CN106741863A - The high-lift system of aircraft - Google Patents
The high-lift system of aircraft Download PDFInfo
- Publication number
- CN106741863A CN106741863A CN201611012555.3A CN201611012555A CN106741863A CN 106741863 A CN106741863 A CN 106741863A CN 201611012555 A CN201611012555 A CN 201611012555A CN 106741863 A CN106741863 A CN 106741863A
- Authority
- CN
- China
- Prior art keywords
- aircraft
- electric notor
- electric
- slat
- mde
- 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.)
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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 system of aircraft.High-lift system of the invention, including mixed dynamic PDU, MDE and SFCC, MDE mixes dynamic PDU to drive the motion of the wing flap and/or slat of aircraft according to the 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 network when being run with electric motor mode, MDE is additionally operable to when the stand-by power supply instruction that SFCC sends is received, control hydraulic motor is run as prime mover driven electric notor with generator mode, it is powered.The present invention can produce enough redundant powers independently of the other systems of aircraft, so as in the case where aircraft needs emergency service, be independent of aircraft power network 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 system of aircraft.
Background technology
The high-lift system of modern large aircraft includes the slat positioned at the leading edge of a wing and the wing flap positioned at trailing edge.
Taking off, the low-speed stage such as land by the protruding of leading edge slat and trailing edge flap, be bent downwardly increase airfoil
Product, change configuration to provide airplane ascensional force, with ensure the rational ground run distance of aircraft and safety takeoff speed, while improve fly
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)
By after inter-process parsing after control signal, then send command signal and give Motorized drive unit (PDU).PDU exports rotation torque,
Swing pinion actuator is transferred to by the motion of the drive line based part such as torque tube, bearing spider, and then drives wing flap, slat
Control surface motion.The position signalling of control surface is fed back to SFCC by the position sensor positioned at wing tip.When SFCC receives table
After levying the sensor signal that control surface reaches specified location, send command signal and allow PDU to stop output torque, and send instruction letter
Number wing tip brake gear is given, locking transmission and then makes control surface be maintained at specified location at linear system.
PDU in aircraft drives power for high-lift system is provided, and generally PDU at least includes a hydraulic pressure horse
Reach, positioned at the fuselage middle position of aircraft and be connected to transmission linear system, transmission linear system is again provided in wing flap machine power
Or the swing pinion actuator on slat control surface erect-position.For example, the aircraft of the A380/350 models of current Air Passenger company, its seam
The PDU of wing system includes a hydraulic motor and an electro-motor.
Aircraft will drive generator or hydraulic pump in the case of all power failures using ram-air turbine,
Be only to ensureing that aircraft continues the important system or equipment offer energy of safe flight and landing floor level, such as it is main to fly
Control electronics and actuator of control system, undercarriage and high-lift system etc..Limited by aircraft weight volume, generator
Or hydraulic pump is only capable of providing less power, under this powering mode, said system and equipment can keep normal function,
But performance has certain decline.For high-lift system, to keep the normal function of wing flap and slat, wing flap and seam
At most one hydraulic motor or electric notor in wing PDU can work, it is ensured that control surface can put down, and speed slows down.
Used because the wing flap and slat control surface of high-lift system only enter near and landing period in aircraft, and 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 long, and high-lift system takes substantial amounts of electric power, then reduce the efficiency of using energy source.And
And, it is contemplated that hydraulic pump does not ensure that all of load all obtains the flow of abundance, therefore would generally be set in existing aircraft
Put prioritizing valve, it is preferential to ensure aileron actuator, elevator actuator, rudder actuator and undercarriage actuator it is required
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 long, and wing flap and slat will have great probability to cannot get enough flows, causes slat and wing flap to put down, or
Wing flap cannot put down.Therefore, the energy source configuration mode on current aircraft, cause high-lift system for the energy utilization ratio compared with
Low, especially in the case where aircraft needs emergency service, the energy of high-lift system cannot be utilized effectively.
The content of the invention
The technical problem to be solved in the present invention is to overcome the energy profit of the high-lift system of aircraft of the prior art
With defect that is less efficient, cannot effectively being utilized in the case where emergency service is needed, a kind of high-lift system of aircraft is proposed
System.
The present invention is to solve above-mentioned technical problem by following technical proposals：
The invention provides a kind of high-lift system of aircraft, its feature is, it includes mixed dynamic PDU, MDE (i.e. motor
Drive electronic-controlled installation) and SFCC, the MDE according to the instruction control mixed dynamic PDU of the SFCC to drive aircraft
The motion 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
Aircraft power network is connected to, and the electric notor receives the power supply of aircraft power network when being run with electric motor mode, and the MDE is also
For when the stand-by power supply instruction that the SFCC sends is received, the brake of the detection hydraulic motor and the electric notor to be
It is no in on-position, and in the case where the brake is in on-position by the arrangement of clutch by the hydraulic pressure
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 be run with generator mode, and by the MDE to the SFCC and/or the flap of aircraft
The electric wing tip brake gear of the wing and/or slat is powered.
It is preferred that the SFCC is additionally operable to detect whether the wing flap of aircraft and/or the electric wing tip brake gear of slat are in
On-position, and the stand-by power supply instruction is sent when the electric wing tip brake gear is in on-position.
It is preferred that the SFCC be additionally operable to detect aircraft slat electric wing tip brake gear whether in on-position,
Whether whether the ram-air turbine in fully retracted position and aircraft is in down state to slat, and in the electric wing of slat
Sharp brake gear is in on-position, slat and is in when fully retracted position and ram-air turbine are in down state and sends institute
State stand-by power supply instruction.
It is preferred that when the electric notor is run with generator mode, also being powered to aircraft power network by the MDE.
It is preferred that the MDE is provided with transformer, it is the electricity that the transformer is used for the voltage conversion of aircraft power network
The operating voltage of motor and the electricity by the electric notor with the exported voltage conversion of generator mode operation as aircraft power network
Pressure.
It is preferred that the transformer is used to run the voltage of aircraft power network and/or the electric notor with generator mode
The voltage conversion for being exported is the operating voltage of the SFCC and the operating voltage of the electric wing tip brake gear.
It is preferred that the differential integrated gear case includes planetary gear set and cylinder gear speed reducer, the hydraulic pressure horse
The output shaft for reaching is connected to the rotor of the electric notor via the planetary gear set and the cylinder gear speed reducer, so that
Drive the rotor of the electric notor to rotate by the hydraulic motor and produce exciting current.
On the basis of common sense in the field is met, above-mentioned each optimum condition can be combined, and obtain final product each preferable reality of the present invention
Example.
Positive effect of the invention is：
The high-lift system of aircraft of the invention, can effectively drive the motion of the flap slat of aircraft, also using mixed dynamic PDU
Enough redundant powers can be produced independently of the other systems of aircraft, so as in the case where aircraft needs emergency service, drive
Electric notor in dynamic PDU switchs to generator mode, be can be achieved with to high-lift system inside so as to be independent of aircraft power network
All electrical equipments power supply, including independently realize the driving of Chinese-style jacket with buttons down the front slat control surface, and without by aircraft power network by electricity
Busbar is powered, additionally it is possible to when necessary in the case where aircraft enters cruising phase for aircraft provides stand-by power source.
Brief description of the drawings
Fig. 1 is the schematic diagram of the high-lift system of the aircraft of a preferred embodiment of the present invention.
Fig. 2 is inside of the high-lift system of the aircraft of a preferred embodiment of the present invention in the state of stand-by power supply is enabled
The schematic diagram of one example of electric network configuration.
Specific embodiment
With reference to Figure of description, further the preferred embodiments of the present invention are described in detail, description below
For exemplary, not limitation of the present invention, other any similar situations are still fallen among protection scope of the present invention.
In following specific descriptions, the term of directionality, such as "left", "right", " on ", D score, "front", "rear", etc.,
Direction described in refer to the attached drawing uses.The part of embodiments of the invention can be placed in various different directions, directionality
Term is for illustrative purposes and nonrestrictive.
With reference to shown in Fig. 1, the high-lift system of the aircraft according to a preferred embodiment of the present invention includes mixed dynamic PDU1, motor
Control electronic installation 2 (i.e. MDE) and SFCC3, MDE2 according to the mixed dynamic PDU1 of instruction control of SFCC3 with drive aircraft wing flap or
The motion 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 pressure horse via the transmission mechanism 4 of arrangement of clutch 5 and aircraft wing respectively with electric notor 13
It is connected via differential integrated gear case 12 with electric notor 13 up to 11, electric notor 13 is connected to aircraft power network, and electricity via MDE2
Motor 13 receives the power supply of aircraft power network when being run with electric motor mode, and MDE2 is additionally operable to standby receive that SFCC3 sends
During power supply instruction, whether the brake of detection hydraulic motor 11 and electric notor 13 is in on-position, and be in brake
Hydraulic motor 11 and electric notor 13 are separated with transmission mechanism 4 by arrangement of clutch 5 in the case of on-position, liquid is then controlled
Pressure motor 11 drives electric notor 13 to be run with generator mode as prime mover via differential integrated gear case 12, and by MDE2
Powered to the electric wing tip brake gear 6 (i.e. WTB) of the wing flap or slat of SFCC3 and aircraft.High-lift system also includes torque
Limiter 14, it 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 network
Voltage and electric notor 13 operating voltage and electric wing tip brake of exported voltage conversion as SFCC3 are run with generator mode
The operating voltage of device 6, and by the voltage conversion of aircraft power network for electric notor 13 operating voltage and by electric notor 13 with
It is the voltage of aircraft power network that generator mode runs exported voltage conversion.
In some exemplary embodiment, SFCC3 is additionally operable to detect the wing flap of aircraft and/or the electric wing tip brake dress of slat
Whether 6 are put in on-position, and stand-by power supply instruction is sent when electric wing tip brake gear 6 is in on-position, or,
SFCC3 be additionally operable to the slat for detecting aircraft electric wing tip brake gear 6 whether in on-position, slat whether in receiving completely
Return put and aircraft ram-air turbine whether in down state, and electric wing tip brake gear 6 in slat is in system
Dynamic state, slat are in fully retracted position and send stand-by power supply instruction when 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 for receiving SFCC3 is instructed
11 separate from system completely, i.e., with the part of the transmission mechanism 4 positioned at both sides wing (for example, including torque tube and various shapes
The parts such as the connecting support seat of formula) it is completely disengaged.After disengagement, moment of torsion is no longer transferred to transmission by electric notor 13 with hydraulic motor 11
Mechanism 4.
After being separated from system, electric notor 13 can be run with generator mode, and hydraulic motor 11 is by hydraulic energy source
Drive, and drive electric notor 13 to generate electricity by the gear train of differential integrated gear case 12.Specifically, differential integrated gear case 12
Planetary gear set and cylinder gear speed reducer are may include, 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, so that driving the rotor of electric notor 13 to rotate by hydraulic motor 11 produces excitation
Electric current.
In some typical implementation methods of the invention, differential integrated gear case may include two sun gears and two pairs of rows
Star-wheel.The output shaft of two sun gears respectively with hydraulic motor and motor is connected.Two planetary gears are identicals.Two sun
Wheel is each engaged with one of planetary gear, and is intermeshed between two planetary gears, so as to pass through gear train by hydraulic pressure horse
The power output for reaching to electric notor rotor, and then produce exciting current cause electric notor as generator operation.
It will be appreciated by those skilled in the art that brshless DC motor is roughly the same with the structure of generator, typical structure
It is made up of two major parts of stator and rotor, stator is located at outside motor body, rotor is located at electronics bore of stator, thus logical
Crossing outside prime mover driven rotor can just make it as generator operation.Therefore, the electric notor in the present invention, its structure is same
Existing brshless DC motor is identical.
High-lift system hereinafter with reference to the aircraft of Fig. 2 explanation presently preferred embodiments of the present invention is enabling stand-by power supply
The exemplary of the internal electric network network configuration under state.
Shown in reference picture 2, in this example, high-lift system has two SFCC as redundant configuration, and slat
MDE and slat generating mechatronics, slat generator are the electric notor in the mixed dynamic PDU of 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 the case of conventional operation, wing flap and slat
MDE receives the power supply of aircraft power network, and and then 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 stand-by power supply is enabled, as above, the mixed dynamic PDU of slat can utilize hydraulic energy source to drive the electric horse of slat
Up to as generator operation.With reference to shown in Fig. 2, in this example, the transformer that slat MDE inside is set can send out slat
The 380V direct currents of motor output, are converted into 28V direct currents and are supplied to SFCC and WTB, and the 380V that slat generator is exported is straight
Stream electricity is converted into 115V/230V alternating currents and is powered to the MDE of wing flap, and then drives the electric notor of wing flap.
It should be appreciated that high-lift system of the invention can also use other internal point network configurations, for example, can be by
The mixed dynamic PDU of wing flap is as generator for the other assemblies in high-lift system are powered.
In this way, the high-lift system of aircraft of the invention can also be independently of the other systems of aircraft especially
Enough redundant powers are independently produced independently of the aircraft power network of power supply is used as under normal circumstances, it is emergent so as to be needed in aircraft
In the case of power supply, it is able to be independent of the power supply that aircraft power network can be achieved with to all electrical equipments inside high-lift system,
Driving including independently realizing Chinese-style jacket with buttons down the front slat control surface.When necessary, in the case where aircraft enters cruising phase, can also pass through
Similar fashion provides stand-by power source for aircraft.
Although the foregoing describing specific embodiment of the invention, 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
On the premise of principle of the invention and essence, various changes or modifications can be made to these implementation methods, but these are changed
Protection scope of the present invention is each fallen within modification.
Claims (7)
1. a kind of high-lift system of aircraft, it is characterised in that it includes mixed dynamic PDU, MDE and SFCC, and the MDE is according to
The instruction control of SFCC is described to mix dynamic PDU to drive the motion of the wing flap and/or slat of aircraft, wherein, the mixed dynamic PDU 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 network, and the electric notor with motor via the MDE
Receive the power supply of aircraft power network during mode operation, the MDE is additionally operable to when the stand-by power supply instruction that the SFCC sends is received,
Detect whether the hydraulic motor and the brake of the electric notor are in on-position, and braking is in the brake
The hydraulic motor and the electric notor are separated with the transmission mechanism by the arrangement of clutch in the case of state, then
The hydraulic motor is controlled to drive the electric notor to be transported with generator mode via the differential integrated gear case as prime mover
OK, and by the MDE powered to the electric wing tip brake gear of the wing flap and/or slat of the SFCC and/or aircraft.
2. the high-lift system of aircraft as claimed in claim 1, it is characterised in that the SFCC is additionally operable to detect the flap of aircraft
Whether the electric wing tip brake gear of the wing and/or slat is in on-position, and is in braking shape in the electric wing tip brake gear
The stand-by power supply instruction is sent during state.
3. the high-lift system of aircraft as claimed in claim 1, it is characterised in that the SFCC is additionally operable to detect the seam of aircraft
Whether whether the electric wing tip brake gear of the wing be in the ram-air of fully retracted position and aircraft in on-position, slat
Turbine whether be in down state, and slat electric wing tip brake gear be in on-position, slat be in withdraw position completely
Put and send the stand-by power supply instruction when ram-air turbine is in down state.
4. the high-lift system of aircraft as claimed in claim 1, it is characterised in that when the electric notor is transported with generator mode
During row, also powered to aircraft power network by the MDE.
5. the high-lift system of aircraft as claimed in claim 1, it is characterised in that the MDE is provided with transformer, the change
It is described that depressor is used to for the voltage of aircraft power network and/or the electric notor to run exported voltage conversion with generator mode
The operating voltage of the operating voltage of SFCC and the electric wing tip brake gear.
6. the high-lift system of aircraft as claimed in claim 4, it is characterised in that the MDE is provided with transformer, the change
Depressor be used for by operating voltage that the voltage conversion of aircraft power network is the electric notor and by the electric notor with generator mould
It is the voltage of aircraft power network that formula runs exported voltage conversion.
7. the high-lift system of aircraft as claimed in claim 1, it is characterised 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, so as to drive the rotor of the electric notor to rotate by the hydraulic motor produce
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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106741863A true CN106741863A (en) | 2017-05-31 |
| CN106741863B CN106741863B (en) | 2019-04-02 |
Family
ID=58969166
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611012555.3A Active CN106741863B (en) | 2016-11-17 | 2016-11-17 | The high-lift system of aircraft |
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| CN (1) | CN106741863B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110667826A (en) * | 2019-09-03 | 2020-01-10 | 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 |
| CN111143987A (en) * | 2019-12-24 | 2020-05-12 | 中国航空工业集团公司西安飞机设计研究所 | Dynamics modeling method for aircraft high-lift system |
| CN111196349A (en) * | 2018-11-16 | 2020-05-26 | 庞巴迪公司 | High lift actuation system with centralized inboard actuation control and independent outboard actuation control |
| US11111005B2 (en) * | 2017-11-22 | 2021-09-07 | Hamilton Sundstrand Corporation | Control of multiple flight control surface systems using single power drive unit |
Citations (3)
| 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 |
| WO2009040102A1 (en) * | 2007-09-24 | 2009-04-02 | Airbus Deutschland Gmbh | Automatic control of a high lift system of an aircraft |
| US20150076282A1 (en) * | 2013-07-26 | 2015-03-19 | Liebherr-Aerospace Lindenberg Gmbh | Aircraft |
-
2016
- 2016-11-17 CN CN201611012555.3A patent/CN106741863B/en active Active
Patent Citations (3)
| 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 |
| WO2009040102A1 (en) * | 2007-09-24 | 2009-04-02 | Airbus Deutschland Gmbh | Automatic control of a high lift system of an aircraft |
| US20150076282A1 (en) * | 2013-07-26 | 2015-03-19 | Liebherr-Aerospace Lindenberg Gmbh | Aircraft |
Non-Patent Citations (1)
| Title |
|---|
| 史佑民，杨新团: "大型飞机高升力系统的发展及关键技术分析", 《航空制造技术》 * |
Cited By (6)
| 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 |
| CN111196349A (en) * | 2018-11-16 | 2020-05-26 | 庞巴迪公司 | High lift actuation system with centralized inboard actuation control and independent outboard actuation control |
| CN111196349B (en) * | 2018-11-16 | 2023-08-08 | 庞巴迪公司 | High lift actuation system with centralized inboard actuation control and independent outboard actuation control |
| CN110667826A (en) * | 2019-09-03 | 2020-01-10 | 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 |
| CN111143987A (en) * | 2019-12-24 | 2020-05-12 | 中国航空工业集团公司西安飞机设计研究所 | Dynamics modeling method for aircraft high-lift 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106741863B (en) | 2019-04-02 |
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