Aircraft engine test site digital bus control device

An aero-engine and digital bus technology, applied in the direction of engine testing, measuring devices, electrical program control, etc., to achieve good performance and realize the effect of intelligence

Inactive Publication Date: 2015-04-29
HARBIN DONGAN ENGINE GRP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

This technology doesn't require extra components like controllers or wires for testing an aircraft gas turbine (Airplane). It uses wireless communication between different devices at both ends connected through specialized hardware that monitors the location where they are located. By doing this, these tests have improved safety and reliability compared with older methods such as manual inspections. They work well even when there may be interruptions from other sources.

Problems solved by technology

This technical problem addressed by this patented describes how testing airplanes during their manufacturing must have advanced technology capabilities that allow them to perform more accurate tests while also being able to handle complex operations like starting up/down from sleep mode when they're flying at altitudes above 50 km (the highest level). Current methods require expensive hardware systems due to high power consumption required for long periods of time. Additionally, existing analogue controllers used for these purposes may become less effective over longer durations because of changes made after hours of use.

Method used

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  • Aircraft engine test site digital bus control device

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Embodiment Construction

[0008] As shown in the figure, the digital bus control device at the aero-engine test site includes a control system I, a communication interface II, an output interface III, and a power supply interface IV. The control system I includes a main control circuit board 1 and a central processing unit set on the main control circuit board 1a, output module 1c, power supply module 1d, communication module 1e, relay module 1f; the power supply interface IV is connected to the power supply through a shielded signal cable, and connected to the main control circuit board 1 through the power supply module 1d and the power supply circuit to supply power for each electronic component; The communication interface II is connected to the control system of the engine test bench through a shielded signal cable, and is connected to the signal input end of the central processing unit 1a on the main control circuit board 1 through the module 1b and the communication circuit; the signal output end of t

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PUM

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Abstract

The invention relates to an aircraft engine test site digital bus control device. The aircraft engine test site digital bus control device comprises a control system, a communication interface, an output interface and a power supply interface, and the control system comprises a main control circuit board, a central processing unit, an output module, a power supply module, a communication module and a relay module; the power supply interface is connected with the main control circuit board; the communication interface is connected with an engine test bed; the central processing unit is connected with the relay module which is connected with the output interface, and the output interface is connected with engine test bed site test equipment through a cable. The aircraft engine test site digital bus control device can monitor the status of an equipment site in real time and has good performance of safety, stability and anti-interference, intelligence of the control device is achieved better, and the requirement for aircraft engine test equipment site control is met.

Description

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Claims

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Application Information

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Owner HARBIN DONGAN ENGINE GRP
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