CN204575329U - A kind of miniature whirlpool spray aeromotor ground observing and controlling system - Google Patents
A kind of miniature whirlpool spray aeromotor ground observing and controlling system Download PDFInfo
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- CN204575329U CN204575329U CN201520240190.4U CN201520240190U CN204575329U CN 204575329 U CN204575329 U CN 204575329U CN 201520240190 U CN201520240190 U CN 201520240190U CN 204575329 U CN204575329 U CN 204575329U
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Abstract
The utility model discloses a kind of miniature whirlpool spray aeromotor ground observing and controlling system, described engine has an electric control unit, and engine afterbody is provided with a jet pipe, and this system comprises: industrial computer, and it is connected to electric control unit; Data acquisition unit, it comprises the wind-tunnel balance be arranged at below engine foundation and the first data collecting card gathering the balance signal that measurement wind-tunnel balance produces when engine rotation, also comprise two to control rocking bar and gather the second data collecting card measuring the two-way voltage output signal that described two control current present positions of rocking bar produce, the first data collecting card, the second data collecting card are connected with industrial computer communication; Performance element, it comprises two steering wheels and a servos control module, and described two steering wheels are connected to jet pipe, and described servos control model calling is to industrial computer.The utility model can meet the ground test of miniature whirlpool spray aeromotor comprehensively and rotating speed controls, jet pipe Angle ambiguity.
Description
Technical Field
The utility model discloses a simulation conditioning equipment among miniature turbojet engine ground observing and controlling system of aviation belongs to aviation ground observing and controlling field, especially relates to a miniature turbojet aero-engine ground observing and controlling system.
Background
In industrial production, various engines need to be subjected to qualification testing before being put on the market formally, and testing parameters are many, such as the rotating speed, the oil consumption and the like of the engines. However, most of the existing test systems are dispersed and independent, only a certain test instrument can be used alone to test a certain parameter, and the existing test systems are provided with a universal data acquisition and test module, so that the measurement accuracy of a specific engine is not high, the parameter often does not meet the industrial requirement, and the test of some special parameters cannot be met. For example, the research on the thrust of a micro turbojet aircraft engine applied to an aircraft has an important influence on actions of takeoff, cruising, landing and the like of the aircraft, but the measurement and control system applicable to the type of engine has few reports.
SUMMERY OF THE UTILITY MODEL
An object of the present invention is to solve at least the above problems and/or disadvantages and to provide at least the advantages which will be described later.
The utility model discloses it is still another purpose to provide a miniature turbojet aeroengine ground system of observing and controling, it can accomplish the control to engine speed, jet nozzle pitch angle and yaw angle's control, and the 8 component wind-tunnel strain balances of accessible measure the engine at different rotational speeds, and the jet nozzle pitch angle of difference and the three direction's of X, Y, Z aerodynamic force and moment that yaw angle received down, this has extremely important effect to the characteristic of studying this type of engine, still provide fine technical support for the use on the aircraft simultaneously.
In order to achieve these objects and other advantages in accordance with the present invention, the following technical solution is provided:
the utility model provides a miniature turbojet aeroengine ground system of observing and controling, the engine has an electrical control unit, and the engine afterbody is provided with a jet-tail pipe, wherein, this system includes:
an industrial personal computer connected to the electrical control unit;
the system comprises a data acquisition unit, a remote console and an industrial personal computer, wherein the data acquisition unit comprises a wind tunnel strain balance arranged below an engine base, a first data acquisition card for acquiring and measuring balance signals generated by the wind tunnel strain balance when an engine rotates, two control rockers arranged on the remote console, and a second data acquisition card for acquiring and measuring two paths of voltage output signals generated at the current positions of the two control rockers, and the first data acquisition card and the second data acquisition card are in communication connection with the industrial personal computer;
and the execution unit comprises two steering engines and a steering engine control module, the two steering engines are connected to the tail jet pipe and respectively control the pitching angle and the yawing angle of the tail jet pipe based on the steering engine control module, and the steering engine control module is connected to an industrial personal computer.
Preferably, the wind tunnel strain balance adopts an 8-channel 6-component static box type wind tunnel strain balance which is connected to the first data acquisition card through a twisted pair shielding cable.
Preferably, the first data acquisition card adopts an 8-channel synchronous strain signal acquisition module PXIe-4330.
Preferably, the ground measurement and control system of the micro turbojet aeroengine further comprises:
the signal conditioning box is arranged at the data receiving front end of the second data acquisition card; wherein
And two paths of voltage output signals output by the two control rockers are processed by the signal conditioning box and then are sent to a second data acquisition card for measurement.
Preferably, the data acquisition unit further includes:
the system comprises a fuel electronic scale for collecting the fuel quantity of an engine, an air pressure sensor for collecting the atmospheric pressure of the test environment where the engine is located, a temperature sensor for collecting the temperature of the test environment where the engine is located, a voltage sensor for collecting the power supply voltage of the engine and a current sensor for collecting the power supply current of the engine; wherein,
the fuel electronic scale, the air pressure sensor, the temperature sensor, the voltage sensor and the current sensor are electrically connected to the signal conditioning box and are output to the second data acquisition card by the signal conditioning box for measurement.
Preferably, the second data acquisition card adopts a 32-channel multifunctional data acquisition module PXI-6289.
Preferably, the first data acquisition card and the second data acquisition card are arranged in a PXIe chassis, a PXIe bridge module connected with the PXIe chassis through a PXIe bus is further arranged in the PXIe chassis, and the PXIe bridge module is connected to an industrial personal computer.
Preferably, the steering engine control module adopts a 6-channel PWM output module MI6606, and is connected to an industrial personal computer through a USB (universal serial bus) line.
Preferably, the ground measurement and control system of the micro turbojet aeroengine further comprises:
the system comprises four groups of camera devices distributed in an engine test environment and a hard disk video host computer in communication connection with the four groups of camera devices; wherein,
the hard disk video recording host computer with industrial computer, signal regulation case, PXIe machine case, steering wheel control module set up in a rack jointly, the rack is located a control room, set up in the control room the remote operation platform, this remote operation platform are three station operation panels to be provided with the LCD display screen on every station.
Preferably, the ground measurement and control system of the micro turbojet aeroengine further comprises:
the power supply unit is connected with commercial power to supply power for the four groups of camera devices and the hard disk video host, and provides power for the industrial personal computer, the signal conditioning box, the PXIe case and the LCD display screen through the UPS,
the power supply unit further comprises a program-controlled power supply connected to the UPS through an emergency stop button, the program-controlled power supply supplies power to the engine and the two steering engines and is arranged in the cabinet together with the UPS.
Measurement and control system includes following beneficial effect at least:
the ground measurement and control system of the miniature turbojet aero-engine can meet the ground test and rotating speed control targets of the miniature turbojet aero-engine and the angle control targets of the tail jet pipe, and particularly comprises the following steps:
the device can complete the measurement of the test environment temperature, the atmospheric pressure, the engine power supply parameters (power supply voltage and power supply current signals), the fuel weight and the like, complete the measurement of the 8-channel 6-component balance signal and complete the reading of the engine working state parameters;
the control of the rotating speed of the engine and the control targets of the pitching angle and the yawing angle of the tail nozzle can be finished;
the work of calculating and storing measurement parameters can be completed through an industrial personal computer and a built-in software system, important parameter monitoring and alarming are provided, and a test original data file, a test initial reading file, a monitoring data file and a test data report file of each test are recorded in a background;
the omnibearing video monitoring function on a test site can be completed; in addition, the built-in software system of the industrial personal computer also provides functions of user management, data playback, parameter setting, system calibration and the like.
Additional advantages, objects, and features of the invention will be set forth in part in the description which follows and in part will become apparent to those having ordinary skill in the art upon examination of the following or may be learned from practice of the invention.
Drawings
Fig. 1 is a block diagram of the overall working principle of the measurement and control system of the present invention;
FIG. 2 is a schematic diagram of an engine control according to one embodiment of the present invention;
FIG. 3 is a schematic diagram of the measurement and control system of the present invention for measuring balance signals generated during the rotation of the engine;
FIG. 4 is a schematic block diagram of the measurement and control system of the present invention for controlling the angle of the tail nozzle;
FIG. 5 is a schematic block diagram of data acquisition of the test environment of the engine by the measurement and control system of the present invention;
fig. 6 is a schematic diagram of a cabinet structure of the measurement and control system of the present invention;
fig. 7 is a schematic structural view of a three-station operating platform of the measurement and control system of the present invention;
fig. 8 is a power supply topology structure diagram of the measurement and control system of the present invention;
FIG. 9 is a flow chart of a manual test of the measurement and control system of the present invention;
FIG. 10 is a flow chart of the automatic test of the measurement and control system according to the present invention.
Detailed Description
The present invention is further described in detail below with reference to the drawings so that those skilled in the art can implement the invention with reference to the description.
It will be understood that terms such as "having," "including," and "comprising," as used herein, do not preclude the presence or addition of one or more other elements or groups thereof.
Referring to fig. 1-4, the utility model provides a miniature turbojet aeroengine ground system of observing and controling, the engine has an electrical control unit (ECU for short), and the engine afterbody is provided with a jet-tail pipe (not shown), and wherein this system includes:
the industrial personal computer is connected to an electric control unit of the engine through an RS232 serial port to control the rotating speed of the engine (namely, one control mode of the rotating speed of the engine is provided, namely, the upper computer is communicated with an ECU of the engine through the serial port and controls the rotating speed through software);
the data acquisition unit comprises a wind tunnel strain balance arranged below the engine base, a first data acquisition card for acquiring and measuring balance signals generated by the wind tunnel strain balance when the engine rotates, two control rockers (namely operating rods in the figure 1) arranged on a remote operation table and a second data acquisition card for acquiring and measuring two paths of voltage output signals generated by the current positions of the two control rockers, wherein the first data acquisition card and the second data acquisition card are in communication connection with an industrial personal computer;
the execution unit comprises two steering engines and a steering engine control module, the two steering engines are connected to the tail jet pipe and respectively control the pitching angle and the yawing angle of the tail jet pipe based on the steering engine control module, and the steering engine control module is connected to an industrial personal computer; the industrial personal computer controls the steering engine control module according to the two paths of signals output by the second data acquisition card, and performs aerodynamic force and torque measurement of the engine at the current rotating speed and when the tail nozzle is at the current pitch angle and yaw angle based on the received signals output by the first data acquisition card. Two paths of voltage signals output by the two control rockers and collected by the second data acquisition card are respectively used as control signals of the pitching angle and the yawing angle of the tail nozzle, and balance signals collected by the first data acquisition card are used as the basis for measuring the aerodynamic force and the moment applied to the engine.
The above technical scheme of the utility model, can test the air-powered power and the moment that miniature turbojet aeroengine received when different rotational speeds and tail nozzle are in different pitch angles or driftage angle, this provides fine technical support to the especially thrust research of application on the aircraft.
For the control of the engine:
referring specifically to fig. 2, a schematic diagram of engine control according to one embodiment of the present invention is shown, and from this diagram, two control modes for the engine are included: one is that the above mentioned scheme communicates with the electrical control unit ECU of the engine through the serial RS232 of the computer to control and read back the state, the other is that the engine is equipped with the remote controller to communicate with the wireless receiver in the electrical control unit of the engine to control and read back the state. The realized functions comprise the control of the engine speed and the read-back of relevant parameters of the engine. The parameters returned by the engine mainly comprise rotating speed, temperature, battery voltage, pumping pressure accelerator position and the like. In engine control, the engine and the ECU need to be powered up.
The utility model discloses on the test control to miniature turbojet aeroengine, combine software and hardware's generally, it is experimental to have three kinds of concrete test control modes:
the first is manually controlled by software: after the mode is selected, the engine can be controlled to perform manual test, initial reading and test data are manually collected, the engine control and the collected data are completely independent in the mode, and testers can independently start the engine or collect test related data;
the second is automatically controlled by software: the engine can be controlled to automatically test after the mode is selected, initial readings and test data are automatically collected, the mode only needs to start the engine and operates, then the 'starting test' in the software panel is clicked, all tests can be automatically completed according to test numbers (namely, the engine and the tail nozzle are controlled according to the test numbers, data are collected, displayed, data are stored and the like), and the engine needs to be started before the test is started in the mode, and the test can be started after the test is successful;
the third is manual control through external remote control, after the mode is selected, the rotating speed or the tail spray pipe angle of the engine can be controlled through an external engine control mode irrelevant to the system, manual test is carried out, initial reading and test data are manually collected, in the mode, the engine control and the collected data are completely independent, and testers can independently start the engine or collect test related data;
referring to fig. 9 and fig. 10, a manual test flowchart and an automatic test flowchart of the measurement and control system according to the present invention are respectively shown. It should be noted that, in the above three modes, before the manual test, the angle of the tail nozzle can be controlled by a software panel or a rocker, but the angle cannot be controlled by an external rocker in the manual test process; and in the external remote control or automatic test, the software panel control and the external rocker cannot be used for controlling the angle of the tail spray pipe.
The utility model discloses an in another embodiment, the data acquisition unit is still including setting up the throttle push rod on this remote operation platform, and the voltage signal of its output sends into second data acquisition card after signal conditioning case is taked care of the output and is gathered, then transmits to the industrial computer, and the industrial computer can be based on this signal to control the rotational speed of engine.
For the acquisition measurement of the balance signals:
in the scheme, the wind tunnel strain balance preferably adopts an 8-channel 6-component static box type wind tunnel strain balance which is connected to the first data acquisition card through a twisted pair shielding cable. The twisted pair shielding cable is adopted for transmission, so that other signals, power supply cables and the like are isolated from balance excitation and signals, and the interference of serial port pulse and engine power supply on weak balance signals (actually 8-channel voltage signals) is solved. Preferably, the first data acquisition card adopts an 8-channel synchronous strain signal acquisition module PXIe-4330. PXIe-4330 is an 8-channel 24-bit, band-calibrated, band-filtered, high-precision synchronous bridge acquisition card from NI corporation, as shown in FIG. 3, that provides integrated data acquisition and signal conditioning for bridge-based sensors. The module comprises higher precision, strong data processing capability and synchronization function, and is an ideal choice for a high-density measurement system. All 8-channel channels of the NI PXIe-4330 are equipped with 24-bit analog-to-digital converters, and the software selectable excitation voltage per channel is 0.625V to 10V.
To the balance signal of collection, the utility model discloses a full-bridge measurement method measures, and under the general condition, the balance power supply adopts 10VDC power supply according to every passageway of requirement, is encouraged the setting by software, PXIe-4330 produces. Because the balance signal is very weak, in order to ensure the measurement accuracy of the balance signal, a full differential measurement method is adopted in the system, and in addition, a twisted pair shielding cable is considered in wiring and is isolated from other power supply lines or signal lines. When the balance signal is measured, the system carries out load synthesis and calculation on the acquired analog signals output by the 8-channel balance, 7 iterative algorithms are adopted, and 6 components of the balance, including X, Y, Z-direction force and Mx, My and Mz-direction moments, are calculated respectively. I.e. drag, force and lift, yaw, roll and pitch moments.
Controlling the angle of the tail spray pipe of the engine:
in the above scheme, the ground measurement and control system of the micro turbojet aero-engine further comprises: the signal conditioning box is arranged at the data receiving front end of the second data acquisition card; two paths of voltage output signals output by the two control rockers are processed by the signal conditioning box and then sent to a second data acquisition card for measurement, as shown in fig. 1 or fig. 4. The signal conditioning box can condition the two collected voltage output signals, so that better precision can be obtained.
The utility model discloses in the above-mentioned scheme given the scheme of controlling the angle (including pitch angle and driftage angle) of engine exhaust nozzle, control two steering engines and then control exhaust nozzle driftage and pitch angle's mode promptly through two control rockers. Wherein, the rudder control module preferably adopts a 6-channel PWM output module MI6606 which is connected to the industrial personal computer through a USB line. Specifically, as shown in fig. 4, the two control rockers output yaw and pitch analog voltage signals respectively, the analog voltage signals are conditioned by the signal conditioning box and then sent to the second data acquisition card PXI-6289, after being acquired by the data acquisition card, the data and relevant parameters such as PWM pulse width set in system software are calculated to obtain the PWM pulse width corresponding to the control angle, and then the two paths of control PWM modules output to corresponding steering engines to enable the tail nozzle to act. The industrial personal computer controls the PWM module through the USB to generate PWM pulses with different periods and duty ratios, and then controls the steering engine so as to control the yaw and pitch angles of the tail nozzle. The two rocker arms output analog signals, and the analog signals are connected to a PXIe data acquisition card for measurement after passing through a signal conditioning box. The measured signal is calculated and processed by an industrial personal computer and is used as a basis for PWM control output.
The utility model discloses a guarantee the precision of control, need set up the PWM parameter in software system, and in order to guarantee the safety of steering wheel, need ensure that the value of input is correct when setting up the PWM parameter, angle range and pulse width realize soft spacing, otherwise the steering wheel is easy for a long time the lock-rotor, causes the damage.
Furthermore, besides controlling the angle of the tail jet pipe through a rocker, the PWM pulse width value can be manually input in system software for testing, and a schedule table of the angle points to be controlled corresponding to the pulse width value can be established during automatic testing, so that the tail jet pipe is sequentially controlled and stably tested.
And (3) testing the data of the test environment in which the engine is located:
the utility model discloses a satisfy the test environment data comprehensive test to miniature turbojet aeroengine when the operation, the data acquisition unit is preferred still includes: the system comprises a fuel electronic scale for collecting the fuel quantity of an engine, an air pressure sensor for collecting the atmospheric pressure of the test environment where the engine is located, a temperature sensor for collecting the temperature of the test environment where the engine is located, a voltage sensor for collecting the power supply voltage of the engine and a current sensor for collecting the power supply current of the engine; the fuel electronic scale, the air pressure sensor, the temperature sensor, the voltage sensor and the current sensor are electrically connected to the signal conditioning box and output to the second data acquisition card for measurement by the signal conditioning box. As shown in FIG. 5, the test environment data acquisition system of the present invention mainly comprises a sensor, a signal conditioning unit, a second data acquisition card, an industrial personal computer, a cable, etc. The sensor and the transmitter convert the measured physical quantity into a current, voltage or resistance signal. The signal conditioning box carries out necessary filtering, amplification or attenuation, current/voltage conversion, resistance/voltage conversion and the like on the signals, and outputs ideal voltage signals to the data acquisition card. The data acquisition card realizes the acquisition of the signals and uploads the signals to the industrial personal computer. The industrial personal computer displays, processes and stores the acquired data.
Here, the air pressure sensor, the temperature sensor and the like are used for measuring the test site and the environmental condition of the engine, and the starting condition and the real-time power consumption condition of the engine are inspected through the power supply voltage and current signals of the engine.
In the scheme, the MI2503 multi-channel mixed signal conditioning box is preferentially adopted by the signal conditioning box, conditioning and isolation can be provided for parameters (including temperature, air pressure, oil quantity, engine power supply voltage, engine power supply current, control rocker signals and the like) collected in the system, signals generated by different sensors and components are conditioned, and the system can work stably in a higher precision range more safely, stably and reliably. The two control rockers are respectively a front push rod, a rear push rod and a left push rod and a right push rod on the remote operation table and are controlled by a set of rocker controller.
The utility model discloses in the above-mentioned scheme, as shown in fig. 1, 4, 5, the second data acquisition card preferentially adopts 32 multi-functional data acquisition module PXI-6289 of passageway, and it is the multi-functional M series data acquisition integrated circuit board of NI company 3U, PXI high accuracy, 18 bits, 500kSPS, the multi-functional data acquisition of 32CH analog input, compatible PXI hybrid bus. To the utility model discloses the collection of well various parameters is very suitable.
Referring to fig. 1, in the measurement and control system, the first data acquisition card NI PXIe-4330 and the second data acquisition card NI PXI-6289 are disposed in a PXIe chassis, and a PXIe bridge module (NI PXIe-8361) connected to the PXIe chassis through a PXIe bus is further disposed in the PXIe chassis, and the PXIe bridge module is connected to an industrial personal computer. Here, the PXIe chassis is an NI PXIe-1078 combo chassis, which is configured with an alternating-current 9-slot 3U PXI Express chassis, 5 hybrid slots, and 3 PXI Express slots, and can meet the requirements of various test and measurement applications.
In the basis of the above scheme, the system also has a safety protection function and a monitoring function, and meets the monitoring of a test state and the processing of emergency, namely, the ground measurement and control system of the micro turbojet aeroengine further comprises:
the system comprises four groups of camera devices distributed in an engine test environment and a hard disk video host computer in communication connection with the four groups of camera devices; the hard disk video host, the industrial personal computer, the signal conditioning box, the PXIe case and the steering engine control module are arranged in a cabinet together (as shown in FIG. 6, a PXI data acquisition system in the drawing comprises the PXIe case and the PWM output module MI 6606), the cabinet is located in a control room, the remote operation table is arranged in the control room and is a three-station operation table, and an LCD display screen is arranged on each station (as shown in FIG. 7). As mentioned above, two control rockers are provided on the remote console, not shown here in fig. 7.
As shown in fig. 8, it provides the utility model discloses a measurement and control system's power supply topological structure chart, it includes:
the power supply unit is connected with commercial power to supply power for the four groups of camera devices and the hard disk video host, and provides power for the industrial personal computer, the signal conditioning box, the PXIe case and the LCD display screen through the UPS,
the power supply unit further comprises a program-controlled power supply connected to the UPS through an emergency stop button, the program-controlled power supply supplies power to the engine and the two steering engines, and the program-controlled power supply and the UPS are arranged in the cabinet together (see fig. 7). As can be seen from FIG. 8, the power system consists essentially of a 220VAC system with programmable power and a 5V/1A system output. The program-controlled power supply supplies power to the engine and the steering engine and performs program control through RS 232. The 5V/1A power supply is taken from a PXIe chassis and provides working power supply for the ECU.
When the system is powered on, four groups of cameras, the hard disk video recorder and the UPS are powered on, so that the field can be monitored before the test. In addition, after the UPS is powered on, the UPS power supply needs to be manually started to output 220VAC to each device.
The programmed power supply is NS3543 which supplies power to the engine and the jet nozzle control steering engine in the system, and because the power supply is particularly important, an emergency stop button is connected to the input end of the programmed power supply in series, and the power supply can be cut off in an emergency so as to determine the safety of the test object. In addition, the program-controlled power supply is connected to two steering engines at the same time in a laboratory to supply power to the steering engines.
In conclusion, the test system for the micro turbojet engine can be used for detecting six-component balance signals in the test process of the engine and data such as voltage, current, air pressure, temperature, oil quantity and the like of a test environment; four paths of video signals are provided to monitor the environment state of a test site, and an engine starting power supply and the like are provided; controlling the starting and stopping of the engine and controlling the rotating speed; and establishing a test database of various parameters of the engine, extracting test data and replaying the data.
The utility model discloses test system can extract experimental data, provides flight simulation data, with the rotational speed of various environmental parameter data and engine itself, and each weight of balance has reduced experimenter quantity with the data transfer of high accuracy to the industrial computer, greatly reduced work load, make the test more standardized, rapid, the direction of accuracy is further.
The following briefly introduces the design scheme of the measurement and control system in software:
the industrial computer adopts LabWindows/CVI 2012 to develop. And after the system is wired, powering on the system, starting system software and controlling a power supply to output the engine to work. Connecting and initializing a PXI acquisition module, setting system parameters, sending a sampling starting instruction through system software after the setting is finished, acquiring, storing and displaying data, performing read-back processing and data output after the acquisition is stopped, quitting the software after the test is finished, and completing the test for system power failure.
The measurement and control system mainly comprises parameter configuration, data acquisition and processing, data display, data recording, test data playback analysis and test channel calibration on the aspect of functional design of software, and the detailed analysis is as follows:
1. the parameter configuration function module: the method mainly completes the parameter configuration of each test channel, and the main configuration parameters comprise: the channel serial number of the test channel, the test parameter code number, the test parameter name, the signal property range and range, the correction coefficient, the alarm upper limit and the like.
2. The data acquisition and processing functional module: the software processes the acquired voltage signal into engineering value. The functional requirements mainly comprise the following aspects:
a) the acquired voltage signals need to be filtered digitally, and a point-by-point averaging method can be adopted for filtering;
b) according to the channel configuration information in the configuration file: calculating and processing the measuring range, the correction coefficient, the upper and lower alarm limits and the like to obtain an engineering value;
c) the engineering value should retain 4 significant digits;
d) if the engineering value exceeds the alarm limit, alarm display is carried out, and the alarm form is that the color of the cell is changed.
3. The data display function module: the collected data is displayed on an interface so as to be convenient for a tester to observe. The functional requirements mainly comprise the following aspects:
a) the measured values of the test data show two forms of numerical values and curves: the numerical display comprises all test data and can be displayed in a plurality of display partitions; and (4) performing curve display on only part of the test data in the curve display, wherein the curve display data is added or deleted by a tester. The measured value of the test data is displayed in a switching way according to two forms of a voltage value and an engineering quantity value, and the display form is selected by a tester;
b) the curve display of the measured value needs to have a separate display interface, and the curve can display the data change trend of the whole test process;
c) each actual display information includes a channel number, a data name, a measurement value and a unit;
d) each page of display interface should have an important data display area, data is added or deleted by a tester, and the quantity of the displayable data depends on the interface space and is not less than 10.
4. The data record storage function module: the method records and stores test data in a file form, and the functional requirements mainly comprise the following aspects:
a) all test data are recorded and stored;
b) the file name for recording the test data is edited by a tester, and the file name is automatically generated by software and contains the test starting recording time;
c) the tester can start and stop the test data recording at any time;
d) storing the test data by an engineering value, and reserving 4-bit effective numbers;
e) the file storage format is binary;
f) when the storage space of the hard disk of the file is insufficient, prompt in advance is needed to avoid test data loss.
5. The test data playback analysis function module: the data file recorded in the test is played back in a curve graph mode for analysis and processing by a tester. The requirements are as follows:
a) the tester displays and plays back the test data by selecting the data file name;
b) the data displayed on the same interface at the same time is not less than 10 paths, and the displayed data channel is selected by a tester and can be displayed and hidden;
c) the test data of the whole test process is displayed on the same interface, and a tester operates the functional button for enlarging or reducing the curve, and if the data volume is too large, the data can be displayed in a page mode;
d) different coordinate systems are needed for display data due to different engineering values of the test data;
e) reading the X value (time) and the Y value (measured value) of the data curve by operating a cursor and displaying;
f) and calculating the slope between any bright points of the curve and displaying.
6. Testing the functions of the channel calibration module: the method comprises the following steps of carrying out online calibration on each test channel, calculating a calibration correction coefficient by software, and calling a test, wherein the specific steps and requirements are as follows:
a) providing a calibration signal for each channel externally, requiring a tester to speak a standard value for inputting, and acquiring and recording an actual measurement system by using calibration software;
b) the number of the calibration points is not less than 5;
c) the software is fitted according to the standard value to obtain K, b correction coefficients, and K, b correction coefficients are stored in
And the parameter configuration file is used for the test program to call.
The system software is designed according to the user test requirements, the operator requirements and the similar products abroad, and provides a stable, reliable, powerful, intelligent and easy-to-use test tool in the Windows graphic environment for the operator. The system software is mainly characterized in that:
a) the operator can operate without knowing the computer program;
b) the operator does not need to input long and hard-to-remember commands;
c) all operations can be performed through the mouse and the keyboard at the same time;
d) real-time responsiveness;
e) simultaneously multitask operation;
f) the method has industrial development and can be integrated with third-party application software;
the upgrading is convenient, and the investment and resources of users are protected.
The number of apparatuses and the scale of the process described here are intended to simplify the description of the present invention. The utility model discloses a miniature turbojet aeroengine system of observing and controling application, modification and change to will be obvious to those skilled in the art.
Observe and control the state that the system can accomplish the control engine, gather the environmental parameter data of engine, gather each weight of engine balance, extract engine parameter data, establish experimental database etc.. In software, advanced high-precision and stable balance calibration and algorithm are adopted, each test channel can be independently calibrated on line, and the software obtains a calibration correction coefficient through calculation for test calling; in addition, the test system also has a preprocessing module for managing, replaying and storing the test database.
While embodiments of the invention have been disclosed above, it is not intended to be limited to the applications listed in the specification and the examples. It can be applicable to various and be fit for the utility model discloses a field completely. Additional modifications will readily occur to those skilled in the art. The invention is therefore not to be limited to the specific details and illustrations shown and described herein, without departing from the general concept defined by the claims and their equivalents.
Claims (10)
1. The utility model provides a miniature turbojet aeroengine ground system of observing and controling, the engine has an electrical control unit, and the engine afterbody is provided with a jet-tail pipe, its characterized in that, this system includes:
an industrial personal computer connected to the electrical control unit;
the system comprises a data acquisition unit, a remote console and an industrial personal computer, wherein the data acquisition unit comprises a wind tunnel strain balance arranged below an engine base, a first data acquisition card for acquiring and measuring balance signals generated by the wind tunnel strain balance when an engine rotates, two control rockers arranged on the remote console, and a second data acquisition card for acquiring and measuring two paths of voltage output signals generated at the current positions of the two control rockers, and the first data acquisition card and the second data acquisition card are in communication connection with the industrial personal computer;
and the execution unit comprises two steering engines and a steering engine control module, the two steering engines are connected to the tail jet pipe, and the steering engine control module is connected to an industrial personal computer.
2. The ground measurement and control system of the micro turbojet aero engine according to claim 1, wherein the wind tunnel strain balance is an 8-channel 6-component static box type wind tunnel strain balance, and the wind tunnel strain balance is connected to the first data acquisition card through a twisted pair shielding cable.
3. The ground measurement and control system of the micro turbojet aero-engine according to claim 2, wherein the first data acquisition card adopts an 8-channel synchronous strain signal acquisition module PXIe-4330.
4. The micro turbojet aero engine ground measurement and control system of claim 3 wherein the system further comprises:
the signal conditioning box is arranged at the data receiving front end of the second data acquisition card; wherein
And two paths of voltage output signals output by the two control rockers are processed by the signal conditioning box and then are sent to a second data acquisition card for measurement.
5. The micro turbojet aero engine ground measurement and control system of claim 4 wherein the data acquisition unit further comprises:
the system comprises a fuel electronic scale for collecting the fuel quantity of an engine, an air pressure sensor for collecting the atmospheric pressure of the test environment where the engine is located, a temperature sensor for collecting the temperature of the test environment where the engine is located, a voltage sensor for collecting the power supply voltage of the engine and a current sensor for collecting the power supply current of the engine; wherein,
the fuel electronic scale, the air pressure sensor, the temperature sensor, the voltage sensor and the current sensor are electrically connected to the signal conditioning box and are output to the second data acquisition card by the signal conditioning box for measurement.
6. The ground measurement and control system of the micro turbojet aero-engine according to claim 5, wherein the second data acquisition card adopts a 32-channel multifunctional data acquisition module PXI-6289.
7. The ground measurement and control system of the micro turbojet aero engine according to claim 6, wherein the first data acquisition card and the second data acquisition card are arranged in a PXIe case, a PXIe bridge module connected with the PXIe case through a PXIe bus is further arranged in the PXIe case, and the PXIe bridge module is connected to an industrial personal computer.
8. The ground measurement and control system of the micro turbojet aero-engine according to claim 7, wherein the rudder control module adopts a 6-channel PWM output module MI6606 which is connected to an industrial personal computer through a USB line.
9. The micro turbojet aero engine ground measurement and control system of claim 8 wherein the system further comprises:
the system comprises four groups of camera devices distributed in an engine test environment and a hard disk video host computer in communication connection with the four groups of camera devices; wherein,
the hard disk video recording host computer with industrial computer, signal regulation case, PXIe machine case, steering wheel control module set up in a rack jointly, the rack is located a control room, set up in the control room the remote operation platform, this remote operation platform are three station operation panels to be provided with the LCD display screen on every station.
10. The micro turbojet aero engine ground measurement and control system of claim 9 wherein the system further comprises:
the power supply unit is connected with commercial power to supply power for the four groups of camera devices and the hard disk video host, and provides power for the industrial personal computer, the signal conditioning box, the PXIe case and the LCD display screen through the UPS,
the power supply unit further comprises a program-controlled power supply connected to the UPS through an emergency stop button, the program-controlled power supply supplies power to the engine and the two steering engines and is arranged in the cabinet together with the UPS.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201520240190.4U CN204575329U (en) | 2015-04-20 | 2015-04-20 | A kind of miniature whirlpool spray aeromotor ground observing and controlling system |
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| CN201520240190.4U CN204575329U (en) | 2015-04-20 | 2015-04-20 | A kind of miniature whirlpool spray aeromotor ground observing and controlling system |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106314828A (en) * | 2016-08-26 | 2017-01-11 | 北京遥测技术研究所 | Dynamic reconfigurable ground measuring and controlling system |
| CN106769068A (en) * | 2016-12-15 | 2017-05-31 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft engine loads Servo simulation test method |
| CN113277118A (en) * | 2021-06-04 | 2021-08-20 | 西安交通大学 | Crawling robot for detecting blades of aero-engine |
-
2015
- 2015-04-20 CN CN201520240190.4U patent/CN204575329U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106314828A (en) * | 2016-08-26 | 2017-01-11 | 北京遥测技术研究所 | Dynamic reconfigurable ground measuring and controlling system |
| CN106769068A (en) * | 2016-12-15 | 2017-05-31 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft engine loads Servo simulation test method |
| CN113277118A (en) * | 2021-06-04 | 2021-08-20 | 西安交通大学 | Crawling robot for detecting blades of aero-engine |
| CN113277118B (en) * | 2021-06-04 | 2023-08-22 | 西安交通大学 | Crawling robot for detecting aero-engine blades |
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