CN105717461A - Rack power supply fault simulation testing device - Google Patents

Abstract

The invention belongs to the engine numerical control system measurement and control field, and provides a rack power supply fault simulation testing device being able to perform remote control. The rack power supply fault simulation testing device includes a CPU module (3), an analog quantity acquisition module (4), a digital quantity output module (5), a relay module (6), a power acquisition module (7) and an interface module (8).

Description

Stand power failure simulation test device

Technical field

The invention belongs to Engine digital control system measurement and control area.

Background technology

Stand power failure analog is mounted on engine pedestal, for a kind of test tool of power interruptions test in aero-engine Digital electronic control system bench test, according to aircraft power supply characteristic requirements, the fail operation situation that aero-engine Digital electronic control system power supply transient state is interrupted need to be verified.

Being generally adopted programmable power supply in conventional power failure simulation test and realize the simulation of aero-engine Digital electronic control system DC source 50ms broken string situation, this method has problems with: 1) cost is high；2) fault characteristic that Special alternating-current generator power supply interrupts cannot be simulated；3) owing to electromotor is hung on stand, inconvenient operation；4) record to process of the test is lacked.

Summary of the invention

The purpose of the invention: a kind of stand power failure simulation test device that can carry out remotely control is provided in aero-engine Digital electronic control system bench test.

The technical scheme of the invention:

A kind of stand power failure simulation test device, including:

CPU module (3), analogue collection module (4), digital output module (5), relay module (6), electric quantity acquisition module (7), interface module (8)；

CPU module (3), it is connected with host computer (1), receive the control instruction of host computer, described control instruction includes the open command to a certain bar power circuit and broken string duration, CPU module (3) sends described open command to digital output module (5), sends the broken string to same power circuit and recover instruction after broken string duration；

Digital output module (5), it is connected with CPU module (3), open command according to CPU module (3) produces relay and disconnects control signal, recovers instruction according to the broken string of CPU module (3) and produces relay Closed control signal；

Relay module (6), it is connected with digital output module (5), including one or more power circuit, relay module (6) disconnects control signal according to described relay and controls corresponding power circuit disconnection, controls corresponding power circuit according to described relay Closed control signal and again closes；

Interface module (8), each road power circuit of aircraft/stand power-supply system (9) is connected with one end of the corresponding power circuit of relay module (6), the corresponding power interface of the other end of described corresponding power circuit with aero-engine Digital electronic control system (10) is connected；

Electric quantity acquisition module (7), is connected with interface module (8), and the information about power of collection power circuit converts master die analog quantity signal to and feeds back to analogue collection module (4)；

Analogue collection module (4), is connected with electric quantity acquisition module (7) and CPU module (3) respectively, and by CPU module (3), described information about power is sent to host computer (1).

The advantage of the invention is

1) adopting modularized design, technology maturation, autgmentability, maintainability are good.

2) adopt host computer remotely to control, and process of the test parameter (voltage of power supply, electric current, frequency etc.) can be recorded, and can play back；

3) adopt removable interface module, realize generalization by changing interface module, reduce cost；

4) control accuracy is high, and CPU module adopts mature modules, have precision reach 1ms intervalometer；

5) adopt balanced force type relay as the switch controlling on/off, reduce the error that timing outage time controls.

Accompanying drawing illustrates:

Fig. 1 is the schematic diagram of aero-engine Digital electronic control system power failure simulation test device.

1-host computer, 3-CPU module, 4-AI module, 5-DO module, 6-relay module, 7-electric quantity acquisition module, 8-interface module, 9-aircraft/stand power-supply system, 10-aero-engine Digital electronic control system

Detailed description of the invention

A kind of stand power failure simulation test device, as it is shown in figure 1, include:

CPU module (3), analogue collection module (4), digital output module (5), relay module (6), electric quantity acquisition module (7), interface module (8)；

CPU module (3), it is connected with host computer (1), receive the control instruction of host computer, described control instruction includes the open command to a certain bar power circuit and broken string duration, CPU module (3) sends described open command to digital output module (5), sends the broken string to same power circuit and recover instruction after broken string duration；

Digital output module (5), it is connected with CPU module (3), open command according to CPU module (3) produces relay and disconnects control signal, recovers instruction according to the broken string of CPU module (3) and produces relay Closed control signal；

Relay module (6), it is connected with digital output module (5), including one or more power circuit, relay module (6) disconnects control signal according to described relay and controls corresponding power circuit disconnection, controls corresponding power circuit according to described relay Closed control signal and again closes；

Interface module (8), each road power circuit of aircraft/stand power-supply system (9) is connected with one end of the corresponding power circuit of relay module (6), the corresponding power interface of the other end of described corresponding power circuit with aero-engine Digital electronic control system (10) is connected；

Electric quantity acquisition module (7), is connected with interface module (8), and the information about power of collection power circuit converts master die analog quantity signal to and feeds back to analogue collection module (4)；

Analogue collection module (4), is connected with electric quantity acquisition module (7) and CPU module (3) respectively, and by CPU module (3), described information about power is sent to host computer (1).

The specific works process of this device is as follows:

In relay module 6, all relays are normally off, when arranging a certain road power circuit disconnection fault or time power source, (timing is 20ms～200ms, precision is 2ms) hit fault time, host computer 1 sends broken string instruction and the wink break time of this road power circuit to CPU module 3, CPU module 3 controls digital output module 5 after receiving this road power circuit broken string instruction and produces relay disconnection control signal and broken string recovery signal, the disconnection and the broken string that control relay module 6 Zhong Gai road power circuit recover, electric quantity acquisition module (comprises the voltage of power supply, electric current, the electricity such as frequency) 7, the electricity of power supply is converted to standard (being usually the voltage signal of the 0V～10V) analog signals that analogue collection module 4 gathers.Electric quantity signal is sent to host computer 1 end by CPU module 3 and displays and can be recorded by analog acquisition signal.

It is achieved thereby that Digital electronic control system bench test power supply broken string and hit fault simulation.

Claims (1)

1. a stand power failure simulation test device, it is characterised in that including:

CPU module (3), analogue collection module (4), digital output module (5), relay module (6), electric quantity acquisition module (7), interface module (8)；

CPU module (3), it is connected with host computer (1), receive the control instruction of host computer, described control instruction includes the open command to a certain bar power circuit and broken string duration, CPU module (3) sends described open command to digital output module (5), sends the broken string to same power circuit and recover instruction after broken string duration；

Digital output module (5), it is connected with CPU module (3), open command according to CPU module (3) produces relay and disconnects control signal, recovers instruction according to the broken string of CPU module (3) and produces relay Closed control signal；

Relay module (6), it is connected with digital output module (5), including one or more power circuit, relay module (6) disconnects control signal according to described relay and controls corresponding power circuit disconnection, controls corresponding power circuit according to described relay Closed control signal and again closes；

Interface module (8), each road power circuit of aircraft/stand power-supply system (9) is connected with one end of the corresponding power circuit of relay module (6), the corresponding power interface of the other end of described corresponding power circuit with aero-engine Digital electronic control system (10) is connected；

Electric quantity acquisition module (7), is connected with interface module (8), and the information about power of collection power circuit converts master die analog quantity signal to and feeds back to analogue collection module (4)；

Analogue collection module (4), is connected with electric quantity acquisition module (7) and CPU module (3) respectively, and by CPU module (3), described information about power is sent to host computer (1).