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Main engine linkage test system and method

A test system and test method technology, applied in the field of the main engine linkage test system, can solve problems such as over-rotation, and achieve the effects of fast response speed, solving over-rotation, high degree of automation and reliability

Active Publication Date: 2019-03-22
CHINA AVIATION POWER MACHINE INST
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AI Technical Summary

Problems solved by technology

[0004] The present invention provides a main engine linkage test system and method to solve the technical problem of the over-rotation phenomenon in the existing main engine start test system

Method used

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  • Main engine linkage test system and method
  • Main engine linkage test system and method

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Embodiment Construction

[0035] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0036] refer to figure 1 , a preferred embodiment of the present invention provides a main engine linkage test system, including a host computer 10, a programmable controller 20, a contactor 30, an auxiliary power unit 40, a digital controller panel 50, a generator 60, a pure resistance The electrical adjustable load 70 and the power generation controller 80, the generator 60, the contactor 30 and the purely resistive adjustable load 70 are sequentially connected in series to form an electrical circuit, and the contacts of the contactor 30 are connected across the generator 60 and the purely resistive adjustable load. Between the loads 70, the upper computer 10 is electrically connected to the...

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Abstract

The invention discloses a main initiated linkage test system and method. The system is composed of an upper computer, a programmable controller, a contactor, an auxiliary power unit, a digital controller panel, a generator, a purely resistive adjustable load and a generation controller. The generator, the purely resistive adjustable load, and the contactor are connected in series successively to form an electrical loop. Main initiated starting signals on the digital controller panel are divided into two paths; at one path, the programmable controller controls the coil of the contactor to open or close so as to realize connection or disconnection of the electrical loop; and at the other path, a fuel adjusting value of the auxiliary power unit is connected to adjust the fuel amount. Besides, a main initiated starting key is arranged on the digital controller panel; and the programmable controller is used for processing a loading signal and a main initiated starting signal, so that the loading signal and the main initiated signal are triggered together in a linkage manner by the main initiated starting key, so that an excess revolution problem during the main initiated starting process can be solved. The main initiated linkage test system has advantages of fast response speed, high automation degree, and high reliability.

Description

technical field [0001] The invention relates to the field of aero-engine control, in particular to a main engine linkage test system and method. Background technique [0002] In the prior art, an active starting test system is disclosed, which simulates the situation of starting a large engine by an APU (auxiliary power unit) in the field. For the APU, the power required to start a large engine is equivalent to the load power of the APU, and the APU test bench does not have a large engine, so it is necessary to use a suitable pure resistive load device to equivalent to the power required for the start of a large engine. The existing active starting test system includes APU (including digital controller), digital controller panel, generator and power generation controller, pure resistive load and upper computer, etc., such as figure 1 As shown, the working principle of the active starter test system is: the APU starts normally to the no-load state; press the button on the di...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M15/00
CPCG01M15/00
Inventor 李伟蔡衍言洁奕于海燕
Owner CHINA AVIATION POWER MACHINE INST
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