CN104608933B - A kind of engine inertia separator control system and its control method - Google Patents
A kind of engine inertia separator control system and its control method Download PDFInfo
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- CN104608933B CN104608933B CN201510038467.XA CN201510038467A CN104608933B CN 104608933 B CN104608933 B CN 104608933B CN 201510038467 A CN201510038467 A CN 201510038467A CN 104608933 B CN104608933 B CN 104608933B
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- inertia separator
- engine
- engine inertia
- control system
- separator
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Abstract
The invention belongs to airborne motor drive mechanism job control and instruction technology, and in particular to a kind of engine inertia separator control system and control method.Inventive engine inertia separator control system includes two control subsystems in left and right, and each subsystem includes 1 engine inertia separator electric mechanism, 2 control relays, 1 controlling switch and synthetical display control system.The present invention passes through a kind of design of engine inertia separator control system control mode, realize the control to engine inertia rejector motor, and the configured information of engine inertia separator state is integrated into synthetical display control system shown, it is ensured that the crosslinking of indication signal and synthetical display control system.The fault rate of equipment is reduced, maintenance efficiency is improved, man-machine efficacy is improved, and saves instrument panel space, the security of engine inertia separator control system is improved.
Description
Technical field
The invention belongs to engine electrically control technology, and in particular to a kind of engine inertia separator control system and its
Control method.
Background technology
Engine inertia separator control system is to ensure the important system that aircraft is normally run, and its function is to ensure to fly
The normal work of engine inertia piece-rate system on machine, closing and work adjustment engine intake by inertial separation system
Air inflow, the engine inertia separator static indication system used on current aircraft is generally signal lamp prompting, it is necessary to extra
Emergency warning lamp box is made, and use signal lamp adds the fault rate of equipment, and the maintenance to ground crew brings inconvenience, simultaneously
Occupy instrument panel space.
The content of the invention
The purpose of the present invention is：Propose that a kind of configured information by engine inertia separator state is integrated into synthesis display
Control system is shown, it is ensured that indication signal is crosslinked with synthetical display control system, improves the engine inertia separation of man-machine efficacy
Device control system.
In addition, the present invention also provides a kind of engine inertia separator control method.
The technical scheme is that：A kind of engine inertia separator control system, it includes two identicals in left and right
Control subsystem and supply line, each subsystem include 1 engine inertia separator electric mechanism, 2 control relays
Device, 1 controlling switch and synthetical display control system.When left/right engine inertia separator controlling switch gets to " work " position
When putting, the work of left/right engine inertia separator electric mechanism moves to engine inertia piece-rate system behind " work " position
It is stopped, amber warning information is shown in synthetical display control system；When left/right engine inertia separator controlling switch
When getting to " closing " position, the work of left/right engine inertia separator electric mechanism moves to engine inertia piece-rate system
It is stopped behind " closing " position, cyan prompt message is shown in synthetical display control system.
It is an advantage of the invention that：The present invention passes through engine inertia separator Control System Design, realization synthesis display
Control system shows the purpose of engine inertia separator work state.The fault rate of equipment is reduced, maintenance efficiency is improved,
Man-machine efficacy is improved, and saves instrument panel space, the security of engine inertia separator control system is improved.
Brief description of the drawings
Fig. 1 is the principle assumption diagram of inventive engine inertia separator control system；
Fig. 2 is the wiring diagram of inventive engine inertia separator control system；
Wherein, 1- engine inertias piece-rate system controlling switch, 2- engine inertia separator electrics mechanism, 3- inertia point
Indicating relay, 4- inertia separators work indicating relay, 5- synthetical display control systems are closed from device.
Embodiment
The invention will be further described with reference to the accompanying drawings and examples：
Please refer to Fig. 1 and Fig. 2, a kind of aircraft engine inertia separator control system, including the control of left and right two
Subsystem, left control subsystem includes engine inertia piece-rate system controlling switch 1；Engine inertia separator electric mechanism 2；
Inertia separator closes indicating relay 3；Inertia separator work indicating relay 4；Synthetical display control system 5.
Power-supply system extraction wire is connected to 4 ends of engine inertia piece-rate system controlling switch 1, engine inertia separation
3 ends of system control switch 1 are connected to 1 end of engine inertia separator electric mechanism 2, engine inertia separator electric machine
2 ends of structure 2 be connected to inertia separator close indicating relay 33 ends, inertia separator close indicating relay 31 end and
7 ends are grounded, and 6 ends that inertia separator closes indicating relay 3 are connected to synthetical display control system 5.
The 9 ends ground connection of engine inertia separator electric mechanism 2, the 3 ends connection of engine inertia separator electric mechanism 2
To 1 end of engine inertia piece-rate system controlling switch 1,4 ends of engine inertia separator electric mechanism 2 are connected to inertia point
From 3 ends of device work indicating relay 4,1 end of inertia separator work indicating relay 4 and 7 ends ground connection, inertia separator work
6 ends for making indicating relay 4 are connected to synthetical display control system 5.
Right side oil fuel booster pump control principle is identical with left side oil fuel booster pump control principle.
During work：
Engine inertia piece-rate system controlling switch is placed in " work " position, engine inertia separator electric mechanism work
Make, be stopped after engine inertia piece-rate system is moved into " work " position, appearance is shown in synthetical display control system
Amber warning information.
Engine inertia piece-rate system controlling switch is placed in " closing " position, engine inertia separator electric mechanism work
Make, be stopped after engine inertia piece-rate system is moved into " closing " position, appearance is shown in synthetical display control system
Cyan prompt message.
Concrete operation step is as follows：
Power supply on connection machine；
Left Hand Engine inertial separation system control switch 1 is placed in " work " position, Left Hand Engine inertia separator is electronic
Mechanism works, after Left Hand Engine inertial separation system motion to " work " position, Left Hand Engine inertia separator motor drive mechanism 2
Interior microswitch work, 1 end and 2 terminations are logical, and motor drive mechanism 2 is stopped, and inertia separator closes the confession of indicating relay 3
Electric line is connected, and the alarming page of synthetical display control system 5 shows amber " work of Left Hand Engine inertial separation system " word
Curtain；
Left Hand Engine inertial separation system control switch 1 is placed in " closing " position, Left Hand Engine inertia separator is electronic
Mechanism 2 works, after Left Hand Engine inertial separation system motion to " closing " position, Left Hand Engine inertia separator motor drive mechanism
Microswitch work in 2,3 ends and 4 terminations are logical, and motor drive mechanism 2 is stopped, inertia separator work indicating relay 4
Supply line connects, and the alarming page of synthetical display control system 5 shows cyan " closing of Left Hand Engine inertial separation system " word
Curtain.
Right engine inertia piece-rate system operation sequence is identical with Left Hand Engine inertial separation system, and the two is separate,
Aircraft or so two separate engines are controlled respectively.
The present invention is realized used to engine by a kind of design of engine inertia separator control system control mode
The control of property separator electric mechanism, and the configured information of engine inertia separator state is integrated into synthetical display control system
System display, it is ensured that the crosslinking of indication signal and synthetical display control system.The fault rate of equipment is reduced, maintenance effect is improved
Rate, improves man-machine efficacy, and saves instrument panel space, improves the security of engine inertia separator control system.
Claims (5)
1. a kind of engine inertia separator control system, it is characterised in that including the identical control subsystem of left and right two with
And supply line, wherein, the control subsystem includes inertia separator work indicating relay, inertia separator and closes and indicate
Relay, engine inertia separator electric mechanism, inertia separator work indicating relay and inertia separator are closed and referred to
When showing the coil connection of relay, the ground path of absorption connection synthetical display control system, and inertia separator work instruction
The main track that relay, inertia separator close the respective coil of indicating relay is connected respectively to corresponding engine inertia separation
Device motor drive mechanism coil, supply line is connected by busbar by the conducting of breaker through engine inertia piece-rate system controlling switch
It is connected to engine inertia separator electric mechanism.
2. engine inertia separator control system according to claim 1, it is characterised in that engine inertia separator
The limit position of the opening and closing of motor drive mechanism is provided with the microswitch that circuit is opened or closed for cutting off.
3. a kind of control method of the engine inertia separator control system based on described in claim 1, it is characterised in that：
During work：
Engine inertia piece-rate system controlling switch is placed in " work " position, engine inertia separator electric mechanism works,
It is stopped after engine inertia piece-rate system is moved into " work " position, shows and warn in synthetical display control system
Information；
Engine inertia piece-rate system controlling switch is placed in " closing " position, engine inertia separator electric mechanism works,
It is stopped after engine inertia piece-rate system is moved into " closing " position, shows and point out in synthetical display control system
Information.
4. the control method of engine inertia separator control system according to claim 3, it is characterised in that specific behaviour
Make process as follows：
Step 1：Engine inertia piece-rate system moves to operating position
Left Hand Engine inertial separation system control switch is placed in " work " position, Left Hand Engine inertia separator motor drive mechanism work
Make, after Left Hand Engine inertial separation system motion to " work " position, fine motion in Left Hand Engine inertia separator motor drive mechanism
Switch, disconnects the supply line of motor drive mechanism, and motor drive mechanism is stopped, and inertia separator closes the confession of indicating relay
Electric line is connected, and the alarming page of synthetical display control system shows amber " work of Left Hand Engine inertial separation system " word
Curtain；
Step 2：Engine inertia piece-rate system moves to closed position
Left Hand Engine inertial separation system control switch is placed in " closing " position, Left Hand Engine inertia separator motor drive mechanism work
Make, after Left Hand Engine inertial separation system motion to " closing " position, fine motion in Left Hand Engine inertia separator motor drive mechanism
Switch, disconnects the supply line of motor drive mechanism, and motor drive mechanism is stopped, the confession of inertia separator work indicating relay
Electric line is connected, and the alarming page of synthetical display control system shows cyan " closing of Left Hand Engine inertial separation system " captions.
5. the control method of engine inertia separator control system according to claim 4, it is characterised in that start on the right side
Machine inertial separation system operation procedure is identical with Left Hand Engine inertial separation system operation procedure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510038467.XA CN104608933B (en) | 2015-01-26 | 2015-01-26 | A kind of engine inertia separator control system and its control method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510038467.XA CN104608933B (en) | 2015-01-26 | 2015-01-26 | A kind of engine inertia separator control system and its control method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104608933A CN104608933A (en) | 2015-05-13 |
| CN104608933B true CN104608933B (en) | 2017-09-15 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN201510038467.XA Active CN104608933B (en) | 2015-01-26 | 2015-01-26 | A kind of engine inertia separator control system and its control method |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113530857A (en) * | 2021-08-24 | 2021-10-22 | 中国航发湖南动力机械研究所 | Electric driving type sand discharging device for particle separator of aircraft engine |
| CN114360323B (en) * | 2022-01-11 | 2023-11-03 | 安胜（天津）飞行模拟系统有限公司 | Method for simulating engine separation and EGT red box display on flight simulator |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7975465B2 (en) * | 2003-10-27 | 2011-07-12 | United Technologies Corporation | Hybrid engine accessory power system |
| RU2387854C2 (en) * | 2008-04-21 | 2010-04-27 | Открытое акционерное общество "СТАР" | Method to control gas turbine engine fuel system |
| US8720258B2 (en) * | 2012-09-28 | 2014-05-13 | United Technologies Corporation | Model based engine inlet condition estimation |
| CN104118566A (en) * | 2013-04-24 | 2014-10-29 | 哈尔滨飞机工业集团有限责任公司 | Aircraft inertia separator |
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