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Aircraft actuation system load loading device

An actuation system and load-loading technology, which is applied in the aviation field, can solve problems such as difficult position adjustment and space occupation, and achieve the effects of shortening the time cycle, speeding up the workflow, and speeding up the process

Active Publication Date: 2017-01-25
BEIJING AERONAUTIC SCI & TECH RES INST OF COMAC +1
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The equivalent loading method applies the force of the loading actuator to the tested actuator through the rocker arm mechanism, which is simple and convenient. The disadvantage is that the tested actuator is installed on the bench, which takes up more space. The loading actuator is fixed on the table, and each actuator needs to be drilled for installation, and the position is difficult to adjust

Method used

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Embodiment Construction

[0033] The technical solution of the present invention will be further described below in conjunction with the accompanying drawings.

[0034] Such as Figure 1-Figure 4 As shown, the present invention is an aircraft actuation system load loading device, which device includes: a connecting mechanism, a slider mechanism and a bracket mechanism;

[0035] The connection mechanism includes a wing shaft, a wing shaft rocker arm, an adjustment device, a fixing bolt of the tested actuator and a loading actuator bolt;

[0036] The slider mechanism includes a first slider, a second slider and a slide rail;

[0037] The support mechanism includes a loading platform, a first slider bracket, a second slider bracket and a loading platform bracket;

[0038] Wherein, the upper end of the loading platform is provided with a reserved hole for installing the wing shaft, the loading platform bracket is arranged on the loading platform below the reserved hole, and the first slider bracket is se...

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Abstract

The invention belongs to the technical field of aviation and particularly relates to an aircraft actuation system load loading device applicable to an aircraft actuation system loading project. According to the device, a single-actuator loading device and an aircraft airfoil loading device are improved, double effects of applying one device to single-actuator performance parameter index evaluation and aircraft airfoil actuator joint loading are realized, and a novel loading device is provided for the aircraft actuation system. The loading device provided by the invention is simple and convenient, and meets two loading needs for top loading and airfoil loading in the field of aircraft actuation system load loading through a connecting mechanism, a slider mechanism and a bracket mechanism. The resources are saved; and two processes in the aircraft loading project are realized by one mechanism, thus the equipment resources as well as the space resources of a laboratory are saved. The workflow is accelerated; and through the technical scheme, the time period of original two processes can be effectively shortened, and the process of applying an actuator to the aircraft airfoil is accelerated.

Description

technical field [0001] The invention belongs to the technical field of aviation, and in particular relates to a load loading device suitable for loading engineering of an aircraft actuation system. Background technique [0002] In the field of traditional aircraft actuation loading, there are mainly two ways to assess the technical indicators of a single actuator. One is to simulate the parameters of the actuator loading through the load simulation platform, and the other is to conduct the same level of actuators. In the "top-to-top" simulation of actuating parameters, the performance parameters of a single actuator can be obtained in both ways. In the field of wing surface loading, there are mainly two ways. One is through the pasting method. Stretchable rubber strips are added to the upper and lower skins of the surface to simulate the load of the aircraft wing surface, so as to achieve equivalent loading on the actuator. The second is to realize the joint loading effect ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C13/00B64F5/60G01M13/00
CPCB64C13/00G01M13/00
Inventor 李喜玉白志强熊斯
Owner BEIJING AERONAUTIC SCI & TECH RES INST OF COMAC
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