CN110887670B - Aircraft engine propeller test system - Google Patents
Aircraft engine propeller test systemDownload PDFInfo
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- CN110887670B CN110887670BCN201911165188.4ACN201911165188ACN110887670BCN 110887670 BCN110887670 BCN 110887670BCN 201911165188 ACN201911165188 ACN 201911165188ACN 110887670 BCN110887670 BCN 110887670B
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- 238000004891communicationMethods0.000claimsdescription11
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- 238000012806monitoring deviceMethods0.000claimsdescription9
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- 238000001514detection methodMethods0.000abstract1
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- 239000000295fuel oilSubstances0.000description2
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- 230000005540biological transmissionEffects0.000description1
- 229910002091carbon monoxideInorganic materials0.000description1
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- 238000011835investigationMethods0.000description1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Combined Controls Of Internal Combustion Engines (AREA)
Abstract
Translated fromChinese
Description
Technical Field
The invention belongs to the technical field of aero-engines, and particularly relates to an aero-engine propeller test system.
Background
At present, a common engine for a medium-large type investigation or scouting integrated unmanned aerial vehicle is a turboprop aero-engine. Before an engine is formally assembled to an unmanned aerial vehicle, a ground test run for hundreds of hours is required to verify the mutual matching condition of a fuel system, a control system and an acquisition system of the unmanned aerial vehicle so as to obtain accurate accelerator-rotating speed and accelerator-thrust torque curves. The current engine propeller test is facing the following problems:
1. the danger coefficient of the test site is high, and the method is mainly embodied in two aspects:
due to signal transmission and engine starting control, an operator often needs to be close to a test site, and a propeller rotating at a high speed is extremely easy to damage a human body, so that the life cost is seriously needed;
during the engine test run, can get rid of waste gas through the blast pipe, wherein contain harmful gas such as sulfur monoxide, sulfur dioxide, carbon monoxide, stay for a long time near the test bench, lead to harmful gas poisoning easily, harm personal safety.
2. It is difficult to achieve high quality signal acquisition. Along with the rotation speed of the engine from low to high, the vibration frequency of the system covers the vibration interference from low frequency to high frequency, and the high-quality signal acquisition and transmission requirements are high.
Disclosure of Invention
In view of this, the embodiment of the invention provides an aircraft engine propeller test system, which at least solves the problems of personal safety of testers and low accuracy and reliability of test results in the prior art.
The embodiment of the invention provides an aircraft engine propeller test system, which comprises:
the acquisition equipment: the remote control test bed is used for acquiring state signals of the engine and receiving control data of the remote control test bed to realize control of system signals of the engine;
a fuel system: the remote control test bed is used for supplying oil to the engine and transmitting the acquired fuel weight data to the remote control test bed;
the remote control test bed comprises: the device is used for receiving the state signals of the engine collected by the collecting device and controlling the collecting device.
Optionally, the system further comprises:
a supporting platform and a monitoring device, wherein the collecting device is arranged on the supporting platform,
the supporting platform comprises a supporting rack and a heat dissipation loop, wherein the supporting rack is used for supporting the engine and the propeller body, and the heat dissipation loop is used for dissipating heat of the engine;
and the monitoring equipment is used for monitoring the test state and transmitting the monitoring signal to the remote control test bed.
Optionally, the heat dissipation loop includes a lubricating oil cooling unit and a cooling liquid cooling unit.
Optionally, the fuel oil system includes fuel tank, fuel feeding return circuit and weighing equipment, the fuel feeding return circuit includes oil pipe and oil return pipe, weighing equipment is used for weighing to the fuel tank to obtain fuel weight data, oil pipe and oil return pipe are connected with the oil-out and the oil return opening of fuel tank respectively.
Optionally, the oil tank is of a box-type structure, an oil outlet is formed in the bottom of the oil tank, and an oil return port is formed in the top of the oil tank;
an oil pump is installed in the oil supply loop, and the start and stop of the oil pump are controlled based on fuel oil weight data obtained by the weighing equipment.
Optionally, the remote control test bed includes: the device comprises an acquisition module, a vibration analysis module, a monitoring module and a control module;
the acquisition module is electrically connected with the acquisition equipment and used for receiving the signals acquired by the acquisition equipment and sending control instructions to the acquisition equipment;
the monitoring module is electrically connected with the monitoring equipment and used for receiving a monitoring signal of the monitoring equipment and sending a control instruction to the monitoring module;
the control module controls the key switching value through a soft switch and a hard switch;
and the vibration analysis module receives the signal of the acquisition module and is used for analyzing the vibration condition of the engine in a test state.
Optionally, the acquisition module controls the acquisition device to acquire at least one of temperature, frequency, vibration, and pressure of the object to be measured.
Optionally, the control module remotely controls the soft switch and the hard switch,
the soft switch controls the software switch by clicking the form of sending serial port instructions through the interface, and the hard switch controls the switching value of a test field by the switching state of a physical switch on the remote control test bed.
Optionally, the collecting device includes: a sensor unit, an electronic control unit and a communication unit,
the sensor unit is used for acquiring at least one of voltage, resistance, current, frequency and pressure of the engine;
the electronic control unit realizes digital quantity signal control on starting and stopping of an engine, emergency stop, starting and stopping of a cooling fan or a power supply switch of a fuel system by outputting TTL level, and realizes analog quantity signal control on an actuating mechanism by outputting 0-10V voltage;
the communication unit is communicated with the remote control test bed and receives fuel weight data of the fuel system.
Optionally, the soft switch includes: the loop A can not start a safety loop soft switch, the loop B can not start a safety loop soft switch, a main oil pump start-stop soft switch and an auxiliary oil pump start-stop soft switch;
the hard switch, comprising: the circuit A can not start a safety circuit hard switch, the circuit B can not start a safety circuit hard switch, a main oil pump start-stop hard switch, an auxiliary oil pump start-stop hard switch, an emergency stop switch, an engine start-stop enabling hard switch and an engine start-stop hard switch;
when the four switches of the circuit A non-startable safety circuit soft switch, the circuit A non-startable safety circuit hard switch, the circuit B non-startable safety circuit soft switch and the circuit B non-startable safety circuit hard switch are simultaneously disconnected, the engine disconnects the non-startable safety circuit, and the engine has a starting condition;
when any one of the four switches of the circuit A non-startable safety circuit soft switch, the circuit A non-startable safety circuit hard switch, the circuit B non-startable safety circuit soft switch and the circuit B non-startable safety circuit hard switch is closed, the connection of the engine non-startable safety circuit is closed, and the engine does not have the starting condition;
when the main oil pump start-stop soft switch and the main oil pump start-stop hard switch are closed simultaneously, the power supply of the main oil pump of the fuel system is switched on, and the start control of the main oil pump is realized;
when the auxiliary oil pump start-stop soft switch and the auxiliary oil pump start-stop hard switch are closed simultaneously, the power supply of the auxiliary oil pump of the fuel system is switched on, and the start control of the auxiliary oil pump is realized;
when any one of the two ways of the main oil pump start-stop soft switch and the main oil pump start-stop hard switch is disconnected, the power supply of the main oil pump of the fuel system is disconnected, and the main oil pump stops working;
when any one of the two ways of the auxiliary oil pump start-stop soft switch and the auxiliary oil pump start-stop hard switch is disconnected, the power supply of the auxiliary oil pump of the fuel system is disconnected, and the auxiliary oil pump stops working;
when the emergency stop switch is closed, the connection of the safety circuit which can not be started by the engine is closed, and simultaneously the main oil pump and the auxiliary oil pump are immediately powered off to stop working;
the engine start-stop enabling hard switch and the engine start-stop hard switch are used for controlling the output of an engine starting power supply, the engine start-stop enabling hard switch and the engine start-stop hard switch are used in series, and when the engine start-stop enabling hard switch and the engine start-stop hard switch are both closed, a starting signal is sent and output to the engine.
The invention collects the state signal of the engine by arranging the collecting device and transmits the collected signal to the remote control test bed, and the remote control test bed realizes the control of the switching value signal or the analog value signal of the engine system by the collecting device; and simultaneously transmitting the acquired fuel weight data of the fuel system to a remote control test bed. Thereby avoiding the operator to be close to the test site in the test process. The acquisition equipment improves the accuracy of data acquisition, ensures the personal safety of testers, does not need to be close to danger zones during the test, has more accurate and reliable test results, and indirectly ensures the flight safety. Thereby achieving the purpose of ensuring the personal safety of the testing personnel and simultaneously ensuring the accuracy and reliability of the testing result.
Additional features and advantages of the invention will be set forth in the detailed description which follows.
Drawings
The above and other objects, features and advantages of the present invention will become more apparent by describing in more detail exemplary embodiments thereof with reference to the attached drawings, in which like reference numerals generally represent like parts throughout.
FIG. 1 illustrates a block diagram of an aircraft engine propeller testing system in accordance with an embodiment of the present invention;
FIG. 2a shows an electrical schematic of the control of the main oil pump of one embodiment of the present invention;
FIG. 2b shows an electrical schematic of the control of the auxiliary oil pump of one embodiment of the present invention;
FIG. 2c shows a control electrical schematic of loop A of one embodiment of the present invention;
FIG. 2d shows a control electrical schematic of loop B of one embodiment of the present invention;
fig. 2e shows the control electrical schematic of the activation signal of one embodiment of the present invention.
Description of reference numerals:
1. a supporting platform, 2, a remote control test bed, 3, a fuel system, 4 and a monitoring device,
101. a support rack 102, an acquisition device 103, a heat dissipation loop,
1011. a support tool 1012, a moving frame,
1021. a sensor unit 1022, an electronic control unit 1023, a communication unit,
1031. a lubricatingoil cooling unit 1032, a cooling liquid cooling unit,
201. a monitoring module, 202, a vibration analysis module,
203. an acquisition module, 204, a control module,
2041. a soft switch, 2042, a hard switch,
301. an oil tank 302, an oil supply loop 303, a weighing device,
2041-1, a main oil pump start-stop soft switch, 2042-1, a main oil pump start-stop hard switch,
2041-2, an auxiliary oil pump start-stop soft switch, 2042-2, an auxiliary oil pump start-stop hard switch,
3021. a main oil pump, 3022, an auxiliary oil pump,
2041-3, circuit A can not start the soft switch of the safety circuit,
2042-3, circuit A can not start the hard switch of the safety circuit,
2041-4, the circuit B can not start the soft switch of the safety circuit,
2042-4, circuit B can not start the hard switch of the safety circuit,
2042-5, an engine start-stop enable hard switch 2042-6, an engine start-stop hard switch,
2042-7 and an emergency stop switch.
The scram switch in fig. 2a to 2d is a switch, but a plurality of circuits are connected.
Detailed Description
Preferred embodiments of the present invention will be described in more detail below. While the following describes preferred embodiments of the present invention, it should be understood that the present invention may be embodied in various forms and should not be limited by the embodiments set forth herein.
As shown in fig. 1, an aircraft engine propeller testing system includes:
the acquisition device 102: the remote control test bed is used for acquiring state signals of the engine and receiving control data of the remote control test bed to realize control of system signals of the engine;
and a fuel system 3: the remote control test bed is used for supplying oil to the engine and transmitting the acquired fuel weight data to the remote control test bed 2;
the remote control test bed 2: for receiving the engine status signals collected by the collection device 102 and controlling the collection device 102.
Optionally, the system further comprises a controller,
a supporting platform 1 and a monitoring device 4, wherein the acquisition device 102 is arranged on the supporting platform 1,
the supporting platform 1 comprises a supporting rack 101, a collecting device 102 and a heat dissipation loop 103, wherein the supporting rack 101 is used for supporting the engine and the propeller body, and the heat dissipation loop 103 is used for dissipating heat of the engine;
and the monitoring equipment 4 is used for monitoring the test state and transmitting the monitoring signal to the remote control test bed 2.
Optionally, the heat dissipation loop 103 includes a lubricating oil cooling unit 1031 and a coolingliquid cooling unit 1032.
Optionally, the fuel system 3 includes a fuel tank 301, a fuel supply loop 302 and a weighing device 303, the fuel supply loop 302 includes a fuel outlet pipe and a fuel return pipe, the weighing device 303 is used for weighing the fuel tank 301 so as to obtain fuel weight data, and the fuel outlet pipe and the fuel return pipe are respectively connected with a fuel outlet and a fuel return opening of the fuel tank 301.
Optionally, the oil tank 301 adopts a box-type structure, an oil outlet is formed at the bottom of the oil tank 301, and an oil return port is formed at the top of the oil tank 301;
an oil pump is installed in the oil supply loop 302, and the start and stop of the oil pump are controlled based on the fuel weight data acquired by the weighing device 303.
Optionally, the remote control test bed 2 includes: the system comprises an acquisition module 203, a vibration analysis module 202, a monitoring module 201 and a control module 204;
the acquisition module 203 is electrically connected to the acquisition device 102, and is configured to receive a signal acquired by the acquisition device 102 and send a control instruction to the acquisition device 102;
the monitoring module 201 is electrically connected with the monitoring device 4, and is configured to receive a monitoring signal of the monitoring device 4 and send a control instruction to the monitoring module 201;
the control module 204 controls the key switching value through thesoft switch 2041 and thehard switch 2042;
the vibration analysis module 202 receives the data of the acquisition module 203 and is used for analyzing the vibration condition of the engine under the test state.
Optionally, the acquisition module 203 controls the acquisition device 102 to acquire at least one of temperature, frequency, vibration, and pressure of the measured object.
Optionally, the control module 204 remotely controls thesoft switch 2041 and thehard switch 2042,
thesoft switch 2041 controls the software switch through the form of interface clicking to send serial port instructions, and thehard switch 2042 controls the switching value of a test site through the switching state of a physical switch on the remote control test bed 2.
Optionally, the acquisition device 102 includes: a sensor unit 1021, an electronic control unit 1022 and a communication unit 1023,
the sensor unit 1021 is used for collecting at least one of voltage, resistance, current, frequency and pressure of the engine;
the electronic control unit 1022 realizes digital quantity signal control on starting and stopping of an engine, emergency stop, starting and stopping of a cooling fan or a power supply switch of the fuel system 3 by outputting TTL level, and realizes analog quantity signal control on an actuating mechanism by outputting 0-10V voltage;
and the communication unit 1023 is communicated with the remote control test bed 2 and receives fuel weight data of the fuel system 3.
The support platform 1 is composed of a support bench 101, an acquisition device 102 and a heat dissipation loop 103. The support bench 101 consists of a support tool 1011 and a moving frame 1012; the supporting tool 1011 is used for supporting the engine and the propeller body, the moving frame 1012 is of a four-wheel vehicle type structure, and the supporting tool 1011 is welded on the moving frame 1012, so that the transition of the test bed can be conveniently realized. The acquisition equipment 102 is the center of signal cross-linking of the near-end acquisition end and consists of a sensor unit 1021, an electronic control unit 1022 and a communication unit 1023; the sensor unit 1021 is connected with the engine sensor through a wire or wireless communication, so that the acquisition of signals such as voltage, resistance, current, frequency, pressure and the like is realized; the electronic control unit 1022 realizes digital quantity signal control on starting and stopping of an engine, emergency stop, starting and stopping of a cooling fan and a power supply switch of the fuel system 3 by outputting TTL level, and realizes analog quantity control on actuating mechanisms such as a choke valve and an accelerator by outputting 0-10V voltage; the communication unit 1023 communicates with the remote control test bed 2 through a serial bus, and meanwhile, the communication unit 1023 receives fuel weight data of the fuel system 3.
The monitoring module 201 of the remote control test bed 2 is responsible for receiving and displaying the video data of the monitoring equipment 4; the acquisition module 203 is connected with the acquisition equipment 102 of the support platform 1 through a cable, and realizes control of the acquisition equipment 102 and acquisition of signals of temperature, frequency, vibration, pressure and the like of a measured object by using a serial port bus; the vibration analysis module 202 is used for analyzing the vibration data received by the acquisition module 203; the control module 204 is provided with asoft switch 2041 and ahard switch 2042 which are remotely controlled, wherein thesoft switch 2041 realizes the control of a software switch by clicking and selecting a serial port instruction form through an interface, and thehard switch 2042 controls the switching value of a test field through the on-off state of a physical switch on the remote control test bed 2;
the fuel system 3 consists of an oil tank 301, an oil supply loop 302 and a weighing device 303, and is connected with the supporting platform 1 through a cable to realize power supply input and signal transmission; the oil tank 301 adopts a box-type structure, the bottom of the oil tank is an oil outlet, and the top of the oil tank is an oil return port; an oil pump is installed in the oil supply loop 302, and the start and stop control of the oil pump is realized by receiving a digital quantity signal of the acquisition equipment 102 supporting the weighing platform; the weighing device 303 is arranged at the bottom of the oil tank 301 and used for measuring the weight of the fuel in real time and transmitting the weight to the acquisition device 102 of the support platform 1 through a 485 bus.
The monitoring equipment 4 is connected with the remote control test bed 2 by a network cable, so that the remote monitoring of the field test state is realized.
The remote control test bed 2 sends an inquiry instruction to the fuel system 3 every 1 second to obtain the fuel consumption, and the real-time fuel consumption can be calculated according to the ratio of the fuel quantity difference value and the time interval of two adjacent inquiries.
Optionally, as shown in fig. 2a to 2e, the remote control test bed 2 employs a switch control strategy with high reliability and safety. Thesoft switch 2041 includes: a loop A non-startable safety loop soft switch 2041-3, a loop B non-startable safety loop soft switch 2041-4, a main oil pump starting soft switch 2041-1 and an auxiliary oil pump starting and stopping soft switch 2041-2;
thehard switch 2042 includes: a circuit A non-startable safety circuit hard switch 2042-3, a circuit B non-startable safety circuit hard switch 2042-4, a main oil pump start-stop hard switch 2042-1, an auxiliary oil pump start-stop hard switch 2042-2, an emergency stop switch 2042-7, an engine start-stop enable hard switch 2042-5 and an engine start-stop hard switch 2042-6;
when the four switches of the circuit A non-startable safety circuit soft switch 2041-3, the circuit A non-startable safety circuit hard switch 2042-3, the circuit B non-startable safety circuit soft switch 2041-4 and the circuit B non-startable safety circuit hard switch 2042-4 are simultaneously disconnected, the engine disconnects the non-startable safety circuit, and the engine has a starting condition;
when any of the four switches of the circuit A non-startable safety circuit soft switch 2041-3, the circuit A non-startable safety circuit hard switch 2042-3, the circuit B non-startable safety circuit soft switch 2041-4 and the circuit B non-startable safety circuit hard switch 2042-4 is closed, the connection of the engine non-startable safety circuit is closed, and the engine does not have the starting condition;
circuit a and circuit B are safety circuits that control engine start. The start signal is a signal that controls the start of the engine.
When the main oil pump start-stop soft switch 2041-1 and the main oil pump start-stop hard switch 2042-1 are closed simultaneously, the power supply of the main oil pump of the fuel system is switched on, and the start control of the main oil pump 3021 is realized;
when the auxiliary oil pump start-stop soft switch 2041-2 and the auxiliary oil pump start-stop hard switch 2042-2 are closed simultaneously, the power supply of an auxiliary oil pump of the fuel system is switched on, and the start control of the auxiliary oil pump 3022 is realized;
when any one of the two ways of the main oil pump start-stop soft switch 2041-1 and the main oil pump start-stop hard switch 2042-1 is disconnected, the power supply of the main oil pump of the fuel system is disconnected, and the main oil pump 3021 stops working;
when any one of the two-way switch of the auxiliary oil pump start-stop soft switch 2041-2 and the auxiliary oil pump start-stop hard switch 2042-2 is disconnected, the power supply of the auxiliary oil pump of the fuel system is disconnected, and the auxiliary oil pump 3022 stops working;
when the emergency stop switch is closed, the connection of the safety circuit which can not be started by the engine is closed, and simultaneously the main oil pump and the auxiliary oil pump are immediately powered off to stop working;
the engine start/stop enabling hard switch 2042-5 and the engine start/stop hard switch 2042-6 are used for controlling the output of an engine starting power supply, the engine start/stop enabling hard switch 2042-5 and the engine start/stop hard switch 2042-6 are used in series, and when the engine start/stop enabling hard switch 2042-5 and the engine start/stop hard switch 2042-6 are both closed, a starting signal is sent to the engine to be output.
Having described embodiments of the present invention, the foregoing description is intended to be exemplary, not exhaustive, and not limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments.
Claims (6)
Translated fromChinesePriority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201911165188.4ACN110887670B (en) | 2019-11-25 | 2019-11-25 | Aircraft engine propeller test system |
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| CN201911165188.4ACN110887670B (en) | 2019-11-25 | 2019-11-25 | Aircraft engine propeller test system |
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| CN110887670Btrue CN110887670B (en) | 2022-02-22 |
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