Centrifugal force separation type loading test device for rigid rotor wing main paddle central piece

Abstract

The invention provides a centrifugal force separation type loading test device for a rigid rotor wing main paddle central piece. The centrifugal force separation type loading test device comprises the rigid main paddle central piece, a tension and torsion strip false piece, a support arm false piece, a separation type loading connector and two centrifugal force loading mechanisms, the rigid main paddle central part is nested in a columnar sleeve structure of the support arm false part, one end of the tension-torsion strip false part is fixedly connected with the tension-torsion strip base and is fixedly connected with the end part of the rigid main paddle central part, and the other end of the tension-torsion strip false part is fixedly connected with the middle connecting part of the separated loading joint; and the joint parts at the two ends of the separated loading joint are respectively connected with a centrifugal force loading mechanism so as to be connected with the loading execution mechanism through the centrifugal force loading mechanisms, and the separated loading joint is used for applying centrifugal force to the two centrifugal force loading mechanisms and transmitting the centrifugal force to the tension-torsion bar false part. According to the technical scheme provided by the embodiment of the invention, the problems that the test measurement and control difficulty is high and uncontrollable risks exist due to the fact that the flapping force and the shimmy force need to be greatly improved in the test process in the existing fatigue test scheme are solved.

Description

technical field [0001] The present invention relates to but not limited to the technical field of fatigue test of rigid rotor main propeller central part, in particular to a centrifugal force separation loading test device for rigid rotor main propeller central part. Background technique [0002] As the key part of the helicopter structure, the main propeller central part bears all the loads transmitted by the blades. During the fatigue test, each arm needs to be loaded with centrifugal force, shimmy force and flapping force at the same time. [0003] At present, the laboratory has a relatively mature fatigue test plan for the main rotor central part of the spherical flexible rotor helicopter, and its test device has successfully verified the fatigue life of the main rotor central part of the spherical flexible rotor helicopter. However, for the fatigue life assessment of the rigid rotor main propeller central part, in the existing fatigue test program of a certain type of r...

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Problems solved by technology

[0005] The purpose of the present invention is: the present invention provides a kind of centrifugal force separation type loading test device of rigid rotor main propeller central part, to solve the existing scheme of carrying out fatigue test by centrifugal force terminal loading, due to the impact of centrifugal force on swinging force, shimmy force load There is a phenomenon of unloading. Therefore, it is necessary to greatly increase the swinging force and shimmy force during the test, which makes the test measurement and control difficult, and there are problems of uncontrollable risks.

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