CN105446226A

CN105446226A - Aero engine controller

Info

Publication number: CN105446226A
Application number: CN201510981758.2A
Authority: CN
Inventors: 沙群; 嵇治刚; 牛志朝; 王超; 丛晖; 梁凤麒
Original assignee: China Academy of Aerospace Aerodynamics CAAA
Current assignee: China Academy of Aerospace Aerodynamics CAAA
Priority date: 2015-12-23
Filing date: 2015-12-23
Publication date: 2016-03-30

Abstract

The invention discloses an aero engine controller. The aero engine controller comprises a control card board and a power source card board; by means of PC104 pins and PC104 jacks, the control card board and the power source card board are stacked together and are installed together in a meter box; mechanical seal and electrical isolation are realized through an upper seal plate and a front seal plate; equipment such as an steering engine controller, an ignition needle and a fuel pump can be controlled through a numerical control unit which is integrated on the power source card board; a main control unit integrated on the control card board converts configuration instructions into serial instructions satisfying TTL electric level requirements, and controls an analog output interface, so as to control the opening degrees of three throttles of an engine; and the related temperature, pressure and flow parameters of the engine are acquired through a thermal resistance unit, a K type thermocouple unit, an mV unit, an mA unit, a PWM unit and an analog input interface which are integrated on the control card board. The aero engine controller integrates a control function and a monitoring function and can monitor a plurality of groups of data simultaneously.

Description

Aero-engine control unit

Technical field

The present invention relates to a kind of aero-engine control unit, particularly relate to a kind of piston aviation engine controller.

Background technology

Piston aviation engine is widely used in small-sized giro, recently along with the develop rapidly of unmanned plane, piston aviation engine is also more and more equipped in unmanned plane, this makes the control mode of in the past carrying out controlling with instrument more and more be not suitable with news, piston aviation engine comprises electrically and oil circuit two parts, existing controller is also divided into electric controller and oil circuit controller two parts accordingly, which increase the complexity of Control system architecture, in order to ensure the flight safety of piston aviation engine, need the temperature of Real-Time Monitoring engine, the parameter such as pressure and flow, this needs extra configuration engine monitoring means, carry out data acquisition and the forwarding of respective sensor and status monitor, in sum, the settling mode of existing aeroengine control system, unimodule is main composition proposal in a distributed manner, it is high that the program has complexity, the deficiency that the many and measurement and control unit of peripheral auxiliary quantity is separated.

Summary of the invention

The invention provides a kind of aero-engine control unit, this controller achieves igniting and the power supply control of engine, and pass through the oil circuit control of the control realization to fuel pump, in addition, the status monitoring of engine is achieved by sensor conversion circuit, utilize RS232 serial ports to achieve the status monitoring of engine powered auxiliary equipment, really to achieve electrically and oil circuit is integrated and control and the design proposal of monitoring integration.

Aero-engine control unit of the present invention is secured by bolts on engine body, by uploading and power supply interface, obtain host computer instruction and power supply, it comprises Control card and power supply board, both utilize PC104 contact pin and PC104 jack to be stacked to be installed in instrument case, mechanical seal and electrical isolation is realized subsequently by top shrouding and anterior shrouding, after unlatching, under can different mode being worked according to the difference of host computer instruction, receive engine start, stop or stop command, by being integrated in the numerical control unit control flaps machine controller of described power supply board, the equipment such as ignition electrode and fuel pump, in equipment runs, configuration-direct is converted into the serial command meeting Transistor-Transistor Logic level and require by the main control unit being integrated in described Control card, control simulation output interface, thus reach the object of the three road accelerator open degrees controlling engine, utilize the thermal resistance unit be integrated in equally on described Control card, the even unit of K, mV unit, mA unit, PWM unit and analog input interface gather the relevant temperature of engine, pressure and flow parameter, utilize equipment interface and RS232 communication protocol, realize state acquisition and the forwarding of engine powered auxiliary equipment.

Preferred described power supply board is also integrated with: 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 mimic channel by external power source.

The invention has the beneficial effects as follows:

1. the electrical control and the oil circuit that collect engine are controlled in one, and ad hoc have data cell to carry out the power supply of corresponding engine powered auxiliary equipment and the control of duty.

2. integrate the control of engine and monitor, the control of engine is carried out by data cell and modulating output interface, realized the collection of temperature, pressure and the flow parameter that engine is correlated with by sensor conversion circuit, and utilize equipment interface to realize state acquisition and the forwarding of engine powered auxiliary equipment.

3. picking rate can reach 1kHz, and has real-time hold function, utilizes modified Newton iteration method and ten grades of polynomial expressions to resolve, achieves resistance and temperature precision and be ± 0.2 DEG C, and the even temperature of K is ± 1 DEG C.

Accompanying drawing explanation

Fig. 1 is structural drawing of the present invention.

Fig. 2 is Control card structural drawing.

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 supply unit, 8. uploads and power supply interface, 9. equipment interface, 10. modulating output interface, 11. thermal resistance unit, the even unit of 12.K, 13. analog input interfaces, 14.PWM unit, 15.mA unit, 16.mV unit, 17. number deposit receipt units, 18.PC104 contact pin, 19. number electric units, 20. mould electric units, 21. numerical control units, 22.PC104 jack

Embodiment

Below in conjunction with accompanying drawing, the present invention is described in more detail.

The present invention includes top shrouding 1, instrument case 2, Control card 3, power supply board 4, anterior shrouding 5, main control unit 6, power supply unit 7, upload and power supply interface 8, equipment interface 9, modulating output interface 10, thermal resistance unit 11, the even unit 12 of K, analog input interface 13, PWM unit 14, mA unit 15, mV unit 16, number deposit receipt unit 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 and power supply board 4 are stacked by PC104 contact pin and PC104 jack, and are secured by bolts in instrument case, carry out mechanical seal and electrical isolation subsequently by top shrouding 1 and anterior shrouding 5.

In fig. 2, main control unit 6 carries out process and the aftertreatment of steering order parsing and image data, by thermal resistance unit 11, the even unit 12 of K, analog input interface 13, PWM unit 14, mA unit 15 and mV unit 16 carries 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 deposit receipt unit 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 mimic channel by mould electric unit 20, is received the control signal of Control card 3, and control engine powered auxiliary equipment by numerical control unit 21 by stacking jointing holes 22.

In collection and preservation, the picking rate of 1kHz can be realized, and utilize number deposit receipt unit to carry out the real-time preservation of data, the unary biquadratic equation adopting 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, adopt ten grades of polynomial expressions to realize the linear fit of the even temperature of K, compared to traditional look-up table, the acquisition precision of K idol is brought up to ± 1 DEG C.

Claims

1. 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 comprises Control card and power supply board, both utilize PC104 contact pin and PC104 jack to be stacked to be installed in instrument case, mechanical seal and electrical isolation is realized subsequently by top shrouding and anterior shrouding, after unlatching, under can different mode being worked according to the difference of host computer instruction, receive engine start, stop or stop command, by being integrated in the numerical control unit control flaps machine controller of described power supply board, the equipment such as ignition electrode and fuel pump, in equipment runs, configuration-direct is converted into the serial command meeting Transistor-Transistor Logic level and require by the main control unit being integrated in described Control card, control simulation output interface, thus reach the object of the three road accelerator open degrees controlling engine, utilize the thermal resistance unit be integrated in equally on described Control card, the even unit of K, mV unit, mA unit, PWM unit and analog input interface gather the relevant temperature of engine, pressure and flow parameter, utilize equipment interface and RS232 communication protocol, realize state acquisition and the forwarding of engine powered auxiliary equipment.

2. aero-engine control unit according to claim 1, is characterized in that: described power supply board is also integrated with: number electric unit, for external power source being converted into the power supply needed for digit chip; With mould electric unit, for external power source being converted into the power supply needed for mimic channel.