Rotor head pulling and twisting strip type propeller hub for helicopter blade dynamic balance test table

Abstract

The invention relates to the technical field of helicopter test, in particular to a rotor head pulling and twisting strip type propeller hub for a helicopter blade dynamic balance test table. The propeller hub comprises a pin shaft (1), a needle bearing (2), a shaft pin (3), a variable-pitch hinge casing end cover (4), a pulling and twisting strip (5), a variable-pitch hinge shaft casing (6) and a variable-pitch hinge shaft neck (7), wherein the first end of the tubular element variable-pitch hinge shaft neck (7) is connected with a test table center element through a swinging hinge, the variable-pitch hinge shaft neck (7) is arranged inside the variable-pitch hinge shaft casing (6) through the needle bearing (2) in a sleeving way, one end of the pulling and twisting strip (5) is fixedly connected with the first end of the variable-pitch hinge shaft neck (7) through the shaft pin (1), and the other end of the pulling and twisting strip (5) is connected with the variable-pitch hinge shaft casing (6) and the variable-pitch hinge casing end cover (4) through the pin shaft (3). The structure can be designed to be simpler and more compact. The needle bearing (2) does not bear the centrifugal force, so the service life of the needle bearing can reach the limitless service life, and higher-precision blade hinge moment measurement can be realized.

Description

technical field [0001] The invention relates to the technical field of helicopter testing, in particular to a helicopter blade dynamic balance test bench rotor head twist bar type propeller hub. Background technique [0002] There are two methods for the rotor head hub of the existing helicopter blade dynamic balance test bench. One is to use the elastic bearing to realize the pitch change of the hub. The main part of the elastic bearing is made of rubber and bowl-shaped thin steel sheets. The advantage of the bearing is that the propeller hub does not need to be lubricated, and the maintenance is very convenient, but at the same time, there is an obvious defect that the elastic bearing has a torsional elastic moment, and it is large and unstable with the change of the ambient temperature. have a greater impact. The other is to use end bearings plus needle roller bearings to realize the pitch change of the propeller hub. The end face bearings bear the centrifugal force, and...

AI Technical Summary

Problems solved by technology

[0003] Due to the above two types of existing helicopter blade dynamic balancer rotor head hub types, the first type has the disadvantage of poor hinge torque accuracy, and this method cannot be used for models that require high hinge torque measurement accuracy

The second type has a relatively high measurement accuracy of the hinge torque due to the small rolling friction of the metal bearing, but due to the large size of the end bearing, it is not conducive to the propeller hub parameter measurement equipment on the test bench, such as the hinge torque sensor and the linear operation of the pitch angle adjustment. actuator layout

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