Aeronautics and astronautics – Landing gear
Patent
1987-04-29
1989-07-25
Peters, Jr., Joseph F.
Aeronautics and astronautics
Landing gear
244108, 244 1R, B64C 2502, B64C 2552
Patent
active
048505528
DESCRIPTION:
BRIEF SUMMARY
TECHNICAL FIELD
This invention relates to load transducers, and more particularly to a transducer for use with an aircraft having a skid type energy absorbing landing gear.
BACKGROUND ART
Many helicopter performance factors are affected by the actual gross weight at which a helicopter is being operated. To make the best use of an aircraft and to avoid unsafe operation, it is important for the pilot to have reasonably accurate knowledge of the gross weight of the aircraft and load. Closely related, and also important, is the knowledge of the center of gravity location relative to aircraft limitations.
Attempts have been made to develop an on-board aircraft weighing system which will provide a direct indication of gross weight and the center of gravity of the aircraft. Attempts have also been made to measure gross weight by using various sensors installed in and on the landing gear of an aircraft. For aircraft using oleo strut type landing gears, attempts have involved the use of pressure transducers to measure the oleo pressure. Because of friction in the oleo strut, this approach has not provided the necessary accuracy in determining gross weight. Load transducers have been proposed in various systems to eliminate friction, but these approaches have been complex, involving increased weight with marginal accuracy.
Additional approaches to measuring gross weight have involved the use of strain gauges. Strain gauges have been installed directly on existing parts of the landing gear as well as being placed inside axle shafts using collet arrangements. However, accuracy has been poor due to low strain levels during normal operation.
Therefore, a need has arisen for a landing gear load sensor for use in an on-board weighing system which provides an accurate measurement of the gross weight of an aircraft. More particularly, a need has arisen for a strain gauged landing gear load transducer which operates at strain levels that are sufficiently high to produce an accurate measurement of critical shear load while being insensitive to other loads. Further, a need has arisen for a landing gear load sensor that is light weight and can be adapted to various types of landing gear configurations.
DISCLOSURE OF THE INVENTION
In accordance with the present invention, a landing gear load sensor for an aircraft having a skid type landing gear is provided which substantially eliminates the problems heretofore associated with such sensors.
In accordance with the present invention, a landing gear load sensor for an aircraft having a skid type landing gear is provided. The load sensor includes a shear beam having a loadbearing area. The shear beam is mounted to the helicopter, such that the loadbearing area is disposed adjacent the landing gear. Structure is disposed on the shear beam between the loadbearing area and the point of mounting to the aircraft for sensing shear load on the shear beam.
In accordance with another aspect of the present invention, a landing gear load sensor for a helicopter having a skid type landing gear is provided. The sensor includes a shear beam having first and second ends with a loadbearing area disposed between the ends. Structure extends from the first and second ends of the shear beam for mounting the shear beam to the helicopter, such that the loadbearing area is disposed adjacent the landing gear. Structure is disposed on the front and back surfaces of the shear beam and between the ends of the shear beam and the point of attachment to the helicopter for sensing shear load on the shear beam.
In accordance with another aspect of the present invention, a landing gear load transducer for determining the weight of an aircraft having a landing gear including a pair of skids is provided. A pair of shear beams is mounted to each of the cross tubes between the skids. The shear beams each include a loadbearing surface which is mounted adjacent the cross tubes. Structure is mounted on the shear beam between the point of attachment to the helicopter and the loadbearing area for sensing shear load o
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Darden Paul E.
Dickson Billy H.
Bell Helicopter Textron Inc.
Corl Rodney
Peters Jr. Joseph F.
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