CN205450644U - Aircraft engine control ware - Google Patents
Aircraft engine control ware Download PDFInfo
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- CN205450644U CN205450644U CN201521089431.6U CN201521089431U CN205450644U CN 205450644 U CN205450644 U CN 205450644U CN 201521089431 U CN201521089431 U CN 201521089431U CN 205450644 U CN205450644 U CN 205450644U
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Abstract
The utility model discloses an aircraft engine control ware, it includes control card and power integrated circuit board, both utilize PC104 contact pin and PC104 jack to pile up and install together in the instrument case, realize mechanical seal and electric isolation through upper portion shrouding and anterior shrouding afterwards, the accessible integration in equipment such as numerical control unit control steering engine control ware, ignition needle and the fuel pump of power integrated circuit board, integrated in control card's main control unit will dispose the instruction and turn into the serial instruction that accords with the TTL level and require, control simulation output interface to reach the purpose of control engine's three routes throttle aperture, utilize same integrated in temperature, pressure and the flow parameter that the engine is relevant is gathered to last thermal resistance unit, K idol unit, mV unit, mA unit, PWM unit and the analog input interface of control card. The utility model provides a collect the control of engine and monitor in an organic whole, can monitor the multiunit data simultaneously.
Description
Technical field
This utility model relates to a kind of aero-engine control unit, particularly relates to a kind of piston aviation engine controller.
Background technology
nullPiston aviation engine is widely used in small-sized gyroplane，Developing rapidly recently as unmanned plane，Piston aviation engine is the most more and more equipped in unmanned plane，This makes the control mode being in the past controlled with instrument increasingly be not suitable with news，Piston aviation engine comprises electrically and oil circuit two parts，Existing controller is divided into electric controller and oil circuit controller two parts the most accordingly，Which increase the complexity of Control system architecture，In order to ensure the flight safety of piston aviation engine，Need to monitor in real time the temperature of electromotor、The parameter such as pressure and flow，This needs extra configuration electromotor monitoring means，Carry out respective sensor and the data acquisition of status monitor and forwarding，In sum，The settling mode of existing aeroengine control system，Unimodule is for mainly comprising scheme in a distributed manner，It is high that the program has complexity、The deficiency that peripheral auxiliary quantity is many and measurement and control unit separates.
Utility model content
This utility model provides a kind of aero-engine control unit, this controller achieves igniting and the power supply control of electromotor, and the oil circuit control by the control realization to fuel pump, in addition, the status monitoring of electromotor is achieved by sensor conversion circuit, utilize RS232 serial ports to achieve the status monitoring of engine powered auxiliary equipment, be truly realized electrically and oil circuit is integrated and controls and the design of monitoring integration.
nullAero-engine control unit of the present utility model is secured by bolts on engine body，By uploading and power supply interface，Obtain host computer instruction and power supply，It includes Control card and power supply board，Both utilize PC104 contact pin and PC104 jack to be stacked and be installed in instrument case，Mechanical seal and electrical isolation is realized subsequently by top shrouding and anterior shrouding，After unlatching，Difference according to host computer instruction is operable with under different mode，Receive engine start、Stop or stop command，Can be by being integrated in the numerical control unit control flaps machine controller of described power supply board、Ignition electrode and fuel pump equipment，In equipment runs，It is integrated in the main control unit of described Control card to be converted into by configuration-direct and meet the serial command that Transistor-Transistor Logic level requires，Control simulation output interface，Thus reach to control the purpose of three road accelerator open degrees of electromotor，Utilize the thermal resistance unit being integrated in equally on described Control card、K idol unit、MV unit、MA unit、PWM unit and simulation input interface gather the temperature that electromotor is relevant、Pressure and flow parameter，Utilize equipment interface and RS232 communication protocol，Realize state acquisition and the forwarding of engine powered auxiliary equipment.
It is also integrated with on the most described power supply board: number electric unit, for external power source being converted into the power supply needed for digit chip；Mould electric unit, for being converted into the power supply needed for analog circuit by external power source.
The beneficial effects of the utility model are:
1. electrical control and the oil circuit of collection electromotor is controlled in one, the ad hoc power supply having data cell to carry out corresponding engine powered auxiliary equipment and the control of duty.
2. integrate the control of electromotor and monitor, the control of electromotor is carried out by data cell and simulation output interface, realized the collection of electromotor relevant temperature, pressure and flow parameter by sensor conversion circuit, and utilize equipment interface to realize state acquisition and the forwarding of engine powered auxiliary equipment.
3. picking rate is up to 1kHz, and has and preserve function in real time, utilizes modified model Newton iteration method and ten grades of multinomials to resolve, it is achieved that resistance and temperature precision is ± 0.2 DEG C, and K idol temperature is ± 1 DEG C.
Accompanying drawing explanation
Fig. 1 is structure chart of the present utility model.
Fig. 2 is Control card structure chart.
Fig. 3 is power panel card structure figure.
Symbol description
1. top shrouding, 2. instrument case, 3. Control card, 4. power supply board, 5. anterior shrouding, 6. main control unit, 7. power subsystem, 8. upload and power supply interface, 9. equipment interface, 10. simulation output interface, 11. thermal resistance unit, 12.K idol unit, 13. simulation input interfaces, 14.PWM unit, 15.mA unit, 16.mV unit, 17. number memory cell, 18.PC104 contact pin, 19. number electric units, 20. mould electric units, 21. numerical control units, 22.PC104 jack
Detailed description of the invention
Below in conjunction with accompanying drawing, this utility model is further described.
This utility model includes top shrouding 1, instrument case 2, Control card 3, power supply board 4, anterior shrouding 5, main control unit 6, power subsystem 7, uploads and power supply interface 8, equipment interface 9, simulation output interface 10, thermal resistance unit 11, K idol unit 12, simulation input interface 13, PWM unit 14, mA unit 15, mV unit 16, number memory cell 17, PC104 contact pin 18, number electric unit 19, mould electric unit 20, numerical control unit 21, PC104 jack 22.
In FIG, Control card 3 is stacked by PC104 contact pin and PC104 jack with power supply board 4, and is secured by bolts in instrument case, carries out mechanical seal and electrical isolation by top shrouding 1 and anterior shrouding 5 subsequently.
In fig. 2, main control unit 6 is controlled instruction and resolves and gather process and the post processing of data, by thermal resistance unit 11, K idol unit 12, simulation input interface 13, PWM unit 14, mA unit 15 and mV unit 16 carry out the collection of sensing data, gathered the status information of engine powered auxiliary equipment by equipment interface 9, subsequently data are stored in several memory cell 17.
In figure 3, external power source is converted into the power supply needed for digit chip by number electric unit 19, external power source is converted into the power supply needed for analog circuit by mould electric unit 20, is received the control signal of Control card 3 by stacking jointing holes 22, and controls engine powered auxiliary equipment by numerical control unit 21.
In terms of collection and preservation, the picking rate of 1kHz can be realized, and utilize number memory cell to carry out the real-time preservation of data, the unary biquadratic equation using follow-on Newton iteration method to achieve resistance and temperature resolves, and combined with hardware and software filtering, the acquisition precision of thermal resistance is brought up to ± 0.2 DEG C, uses ten grades of multinomials to realize the linear fit of K idol temperature, compared to traditional look-up table, the acquisition precision that K is even is brought up to ± 1 DEG C.
Claims (2)
- null1. an aero-engine control unit，It is characterized in that: it is secured by bolts on engine body，By uploading and power supply interface，Obtain host computer instruction and power supply，It includes Control card and power supply board，Both utilize PC104 contact pin and PC104 jack to be stacked and be installed in instrument case，Mechanical seal and electrical isolation is realized subsequently by top shrouding and anterior shrouding，After unlatching，Difference according to host computer instruction is operable with under different mode，Receive engine start、Stop or stop command，Can be by being integrated in the numerical control unit control flaps machine controller of described power supply board、Ignition electrode and fuel pump equipment，In equipment runs，It is integrated in the main control unit of described Control card to be converted into by configuration-direct and meet the serial command that Transistor-Transistor Logic level requires，Control simulation output interface，Thus reach to control the purpose of three road accelerator open degrees of electromotor，Utilize the thermal resistance unit being integrated in equally on described Control card、K idol unit、MV unit、MA unit、PWM unit and simulation input interface gather the temperature that electromotor is relevant、Pressure and flow parameter，Utilize equipment interface and RS232 communication protocol，Realize state acquisition and the forwarding of engine powered auxiliary equipment.
- Aero-engine control unit the most according to claim 1, it is characterised in that: it is also integrated with on described power supply board: number electric unit, for external power source being converted into the power supply needed for digit chip；With mould electric unit, it is used for being converted into external power source the power supply needed for analog circuit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521089431.6U CN205450644U (en) | 2015-12-23 | 2015-12-23 | Aircraft engine control ware |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521089431.6U CN205450644U (en) | 2015-12-23 | 2015-12-23 | Aircraft engine control ware |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205450644U true CN205450644U (en) | 2016-08-10 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201521089431.6U Active CN205450644U (en) | 2015-12-23 | 2015-12-23 | Aircraft engine control ware |
Country Status (1)
| Country | Link |
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| CN (1) | CN205450644U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105446226A (en) * | 2015-12-23 | 2016-03-30 | 中国航天空气动力技术研究院 | Aero engine controller |
-
2015
- 2015-12-23 CN CN201521089431.6U patent/CN205450644U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105446226A (en) * | 2015-12-23 | 2016-03-30 | 中国航天空气动力技术研究院 | Aero engine controller |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20170420 Address after: 313216 Zhejiang city of Huzhou province Deqing County Qianyuan town Nanyang Road No. 58 Patentee after: Aerospace Nanyang (Zhejiang) Technology Co., Ltd. Address before: 100074 Beijing, Fengtai District Yungang West Road, No. 17 Patentee before: China Aerospace Aerodynamic Technology Institute |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20170823 Address after: 100074 Beijing, Fengtai District Yungang West Road, No. 17 Patentee after: China Aerospace Aerodynamic Technology Institute Address before: 313216 Zhejiang city of Huzhou province Deqing County Qianyuan town Nanyang Road No. 58 Patentee before: Aerospace Nanyang (Zhejiang) Technology Co., Ltd. |
|
| TR01 | Transfer of patent right |