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Nose landing gear hinge point force testing device and load calibration method

A technology of nose landing gear and testing device, which is applied in the direction of aircraft component testing, etc., which can solve the problems of test accuracy decline and existing test accuracy, and achieve the effect of accurate hinge point force test

Active Publication Date: 2020-05-19
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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  • Nose landing gear hinge point force testing device and load calibration method
  • Nose landing gear hinge point force testing device and load calibration method
  • Nose landing gear hinge point force testing device and load calibration method

Examples

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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 with 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 with 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 ap...

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 airplane ground strength tests. The invention provides a nose landing gear hinge point force testing device and a load calibration method. Different using workingconditions of a nose landing gear are simulated by means of a test bed, the hinge point force of the nose landing gear under various working conditions is accurately tested, the hinge point force test method which is high in precision, long in service life and capable of bearing large impact vibration is achieved, and data guidance is provided for design of the structure and strength of the noselanding 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 Applications(China)
IPC IPC(8): B64F5/60
CPCB64F5/60
Inventor 李霄杨正权陈熠
Owner CHINA AIRPLANT STRENGTH RES INST