CN107074344B - Propeller, power suit and the unmanned plane of aircraft - Google Patents
Propeller, power suit and the unmanned plane of aircraft Download PDFInfo
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- CN107074344B CN107074344B CN201780000122.2A CN201780000122A CN107074344B CN 107074344 B CN107074344 B CN 107074344B CN 201780000122 A CN201780000122 A CN 201780000122A CN 107074344 B CN107074344 B CN 107074344B
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- blade
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- suction surface
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/18—Aerodynamic features
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/20—Constructional features
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/20—Constructional features
- B64C11/26—Fabricated blades
-
- 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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- 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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A kind of propeller of aircraft (200), including：Blade (210) and propeller hub (230)；The blade (210) connect with the propeller hub (230), and the blade (210) includes suction surface and the pressure face opposite with suction surface；Wherein, the suction surface is equipped with turbulent flow generator (213), for delaying fluid to be detached from the suction surface.Propeller (200) provided by the invention can reduce the separation of blade (210) upper fluid, to reduce the resistance of propeller (200) to improve its working efficiency, and the cost that this mode for improving propeller (200) working efficiency is spent is also low.The present invention also provides a kind of power suit and unmanned planes.
Description
Technical field
The present invention provides a kind of propeller of aircraft, power suit and unmanned plane, belongs to aircraft manufacture technical field.
Background technology
With the development of airmanship, aircraft is gradually from enlargement to miniaturization, from special purpose to a variety of use
Way develops, such as existing multi-rotor unmanned aerial vehicle can be applied in engineering construction, the multiple fields such as take photo by plane, monitor.But with
The increase of application field also gradually increases the performance requirement of aircraft, wherein a main aspect is exactly to improve spiral
The working efficiency of paddle.But in the prior art in order to improve the working efficiency of propeller, it generally can all use and improve propeller
The mode of output, still, this mode are limited by aircraft electrical tankage, motor speed, electricity and adjust the factors such as control accuracy
Influence cause the cost spent when improving propeller works efficiency very big, it is not economical enough.
Invention content
In order to solve existing in the prior art above-mentioned or other potential problems, the embodiment of the present invention provides a kind of aircraft
Propeller, power suit and unmanned plane.
A kind of propeller of aircraft is provided according to some embodiments of the invention, including：Propeller hub and blade；The blade
It is connect with the propeller hub, the blade includes suction surface and the pressure face opposite with suction surface；Wherein, the suction surface is equipped with
Multiple turbulent flow generators, for delaying fluid to be detached from the suction surface.
A kind of power suit is provided according to some embodiments of the invention, including：Above-mentioned propeller and motor；The electricity
Machine is connect with the propeller, for driving the propeller rotational.
A kind of unmanned plane is provided according to some embodiments of the invention, including：Rack and above-mentioned power suit；The power
Suit is mounted in the rack.
Technical solution according to an embodiment of the invention is sent out by the way that turbulent flow is arranged on the suction surface of the propeller of aircraft
Raw device, it is possible to reduce fluid is detached from suction surface, to reduce the resistance of blade, to improve the working efficiency of propeller, and
And the cost that this mode for improving propeller works efficiency is spent is also low.
Description of the drawings
Described in detail below, the above and other objects, features and advantages general of the embodiment of the present invention by referring to accompanying drawing
It becomes more clearly understood from.In the accompanying drawings, by by example and it is unrestricted in a manner of to the present invention multiple embodiments say
It is bright, wherein：
Fig. 1 is the structural schematic diagram for the aircraft that one embodiment of the invention provides；
Fig. 2 is the structural schematic diagram of the propeller of unmanned plane in Fig. 1；
Fig. 3 is sectional view along A-A in Fig. 2；
Fig. 4 is the partial enlarged view of the positions F in Fig. 2；
Fig. 5 a to Fig. 5 e are the schematic diagram of the turbulent flow generator with varying cross-section shape；
Fig. 6 a are the schematic diagram of the turbulent flow generator for the matrix form arrangement that one embodiment of the invention provides；
Fig. 6 b are the schematic diagram of the turbulent flow generator for the matrix form arrangement that another embodiment of the present invention provides；
Fig. 6 c are the schematic diagram of the turbulent flow generator for the radial arrangement that one embodiment of the invention provides；
Fig. 7 a and Fig. 7 b are different turbulent region arrangement schematic diagrames provided in an embodiment of the present invention；
Fig. 8 a are the position relationship schematic diagram of turbulent region and leading edge and rear that one embodiment of the invention provides；
Fig. 8 b are the turbulent region that another embodiment of the present invention provides and connecting pin and free end are position relationship signal
Figure.
In figure：
100, aircraft；110, unmanned plane；
120, holder；121, electricity is adjusted；
122, motor；123, capture apparatus；
130, equipment is shown；140, commanding apparatus；
150, power is set with；151, electricity is adjusted；
152, motor；153, propeller；
160, flight control system；161, flight controller；
162, sensor-based system；170, rack；
200, propeller；210, blade；
211, leading edge；212, rear；
213, turbulent flow generator；214, direction of rotation；
215, unlock mark；216, turbulent region；
230, propeller hub.
Specific implementation mode
Below in conjunction with the accompanying drawings, it elaborates to some embodiments of the present invention.In the absence of conflict, following
Feature in embodiment and embodiment can be combined with each other.
The structure for briefly introducing aircraft first, to be understood more readily from the use environment of propeller.
Fig. 1 is the structural schematic diagram of aircraft provided in this embodiment.The present embodiment is carried out by taking multi-rotor aerocraft as an example
Explanation.Certainly, the aircraft may be single rotor aircraft, or the Fixed Wing AirVehicle with propeller.
Aircraft 100 may include unmanned plane 110, holder 120, display equipment 130 and commanding apparatus 140.Wherein, nobody
Machine 110 may include power suit 150, flight control system 160 and rack 170.Unmanned plane 110 can be with commanding apparatus 140
It is carried out wireless communication with display equipment 130.
Rack 170 may include fuselage and tripod (also referred to as undercarriage).Fuselage may include centre frame and and center
One or more horns of frame connection, one or more horns radially extend from centre frame.Tripod is connect with fuselage, is used
It plays a supportive role in when unmanned plane 110 lands.
Power suit 150 may include that electron speed regulator (referred to as electricity adjust) 151, one or more propellers 153 are (following
Will be described) and one or more motor 152 corresponding with one or more propellers 153, wherein motor 152 be connected to electricity
Between sub- governor 151 and propeller 153, motor 152 and propeller 153 are arranged on corresponding horn；Electron speed regulator 151
Drive signal for receiving the generation of flight controller 160, and driving current is provided to motor 152, with control according to drive signal
The rotating speed of motor 152 processed.Motor 152 is for driving propeller to rotate, and to provide power for the flight of unmanned plane 110, this is dynamic
Power enables unmanned plane 110 to realize the movements of one or more degree of freedom.In certain embodiments, unmanned plane 110 can enclose
It is rotated around one or more rotary shafts.For example, above-mentioned rotary shaft may include roll axis, translation shaft and pitch axis.It should be understood that electricity
Machine 152 can be direct current generator, can also alternating current generator.In addition, motor 152 can be brushless motor, it is possibility to have brush motor.
Flight control system 160 may include flight controller 161 and sensor-based system 162.Sensor-based system 162 is for measuring
The posture information of unmanned plane, i.e. unmanned plane 110 space location information and status information, for example, three-dimensional position, three dimensional angular
Degree, three-dimensional velocity, three-dimensional acceleration and three-dimensional angular velocity etc..Sensor-based system 162 for example may include gyroscope, electronic compass,
IMU (Inertial Measurement Unit, Inertial Measurement, Unit), visual sensor, Global Navigation Satellite System and air pressure
At least one of sensors such as meter.For example, Global Navigation Satellite System can be GPS (global positioning system, Global
Positioning System) or triones navigation system.Flight controller 161 is used to control the flight of unmanned plane 110, example
Such as, the posture information that can be measured according to sensor-based system 162 controls the flight of unmanned plane 110.It should be understood that flight controller 161
Unmanned plane 110 can be controlled according to the program instruction finished in advance, it can also be by responding from commanding apparatus 140
One or more control instructions control unmanned plane 110.
Holder 120 may include that electricity adjusts 121 and motor 122.Holder is for carrying capture apparatus 123.Flight controller 161
The movement of 121 and the control holder 120 of motor 122 can be adjusted by electricity.Optionally, as another embodiment, holder 120 can be with
Including controller, for controlling the movement of holder 120 by controlling electricity tune 121 and motor 122.It should be understood that holder 120 can be with
Independently of unmanned plane 110, or a part for unmanned plane 110.It should be understood that motor 122 can be direct current generator, it can also
Alternating current generator.In addition, motor 122 can be brushless motor, it is possibility to have brush motor.It should also be understood that holder can be located at flight
The top of device can also be located at the bottom of aircraft.
The equipment that capture apparatus 123 is used for capture images such as can be camera or video camera, shooting 123 can be with
Flight controller communicates, and is shot under the control of flight controller.
Display equipment 130 is located at the ground surface end of aircraft 100, can be communicated wirelessly with unmanned plane 110,
And it is displayed for the posture information of unmanned plane 110.Furthermore it is also possible to show that capture apparatus is clapped in display equipment 130
The image taken the photograph.It should be understood that display equipment 130 can be independent equipment, can also be arranged in commanding apparatus 140.
Commanding apparatus 140 is located at the ground surface end of aircraft 100, can be communicated wirelessly with unmanned plane 110,
For carrying out remote control to unmanned plane 110.Commanding apparatus for example can be remote controler or the APP for being equipped with control unmanned plane
The user terminal of (application program, Application), for example, smart mobile phone, tablet computer etc..In the embodiment of the present invention, lead to
Cross commanding apparatus receive user input, can refer to by remote controler pull out the input units such as wheel, button, button, rocking bar or
User interface (UI) on person's user terminal manipulates unmanned plane.
It should be understood that the above-mentioned name for each component part of aircraft is only the purpose for mark, it is not construed as
Limitation to the embodiment of the present invention.
The propeller of the present embodiment described in detail below, so that those skilled in the art can fully understand the present invention.
Fig. 2 is the structural schematic diagram of propeller provided in this embodiment；Fig. 3 is sectional view along A-A in Fig. 2.
As shown in Figures 2 and 3, propeller 200 (namely propeller 153 in above-described embodiment) may include blade 210
With propeller hub 230, above-mentioned blade 210 links together with propeller hub 230.In some embodiments, blade 210 can be fixed on propeller hub
On 230, such as by the modes such as welding, interference connection or expanded joint blade 210 is fixed on propeller hub 230, it is straight to be formed
The form of paddle.Preferably, blade 210 and propeller hub 230 can form integral piece by integrally formed mode, to improve propeller
200 structural strength.In further embodiments, blade 210 can also be and be removably mounted on propeller hub 230, such as can
By be bolted, be clamped or pin connection etc. in a manner of be mounted on propeller hub 230, so as to adjust according to actual needs
The size of blade 210 or propeller hub 230 is to adapt to the different use environments of propeller 200.In some other embodiment, blade
210 can also be rotatably coupled on propeller hub 230, such as 210 He of blade can be realized by modes such as shaft or hinges
Propeller hub 230 is rotatably connected, to form 200 structure of folding propeller to reduce 200 non-working condition of propeller
When volume, convenient for storage.
Propeller hub 230 is used for connecting with motor, to drive the rotation of entire propeller 200 to realize aircraft by motor
The adjustment of the various flight attitudes such as up and down, hovering.Specifically, in some embodiments, propeller hub 230 can be with motor
Shaft is detachably connected, to drive propeller hub 230 to rotate by the shaft of motor.For example, in a kind of specific embodiment,
Can the inner wall of propeller hub 230 be provided with card slot, the buckle coordinated with card slot is provided in the shaft of motor, to realize electricity
The shaft of machine is detachably connected with propeller hub 230.Certainly, in some other specific embodiment, can also be connected by screw thread
It connects or the shaft of motor and propeller hub 230 is detachably connected by the connection type of other prior arts.In other realities
It applies in example, propeller hub 230 can also be detachably connected with the rotor case of motor, to drive propeller hub 230 to revolve by the rotor case of motor
Turn.For example, the rotor case of motor and propeller hub 230 can also use the card slot that the shaft of above-mentioned motor is used with propeller hub 230
And buckle connecting structure, or other Detachable connection structures in the prior art can also be used.Certainly, propeller hub 230 and electricity
The other modes in the prior art in addition to being detachably connected can also be used to be attached between machine, specifically be referred to religion section
The record of book, technical manual or other common knowledge materials.
Any materials that the prior art may be used in blade 210 are fabricated, and its size can also be according to practical need
It is designed.Six faces of blade 210 may be respectively referred to as connecting pin, free end, leading edge 211, rear 212, suction surface and
Pressure face.In general, connecting pin refers to the side that blade 210 is connect with propeller hub 230, and free end is then opposite with connecting pin
Side；Leading edge 211 and rear 212 are the front and back sides of blade 210 respectively；Suction surface and pressure face are respectively the upper of blade 210
Lower surface.
Specifically, as shown in Fig. 2, its connecting pin of blade 210 being located above is the lower end being connect with propeller hub 230, freely
End is the upper end opposite with propeller hub 230；Its connecting pin of underlying blade 210 is the upper end being connect with propeller hub 230, free end
For the lower end opposite with propeller hub 230.Blade 210 at work, by the driving of motor, around the center of propeller hub 230 revolve by free end
The Plane of rotation (also referred to as paddle disk, a diameter of L1 shown in figure of the paddle disk) for turning to be formed propeller 200, to be carried for aircraft
For drawing force.In some embodiments, direction of rotation 214 and the unlock of blade 210 can also be set in the connecting pin of blade 210
Mark 215, convenient for improving installation effectiveness when installing propeller 200.
It is located at the blade 210 of 230 top of propeller hub in Fig. 2, forward edge (abbreviation leading edge 211) is located at the right side in figure,
The rear part edge (abbreviation rear 212) is located at the left side in figure；Leading edge 211 positioned at the blade 210 of 230 lower section of propeller hub is located at figure
In left side, and its rear 212 is located at the right side in figure.It should be noted that the shape of blade 210 leading edge 211 and rear 212
It can be configured according to the actual needs of aircraft.By taking Fig. 2 as an example, in some optional embodiments, the leading edge of blade 210
211 can be from free end to connecting pin in gradually expansion outward and then again gradually toward the trend of contract, to form a mountain
The same shape in peak.Specifically, the length that leading edge 211 is expanded outward can compared to the length ratio of leading edge 211 toward contract
With bigger, such as the length expanded outward of leading edge shown in Fig. 2 211 accounts for the overwhelming majority of 211 length of entire leading edge.Certainly,
This not expands leading edge 211 the absolute limitation of length outward, and those skilled in the art can be designed according to actual needs.
Correspondingly, rear 212 can also be as leading edge 211 from free end to connecting pin in gradually outward expansion then again gradually it is past
The trend of contract, and the mountain peak that rear 212 is formed can be located at same cross section with the mountain peak of the formation of leading edge 211, to
Blade 210 is set to form a minimum chord length and a maximum chord length.However, you should be able to understand, the shape of leading edge 211 and rear 212
Not necessarily it is designed to that the same curve, or the mountain peak convexed to form must be positioned at same cross section.
It is located at the blade 210 of 230 top of propeller hub and the blade 210 of lower section in Fig. 2, the suction surface of the two is outside table
Face, correspondingly, the pressure face of the two is inner surface.In some embodiments, 210 both side surface of blade can be fabricated to one
Side is the curved surface toward evagination, and side is the curved surface toward indent.At this point, being suction surface toward the surface of evagination, the curved surface toward indent is
Pressure face.In other embodiments, can using blade 210 backwards to a side surface of motor as suction surface, and by blade
210 towards the surface of motor side, as pressure face, (for details, reference can be made to Fig. 3, left-hand face is suction surface, and right lateral surface is
Pressure face).
In order to improve the working efficiency of aircraft, multiple turbulent flow generators 213 are equipped in the suction surface of blade 210, these
Turbulent flow generator 213 is for delaying fluid to be detached from suction surface.Specifically, turbulent flow generator 213 can be can be at this
213 region of turbulent flow generator generates the arbitrary structures of turbulent flow, such as the turbulent flow generator 213 can be in some embodiments
It is protrusion, and the turbulent flow generator 213 can be groove in further embodiments.The present embodiment is more by being arranged in suction surface
A turbulent flow generator 213, the fluid flowed through in this way from blade 210 will generate turbulent flow in turbulent flow generator 213 one by one,
And other regions that will not be except turbulent flow generator 213 generate turbulent flow, turbulent flow meeting caused by these turbulent flow generators 213
Transfer energy to the boundary layer in adverse pressure gradient so that boundary layer obtains corresponding energy and is enough to continue to be attached to the suction of blade
Power face, to the time point for delaying fluid to be detached with suction surface after being contacted with suction surface, to reduce the air that blade 210 is subject to
Resistance, and then reduce torque, improve the efficiency under the working efficiency of propeller 200, such as hovering operating mode.Following table one specifically illustrates
It is provided with the propeller 200A of turbulent flow generator 213 and is not provided with the work ginseng of the propeller 200B of turbulent flow generator 213
Number comparative situation.
Table one
According to test, in a kind of specific embodiment, under hovering section 350g pulling force, there is the spiral shell of turbulent flow generator
It is higher than the hovering efficiency of the propeller of not turbulent flow generator by about 4.6% to revolve paddle.
The present embodiment can also avoid turbulent flow premature disengagement so that boundary layer flow by the way that multiple turbulent flow generators 213 are arranged
Body is attached to solid structure surface, and delay separation reduces resistance when propeller works.
Further, with reference to figure 4 (Fig. 4 is the partial enlarged view of the positions F in Fig. 2), in some embodiments, adjacent two
Setting can be spaced between turbulent flow generator 213, to occur to reduce the two turbulent flows by spacing distance between the two
The turbulent flow formed on device 213 influences, to improve the synergistic effect of multiple turbulent flow generators 213, to delay to flow to improve between each other
The ability that body is detached from suction surface.Certainly, between above-mentioned two neighboring turbulent flow generator 213 interval setting not be it is necessary,
Only it is that one kind is preferable to provide, it can also be by two neighboring turbulent flow generator 213 closely in some other embodiment
Setting, as long as the two turbulent flow generators 213 can respectively generate turbulent flow.
Below from multiple angles pair such as the shape of turbulent flow generator 213, quantity, size, arrangement mode and generation type
Some achievable modes of turbulent flow generator 213 are illustrated.
In some embodiments, the cross section of turbulent flow generator 213 can be round or ellipse.Fig. 5 a show rapids
The cross section of flow-generator 213 is circular embodiment, and Figure 5b shows that the realities that the cross section of turbulent flow generator 213 is ellipse
Apply example.In specific processing, circular protrusions either circular pit or be to form elliptical shaped lobes or ellipse can be formed
Shape pit.Further, more preferably, it can be 210 smallest chord of blade that cross section, which is the diameter of circular turbulent flow generator 213,
Long 2% to 7%.When the diameter design of round turbulent flow generator 213 be above-mentioned numberical range when, can obtain delay fluid from
The effect of suction surface disengaging time.It is more preferably the 2% of minimum chord length by the circular diameter design of turbulent flow generator 213
To 4%, the effect for delaying fluid from suction surface disengaging time can have not only been obtained in this way, but also did not influenced other performances of blade 210.
In further embodiments, the cross section of turbulent flow generator 213 can also be polygon, such as pentagon or six
Side shape.Fig. 5 c show that the cross section of turbulent flow generator 213 is pentagonal embodiment；Fig. 5 d show turbulent flow generator 213
Cross section be hexagon embodiment.In specific processing, pentagonal protrusion can be formed on the suction surface of blade 210
Or pit is as turbulent flow generator 213；The protrusion or pit that hexagon can also be formed on the suction surface of blade 210 are made
For turbulent flow generator 213.More preferably, the apex angle of polygon can be with round-corner transition, to make blade 210 meet corresponding stream
Mechanics improve its working efficiency.Fig. 5 e show that the cross section of turbulent flow generator 213 is the implementation of hexagon with rounded corners
Example.It should be understood that the apex angle round-corner transition of above-mentioned polygon may include：The equal round-corner transition of all apex angles of polygon, Yi Jiqi
In certain apex angle round-corner transitions and some other apex angle does not have round-corner transition etc..
It should be noted that in the embodiment above, the shape of the cross section of multiple turbulent flow generators 213 can be homogeneous
Together, but also it is not excluded for the different situation of the cross-sectional shape of multiple turbulent flow generators 213.It such as in some embodiments, can be with
It is the round combination with ellipse, can also be round and polygon combination, or can also be ellipse and polygon
Combination, naturally it is also possible to be the combination of round ellipse and polygon three.Fig. 6 a and 6b show two different matrix forms
Arrangement turbulent flow generator 213, wherein Fig. 6 a show that cross section is the combination shape of round and ellipse turbulent flow generator 213
Formula；Fig. 6 b show that cross section is the combining form of the turbulent flow generator 213 of round, ellipse and hexagon.
The quantity of above-mentioned multiple turbulent flow generators 213 can occur according to the size and/or turbulent flow of 210 suction surface of blade
The cross sectional dimensions of device 213 determines, such as in some embodiments, the number of turbulent flow generator 213 can be designed to much
In 50.Specifically, the number of turbulent flow generator 213 can be 50,80,100 or 1000.By so most
Time of the synergistic effect to delay fluid to be detached from suction surface caused by the turbulent flow generator 213 of amount.
Just as described above, in some embodiments, multiple turbulent flow generators 213 can be as shown in Fig. 2, Fig. 6 a and Fig. 6 b
As in matrix form arrangement namely multiple turbulent flow generators 213 have multirow and more along chord length direction and paddle disk directional spreding
Row.Can include at least 5 rows along the chord length direction of blade 210 specifically in the ranks number of design matrix formula；It can also be edge
The paddle disk direction of blade 210 includes at least 10 row.For example, in an alternative embodiment, multiple turbulent flow generators 213 can be with
5 rows are set along the chord length direction of blade 210, along 10 row of the paddle disk direction of blade 210 setting.In addition it is also necessary to explanation, on
The every a line or each row for stating matrix form arrangement can be with close alignments, and can also slightly be staggered certain distance.Above by
The turbulent flow generator 213 that matrix form is arranged on the suction surface of blade 210, can not only obtain and delay the fluid to be detached from suction surface
Effect, and handling ease.
As fig. 6 c, in further embodiments, these turbulent flow generators 213 radial can be arranged.Passing through will
Turbulent flow generator 213 be designed to it is radial, then when on 210 suction surface of blade some regional fluid have stronger separation trend and
When the separation trend on periphery is weaker, the stronger region of separation trend can be made to be disposed with more turbulent flow generators 213, so as to inhale
The effect that power face different zones delay fluid to detach is more balanced.
It, in some embodiments can also be close to 210 connecting pin of blade specifically when arranging multiple turbulent flow generators 213
The more turbulent flow generators 213 of location arrangements, that is to say, close to 210 free end of blade turbulent flow generator 213 quantity it is few
In the quantity of the turbulent flow generator 213 close to 210 connecting pin of blade, specifically referring to Fig. 7 a, (Fig. 7 a show that blade 210 connects
End is disposed with more turbulent flow generators 213 compared with free end).It arranges in this way, it can be in the stronger region of fluid separation trend
It arranges more turbulent flow generators 213, enables adaptation to flow regime of the fluid on blade 210, preferably prolonged with obtaining
The effect that the body that flows slowly detaches.
It in further embodiments, can also be in the more turbulent flow generators of location arrangements close to 210 leading edge 211 of blade
213, it that is to say, be more than the turbulent flow generation close to 210 rear 212 of blade close to the quantity of the turbulent flow generator 213 of paddle leading edge 211
The quantity of device 213, specifically referring to Fig. 7 b, (Fig. 7 b show that 210 leading edge 211 of blade is disposed with more turbulent flow hairs compared with rear 212
Raw device 213).It arranges in this way, can arrange more turbulent flow generators 213 in the stronger region of fluid separation trend, from
And flow regime of the fluid on blade 210 is can adapt to, to obtain the effect for preferably delaying fluid to detach.
It also should be noted that turbulent flow generator 213 can be formed in suction by any way of the prior art
On face, such as molding, forging etc..In some embodiments, it can be formed on suction surface by way of face coat above-mentioned
Turbulent flow generator 213.It is simple for process by way of face coat, it is efficient.
It is arranged in different forms on the suction surface of blade 210 above by by multiple turbulent flow generators 213, thus by
The region of these turbulent flow generators 213 distribution constitutes turbulent region 216 (being indicated by label 116 in Fig. 2).
Referring to Fig.2, in some embodiments, length L2 of the turbulent region 216 along 200 paddle disk direction of propeller is more than along paddle
The length H2 in 210 chord length direction of leaf.Certainly, in further embodiments, can also be needed according to other to turbulent region 216
Size is configured.For example, length L2 of the turbulent region 216 along paddle disk direction is equal to or less than the length along chord length direction
H2。
Specifically when turbulent region 216 is arranged along the length L2 in 200 paddle disk direction of propeller, in some optional embodiments
In, the length L2 of turbulent region 216 can be set to the 40% to 90% of 200 paddle disk radius (L1/2) of propeller.It is more excellent
Choosing, the length L2 of turbulent region 216 is the 70% to 80% of 200 paddle disk radius of propeller.
And when specifically setting turbulent region 216 is along the length H2 in 210 chord length direction of blade, in some optional embodiments
In, the length H2 of turbulent region 216 can be set to the 30% to 75% of the minimum chord length of blade 210.It is more preferred, turbulent flow
The length H2 in region 216 is the 40% to 60% of the minimum chord length of blade 210.
Next, being described from relative position this angle of turbulent region 216 on 210 suction surface of blade.
Fig. 8 a (Fig. 8 a show the schematic diagram of turbulent region 216 and 212 position relationship of leading edge 211 and rear) are please referred to,
Spacing H3 (the first pre-determined distance), the rear with blade 210 are provided between turbulent region 216 and the leading edge 211 of blade 210
Spacing H4 (the second pre-determined distance) is provided between 212, wherein H3 can be less than or equal to H4, but it is preferable to H3
More than H4.
Below refering to Fig. 8 b (Fig. 8 b show the schematic diagram of turbulent region 216 and free end and connecting pin position relationship),
Spacing L3 (third pre-determined distance), the connecting pin with blade 210 are provided between turbulent region 216 and the free end of blade 210
Between be provided with spacing L4 (the 4th pre-determined distance), wherein L3 can be more than or equal to L4, but it is preferable to L3 is less than
L4。
It, can by being adjusted to turbulent region 216 and leading edge 211, rear 212, free end and the spacing of connecting pin
So that fluid with 210 suction surface disengaging time of blade delaying as possible, to improve the working efficiency of propeller 200.More preferably
A kind of embodiment be that the spacing H3 of turbulent region 216 and leading edge 211 is more than the spacing H4 with rear 212, and turbulent area
The spacing L3 of domain 216 and free end is less than the spacing L4 with connecting pin.
More specifically, several when can be according to propeller works in actual design turbulent region when position in blade
Speed conditions, for example, hovering when rotating speed, preceding winged acceleration when rotating speed, by Fluid Mechanics Computation emulation (CFD,
Computational Fluid Dynamics), fluid mechanical emulation calculating is carried out to above-mentioned speed conditions, then pass through post-processing
(Post-processing) determine that the specific area of flow separation phenomenon occurs for the blade of the propeller suction surface under different rotating speeds
Domain, and set the region to turbulent region, to form above-mentioned turbulent flow generator in the area.
Next from the area of turbulent region 216, this angle is described.
The area of turbulent region 216 can be configured by technical staff according to actual needs, but it is preferable to rapid
The area in stream region 216 is more than 1/8th of the area of suction surface, so that turbulent region 216 is sized to and blade 210
Suction surface match, to play the role of delaying fluid disengaging time.It is highly preferred that the area of turbulent region 216 is more than
The a quarter of the area of suction surface further delays fluid to be detached from suction surface in this way, the range of turbulent flow generation can be improved
Time, improve propeller 200 working efficiency.
Meanwhile above-mentioned each embodiment can separately from and can combine in the case of no contradiction it is applicable, and
The present embodiment does not limit a combination thereof quantity and combining form, and the form that these are individual and combination is later is in the guarantor of the present invention
It protects within range.
In several embodiments provided by the present invention, it should be understood that disclosed relevant apparatus and method, Ke Yitong
Other modes are crossed to realize.For example, the apparatus embodiments described above are merely exemplary, for example, the module or list
Member division, only a kind of division of logic function, formula that in actual implementation, there may be another division manner, such as multiple units or
Component can be combined or can be integrated into another system, or some features can be ignored or not executed.Another point is shown
The mutual coupling, direct-coupling or communication connection shown or discussed can be by some interfaces, between device or unit
Coupling or communication connection are connect, can be electrical, machinery or other forms.
The unit illustrated as separating component may or may not be physically separated, aobvious as unit
The component shown may or may not be physical unit, you can be located at a place, or may be distributed over multiple
In network element.Some or all of unit therein can be selected according to the actual needs to realize the mesh of this embodiment scheme
's.
In addition, each functional unit in each embodiment of the present invention can be integrated in a processing unit, it can also
It is that each unit physically exists alone, it can also be during two or more units be integrated in one unit.Above-mentioned integrated list
The form that hardware had both may be used in member is realized, can also be realized in the form of SFU software functional unit.
If the integrated unit is realized in the form of SFU software functional unit and sells or use as independent product
When, it can be stored in a computer read/write memory medium.Based on this understanding, technical scheme of the present invention is substantially
The all or part of the part that contributes to existing technology or the technical solution can be in the form of software products in other words
It embodies, which is stored in a storage medium, including some instructions are used so that computer disposal
Device 101 (processor) performs all or part of the steps of the method described in the various embodiments of the present invention.And storage medium above-mentioned
Including：USB flash disk, mobile hard disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random
Access Memory), the various media that can store program code such as disk or CD.
Example the above is only the implementation of the present invention is not intended to limit the scope of the invention, every to utilize this hair
Equivalent structure or equivalent flow shift made by bright specification and accompanying drawing content is applied directly or indirectly in other relevant skills
Art field, is included within the scope of the present invention.
Finally it should be noted that：The above embodiments are only used to illustrate the technical solution of the present invention., rather than its limitations；To the greatest extent
Present invention has been described in detail with reference to the aforementioned embodiments for pipe, it will be understood by those of ordinary skill in the art that：Its according to
So can with technical scheme described in the above embodiments is modified, either to which part or all technical features into
Row equivalent replacement；And these modifications or replacements, various embodiments of the present invention technology that it does not separate the essence of the corresponding technical solution
The range of scheme.
Claims (33)
1. a kind of propeller of aircraft, which is characterized in that including：Propeller hub and blade；
The blade is connect with the propeller hub, and the blade includes suction surface and the pressure face opposite with suction surface；
Wherein, the suction surface is equipped with multiple turbulent flow generators, for delaying fluid to be detached from the suction surface；
The turbulent flow close to the blade connecting pin is less than close to the quantity of the turbulent flow generator of the blade free end
The quantity of generator；
It is more than the turbulent flow generation close to the blade rear close to the quantity of the up-front turbulent flow generator of the blade
The quantity of device.
2. propeller according to claim 1, which is characterized in that the turbulent flow generator is protrusion or groove.
3. propeller according to claim 1, which is characterized in that be spaced and set between the two neighboring turbulent flow generator
It sets.
4. propeller according to claim 1, which is characterized in that the cross section of the turbulent flow generator is round or ellipse
It is round.
5. propeller according to claim 4, which is characterized in that circular a diameter of blade minimum chord length
2% to 7%.
6. propeller according to claim 4, which is characterized in that circular a diameter of blade minimum chord length
2% to 4%.
7. propeller according to claim 1, which is characterized in that the cross section of the turbulent flow generator is polygon.
8. propeller according to claim 7, which is characterized in that the apex angle round-corner transition of the polygon.
9. according to claim 1-8 any one of them propellers, which is characterized in that the turbulent flow generator is no less than 50.
10. according to claim 1-8 any one of them propellers, which is characterized in that multiple turbulent flow generators are in matrix
Formula is arranged.
11. propeller according to claim 10, which is characterized in that string of multiple turbulent flow generators along the blade
Length direction includes at least 5 rows.
12. propeller according to claim 10, which is characterized in that paddle of multiple turbulent flow generators along the blade
Disk direction includes at least 10 row.
13. according to claim 1-8 any one of them propellers, which is characterized in that multiple turbulent flow generators are in radiation
Shape is arranged.
14. according to claim 1-8 any one of them propellers, which is characterized in that the region of the turbulent flow generator distribution
For turbulent region.
15. propeller according to claim 14, which is characterized in that the leading edge of the turbulent region and the blade has
First pre-determined distance；The rear of the turbulent region and the blade has the second pre-determined distance.
16. propeller according to claim 15, which is characterized in that second pre-determined distance be more than first it is default away from
From.
17. propeller according to claim 15, which is characterized in that the free ending tool of the turbulent region and the blade
There is third pre-determined distance；The connecting pin of the turbulent region and the blade has the 4th pre-determined distance.
18. propeller according to claim 17, which is characterized in that the 4th pre-determined distance is default more than the third
Distance.
19. propeller according to claim 14, which is characterized in that the turbulent region is along the propeller paddle disk direction
Length be more than the turbulent region along the chord of blade length direction length.
20. propeller according to claim 14, which is characterized in that the turbulent region is along the propeller paddle disk direction
Length be the propeller paddle disk radius 40% to 90%.
21. propeller according to claim 20, which is characterized in that the turbulent region is along the propeller paddle disk direction
Length be the propeller paddle disk radius 70% to 80%.
22. propeller according to claim 14, which is characterized in that the turbulent region is along the chord of blade length direction
Length is the 30% to 75% of the blade minimum chord length.
23. propeller according to claim 22, which is characterized in that the turbulent region is along the chord of blade length direction
Length is the 40% to 60% of the blade minimum chord length.
24. propeller according to claim 14, which is characterized in that the area of the turbulent region is more than the suction surface
Area 1/8th.
25. propeller according to claim 24, which is characterized in that the area of the turbulent region is more than the suction surface
Area a quarter.
26. according to claim 1-8 any one of them propellers, which is characterized in that the turbulent flow generator is applied by surface
The mode of layer is formed in the suction surface.
27. according to claim 1-8 any one of them propellers, which is characterized in that the suction surface be the blade outward
Convex curved surface, the turbulent flow generator are set to the side of the curved surface.
28. according to claim 1-8 any one of them propellers, which is characterized in that the blade is fixed with the propeller hub to be connected
It connects or is rotatablely connected.
29. according to claim 1-8 any one of them propellers, which is characterized in that the blade is integrated with the propeller hub
Part.
30. a kind of power suit, which is characterized in that including：Claim 1-29 any one of them propeller and motor；
The motor is connect with the propeller, for driving the propeller rotational.
31. power according to claim 30 suit, which is characterized in that the pressure face of the propeller is towards the motor
Setting, the suction surface of the propeller are arranged back to the motor.
32. power suit according to claim 30, which is characterized in that
The shaft of the motor and the propeller hub of the propeller are detachably connected, and the shaft drives the propeller hub rotation；
Alternatively,
The rotor case of the motor and the propeller hub of the propeller are detachably connected, and the rotor case drives the propeller hub rotation
Turn.
33. a kind of unmanned plane, which is characterized in that including：Rack and claim 30-32 any one of them power suit；
The power suit is mounted in the rack.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/CN2017/071180 WO2018129721A1 (en) | 2017-01-13 | 2017-01-13 | Propeller of aircraft, power set and unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107074344A CN107074344A (en) | 2017-08-18 |
| CN107074344B true CN107074344B (en) | 2018-09-25 |
Family
ID=59613583
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201780000122.2A Expired - Fee Related CN107074344B (en) | 2017-01-13 | 2017-01-13 | Propeller, power suit and the unmanned plane of aircraft |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN107074344B (en) |
| WO (1) | WO2018129721A1 (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019127028A1 (en) * | 2017-12-26 | 2019-07-04 | 深圳市大疆创新科技有限公司 | Propeller, power assembly and aircraft |
| WO2019227268A1 (en) * | 2018-05-28 | 2019-12-05 | 深圳市大疆创新科技有限公司 | Propeller assembly, power assembly and aircraft |
| CN109018382B (en) * | 2018-08-07 | 2021-08-13 | 江西华友机械有限公司 | Aircraft engine deformation fairing structure |
| CN109606645A (en) * | 2018-12-28 | 2019-04-12 | 成都纵横大鹏无人机科技有限公司 | Paddle blade structure and unmanned plane |
| CN112572766A (en) * | 2020-12-17 | 2021-03-30 | 重庆工程职业技术学院 | Water vapor propeller of unmanned aerial vehicle on water and processing technology thereof |
| CN114084327A (en) * | 2021-11-26 | 2022-02-25 | 大连海事大学 | Marine propeller blade structure |
| CN116409458A (en) * | 2021-12-29 | 2023-07-11 | 北京三快在线科技有限公司 | Propeller and aircraft |
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Also Published As
| Publication number | Publication date |
|---|---|
| WO2018129721A1 (en) | 2018-07-19 |
| CN107074344A (en) | 2017-08-18 |
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