CN114323653A - Unmanned helicopter engine parameter acquisition system - Google Patents
Unmanned helicopter engine parameter acquisition system Download PDFInfo
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- CN114323653A CN114323653A CN202111523738.2A CN202111523738A CN114323653A CN 114323653 A CN114323653 A CN 114323653A CN 202111523738 A CN202111523738 A CN 202111523738A CN 114323653 A CN114323653 A CN 114323653A
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Abstract
The invention provides a parameter acquisition system of an unmanned helicopter engine, which comprises a power supply module, a data input module, a data processing module, a data output module, a data transmission module, a data storage module, a shell and a connector, wherein the power supply module is connected with the data input module; the power supply module comprises DC28V-DC12V, DC12V-DC5V and DC 5V-DC3.3V; the data acquisition module comprises a rotating speed signal acquisition submodule, a liquid level signal acquisition submodule, a temperature signal acquisition submodule, a pressure signal acquisition submodule and a discrete magnitude signal acquisition submodule; the data processing module mainly refers to an STM32 singlechip; the data output module mainly comprises a first oil pump state signal, a second oil pump state signal, a first electronic fan state signal, a second electronic fan state signal, a clutch control signal and an engine starting signal. The unmanned helicopter engine parameter acquisition system can monitor the state of an engine tool in real time, control the engine in real time and transmit acquired engine information to an avionic system in time.
Description
Technical Field
The invention relates to the technical field of unmanned helicopter engine parameter acquisition, in particular to an unmanned helicopter engine parameter acquisition system.
Background
As one of the key components of the unmanned helicopter, the engine provides power for the main rotor wing, the tail rotor wing and the system accessories of the unmanned helicopter, and the working state of the unmanned helicopter needs to be known and controlled timely and accurately in the flight process. With the development of aircraft engine technology, the number of parameters to be monitored and controlled of the engine is increasing. The existing unmanned helicopter engine parameters are difficult to acquire and monitor the state in real time, so that the engine cannot be controlled in real time, and part of acquired engine information is difficult to transmit to an avionic system in time, so that the operation of the existing engine parameter acquisition system is not perfect.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a parameter acquisition system of an unmanned helicopter engine, which aims to solve the problems in the background art.
In order to achieve the purpose, the invention is realized by the following technical scheme: the utility model provides an unmanned helicopter engine parameter acquisition system, includes the acquisition system body, its characterized in that: the acquisition system body comprises a power supply module, a data input module, a data processing module, a data output module, a data transmission module, a data storage module, a shell and a connector.
As a preferred embodiment of the invention, the power supply module comprises DC28V-DC12V, DC12V-DC5V and DC 5V-DC3.3V.
As a preferred embodiment of the present invention, the data acquisition module includes a rotation speed signal acquisition submodule, a liquid level signal acquisition submodule, a temperature signal acquisition submodule, a pressure signal acquisition submodule, and a discrete magnitude signal acquisition submodule.
As a preferred implementation mode of the invention, the data processing module mainly refers to an STM32 single chip microcomputer.
As a preferred embodiment of the present invention, the data output module mainly includes a first oil pump status signal, a second oil pump status signal, a first electronic fan status signal, a second electronic fan status signal, a clutch control signal, and an engine start signal.
As a preferred embodiment of the invention, the data transmission module is mainly used for the communication between the engine parameter collector and the avionics system of the unmanned helicopter and is realized by adopting a CAN bus.
As a preferred embodiment of the present invention, the data storage module mainly refers to a Flash chip.
In a preferred embodiment of the present invention, the housing is designed to dissipate heat, the heat dissipation area is increased by providing the heat dissipation fins, and the housing is subjected to a waterproof treatment using the sealing ring.
As a preferred embodiment of the invention, the connector is a J599 system connector.
As a preferred embodiment of the present invention, the signals collected by the rotation speed signal collection submodule include an engine rotation speed signal and a rotor rotation speed signal, the signals collected by the liquid level signal collection submodule are mainly oil mass sensor signals, the signals collected by the temperature signal collection submodule include a lubricant temperature signal, a coolant temperature signal, an ambient temperature signal and a main reducer temperature signal, the signals collected by the pressure signal collection submodule are mainly engine lubricant pressure signals, the signals collected by the discrete magnitude signal collection submodule are mainly ground/open signals, and include an oil pump one state signal, an oil pump two state signal, an electronic fan one state signal, an electronic fan two state signal, a generator state signal, a clutch state signal, an engine over-temperature signal, an engine start signal, a generator start signal, a rotor speed, And (5) engine vehicle-out signals.
The invention has the beneficial effects that:
1. the unmanned helicopter engine parameter acquisition system comprises a power module, a data input module, a data processing module, a data output module, a data transmission module, a data storage module, a shell and a connector, so that the engine tool state can be monitored in real time and the engine can be controlled in real time.
2. The data transmission module of the unmanned helicopter engine parameter acquisition system CAN communicate the engine parameter acquisition device with the unmanned helicopter avionics system, is realized by adopting a CAN (controller area network) bus, and transmits acquired engine information to the avionics system in time, so that the information acquisition is more accurate and comprehensive.
Drawings
FIG. 1 is a schematic diagram of the overall composition of an unmanned helicopter engine parameter acquisition system of the present invention;
FIG. 2 is a schematic diagram of the power module components of an engine parameter acquisition system for an unmanned helicopter according to the present invention;
FIG. 3 is a schematic diagram of the data acquisition module of the unmanned helicopter engine parameter acquisition system of the present invention;
FIG. 4 is a schematic diagram of a data output module of the unmanned helicopter engine parameter acquisition system of the present invention.
Detailed Description
In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further described with the specific embodiments.
Referring to fig. 1 to 4, the present invention provides a technical solution: the utility model provides an unmanned helicopter engine parameter acquisition system, includes the acquisition system body, its characterized in that: the acquisition system body comprises a power supply module, a data input module, a data processing module, a data output module, a data transmission module, a data storage module, a shell and a connector.
As a preferred embodiment of the invention, the power module comprises DC28V-DC12V, DC12V-DC5V, DC5V-DC3.3V, and DC28V-DC12V, wherein the power module is used for converting onboard 28V direct current into 12V direct current required by an engine parameter acquisition system and is mainly used for controlling an internal relay of the engine parameter acquisition system; the DC12V-DC5V is used for converting 12V direct current in the engine parameter acquisition system into 5V direct current and is mainly used for providing a working power supply for oil mass sensor equipment on the unmanned helicopter; the DC12V-DC3.3V is used for converting 12V direct current in the engine parameter acquisition system into 3.3V direct current and is mainly used for supplying power to the data processing module of the engine parameter acquisition system and providing a working power supply for the speed sensor equipment on the unmanned helicopter.
As a preferred embodiment of the present invention, the data acquisition module includes a rotation speed signal acquisition submodule, a liquid level signal acquisition submodule, a temperature signal acquisition submodule, a pressure signal acquisition submodule, and a discrete magnitude signal acquisition submodule, and signals acquired by the rotation speed signal acquisition submodule include an engine rotation speed signal and a rotor rotation speed signal; the signal collected by the liquid level signal collecting submodule is mainly an oil mass sensor signal; the signals collected by the temperature signal collecting submodule comprise an oil temperature signal, a cooling liquid temperature signal, an environment temperature signal and a main speed reducer temperature signal; the signals collected by the pressure signal collecting submodule are mainly engine lubricating oil pressure signals; the signals acquired by the discrete magnitude signal acquisition submodule are mainly ground/open signals and comprise a first oil pump state signal, a second oil pump state signal, a first electronic fan state signal, a second electronic fan state signal, a generator state signal, a clutch state signal, an engine overtemperature signal, an engine starting signal and an engine vehicle-out signal.
As a preferred embodiment of the present invention, the data processing module mainly refers to an STM32 single chip microcomputer, which is used for collecting, calculating and controlling engine parameters, and mainly includes resolving a rotational speed signal (engine rotational speed, rotor rotational speed) and outputting an over-rotational speed warning signal, resolving a temperature signal (oil temperature, coolant temperature, ambient temperature, main reducer temperature), outputting a temperature signal, determining whether to turn on or off an electronic fan according to the coolant temperature, resolving a liquid level signal (oil sensor), outputting a low oil warning signal, resolving a pressure signal (engine oil pressure), outputting a high pressure warning signal, outputting discrete quantity signals (oil pump one state signal, oil pump two state signal, electronic fan one state signal, electronic fan two state signal, generator state signal, clutch state signal, engine state signal, and the like, Engine over-temperature signal) is calculated and output.
As a preferred embodiment of the present invention, the data output module mainly includes a first oil pump state signal, a second oil pump state signal, a first electronic fan state signal, a second electronic fan state signal, a clutch control signal, and an engine start signal, determines whether to start the first electronic fan or the second electronic fan and the rotation speed of the electronic fan according to the temperature of the coolant, determines whether to start the oil pump (simultaneously start/stop the first oil pump or the second oil pump) according to a remote control instruction, and determines to start the engine or to shut down the engine according to the remote control instruction.
As a preferred embodiment of the invention, the data transmission module is mainly used for the communication between the engine parameter collector and the avionics system of the unmanned helicopter and is realized by adopting a CAN bus.
As a preferred embodiment of the present invention, the data storage module mainly refers to a Flash chip, and stores the engine operating time and the number of times of opening/closing the relay, and the data is not output externally, and can be read through a debug interface.
In a preferred embodiment of the present invention, the housing is designed to dissipate heat, the heat dissipation area is increased by providing the heat dissipation fins, and the housing is subjected to a waterproof treatment using the sealing ring.
As a preferred embodiment of the invention, the connector adopts a J599 system connector, so that the reliability is high and the universality is strong.
While there have been shown and described what are at present considered the fundamental principles and essential features of the invention and its advantages, it will be apparent to those skilled in the art that the invention is not limited to the details of the foregoing exemplary embodiments, but is capable of other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.
Claims (10)
1. The utility model provides an unmanned helicopter engine parameter acquisition system, includes the acquisition system body, its characterized in that: the acquisition system body comprises a power supply module, a data input module, a data processing module, a data output module, a data transmission module, a data storage module, a shell and a connector.
2. The unmanned helicopter engine parameter acquisition system of claim 1, wherein: the power supply module comprises DC28V-DC12V, DC12V-DC5V and DC 5V-DC3.3V.
3. The unmanned helicopter engine parameter acquisition system of claim 1, wherein: the data acquisition module comprises a rotating speed signal acquisition submodule, a liquid level signal acquisition submodule, a temperature signal acquisition submodule, a pressure signal acquisition submodule and a discrete magnitude signal acquisition submodule.
4. The unmanned helicopter engine parameter acquisition system of claim 1, wherein: the data processing module mainly refers to an STM32 single chip microcomputer.
5. The unmanned helicopter engine parameter acquisition system of claim 1, wherein: the data output module mainly comprises a first oil pump state signal, a second oil pump state signal, a first electronic fan state signal, a second electronic fan state signal, a clutch control signal and an engine starting signal.
6. The unmanned helicopter engine parameter acquisition system of claim 1, wherein: the data transmission module is mainly used for communicating the engine parameter collector with the avionics system of the unmanned helicopter and is realized by adopting a CAN bus.
7. The unmanned helicopter engine parameter acquisition system of claim 1, wherein: the data storage module mainly refers to a Flash chip.
8. The unmanned helicopter engine parameter acquisition system of claim 1, wherein: the shell is subjected to heat dissipation design, the heat dissipation area is increased by arranging the heat dissipation fins, and the shell is subjected to waterproof treatment by using the sealing ring.
9. The unmanned helicopter engine parameter acquisition system of claim 1, wherein: the connector adopts a J599 system connector.
10. The unmanned helicopter engine parameter acquisition system of claim 3, wherein: the signal that rotational speed signal gathered the submodule piece includes engine speed signal, rotor speed signal, the signal that the liquid level signal gathered the submodule piece is mainly the oil mass sensor signal, the signal that the temperature signal gathered the submodule piece includes lubricating oil temperature signal, coolant temperature signal, ambient temperature signal, final drive temperature signal, the signal that the pressure signal gathered the submodule piece is mainly engine lubricating oil pressure signal, the signal that the discrete quantity signal gathered the submodule piece is mainly ground/opening signal, including oil pump a state signal, two state signals of oil pump, an electronic fan state signal, two state signals of electronic fan, generator state signal, clutch state signal, engine overtemperature intensity signal, engine start signal, engine signal of going out.
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| CN202111523738.2A CN114323653A (en) | 2021-12-13 | 2021-12-13 | Unmanned helicopter engine parameter acquisition system |
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| CN202111523738.2A CN114323653A (en) | 2021-12-13 | 2021-12-13 | Unmanned helicopter engine parameter acquisition system |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101256117A (en) * | 2008-03-26 | 2008-09-03 | 北京航空航天大学 | Device and method for testing synthesis parameter of aviation piston engine |
| CN106197559A (en) * | 2016-08-26 | 2016-12-07 | 西安航空电子科技有限公司 | A kind of general aircraft engine parameter collecting method and device |
| US20170363514A1 (en) * | 2016-06-17 | 2017-12-21 | Airbus Operations Sas | Method for monitoring the engines of an aircraft |
| CN109113804A (en) * | 2017-06-22 | 2019-01-01 | 通用电气公司 | Engine and motor health monitoring method and gas-turbine unit |
| CN214409627U (en) * | 2021-01-11 | 2021-10-15 | 成都欧开科技有限公司 | Airborne equipment parameter collector |
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2021
- 2021-12-13 CN CN202111523738.2A patent/CN114323653A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101256117A (en) * | 2008-03-26 | 2008-09-03 | 北京航空航天大学 | Device and method for testing synthesis parameter of aviation piston engine |
| US20170363514A1 (en) * | 2016-06-17 | 2017-12-21 | Airbus Operations Sas | Method for monitoring the engines of an aircraft |
| CN106197559A (en) * | 2016-08-26 | 2016-12-07 | 西安航空电子科技有限公司 | A kind of general aircraft engine parameter collecting method and device |
| CN109113804A (en) * | 2017-06-22 | 2019-01-01 | 通用电气公司 | Engine and motor health monitoring method and gas-turbine unit |
| CN214409627U (en) * | 2021-01-11 | 2021-10-15 | 成都欧开科技有限公司 | Airborne equipment parameter collector |
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