CN109923036A - Propeller, Power Component and aircraft - Google Patents

Propeller, Power Component and aircraft Download PDF

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Publication number
CN109923036A
CN109923036A CN201780069690.8A CN201780069690A CN109923036A CN 109923036 A CN109923036 A CN 109923036A CN 201780069690 A CN201780069690 A CN 201780069690A CN 109923036 A CN109923036 A CN 109923036A
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China
Prior art keywords
blade
propeller
paddle disk
paddle
center
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CN201780069690.8A
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Chinese (zh)
Inventor
刘峰
陈鹏
邓涛
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SZ DJI Technology Co Ltd
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SZ DJI Technology Co Ltd
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Publication of CN109923036A publication Critical patent/CN109923036A/en
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    • 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
    • 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

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Toys (AREA)

Abstract

A kind of propeller, Power Component and aircraft, wherein propeller includes paddle seat (6) and the blade (1) being connected on paddle seat；It is 22.59 ° ± 2.5 ° that blade (1), which is apart the angle of attack at the 45.8% of paddle disk radius at the center of the paddle disk formed with propeller (6), and chord length is 26.98mm ± 5mm；It is 19.57 ° ± 2.5 ° that blade (1), which is apart the angle of attack at the 62.5% of paddle disk radius at the center of the paddle disk formed with propeller (6), and chord length is 21.91mm ± 5mm；It is 16.56 ° ± 2.5 ° that blade (1), which is apart the angle of attack at the 79.2% of paddle disk radius at the center of the paddle disk formed with propeller (6), and chord length is 17.64mm ± 5mm.The propeller, Power Component and aircraft can reduce the resistance of propeller rotational, to further decrease the flight resistance of aircraft, improve the flying speed and flight efficiency of aircraft, improve the flying quality of aircraft by optimizing the structure of propeller.

Description

Propeller, Power Component and aircraft Technical field
The present invention relates to propeller arrangement technology more particularly to a kind of propellers, Power Component and aircraft.
Background technique
Carry-on propeller is used to convert thrust or lift for the rotation of shaft in motor or engine as the important Primary Component of aircraft.
Propeller in the prior art, blade outer shape are in rectangle mostly, and resistance is big when leading to its flight, low efficiency, lead to that the flying speed of aircraft is small, endurance distance is short, have seriously affected the flying quality of aircraft.
Summary of the invention
The present invention provides a kind of propeller, Power Component and aircraft and, to optimize the structure of propeller, improves the flying quality of aircraft to solve drawbacks described above in the prior art.
One aspect of the present invention provides a kind of propeller, including blade, and the blade rotates to form paddle disk；
The blade be apart with the spiral shell paddle disk radius 45.8% at the angle of attack be 22.59 ° ± 2.5 °, chord length be 26.98mm ± 5mm；
The blade with the propeller shape at the center of paddle disk be apart the angle of attack at the 62.5% of paddle disk radius be 19.57 ° ± 2.5 °, chord length is 21.91mm ± 5mm；
The blade with the propeller shape at the center of paddle disk be apart the angle of attack at the 79.2% of paddle disk radius be 16.56 ° ± 2.5 °, chord length is 17.64mm ± 5mm.
Propeller as described above, the propeller shape at paddle disk diameter be 240mm；
The blade with the propeller shape at the center of paddle disk be apart at 55mm The angle of attack be 22.59 °, chord length 26.98mm；
The blade with the propeller shape at the center of paddle disk be apart the angle of attack at 75mm be 19.57 °, chord length 21.91mm；
The blade with the propeller shape at the center of paddle disk be apart the angle of attack at 95mm be 16.56 °, chord length 17.64mm.
Propeller as described above,
The blade with the propeller shape at the center of paddle disk be apart the angle of attack at the 29.2% of paddle disk radius be 24.74 ° ± 2.5 °, chord length is 33.58mm ± 5mm.
Propeller as described above, the propeller shape at paddle disk diameter be 240mm；
The blade with the propeller shape at the center of paddle disk be apart the angle of attack at 35mm be 24.74 °, chord length 33.58mm.
Propeller as described above,
The blade with the propeller shape at the center of paddle disk be apart the angle of attack at the 95.8% of paddle disk radius be 12.80 ° ± 2.5 °, chord length is 13.83mm ± 5mm.
Propeller as described above, the propeller shape at paddle disk diameter be 240mm；
The blade with the propeller shape at the center of paddle disk be apart the angle of attack at 115mm be 12.80 °, chord length 13.83mm.
Propeller as described above, the quantity of the blade are two, and two blades are centrosymmetric about the center of paddle disk.
Propeller as described above, one end from the blade close to one end of the paddle disk center to the blade far from the paddle disk center, the thickness of the blade are gradually reduced.
Propeller as described above, the blade includes blade face upward, blade back directed downwardly, and the second lateral margin for being connected to the first lateral margin between the side on the blade back and the blade face and being connected between the other side on the blade back and the blade face, first lateral margin are located at below second lateral margin；The blade back and the blade face are curved surface.
Propeller as described above, including at least two blades, the propeller further include connecting The paddle seat of the blade is connect, at least two blade is circumferentially uniformly distributed along the paddle seat.
Propeller as described above, first lateral margin include that curved first outwardly protruded is arched upward portion, and second lateral margin includes that curved second outwardly protruded is arched upward portion；Described first arches upward portion and second portion of arching upward is close to one end that the blade is connected with the paddle seat；And described first the protrusion degree for arching upward portion be greater than the described second protrusion degree for arching upward portion.
The screw pitch of propeller as described above is 5.5 inches.
Another aspect of the present invention also provides a kind of Power Component, including actuator and described in any item propellers as above, the propeller are connect by paddle seat with the actuator.
Power Component as described above, the actuator are motor, the KV value of the motor is 750~850 turns/(minute volt).
Another aspect of the invention provides a kind of aircraft, including fuselage, further includes at least one Power Component as described above, and the Power Component is connect with the fuselage.
The aircraft includes multiple Power Components, and the steering of the multiple Power Component is different.
Propeller, Power Component and aircraft provided by the invention, due to the blade with the propeller shape at the center of paddle disk be apart the angle of attack at the 45.8% of paddle disk radius be 22.59 ° ± 2.5 °, chord length is 26.98mm ± 5mm；The blade with the propeller shape at the center of paddle disk be apart the angle of attack at the 62.5% of paddle disk radius be 19.57 ° ± 2.5 °, chord length is 21.91mm ± 5mm；The blade with the propeller shape at the center of paddle disk be apart the angle of attack at the 79.2% of paddle disk radius be 16.56 ° ± 2.5 °, chord length is 17.64mm ± 5mm.Therefore it can reduce the resistance of propeller during rotation, reduce the flight resistance during aircraft flight, improve flight efficiency, increase endurance distance, improve the flying quality of aircraft.
Detailed description of the invention
Fig. 1 is the perspective view for the propeller that the embodiment of the present invention one provides；
Fig. 2 is the main view of propeller shown in Fig. 1；
Fig. 3 is the left view of propeller shown in Fig. 1；
Fig. 4 is propeller in Fig. 2 along the diagrammatic cross-section of line A-A；
Fig. 5 is propeller in Fig. 2 along the diagrammatic cross-section of line B-B；
Fig. 6 is propeller in Fig. 2 along the diagrammatic cross-section of line C-C；
Fig. 7 is propeller in Fig. 2 along the diagrammatic cross-section of line D-D；
Fig. 8 is propeller in Fig. 2 along the diagrammatic cross-section of E-E line.
Appended drawing reference:
1- blade；The blade face 2-；3- blade back
The first lateral margin 4-；The second lateral margin 5-；6- paddle seat；
401- first arches upward portion；501- second arches upward portion.
Specific embodiment
In order to make the object, technical scheme and advantages of the embodiment of the invention clearer, following will be combined with the drawings in the embodiments of the present invention, technical scheme in the embodiment of the invention is clearly and completely described, obviously, described embodiments are some of the embodiments of the present invention, instead of all the embodiments.Based on the embodiments of the present invention, every other embodiment obtained by those of ordinary skill in the art without making creative efforts, shall fall within the protection scope of the present invention.
It should be noted that it can be directly on another component or there may also be components placed in the middle when component is referred to as " being fixed on " another component.When a component is considered as " connection " another component, it can be directly to another component or may be simultaneously present component placed in the middle.
Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs.Term as used herein in the specification of the present invention, which is only for the purpose of describing specific embodiments, is not intended to limit the present invention.Term " and or " used herein includes any and all combinations of one or more related listed items.
Embodiment one
The embodiment of the present invention one provides a kind of propeller.Propeller in the present embodiment, can be applied to aircraft, and propeller may include: paddle seat and the blade that is connected on paddle seat.This implementation In the propeller that example provides, blade can be an integral molding structure with paddle seat, or interconnection can also be realized otherwise, such as it can be fixed by way of welding, or it can be fixedly connected by dismountable connector, such as the fixation that is spirally connected, or connection etc. is realized by other connectors.Here, the present embodiment is not especially limited.
In the present embodiment, propeller can be positive paddle or anti-paddle, and so-called positive paddle refers to rotating clockwise and generate the propeller of lift from the point of view of (alternatively, in terms of from actuator such as motor tail portion to motor head direction) overlook aircraft；So-called anti-paddle refers to (referring in terms of from motor tail portion to motor head direction) from the point of view of vertical view aircraft, rotates and generate the propeller of lift counterclockwise.It is symmetrical for mirror surface between the positive structure of paddle and the structure of anti-paddle, only the structure of propeller is illustrated by taking the structure of positive paddle as an example in the present embodiment, those skilled in the art's mode according to provided by the present embodiment, which is extended, obtains the structure of anti-paddle.
The perspective view of blade in the propeller that Fig. 1 provides for the embodiment of the present invention one；Fig. 2 is the main view of blade shown in Fig. 1；Fig. 4 is blade in Fig. 1 along the diagrammatic cross-section of line A-A；Fig. 5 is blade in Fig. 1 along the diagrammatic cross-section of line B-B；Fig. 6 is blade in Fig. 1 along the diagrammatic cross-section of line C-C；Fig. 7 is blade in Fig. 1 along the diagrammatic cross-section of line D-D；Fig. 8 is blade in Fig. 1 along the diagrammatic cross-section of E-E line.The present embodiment improves the size at five sections of blade, wherein the improvement carried out to the size at section B-B, the section C-C and the section D-D is mostly important.
When the paddle seat of propeller provided by the present embodiment drives blade rotation, the circle formed in rotary course, referred to as paddle disk, the center of the circle are known as the center of paddle disk, which is known as the diameter of paddle disk.For split type blade 1, the radius of paddle disk can be greater than the length of blade 1.The quantity of blade 1 can be two, or more than two, in the present embodiment, it is preferred that the quantity of blade 1 is two, and two blades 1 can be centrosymmetric about the center of paddle disk, and the balance of propeller can be improved as a result,.For the propeller of integral type, the radius of paddle disk is the radius of propeller.
As shown in Figure 2 and Figure 5, blade 1 with propeller shape at the center of paddle disk be apart at the 45.8% of paddle disk radius, that is: at the section B-B apart from paddle disk center L2 as shown in Figure 2, angle of attack A2 of blade 1 is 22.59 ° ± 2.5 ° at this, and chord length D2 is 26.98mm ± 5mm.Wherein, chord length is the length that section of the blade 1 at this projects in the horizontal direction, and the angle of attack is the angle of the string wing and gas direction of flow.
As shown in Figure 2 and Figure 6, blade 1 with propeller shape at the center of paddle disk be apart at the 62.5% of paddle disk radius, that is: at the section C-C apart from paddle disk center L3 as shown in Figure 2, angle of attack A3 of blade 1 is 19.57 ° ± 2.5 ° at this, and chord length D3 is 21.91mm ± 5mm.
As shown in Figure 2 and Figure 7, blade 1 with propeller shape at the center of paddle disk be apart at the 79.2% of paddle disk radius, that is: at the section D-D apart from paddle disk center L4 as shown in Figure 2, it is 16.56 ° ± 2.5 ° that angle of attack of blade 1, which is A4, at this, and chord length D4 is 17.64mm ± 5mm.
The present embodiment passes through to the chord length in above three section in blade 1 and the setting of the angle of attack, the blade for having specific shape is limited by above-mentioned parameter, it is smaller to have the resistance of the propeller of this kind of blade during rotation, the flying speed and flight efficiency of aircraft are high, and increases endurance distance under certain power conditions supply, improve the flying quality of aircraft.
Based on the above technical solution, the angle of attack chord of Section A-A in blade 1 and the section E-E length can also be optimized, to further decrease the air drag of propeller during rotation.
As shown in Fig. 2 and Fig. 6 Fig. 4, blade 1 with propeller shape at the center of paddle disk be apart at the 29.2% of paddle disk radius, that is: at the Section A-A apart from paddle disk center L1 as shown in Figure 2, angle of attack of blade 1 is 24.74 ° ± 2.5 ° at this, and chord length is 33.58mm ± 5mm.
As shown in Figure 2 and Figure 8, blade 1 with propeller shape at the center of paddle disk be apart at the 95.8% of paddle disk radius, that is: at the section E-E apart from paddle disk center L5 as shown in Figure 2, angle of attack of blade 1 is 12.80 ° ± 2.5 ° at this, and chord length is 13.83mm ± 5mm.
Certainly, it will be appreciated by persons skilled in the art that above-mentioned Section A-A, section B-B, the section C-C, the section D-D and the position in the section E-E can slightly change.
For above-mentioned technical proposal, the present embodiment provides a kind of specific propeller, it is 240mm which, which is formed by paddle disk diameter, and the distance of paddle disk center to 1 end of blade is the half of paddle disk diameter, and the distance of Ji Jiang disk center to 1 end of blade is 115mm.
By taking paddle disk diameter 240mm as an example, blade 1 with propeller shape at paddle disk center be apart (i.e. the 50% of 115mm) at 55mm the angle of attack be 22.59 °, chord length 26.98mm；Blade 1 with propeller shape at paddle disk center be apart (i.e. the 66.7% of 115mm) at 75mm the angle of attack be 19.57 °, chord length 21.91mm；Blade 1 with propeller shape at Paddle disk center be apart (i.e. the 79.2% of 115mm) at 95mm the angle of attack be 16.56 °, chord length 17.64mm.
Further, with paddle disk center distance 35mm (i.e. the 33.3% of 115mm) at, the angle of attack of blade 1 is 24.74 °, chord length 33.58mm.With paddle disk center distance 115mm (i.e. the 100% of 115mm) at, the angle of attack of blade 1 is 12.80 °, chord length 13.83mm.
It is understood that because Section A-A, section B-B, the section C-C, the section D-D and the position in the section E-E can slightly change, therefore correspondingly, resulting angle of attack chord long value can accordingly change at Section A-A, section B-B, the section C-C, the section D-D and the section E-E.
The setting of the chord length in above-mentioned each section and the angle of attack can be set with the size of paddle disk.Paddle seat 6 can be cylindrical, also, can install actuator at cylindric 6 center of paddle seat, and blade 1 can be in long strip, and blade 1 can be integrally formed with paddle seat 6 or be connect by connector, and radially extending along paddle seat.Specifically, actuator can be motor, the shaft of motor is fixedly connected with the center of paddle seat 6, and directly to transmit torque, actuator can drive paddle seat 6 to rotate, and paddle seat 6 then drives blade 1 to rotate, and then generate thrust or lift.
Above-mentioned propeller provided by the present embodiment, by comparing test with propeller in the prior art, according to table one, under identical revolving speed, pulling force provided by the present embodiment is bigger, namely: under lesser revolving speed, with bigger pulling force, to improve the power of propeller, kwh loss is reduced, increases endurance distance.Particularly, propeller provided in this embodiment can significantly improve pulling force, guarantee enough power while extending cruise duration under the High aititude region or the biggish extreme case of low altitude area take-off weight that density reduces, and improve flying quality.
The reduced parameter of propeller and the prior art provided by one the present embodiment of table
Fig. 3 is the left view of blade shown in Fig. 1；As shown in Figure 1 to Figure 3, the blade of propeller in the present embodiment, it may include blade back 3 upward, blade face directed downwardly 2, and the second lateral margin 5 for being connected to the first lateral margin 4 between the side on blade back 3 and blade face 2 and being connected between the other side on blade back 3 and blade face 2, the first lateral margin 4 are located at 5 lower section of the second lateral margin；Blade back 3 and blade face 2 are curved surface.
Wherein, blade back 3 is aircraft in flight course, the one side of blade 1 upward；Blade face 2 is aircraft in flight course, the one side directed downwardly of blade 1.As shown in Figure 1, blade back 3 and blade face 2 are curved surface, and curved trend are as follows: when blade 1 is generally in horizontality, the location of first lateral margin 4 is lower than the location of the second lateral margin 5, therefore can reduce the resistance of air, the pulling force of raising blade 1.
First lateral margin 4 may include that curved first outwardly protruded is arched upward portion 401, thus can further improve the pulling force of blade 1, and the first rest part for arching upward portion 401 and the first lateral margin 4 is to be connected smoothly.On the length direction of entire blade 1, one end relative to blade 1 far from paddle seat 6, first arches upward one end that portion 401 is connected closer to blade 1 with paddle seat 6.First portion 401 that arches upward not only arches upward towards the side of blade 1, while can also arch upward downwards, i.e., arches upward towards the direction where blade face 2, and can be formed and be connected smoothly with blade face 2.
Second lateral margin 5 may include that curved second outwardly protruded is arched upward portion 501, thus can further improve the pulling force of blade 1, and the second rest part for arching upward portion 501 and the second lateral margin 5 is to be connected smoothly.On the length direction of entire blade 1, one end relative to blade 1 far from paddle seat 6, second arches upward one end that portion 501 is connected closer to blade 1 with paddle seat 6.
In the present embodiment, the first protrusion degree for arching upward portion 401 can be greater than the second protrusion degree that arch upward portion 501.First arches upward the vertex in portion 401 and the second vertex for arching upward portion 501 can be located substantially on the same cross section of blade 1.Also, it is smooth transition at each position in the surface of blade 1, without sharply torsion place, therefore there is lesser stress, and intensity is higher is not easily broken, entire propeller reliability with higher.
Circle of the propeller provided by the present embodiment formed in rotary course, referred to as paddle disk, The center of the circle is known as the center of paddle disk, which is known as the diameter of paddle disk.For split type blade 1, the radius of paddle disk can be greater than the length of blade 1.
The thickness of one end from blade 1 close to one end of paddle disk center to blade 1 far from paddle disk center, blade 1 can be gradually reduced.The end in blade 1 from paddle disk center farthest is part most thin in blade 1 as a result, thus advantageously reduces air drag when flight, improves flight efficiency.
Embodiment two
Second embodiment of the present invention provides a kind of Power Components, and including propeller described in actuator and above-described embodiment, the propeller is connect by paddle seat with the actuator.
After paddle seat is connect with actuator, actuator can drive paddle seat to rotate, and then paddle seat drives blade rotation.And the quantity of blade can be arranged according to actual needs.Wherein, actuator is specifically as follows motor, and the KV value of motor is 750~850 turns/(minute volt), wherein, KV value is for measuring motor speed to the increased susceptibility of voltage, and the voltage of the motor in the present embodiment is every to increase by 1 volt, and motor revolving speed per minute just improves 750~850 turns.
Power Component provided in this embodiment, by the setting to three section chord lengths and the angle of attack in blade, it can reduce the resistance of propeller during rotation, improve the flying speed of aircraft, extend distance to go under certain power conditions supply, improves flying quality.
Embodiment three
The embodiment of the present invention three provides a kind of aircraft.Aircraft in the present embodiment may include that fuselage and at least one Power Component as described in above-described embodiment two, the Power Component are connect with the fuselage.The number of Power Component can be one in aircraft, or multiple, the aircraft of the present embodiment includes multiple Power Components, and the steering of the multiple Power Component is different.
Aircraft provided in this embodiment, using above-mentioned Power Component, pass through the setting at least three section chord lengths and the angle of attack in blade, it can reduce the resistance of propeller during rotation, improve the flying speed of aircraft, extend distance to go under certain power conditions supply, improves flying quality.
Finally, it should be noted that the above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations；Although the present invention is described in detail referring to the foregoing embodiments, those skilled in the art should understand that: it still can be to skill documented by foregoing embodiments Art scheme is modified or equivalent replacement of some of the technical features；And these are modified or replaceed, the spirit and scope for technical solution of various embodiments of the present invention that it does not separate the essence of the corresponding technical solution.

Claims (36)

  1. A kind of propeller, including blade, which is characterized in that the blade rotates to form paddle disk；
    The blade with the propeller shape at the center of paddle disk be apart the angle of attack at the 45.8% of paddle disk radius be 22.59 ° ± 2.5 °, chord length is 26.98mm ± 5mm；
    The blade with the propeller shape at the center of paddle disk be apart the angle of attack at the 62.5% of paddle disk radius be 19.57 ° ± 2.5 °, chord length is 21.91mm ± 5mm；
    The blade with the propeller shape at the center of paddle disk be apart the angle of attack at the 79.2% of paddle disk radius be 16.56 ° ± 2.5 °, chord length is 17.64mm ± 5mm.
  2. Propeller according to claim 1, which is characterized in that the propeller shape at paddle disk diameter be 240mm；
    The blade with the propeller shape at the center of paddle disk be apart the angle of attack at 55mm be 22.59 °, chord length 26.98mm；
    The blade with the propeller shape at the center of paddle disk be apart the angle of attack at 75mm be 19.57 °, chord length 21.91mm；
    The blade with the propeller shape at the center of paddle disk be apart the angle of attack at 95mm be 16.56 °, chord length 17.64mm.
  3. Propeller according to claim 1, which is characterized in that
    The blade with the propeller shape at the center of paddle disk be apart the angle of attack at the 29.2% of paddle disk radius be 24.74 ° ± 2.5 °, chord length is 33.58mm ± 5mm.
  4. Propeller according to claim 3, which is characterized in that the propeller shape at paddle disk diameter be 240mm；
    The blade with the propeller shape at the center of paddle disk be apart the angle of attack at 35mm be 24.74 °, chord length 33.58mm.
  5. Propeller according to claim 1, which is characterized in that
    The blade with the propeller shape at the center of paddle disk be apart the angle of attack at the 95.8% of paddle disk radius be 12.80 ° ± 2.5 °, chord length is 13.83mm ± 5mm.
  6. Propeller according to claim 5, which is characterized in that the propeller shape at paddle disk diameter be 240mm；
    The blade with the propeller shape at the center of paddle disk be apart the angle of attack at 115mm be 12.80 °, chord length 13.83mm.
  7. Propeller according to claim 1, which is characterized in that the quantity of the blade is two, and two blades are centrosymmetric about the center of paddle disk.
  8. Propeller according to claim 1, which is characterized in that one end from the blade close to one end of the paddle disk center to the blade far from the paddle disk center, the thickness of the blade are gradually reduced.
  9. Described in any item propellers according to claim 1~8, it is characterized in that, the blade includes blade face blade back directed downwardly upward, and the second lateral margin for being connected to the first lateral margin between the side on the blade back and the blade face and being connected between the other side on the blade back and the blade face, first lateral margin are located at below second lateral margin；The blade back and the blade face are curved surface.
  10. Propeller according to claim 9, which is characterized in that the propeller includes at least two blades, and the propeller further includes the paddle seat for connecting the blade, and at least two blade is circumferentially uniformly distributed along the paddle seat.
  11. Propeller according to claim 10, which is characterized in that first lateral margin includes that curved first outwardly protruded is arched upward portion, and second lateral margin includes that curved second outwardly protruded is arched upward portion；Described first arches upward portion and second portion of arching upward is close to one end that the blade is connected with the paddle seat；And described first the protrusion degree for arching upward portion be greater than the described second protrusion degree for arching upward portion.
  12. Described in any item propellers according to claim 1~8, which is characterized in that the screw pitch of the propeller is 5.5 inches.
  13. A kind of Power Component, which is characterized in that including actuator and propeller, the actuator is motor, the KV value of the motor is 750~850 turns/(minute volt), the propeller includes blade, and the blade rotates to form paddle disk；
    The blade with the propeller shape at the center of paddle disk be apart the angle of attack at the 45.8% of paddle disk radius be 22.59 ° ± 2.5 °, chord length is 26.98mm ± 5mm；
    The blade with the propeller shape at the center of paddle disk be apart the angle of attack at the 62.5% of paddle disk radius be 19.57 ° ± 2.5 °, chord length is 21.91mm ± 5mm；
    The blade with the propeller shape at the center of paddle disk be apart the angle of attack at the 79.2% of paddle disk radius be 16.56 ° ± 2.5 °, chord length is 17.64mm ± 5mm；
    The propeller is connect by paddle seat with the actuator.
  14. Power Component according to claim 13, which is characterized in that the propeller shape at paddle disk diameter be 240mm；
    The blade with the propeller shape at the center of paddle disk be apart the angle of attack at 55mm be 22.59 °, chord length 26.98mm；
    The blade with the propeller shape at the center of paddle disk be apart the angle of attack at 75mm be 19.57 °, chord length 21.91mm；
    The blade with the propeller shape at the center of paddle disk be apart the angle of attack at 95mm be 16.56 °, chord length 17.64mm.
  15. Power Component according to claim 13, which is characterized in that
    The blade with the propeller shape at the center of paddle disk be apart the angle of attack at the 29.2% of paddle disk radius be 24.74 ° ± 2.5 °, chord length is 33.58mm ± 5mm.
  16. Power Component according to claim 15, which is characterized in that the propeller shape at paddle disk diameter be 240mm；
    The blade with the propeller shape at the center of paddle disk be apart the angle of attack at 35mm be 24.74 °, chord length 33.58mm.
  17. Power Component according to claim 13, which is characterized in that
    The blade with the propeller shape at the center of paddle disk be apart the angle of attack at the 95.8% of paddle disk radius be 12.80 ° ± 2.5 °, chord length is 13.83mm ± 5mm.
  18. Power Component according to claim 17, which is characterized in that the propeller The paddle disk diameter of formation is 240mm；
    The blade with the propeller shape at the center of paddle disk be apart the angle of attack at 115mm be 12.80 °, chord length 13.83mm.
  19. Power Component according to claim 13, which is characterized in that the quantity of the blade is two, and two blades are centrosymmetric about the center of paddle disk.
  20. Power Component according to claim 13, which is characterized in that one end from the blade close to one end of the paddle disk center to the blade far from the paddle disk center, the thickness of the blade are gradually reduced.
  21. 3~20 described in any item Power Components according to claim 1, it is characterized in that, the blade includes blade face blade back directed downwardly upward, and the second lateral margin for being connected to the first lateral margin between the side on the blade back and the blade face and being connected between the other side on the blade back and the blade face, first lateral margin are located at below second lateral margin；The blade back and the blade face are curved surface.
  22. Power Component according to claim 21, which is characterized in that the propeller includes at least two blades, and the propeller further includes the paddle seat for connecting the blade, and at least two blade is circumferentially uniformly distributed along the paddle seat.
  23. Power Component according to claim 22, which is characterized in that first lateral margin includes that curved first outwardly protruded is arched upward portion, and second lateral margin includes that curved second outwardly protruded is arched upward portion；Described first arches upward portion and second portion of arching upward is close to one end that the blade is connected with the paddle seat；And described first the protrusion degree for arching upward portion be greater than the described second protrusion degree for arching upward portion.
  24. 3~20 described in any item Power Components according to claim 1, which is characterized in that the screw pitch of the propeller is 5.5 inches.
  25. A kind of aircraft, including fuselage, it is characterized in that, it further include Power Component, the Power Component includes actuator and propeller, and the actuator is motor, and the KV value of the motor is 750~850 turns/(minute volt), the propeller includes blade, and the blade rotates to form paddle disk；
    The blade with the propeller shape at the center of paddle disk be apart the angle of attack at the 45.8% of paddle disk radius be 22.59 ° ± 2.5 °, chord length is 26.98mm ± 5mm；
    The blade with the propeller shape at the center of paddle disk be apart the angle of attack at the 62.5% of paddle disk radius be 19.57 ° ± 2.5 °, chord length is 21.91mm ± 5mm；
    The blade with the propeller shape at the center of paddle disk be apart the angle of attack at the 79.2% of paddle disk radius be 16.56 ° ± 2.5 °, chord length is 17.64mm ± 5mm；
    The propeller is connect by paddle seat with the actuator；
    The Power Component is connect with the fuselage.
  26. Aircraft according to claim 25, which is characterized in that the propeller shape at paddle disk diameter be 240mm；
    The blade with the propeller shape at the center of paddle disk be apart the angle of attack at 55mm be 22.59 °, chord length 26.98mm；
    The blade with the propeller shape at the center of paddle disk be apart the angle of attack at 75mm be 19.57 °, chord length 21.91mm；
    The blade with the propeller shape at the center of paddle disk be apart the angle of attack at 95mm be 16.56 °, chord length 17.64mm.
  27. Aircraft according to claim 25, which is characterized in that
    The blade with the propeller shape at the center of paddle disk be apart the angle of attack at the 29.2% of paddle disk radius be 24.74 ° ± 2.5 °, chord length is 33.58mm ± 5mm.
  28. Aircraft according to claim 27, which is characterized in that the propeller shape at paddle disk diameter be 240mm；
    The blade with the propeller shape at the center of paddle disk be apart the angle of attack at 35mm be 24.74 °, chord length 33.58mm.
  29. Aircraft according to claim 25, which is characterized in that
    The blade with the propeller shape at the center of paddle disk be apart the angle of attack at the 95.8% of paddle disk radius be 12.80 ° ± 2.5 °, chord length is 13.83mm ± 5mm.
  30. Aircraft according to claim 29, which is characterized in that the propeller shape at paddle disk diameter be 240mm；
    The blade with the propeller shape at the center of paddle disk be apart the angle of attack at 115mm be 12.80 °, chord length 13.83mm.
  31. Aircraft according to claim 25, which is characterized in that the quantity of the blade is two, and two blades are centrosymmetric about the center of paddle disk.
  32. Aircraft according to claim 25, which is characterized in that one end from the blade close to one end of the paddle disk center to the blade far from the paddle disk center, the thickness of the blade are gradually reduced.
  33. According to the described in any item aircraft of claim 25~32, it is characterized in that, the blade includes blade face blade back directed downwardly upward, and the second lateral margin for being connected to the first lateral margin between the side on the blade back and the blade face and being connected between the other side on the blade back and the blade face, first lateral margin are located at below second lateral margin；The blade back and the blade face are curved surface.
  34. Aircraft according to claim 33, which is characterized in that the propeller includes at least two blades, and the propeller further includes the paddle seat for connecting the blade, and at least two blade is circumferentially uniformly distributed along the paddle seat.
  35. Aircraft according to claim 34, which is characterized in that first lateral margin includes that curved first outwardly protruded is arched upward portion, and second lateral margin includes that curved second outwardly protruded is arched upward portion；Described first arches upward portion and second portion of arching upward is close to one end that the blade is connected with the paddle seat；And described first the protrusion degree for arching upward portion be greater than the described second protrusion degree for arching upward portion.
  36. According to the described in any item aircraft of claim 25~32, which is characterized in that the screw pitch of the propeller is 5.5 inches.
CN201780069690.8A 2017-06-30 2017-08-03 Propeller, Power Component and aircraft Pending CN109923036A (en)

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CN201720792105.4U CN206954494U (en) 2017-06-30 2017-06-30 Propeller, Power Component and aircraft
CN2017207921054 2017-06-30
PCT/CN2017/095865 WO2019000560A1 (en) 2017-06-30 2017-08-03 Propeller, power assembly, and aircraft

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113022849A (en) * 2021-05-28 2021-06-25 北京三快在线科技有限公司 Propeller and rotor craft

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN208291465U (en) * 2018-05-25 2018-12-28 深圳市大疆创新科技有限公司 Propeller, Power Component and aircraft

Citations (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4248572A (en) * 1978-12-11 1981-02-03 United Technologies Corporation Helicopter blade
EP0036825A1 (en) * 1980-03-25 1981-09-30 AEROSPATIALE Société Nationale Industrielle High-performance blade for helicopter rotor
EP1714869A1 (en) * 2005-04-21 2006-10-25 Deutsches Zentrum für Luft- und Raumfahrt e.V. Lifting surface with improved separation behaviour under strongly variable angle of incidence
EP2123557A1 (en) * 2008-05-22 2009-11-25 Agusta S.p.A. Helicopter antitorque tail rotor blade
EP2253836A1 (en) * 2009-05-18 2010-11-24 Lm Glasfiber A/S Wind turbine blade
WO2012079100A2 (en) * 2010-12-09 2012-06-21 Fd-Composites Gmbh Rotor blades of a gyrocopter
CN104071334A (en) * 2014-06-27 2014-10-01 天津三爻航空航天科技发展有限公司 Helicopter rotor oar
CN203996873U (en) * 2014-07-30 2014-12-10 深圳市大疆创新科技有限公司 Aircraft and screw propeller thereof
US20150037149A1 (en) * 2013-08-01 2015-02-05 Alfred Alan Gates Rotorcraft control system for rotorcraft with two or more rotor systems
CN105691612A (en) * 2014-12-15 2016-06-22 波音公司 Rotor assembly apparatus
CN205345320U (en) * 2016-01-27 2016-06-29 深圳市大疆创新科技有限公司 Screw, power component and aircraft
CN205345321U (en) * 2016-01-19 2016-06-29 深圳市大疆创新科技有限公司 Screw, power suit and unmanned vehicles
CN205469778U (en) * 2016-02-29 2016-08-17 深圳市大疆创新科技有限公司 Screw, power component and aircraft
CN205524940U (en) * 2016-02-29 2016-08-31 深圳市大疆创新科技有限公司 Screw, power component and aircraft
CN205801500U (en) * 2016-06-30 2016-12-14 深圳市大疆创新科技有限公司 Propeller, power suit and unmanned vehicle
CN106218886A (en) * 2016-08-18 2016-12-14 上海未来伙伴机器人有限公司 Many rotorcraft blades and many gyroplanes
CN206155775U (en) * 2016-11-11 2017-05-10 深圳市大疆创新科技有限公司 Screw, power component and aircraft

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9688395B2 (en) * 2013-12-04 2017-06-27 Sikorsky Aircraft Corporation Boundary layer ingesting blade
CN205589457U (en) * 2016-02-29 2016-09-21 深圳市大疆创新科技有限公司 Screw, power component and aircraft
CN205554565U (en) * 2016-02-29 2016-09-07 深圳市大疆创新科技有限公司 Screw, power component and aircraft

Patent Citations (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4248572A (en) * 1978-12-11 1981-02-03 United Technologies Corporation Helicopter blade
EP0036825A1 (en) * 1980-03-25 1981-09-30 AEROSPATIALE Société Nationale Industrielle High-performance blade for helicopter rotor
EP1714869A1 (en) * 2005-04-21 2006-10-25 Deutsches Zentrum für Luft- und Raumfahrt e.V. Lifting surface with improved separation behaviour under strongly variable angle of incidence
EP2123557A1 (en) * 2008-05-22 2009-11-25 Agusta S.p.A. Helicopter antitorque tail rotor blade
CN101585412A (en) * 2008-05-22 2009-11-25 阿古斯塔公司 Helicopter antitorque tail rotor blade
EP2253836A1 (en) * 2009-05-18 2010-11-24 Lm Glasfiber A/S Wind turbine blade
WO2012079100A2 (en) * 2010-12-09 2012-06-21 Fd-Composites Gmbh Rotor blades of a gyrocopter
US20150037149A1 (en) * 2013-08-01 2015-02-05 Alfred Alan Gates Rotorcraft control system for rotorcraft with two or more rotor systems
CN104071334A (en) * 2014-06-27 2014-10-01 天津三爻航空航天科技发展有限公司 Helicopter rotor oar
CN203996873U (en) * 2014-07-30 2014-12-10 深圳市大疆创新科技有限公司 Aircraft and screw propeller thereof
CN105691612A (en) * 2014-12-15 2016-06-22 波音公司 Rotor assembly apparatus
CN205345321U (en) * 2016-01-19 2016-06-29 深圳市大疆创新科技有限公司 Screw, power suit and unmanned vehicles
CN205345320U (en) * 2016-01-27 2016-06-29 深圳市大疆创新科技有限公司 Screw, power component and aircraft
CN205469778U (en) * 2016-02-29 2016-08-17 深圳市大疆创新科技有限公司 Screw, power component and aircraft
CN205524940U (en) * 2016-02-29 2016-08-31 深圳市大疆创新科技有限公司 Screw, power component and aircraft
CN205801500U (en) * 2016-06-30 2016-12-14 深圳市大疆创新科技有限公司 Propeller, power suit and unmanned vehicle
CN106218886A (en) * 2016-08-18 2016-12-14 上海未来伙伴机器人有限公司 Many rotorcraft blades and many gyroplanes
CN206155775U (en) * 2016-11-11 2017-05-10 深圳市大疆创新科技有限公司 Screw, power component and aircraft

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
佟刚等: "基于片条理论的微型旋翼设计", 《沈阳航空航天大学学报》 *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113022849A (en) * 2021-05-28 2021-06-25 北京三快在线科技有限公司 Propeller and rotor craft
CN113022849B (en) * 2021-05-28 2024-02-06 北京三快在线科技有限公司 Propeller and rotary wing aircraft

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