxiliary strut control unit is operable to issue a lock-up command signal to the auxiliary strut upon detecting signals from the sensors indicating that the aircraft is on the ground and that the aircraft is operating in a throttled-up mode, whereby the auxiliary strut is caused to lock up during a takeoff roll but is unlocked during other operating modes of the aircraft.

Abstract: A relatively expensive, relatively heavy, and relatively nonflammable hydraulic fluid (chlorotrifluorethylene) is used in an aircraft ground wheel brake system between the piston (72) of a deboost device (68) and a set of wheel brakes (196). A relatively cheaper and relatively lighter, conventional hydraulic fluid (MIL-H-5606), which is also relatively flammable, is used in the remainder of the system. A replenish system for the relatively nonflammable fluid includes a reservoir divided into two chambers by a piston. One chamber contains a quantity of the relatively nonflammable fluid and the other chamber is connected to the system pressure. The deboost device includes a replenish valve which is opened in response to a position of the deboost piston. Replenishment only occurs when the brakes are applied and replenishment is necessary. At other times, all portions of the brake system are at return pressure.

Abstract: A control system for maintaining an aircraft within the lateral boundaries of a runway during landing rollout under conditions of combined crosswind and low runway friction is disclosed. An automatic mode of operation is provided wherein the system utilizes an input signal representative of the heading of the runway being utilized and signals provided by (or derivable from ) an inertial navigation system to exercise coordinated control of the aircraft rudder, steering and differential braking system. In a semiautomatic mode of operation, signals supplied by the inertial navigation system (or its equipment) are utilized in conjunction with a continuous command signal that is provided by the pilot to indicate the desired aircraft trajectory. An optional provision is included for limiting the aircraft ground velocity slip angle to a range wherein an increase in ground velocity slip angle results in increased lateral corrective force on the aircraft.