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Gap measurement method suitable for nonlinear steering system

A measurement method and rudder system technology, applied in the field of rudder systems, can solve problems such as inability to distinguish between gaps and elastic deformations, and achieve the effect of simple operation and broad application prospects

Inactive Publication Date: 2012-12-19
BEIJING RES INST OF MECHANICAL & ELECTRICAL TECH
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Problems solved by technology

[0005] The purpose of the present invention is to provide a new measurement method for the clearance of the aircraft rudder system, which overcomes the defect that the traditional measurement method cannot distinguish the clearance from the elastic deformation, and is especially suitable for the clearance measurement of the nonlinear rudder system

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  • Gap measurement method suitable for nonlinear steering system
  • Gap measurement method suitable for nonlinear steering system
  • Gap measurement method suitable for nonlinear steering system

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Embodiment Construction

[0018] The method for measuring the gap of the aircraft rudder system of the present invention will be described in detail below by taking a non-linear rudder system with low stiffness as an example. In this embodiment, a rudder system with horizontally arranged rudder surfaces common in the field is selected as the measurement object. Those skilled in the art should understand that the method is also applicable to other rudder systems, and the description of the following embodiments does not limit the present invention.

[0019] Such as figure 2 Shown is a schematic diagram of the rudder surface in the rudder system. Wherein, the rudder shaft 2 is connected with the steering gear (not shown in the figure) through the flange, and the rudder shaft 2 drives the rudder surface 1 to rotate around the center line of the rudder shaft.

[0020] (1) Since the rudder surface is installed horizontally, the loading tool is installed at the root of the rudder surface, and the loading ...

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Abstract

The invention provides a gap measurement method suitable for a nonlinear steering system, comprising the following steps of: arbitrarily selecting two points A and B which are symmetrical with each other by taking the centre line of a rudder axle as the center at the root of a control plane; powering off a steering engine, adjusting the control plane drift angle of the steering system to be 0 degree, and respectively carrying out load test at the point A and the point B by taking F as a loading unit, so that a rotating minimum load G' of the control plane is equal to n*F; and 3) resetting the control plane drift angle to be zero degree, loading and unloading the point A and the point B step by step by taking F as the unit, respectively recording the values of the control plane drift angles alpha under the different loads G, and drawing a 'load-angle' relation curve until two closed curves are obtained, wherein the angle difference value of the closed curves is the gap of the steering system at the place where G=0. According to the gap measurement method, the defect of the application of the conventional gap measurement method in a nonlinear system can be overcome, and the elastic deformation can be completely distinguished due to the obtained gap value.

Description

technical field [0001] The invention relates to a rudder system on an aircraft, in particular to a method for measuring the clearance of the rudder system. Background technique [0002] The rudder system of an aircraft is composed of multiple components such as a steering gear, a linkage mechanism, a bearing, and a rudder surface. The accumulation of fit tolerances between various kinematic pairs has brought about structural gaps. The clearance has a strong nonlinearity, which will cause hysteresis on the control surface, reduce the sensitivity, accuracy and torsional frequency of the control, increase the possibility of control surface vibration and flutter, and have an important impact on flight safety. Therefore, the clearance index is very important. The key is that it is comprehensively proposed based on the flight performance requirements (lag and flutter, etc.) and the possibility of structural realization. [0003] When a load is applied to the rudder surface, under...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01B21/16
Inventor 宋锋李增文宋月娥张可
Owner BEIJING RES INST OF MECHANICAL & ELECTRICAL TECH
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