Loading method and loading device for static strength experiment of aircraft wing

Abstract

The invention provides a loading method and device for a static strength experiment of an airplane wing. The device comprises a two-rotation two-movement four-degree-of-freedom parallel loading device and two two-stage lever systems. The parallel loading device comprises a fixed platform, a loading platform, a force sensor, a first motion branch, a second motion branch, a third motion branch and a fourth motion branch, the loading platform is connected with the fixed platform through the four motion branches, and the two two-stage lever systems are located on the loading platform and symmetrically distributed on the two sides of the upper portion of the loading platform. Each two-stage lever system is provided with four loading point positions, and the whole device is provided with eight loading point positions. And force sensors are arranged on the four motion branches. The four motion branches are all driven by a driving moving pair, and a hydraulic cylinder is adopted for driving. According to the invention, the direction and magnitude of the loading force can be adjusted at the same time in the loading process of the wing static experiment, and the experiment error is effectively reduced.

Description

technical field [0001] The invention relates to the field of aviation experiment testing, in particular to a loading method and a loading device for an aircraft wing static strength experiment based on a parallel mechanism and a lever system. Background technique [0002] In the ground strength test of the aircraft structure, the static test of the whole aircraft is an important test item for checking the bearing capacity, stiffness and other characteristics of the aircraft structure. In the whole machine static test, in order to simulate the loading force on the wing in flight, it is necessary to adjust the loading direction to ensure that the loading force is perpendicular to the wing surface. [0003] At present, the loading device for static experiments on aircraft wings is mainly the adhesive tape-lever loading system. Other common static loading methods for wings include pallet loading and airbag loading. The tape-lever system requires tape to be applied to the surfac...

AI Technical Summary

Problems solved by technology

[0004] The invention provides a four-degree-of-freedom wing experimental loading device, which aims to solve the problem that the loading direction cannot always be perpendicular to the wing surface and the problem that the loading force is uniformly distributed when performing the wing static test by other loading methods

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