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A test device for hinge point force of nose landing gear and load calibration method

A technology of nose landing gear and testing device, which is applied in the direction of aircraft component testing, etc. It can solve the problems of test accuracy decline and existing test accuracy, and achieve the effects of improving test accuracy, test accuracy, and eliminating relative deviations

Active Publication Date: 2021-10-15
CHINA AIRPLANT STRENGTH RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The concentrated load on the ground is not exactly equal to the sum of the component forces of each hinge point, so there is a problem of test accuracy, and the non-linear term is generated due to the influence of mechanical errors during the installation of the test bench and force sensor, which makes the hinge point force test process , it will also cause the problem of test accuracy drop

Method used

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  • A test device for hinge point force of nose landing gear and load calibration method
  • A test device for hinge point force of nose landing gear and load calibration method
  • A test device for hinge point force of nose landing gear and load calibration method

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Embodiment 1

[0033] The present embodiment provides a test device for testing the hinge point force of the front landing gear, such as figure 1 and figure 2 as shown, figure 1 It is the front view of the hinge point force testing device of the present invention, figure 2 It is a side view of the hinge point force testing device of the present invention.

[0034] combine figure 1 and figure 2 As shown, the test device for the hinge point force test of the front landing gear includes a load-bearing column 1, a hanging basket 6, a second loading actuator 2, a three-way force sensor 8, a first loading actuator 18, and a first force sensor 17 , guide pulley 16 and flywheel 19.

[0035] Such as figure 1 As shown, the load-bearing column 1 is a frame structure, one end of the second loading actuator 2 is connected with the upper frame of the load-bearing column 1, and the other end is connected with the upper end of the hanging basket 6, and the second loading actuator 2 is used to appl...

Embodiment 2

[0047] The present embodiment provides a method for testing the hinge point force of the front landing gear, utilizing the test device as described above, such as Figure 4 and as shown in Figure 5, Figure 4 It is the force schematic diagram of the landing gear hinge point of the present invention, Figure 5 It is a logical schematic diagram of the landing gear hinge point test method of the present invention, and the test method comprises the following steps:

[0048] (1) Front landing gear installation

[0049] Test device providing the hinge point force of the nose landing gear:

[0050] Three-way force sensors are respectively arranged at the two front hinge points (10), the two rear hinge points (13), the diagonal brace hinge point (11) and the lock brace hinge point (12) of the front landing gear (14) (8). The upper end surface of each three-way force sensor (8) is connected with the test fixture (7) at the bottom of the hanging basket (6), and the lower end surface...

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Abstract

The invention belongs to the field of aircraft ground strength testing, and provides a nose landing gear hinge point force test device and a load calibration method, which simulate different operating conditions of the nose landing gear by means of a test bench, and accurately test the hinge point force of the nose landing gear under various working conditions. Point force, realize a hinge point force test method with high precision, long life, and can withstand large impact vibration, and provide data guidance for the structure and strength design of the nose landing gear.

Description

technical field [0001] The invention belongs to the field of aircraft ground strength tests, and in particular relates to a test device and a test method for the hinge point force of a nose landing gear. Background technique [0002] From landing to taking off again, the aircraft needs to go through the stages of landing and rolling, braking to decelerate, maneuvering and turning, and rolling and taking off. Force and lateral maneuvering force. The landing gear is connected to the fuselage of the aircraft through structures such as hinge points and struts, among which, the main hinge point and the rear hinge point bear almost all ground loads. Therefore, the hinge point force is one of the important parameters in the strength design of the landing gear and the fuselage structure. [0003] During the dynamic test of the landing gear, the landing gear is installed on a special test bench to load it through a hydraulic actuator, and the load test is usually carried out by pas...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/60
CPCB64F5/60
Inventor 李霄杨正权陈熠
Owner CHINA AIRPLANT STRENGTH RES INST