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Aircraft braking system dynamic load spectrum integration test method

A technology of dynamic load and braking system, applied in the direction of aircraft component testing, aircraft parts, ground devices, etc., can solve problems such as inaccurate and sufficient simulation, reduce the number of installed test taxis and test flights, reduce technical risks, and save money Effect

Active Publication Date: 2014-03-05
XIAN AVIATION BRAKE TECH
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  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] In order to overcome the shortcomings in the prior art that cannot accurately and fully simulate the influence of aircraft aerodynamic lift on the aircraft landing load during the aircraft landing braking process, the present invention proposes a joint test method for the dynamic load spectrum of the aircraft braking system

Method used

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  • Aircraft braking system dynamic load spectrum integration test method
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  • Aircraft braking system dynamic load spectrum integration test method

Examples

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Embodiment 1

[0057]This embodiment is a method for the joint test of the dynamic load spectrum of the brake system of a certain type of aircraft.

[0058] The joint test of the dynamic load spectrum of the aircraft brake system is carried out on an aircraft brake inertia test bench. The drum diameter of the test bench is 2.54m, and the surface friction coefficient is 0.5. The aircraft brake inertia test bench is an existing technology, including drums, motors, drivers and other parts, which provide energy and rotational speed for the joint test of the dynamic load spectrum of the aircraft brake system.

[0059] The joint test of the dynamic load spectrum of the aircraft brake system also requires a dynamic load spectrum control device, which is also an existing technology, including a hydraulic source, a dynamic load spectrum controller, a hydraulic servo loading module, a hydraulic loading cylinder, a drum speed sensor and a load sensors etc. The dynamic load spectrum controller is an in...

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Abstract

The invention discloses an aircraft braking system dynamic load spectrum integration test method. According to actual lifting force characteristics of an aircraft during landing, a dynamic load spectrum of aircraft wheel loads on the speed of the aircraft can be established; in a braking system integration test, the aircraft wheel loads are regulated in real time according to the dynamic load spectrum, and a braking system dynamic integration test is conducted. In the aircraft braking system dynamic integration test, accurate simulation of the actual lifting force characteristics of the aircraft during landing is realized by means of dynamic regulation of the aircraft wheel loads, and consistency between in-plant test conditions and external-field actual working conditions is improved. By means of the aircraft braking system dynamic load spectrum integration test method, performance tests can be conducted on braking systems of various models of aircrafts more strictly, accuracy and the degree of confidence of braking system test results are increased, as a result, the number of times of test gliding and test flights for installation of the braking systems can be greatly reduced, a large amount of expenditure is saved, and the technical risk is lowered. Meanwhile, the aircraft braking system dynamic load spectrum integration test method can also provide accurate and comprehensive test data for take-off and landing of the aircrafts under complicated meteorological conditions, and therefore safety and reliability of aircraft braking are improved.

Description

technical field [0001] The invention relates to the field of aircraft wheels, in particular to a dynamic load spectrum joint test method for an aircraft braking system. Background technique [0002] The joint test of the aircraft braking system is the most important test item before the installation of the aircraft braking system. During the test, a large-diameter drum is used to simulate the airstrip, and the rolling of the wheel relative to the ground when the aircraft lands is converted into the friction of the wheel relative to the surface of the drum. Rolling; the hydraulic cylinder is used to push the wheel to press the drum to simulate the load of the weight of the aircraft on the wheel; and the kinetic energy of the drum is used to simulate the kinetic energy of the actual landing of the aircraft; thus simulating the take-off and taxiing of the aircraft under various runway conditions , Landing, aborted take-off process, check and evaluate the working performance of ...

Claims

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Application Information

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IPC IPC(8): B64F5/00B64F5/60
Inventor 刘劲松焦坤范淑芳刘彦斌
Owner XIAN AVIATION BRAKE TECH
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