CN208476347U - Integrated aero-engine fuel measurement monitoring device - Google Patents
Integrated aero-engine fuel measurement monitoring device Download PDFInfo
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- CN208476347U CN208476347U CN201820989525.6U CN201820989525U CN208476347U CN 208476347 U CN208476347 U CN 208476347U CN 201820989525 U CN201820989525 U CN 201820989525U CN 208476347 U CN208476347 U CN 208476347U
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Abstract
The utility model discloses a kind of integrated aero-engine fuel measurement monitoring devices, including Portable movable protective housing, transmitter module and controller, Portable movable protective housing is equipped with sensor interface and power supply communication interface, and sensor interface includes fuel-quantity transducer interface, oil temperature sensor interface, oil pressure sensor interface and oil pump current sensor interface；Control panel is installed in Portable movable protective housing, and control panel is equipped with transmitter module and controller；Transmitter module includes oil mass transducing unit, oil temperature transducing unit, oil pressure transducing unit and electric current transducing unit, is connected respectively with respective sensor interface；Controller is according to the start and stop of the signal control oil pump from transmitter module.The utility model improves convenience, the versatility of aero-engine fuel measurement monitoring device use and maintenance as independent integrated aero-engine fuel quantity monitoring device.
Description
Technical field
The utility model belongs to the engine fuel oil system field of unmanned vehicle, more particularly, to a kind of integrated
Aero-engine fuel measurement monitoring device.
Background technique
Aircraft engine fuel oil system is a complexity and important system, it contains fuel tank, fuel pipe, fuel oil
Multiple component parts such as pump and accessory are the energy sources that unmanned vehicle operates normally.The monitoring of aero-engine fuel measurement
Device is a kind of dedicated monitoring and control equipment of engine fuel oil system for being intended for unmanned vehicle, is aero-engine
The control core of fuel system, the parameters of real-time detection fuel system, pressure, temperature, oil mass and alarm signal etc., and root
Fuel pump is opened or closed according to engine requirement, to control the oil mass output of fuel system.
Under normal conditions, aero-engine fuel measurement monitoring device does not form independent equipment, as aeroplane engine
A part of machine fuel system mixes with the rest part of aircraft engine fuel oil system, aero-engine is caused to fire
Installation, the maintenance of oil measurement monitoring device are extremely inconvenient, significantly limit the use of aero-engine fuel measurement monitoring device
The convenience of maintenance, versatility.Therefore, how to realize general aero-engine fuel measurement monitoring device, improve aviation hair
The convenience of motivation fuel measurement monitoring device use and maintenance, versatility, become technical problem urgently to be resolved.
Utility model content
The purpose of this utility model is to propose a kind of installation and maintenance is convenient and integrated aeroplane engine with versatility
Machine fuel measurement monitoring device.
To achieve the goals above, the utility model provides a kind of integrated aero-engine fuel measurement monitoring dress
It sets, which includes:
Portable movable protective housing, the Portable movable protective housing are equipped with sensor interface and power supply communication interface,
The sensor interface includes fuel-quantity transducer interface, oil temperature sensor interface, oil pressure sensor interface and oil pump current sense
Device interface；
Control panel, the control panel are installed in the Portable movable protective housing, and the control panel is equipped with transmitter
Module and controller；
The transmitter module includes oil mass transducing unit, oil temperature transducing unit, oil pressure transducing unit and electric current pick-up list
Member, the oil mass transducing unit, oil temperature transducing unit, oil pressure transducing unit, electric current transducing unit are sensed with the oil mass respectively
Device interface, oil temperature sensor interface, oil pressure sensor interface, oil pump current sensor interface are connected, and with the controller
It is connected；
Controller, the controller are used for the start and stop according to the signal control oil pump from the transmitter module.
Preferably, the controller and flight-control computer communicate to connect, and the controller will be from the pick-up
The signal of device module is sent to the flight-control computer, and receives the oil pump control letter that the flight-control computer is sent
Number, thus according to the start and stop of the oil pump control signal control oil pump.
Preferably, the Portable movable protective housing is using electromagnetic shielding box, and is installed on engine by fixing leg
In equipment compartment.
Preferably, the measurement monitoring device further includes input filter, and it is logical that the input filter is set to the power supply
Between communication interface and the control panel.
Preferably, the measurement monitoring device further includes output filter, and the output filter is set to the control panel
Between the sensor interface.
Preferably, the power supply communication interface includes serial communication interface.
Preferably, the measurement monitoring device further includes low oil level detection unit, and the low oil level detection unit is set to institute
It states between fuel-quantity transducer interface and the controller, when the measuring signal of the fuel-quantity transducer is lower than predetermined oil level, institute
It states low oil level detection unit and transmits low oil level alarm signal to the controller.
Preferably, the controller and flight-control computer communicate to connect, and the controller is also used to the alarm
Signal passes to the flight-control computer.
Preferably, the oil pump includes main oil pump, and the measurement monitoring device further includes main oil pump relay unit, described
Main oil pump relay unit is connected with the controller, and connect with the electric current transducing unit.
Preferably, the oil pump further includes emergency bearing oil pump, and the measurement monitoring device further includes emergency bearing oil pump relay list
Member, the emergency bearing oil pump relay unit are connected with the controller, and connect with the electric current transducing unit.
The utility model has the beneficial effects that: the fuel measurement monitoring device of the utility model is by by sensor interface
It is set on Portable movable protective housing, control panel is mounted in Portable movable protective housing, control panel with power supply communication interface
On transmitter module connect respectively with respective sensor interface, realize and fuel measurement monitoring device be integrated in one, shape
At independent device, the convenience of fuel oil monitoring device installation and maintenance is improved, and there is versatility, to improve nobody
Design, the production efficiency of aircraft.
The fuel measurement monitoring device of the utility model uses electromagnetic shielding box by Portable movable protective housing, for measurement
Monitoring device provides high-intensitive physically and electrically magnetic protection, can meet the requirement of national military standard, be suitble to small space installation and
Maintenance, to greatly increase the convenience of the installation of measurement monitoring device and maintenance and measure the versatility of monitoring device.
The system of the utility model has other characteristics and advantages, these characteristics and advantages are from the attached drawing being incorporated herein
It will be apparent in subsequent specific embodiment, or will be in the attached drawing and subsequent specific embodiment being incorporated herein
Middle to be stated in detail, these the drawings and specific embodiments are used together to explain the specific principle of the utility model.
Detailed description of the invention
The utility model illustrative embodiments are described in more detail in conjunction with the accompanying drawings, the utility model it is upper
It states and other purposes, feature and advantage will be apparent.Wherein, in the utility model illustrative embodiments, phase
Same appended drawing reference typically represents same parts.
Fig. 1 shows the integrated aero-engine fuel measurement monitoring device of one embodiment according to the present utility model
General structure schematic diagram.
Fig. 2 shows the integrated aero-engine fuel measurement monitoring devices of one embodiment according to the present utility model
Schematic diagram of internal structure.
Fig. 3 shows the integrated aero-engine fuel measurement monitoring device of one embodiment according to the present utility model
Control panel functional block diagram.
Description of symbols:
1, shielding box side plate；2, shielding box cover board；3, fixing leg；4, sensor interface；5, power supply communication interface；6, it controls
Making sheet；7, output filter；8, input filter；9, oil mass transducing unit；10, low oil level detection unit；11, oil temperature pick-up list
Member；12, oil pressure transducing unit；13, relay unit；14, electric current transducing unit；15, A/D chip；16, controller；17, serial ports
Unit；18, DC-DC module.
Specific embodiment
The preferred embodiment of the utility model is more fully described below with reference to accompanying drawings.Although showing this reality in attached drawing
With novel preferred embodiment, however, it is to be appreciated that may be realized in various forms the utility model without that should be illustrated here
Embodiment limited.On the contrary, thesing embodiments are provided so that the utility model is more thorough and complete, and energy
It is enough that the scope of the utility model is completely communicated to those skilled in the art.
Integrated aero-engine fuel measurement monitoring device according to the present utility model includes: Portable movable protection
Case, Portable movable protective housing are equipped with sensor interface and power supply communication interface, and sensor interface includes that fuel-quantity transducer connects
Mouth, oil temperature sensor interface, oil pressure sensor interface and oil pump current sensor interface；Control panel, control panel are installed on portable
In the mobile protective housing of formula, control panel is equipped with transmitter module and controller；Transmitter module includes oil mass transducing unit, oil temperature
Transducing unit, oil pressure transducing unit and electric current transducing unit, oil mass transducing unit, oil temperature transducing unit, oil pressure transducing unit, electricity
Stream transducing unit connects with fuel-quantity transducer interface, oil temperature sensor interface, oil pressure sensor interface, oil pump current sensor respectively
Mouth is connected, and is connected with the controller；Controller, controller are used to be controlled according to the signal from transmitter module
The start and stop of oil pump.
Specifically, fuel-quantity transducer is connect with fuel-quantity transducer interface, so that the measuring signal of fuel-quantity transducer be made to enter
Oil mass transducing unit, is resent to controller.Such as fuel-quantity transducer can be four-wire system capacitance type sensor, fuel-quantity transducer connects
Mouth provides stable DC28V power supply for fuel-quantity transducer, and follows circuit to obtain the electric signal of oil mass by amplification, passes through calibration
Parameter and solution formula obtain the numerical value of fuel quantity, it can be achieved that 0.1%.FS measurement accuracy, and can be expanded according to service condition
It opens up four-way while sampling.Equipped with fuel oil temperature acquisition channel all the way, oil temperature sensor is connect with oil temperature sensor interface, from
And the measuring signal of oil temperature sensor is made to enter oil temperature transducing unit, then access controller.For example, oil temperature sensor can be used three
Line PT200 sensor, and three-wire system PT200 transmitter is used, -40 DEG C~80 DEG C of surveying range and 0.1%.FS can be met
Measurement accuracy.Equipped with fuel pressure acquisition channel all the way, oil pressure sensor is connect with oil pressure sensor interface, to make oil pressure
The measuring signal of sensor enters oil pressure transducing unit, is resent to controller.Such as four-wire system strain gauge transducer can be used,
Stable DC10V driving voltage is provided for oil pressure sensor by oil pressure sensor interface, and is obtained by difference transmission circuit
The electric signal of fuel pressure, by calibrating parameters and solution formula obtain fuel pressure numerical value, it can be achieved that 0.1%.FS survey
Accuracy of measurement.Equipped with oil pump current acquisition channel, oil pump is connected to oil pump current sensor interface, so that oil pump electric current enters electric current
Transducing unit is resent to controller.Isolated current collection circuit can be used, it, can in the case where guaranteeing that oil pump works normally
Acquisition Circuit is effectively protected is not influenced the current acquisition precision, it can be achieved that 1%.FS by operation of oil pump voltage fluctuation.
According to the fuel measurement monitoring device of illustrative embodiment by by sensor interface and power supply communication interface
On Portable movable protective housing, control panel is mounted in Portable movable protective housing, the transmitter module on control panel
It is connect respectively with respective sensor interface, realizes and fuel measurement monitoring device is integrated in one, formed independent device, mention
The high convenience of fuel oil monitoring device installation and maintenance, and there is versatility, to improve the design of unmanned vehicle, life
Produce efficiency.
Preferably, controller and flight-control computer communicate to connect, and controller will be from transmitter module
Signal be sent to flight-control computer, and receive flight-control computer transmission oil pump control signal, thus according to oil
The start and stop of pump control signal control oil pump.Flight-control computer receives the signal from controller, and is sent out based on controller
The signal from transmitter module sent determines whether engine condition is normal by artificial judgment or by automatic decision,
When engine condition occurs abnormal, then corresponding oil pump control signal is sent to controller, shut down oil pump；In engine condition
When restoring normal, corresponding oil pump control signal also is sent to controller, restarts oil pump.This partial function is this field
The prior art, details are not described herein.
Preferably, Portable movable protective housing is using electromagnetic shielding box, and is installed on and is started by fixing leg
In machine equipment cabin.
Electromagnetic screen is used by Portable movable protective housing according to the fuel measurement monitoring device of illustrative embodiment
Box is covered, high-intensitive physically and electrically magnetic protection is provided for measurement monitoring device, the requirement of national military standard can be met, be suitble to narrow sky
Between installation and maintenance, thus greatly increase measurement monitoring device installation and maintenance convenience and measurement monitoring device
Versatility.
Preferably, measurement monitoring device further includes input filter, and input filter is set to power supply communication interface
Between control panel.
Specifically, it after the power supply of unmanned vehicle is entered in the mobile protective housing of formula of taking by power supply communication interface, passes through first
It crosses input filter to be filtered, then accesses control panel and be powered for control panel.
Preferably, measurement monitoring device further includes output filter, and output filter is set to control panel and sensing
Between device interface.
Specifically, control panel can provide the DC28V power supply of (DC voltage) for fuel-quantity transducer, and the power supply is by output
After filter is filtered, enter fuel-quantity transducer via sensor interface.
Preferably, power supply communication interface includes serial communication interface.
Preferably, measurement monitoring device further includes low oil level detection unit, and low oil level detection unit is set to oil mass
Between sensor interface and controller, when the measuring signal of fuel-quantity transducer be lower than predetermined oil level when, low oil level detection unit to
Controller transmits low oil level alarm signal.
Specifically, the measuring signal all the way of fuel-quantity transducer is sent to low oil level detection unit, when measuring signal is lower than pre-
When stand oil position, the measuring signal of fuel-quantity transducer enters low oil level detection unit via fuel-quantity transducer interface, by DC28V high electricity
Pressure is converted into DC3.3V (DC voltage) level, and DC3.3V level is sent to controller by low oil level detection unit, as effective
The low alarm signal of oil level, with alert action, personnel are handled in time.
Preferably, controller and flight-control computer communicate to connect, and controller is also used to pass alarm signal
Pass flight-control computer.
Preferably, oil pump includes main oil pump, and measurement monitoring device further includes main oil pump relay unit, main oil pump
Relay unit is connected with controller, and connect with electric current transducing unit.
Preferred embodiment, oil pump further include emergency bearing oil pump, and measurement monitoring device further includes emergency bearing oil pump relay unit, spare
FP Fuel Pump Relay unit is connected with controller, and connect with electric current transducing unit.
Specifically, the utility model is equipped with main oil pump and emergency bearing oil pump, and main oil pump and emergency bearing oil pump can be all made of two-way
Control circuit.It is illustrated by taking the control circuit of single channel oil pump as an example, the independent control circuit of two-way is equipped on control panel 6,
On 2 relays that the two path control signal come out from controller 16 is respectively connected to relay unit, relay is using normally closed
The relay of contact, and be double-contact relay, double-contact is connected to oil pump simultaneously, that is to say, that has 4 contacts while connecting
To single channel oil pump.When controller receives by serial communication interface the oil pump stop signal from flight-control computer
When, controller controls relay unit, keeps the contact of relay in the open state, and relay signal passes through electric current pick-up list
Member, oil pump current sensor interface are transmitted to oil pump, so that control oil pump stops.
Oil pump according to the fuel measurement monitoring device of illustrative embodiment includes main oil pump and emergency bearing oil pump, every road
Oil pump is connect with relay unit, passes through the start and stop of relay unit control oil pump.In addition, relay unit can be soft or hard
Redundancy control capability is all made of on part, i.e. software redundancy control prevents software counting loss, and hardware redundancy control prevents single channel different
Often, the time between failures for effectively guaranteeing fuel measurement monitoring device improve the stability of measurement monitoring device.
Embodiment
The integrated aero-engine fuel oil that Fig. 1 and Fig. 2 respectively illustrates one embodiment according to the present utility model is surveyed
The general structure schematic diagram and schematic diagram of internal structure of monitoring device are measured, Fig. 3 shows an implementation according to the present utility model
The functional block diagram of the control panel of the integrated aero-engine fuel measurement monitoring device of example.
In conjunction with shown in Fig. 1, Fig. 2 and Fig. 3, which includes: portable shifting
Dynamic protective housing, Portable movable protective housing are equipped with sensor interface 4 and power supply communication interface 5, and sensor interface 4 includes oil mass
Sensor interface, oil temperature sensor interface, oil pressure sensor interface and oil pump current sensor interface；Control panel 6, control panel 6
It is installed in Portable movable protective housing, control panel 6 is equipped with transmitter module and controller 16；Transmitter module includes oil mass
Transducing unit 9, oil temperature transducing unit 11, oil pressure transducing unit 12 and electric current transducing unit 14, oil mass transducing unit 9, oil temperature become
Send unit 11, oil pressure transducing unit 12, electric current transducing unit 14 respectively with fuel-quantity transducer interface, oil temperature sensor interface, oil
Pressure sensor interface, oil pump current sensor interface are connected, and are connected with the controller；Controller 16, controller 16
For the start and stop according to the signal control oil pump from transmitter module.
Wherein, controller 16 and flight-control computer communicate to connect, and controller 16 will be from the letter of transmitter module
Number it is sent to flight-control computer, and receives the oil pump control signal of flight-control computer transmission, thus according to oil pump control
The start and stop of signal control oil pump processed.
Wherein, the power supply of each sensor of engine and output signal access Portable movable by sensor interface 4 and protect
In case, the power supply of unmanned vehicle and the communication interface of flight-control computer access portable shifting by power supply communication interface 5
In dynamic protective housing.
Wherein, Portable movable protective housing is using electromagnetic shielding box comprising shielding box side plate 1 and upper and lower two pieces of shielding boxs
Cover board 2, shielding box cover board 2 are installed on shielding box side plate 1 by M3 bolt.Using the bolt of M5 by Portable movable protective housing
It is installed in engine apparatus cabin by fixing leg 3.Control panel 6 is installed in Portable movable protective housing by M3 bolt,
And tie point is reinforced using locking glue.
Wherein, measurement monitoring device further includes input filter 8, and input filter 8 is set to power supply communication interface 5 and control
Between plate 6.
Wherein, measurement monitoring device further includes output filter 7, and output filter 7 is set to control panel 6 and sensor interface
Between 4.
Wherein, power supply communication interface 5 includes serial communication interface.
Wherein, measurement monitoring device further includes low oil level detection unit 10, and low oil level detection unit 10 is sensed set on oil mass
Between device Interface and Controler, when the measuring signal of fuel-quantity transducer is lower than predetermined oil level, low oil level detection unit 10 is to control
Device processed transmits low oil level alarm signal, and controller is also used to alarm signal passing to flight-control computer.
Wherein, measurement monitoring device further includes relay unit 13, and relay unit 13 is connected with controller 16, and with
The connection of electric current transducing unit, the oil pump control signal control oil pump start and stop for being received according to controller.
The course of work of the integrated aero-engine fuel measurement monitoring device is as follows:
After the power supply of unmanned vehicle is entered in the mobile protective housing of formula of taking by power supply communication interface 4, input is first passed around
Filter 8 is filtered, and is then powered again for control panel 6；Control panel 6 provides the power supply of DC28V for fuel-quantity transducer, should
Power supply enters fuel-quantity transducer after output filter 7 is filtered, via sensor interface 4.Above each internal component is equal
It is installed on by M3 bolt on the dedicated tie point in the mobile protective housing of formula of taking, and carries out fastening and locking place using locking glue
Reason.
The measuring signal of fuel-quantity transducer sends oil mass transducing unit 9 to by fuel-quantity transducer interface, in oil mass pick-up
Unit 9 is converted into number by the acquisition of AD (analog signal conversion digital signal) chip 15 by voltage follow treated electric signal
Signal enters controller 16 (being MCU unit in the present embodiment) by universal serial bus, controller 16 by calibrating parameters and
Solution formula obtains the numerical value of fuel quantity, and controller 16 is by serial port unit 17 via serial communication interface by the numerical value of oil mass
It is uploaded to flight-control computer；When the measuring signal of fuel-quantity transducer is lower than predetermined oil level, the measurement letter of fuel-quantity transducer
Number enter low oil level detection unit 10, DC3.3V level is converted by DC28V high voltage, and be sent to controller 16, as having
The low alarm signal of the oil level of effect, controller 16 will be in the low alarm signals of the oil level via serial communication interface by serial port unit 17
Flight-control computer is reached, personnel are handled in time with alert action.
The measuring signal of oil temperature sensor sends oil temperature transducing unit 11 to by oil temperature sensor interface, in oil temperature pick-up
Unit 11 is converted into digital signal by the acquisition of A/D chip 15 by the transformed electric signal of resistance to voltage, passes through universal serial bus
Into controller 16, oil temperature data is uploaded to flight control meter via serial communication interface by serial port unit 17 by controller 16
Calculation machine.
The measuring signal of oil pressure sensor transmits oil feed pressure transducing unit 12 by oil pressure sensor interface, in oil pressure pick-up
Unit 12 obtains the electric signal of fuel pressure by difference transmission circuit, by millivolt to the transformed electric signal for lying prostrate threshold voltage
Digital signal is converted by the acquisition of A/D chip 15, controller 16 is entered by universal serial bus, passes through calibrating parameters in controller 16
The numerical value of fuel pressure is obtained with solution formula, and controller 16 is by serial port unit 17 via serial communication interface by the number of oil pressure
Value is uploaded to flight-control computer.
Oil pump electric current enters electric current transducing unit 14 by oil pump current sensor interface, in the warp of electric current transducing unit 14
After the sample resistance sampling in portion, converts current signal to the voltage signal of volt value, adopted by the designated lane of A/D chip 15
Collection is transmitted digital signal in controller 16 by universal serial bus after the completion of acquisition, and controller 16 is passed through by serial port unit 17
The oil pump current value is uploaded to flight-control computer by serial communication interface.
Every road binders pump is all made of two-way control circuit, the independent control circuit of two-way is equipped on control panel 6, from controller
16 two path control signals come out are respectively connected on 2 relays of relay unit 13, and relay is using normally-closed contact
Relay, and be double-contact relay, that is to say, that it is connected to oil pump simultaneously using 4 contacts.When under flight-control computer
Sending instructions to controller 16, controller 16 is received by serial port unit 17 to send instructions under flight-control computer,
And send instructions under and parse, the control signal of relay is obtained, and export the control signal to relay unit 13, relay
Device unit 13 executes movement according to the control signal, and the electric signal of output is converted into voltage signal through electric current transducing unit 14
Afterwards, oil pump is transmitted to by oil pump current sensor interface, thus the start and stop of control oil pump.
Preferably, serial port unit 17 uses RS422 serial communication.
The DC28V power supply that unmanned vehicle provides accesses in portable protection case via power supply communication interface 5, connects
To the DC-DC module 18 of control panel 6.DC-DC module 18 by DC28V power conversion be control panel 6 needed for DC5V, DC3.3V and
DC10V voltage.
In addition, can realize that multiplexer (MUX signal controls the control mode of single channel oil pump by all channel decoder；Controller
Program can carry out writing for software based on the embedded platform of C language, possess self-test and work normally two modes, real-time resolving
The measuring signal of sensor is simultaneously connected to flight-control computer via serial communication interface using serial port unit 17；It simultaneously can benefit
It with the software architecture of parallel more redundancies, improves the non-failure operation time of software, improves the stability of measurement monitoring device.
The embodiments of the present invention are described above, above description is exemplary, and non-exclusive, and
It is also not necessarily limited to disclosed embodiment.Without departing from the scope and spirit of embodiment described, for this technology
Many modifications and changes are obvious for the those of ordinary skill in field.
Claims (10)
1. a kind of integrated aero-engine fuel measurement monitoring device, which is characterized in that the measurement monitoring device includes:
Portable movable protective housing, the Portable movable protective housing is equipped with sensor interface and power supply communication interface, described
Sensor interface includes that fuel-quantity transducer interface, oil temperature sensor interface, oil pressure sensor interface and oil pump current sensor connect
Mouthful；
Control panel, the control panel are installed in the Portable movable protective housing, and the control panel is equipped with transmitter module
And controller；
The transmitter module includes oil mass transducing unit, oil temperature transducing unit, oil pressure transducing unit and electric current transducing unit, institute
Oil mass transducing unit, oil temperature transducing unit, oil pressure transducing unit, electric current transducing unit is stated to connect with the fuel-quantity transducer respectively
Mouth, oil temperature sensor interface, oil pressure sensor interface, oil pump current sensor interface are connected, and are connected with the controller
It connects；
Controller, the controller are used for the start and stop according to the signal control oil pump from the transmitter module.
2. integrated aero-engine fuel measurement monitoring device according to claim 1, which is characterized in that
The controller and flight-control computer communicate to connect, and the controller will be from the signal of the transmitter module
It is sent to the flight-control computer, and receives the oil pump control signal that the flight-control computer is sent, thus according to
The start and stop of the oil pump control signal control oil pump.
3. integrated aero-engine fuel measurement monitoring device according to claim 1, which is characterized in that
The Portable movable protective housing is installed in engine apparatus cabin using electromagnetic shielding box by fixing leg.
4. integrated aero-engine fuel measurement monitoring device according to claim 1, which is characterized in that the measurement
Monitoring device further includes input filter, and the input filter is set between the power supply communication interface and the control panel.
5. integrated aero-engine fuel measurement monitoring device according to claim 1, which is characterized in that the measurement
Monitoring device further includes output filter, and the output filter is set between the control panel and the sensor interface.
6. integrated aero-engine fuel measurement monitoring device according to claim 1, which is characterized in that the power supply
Communication interface includes serial communication interface.
7. integrated aero-engine fuel measurement monitoring device according to claim 1, which is characterized in that the measurement
Monitoring device further includes low oil level detection unit, and the low oil level detection unit is set to the fuel-quantity transducer interface and the control
Between device processed, when the measuring signal of the fuel-quantity transducer is lower than predetermined oil level, the low oil level detection unit is to the control
Device processed transmits low oil level alarm signal.
8. integrated aero-engine fuel measurement monitoring device according to claim 7, which is characterized in that the control
Device and flight-control computer communicate to connect, and the controller is also used to pass to the alarm signal flight control meter
Calculation machine.
9. integrated aero-engine fuel measurement monitoring device according to claim 1, which is characterized in that the oil pump
Including main oil pump, the measurement monitoring device further includes main oil pump relay unit, the main oil pump relay unit with it is described
Controller is connected, and connect with the electric current transducing unit.
10. integrated aero-engine fuel measurement monitoring device according to claim 1, which is characterized in that the oil
Pump further includes emergency bearing oil pump, and the measurement monitoring device further includes emergency bearing oil pump relay unit, the emergency bearing oil pump relay
Unit is connected with the controller, and connect with the electric current transducing unit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820989525.6U CN208476347U (en) | 2018-06-26 | 2018-06-26 | Integrated aero-engine fuel measurement monitoring device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820989525.6U CN208476347U (en) | 2018-06-26 | 2018-06-26 | Integrated aero-engine fuel measurement monitoring device |
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| Publication Number | Publication Date |
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| CN208476347U true CN208476347U (en) | 2019-02-05 |
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| CN201820989525.6U Active CN208476347U (en) | 2018-06-26 | 2018-06-26 | Integrated aero-engine fuel measurement monitoring device |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111664918A (en) * | 2020-05-22 | 2020-09-15 | 中船重工(青岛)海洋装备研究院有限责任公司 | Water level monitoring device for ocean tides |
| CN112833941A (en) * | 2020-12-28 | 2021-05-25 | 航天南洋（浙江）科技有限公司 | Multifunctional sensor for monitoring working state of oil tank and use method |
| CN116047957A (en) * | 2022-12-27 | 2023-05-02 | 中国航天空气动力技术研究院 | Fuel control system |
-
2018
- 2018-06-26 CN CN201820989525.6U patent/CN208476347U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111664918A (en) * | 2020-05-22 | 2020-09-15 | 中船重工(青岛)海洋装备研究院有限责任公司 | Water level monitoring device for ocean tides |
| CN112833941A (en) * | 2020-12-28 | 2021-05-25 | 航天南洋（浙江）科技有限公司 | Multifunctional sensor for monitoring working state of oil tank and use method |
| CN116047957A (en) * | 2022-12-27 | 2023-05-02 | 中国航天空气动力技术研究院 | Fuel control system |
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