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Aircraft driving wheel column force sensor

A force sensor and steering wheel technology is applied in the aviation field to achieve the effect of improving safety assurance capability, reasonable design and high measurement accuracy

Active Publication Date: 2017-02-22
中航电测仪器(西安)有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, the direct measurement of the push-pull force and torsion moment exerted on the steering wheel by the pilot during the flight of the aircraft is a major technical problem that plagues the entire aviation field. Method or device for pushing and pulling forces and torsion moments applied to the steering wheel during the process

Method used

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  • Aircraft driving wheel column force sensor
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Embodiment Construction

[0020] The present invention will be further described in detail below in conjunction with specific embodiments, which are for explanation rather than limitation of the present invention.

[0021] The present invention is a steering column force sensor for an aircraft, which directly measures the push-pull force and torsion moment applied on the steering wheel by the pilot of the aircraft in the process of driving the aircraft, such as figure 1 As shown, it includes a steering wheel connection structure 1, a steering column force sensor 2, a first connecting clamp 3, a second connecting clamp 4 and a steering column connecting structure 5; the steering wheel connecting structure 1 is provided with a steering column force sensor 2 The matching groove, the disc column force sensor 2 is nested in the groove of the steering wheel connecting structure 1; the other end of the disc column force sensor 2 is connected to the steering column through the first connecting clamp 3 and the secon...

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Abstract

The invention provides an aircraft driving wheel column force sensor which is capable of directly measuring the pushing force and the torsional moment of an aircraft driver on a driving wheel during an aircraft driving process. The aircraft steering wheel column force sensor comprises a driving wheel connection structure, a wheel column force sensor body and a driving column connection structure. The wheel column force sensor body comprises a box body structure which is used for measuring the pushing force and a prism structure which is used for measuring the torque. The box body structure and the prism structure are elastomer. Upper and lower inner surfaces of the box body structure are respectively provided with at least one group of resistance strain gauges. One end of the prism structure is fixed on the upper or lower surface of the box body structure along the axis. A boss and a connection spline are successively arranged on the other end. At least two side walls of the prism structure are respectively provided with at least one group of resistance strain gauges. The box body structure is embedded in a groove arranged in the driving wheel connection structure. The spline is embedded in the driving column connection structure.

Description

Technical field [0001] The invention belongs to the aviation field, and particularly relates to a steering column force sensor for an aircraft. Background technique [0002] Existing measurement methods all adopt indirect methods to measure the push-pull force and torsion moment exerted on the steering wheel by the pilot of the aircraft. At present, the direct measurement of the push-pull force and torsion torque exerted on the steering wheel by the pilot of the aircraft is a major technical problem that plagues the entire aviation field. Up to now, there is no direct measurement of the pilot’s driving of the aircraft. The method or equipment of pushing and pulling force and torsion moment applied to the steering wheel during the process. Summary of the invention [0003] The purpose of the present invention is to overcome the shortcomings of the existing measurement methods and provide a steering column force sensor for an aircraft, which can directly measure the push-pull force...

Claims

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Application Information

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IPC IPC(8): G01L5/22G01L1/22
CPCG01L1/22G01L5/221
Inventor 石荣武尚宏元李晓鹏吕江涛杜友民李明波
Owner 中航电测仪器(西安)有限公司
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