Arrangement of at least one sensor on the landing gear of an aircraft for measuring its weight and position of center of gravity
AssigneeVDO Adolf Schindling AG
InventorsHans-Norbert Patzig, Klaus Schult
Life of this patent
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Abstract
An arrangement in which at least one sensor is provided on the landing gear of an aircraft for measuring its weight and the position of its center of gravity, and in which a sensor for a measurement of shear is arranged at a measurement point formed by a pair of lugs on an axle or bogie beam. The axle (9) or bogie beam is of constant cross section above the measurement point and symmetrical to a vertical axis which lies centrally between the two lugs of a pair (10, 13 and 14, 15 respectively).
Claims8
A system of sensors for a landing gear of an aircraft, comprising
- at least one sensor on a landing gear of an aircraft for measuring weight of the aircraft and the position of the center of gravity of the aircraft, wherein
- the landing gear includes an axle or bogie beam, and a sensor for a measurement of shear is arranged at a measurement point, there being a pair of lugs located on the axle or the bogie beam at the measurement point;
- and
- the axle or the bogie beam varies in cross section at the measurement point and is asymmetrical about a vertical plane which bisects said at least one sensor and lies centrally between the pair of lugs, there being a larger cross section to one side of the vertical plane and a smaller cross section to an opposite side of the plane;
- wherein
- the sensor comprises a first sensor part attached to a first lug of the pair of lugs and a second sensor part attached to a second lug of the pair of lugs, the first lug being at the larger beam cross section and further from the vertical plane than the second lug which is at the smaller beam cross section;
- the sensor operates via an asymmetrical operation, wherein the first sensor part attached to the first lug and the second part attached to the second lug differently influence a mutual relative movement of the first and the second sensor parts to produce an electric output variable.
A system of sensors for an aircraft landing gear, the system comprising
- at least one sensor on a landing gear of an aircraft for measuring weight of the aircraft and position of a center of gravity of the aircraft, said at least one sensor being of symmetrical type;
- wherein the landing gear includes an axle or bogie beam with a pair of lugs disposed on the axle or bogie beam;
- the axle or bogie beam has a central portion for connection to an aircraft and two opposed end portions for connection to wheels of the aircraft, said pair of lugs is disposed on one side of said central portion and, in said pair of lugs there in an inner lug closer to said central portion and an outer lug closer to an end portion of said axle or bogie beam;
- said at least one sensor provides a measurement of shear and is located at a measurement point formed by the pair of lugs on the axle or the bogie beam;
- in the case of an axle or bogie beam which varies in shape of cross section at the measurement point and is symmetrical about a vertical axis passing between the lugs, the pair of lugs is developed with unequal undercuts in the manner that an undercut on an outer side of each lug in said pair of lugs extends more deeply into a lug than an undercut on a corresponding opposite inner side of each of the lugs;
- and
- in each of the lugs, an extension of an undercut into a lug produces a reduction in cross section of the lug at the site of the undercut.
Dependencies are inferred from the claim text.