CN104897297A - Embedded test device and control method for wireless temperature of aviation piston engine - Google Patents
Embedded test device and control method for wireless temperature of aviation piston engine Download PDFInfo
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- CN104897297A CN104897297A CN201510296246.2A CN201510296246A CN104897297A CN 104897297 A CN104897297 A CN 104897297A CN 201510296246 A CN201510296246 A CN 201510296246A CN 104897297 A CN104897297 A CN 104897297A
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Abstract
The invention discloses an embedded test device and control method for wireless temperatures of aviation piston engines. The embedded test device includes a temperature sensor node, a temperature data acquisition gathering node, a temperature data processing base station and a remote control center. The temperature sensor node is formed by a plurality of temperature measuring points on aviation piston engines. The temperature data acquisition gathering node is formed by a plurality of embedded control systems, and is positioned in a temperature measuring scene. The temperature measuring scene is equipped with a PC. The remote control center, positioned in a remote monitoring scene where users stay, includes a remote server. The embedded test device helps to overcome the disadvantages of a conventional temperature measuring device for aviation piston engines in terms of equipment mounting, data acquisition or the like, and effectively solves the technical problems that the conventional temperature measuring device for aviation piston engines has complicated connecting wires, is low in efficiency, low in data communication reliability and low in accuracy, is less adaptable to changes of on-the-wing operation tests or test places, etc.
Description
Technical field
The invention belongs to aviation field thermometry, be specifically related to a kind of embedded aviation piston engine wireless temperature proving installation and control method thereof.
Background technology
Aviation piston engine is as the conventional engine of general aviation aircraft, the heat nearly 30% of its fuel combustion release is converted into Effective power and goes to drive screw propeller to produce pulling force, the heat of 45% is lost in air with waste gas, separately has 25% cooled agent to take in air.During aviation piston engine work, temperature in cylinder after mixture combustion very high (maximum temperature can reach 2500 DEG C ~ 3000 DEG C), the parts contacted with high-temperature fuel gas or part, such as cylinder head, valve, sparking plug and piston obtain the heat of combustion gas, and temperature also rises quite high.If do not cooled engine, temperature cylinder will be too high, thus make engine that a series of abnormal phenomenon occur.Therefore, the temperature of aviation piston engine main parts size and situation of change characterize one of whether normal important parameter of aviation piston engine duty, also be the important parameter that pilot and maintenance personnel must grasp, detect aviation piston engine temperature tool accurately and efficiently and be of great significance.
According to the difference of heat eliminating medium, aviation piston engine cooling system can be divided into ventilation type and liquid-cooled two kinds, the present invention for be ventilation type aviation piston engine.Ventilation type aviation piston engine needs to carry out test run after finishing assembly, and the temperature test of its main parts size is one of important step of test run.In addition, when the type engine is arranged on after on general aviation aircraft, also need to carry out at wing testing results aboard, the temperature test of engine is indispensable important step equally.
Along with developing rapidly of General Aviation industry, the demand of aviation piston engine also increases gradually, connecting line existing for traditional aviation piston engine temperature-controlled process based on wire communication is complicated and efficiency is low, the reliability of, communication data low to the fitness changed at wing testing results or test site and accuracy is low etc. that problem is more and more outstanding, urgently improves.Concrete manifestation is as follows:
(1) aviation piston engine temperature test is all often be arranged on fixing engine pedestal by engine at present, engine bed is placed among the air channel of wind-tunnel, various temperature sensor is arranged on the different thermometric position of engine, relevant various test instrumentations are arranged on the control and monitor console of distance engine pedestal certain distance, each temperature sensor on engine is connected by cable with the various test instrumentations on control and monitor console, and connecting line is complicated and efficiency is low.In test process, on the one hand due in wind-tunnel compared with the impact of high wind speed, on the other hand due to vibrations when engine runs, the situation easily causing the connection cable between temperature sensor with test instrumentation to be connected built on the sand, easily loosen, affects the reliability of measurement data.
(2) when carry out on ground engine wing testing results or on fuselage install after test time, aircraft can not be moved on the one hand original automotive engine test bench place (original Spatial General 6 R cannot hold get off the plane), also can not originally fixing automotive engine test bench be moved to by aircraft on the other hand, therefore just need the aviation piston engine temperature testing device of Portable movable.Meanwhile, during due to engine operation, screw propeller rotates the safe distance causing test instrumentation needs distance aircraft certain, and according to wire communication mode, then line is apart from oversize, causes adverse effect by the accuracy of test data.
(3) due to the restriction of communication data connecting line and data acquisition and procession mode, is generally all configure one to one between current aviation piston engine temperature test control and monitor console and engine.That is: temperature test control and monitor console is to monitor an engine in real time, and can not carry out real-time synchronization monitoring to the operating engine of multiple stage, this is also the main cause causing testing efficiency low.
In above-mentioned aviation piston engine temperature test, Problems existing mainly causes due to the backwardness of traditional collecting method and data processing platform (DPP) and technology.At present along with the fast development of Embedded computer system technology and wireless communication technology, it can be applied to innovatively in aviation piston engine temperature test, while effectively solving Problems Existing, greatly improve the automatization level of all purpose aircraft manufacture and maintenance.
Summary of the invention
Goal of the invention: the object of the invention is to overcome the deficiency of existing aviation piston engine temperature testing device in equipment installation and data acquisition etc., design a kind of embedded aviation piston engine wireless temperature proving installation, effectively can to solve in existing aviation piston engine temperature test that existing connecting line is complicated and efficiency is low, the reliability of, communication data low to the fitness changed at wing testing results or test site and the technical matters such as accuracy is low.
Technical scheme: one of the present invention embedded aviation piston engine wireless temperature proving installation, comprises
Temperature sensor node, be made up of several points for measuring temperature be arranged on each aviation piston engine, the temperature data that each point for measuring temperature on every platform engine gathers, by ZigBee wireless sensor network, carries out Wireless data transmission through the ZigBee-network router corresponding to this engine to temperature data acquisition aggregation node;
Temperature data acquisition aggregation node, be made up of some embedded control systems, each embedded control system is for every platform aviation piston engine, wireless data communications is carried out by the point for measuring temperature in corresponding ZigBee network coordinator and ZigBee-network router and aviation piston engine, and aggregation process is carried out to each point for measuring temperature temperature of this gathered engine, data after aggregation process send to temperature data process base station by corresponding ethernet communication module, also receive the thermometric instruction from temperature data process base station by ethernet communication module simultaneously,
Temperature data process base station, be positioned at thermometric scene, thermometric scene is provided with PC, this PC, on the one hand by carrying out data communication between the embedded control system corresponding to Ethernet and each aviation piston engine, is intercomed with remote monitoring center by Internet internet on the other hand mutually;
Remote monitoring center, the remote monitoring being positioned at each user place is on-the-spot, comprise remote server, each user uses remote server by carrying out remote data communication between Internet internet and temperature data process base station, all temperature detection data surveying aviation piston engine can be grasped, and long-rangely can send relevant temperature detection instruction.
Further, the point for measuring temperature in described temperature sensor node comprises temperature data samwpling unit, temperature data processing unit, temperature data transmission unit and centrally connected power supply unit.
Further, described temperature data samwpling unit comprises temperature sensor and A/D converter, and temperature data processing unit comprises microprocessor and data-carrier store, and described temperature data transmission unit comprises wireless communication controller and serial port circuit.
Further, described temperature sensor adopts the thermally sensitive temperature sensor of PT100 or PT1000 series core body; Described microprocessor adopts 8 single-chip microcomputers; Described wireless communication controller adopts CC2530 radio communication transceiving chip.
Further, described embedded control system comprises microprocessor, and the peripheral components, wireless communication unit and the input-output apparatus that are connected with described microprocessor.
Further, described microprocessor adopts the 32-bit microprocessor S3C2440 based on ARM framework, has polytype data-interface such as general purpose I/O, ADC, SPI, PWM etc.
Further, described peripheral components comprises power supply, crystal oscillating circuit, reset circuit, jtag interface, FLASH program storage, SDRAM data-carrier store parts.
Further, described wireless communication unit is made up of embedded ZigBee SOC (system on a chip) CC2530 chip and external antenna module, and described CC2530 chip is connected with described microprocessor by SPI interface.
Further, described input-output apparatus comprises button, input through keyboard and sound and light alarm, LCD display.
The invention also discloses a kind of control method of embedded aviation piston engine wireless temperature proving installation:
Temperature sensor node detects data by Single-chip Controlling timing gradation collecting temperature, is compared by the temperature data that the temperature data newly gathered and last time collect, if the temperature gap of twice collection is lower than threshold value, then will not store, continue to gather; If the temperature gap of twice collection is higher than threshold value, then by new temperature acquisition data stored in storer, override the temperature acquisition data of last time.In order to save the energy of temperature sensor node, the wireless communication module of node is in dormant state at ordinary times, just only open when temperature acquisition data change or the requirement of temperature data acquisition aggregation node transmits temperature data;
Temperature data acquisition aggregation node is responsible for the flow process run according to data processing station, according to the actual needs of aviation piston engine temperature detection, wake up and start the temperature data acquisition aggregation node communication module corresponding to certain engine, and by the startup of temperature data acquisition aggregation node communication module to the data acquisition of temperature sensor node and transmission; The data of storage are issued temperature data acquisition aggregation node by temperature sensor node, then send the data to data processing station by temperature data acquisition aggregation node; Data processing station can be selected to carry out Acquire and process to all aviation piston engine temperature informations surveying, and also can carry out independent Acquire and process to the temperature information of wherein any aviation piston engine.
Beneficial effect: instant invention overcomes the deficiency of existing aviation piston engine temperature testing device in equipment installation and data acquisition etc., design a kind of embedded aviation piston engine wireless temperature proving installation, based on Embedded computer system system, by system architecture compositional model (the level Four node: " temperature sensor node ", " temperature data acquisition aggregation node ", " temperature data process base station ", " remote monitoring center " of " level Four node, three-layer network "; Three-layer network: " ZigBee wireless sensor network ", " Ethernet ", " Internet internet "), effectively can to solve in existing aviation piston engine temperature test that existing connecting line is complicated and efficiency is low, the reliability of, communication data low to the fitness changed at wing testing results or test site and the technical matters such as accuracy is low.
Accompanying drawing explanation
Fig. 1 is present system one-piece construction schematic diagram;
Fig. 2 is temperature sensor node point for measuring temperature hardware configuration schematic diagram of the present invention;
Fig. 3 is temperature data acquisition aggregation node embedded control system hardware configuration schematic diagram of the present invention;
Fig. 4 is temperature data collecting system testing process structural representation.
Embodiment
The embedded aviation piston engine wireless temperature of one as shown in Figure 1 proving installation, comprises
Temperature sensor node, be made up of several points for measuring temperature be arranged on each aviation piston engine, the temperature data that each point for measuring temperature on every platform engine gathers, by ZigBee wireless sensor network, carries out Wireless data transmission through the ZigBee-network router corresponding to this engine to temperature data acquisition aggregation node;
Temperature data acquisition aggregation node, be made up of some embedded control systems, each embedded control system is for every platform aviation piston engine, wireless data communications is carried out by the point for measuring temperature in corresponding ZigBee network coordinator and ZigBee-network router and aviation piston engine, and aggregation process is carried out to each point for measuring temperature temperature of this gathered engine, data after aggregation process send to temperature data process base station by corresponding ethernet communication module, also receive the thermometric instruction from temperature data process base station by ethernet communication module simultaneously,
Temperature data process base station, be positioned at thermometric scene, thermometric scene is provided with PC, this PC, on the one hand by carrying out data communication between the embedded control system corresponding to Ethernet and each aviation piston engine, is intercomed with remote monitoring center by Internet internet on the other hand mutually;
Remote monitoring center, the remote monitoring being positioned at each user place is on-the-spot, comprise remote server, each user uses remote server by carrying out remote data communication between Internet internet and temperature data process base station, all temperature detection data surveying aviation piston engine can be grasped, and long-rangely can send relevant temperature detection instruction.
As shown in Figure 2, temperature sensor node point for measuring temperature forms primarily of temperature data samwpling unit, temperature data processing unit, temperature data transmission unit and centrally connected power supply unit.
Temperature sensor node point for measuring temperature is arranged on each relevant temperature test position of aviation piston engine, because most of point for measuring temperature is arranged on engine interior, temperature is high, vibration is large, work under bad environment, so adopt unified centrally connected power supply unit (as battery power supply unit) to each unit centrally connected power supply of temperature sensor node point for measuring temperature.
Temperature data samwpling unit adopts the thermally sensitive temperature sensor of high-accuracy PT100 or PT1000 core body, and the simulating signal that temperature sensor exports is that digital signal sends temperature data processing unit to by A/D converter on-line conversion.
Temperature data processing unit is primarily of microprocessor and data-carrier store composition.Microprocessor adopts 8 single-chip microcomputers, is the core of temperature sensor node point for measuring temperature hardware design, and temperature data acquisition and process, communication data transmitting-receiving etc. all complete under the support of this unit.Will store after temperature data samwpling unit collecting temperature data, propose just data to be sent after data transfer request until temperature data acquisition aggregation node, the data volume of storage is comparatively large, so need external memorizer.
Temperature data transmission unit is primarily of wireless communication controller and serial port circuit composition.Wireless communication controller adopts the CC2530 radio communication transceiving chip of Chipcon company, and serial port circuit is used for connecting temperature data processing unit and temperature data transmission unit easily.
As shown in Figure 3, temperature data acquisition aggregation node embedded control system is primarily of part compositions such as microprocessor, peripheral components, wireless communication unit and input-output apparatus.
Microprocessor is the core control element of embedded control system, adopts the 32-bit microprocessor S3C2440 based on ARM framework, has polytype data-interface such as general purpose I/O, ADC, SPI, PWM etc.
Peripheral components comprises the parts such as power supply, crystal oscillating circuit, reset circuit, jtag interface, FLASH program storage, SDRAM data-carrier store, is responsible for support microcontroller S3C2440 and normally runs.
Wireless communication unit is made up of embedded ZigBee SOC (system on a chip) CC2530 chip and external antenna module.Be connected by SPI interface (synchronous serial Peripheral Interface) between microprocessor S3C2440 and CC2530, CC2530 is connected with external antenna module by the rf receiver and transmitter of its inside again, just mode regularly can carry out data communication by radio network router, telegon and cordless communication network.
Input-output apparatus comprises the part such as button, input through keyboard and sound and light alarm, LCD display.Button, input through keyboard can carry out the setting of mode of operation and parameter to temperature testing device control system.Sound and light alarm, LCD display is used for monitoring in real time temperature detection working condition and reporting to the police.
As shown in Figure 4, the mode transmitted according to aviation piston engine temperature detection data and path, temperature data acquisition software systems are primarily of part compositions such as temperature sensor node software, temperature data acquisition aggregation node software, data processing station softwares.
Temperature sensor node software detects data by Single-chip Controlling timing gradation collecting temperature, is compared by the temperature data that the temperature data newly gathered and last time collect, if the temperature gap of twice collection is lower than threshold value, then will not store, continue to gather; If the temperature gap of twice collection is higher than threshold value, then by new temperature acquisition data stored in storer, override the temperature acquisition data of last time.In order to save the energy of temperature sensor node, the wireless communication module of node is in dormant state at ordinary times, just only open when temperature acquisition data change or the requirement of temperature data acquisition aggregation node transmits temperature data.
The flow process according to data processing station running software is responsible for by temperature data acquisition aggregation node software, according to the actual needs of aviation piston engine temperature detection, wake up and start the temperature data acquisition aggregation node communication module corresponding to certain engine, and by the startup of temperature data acquisition aggregation node communication module to the data acquisition of temperature sensor node and transmission.The data of storage are issued temperature data acquisition aggregation node by temperature sensor node, then send the data to data processing station by temperature data acquisition aggregation node.Data processing station can be selected to carry out Acquire and process to all aviation piston engine temperature informations surveying, and also can carry out independent Acquire and process to the temperature information of wherein any aviation piston engine.
The above, it is only preferred embodiment of the present invention, not any pro forma restriction is done to the present invention, although the present invention discloses as above with preferred embodiment, but and be not used to limit the present invention, any those skilled in the art, do not departing within the scope of technical solution of the present invention, make a little change when the technology contents of above-mentioned announcement can be utilized or be modified to the Equivalent embodiments of equivalent variations, in every case be the content not departing from technical solution of the present invention, according to any simple modification that technical spirit of the present invention is done above embodiment, equivalent variations and modification, all still belong in the scope of technical solution of the present invention.
Claims (10)
1. an embedded aviation piston engine wireless temperature proving installation, is characterized in that: comprise
Temperature sensor node, be made up of several points for measuring temperature be arranged on each aviation piston engine, the temperature data that each point for measuring temperature on every platform engine gathers, by ZigBee wireless sensor network, carries out Wireless data transmission through the ZigBee-network router corresponding to this engine to temperature data acquisition aggregation node;
Temperature data acquisition aggregation node, be made up of some embedded control systems, each embedded control system is for every platform aviation piston engine, wireless data communications is carried out by the point for measuring temperature in corresponding ZigBee network coordinator and ZigBee-network router and aviation piston engine, and aggregation process is carried out to each point for measuring temperature temperature of this gathered engine, data after aggregation process send to temperature data process base station by corresponding ethernet communication module, also receive the thermometric instruction from temperature data process base station by ethernet communication module simultaneously,
Temperature data process base station, be positioned at thermometric scene, thermometric scene is provided with PC, this PC, on the one hand by carrying out data communication between the embedded control system corresponding to Ethernet and each aviation piston engine, is intercomed with remote monitoring center by Internet internet on the other hand mutually;
Remote monitoring center, the remote monitoring being positioned at each user place is on-the-spot, comprise remote server, each user uses remote server by carrying out remote data communication between Internet internet and temperature data process base station, all temperature detection data surveying aviation piston engine can be grasped, and long-rangely can send relevant temperature detection instruction.
2. one according to claim 1 embedded aviation piston engine wireless temperature proving installation, is characterized in that: the point for measuring temperature in described temperature sensor node comprises temperature data samwpling unit, temperature data processing unit, temperature data transmission unit and centrally connected power supply unit.
3. one according to claim 2 embedded aviation piston engine wireless temperature proving installation, it is characterized in that: described temperature data samwpling unit comprises temperature sensor and A/D converter, temperature data processing unit comprises microprocessor and data-carrier store, and described temperature data transmission unit comprises wireless communication controller and serial port circuit.
4. one according to claim 3 embedded aviation piston engine wireless temperature proving installation, is characterized in that: described temperature sensor adopts the thermally sensitive temperature sensor of PT100 or PT1000 series core body; Described microprocessor adopts 8 single-chip microcomputers; Described wireless communication controller adopts CC2530 radio communication transceiving chip.
5. one according to claim 1 embedded aviation piston engine wireless temperature proving installation, it is characterized in that: described embedded control system comprises microprocessor, and the peripheral components, wireless communication unit and the input-output apparatus that are connected with described microprocessor.
6. one according to claim 5 embedded aviation piston engine wireless temperature proving installation, it is characterized in that: described microprocessor adopts the 32-bit microprocessor S3C2440 based on ARM framework, has polytype data-interface such as general purpose I/O, ADC, SPI, PWM etc.
7. one according to claim 5 embedded aviation piston engine wireless temperature proving installation, is characterized in that: described peripheral components comprises power supply, crystal oscillating circuit, reset circuit, jtag interface, FLASH program storage, SDRAM data-carrier store parts.
8. one according to claim 5 embedded aviation piston engine wireless temperature proving installation, it is characterized in that: described wireless communication unit is made up of embedded ZigBee SOC (system on a chip) CC2530 chip and external antenna module, described CC2530 chip is connected with described microprocessor by SPI interface.
9. one according to claim 5 embedded aviation piston engine wireless temperature proving installation, is characterized in that: described input-output apparatus comprises button, input through keyboard and sound and light alarm, LCD display.
10. the control method of a kind of embedded aviation piston engine wireless temperature proving installation according to arbitrary one of claim 1-9, is characterized in that:
Temperature sensor node detects data by Single-chip Controlling timing gradation collecting temperature, is compared by the temperature data that the temperature data newly gathered and last time collect, if the temperature gap of twice collection is lower than threshold value, then will not store, continue to gather; If the temperature gap of twice collection is higher than threshold value, then by new temperature acquisition data stored in storer, override the temperature acquisition data of last time, in order to save the energy of temperature sensor node, the wireless communication module of node is in dormant state at ordinary times, only just opens when temperature acquisition data change or the requirement of temperature data acquisition aggregation node transmits temperature data;
Temperature data acquisition aggregation node is responsible for the flow process run according to data processing station, according to the actual needs of aviation piston engine temperature detection, wake up and start the temperature data acquisition aggregation node communication module corresponding to certain engine, and by the startup of temperature data acquisition aggregation node communication module to the data acquisition of temperature sensor node and transmission; The data of storage are issued temperature data acquisition aggregation node by temperature sensor node, then send the data to data processing station by temperature data acquisition aggregation node; Data processing station can be selected to carry out Acquire and process to all aviation piston engine temperature informations surveying, and also can carry out independent Acquire and process to the temperature information of wherein any aviation piston engine.
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| CN108266715A (en) * | 2018-02-13 | 2018-07-10 | 华电电力科学研究院有限公司 | A kind of discharge smoke temperature of power station boiler intelligent test system |
| CN110362933A (en) * | 2019-07-17 | 2019-10-22 | 哈尔滨工业大学 | Aircraft auxiliary power plant life-span prediction method based on transfer learning |
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