CN106741863B - The high-lift system of aircraft - Google Patents
The high-lift system of aircraft Download PDFInfo
- Publication number
- CN106741863B CN106741863B CN201611012555.3A CN201611012555A CN106741863B CN 106741863 B CN106741863 B CN 106741863B CN 201611012555 A CN201611012555 A CN 201611012555A CN 106741863 B CN106741863 B CN 106741863B
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- CN
- China
- Prior art keywords
- aircraft
- slat
- electric
- electric notor
- lift system
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- 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.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/12—Adjustable control surfaces or members, e.g. rudders surfaces of different type or function being simultaneously adjusted
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D25/00—Emergency apparatus or devices, not otherwise provided for
Abstract
The invention discloses a kind of high-lift systems of aircraft.High-lift system of the invention, including mixed dynamic PDU, MDE and SFCC, MDE drives the movement of the wing flap and/or slat of aircraft according to the mixed dynamic PDU of instruction control of SFCC, hydraulic motor and electric notor in mixed dynamic PDU are connected to the wing flap and/or slat of aircraft via the transmission mechanism of arrangement of clutch and aircraft wing respectively, the two is connected via differential integrated gear case, electric notor receives the power supply of aircraft power grid when running with electric motor mode, MDE is also used in the stand-by power supply instruction for receiving SFCC sending, control hydraulic motor is run as prime mover driven electric notor with generator mode, it is powered.The present invention can generate enough redundant powers independently of the other systems of aircraft, to not depend on aircraft power grid in the case where aircraft needs emergency service and realize the power supply to all electrical equipments inside high-lift system.
Description
Technical field
The present invention relates to aircraft circles more particularly to a kind of high-lift systems of aircraft.
Background technique
The high-lift system of modern large aircraft includes the wing flap positioned at the slat of the leading edge of a wing and positioned at trailing edge.
It the low-speed stages such as taking off, landing by the protruding of leading edge slat and trailing edge flap, be bent downwardly increase airfoil
Product changes configuration to provide airplane ascensional force, to guarantee the takeoff speed of the reasonable ground run distance of aircraft and safety, while improving and flying
The machine climb rate, approach speed and approach attitude.
The drive manner of modern large aircraft high-lift system is usually detecting behaviour by flap slat computer (SFCC)
After control signal after inter-process parses, then issues command signal and give Motorized drive unit (PDU).PDU exports rotation torque,
It is transferred to rotary teeth wheel actuator by the movement of the drive lines component such as torque tube, bearing spider, and then drives wing flap, slat
Control surface movement.The position signal of control surface is fed back to SFCC by the position sensor positioned at wing tip.When SFCC receives table
It after levying the sensor signal that control surface reaches designated position, issues command signal and PDU is allowed to stop output torque, and issue instruction letter
Number wing tip brake gear is given, locking transmission and then makes control surface be maintained at designated position at linear system.
PDU in aircraft provides driving power for high-lift system, and PDU includes at least a hydraulic horse under normal circumstances
Reach, positioned at aircraft fuselage central location and be connected to transmission linear system, transmission linear system machine power is provided in wing flap again
Or the rotary teeth wheel actuator on slat control surface erect-position.For example, the aircraft of the A380/350 model of current Air Passenger company, seam
The PDU of wing system includes a hydraulic motor and an electric motor.
Aircraft will use ram-air turbine driven generator or hydraulic pump in the case where all power failures,
It is only and the important system or equipment offer energy for guaranteeing aircraft continuation safe flight and landing floor level, such as master is flown
Control system, the control electronics of undercarriage and high-lift system and actuator etc..It is limited by aircraft weight volume, generator
Or hydraulic pump is only capable of providing lesser power, under this powering mode, above system and equipment can keep normal function,
But performance has certain decline.For high-lift system, for the normal function for keeping wing flap and slat, wing flap and seam
At most a hydraulic motor or electric notor in wing PDU can work, and guarantee that control surface can be put down, and speed slows down.
Since the wing flap and slat control surface of high-lift system are only used in aircraft into close and landing period, and it is above-mentioned two
The duration in stage is significantly shorter than the duration of cruising phase.For the configuration of the high-lift system of existing aircraft,
If the aircraft cruise time is too long, and high-lift system occupies a large amount of electric power, then reduces the efficiency of using energy source.And
And, it is contemplated that hydraulic pump does not ensure that all loads all obtain sufficient flow, therefore would generally set in existing aircraft
Prioritizing valve is set, preferential to guarantee aileron actuator, elevator actuator, rudder actuator are required with undercarriage actuator
Flow, and high-lift system PDU is usually arranged on behind pressure-gradient control valve.Therefore, if patrolled under the conditions of all power failures
ETS estimated time of sailing is too long, and wing flap and slat will have great probability to cannot get enough flows, causes slat and wing flap that can not put down, or
Wing flap can not be put down.Therefore, the energy source configuration mode on aircraft at present, cause high-lift system for the energy utilization efficiency compared with
Low, especially in the case where aircraft needs emergency service, the energy of high-lift system cannot be efficiently used.
Summary of the invention
The technical problem to be solved by the present invention is to the energy benefits in order to overcome the high-lift system of aircraft in the prior art
Defect lower with efficiency, cannot efficiently using in the case where needing emergency service proposes a kind of high-lift system of aircraft
System.
The present invention is to solve above-mentioned technical problem by following technical proposals:
The present invention provides a kind of high-lift systems of aircraft, it is characterized in that comprising mixed dynamic PDU, MDE (i.e. motor
Drive electronic control unit) and SFCC, the MDE according to the instruction of the SFCC control mixed PDU that moves to drive aircraft
The movement of wing flap and/or slat, wherein the mixed dynamic PDU includes differential integrated gear case, hydraulic motor and electric notor, described
Hydraulic motor and the electric notor respectively via the transmission mechanism of arrangement of clutch and aircraft wing be connected to aircraft wing flap and/or
Slat, the hydraulic motor and the electric notor are connected via the differential integrated gear case, and the electric notor is via the MDE
It is connected to aircraft power grid, and the electric notor receives the power supply of aircraft power grid when running with electric motor mode, the MDE is also
For when receiving the stand-by power supply instruction that the SFCC is issued, the brake for detecting the hydraulic motor and the electric notor to be
It is no to be in on-position, and will be described hydraulic by the arrangement of clutch in the case where the brake is in on-position
Motor and the electric notor are separated with the transmission mechanism, then control the hydraulic motor as prime mover via the differential
Integrated gear case drives the electric notor to run with generator mode, and passes through the MDE to the SFCC and/or the flap of aircraft
The power supply of the electric wing tip brake gear of the wing and/or slat.
Preferably, whether the electric wing tip brake gear of wing flap and/or slat that the SFCC is also used to detect aircraft is in
On-position, and the stand-by power supply instruction is issued when the electric wing tip brake gear is in on-position.
Preferably, the electric wing tip brake gear that the SFCC is also used to detect the slat of aircraft whether be in on-position,
Whether slat is in fully retracted position and whether the ram-air turbine of aircraft is in down state, and in the electric wing of slat
Institute is issued when sharp brake gear is in on-position, slat is in fully retracted position and ram-air turbine is in down state
State stand-by power supply instruction.
Preferably, also being powered by the MDE to aircraft power grid when the electric notor is run with generator mode.
Preferably, the MDE is provided with transformer, the transformer is used to the voltage of aircraft power grid being converted to the electricity
The operating voltage of motor and the electricity that the electric notor is converted to aircraft power grid with the exported voltage of generator mode operation
Pressure.
Preferably, the transformer is for running the voltage of aircraft power grid and/or the electric notor with generator mode
The voltage exported is converted to the operating voltage of the SFCC and the operating voltage of the electric wing tip brake gear.
Preferably, the differential integrated gear case includes planetary gear set and cylinder gear speed reducer, the hydraulic horse
The output shaft reached is connected to the rotor of the electric notor via the planetary gear set and the cylinder gear speed reducer, thus
It drives the rotor of the electric notor to rotate by the hydraulic motor and generates exciting current.
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:
The high-lift system of aircraft of the invention can efficiently use the movement of the flap slat of mixed dynamic PDU driving aircraft, also
Enough redundant powers can be generated independently of the other systems of aircraft, to drive in the case where aircraft needs emergency service
Electric notor in dynamic PDU switchs to generator mode, so that not depending on aircraft power grid can be achieved with to high-lift system inside
All electrical equipments power supply, including the independent driving for realizing Chinese-style jacket with buttons down the front slat control surface, without passing through electricity by aircraft power grid
Busbar power supply, additionally it is possible to provide stand-by power source in the case where aircraft enters cruising phase if necessary for aircraft.
Detailed description of the invention
Fig. 1 is a preferred embodiment of the present invention the schematic diagram of the high-lift system of aircraft.
Fig. 2 is a preferred embodiment of the present invention inside of the high-lift system of aircraft in the state of enabling stand-by power supply
One exemplary schematic diagram of electric network configuration.
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 high-lift system of the aircraft of a preferred embodiment includes mixed dynamic PDU1, motor according to the present invention
Control electronic device 2 (i.e. MDE) and SFCC3, MDE2 driven according to the mixed dynamic PDU1 of instruction control of SFCC3 aircraft wing flap or
The movement of slat.Wherein, mixing dynamic PDU1 includes differential integrated gear case 12, hydraulic motor 11 and electric notor 13, hydraulic motor 11
It is connected to the wing flap or slat of aircraft, hydraulic horse via the transmission mechanism 4 of arrangement of clutch 5 and aircraft wing respectively with electric notor 13
It is connected up to 11 with electric notor 13 via differential integrated gear case 12, electric notor 13 is connected to aircraft power grid, and electricity via MDE2
Motor 13 receives the power supply of aircraft power grid when running with electric motor mode, and MDE2 is also used to receiving the spare of SFCC3 sending
When power supply instruction, whether the brake for detecting hydraulic motor 11 and electric notor 13 is in on-position, and is in brake
Hydraulic motor 11 and electric notor 13 are separated by arrangement of clutch 5 with transmission mechanism 4 in the case where on-position, then control liquid
Pressure motor 11 drives electric notor 13 to run with generator mode as prime mover via differential integrated gear case 12, and passes through MDE2
Electric wing tip brake gear 6 (i.e. WTB) power supply to the wing flap or slat of SFCC3 and aircraft.High-lift system further includes torque
Limiter 14 provides necessary protection for mixed dynamic PDU1.
Typically, MDE2 is provided with multiple transformers, and as needed, each transformer can be respectively configured as aircraft power grid
Voltage and electric notor 13 run that exported voltage is converted to the operating voltage of SFCC3 and electric wing tip brakes with generator mode
The operating voltage of device 6, and by the voltage of aircraft power grid be converted to electric notor 13 operating voltage and by electric notor 13 with
Generator mode runs the voltage that exported voltage is converted to aircraft power grid.
In some exemplary embodiment, SFCC3 is also used to detect the wing flap of aircraft and/or the electric wing tip brake dress of slat
6 are set whether in on-position, and issues stand-by power supply instruction when electric wing tip brake gear 6 is in on-position, alternatively,
Whether the electric wing tip brake gear 6 that SFCC3 is also used to detect the slat of aircraft is in on-position, whether slat is in complete receipts
Return is set and whether the ram-air turbine of aircraft is in down state, and is in system in the electric wing tip brake gear 6 of slat
Stand-by power supply instruction is issued when dynamic state, slat are in fully retracted position and ram-air turbine is in down state.
MDE2, can be by arrangement of clutch 5 by electric notor 13 and hydraulic motor after the stand-by power supply instruction for receiving SFCC3
11 completely from system separate, i.e., be located at two sides wing transmission mechanism 4 component (e.g., including torque tube and various shapes
The components such as the connecting support seat of formula) it is completely disengaged.After disengagement, torque is no longer transferred to transmission by electric notor 13 and hydraulic motor 11
Mechanism 4.
After separating in system, electric notor 13 can be run with generator mode, and hydraulic motor 11 is by hydraulic energy source
Driving, and drive electric notor 13 to generate electricity by the gear train of differential integrated gear case 12.Specifically, differential integrated gear case 12
It may include planetary gear set and cylinder gear speed reducer, the output shaft of hydraulic motor 11 is via planetary gear set and Cylinder Gear
Wheel decelerator is connected to the rotor of electric notor 13, to drive the rotor rotation of electric notor 13 to generate excitation by hydraulic motor 11
Electric current.
In some typical embodiments of the invention, differential integrated gear case may include two sun gears and two pairs of rows
Star-wheel.Two sun gears are connected with the output shaft of hydraulic motor and motor respectively.Two planetary gears are identical.Two sun
Wheel is respectively engaged with one of planetary gear, and is intermeshed between two planetary gears, to pass through gear train for hydraulic horse
The power output reached to electric notor rotor, and then generate exciting current make electric notor as generator work.
It will be appreciated by those skilled in the art that the structure of brshless DC motor and generator is roughly the same, typical structure
It is made of two major parts of stator and rotor, stator is located at outside motor body, and rotor is located at electronics bore of stator, thus logical
Crossing external prime mover driven rotor can make it work as generator.Therefore, the electric notor in the present invention, structure are same
Existing brshless DC motor is identical.
Illustrate that the high-lift system of the aircraft of presently preferred embodiments of the present invention is enabling stand-by power supply hereinafter with reference to Fig. 2
The typical example of internal electric network network configuration under state.
Referring to shown in Fig. 2, in this example, there are two SFCC for high-lift system tool using as redundant configuration, and slat
MDE and slat power generation mechatronics, the mixed electric notor moved in PDU of slat generator, that is, slat.Slat MDE and slat generator
Also it is connected with two SFCC, wing flap electric notor.As shown in dashed line in figure 2, in conventional operation, wing flap and slat
MDE receives the power supply of aircraft power grid, and in turn by power transmission to wing flap, the respective electric notor of slat and WTB, this
In the case of, wing flap, slat electric notor can be with motor mode.
In the state of enabling stand-by power supply, as above, the mixed dynamic PDU of slat can utilize the electric horse of hydraulic energy source driving slat
It works up to as generator.Refering to what is shown in Fig. 2, in this example, the transformer being arranged inside slat MDE can be sent out slat
The 380V direct current of motor output, is converted into 28V direct current and is supplied to SFCC and WTB, the 380V that slat generator is exported is straight
Galvanic electricity is converted into 115V/230V alternating current and powers to the MDE of wing flap, and then drives the electric notor of wing flap.
It should be understood that other internal point network configurations also can be used in high-lift system of the invention, for example, can be by
The mixed dynamic PDU of wing flap is as the other assemblies power supply that generator is in high-lift system.
In this way, the high-lift system of aircraft of the invention can also independently of aircraft other systems especially
Enough redundant powers are independently generated independently of the aircraft power grid of power supply is used as under normal conditions, to need to meet an urgent need in aircraft
In the case where power supply, being able to not depend on aircraft power grid can be achieved with power supply to all electrical equipments inside high-lift system,
Including the independent driving for realizing Chinese-style jacket with buttons down the front slat control surface.If necessary, in the case where aircraft enters cruising phase, can also pass through
Similar fashion provides stand-by power source for 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 (7)
1. a kind of high-lift system of aircraft, which is characterized in that it includes mixed dynamic Motorized drive unit, motor driven electronic control
Device and flap slat computer, the motor driven electronic control unit is according to the instruction of flap slat computer control
Mixed dynamic Motorized drive unit is to drive the movement of the wing flap and/or slat of aircraft, wherein the mixed dynamic Motorized drive unit includes
Differential integrated gear case, hydraulic motor and electric notor, the hydraulic motor and the electric notor via arrangement of clutch and fly respectively
The transmission mechanism of machine wing is connected to the wing flap and/or slat of aircraft, and the hydraulic motor and the electric notor are via the difference
Fast integrated gear case is connected, and the electric notor is connected to aircraft power grid, and institute via the motor driven electronic control unit
The power supply that electric notor receives aircraft power grid when running with electric motor mode is stated, the motor driven electronic control unit is also used to
When receiving the stand-by power supply instruction that the flap slat computer issues, the braking of the hydraulic motor and the electric notor is detected
Whether device is in on-position, and will be described by the arrangement of clutch in the case where the brake is in on-position
Hydraulic motor and the electric notor are separated with the transmission mechanism, then control the hydraulic motor as prime mover via described
Differential integrated gear case drives the electric notor to run with generator mode, and by the motor driven electronic control unit to
The electric wing tip brake gear of the wing flap and/or slat of the flap slat computer and/or aircraft is powered.
2. the high-lift system of aircraft as described in claim 1, which is characterized in that the flap slat computer is also used to detect
Whether the wing flap of aircraft and/or the electric wing tip brake gear of slat are in on-position, and at the electric wing tip brake gear
The stand-by power supply instruction is issued when on-position.
3. the high-lift system of aircraft as described in claim 1, which is characterized in that the flap slat computer is also used to detect
Whether the electric wing tip brake gear of the slat of aircraft is in whether on-position, slat are in fully retracted position and aircraft
Whether ram-air turbine is in down state, and the electric wing tip brake gear of slat is in on-position, slat has been in
Full retrieving position and when ram-air turbine be in down state, issue the stand-by power supply and instruct.
4. the high-lift system of aircraft as described in claim 1, which is characterized in that when the electric notor is transported with generator mode
When row, also powered by the motor driven electronic control unit to aircraft power grid.
5. the high-lift system of aircraft as described in claim 1, which is characterized in that the motor driven electronic control unit is set
It is equipped with transformer, the transformer is used for the voltage of aircraft power grid and/or the electric notor is defeated with generator mode operation institute
Voltage out is converted to the operating voltage of the flap slat computer and the operating voltage of the electric wing tip brake gear.
6. the high-lift system of aircraft as claimed in claim 4, which is characterized in that the motor driven electronic control unit is set
Be equipped with transformer, the transformer be used to be converted to the voltage of aircraft power grid the electric notor operating voltage and will be described
Electric notor runs the voltage that exported voltage is converted to aircraft power grid with generator mode.
7. the high-lift system of aircraft as described in claim 1, which is characterized in that the differential integrated gear case includes planet
Gear assembly and cylinder gear speed reducer, the output shaft of the hydraulic motor is via the planetary gear set and the Cylinder Gear
Wheel decelerator is connected to the rotor of the electric notor, produces to drive the rotor of the electric notor to rotate by the hydraulic motor
Raw exciting current.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611012555.3A CN106741863B (en) | 2016-11-17 | 2016-11-17 | The high-lift system of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611012555.3A CN106741863B (en) | 2016-11-17 | 2016-11-17 | The high-lift system of aircraft |
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| Publication Number | Publication Date |
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| CN106741863A CN106741863A (en) | 2017-05-31 |
| CN106741863B true CN106741863B (en) | 2019-04-02 |
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| CN201611012555.3A Active CN106741863B (en) | 2016-11-17 | 2016-11-17 | The high-lift system of aircraft |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11111005B2 (en) * | 2017-11-22 | 2021-09-07 | Hamilton Sundstrand Corporation | Control of multiple flight control surface systems using single power drive unit |
| EP3653493B1 (en) * | 2018-11-16 | 2023-01-18 | Bombardier Inc. | High-lift actuation system having centralized inboard actuation control and independent outboard actuation control |
| CN110667826B (en) * | 2019-09-03 | 2023-03-24 | 中国航空工业集团公司西安飞行自动控制研究所 | High-lift distributed telex control system |
| CN111143987B (en) * | 2019-12-24 | 2023-08-04 | 中国航空工业集团公司西安飞机设计研究所 | Dynamics modeling method for high-lift system of airplane |
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| CN101052565A (en) * | 2004-11-01 | 2007-10-10 | 波音公司 | High-lift distributed active flow control system and method |
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|---|---|---|---|---|
| DE102007045547A1 (en) * | 2007-09-24 | 2009-04-16 | Airbus Deutschland Gmbh | Automatic control of a high-lift system of an aircraft |
| DE102014010356B4 (en) * | 2013-07-26 | 2022-11-10 | Liebherr-Aerospace Lindenberg Gmbh | airplane |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101052565A (en) * | 2004-11-01 | 2007-10-10 | 波音公司 | High-lift distributed active flow control system and method |
Non-Patent Citations (1)
| Title |
|---|
| 大型飞机高升力系统的发展及关键技术分析;史佑民，杨新团;《航空制造技术》;20161031(第10期);74-78 |
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