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Power failure fault indication retaining circuit of aero-engine auxiliary power unit controller

An auxiliary power unit and aero-engine technology, which is applied in the field of aero-engines, can solve the problems that pilots know about power failure and cannot effectively ensure flight safety, and achieve the effect of simple structure, strong practicability, and flight safety

Active Publication Date: 2019-06-14
四川海特亚美航空技术有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] When the control system of the aero-engine auxiliary power unit is working normally or malfunctioning, when the power supply of the control system of the auxiliary power unit suddenly loses power or fails, in the prior art, the pilot will not be able to understand the working state of the power-off money, resulting in the inability to effectively use the corresponding control system. Countermeasures, so that the safety of flight cannot be effectively guaranteed

Method used

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  • Power failure fault indication retaining circuit of aero-engine auxiliary power unit controller
  • Power failure fault indication retaining circuit of aero-engine auxiliary power unit controller

Examples

Experimental program
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Effect test

Embodiment 1

[0026] The present invention is realized through the following technical solutions, as figure 1 , figure 2 As shown, the power-down fault indication holding circuit of the aero-engine auxiliary power unit controller is connected with the aero-engine auxiliary power unit controller, and the aero-engine auxiliary power unit controller includes a controller provided with a microprocessor IC1, a data acquisition Sensor, indicator light and solenoid valve assembly; including bidirectional time-division multiplexing buffer driving transceiver IC2 connected to microprocessor IC1, buffer IC3 and driving trigger respectively connected to bidirectional time-division multiplexing buffer driving transceiver IC2, The power-down fault indicator IC6 connected with the drive trigger; the buffer IC3 is connected with the data acquisition sensor; the drive trigger is also respectively connected with the indicator light and the output end of the solenoid valve assembly.

[0027] It should be n...

Embodiment 2

[0030] This embodiment is further optimized on the basis of the above embodiments, such as figure 2 As shown, the driving flip-flop includes a first driving flip-flop IC4 and a second driving flip-flop IC5 with the same structure, the first driving flip-flop IC4 and the power-down fault indicator IC6; the second driving flip-flop IC5 They are respectively connected with the output ends of the indicator light and the solenoid valve assembly.

[0031] It should be noted that, through the above improvements, the first drive trigger IC4 and the second drive trigger IC5 with the same signal and structure, wherein the first drive trigger IC4 is connected with the power-down fault indicator IC6 for power-down The fault signal is transmitted to the power-off fault indicator IC6, and the power-off fault indicator IC6 can display the fault information before the power-off fault occurs in real time, which is convenient for the pilot to check in real time and respond and deal with the fa...

Embodiment 3

[0035] This embodiment is further optimized on the basis of the above embodiments, such as figure 1 As shown, the pin P0.7-pin P0.0 of the microprocessor IC1 is connected with the pin A7-pin A0 of the bidirectional time-division multiplexing buffer driving transceiver IC2.

[0036]It should be noted that, through the above-mentioned improvements, the pin P0.7 of the microprocessor IC1 is connected to the pin A7 of the bidirectional time-division multiplexing buffer drive transceiver IC2, and the pin P0.6 of the microprocessor IC1 is connected to the bidirectional time-division multiplex drive transceiver IC2. The pin A6 of the multiplexing buffer driving transceiver IC2 is connected, the pin P0.5 of the microprocessor IC1 is connected with the pin A5 of the bidirectional time-division multiplexing buffer driving transceiver IC2, and the pin P0.4 of the microprocessor IC1 Connect with pin A4 of bidirectional time-division multiplexing buffer drive transceiver IC2, pin P0.3 of m...

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Abstract

The invention discloses a power failure fault indication retaining circuit of an aero-engine auxiliary power unit controller. The circuit is connected with the aero-engine auxiliary power unit controller, the aero-engine auxiliary power unit controller comprises a controller with a microprocessor, a data collection sensor, an indicator lamp and an electromagnetic valve module, and comprises a bidirectional time-division multiplexing buffer driving transceiver connected with the microprocessor, a buffer and a drive trigger which are connected with the bidirectional time-division multiplexing buffer driving transceiver, and a power failure fault indicator connected with the drive trigger; the buffer is connected with the data collection sensor; and the drive trigger is further connected withthe electromagnetic valve module. The power failure fault indication retaining circuit has the advantages that a working state before power failure can be conveniently mastered by an aviator in comparison with the prior art, thereby adopting a corresponding measure at any time and guaranteeing the flight safety.

Description

technical field [0001] The invention relates to the technical field of aero-engines, in particular to a power-down fault indication holding circuit of an aero-engine auxiliary power unit controller. Background technique [0002] The aero-engine auxiliary power unit controller is based on the controller, APU speed, exhaust temperature, and some switch signals are sent to the microprocessor of the controller after sensor measurement and signal conditioning. After logical judgment by the controller and calculation of the APU control law, the real-time control of the fuel flow of the APU is issued to control the speed and temperature of the APU, and the current status is displayed in the indicator display window of the controller in real time. [0003] When the control system of the aero-engine auxiliary power unit is working normally or malfunctioning, when the power supply of the control system of the auxiliary power unit suddenly loses power or fails, in the prior art, the pi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B23/02
Inventor 蒋勇高剑杨斌陈浩
Owner 四川海特亚美航空技术有限公司