초록 ▼

A method and apparatus for determining the center of gravity of an aircraft having a plurality of wheels includes the steps of determining the load on one of the plurality of aircraft wheels, determining the aircraft inclination with respect to level, relating the wheel load to the aircraft center o

A method and apparatus for determining the center of gravity of an aircraft having a plurality of wheels includes the steps of determining the load on one of the plurality of aircraft wheels, determining the aircraft inclination with respect to level, relating the wheel load to the aircraft center of gravity based on the aircraft inclination. The load determination may be conducted on the aircraft nose wheel using a lever apparatus including a frame having a forward end and an aft end the aft end including an attachment device located at the aft end for providing detachable engagement with the wheel axle. The lever apparatus also includes a pivot arm having a first end and a second end, the first end pivotally attached to the frame at a pivot point located between the forward end and the aft end of the frame. A load cell is positioned on the frame so as to be engaged by the pivot arm as the pivot arm pivots about the pivot point for generating a signal indicative of the force generated on the frame as the wheel is raised. The lever apparatus operates about a fulcrum point located forward of the frame aft end about which the lever apparatus raises the aircraft wheel. A processor may be provided for receiving the load cell signal and determining wheel load.

대표청구항 ▼

1. A method for determining the location of the longitudinal center of gravity of an aircraft of the type having a landing gear arrangement including a pair of transversely spaced apart main landing gear units and a third ground support member located substantially on the longitudinal axis of the ai

1. A method for determining the location of the longitudinal center of gravity of an aircraft of the type having a landing gear arrangement including a pair of transversely spaced apart main landing gear units and a third ground support member located substantially on the longitudinal axis of the aircraft forward or aft of the main landing gear units, said method comprising the steps of:a. determining total aircraft weight; b. applying a force to the aircraft at a selected point located substantially along the aircraft longitudinal axis so as to raise the third ground support member from the ground; c. from a point not in or on the aircraft determining the force applied on the selected point; and d. relating the amount of the force applied on the selected point and total aircraft weight to the aircraft center of gravity so as to determine the longitudinal position of the aircraft center of gravity.