CN108945487A - FADEC power supply control device for airplane and engine thereof - Google Patents
FADEC power supply control device for airplane and engine thereof Download PDFInfo
- Publication number
- CN108945487A CN108945487A CN201810343817.7A CN201810343817A CN108945487A CN 108945487 A CN108945487 A CN 108945487A CN 201810343817 A CN201810343817 A CN 201810343817A CN 108945487 A CN108945487 A CN 108945487A
- Authority
- CN
- China
- Prior art keywords
- engine
- aircraft
- relay
- power supply
- fadec
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000001514 detection method Methods 0.000 claims abstract description 16
- 238000010304 firing Methods 0.000 claims description 2
- 238000001816 cooling Methods 0.000 description 8
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000009423 ventilation Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D31/00—Power plant control systems; Arrangement of power plant control systems in aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combined Controls Of Internal Combustion Engines (AREA)
- Remote Monitoring And Control Of Power-Distribution Networks (AREA)
Abstract
The invention discloses an airplane and a FADEC power supply control device of an engine of the airplane. The power supply control device comprises a first relay and a second relay, wherein the first relay and the second relay are connected in parallel with each other, two ends of each relay are respectively connected to an engine FADEC and a power supply, the engine FADEC power supply control device further comprises a manual control button for controlling the switch of the first relay, a controller, a signal detection unit and a power-on detection unit, the signal detection unit is used for detecting signals related to the working state of an engine, the power-on detection unit is used for detecting signals related to the initial power-on of an airplane, and the controller controls the switch of the second relay according to the received signals. The invention can realize the power supply control of the engine FADEC by combining manual control and automatic control, can prolong the service life of the engine FADEC, has flexible manual control operation, and can reduce the operation burden of a pilot by automatic control.
Description
Technical field
The present invention relates to aircraft engine FADEC (Full Authority Digital Electronic Control,
Full Authority Digital electronic controller), more particularly to suitable for the power supply control apparatus of aircraft engine FADEC.
Background technique
Aircraft engine FADEC (Full Authority Digital electronic controller) is mounted in engine nacelle, and environment temperature is high, is needed
Equipped with special ventilating and cooling pipeline, enters ram-air using ventilation cooling tube pass and cool down.But in the static shape of aircraft
When state and inoperative engine, the cooling air-flow in nacelle air pipeline is insufficient, especially when engine just stops, engine
Temperature backheat rises in nacelle, and engine FADEC environment temperature steeply rises, and engine FADEC is under high temperature environment for a long time
Work will substantially reduce its service life, or even FADEC is caused to damage.This considerably increases the operation costs of airline.
It is traditional solve the excessively high mode of engine FADEC temperature mainly include the following types: 1, in nacelle air pipeline
Increase electronic cooling fan, when engine is inoperative, cooling fan continuous running increases nacelle ventilating and cooling air-flow, reduces
Temperature in nacelle.Program needs increase electronic cooling fan in nacelle air pipeline, increase to nacelle air pipeline arrangement
Difficulty, also increases aircraft weight, increases the electric quantity consumption of aircraft battery, the program is generally only applicable to large aircraft；
2, increase FADEC power supply hand control switch in aircraft cockpit, FADEC power supply and power-off are controlled by pilot, to contract as far as possible
The short FADEC unnecessary working time, inner heat when reducing FADEC work, to extend the FADEC service life, but the control mode
Increase the operating burden of pilot.
Summary of the invention
The technical problem to be solved by the present invention is to the solutions in order to overcome engine FADEC temperature in the prior art excessively high
Scheme needs to increase the operating burden of pilot or is the difficult defect for increasing nacelle air pipeline arrangement, proposes one kind
Aircraft and its engine FADEC power supply control apparatus.
The present invention is to solve above-mentioned technical problem by following technical proposals:
The present invention provides a kind of engine FADEC power supply control apparatus of aircraft, it is characterized in that comprising first after
Electric appliance and the second relay, the first relay and the second relay are connected in parallel to each other and respective both ends are respectively connected to engine
FADEC and power supply, the engine FADEC power supply control apparatus further include the manual control for controlling the switch of the first relay
Button processed；
The engine FADEC power supply control apparatus further includes controller, detecting signal unit and powers on detection unit,
Described in detecting signal unit for detecting associated with engine behavior signal and sending it to the controller,
It is described power on detection unit for detect associated with aircraft initial power-on signal and send it to the controller, it is described
Controller is according to the associated signal of described and engine behavior that receives and described associated with aircraft initial power-on
Signal control the second relay switch.
Preferably, the signal associated with engine behavior include engine start switch switching signal,
The switching signal of engine ignition switch, the signal associated with aircraft initial power-on include aircraft initial power-on detection letter
Number, aircraft wheel information carrying number.
Preferably, the controller is configured to, the condition of control the second relay closure is appointing in following four condition
Meaning one is met: engine start switch is in driving position；Engine ignition switch is closure position；Aircraft initial power-on
Duration is less than preset first duration threshold value；Aircraft wheel information carrying display aircraft is in aerial；
The controller is additionally configured to, and the condition that the second relay of control is opened is while meeting following four condition: hair
Engine start duration of the switch in position of cut-offfing is greater than preset second duration threshold value；Engine ignition switch, which is in, to be opened
The duration of position is greater than preset third duration threshold value；The duration of aircraft initial power-on is greater than the first duration threshold value；Fly
Wheel information carrying display aircraft is in ground.
Preferably, the controller, the detecting signal unit and the electronics for powering on detection unit and being installed on aircraft
In equipment compartment.
Preferably, the manual control button and the first relay are installed in the cockpit of aircraft, and described manual
Control button has the indicator light for showing the first relay switch state.
The present invention also provides a kind of aircrafts including engine FADEC power supply control apparatus as described above.
On the basis of common knowledge of the art, above-mentioned each optimum condition, can any combination to get each preferable reality of the present invention
Example.
The positive effect of the present invention is that:
Aircraft and its engine FADEC power supply control apparatus of the invention is mutually tied, it can be achieved that manually controlling with automatic control
The engine FADEC power supply control of conjunction, manual control operation is flexible, can be used for aircraft condition inspection or maintenance, and automatically controls
It can be used for aircraft normal operation, be not necessarily to pilot operator and intervention, mitigate pilot operator burden, extending engine FADEC makes
Use the service life.
Detailed description of the invention
Fig. 1 is a preferred embodiment of the present invention the schematic diagram of the engine FADEC power supply control apparatus of aircraft.
Fig. 2 is a preferred embodiment of the present invention the control of the controller in the engine FADEC power supply control apparatus of aircraft
Logical schematic processed.
Specific embodiment
With reference to the accompanying drawings of the specification, further the preferred embodiment of the present invention is described in detail, description below
To be illustrative, not limitation of the present invention, any other similar situation are still fallen among protection scope of the present invention.
In specific descriptions below, the term of directionality, such as "left", "right", "upper", "lower", "front", "rear", etc.,
The direction with reference to described in attached drawing uses.The component of the embodiment of the present invention can be placed in a variety of different directions, directionality
Term is for illustrative purposes and not restrictive.
Refering to what is shown in Fig. 1, the engine FADEC power supply control apparatus of the aircraft of a preferred embodiment according to the present invention,
Including manually controlling power pack and automatically controlling power pack.Power pack is manually controlled to include the first relay 1 and be used for
Control the button 3 of the switch of the first relay 1.It can be with for showing the instruction of 1 switch state of the first relay on button 3
Lamp.
Power pack is automatically controlled to include the second relay 2, controller, detecting signal unit and power on detection unit.The
One relay 1 and the second relay 2 are connected in parallel to each other and respective both ends are respectively connected to engine FADEC and power supply.It is described
Detecting signal unit for detecting associated with engine behavior signal and sending it to the controller, it is described on
Electro-detection unit is for detecting signal associated with aircraft initial power-on and sending it to the controller, the controller
The signal associated with engine behavior according to receiving and the signal associated with aircraft initial power-on
Control the switch of the second relay 2.Preferably, it controller, detecting signal unit and powers on detection unit and can be integrated in a control
In box 4 processed.
Some preferred embodiments according to the present invention, the signal associated with engine behavior include starting
Switching signal, the switching signal of engine ignition switch of machine firing switch, the signal associated with aircraft initial power-on
Signal, aircraft wheel information carrying number are detected including aircraft initial power-on.Refering to what is shown in Fig. 2, controller controls the switch of the second relay 2
Control logic, that is, automatically control power pack power on and power-down logic is as follows:
When any one in following four condition obtains meeting, controller is closed the second relay 2, and this four
Condition are as follows: engine start switch is in driving position, engine ignition switch is the duration for being closed position, aircraft initial power-on
It is in aerial less than preset first duration threshold value (T1), aircraft wheel information carrying display aircraft；
When following four condition obtains meeting simultaneously, controller opens the second relay 2, four conditions are as follows:
The duration that engine start switch is in position of cut-offfing is greater than preset second duration threshold value (T2), at engine ignition switch
When the duration of open position being greater than first greater than the duration of preset third duration threshold value (T3), aircraft initial power-on
Long threshold value, aircraft wheel information carrying display aircraft are in ground.
Some preferred embodiments according to the present invention, the controller, the detecting signal unit and the upper electric-examination
It surveys unit to be installed in the electronics bay of aircraft, the ventilating and cooling environment of electronics bay is preferable, thus facilitates engine
FADEC is not overheated.The manual control button 3 and the first relay 1 are installed in the cockpit of aircraft.
Although specific embodiments of the present invention have been described above, it will be appreciated by those of skill in the art that these
It is merely illustrative of, protection scope of the present invention is defined by the appended claims.Those skilled in the art is not carrying on the back
Under the premise of from the principle and substance of the present invention, many changes and modifications may be made, but these are changed
Protection scope of the present invention is each fallen with modification.
Claims (6)
1. a kind of engine FADEC power supply control apparatus of aircraft, which is characterized in that it includes the first relay and the second relay
Device, the first relay and the second relay are connected in parallel to each other and respective both ends are respectively connected to engine FADEC and power supply, institute
Stating engine FADEC power supply control apparatus further includes the manual control button for controlling the switch of the first relay；
The engine FADEC power supply control apparatus further includes controller, detecting signal unit and powers on detection unit, wherein institute
State detecting signal unit for detect associated with engine behavior signal and send it to the controller, it is described
Power on detection unit for detect associated with aircraft initial power-on signal and send it to the controller, the control
Device is according to the associated signal of the described and engine behavior received and the letter associated with aircraft initial power-on
Number according to preset control logic control the second relay switch.
2. engine FADEC power supply control apparatus as described in claim 1, which is characterized in that described and engine operation shape
The associated signal of state includes the switching signal of engine start switch, the switching signal of engine ignition switch, it is described with it is winged
The associated signal of machine initial power-on includes aircraft initial power-on detection signal, aircraft wheel information carrying number.
3. engine FADEC power supply control apparatus as described in claim 1, which is characterized in that the controller is configured to, control
The condition for making the second relay closure is met for any one in following four condition: engine start switch is in and opens
Parking stall；Engine ignition switch is closure position；The duration of aircraft initial power-on is less than preset first duration threshold value；Aircraft
Wheel load signal shows that aircraft is in aerial；
The controller is additionally configured to, and the condition that the second relay of control is opened is while meeting following four condition: engine
The duration that firing switch is in position of cut-offfing is greater than preset second duration threshold value；Engine ignition switch is in open position
Duration is greater than preset third duration threshold value；The duration of aircraft initial power-on is greater than the first duration threshold value；Aircraft wheel
Information carrying display aircraft is in ground.
4. engine FADEC power supply control apparatus as described in claim 1, which is characterized in that the controller, the signal
Detection unit and the detection unit that powers on are installed in the electronics bay of aircraft.
5. engine FADEC power supply control apparatus as described in claim 1, which is characterized in that the manual control button and
First relay is installed in the cockpit of aircraft, and the manual control button has for showing the first relay switch
The indicator light of state.
6. a kind of includes the aircraft of the engine FADEC power supply control apparatus as described in any one of claim 1-5.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810343817.7A CN108945487B (en) | 2018-04-17 | 2018-04-17 | FADEC power supply control device for airplane and engine thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810343817.7A CN108945487B (en) | 2018-04-17 | 2018-04-17 | FADEC power supply control device for airplane and engine thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108945487A true CN108945487A (en) | 2018-12-07 |
| CN108945487B CN108945487B (en) | 2021-10-29 |
Family
ID=64499008
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810343817.7A Active CN108945487B (en) | 2018-04-17 | 2018-04-17 | FADEC power supply control device for airplane and engine thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108945487B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111645867A (en) * | 2020-05-27 | 2020-09-11 | 中国航空工业集团公司西安航空计算技术研究所 | Electronic controller power management system and method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN85205357U (en) * | 1985-12-09 | 1987-07-08 | 廖德 | Starting controller with trouble alarm |
| FR2989125A1 (en) * | 2012-04-10 | 2013-10-11 | Bosch Gmbh Robert | AUTOMOTIVE VEHICLE STARTER DEVICE |
| CN105888849A (en) * | 2016-04-06 | 2016-08-24 | 中国南方航空工业(集团)有限公司 | Bleed air cooling structure and aeroengine with bleed air cooling structure |
| CN106314159A (en) * | 2016-08-31 | 2017-01-11 | 北京新能源汽车股份有限公司 | Relay control method and device and automobile |
| CN206627904U (en) * | 2017-03-29 | 2017-11-10 | 浙江工业职业技术学院 | A kind of self-checking system for computer |
| US9849996B2 (en) * | 2014-02-11 | 2017-12-26 | Sikorsky Aircraft Corporation | Engine electrical load shed control |
-
2018
- 2018-04-17 CN CN201810343817.7A patent/CN108945487B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN85205357U (en) * | 1985-12-09 | 1987-07-08 | 廖德 | Starting controller with trouble alarm |
| FR2989125A1 (en) * | 2012-04-10 | 2013-10-11 | Bosch Gmbh Robert | AUTOMOTIVE VEHICLE STARTER DEVICE |
| US9849996B2 (en) * | 2014-02-11 | 2017-12-26 | Sikorsky Aircraft Corporation | Engine electrical load shed control |
| CN105888849A (en) * | 2016-04-06 | 2016-08-24 | 中国南方航空工业(集团)有限公司 | Bleed air cooling structure and aeroengine with bleed air cooling structure |
| CN106314159A (en) * | 2016-08-31 | 2017-01-11 | 北京新能源汽车股份有限公司 | Relay control method and device and automobile |
| CN206627904U (en) * | 2017-03-29 | 2017-11-10 | 浙江工业职业技术学院 | A kind of self-checking system for computer |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111645867A (en) * | 2020-05-27 | 2020-09-11 | 中国航空工业集团公司西安航空计算技术研究所 | Electronic controller power management system and method |
| CN111645867B (en) * | 2020-05-27 | 2023-05-09 | 中国航空工业集团公司西安航空计算技术研究所 | Electronic controller power management system and method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108945487B (en) | 2021-10-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA2856547C (en) | Automatic control systems for aircraft auxiliary power units, and associated methods | |
| EP2862803B1 (en) | Pneumatic system for an aircraft | |
| US10299343B2 (en) | Exterior aircraft light unit and method of disabling a light output of an exterior aircraft light unit | |
| US8707721B2 (en) | Ram air based cooling and ventilation system for an aircraft | |
| US20110036950A1 (en) | De-icing and/or anti-icing system for the leading edge of an aircraft wing | |
| EP2697119B1 (en) | System for delivering pre-conditioned air to an aircraft on the ground | |
| CN108312861A (en) | A kind of unmanned plane and its battery temperature control and method | |
| EP3162705A1 (en) | Hand-launched unmanned aerial vehicle | |
| CN109305148A (en) | Aircraft airborne brake air cooler control system based on temperature and its design method | |
| US2652216A (en) | Aircraft structure cooling means | |
| JP7339787B2 (en) | Multi-mode generator for aircraft de-icing | |
| CN110040254A (en) | Vehicles air-conditioning sub-assembly with air circulation component | |
| CN105977895A (en) | Ice melting device and method for electric transmission and distribution circuit in winter | |
| CN108945487A (en) | FADEC power supply control device for airplane and engine thereof | |
| CN103249643B (en) | There is the aircraft environment control system of modulated low-temperature receiver | |
| EP3118459B1 (en) | Ram air fan assembly with surge detection | |
| CN110203404A (en) | Heating control device of airplane atmospheric data system | |
| JP2018001814A (en) | Parachute and aircraft with parachute system | |
| CN109869869A (en) | Heating control method for chassis of air conditioner external unit | |
| US6786279B2 (en) | Forward in flight (IFE) entertainment cooling system | |
| CN204821482U (en) | Anti -icing defogging system of hybrid aircraft windscreen | |
| CN203732250U (en) | Instrument used for test control of aircraft air-conditioning system component | |
| CN114326866B (en) | Heating control method of airborne atmospheric data sensor | |
| CN207985214U (en) | Atmosphere control system for aircraft | |
| GB817975A (en) | An air conditioning system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |