STRUCTURE AND METHOD FOR MOUNTING AN AIRCRAFT WEIGHT SENSOR WITHIN A TUBULAR AXLE OF AN AIRCRAFT UNDERCARRIAGE

摘要

A mounting and mounting method for a sensor positioned within a tubular axle of an aircraft undercarriage which will provide an output voltage proportional to the angular deflection of an axle for computation of aircraft gross weight. The sensor is not affected by cross-sectional distortions of the tubular axle under loading, undersirable shear frictional effects at the interface between the sensor mounting and the tubular axle and differential angular deflections of the axle. The cylindrical mounting member for the sensor has a pair of O-rings adjacent opposite ends thereof which are positioned to space the periphery of the mounting member from the bore of the tubular axle and which are under radial compression and act to provide uniform radial compressive forces applied about the full circumferential periphery of the cylindrical mounting member and absorb distortions of the axle by elastic deformation thereof. At least one of the O-rings is axially compressed for increased radial compression between the cylindrical mounting and the tubular axle to further improve the action in immunizing the sensor from distortion effects in the axle and maintain the sensor in the desired position endwise of the tubular axle. In the method of mounting the sensor, the cylindrical mounting member which carries the sensor has a pair of O-rings associated therewith adjacent opposite ends thereof and this structure is inserted axially within the tubular axle. The O-rings are sized to achieve radial compression between the mounting member and the tubular axle and with one of the O-rings having additional axial force exerted thereagainst to increase the radial compression to improve the action of the O-rings and assure maintaining the location of the sensor axially of the tubular axle.