CN208821151U - Aero-engine managing device - Google Patents

Abstract

The utility model discloses a kind of aero-engine managing devices, are arranged in shielding box, and low-temperature sensor interface, pyrostat interface, Ground testing equipment interface and flight-control computer interface are equipped on the side wall of the shielding box；Low temperature transmitting module, the high temperature transmitting module, resolving module for being provided with power module in the shielding box and being connect with the power module.Low temperature and high temperature transmitter module in device pass through corresponding low temperature and pyrostat interface respectively and connect with external sensor, resolving module in device transmits data by Ground testing equipment interface and flight-control computer interface outward and receives the control instruction issued, it realizes and aero-engine managing device is integrated in one, form independent device, improve the convenience of aero-engine managing device installation and maintenance, and there is versatility, to improve the design of unmanned vehicle, production efficiency.

Description

Aero-engine managing device

Technical field

The utility model belongs to the engine management field of unmanned vehicle, more particularly, to a kind of aero-engine Managing device.

Background technique

Aero-engine is the important component of unmanned vehicle and the important controlled device of flight control system, Since aero-engine system complex, monitoring quantity are various, it is unpractical for directly control by flight control system, therefore, In unmanned vehicle electrical system, generallys use aero-engine managing device and supervised to carry out the state of aero-engine It surveys, and parses the control instruction of flight-control computer to realize effective control to engine.

Aero-engine managing device needs to monitor the state parameters such as the temperature, pressure and revolving speed of aero-engine, control The control amounts such as igniting is enabled, utilize number bus to realize instruction and data interaction with flight-control computer.As aviation is sent out The complexity of motivation system improves, and the increase to intelligent demand, aero-engine managing device needs to possess online intelligence Analysis means, and realize that using these means, the intelligent management of aero-engine, such as biometrics and health status are commented The functions such as estimate.

Aero-engine managing device is different from general managing device, the reason is that, first is that its working environment is opposite Badly, second is that it is high to own system stability requirement, in general, it is the high stable worked in adverse circumstances Property equipment.Therefore, how to realize general aero-engine managing device, improve aero-engine managing device use and maintenance Convenience, 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 managing device.

Aero-engine managing device according to the present utility model is arranged in shielding box, on the side wall of the shielding box Equipped with low-temperature sensor interface, pyrostat interface, Ground testing equipment interface and flight-control computer interface:

Low temperature transmitting module, the high temperature for being provided with power module in the shielding box and being connect with the power module Transmitting module resolves module；

Wherein, the low temperature transmitting module is connected by the low-temperature sensor interface and one or more low-temperature sensors It connects, the signal that sensor is exported is converted to standardization signal, and provides regulated power supply for sensor；The high temperature pick-up Module is connect by the pyrostat interface with one or more pyrostats, and the signal that sensor is exported is converted For standard signal, and regulated power supply is provided for sensor；The resolving module and the low temperature transmitting module, the high temperature become It send module to connect, and is connect with the Ground testing equipment interface and flight-control computer interface, by the number of each sensor It is believed that breath is uploaded to the Ground testing equipment and the flight-control computer, while parsing the Ground testing equipment and flight control The control instruction that computer processed issues.

Preferably, the shielding box is installed in engine apparatus cabin by fixing leg.

Preferably, the resolving module passes through respectively with the Ground testing equipment interface and the flight-control computer interface The connection of RS422 bus.

Preferably, the low-temperature sensor includes gas temperature sensor, accelerator open degree sensor, pressure sensor, oil Quantity sensor.

Preferably, the low temperature transmitting module is connect by 11 tunnel channels with 11 gas temperature sensors, It is connect by four paths with four accelerator open degree sensors, is connected by two channels and two pressure sensors It connects, is connect by channel all the way with the fuel-quantity transducer.

Preferably, the pyrostat includes exhaust gas temperature sensor, speed probe.

Preferably, the high temperature transmitting module is connect by eight paths with eight exhaust gas temperature sensors, is passed through Channel is connect with the speed probe all the way.

Preferably, the power module powers link by multichannel as the high temperature transmitting module and the low temperature pick-up Module provides multiple standards power supply.

Preferably, the power module provides power supply by single channel power supply link for the resolving module.

Preferably, described device further includes relay, and the resolving module is connect with the primary side of the relay, described The secondary side of relay starts enabled control channel and the enabled switch connection of external engine by two-way.

The utility model has the beneficial effects that: the aero-engine managing device of the utility model is arranged in shielding box It is interior, by the side that low temperature and pyrostat interface, Ground testing equipment interface and flight-control computer interface are set to shielding box On wall, low temperature and high temperature transmitter module in device pass through corresponding low temperature and pyrostat interface and external biography respectively Sensor connects, and the resolving module in device transmits data by Ground testing equipment interface and flight-control computer interface outward and connects The control instruction for accepting hair realizes and aero-engine managing device is integrated in one, and forms independent device, improves boat The convenience of empty engine management device installation and maintenance, and there is versatility, to improve the design of unmanned vehicle, life Produce efficiency.

The aero-engine managing device setting of the utility model provides high intensity in electromagnetic shielding box for device Physically and electrically magnetic is protected, and can meet the requirement of national military standard, is suitble to the installation and maintenance of small space, to greatly increase survey It measures the convenience of monitoring device installation and maintenance and measures 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 reference label typically represents same parts.

The screen of the aero-engine managing device of one embodiment according to the present utility model is shown respectively in Fig. 1 a and Fig. 1 b Cover the side view and perspective view of box；

Fig. 2 shows the structure charts of the aero-engine managing device of one embodiment according to the present utility model；

Fig. 3 shows the inside of the shielding box of the aero-engine managing device of one embodiment according to the present utility model Structure chart.

Description of symbols:

1, fixing leg；2, Ground testing equipment interface；3, low-temperature sensor interface；4, flight-control computer interface；5, high Temperature sensor interface；6, shielding box；7, shielding box cover board；8, power circuit board；9, lower floor support；10, low temperature acquisition circuit plate； 11, middle layer bracket；12, high temperature collecting circuit board；13, upper layer bracket；14, rack positioning hole；15, circuit board mounting hole；16, it solves Calculate circuit board；17, bracket fastener hole；18, bracket fastener hole fixed point；19, support force end face；20, power module；21, it solves Calculate module；22, high temperature transmitting module；23, low temperature transmitting module；24, multichannel power supply link；25, single channel power supply link； 26, low temperature data bus；27, high-temperature data bus；28, low-temperature sensor bus；29, pyrostat bus；31, low temperature passes Sensor；32, pyrostat；33, Ground testing equipment；34, flight-control computer.

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.

The aero-engine managing device is the aviation developed for the aero-engine of Mr. Yu's money unmanned vehicle Engine management device, the device can realize the intake air temperature, delivery temperature, fuel pressure, air inlet pressure of this aero-engine The monitoring of the state parameters such as power and revolving speed, the monitoring of the control parameters such as engine throttle and mixing ratio throttle, engine start make The control for the amount of can control carries out instruction and the interaction of data using RS422 bus and winged control machine, utilizes RS422 bus and ground Measurement equipment carries out instruction and the interaction of data.

Aero-engine managing device according to the present utility model is arranged in shielding box, and Fig. 1 a shows practical new according to this The side view of the shielding box of the aero-engine managing device of one embodiment of type.As shown in Figure 1a, which passes through solid Determine stabilizer blade 1 to be installed in engine apparatus cabin, specifically, fixing leg 1 is passed through by M5 bolt and is mounted on engine apparatus cabin Frame plate on, meet every environmental experiment requirement of national military standard.

Ground testing equipment interface 2, low-temperature sensor interface 3, flight-control computer is equipped on the side wall of the shielding box to connect Mouth 4 and pyrostat interface 5.

Fig. 1 b shows the perspective view of the shielding box of aero-engine managing device shown in Fig. 1 a.As shown in Figure 1 b, it shields Lid plate 7 is installed on the ontology of shielding box 6 by M3 bolt, and high-intensitive physically and electrically magnetic protection is provided for the device.

Fig. 2 shows the structure charts of the aero-engine managing device of one embodiment according to the present utility model.Such as Fig. 2 It is shown, power module 20 is provided in shielding box 6 and is connect with power module 20 resolving module 21, high temperature pick-up mould Block 22, low temperature transmitting module 23.

Wherein, low temperature transmitting module 23 is connect by low-temperature sensor interface 3 with one or more low-temperature sensors 31.It is low Temperature sensor refers to using sensor at low ambient temperatures.That is, low-temperature sensor 31 passes through low-temperature sensor interface 3 Access the present apparatus.The signal that sensor exports is converted to standardization signal by low temperature transmitting module 23, and is provided for sensor Regulated power supply.

High temperature transmitting module 22 is connect by pyrostat interface 5 with one or more pyrostats 32.High temperature passes Sensor refers to using sensor in a high temperauture environment.That is, pyrostat 32 is accessed by pyrostat interface 5 The present apparatus.The signal that sensor exports is converted to standard signal by high temperature transmitting module 22, and provides pressure stabilizing electricity for sensor Source.

It resolves module 21 to connect with low temperature transmitting module 23, high temperature transmitting module 22, obtains low temperature transmitting module 23, high temperature The valid data of transmitting module 22, and carry out the resolving of corresponding data.It resolves module 21 and Ground testing equipment interface 2 and flight controls Computer interface 4 connects, that is to say, that Ground testing equipment 33 accesses the present apparatus, flight-control computer by Ground testing equipment interface 2 34 access the present apparatus by flight-control computer interface 4.The data information of each sensor is uploaded to outer by resolving module 21 The Ground testing equipment 33 and flight-control computer 34 in portion, while parsing the Ground testing equipment and the flight-control computer issues Control instruction.Resolve module 21 and Ground testing equipment interface 2 and flight-control computer interface 4 respectively by RS422 bus into Row instruction and the interaction of data.

Low-temperature sensor may include gas temperature sensor, accelerator open degree sensor, pressure sensor, oil mass sensing Device.

In one example, low temperature transmitting module 23 is connect by 11 tunnel channels with 11 gas temperature sensors, It is connect by four paths with four accelerator open degree sensors, is connect by two channels with two pressure sensors, pass through one Paths are connect with the fuel-quantity transducer.

Wherein, gas temperature sensor for detecting intake air temperature, temperature etc. in air themperature and cabin, be two-wire system PT1000 sensor, the low temperature transmitting module in the present apparatus correspondingly include dedicated PT1000 transmitter, can meet -40 DEG C ~300 DEG C of surveying range and the measurement accuracy of 0.1%.FS.

Specifically resistor type angle sensor can be used to carry out in the aperture that accelerator open degree sensor is used to measure throttle Feedback.When accelerator open degree sensor is resistor type angle sensor, the low temperature transmitting module in the present apparatus correspondingly includes dedicated Resistor type angle sensor transducer, 0 DEG C~100 DEG C of surveying range and the measurement accuracy of 1%.FS can be met.

Two-way pressure sensor is used for probe gas pressure all the way for detecting fuel pressure all the way.Specifically, pressure Sensor all can be piezoresistive pressure sensor, and the low temperature speed-variable module in the present apparatus correspondingly includes dedicated pressure drag Formula pressure transducer can meet the surveying range of 0~8Bar and the measurement accuracy of 0.1%.FS.Pressure drag type pressure sensing Device transmitter receives the 0-100mV analog signal of pressure sensor, and stable DC10V voltage is provided for sensor.

Fuel-quantity transducer is used to measure the oil mass in fuel tank, can be capacitance level transducer.According to the shape of fuel tank Level value is fitted to volumetric values by shape, and the low temperature speed-variable module in the present apparatus correspondingly includes dedicated liquid level sensor pick-up Device can meet the surveying range of 0~12L and the measurement accuracy of 1%.FS.Liquid level sensor transmitter receives pressure sensor 0-5V analog signal, and stable DC12V voltage is provided for sensor.

Pyrostat may include exhaust gas temperature sensor, speed probe.

In one example, high temperature transmitting module 22 is connect by eight paths with eight exhaust gas temperature sensors, is passed through Channel is connect with speed probe all the way.

Exhaust gas temperature sensor can be armoured thermocouple, concrete form is K-type heat for detecting delivery temperature progress Galvanic couple.When exhaust gas temperature sensor is K-type thermocouple, the high temperature transmitting module in the present apparatus correspondingly includes dedicated K even Transmitter can meet -40 DEG C~1200 DEG C of surveying range and the measurement accuracy of 0.1%.FS.

Speed probe can be Mageneto-sensitive type speed probe for measuring engine speed.Height in the present apparatus Warm transmitting module correspondingly includes isolated Mageneto-sensitive type speed probe transmitter, can meet 0~3000rpm surveying range and The measurement accuracy of ± 10rpm.Isolated Mageneto-sensitive type speed probe transmitter receives the pulse duration frequency signal of speed probe, and Stable DC12V voltage is provided for sensor.

Preferably, which further includes that two-way starts enabled control channel.Start enabled mechanism and is installed on engine body On, according to its connection relationship with ground come whether determining that engine start enables.Present apparatus interior design has isolated redundancy control Circuit processed controls two-way relay by resolving module, to realize that two-way starting makes can control.

Preferably, which further includes that four tunnels ± 5V angle is spare, and being can terminating resistor formula angular transducer or ± 5V Sensor signal meets -5V~+5V surveying range and the measurement accuracy of 0.1%.FS using instrument amplifier.

Power module 20 using multichannel power supply link 24 be high temperature speed-variable module 22 and low temperature speed-variable module 23 provide ± 15V mock standard power supply and DC12V sensor power supply and DC10V reference power supply；Power module 20 is powered using single channel Link 25 is to resolve module 21 to provide DC5V high-current power supply.

It resolves module 21 and high temperature speed-variable module 22 and low temperature is obtained by low temperature data bus 26 and high-temperature data bus 27 The valid data of speed-variable module 23, and carry out the resolving of corresponding data；Low temperature speed-variable module 23 passes through low-temperature sensor bus 28 The data value of low-temperature sensor is obtained, high temperature speed-variable module 22 obtains the number of pyrostat by pyrostat bus 29 According to value.

The device further include include relay, resolve module connect with the primary side of the relay, will start enable control Signal processed is sent to relay.The starting makes to can control signal to be the resolving module by the device according to flight-control computer What control instruction obtained after being resolved.The secondary side of the relay starts enabled control channel by two-way, via flight Control computer interface and the enabled switch connection of external engine.

Aero-engine managing device according to the present utility model is built-in with on-line intelligence Processing Algorithm, contains following several Item function:

Inlet exhaust gas temperature and engine speed are monitored, and intake air temperature, delivery temperature and engine speed are set Assessment threshold values, each signal is mutually indepedent, calculates judge value by coupled operational, and whether in this, as engine operation Judgment basis；

Component is monitored using time, especially relay actuation number and FLASH read-write number, utilizes first device Life curve and the design of Reducing Rating requirement of part, have worked out the life prediction model of component, and utilize software expression-form, have indicated The service condition and biometrics of electronic component are determined according to operation relation stage by stage at the status indicator in four stages, had There is component health control algorithm, it can dynamic pre-estimating component service life；

Writing for software is carried out using the embedded platform based on C language, possess self-test and works normally two modes, if In respect of software self diagnosis and hardware watchdog mechanism, can real-time resolving sensor data information and utilize RS422 bus to carry out Data upload, while parsing and flying the control instruction that control machine and ground checkout equipment issue.In terms of stability, using how superfluous parallel Remaining software architecture improves the non-failure operation time of software.

Fig. 3 shows the inside of the shielding box of the aero-engine managing device of one embodiment according to the present utility model Structure chart.

As shown in figure 3, power circuit board 8 is installed in the inside mounting hole of 6 ontology of shielding box by M3 bolt, lower layer's branch Frame 9 is installed in the inside mounting hole of 6 ontology of shielding box by M3 bolt using bracket fastener hole 17；Low temperature acquisition circuit plate 10 It is fixed on the fixation hole of lower floor support 9 by M3 bolt using circuit board mounting hole 15, middle layer bracket 11 passes through M3 bolt benefit It is installed on the bracket fastener hole fixed point 18 of lower floor support 9 with bracket fastener hole 17；High temperature collecting circuit board 12 passes through M3 Bolt is fixed on the fixation hole of middle layer bracket 11 using circuit board mounting hole 15, and upper layer bracket 13 utilizes bracket by M3 bolt Fastener hole 17 is installed on the bracket fastener hole fixed point 18 of middle layer bracket 11；Resolving circuit plate 16 utilizes electricity by M3 bolt Road plate mounting hole 15 is fixed on the fixation hole of upper layer bracket 13；It is positioned between each bracket by rack positioning hole 14, and Using support force end face 19 as stress supporting point.

Correspondingly, power module 20 is mounted on power circuit board 8, and low temperature speed-variable module 23 is mounted on low temperature acquisition circuit On plate 10, high temperature speed-variable module 22 is mounted on high temperature collecting circuit board 12, is resolved module 21 and is mounted on resolving circuit plate 16.

Aero-engine managing device according to the present utility model possesses multiple sensor acquisition channel, is eight tunnels row respectively Temperature degree, 11 road gas temperatures, four road accelerator open degrees, two-way pressure, all the way oil mass, all the way revolving speed, the enabled control of two-way starting Tetra- tunnels Zhi He ± 5V angle alternate channel, in addition, to meet the needs of long-term stable operation, design has two-way redundancy and maloperation Circuit.

In addition, being required according to the resolving of related sensor equipped with embedded software system in device, realizing sensor Effective conversion of the analog quantity to sensor test volume is directly exported, and realizes a letter in each channel using host computer and signal source Calibration system, is then stored in the FLASH of itself, realizes the Configuration Online function in each channel by several numerical value calibration；According to According to requirement, free switching can be carried out between two modes of self-test and normal work, self-test will carry out self-test after being triggered The operation of module, automatically into normal operating conditions after operation, to guarantee the consistency of working state of device；Using calmly When the device implement of interruption function data upload frequencies of 2Hz, handled in conjunction with the hardware interrupts and software data of serial ports, sensor tested Amount carries out packing upload, and the instruction of winged control machine is carried out parsing and is issued；The caching of data is realized using software FIFO and is total to It enjoys, while guaranteeing data acquiring frequency, high-speed data acquisition and low speed data upload has been subjected to effective linking, that is, guaranteed The validity of data also ensures the real-time of data.

It can realize that multiplexer (MUX signal controls the control mode of single channel oil pump by all channel decoder；Director demon can Embedded platform based on C language carries out writing for software, possesses self-test and works normally two modes, real-time resolving sensor Measuring signal and be connected to flight-control computer via serial communication interface using serial port unit 17；Simultaneously using parallel The software architecture of 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 aero-engine managing device, which is characterized in that described device is arranged in shielding box, in the shielding box Side wall is equipped with low-temperature sensor interface, pyrostat interface, Ground testing equipment interface and flight-control computer interface；

Power module is provided in the shielding box and connect with the power module low temperature transmitting module, high temperature pick-up Module resolves module；

Wherein, the low temperature transmitting module is connect by the low-temperature sensor interface with one or more low-temperature sensors, with The signal that sensor exports is converted into standardization signal, and provides regulated power supply for sensor；The high temperature transmitting module It is connect by the pyrostat interface with one or more pyrostats, the signal that sensor is exported is converted to mark Calibration signal, and regulated power supply is provided for sensor；The resolving module and the low temperature transmitting module, the high temperature pick-up mould Block connection, and connect with the Ground testing equipment interface and flight-control computer interface, the data of each sensor are believed Breath is uploaded to Ground testing equipment and flight-control computer, while parsing the Ground testing equipment and the flight-control computer issues Control instruction.

2. aero-engine managing device according to claim 1, which is characterized in that the shielding box passes through fixing leg It is installed in engine apparatus cabin.

3. aero-engine managing device according to claim 1, which is characterized in that the resolving module with described is surveyed Equipment interface passes through RS422 bus with the flight-control computer interface respectively and connects.

4. aero-engine managing device according to claim 1, which is characterized in that the low-temperature sensor includes gas Temperature sensor, accelerator open degree sensor, pressure sensor, fuel-quantity transducer.

5. aero-engine managing device according to claim 4, which is characterized in that the low temperature transmitting module passes through ten Channel is connect with 11 gas temperature sensors all the way, is connected by four paths and four accelerator open degree sensors It connects, is connect by two channels with two pressure sensors, connect by channel all the way with the fuel-quantity transducer.

6. aero-engine managing device according to claim 1, which is characterized in that the pyrostat includes exhaust Temperature sensor, speed probe.

7. aero-engine managing device according to claim 6, which is characterized in that the high temperature transmitting module passes through eight Paths are connect with eight exhaust gas temperature sensors, are connect by channel all the way with the speed probe.

8. aero-engine managing device according to claim 1, which is characterized in that the power module passes through multichannel Power supply link provides multiple standards power supply for the high temperature transmitting module and the low temperature transmitting module.

9. aero-engine managing device according to claim 1, which is characterized in that the power module passes through single channel Power supply link provides power supply for the resolving module.

10. aero-engine managing device according to claim 1, which is characterized in that described device further includes relay, The resolving module is connect with the primary side of the relay, and the secondary side of the relay makes can control logical by two-way starting Road and the enabled switch connection of external engine.