CN203050894U - Starting control system of aircraft engine - Google Patents
Starting control system of aircraft engine Download PDFInfo
- Publication number
- CN203050894U CN203050894U CN 201320020278 CN201320020278U CN203050894U CN 203050894 U CN203050894 U CN 203050894U CN 201320020278 CN201320020278 CN 201320020278 CN 201320020278 U CN201320020278 U CN 201320020278U CN 203050894 U CN203050894 U CN 203050894U
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- printed board
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- processing circuit
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- connector assembly
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Abstract
The utility model relates to a starting control system of an aircraft engine. The starting control system is characterized in that a transfer printed board is connected with all printed boards through connectors and installed in a chassis, a computer printed board comprises a 1394B processing circuit, a central processing unit (CPU) circuit and an reference standard 422 (RS422) and internet access circuit, an interface printed board is connected with the CPU circuit through a local bus, a discrete magnitude processing circuit is connected with an integrated electronic adjuster, and an analog processing circuit is connected with the engine; a power supply printed board conveys power to each power element; and an output processing printed board is connected with the engine and a CPU circuit power supply. The starting control system takes the integrated circuit to substitute for an electronic circuit of an original starting box and can achieve all control functions of a transmission starting box and complete the analog-digital conversion of partial analog signals in the modern engine.
Description
Technical field
The utility model relates to a kind of control system, especially a kind of airplane engine start control system
Background technique
In the present generation aircraft engine start control system, require starter box not only to want volume little, the life-span is long, when finishing starting control, also to be responsible for the analog-to-digital conversion work of the partial simulation amount of motor, and the signal of aircraft and motor needs is carried out 1394B communication.And conventional airplane engine start control is realized by starter box, and all logic controls of traditional starter box are all finished by the electronic circuit overlap joint that comprises relay, exist volume big, the shortcoming that the life-span is short.
Summary of the invention
The purpose of this utility model provides a kind of airplane engine start control system, and it is little to have a volume, and the characteristics that the life-span is long can realize analog-to-digital conversion work simultaneously, and the signal that aircraft and motor can be needed carry out 1394B communication.
The technical solution of the utility model is: start control system comprises that printed board is handled in computer printed board, interface printed board, power supply printed board, output, transfer printed board, cabinet, described switching printed board connects all printed boards by connector assembly and is installed in the cabinet, the computer printed board comprises 1394B processing circuit, cpu circuit, RS422 and network port circuit, cpu circuit comprises MPC processor and the system logic unit F PGA that communicates by letter by local bus, the pci bus of MPC processor expands 3 road 1394B interfaces, links to each other with the 1394B processing circuit; Expand 2 road RS422 serial ports and 1 road debugging serial interface and link to each other with RS422 and network port circuit, the 1394B processing circuit links to each other with the aircraft computer of outside by connector assembly, and RS422 and network port circuit link to each other with commissioning device; The interface printed board links to each other with cpu circuit by local bus, and the discrete magnitude processing circuit in the interface printed board links to each other with the integrated electronics regulator of outside by connector assembly, and the analog amount processing circuit links to each other with the motor of outside by connector assembly; The power supply printed board is handled printed board by connector assembly and output and is connected, and the accumulator of power supply printed board, 5V voltage transitions processing circuit, 15V voltage transitions processing circuit are used electric device by the switching printed board with power delivery to each; The output processing circuit that printed board is handled in output links to each other with the motor of outside by connector assembly, links to each other with cpu circuit by cable, and power isolation circuit is connected with main electricity, backup battery by connector assembly.
The utility model utilizes intergrated circuit, has replaced the electronic circuit of former starter box, has realized whole control functions of transmission starter box, finished in the novel modernized motor, the analog-to-digital conversion of partial simulation amount signal, simultaneously, all signals have been realized the 1394B digital communication.The advantage that has comprises:
Volume is little, in light weight;
Have memory, memory function, storage capacity is big, the accuracy of timekeeping height;
Carry out the control logic change by rewriting software, avoided former starter box to need again the problem of strap circuits change logic, it is convenient to make control logic change, increase, improve;
Fast operation;
Cancelled the relay in the former starter box, make the starter box life-span long, reliability is high;
In sum, control system is compared with former starter box, has realized new work engine all requirements about control, analog-to-digital conversion, 1394B communication.Possess the characteristics that volume is little, in light weight, the life-span is long, be fit to new work engine and use needs.
Description of drawings
Fig. 1 is connection diagram of the present utility model.
Embodiment
As shown in the figure, start control system comprises computer printed board (A1), interface printed board (A2), power supply printed board (A3), printed board (A4) is handled in output, switching printed board (A5), cabinet, described switching printed board (A5) connects all printed boards by connector assembly and is installed in the cabinet, computer printed board (A1) comprises 1394B processing circuit (A1-1), cpu circuit (A1-2), RS422 and network port circuit (A1-3), cpu circuit (A1-2) comprises MPC processor and the system logic unit F PGA that communicates by letter by local bus, the pci bus of MPC processor expands 3 tunnel 1394 interfaces, and (A1-1) links to each other with the 1394B processing circuit; Expanding 2 road RS422 serial ports and 1 road debugging serial interface links to each other with RS422 and network port circuit (A1-3), 1394 processing circuits (A1-1) link to each other by the aircraft computer (UCP) of connector assembly with the outside, and RS422 and network port circuit (A1-3) link to each other with commissioning device (T); Interface printed board (A2) links to each other with cpu circuit (A1-2) by local bus, discrete magnitude processing circuit (A2-1) in the interface printed board (A2) links to each other by the integrated electronics regulator (ZT) of connector assembly with the outside, and analog amount processing circuit (A2-2) links to each other by the motor (FD) of connector assembly with the outside; Power supply printed board (A3) is handled printed board (A4) by connector assembly and output and is connected, and the accumulator (A3-1) of power supply printed board (A3), 5V voltage transitions processing circuit (A3-2), 15V voltage transitions processing circuit (A3-3) are used electric device by switching printed board (A5) with power delivery to each; The output processing circuit (A4-1) that printed board (A4) is handled in output links to each other by the motor (FD) of connector assembly with the outside, link to each other with cpu circuit (A1-2) by cable, power isolation circuit (A4-2) is connected with main electricity (D1), backup battery (D2) by connector assembly.
The utility model in use, main electricity (D1), backup battery (D2) enter output and handle printed board (A4), after power isolation circuit (A4-2) has guaranteed the power supply quality, enter power supply printed board (A3), in voltage transitions processing circuit (A3-2, A3-3), with 27VDC convert to respectively each module, element required ± 15V DC, 5V DC power supply, offer each element, satisfy the power supply characteristic requirement.
Control system is that starter box has been equipped with backup battery (D2), by accumulator (A3-1), voltage transitions processing circuit (A3-2, A3-3), when guaranteeing the primary power supply dead electricity, starter box has enough power supplys to carry out work, provide control signal to motor, make it proper functioning.
10 tunnel 0～6V DC analog amounts of motor (FD) input starter box, enter interface by connector assembly and handle printed board (A2), analog amount adopts the processing mode of difference input, behind analog amount processing circuit (A2-2), analog amount is converted to digital quantity, cpu circuit (A1-2) in the input computer printed board (A1), CPU reads information by local bus from FPGA, and export to aircraft computer (UCP) after finishing 1394B digital quantity conversion by 1394B processing circuit (A1-1), 54 way switch amount signals of integrated electronics regulator (ZT) input, handle the discrete magnitude processing circuit (A2-1) of printed board (A2) through interface, use optocoupler that the input discrete magnitude is isolated fully herein, after switching value being processed on request the discrete magnitude of Transistor-Transistor Logic level, enter computer printed board (A1).Bottom software analysis in cpu circuit (A1-2), application software logical operation, finish 13 engine condition controls, with 10 tunnel control signals of logic operation result wherein, be sent to the output control and treatment circuit of exporting in the processing printed board (A4) (A4-1) by conjunction cable, in this circuit, utilize optocoupler that out-put supply is isolated.Conducting and the shutoff of field effect transistor are finally controlled in the conducting of optocoupler and shutoff, with the output of control driving power.When control signal when low, diode and field effect transistor conducting, output 27V driving power is given motor, realizes external SC sigmal control; When control signal when being high, diode and field effect transistor turn-off, and do not export the 27V driving power.Simultaneous computer printed board (A1) is converted to corresponding discrete magnitude feedback signal the 1394B digital quantity through 1394B processing circuit (A1-1) analysis and exports to aircraft computer (UCP).
RS422 and network port circuit (A1-3) carry out communication with external debug equipment (T), satisfy the bench test drive needs, finish ground check and system testing function, comprise data checks, program adjustment and control, program input and the outputting communication of debug phase.
Claims (1)
1. airplane engine start control system, it is characterized in that, described starting system comprises computer printed board (A1), interface printed board (A2), power supply printed board (A3), printed board (A4) is handled in output, switching printed board (A5), cabinet, described switching printed board (A5) connects all printed boards by connector assembly and is installed in the cabinet, computer printed board (A1) comprises 1394B processing circuit (A1-1), cpu circuit (A1-2), RS422 and network port circuit (A1-3), cpu circuit (A1-2) comprises MPC processor and the system logic unit F PGA that communicates by letter by local bus, the pci bus of MPC processor expands 3 road 1394B interfaces, and (A1-1) links to each other with the 1394B processing circuit; Expanding 2 road RS422 serial ports and 1 road debugging serial interface links to each other with RS422 and network port circuit (A1-3), 1394B processing circuit (A1-1) links to each other by the aircraft computer (UCP) of connector assembly with the outside, and RS422 and network port circuit (A1-3) link to each other with commissioning device (T); Interface printed board (A2) links to each other with cpu circuit (A1-2) by local bus, discrete magnitude processing circuit (A2-1) in the interface printed board (A2) links to each other by the integrated electronics regulator (ZT) of connector assembly with the outside, and analog amount processing circuit (A2-2) links to each other by the motor (FD) of connector assembly with the outside; Power supply printed board (A3) is handled printed board (A4) by connector assembly and output and is connected, and the accumulator (A3-1) of power supply printed board (A3), 5V voltage transitions processing circuit (A3-2), 15V voltage transitions processing circuit (A3-3) are used electric device by switching printed board (A5) with power delivery to each; The output processing circuit (A4-1) that printed board (A4) is handled in output links to each other by the motor (FD) of connector assembly with the outside, link to each other with cpu circuit (A1-2) by cable, power isolation circuit (A4-2) is connected with main electricity (D1), backup battery (D2) by connector assembly.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320020278 CN203050894U (en) | 2013-01-15 | 2013-01-15 | Starting control system of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320020278 CN203050894U (en) | 2013-01-15 | 2013-01-15 | Starting control system of aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203050894U true CN203050894U (en) | 2013-07-10 |
Family
ID=48733853
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201320020278 Expired - Fee Related CN203050894U (en) | 2013-01-15 | 2013-01-15 | Starting control system of aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203050894U (en) |
-
2013
- 2013-01-15 CN CN 201320020278 patent/CN203050894U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| EE01 | Entry into force of recordation of patent licensing contract |
Assignee: Harbin Dongan electromechanical Manufacturing Co., Ltd. Assignor: Harbin Dongan Engine (Group) Co., Ltd. Contract record no.: 2015230000055 Denomination of utility model: Start control system for aircraft engine Granted publication date: 20130710 License type: Exclusive License Record date: 20150515 |
|
| LICC | Enforcement, change and cancellation of record of contracts on the licence for exploitation of a patent or utility model | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130710 Termination date: 20160115 |
|
| EXPY | Termination of patent right or utility model |