CN116280177A - Airfoil dynamic stall active control device with trailing edge winglet - Google Patents
Airfoil dynamic stall active control device with trailing edge winglet Download PDFInfo
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- CN116280177A CN116280177A CN202310507393.4A CN202310507393A CN116280177A CN 116280177 A CN116280177 A CN 116280177A CN 202310507393 A CN202310507393 A CN 202310507393A CN 116280177 A CN116280177 A CN 116280177A
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- 230000005540 biological transmission Effects 0.000 claims description 27
- 230000007246 mechanism Effects 0.000 claims description 20
- 230000001360 synchronised effect Effects 0.000 claims description 11
- 230000004308 accommodation Effects 0.000 claims description 4
- 238000012360 testing method Methods 0.000 abstract description 7
- 239000012530 fluid Substances 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 9
- 230000008859 change Effects 0.000 description 5
- 230000008569 process Effects 0.000 description 5
- 230000009471 action Effects 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 238000005299 abrasion Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
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- 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
- B64C13/38—Transmitting means with power amplification
- B64C13/50—Transmitting means with power amplification using electrical energy
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/10—Drag reduction
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Abstract
The invention discloses an airfoil dynamic stall active control device with a trailing edge winglet, which relates to the technical field of fluid flow control and comprises the following components: an airfoil center having trailing edge winglet drive units mounted on both sides thereof; the two sides of the trailing edge winglet are respectively and rotatably connected with the trailing edge winglet driving units at the two sides of the airfoil central member; the control system is used for synchronously controlling the movement of the trailing edge winglet driving unit; according to the invention, the servo motor is adopted to directly drive the trailing edge winglet, and the electronic cam is utilized to realize the adjustment of any track equation of the trailing edge winglet, so that the trailing edge winglet is controlled more efficiently, the adjustment precision of the control parameters of the trailing edge winglet is improved, the adjustment mode of the oscillation parameters of the trailing edge winglet is simplified, the test wind speed and the oscillation frequency of the trailing edge winglet of the device are improved, and the adjustment of any track equation of the trailing edge winglet is realized.
Description
Technical Field
The invention relates to the technical field of fluid flow control, in particular to an airfoil dynamic stall active control device with a trailing edge winglet.
Background
The statements in this section merely provide background information related to the present disclosure and may not constitute prior art.
In the forward flight process of the helicopter, the change of the pitch of the rotor wing along with the azimuth angle can cause the periodical change of the incoming flow attack angle of the blade element, and particularly, the backward side blade of the rotor wing in the high-speed forward flight state can generate obvious dynamic stall phenomenon; when dynamic stall occurs, the periodic formation, convection and shedding of blade upper surface leading edge vortices (Leading edge vortex, LEV) can cause nonlinear disturbances in the pressure field and cause abrupt changes in blade lift, drag and pitching moment; the increase of lift force and resistance can limit the improvement of aerodynamic performance and flying speed of the helicopter, and alternating aerodynamic force and moment can induce the vibration of the blade and even stall flutter, thereby influencing the service life of equipment and flying safety, so that the dynamic stall phenomenon of a rotor wing is improved, the influence caused by dynamic stall is reduced, and the method has important value for improving the performance of the helicopter.
In order to overcome the adverse effect of dynamic stall on rotor performance, researchers aim at the motion characteristics of rotor blades, and improve rotor dynamic stall characteristics by developing unsteady design on airfoil profiles, but rotor performance is closely related to three-dimensional flow fields, rotor structural characteristics and the like, so that active flow control strategies are introduced into rotor design in order to break through barriers that traditional profile design cannot meet rotor performance requirements in full working state. The trailing edge winglet (Trailing edge flap, TEF) control realizes the dynamic adjustment of the airfoil profile by changing the deflection angle of the winglet so as to adapt to the requirements of different angles of attack, and because the winglet driving mechanism is very similar to an active control winglet (Active control flap, ACF), the trailing edge winglet control is expected to solve the problems of dynamic stall and vibration of a rotor wing through a set of mechanisms at the same time, and the trailing edge winglet control has good engineering application prospect due to the advantages of simple structure, convenient maintenance and the like, and becomes an important way for improving the dynamic stall; the basic principle of controlling the dynamic stall of the rotor wing by utilizing the trailing edge winglet is to arrange the trailing edge winglet capable of deflecting to move at the trailing edge of the rotor blade, and the dynamic change of the aerodynamic profile of the airfoil is realized by controlling the oscillation amplitude, the balanced attack angle, the oscillation frequency and the deflection track of the trailing edge winglet so as to adapt to the requirements of different attack angles, thereby realizing the dynamic adjustment of aerodynamic load in the dynamic stall process.
In the research aiming at dynamic stall control, various airfoil devices with trailing edge winglets are designed, wherein a part of the airfoil devices are designed into three sections, and the trailing edge winglets are directly driven by a motor from one side due to the limitation of model size and installation space, so that the size and power of the motor are severely limited, the winglets can only adopt ABS materials, and the limitation of the power and the materials can not enable the device to carry out the test of high wind speed (high Reynolds number) and high oscillation frequency (high reduction frequency).
Meanwhile, the motor is adopted to drive the eccentric wheel to rotate, the reciprocating sliding block is driven to do linear motion, a rack is arranged at one end of the reciprocating sliding block, which is far away from the eccentric wheel, and is meshed with the transmission gear set, a pinion meshed with the transmission gear set is arranged in the trailing edge winglet, the rack drives the transmission gear set to rotate, and then the trailing edge winglet is driven to do sinusoidal oscillation motion. The device adopts the eccentric wheel mechanism to realize the conversion from the circular motion of the motor to the linear motion of the rack, so that only the sinusoidal oscillation of the trailing edge winglet can be realized, the change of the winglet oscillation parameters can be realized by manually adjusting the position of the internal part, the change is complicated, the precision is low, the requirement of any trailing edge winglet oscillation track equation can not be met, and only the test of limited conditions can be carried out based on the model. In addition, due to the limitation of the internal space of the model, the limitation of insufficient power still exists in the single motor drive, and the requirement of higher oscillation frequency cannot be met.
Disclosure of Invention
The invention aims at: aiming at the problems existing in the prior art, the airfoil dynamic stall active control device with the trailing edge winglet is provided, a plurality of servo motors are adopted to directly drive the trailing edge winglet, and the electronic cam is utilized to realize the adjustment of any track equation of the trailing edge winglet, so that the trailing edge winglet is more efficiently controlled, the adjustment precision of the control parameters of the trailing edge winglet is improved, the adjustment mode of the oscillation parameters of the trailing edge winglet is simplified, the test wind speed and the oscillation frequency of the trailing edge winglet of the device are improved, and the adjustment of any track equation of the trailing edge winglet is realized, thereby solving the problems.
The technical scheme of the invention is as follows:
an airfoil dynamic stall active control device with trailing edge winglets comprising:
an airfoil center having trailing edge winglet drive units mounted on both sides thereof;
the two sides of the trailing edge winglet are respectively and rotatably connected with the trailing edge winglet driving units at the two sides of the airfoil central member;
and the control system is used for synchronously controlling the movement of the trailing edge winglet driving unit.
Further, the airfoil center is provided with accommodation spaces on both sides, and the trailing edge winglet drive unit is mounted in the accommodation spaces.
Further, the trailing edge winglet drive unit comprises:
the device comprises a mounting frame, wherein a servo motor and a toothed belt transmission mechanism are arranged on the mounting frame, and power output by the servo motor is transmitted to the trailing edge winglet through the toothed belt transmission mechanism to control the trailing edge winglet to rotate.
Further, transmission shafts are arranged on two sides of the trailing edge winglet.
Further, the toothed belt transmission mechanism comprises:
the driving belt pulley is connected with the output shaft of the servo motor;
the driven belt pulley is connected with the transmission shaft;
and the toothed synchronous belt is used for connecting the driving belt pulley and the driven belt pulley in a transmission way, and the toothed synchronous belt drives the trailing edge winglet to rotate.
Further, the control system is an electronic cam, and the rotation of the servo motors at two sides is synchronously controlled through the electronic cam, so that the control of the oscillation amplitude, the balance attack angle, the oscillation frequency and the oscillation track equation of the trailing edge winglet is realized.
Further, two trailing edge winglet drive units are symmetrically arranged on both sides of the airfoil center.
Further, a transmission hole for a transmission shaft to pass through is formed in the mounting frame, and a bearing is mounted in the transmission hole.
Further, the mounting frame is also provided with an output hole for the output shaft of the servo motor to pass through.
Compared with the prior art, the invention has the beneficial effects that:
1. the wing type dynamic stall active control device with the trailing edge winglet adopts a servo motor to directly drive the trailing edge winglet, and utilizes an electronic cam to realize the adjustment of any track equation of the trailing edge winglet, thereby realizing the more efficient control of the trailing edge winglet, improving the adjustment precision of the control parameters of the trailing edge winglet, simplifying the adjustment mode of the oscillation parameters of the trailing edge winglet, improving the test wind speed and the oscillation frequency of the trailing edge winglet of the device and realizing the adjustment of any track equation of the trailing edge winglet.
2. The airfoil type dynamic stall active control device with the trailing edge winglet adopts double-end synchronous driving of double servo motors, improves driving power and realizes higher test wind speed and oscillation frequency.
3. An airfoil dynamic stall active control device with a trailing edge winglet adopts a toothed belt transmission mechanism to directly drive the trailing edge winglet, so that the mechanism is simplified, errors caused by manual operation are avoided, and the reliability is improved.
4. The wing type dynamic stall active control device with trailing edge winglet adopts servo motor to drive directly, and can conveniently realize the control of arbitrary oscillation amplitude, balanced attack angle, oscillation frequency and oscillation track equation through electronic cam.
Drawings
FIG. 1 is a schematic view of a partial structure of an airfoil dynamic stall active control device with trailing edge winglets;
FIG. 2 is a schematic structural view of an airfoil dynamic stall active control device with trailing edge winglets.
Reference numerals: the device comprises a 1-airfoil central part, a 2-trailing edge winglet, a 3-accommodating space, a 4-mounting frame, a 5-servo motor, a 6-transmission shaft, a 7-driving belt pulley, an 8-servo motor output shaft, a 9-driven belt pulley and a 10-toothed synchronous belt.
Detailed Description
It is noted that relational terms such as "first" and "second", and the like, are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises the element.
The features and capabilities of the present invention are described in further detail below in connection with examples.
Example 1
Referring to fig. 1, an active control device for airfoil dynamic stall with trailing edge winglet specifically includes the following structure:
an airfoil center 1, both sides of the airfoil center 1 being mounted with trailing edge winglet drive units;
a trailing edge winglet 2, wherein two sides of the trailing edge winglet 2 are respectively rotatably connected with trailing edge winglet driving units at two sides of the airfoil central member 1;
and the control system is used for synchronously controlling the movement of the trailing edge winglet driving unit.
In this embodiment, specifically, two sides of the airfoil central member 1 are provided with accommodating spaces 3, and the trailing edge winglet driving unit is installed in the accommodating spaces 3; preferably, the size of the accommodating space 3 is consistent with the size of the trailing edge winglet driving unit, so that the trailing edge winglet driving unit is prevented from shaking greatly in the accommodating space 3, and stability is ensured.
In this embodiment, specifically, the trailing edge winglet driving unit includes:
the device comprises a mounting frame 4, wherein a servo motor 5 and a toothed belt transmission mechanism are arranged on the mounting frame 4, and power output by the servo motor 5 is transmitted to the trailing edge winglet 2 through the toothed belt transmission mechanism to control the trailing edge winglet 2 to rotate; preferably, the size and shape of the mounting frame 4 are consistent with those of the accommodating space 3, and the mounting frame 4 is fixed in the accommodating space 3 by screws.
In this embodiment, specifically, two sides of the trailing edge winglet 2 are provided with a transmission shaft 6; preferably, said drive shaft 6 is arranged on the trailing edge winglet 2 near one end of the airfoil central element 1.
In this embodiment, specifically, the toothed belt transmission mechanism includes:
a driving pulley 7, wherein the driving pulley 7 is connected with an output shaft of the servo motor 5;
a driven pulley 9, the driven pulley 9 being connected with the drive shaft 6;
and the toothed synchronous belt 10 is used for connecting the driving pulley 7 and the driven pulley 9 in a transmission way, and the toothed synchronous belt 10 drives the trailing edge winglet 2 to rotate.
In this embodiment, specifically, the control system is an electronic cam (not shown in the figure), and the rotation of the servo motors 5 on two sides is synchronously controlled by the electronic cam, so as to realize the control of the oscillation amplitude, the balanced attack angle, the oscillation frequency and the oscillation track equation of the trailing edge winglet 2.
Referring to fig. 2, in the present embodiment, specifically, two trailing edge winglet drive units are symmetrically arranged on both sides of the airfoil center 1.
In this embodiment, specifically, the mounting frame 4 is provided with a transmission hole through which the transmission shaft 6 passes, and a bearing is installed in the transmission hole.
In this embodiment, specifically, the mounting frame 4 is further provided with an output hole through which the output shaft of the servo motor 5 passes.
The airfoil dynamic stall active control device with the trailing edge winglet provided by the embodiment synchronously drives the trailing edge winglet 2 through the servo motor 5 and the toothed belt transmission mechanism which are symmetrically arranged at two sides, simplifies the driving mechanism of the trailing edge winglet 2, avoids errors caused by manually adjusting oscillation parameters of the trailing edge winglet 2, and improves the reliability of the device; meanwhile, the rotation of the servo motors 5 at two sides is synchronously controlled through the electronic cam, so that the control of any oscillation amplitude, balance attack angle, oscillation frequency and oscillation track equation of the trailing edge winglet 2 is realized; and the driving power of the trailing edge winglet 2 is improved by adopting a synchronous driving mode of the two servo motors 5, so that the trailing edge winglet 2 can be made of metal materials, the strength of the device is improved, and the device can be applied to higher test wind speed (Reynolds number) and oscillation frequency (reduction frequency).
Compared with the prior art, the airfoil dynamic stall active control device with the trailing edge winglet has the following advantages:
1. in the prior art, only one motor is driven from the middle of the trailing edge winglet 2, the power provided by a single motor is limited due to the limitation of the installation space of the model, the frequency of the oscillation of the trailing edge winglet 2 is limited by the power, and the higher requirement cannot be met.
2. The traditional mechanical structure of eccentric wheel and rack and pinion is adopted in the domestic prior art, abrasion inevitably exists due to existence of mechanical friction, and manual adjustment is needed when the oscillation amplitude and the equilibrium attack angle of the trailing edge winglet 2 are adjusted each time, so that the complexity of the device is increased, the control precision and efficiency of the trailing edge winglet 2 are reduced, and the application scene is limited by manual adjustment. The technical scheme of the embodiment uses a toothed belt transmission mechanism, so that the servo motor 5 directly drives the trailing edge winglet 2 through the toothed synchronous belt 10, the abrasion of the eccentric wheel and the gear engagement is reduced, the mechanism is simplified, the error of manual operation is avoided, and the application scene of the device is improved.
3. The domestic prior technical proposal adopts an eccentric wheel mechanism to convert the circular motion of a motor into the linear reciprocating motion of a rack mechanism, and then into the oscillating motion of the trailing edge winglet 2, and the trailing edge winglet 2 can only output sinusoidal motion and can not realize the output of any oscillating track of the trailing edge winglet 2 under the restriction of the eccentric wheel mechanism. According to the embodiment, on the basis that the servo motor 5 directly drives the trailing edge winglet 2, the electronic cam is adopted, and the servo motor 5 with synchronous motion at two ends is controlled to rotate according to a desired track, so that the motion of any oscillating track of the trailing edge winglet 2 can be conveniently realized.
The foregoing examples merely represent specific embodiments of the present application, which are described in more detail and are not to be construed as limiting the scope of the present application. It should be noted that, for those skilled in the art, several variations and modifications can be made without departing from the technical solution of the present application, which fall within the protection scope of the present application.
This background section is provided to generally present the context of the present invention and the work of the presently named inventors, to the extent it is described in this background section, as well as the description of the present section as not otherwise qualify as prior art at the time of filing, are neither expressly nor impliedly admitted as prior art against the present invention.
Claims (9)
1. An airfoil dynamic stall control device with trailing edge winglets, comprising:
an airfoil center (1), both sides of the airfoil center (1) being mounted with trailing edge winglet drive units;
the trailing edge winglet (2), two sides of the trailing edge winglet (2) are respectively rotatably connected with trailing edge winglet driving units at two sides of the wing profile center (1);
and the control system is used for synchronously controlling the movement of the trailing edge winglet driving unit.
2. An airfoil dynamic stall active control device with trailing edge winglet according to claim 1, characterized in that the airfoil centre (1) is provided with accommodation spaces (3) on both sides, the trailing edge winglet drive unit being mounted in an accommodation space (3).
3. An airfoil dynamic stall control device with trailing edge winglet according to claim 2, wherein the trailing edge winglet drive unit comprises:
the device comprises a mounting frame (4), wherein a servo motor (5) and a toothed belt transmission mechanism are arranged on the mounting frame (4), and power output by the servo motor (5) is transmitted to the trailing edge winglet (2) through the toothed belt transmission mechanism to control the trailing edge winglet (2) to rotate.
4. An airfoil dynamic stall active control with trailing edge winglet according to claim 3, characterized in that the trailing edge winglet (2) is provided with drive shafts (6) on both sides.
5. An airfoil dynamic stall control device with trailing edge winglet as claimed in claim 4 wherein the toothed belt drive comprises:
the driving belt wheel (7), the driving belt wheel (7) is connected with the output shaft of the servo motor (5);
a driven pulley (9), wherein the driven pulley (9) is connected with the transmission shaft (6);
and the toothed synchronous belt (10) is used for connecting the driving belt pulley (7) and the driven belt pulley (9) in a transmission way, and the toothed synchronous belt (10) is used for driving the trailing edge winglet (2) to rotate.
6. An airfoil dynamic stall driving control device with trailing edge winglet according to claim 3, wherein the control system is an electronic cam, and the control of the oscillation amplitude, the balanced attack angle, the oscillation frequency and the oscillation trajectory equation of the trailing edge winglet (2) is realized by synchronously controlling the rotation of the servo motors (5) at two sides through the electronic cam.
7. An airfoil dynamic stall active control with trailing edge winglet according to claim 1, characterized in that two trailing edge winglet drive units are symmetrically arranged on both sides of the airfoil centre (1).
8. An active control device for dynamic stall of airfoil with trailing edge winglet according to claim 4, characterized in that said mounting frame (4) is provided with a drive hole for the drive shaft (6) to pass through, and in said drive hole a bearing is mounted.
9. An active control device for dynamic stall with airfoil of trailing edge winglet according to claim 4, wherein said mounting frame (4) is further provided with an output hole for the output shaft of the servomotor (5) to pass through.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310507393.4A CN116280177A (en) | 2023-05-08 | 2023-05-08 | Airfoil dynamic stall active control device with trailing edge winglet |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310507393.4A CN116280177A (en) | 2023-05-08 | 2023-05-08 | Airfoil dynamic stall active control device with trailing edge winglet |
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| CN116280177A true CN116280177A (en) | 2023-06-23 |
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| CN202310507393.4A Pending CN116280177A (en) | 2023-05-08 | 2023-05-08 | Airfoil dynamic stall active control device with trailing edge winglet |
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| CN111392037A (en) * | 2020-03-30 | 2020-07-10 | 南京航空航天大学 | Helicopter rotor dynamic stall control method and system |
| CN113232846A (en) * | 2021-05-19 | 2021-08-10 | 南京航空航天大学 | Flap control method and system |
| CN113371227A (en) * | 2021-07-22 | 2021-09-10 | 中国商用飞机有限责任公司 | Test bench of flap motion mechanism |
| CN113602489A (en) * | 2021-10-11 | 2021-11-05 | 中国空气动力研究与发展中心低速空气动力研究所 | Active control trailing edge winglet device for backflow stall of rotor blade with large advancing ratio |
| WO2022114697A1 (en) * | 2020-11-25 | 2022-06-02 | 한국항공대학교산학협력단 | Transformable wing and aerial vehicle including same |
| CN115924060A (en) * | 2023-02-22 | 2023-04-07 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Asymmetric airfoil inversion mechanism based on connecting rod assembly and use method thereof |
-
2023
- 2023-05-08 CN CN202310507393.4A patent/CN116280177A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070297903A1 (en) * | 2005-02-25 | 2007-12-27 | Wind Innovations Llc | Oscillating fluid power generator |
| US20150083853A1 (en) * | 2013-09-24 | 2015-03-26 | The Boeing Company | Adaptive trailing edge actuator system and method |
| CN210027880U (en) * | 2019-06-24 | 2020-02-07 | 贵州弘安鑫晟航空科技有限责任公司 | Unmanned aerial vehicle wing flap with regulatory function |
| CN111392037A (en) * | 2020-03-30 | 2020-07-10 | 南京航空航天大学 | Helicopter rotor dynamic stall control method and system |
| WO2022114697A1 (en) * | 2020-11-25 | 2022-06-02 | 한국항공대학교산학협력단 | Transformable wing and aerial vehicle including same |
| CN113232846A (en) * | 2021-05-19 | 2021-08-10 | 南京航空航天大学 | Flap control method and system |
| CN113371227A (en) * | 2021-07-22 | 2021-09-10 | 中国商用飞机有限责任公司 | Test bench of flap motion mechanism |
| CN113602489A (en) * | 2021-10-11 | 2021-11-05 | 中国空气动力研究与发展中心低速空气动力研究所 | Active control trailing edge winglet device for backflow stall of rotor blade with large advancing ratio |
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