CN202058037U - Bypass adapter - Google Patents
Bypass adapter Download PDFInfo
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- CN202058037U CN202058037U CN2011200460863U CN201120046086U CN202058037U CN 202058037 U CN202058037 U CN 202058037U CN 2011200460863 U CN2011200460863 U CN 2011200460863U CN 201120046086 U CN201120046086 U CN 201120046086U CN 202058037 U CN202058037 U CN 202058037U
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- 238000006243 chemical reaction Methods 0.000 claims abstract description 12
- 230000003321 amplification Effects 0.000 claims abstract description 11
- 238000003199 nucleic acid amplification method Methods 0.000 claims abstract description 11
- 238000002955 isolation Methods 0.000 claims abstract description 10
- 230000005622 photoelectricity Effects 0.000 claims description 3
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- 238000013519 translation Methods 0.000 claims description 2
- 230000003750 conditioning effect Effects 0.000 abstract description 10
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- 238000012545 processing Methods 0.000 abstract description 3
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- 238000010586 diagram Methods 0.000 description 6
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- 238000006073 displacement reaction Methods 0.000 description 3
- 230000036541 health Effects 0.000 description 3
- 230000009471 action Effects 0.000 description 2
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Abstract
The utility model provides a bypass adapter, which is low in cost, high in efficiency, resistant to interference and simple in application, is used for experimental research of an aircraft engine control system, belongs to the technical field of aircraft engine control and aims to solve the problems of high cost, complicated structure, poor interference resistance and the like of an existing rapid prototype control system for an aircraft engine. The bypass adapter comprises a DSP (digital signal processing) core module, a signal driving module and a signal conditioning module, wherein the signal driving module comprises an optical isolation current amplification module and a voltage/current conversion module, and the signal conditioning module comprises a resistance/voltage conversion module, a level conversion module, two photoelectric isolation level conversion modules and two voltage amplification modules. Besides, input ends of the optical isolation current amplification module and the voltage/current conversion module are respectively connected with an output end of the DSP core module, and output ends of the resistance/voltage conversion module, the level conversion module, the two photoelectric isolation level conversion modules and the two voltage amplification modules are respectively connected with an input end of the DSP core module. High-speed serial ports are used for transmitting digital signals in the adapter and a control computer, and master/slave real-time logic of data transmission is used for ensuring instantaneity of a control loop, so that the bypass adapter is long in transmission distance, high in interference resistance and fine in instantaneity.
Description
Technical field
The utility model is used for the control system experimental study of aeromotor, to satisfy the requirement of setting up the electronic engine management system prototype fast, belongs to the Aeroengine control technology field.The rapid prototyping experiment of aeromotor electronic control system needs to make up fast an environment that makes things convenient for the debugging control rule, sensor signal is nursed one's health and gathered, and output current signal drives topworks.
Background technology
In the development process of aeromotor electronic control system, adopt the method for rapid prototyping control system can save cost, and accelerate the product progress greatly.Rapid prototyping control is meant the initial stage in product development, by setting up controlling object and controller model apace, control corresponding model or control algolithm is carried out repeatedly the feasibility that off-line and online test come access control system hardware and software scheme.
Aeroengine electronic controller is being undertaken vital tasks such as the amplification of the processing of the collection of flight environment of vehicle and engine behavior, steering logic and algorithm, steering order and drivings, it has characteristics such as task complexity, real-time, reliability requirement height, so its lead time is long.Adopt the rapid prototyping control technology can greatly improve development efficiency and research level, overcome traditional length consuming time of the method for designing based on the actual physics platform, cost costliness and the high characteristics of risk.
The method that existing rapid prototyping technology adopts is: insert data collecting card at the industrial control computer host slot and realize that signal drives and conditioning functions.Since data collecting card can only provide standard-10V～+ 10V or 4～20mA signal, also must extra sensor signal conditioning and the topworks's driving circuit of development.Data acquisition calorie requirement install driver in addition.This scheme cost height, what snap into the transmission of signal condition and driving circuit from computer data acquiring is simulating signal, transmission range is limited, is subject to disturb.
The utility model content
The utility model purpose is to solve problems such as cost height, complex structure, poor anti jamming capability in the existing aeromotor rapid prototyping control system, and a kind of low cost, efficient, anti-interference, the simple bypass type adapter of application are provided.
The utility model adopts following technical scheme for achieving the above object:
The utility model bypass type adapter, comprise DSP nucleus module, signal driver module and signal condition module, wherein the signal driver module comprises light isolation electric current amplification module and the voltage/current conversion module that input end is connected with DSP nucleus module output terminal respectively, and the signal condition module comprises resistance/voltage transformation module, level translation module, two photoelectricity isolation level conversion modules and two voltage amplification modules that output terminal is connected with DSP nucleus module input end respectively.
Advantage of the present utility model
1) easy to use.Engine control computer directly is connected with adapter by Serial Port Line, and adapter directly is connected with topworks with sensor, does not need interface integrated circuit board and install driver.The exploitation of control program is directly developed on engine control computer.
2) antijamming capability is strong.Adopt high speed serial ports transmission of digital signals in adapter and control computer, long transmission distance, antijamming capability is strong.
3) real-time is good.Adopt the real-time of the master/slave real-time logic assurance control loop of data transmission.
Description of drawings
Accompanying drawing 1 is an aeromotor electronic control system theory diagram.
Accompanying drawing 2 is based on the aeromotor rapid prototyping control system block diagram of bypass type adapter.
Accompanying drawing 3 is theory of constitution block diagrams of bypass type adapter.
Accompanying drawing 4 is master/slave real-time logical flow charts of data transmission.
Accompanying drawing 5 is theory diagrams of signal condition module.
Accompanying drawing 6 is theory diagrams of signal driver module.
Accompanying drawing 7 is based on the Micro Turbine Jet Engine rapid prototyping control system block diagram of bypass type adapter.
Embodiment
Specify method of the present utility model below in conjunction with Fig. 1-Fig. 6.
As shown in Figure 1, in the aeromotor electronic control system, the status signal of sensor acquisition aeromotor as rotating speed, temperature, pressure etc., is input to electronic controller.Electronic controller is after the engine status signal that sensor is imported is carried out signal condition, carry out the processing of steering logic and algorithm then, generate steering order, after steering order is driven, output to topworks, and then change the engine condition amount to predetermined value.
As shown in Figure 2, aeromotor rapid prototyping control system based on the bypass type adapter adopts ordinary PC as engine control computer, be connected to the bypass type adapter by the high speed serial ports, just can realize the collection of sensor signal and the driving of topworks.
As shown in Figure 3, the bypass type adapter is made up of DSP nucleus module, signal condition and signal driver module.The aeromotor sensor is gathered in real time by the DSP nucleus module after nursing one's health through the signal condition module, converts digital signal to, makes a strategic decision to control computer by high speed serial ports real-time Transmission then; The DSP nucleus module receives the control command signal that the control computer decision-making obtains in real time simultaneously, and the electric current amplification by the signal driver module drives topworks's action.
As shown in Figure 4, the work schedule that is in the bypass type adapter of slave mode of operation is controlled the driving of computing machine, its work schedule is: the collection of input signals such as the instruction of driving cabin panel, rotating speed, temperature, pressure, displacement transducer is the driving that is subjected to 2 milliseconds of timers, is the up-to-date input data that are ready to of control computer with little sampling step length; When receiving the complete data packet that control computer is sent, the make an immediate response driving of main frame of adapter, with ready up-to-date input data, signals such as the driving cabin panel instruction that promptly collects, rotating speed, temperature, pressure, displacement transducer send to control computer, and the steering order real-time update that control computer is sent drives topworks's action to driver module.
As shown in Figure 5, the specific implementation method of signal condition module is as follows: signal collection modulation partly has switch acquisition conditioning, rotating speed collection conditioning and analog acquisition conditioning functions.What switch acquisition conditioning part will collect crosses the signal of output 0/3.3V after the photoelectric coupler isolation as switching values such as driving cabin panel instructions, it is that the square wave of 0/3.3V is given the DSP nucleus module that frequency quantity collection conditioning part is isolated the back output amplitude with the signal of speed probe by photoelectricity, analog acquisition conditioning part can receive the input of thermal resistance and thermocouple temperature sensor, pressure transducer and linear variable difference transformer (LVDT) formula displacement transducer, the drive signal of sensor is provided, and it is nursed one's health into the voltage of 0 ~ 3V.
As shown in Figure 6, the specific implementation method of signal driver module is as follows: the signal driver module comprises switching value instruction output module and current drive signal output module.After the 0/3.3V switching value signal process photoelectric coupler isolation and the amplification of field effect transistor electric current of switching value output module with the output of DSP nucleus module, the level signal of output 0/24V, equipment such as drive point firearm, starter.The current drive signal output module is transformed into the voltage of DSP nucleus module output-current signal of 40mA ~ 40mA through voltage/current, drives equipment such as stator, spindle.
Embodiment, based on the rapid prototyping control of the Micro Turbine Jet Engine of bypass type adapter
As shown in Figure 7, the Micro Turbine Jet Engine control system is according to the rotating speed and exhaust temperature signal controlling engine starting motor, igniting, air valve, fuel tap and the oil pump that collect, wherein tach signal is a frequency quantity, it is switching value output that temperature adopts thermocouple temperature sensor, actuating motor, igniting, air valve and fuel tap signal, and the oil pump signal is analog quantity output.Adopt ordinary PC and bypass type adapter, just can make up the Micro Turbine Jet Engine control system fast, and on PC, carry out the research of control law.
Claims (1)
1. bypass type adapter, it is characterized in that: comprise DSP nucleus module, signal driver module and signal condition module, wherein the signal driver module comprises light isolation electric current amplification module and the voltage/current conversion module that input end is connected with DSP nucleus module output terminal respectively, and the signal condition module comprises resistance/voltage transformation module, level translation module, two photoelectricity isolation level conversion modules and two voltage amplification modules that output terminal is connected with DSP nucleus module input end respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011200460863U CN202058037U (en) | 2011-02-24 | 2011-02-24 | Bypass adapter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011200460863U CN202058037U (en) | 2011-02-24 | 2011-02-24 | Bypass adapter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202058037U true CN202058037U (en) | 2011-11-30 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011200460863U Expired - Fee Related CN202058037U (en) | 2011-02-24 | 2011-02-24 | Bypass adapter |
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| Country | Link |
|---|---|
| CN (1) | CN202058037U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103744394A (en) * | 2014-01-02 | 2014-04-23 | 哈尔滨工程大学 | Device and method for monitoring hydrofoil catamaran flap and tail wing servo system |
-
2011
- 2011-02-24 CN CN2011200460863U patent/CN202058037U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103744394A (en) * | 2014-01-02 | 2014-04-23 | 哈尔滨工程大学 | Device and method for monitoring hydrofoil catamaran flap and tail wing servo system |
| CN103744394B (en) * | 2014-01-02 | 2017-07-11 | 哈尔滨工程大学 | A kind of monitoring device and method of hydrofoil catamaran flap empennage servo-drive system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20111130 Termination date: 20130224 |