Screw, power component and aircraft
阅读说明:本技术 螺旋桨、动力组件及飞行器 (Screw, power component and aircraft ) 是由 林家靖 陈鹏 梁阔 于 2018-09-25 设计创作,主要内容包括:本发明实施例公开了一种螺旋桨(100)、动力组件(200)及飞行器(1000)。螺旋桨(100)包括桨毂(10)和桨叶(20),桨叶(20)连接在桨毂(10)上。桨叶(20)包括桨根(21)、背离桨根(21)的桨尖(22)、压力面(23)、与压力面(23)相背的吸力面(24)。桨尖(22)沿桨叶(20)展向的方向朝压力面(23)所在的一侧倾斜延伸。在距离桨毂(10)的中心为螺旋桨(100)的半径的100%处,桨叶(20)的翼型旋转中心所在的水平面与距离桨毂(10)的中心为螺旋桨(100)的半径的50%处的桨叶(20)的翼型旋转中心所在的水平面之间的距离为螺旋桨(100)半径的3.0%至9.3%;因此,由上述参数限定出具备特定形状的桨叶(20),采用桨叶(20)的螺旋桨(100)一方面能够减少螺旋桨(100)的空气阻力,提高拉力和效率,增加飞行器(1000)的继航距离以提高飞行器(1000)的飞行性能,另一方面能够减小桨叶(20)在工作时产生的噪声,使得飞行器(1000)在悬停时更安静,提高了用户体验。(The embodiment of the invention discloses a propeller (100), a power assembly (200) and an aircraft (1000). The propeller (100) comprises a hub (10) and blades (20), wherein the blades (20) are connected to the hub (10). The paddle (20) comprises a paddle root (21), a paddle tip (22) deviating from the paddle root (21), a pressure surface (23) and a suction surface (24) opposite to the pressure surface (23). The blade tip (22) extends obliquely towards the side of the pressure surface (23) along the span direction of the blade (20). The distance between a horizontal plane where the airfoil-shaped rotation center of the blade (20) is located and the center of the hub (10) is 50% of the radius of the propeller (100) is 3.0% to 9.3% of the radius of the propeller (100) at a position where the distance from the center of the hub (10) is 100% of the radius of the propeller (100); therefore, the blades (20) with specific shapes are defined by the parameters, and the propeller (100) adopting the blades (20) can reduce the air resistance of the propeller (100), improve the pulling force and the efficiency, increase the secondary flight distance of the aircraft (1000) to improve the flight performance of the aircraft (1000) on one hand, and reduce the noise generated by the blades (20) in work on the other hand, so that the aircraft (1000) is quieter when hovering, and the user experience is improved.)
1. A propeller, comprising: a hub and blades attached to said hub, characterized in that:
the paddle comprises a paddle root, a paddle tip, a pressure surface and a suction surface, wherein the paddle tip is deviated from the paddle root;
the blade tip extends towards one side of the pressure surface along the spanwise direction of the blade in an inclined mode;
the distance between a horizontal plane in which the airfoil-shaped rotation center of the blade is located and a horizontal plane in which the airfoil-shaped rotation center of the blade is located at a position that is located at a distance of 100% of the radius of the propeller from the center of the hub and a horizontal plane in which the airfoil-shaped rotation center of the blade is located at a distance of 50% of the radius of the propeller from the center of the hub is 3.0% to 9.3% of the radius of the propeller.
2. The propeller of claim 1, wherein:
the distance between a horizontal plane in which the airfoil rotation center of the blade is located and a horizontal plane in which the airfoil rotation center of the blade is located at a distance of 97.9% of the radius of the propeller from the center of the hub and a horizontal plane in which the airfoil rotation center of the blade is located at a distance of 50% of the radius of the propeller from the center of the hub is 2.6% to 7.0% of the radius of the propeller; and/or
The distance between a horizontal plane where the airfoil rotation center of the blade is located and a horizontal plane where the airfoil rotation center of the blade is located at a distance of 95.8% of the radius of the propeller from the center of the hub and a horizontal plane where the airfoil rotation center of the blade is located at a distance of 50% of the radius of the propeller from the center of the hub is 1.4% to 5.4% of the radius of the propeller; and/or
The distance between a horizontal plane where the airfoil rotation center of the blade is located and a horizontal plane where the airfoil rotation center of the blade is located at a distance of 93.8% of the radius of the propeller from the center of the hub and a horizontal plane where the airfoil rotation center of the blade is located at a distance of 50% of the radius of the propeller from the center of the hub is 1.1% to 3.2% of the radius of the propeller; and/or
The distance between a horizontal plane where the airfoil rotation center of the blade is located and a horizontal plane where the airfoil rotation center of the blade is located at a distance of 91.7% of the radius of the propeller from the center of the hub and a horizontal plane where the airfoil rotation center of the blade is located at a distance of 50% of the radius of the propeller from the center of the hub is 0.2% to 2.1% of the radius of the propeller; and/or
The distance between a horizontal plane where the airfoil rotation center of the blade is located and a horizontal plane where the airfoil rotation center of the blade is located at a position 50% of the radius of the propeller from the center of the hub is 0.2% to 0.6% of the radius of the propeller at a position 89.2% of the radius of the propeller from the center of the hub; and/or
The distance between a horizontal plane in which the airfoil rotation center of the blade is located and a horizontal plane in which the airfoil rotation center of the blade is located at a distance of 87.5% of the radius of the propeller from the center of the hub and a horizontal plane in which the airfoil rotation center of the blade is located at a distance of 50% of the radius of the propeller from the center of the hub is 0.02% to 0.04% of the radius of the propeller; and/or
The distance between a horizontal plane where the airfoil rotation center of the blade is located and a horizontal plane where the airfoil rotation center of the blade is located at a position which is 120mm away from the center of the hub and is 50% of the radius of the propeller from the center of the hub is 7.00mm +/-3 mm; and/or
The distance between the horizontal plane where the airfoil rotation center of the blade is located and the horizontal plane where the airfoil rotation center of the blade is located at the position which is 50% of the radius of the propeller from the center of the hub is 5.40mm +/-3 mm at 117.5mm from the center of the hub; and/or
The distance between the horizontal plane of the airfoil rotation center of the blade at a position 115mm away from the center of the hub and the horizontal plane of the airfoil rotation center of the blade at a position 50% of the radius of the propeller away from the center of the hub is 3.86mm +/-2 mm; and/or
The distance between the horizontal plane of the airfoil rotation center of the blade at 112.5mm from the center of the hub and the horizontal plane of the airfoil rotation center of the blade at 50% of the radius of the propeller from the center of the hub is 2.46mm +/-1 mm; and/or
At a distance of 110mm from the center of the hub, the distance between the horizontal plane of the airfoil rotation center of the blade and the horizontal plane of the airfoil rotation center of the blade at a distance of 50% of the radius of the propeller from the center of the hub is 1.29mm +/-1 mm; and/or
The distance between the horizontal plane where the airfoil rotation center of the blade is located and the horizontal plane where the airfoil rotation center of the blade is located at the position which is at a distance of 107.5mm from the center of the hub and is at 50% of the radius of the propeller from the center of the hub is 0.45mm +/-0.2 mm; and/or
And at a distance of 105mm from the center of the hub, the distance between the horizontal plane where the airfoil rotation center of the blade is located and the horizontal plane where the airfoil rotation center of the blade is located at a distance of 50% of the radius of the propeller from the center of the hub is 0.03mm +/-0.01 mm.
3. The propeller of claim 1, wherein:
the angle of attack of the blades is 17.50 ° ± 2.5 ° at a distance of 41.7% of the radius of the propeller from the center of the hub; and/or
The angle of attack of the blades is 16.54 ° ± 2.5 ° at a distance from the centre of the hub of 50% of the radius of the propeller; and/or
At 58.3% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 15.45 ° ± 2.5 °; and/or
At 66.7% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 14.25 ° ± 2.5 °; and/or
The angle of attack of the blades is 12.97 ° ± 2.5 ° at a distance from the center of the hub of 75% of the radius of the propeller.
4. The propeller of claim 3, wherein:
the angle of attack of the blades is 18.95 ° ± 2.5 ° at a distance from the centre of the hub of 25% of the radius of the propeller; and/or
At 33.3% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 18.38 ° ± 2.5 °; and/or
The angle of attack of the blades is 11.49 ° ± 2.5 ° at 83.3% of the radius of the propeller from the center of the hub; and/or
The angle of attack of the blades is 9.47 ° ± 2.5 ° at 91.7% of the radius of the propeller from the center of the hub; and/or
The angle of attack of the blades is 5.94 ° ± 2.5 ° at a distance from the centre of the hub of 100% of the radius of the propeller; and/or
At 30mm from the centre of the hub, the angle of attack of the blade is 18.95 °; and/or
At 40mm from the centre of the hub, the angle of attack of the blade is 18.38 °; and/or
At 50mm from the centre of the hub, the angle of attack of the blade is 17.50 °; and/or
At 60mm from the centre of the hub, the angle of attack of the blade is 16.54 °; and/or
At 70mm from the centre of the hub, the angle of attack of the blade is 15.45 °; and/or
At 80mm from the centre of the hub, the angle of attack of the blade is 14.25 °; and/or
At 90mm from the center of the hub, the angle of attack of the blade is 12.97 °; and/or
At 100mm from the centre of the hub, the angle of attack of the blade is 11.49 °; and/or
At 110mm from the centre of the hub, the angle of attack of the blade is 9.47 °; and/or
At 120mm from the centre of the hub, the angle of attack of the blade is 5.94 °.
5. The propeller of claim 3, wherein:
the chord length of the blade is 29.80mm ± 5mm at a distance of 41.7% of the radius of the propeller from the centre of the hub; and/or
The chord length of the blade is 28.54mm + -5 mm at a distance of 50% of the radius of the propeller from the center of the hub; and/or
The chord length of the blade is 27.27mm ± 5mm at 58.3% of the radius of the propeller from the centre of the hub; and/or
The chord length of the blade is 25.98mm ± 5mm at 66.7% of the radius of the propeller from the centre of the hub; and/or
The chord length of the blade is 24.71mm ± 5mm at a distance of 75% of the radius of the propeller from the centre of the hub.
6. The propeller of claim 5, wherein:
the chord length of the blade is 32.01mm + -5 mm at a distance of 25% of the radius of the propeller from the center of the hub; and/or
The chord length of the blade is 31.05mm + -5 mm at a distance of 33.3% of the radius of the propeller from the center of the hub; and/or
The chord length of the blade is 21.48mm ± 5mm at a distance of 83.3% of the radius of the propeller from the center of the hub; and/or
The chord length of the blade is 15.40mm + -5 mm at a distance of 91.7% of the radius of the propeller from the center of the hub; and/or
The chord length of the blade is 3.61mm ± 2mm at a distance from the centre of the hub of 100% of the radius of the propeller.
At 30mm from the centre of the hub, the chord length of the blade is 32.01 mm; and/or
The chord length of the blade is 31.05mm at 40mm from the centre of the hub; and/or
At 50mm from the centre of the hub, the chord length of the blade is 29.80 mm; and/or
At 60mm from the centre of the hub, the chord length of the blade is 28.54 mm; and/or
At 70mm from the centre of the hub, the chord length of the blade is 27.27 mm; and/or
At 80mm from the centre of the hub, the chord length of the blade is 25.98 mm; and/or
The chord length of the blade is 24.71mm at 90mm from the centre of the hub; and/or
At 100mm from the centre of the hub, the chord length of the blade is 21.48 mm; and/or
At 110mm from the centre of the hub, the chord length of the blade is 15.40 mm; and/or
The chord length of the blade is 3.61mm at 120mm from the centre of the hub.
7. The propeller of claim 1, wherein:
the diameter of the propeller is 240mm +/-24 mm; and/or
The pitch of the blade is 5.36 + -0.5 inches.
8. The propeller of any one of claims 1 to 7, wherein:
the blade also comprises a front edge connected to one side of the pressure surface and the suction surface, a rear edge connected to the other side of the pressure surface and the suction surface, and a swept-back part formed at the blade tip, wherein the swept-back part extends from the front edge to the rear edge in an inclined manner; and/or
The rear edge is convexly provided with a curved rear edge arch part close to the paddle root.
9. The propeller of claim 8, wherein:
the blade forms a return bend at the position of the blade tip, the front edge extends obliquely from the return bend along the span direction of the blade towards the side where the pressure surface is located, the sweepback extends obliquely from the return bend from the front edge to the rear edge, and the distance from the return bend to the center of the hub is 87.5% of the radius of the propeller.
10. The propeller of claim 8, wherein:
the number of the blades is at least two, and the at least two blades are connected to the hub and are in central symmetry with respect to the center of the hub; and/or
The blade having a central axis passing through the center of the hub, the leading edge having a leading edge tangent parallel to the central axis, the trailing edge having a trailing edge tangent parallel to the central axis, the sweep being located between the leading edge tangent and the trailing edge tangent; and/or
The suction surface and the pressure surface are both curved surfaces.
11. A power assembly comprises a driving piece and a propeller, and is characterized in that the propeller comprises a hub and blades, the blades are connected to the hub, and the blades comprise a root, a tip, a pressure surface and a suction surface, wherein the tip is far away from the root; the blade tip extends towards one side of the pressure surface along the spanwise direction of the blade in an inclined mode; the distance between a horizontal plane where the airfoil-shaped rotation center of the blade is located and a horizontal plane where the airfoil-shaped rotation center of the blade is located at a position which is 100% of the radius of the propeller from the center of the hub and which is 50% of the radius of the propeller from the center of the hub is 3.0% to 9.3% of the radius of the propeller; the propeller is connected with the driving piece through the propeller hub.
12. The power assembly of claim 11, wherein:
the distance between a horizontal plane in which the airfoil rotation center of the blade is located and a horizontal plane in which the airfoil rotation center of the blade is located at a distance of 97.9% of the radius of the propeller from the center of the hub and a horizontal plane in which the airfoil rotation center of the blade is located at a distance of 50% of the radius of the propeller from the center of the hub is 2.6% to 7.0% of the radius of the propeller; and/or
The distance between a horizontal plane where the airfoil rotation center of the blade is located and a horizontal plane where the airfoil rotation center of the blade is located at a distance of 95.8% of the radius of the propeller from the center of the hub and a horizontal plane where the airfoil rotation center of the blade is located at a distance of 50% of the radius of the propeller from the center of the hub is 1.4% to 5.4% of the radius of the propeller; and/or
The distance between a horizontal plane where the airfoil rotation center of the blade is located and a horizontal plane where the airfoil rotation center of the blade is located at a distance of 93.8% of the radius of the propeller from the center of the hub and a horizontal plane where the airfoil rotation center of the blade is located at a distance of 50% of the radius of the propeller from the center of the hub is 1.1% to 3.2% of the radius of the propeller; and/or
The distance between a horizontal plane where the airfoil rotation center of the blade is located and a horizontal plane where the airfoil rotation center of the blade is located at a distance of 91.7% of the radius of the propeller from the center of the hub and a horizontal plane where the airfoil rotation center of the blade is located at a distance of 50% of the radius of the propeller from the center of the hub is 0.2% to 2.1% of the radius of the propeller; and/or
The distance between a horizontal plane where the airfoil rotation center of the blade is located and a horizontal plane where the airfoil rotation center of the blade is located at a position 50% of the radius of the propeller from the center of the hub is 0.2% to 0.6% of the radius of the propeller at a position 89.2% of the radius of the propeller from the center of the hub; and/or
The distance between a horizontal plane in which the airfoil rotation center of the blade is located and a horizontal plane in which the airfoil rotation center of the blade is located at a distance of 87.5% of the radius of the propeller from the center of the hub and a horizontal plane in which the airfoil rotation center of the blade is located at a distance of 50% of the radius of the propeller from the center of the hub is 0.02% to 0.04% of the radius of the propeller; and/or
The distance between a horizontal plane where the airfoil rotation center of the blade is located and a horizontal plane where the airfoil rotation center of the blade is located at a position which is 120mm away from the center of the hub and is 50% of the radius of the propeller from the center of the hub is 7.00mm +/-3 mm; and/or
The distance between the horizontal plane where the airfoil rotation center of the blade is located and the horizontal plane where the airfoil rotation center of the blade is located at the position which is 50% of the radius of the propeller from the center of the hub is 5.40mm +/-3 mm at 117.5mm from the center of the hub; and/or
The distance between the horizontal plane of the airfoil rotation center of the blade at a position 115mm away from the center of the hub and the horizontal plane of the airfoil rotation center of the blade at a position 50% of the radius of the propeller away from the center of the hub is 3.86mm +/-2 mm; and/or
The distance between the horizontal plane of the airfoil rotation center of the blade at 112.5mm from the center of the hub and the horizontal plane of the airfoil rotation center of the blade at 50% of the radius of the propeller from the center of the hub is 2.46mm +/-1 mm; and/or
At a distance of 110mm from the center of the hub, the distance between the horizontal plane of the airfoil rotation center of the blade and the horizontal plane of the airfoil rotation center of the blade at a distance of 50% of the radius of the propeller from the center of the hub is 1.29mm +/-1 mm; and/or
The distance between the horizontal plane where the airfoil rotation center of the blade is located and the horizontal plane where the airfoil rotation center of the blade is located at the position which is at a distance of 107.5mm from the center of the hub and is at 50% of the radius of the propeller from the center of the hub is 0.45mm +/-0.2 mm; and/or
And at a distance of 105mm from the center of the hub, the distance between the horizontal plane where the airfoil rotation center of the blade is located and the horizontal plane where the airfoil rotation center of the blade is located at a distance of 50% of the radius of the propeller from the center of the hub is 0.03mm +/-0.01 mm.
13. The power assembly of claim 11, wherein:
the angle of attack of the blades is 17.50 ° ± 2.5 ° at a distance of 41.7% of the radius of the propeller from the center of the hub; and/or
The angle of attack of the blades is 16.54 ° ± 2.5 ° at a distance from the centre of the hub of 50% of the radius of the propeller; and/or
At 58.3% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 15.45 ° ± 2.5 °; and/or
At 66.7% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 14.25 ° ± 2.5 °; and/or
The angle of attack of the blades is 12.97 ° ± 2.5 ° at a distance from the center of the hub of 75% of the radius of the propeller.
14. The power assembly of claim 13, wherein:
the angle of attack of the blades is 18.95 ° ± 2.5 ° at a distance from the centre of the hub of 25% of the radius of the propeller; and/or
At 33.3% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 18.38 ° ± 2.5 °; and/or
The angle of attack of the blades is 11.49 ° ± 2.5 ° at 83.3% of the radius of the propeller from the center of the hub; and/or
The angle of attack of the blades is 9.47 ° ± 2.5 ° at 91.7% of the radius of the propeller from the center of the hub; and/or
The angle of attack of the blades is 5.94 ° ± 2.5 ° at a distance from the centre of the hub of 100% of the radius of the propeller; and/or
At 30mm from the centre of the hub, the angle of attack of the blade is 18.95 °; and/or
At 40mm from the centre of the hub, the angle of attack of the blade is 18.38 °; and/or
At 50mm from the centre of the hub, the angle of attack of the blade is 17.50 °; and/or
At 60mm from the centre of the hub, the angle of attack of the blade is 16.54 °; and/or
At 70mm from the centre of the hub, the angle of attack of the blade is 15.45 °; and/or
At 80mm from the centre of the hub, the angle of attack of the blade is 14.25 °; and/or
At 90mm from the center of the hub, the angle of attack of the blade is 12.97 °; and/or
At 100mm from the centre of the hub, the angle of attack of the blade is 11.49 °; and/or
At 110mm from the centre of the hub, the angle of attack of the blade is 9.47 °; and/or
At 120mm from the centre of the hub, the angle of attack of the blade is 5.94 °.
15. The power assembly of claim 13, wherein:
the chord length of the blade is 29.80mm ± 5mm at a distance of 41.7% of the radius of the propeller from the centre of the hub; and/or
The chord length of the blade is 28.54mm + -5 mm at a distance of 50% of the radius of the propeller from the center of the hub; and/or
The chord length of the blade is 27.27mm ± 5mm at 58.3% of the radius of the propeller from the centre of the hub; and/or
The chord length of the blade is 25.98mm ± 5mm at 66.7% of the radius of the propeller from the centre of the hub; and/or
The chord length of the blade is 24.71mm ± 5mm at a distance of 75% of the radius of the propeller from the centre of the hub.
16. The power assembly of claim 15, wherein:
the chord length of the blade is 32.01mm + -5 mm at a distance of 25% of the radius of the propeller from the center of the hub; and/or
The chord length of the blade is 31.05mm + -5 mm at a distance of 33.3% of the radius of the propeller from the center of the hub; and/or
The chord length of the blade is 21.48mm ± 5mm at a distance of 83.3% of the radius of the propeller from the center of the hub; and/or
The chord length of the blade is 15.40mm + -5 mm at a distance of 91.7% of the radius of the propeller from the center of the hub; and/or
The chord length of the blade is 3.61mm ± 2mm at a distance from the centre of the hub of 100% of the radius of the propeller.
At 30mm from the centre of the hub, the chord length of the blade is 32.01 mm; and/or
The chord length of the blade is 31.05mm at 40mm from the centre of the hub; and/or
At 50mm from the centre of the hub, the chord length of the blade is 29.80 mm; and/or
At 60mm from the centre of the hub, the chord length of the blade is 28.54 mm; and/or
At 70mm from the centre of the hub, the chord length of the blade is 27.27 mm; and/or
At 80mm from the centre of the hub, the chord length of the blade is 25.98 mm; and/or
The chord length of the blade is 24.71mm at 90mm from the centre of the hub; and/or
At 100mm from the centre of the hub, the chord length of the blade is 21.48 mm; and/or
At 110mm from the centre of the hub, the chord length of the blade is 15.40 mm; and/or
The chord length of the blade is 3.61mm at 120mm from the centre of the hub.
17. The power assembly of claim 11, wherein:
the diameter of the propeller is 240mm +/-24 mm; and/or
The pitch of the blade is 5.36 + -0.5 inches.
18. A power assembly according to any one of claims 11 to 17, wherein:
the blade also comprises a front edge connected to one side of the pressure surface and the suction surface, a rear edge connected to the other side of the pressure surface and the suction surface, and a swept-back part formed at the blade tip, wherein the swept-back part extends from the front edge to the rear edge in an inclined manner; and/or
The rear edge is convexly provided with a curved rear edge arch part close to the paddle root.
19. The power assembly of claim 18, wherein:
the blade forms a return bend at the position of the blade tip, the front edge extends obliquely from the return bend along the span direction of the blade towards the side where the pressure surface is located, the sweepback extends obliquely from the return bend from the front edge to the rear edge, and the distance from the return bend to the center of the hub is 87.5% of the radius of the propeller.
20. The power assembly of claim 18, wherein:
the number of the blades is at least two, and the at least two blades are connected to the hub and are in central symmetry with respect to the center of the hub; and/or
The blade having a central axis passing through the center of the hub, the leading edge having a leading edge tangent parallel to the central axis, the trailing edge having a trailing edge tangent parallel to the central axis, the sweep being located between the leading edge tangent and the trailing edge tangent; and/or
The suction surface and the pressure surface are both curved surfaces.
21. A power assembly according to any one of claims 11 to 20, wherein the drive member is an electric motor having KV values of 720 ± 72 revolutions/(min-volt).
22. An aircraft is characterized by comprising a fuselage and a power assembly, wherein the power assembly is connected with the fuselage, the power assembly comprises a driving piece and a propeller, the propeller comprises a hub and blades, the blades are connected to the hub, and the blades comprise a root, a tip deviating from the root, a pressure surface and a suction surface opposite to the pressure surface; the blade tip extends towards one side of the pressure surface along the spanwise direction of the blade in an inclined mode; the distance between a horizontal plane where the airfoil-shaped rotation center of the blade is located and a horizontal plane where the airfoil-shaped rotation center of the blade is located at a position which is 100% of the radius of the propeller from the center of the hub and which is 50% of the radius of the propeller from the center of the hub is 3.0% to 9.3% of the radius of the propeller; the propeller is connected with the driving piece through the propeller hub.
23. The aircraft of claim 22, wherein:
the distance between a horizontal plane in which the airfoil rotation center of the blade is located and a horizontal plane in which the airfoil rotation center of the blade is located at a distance of 97.9% of the radius of the propeller from the center of the hub and a horizontal plane in which the airfoil rotation center of the blade is located at a distance of 50% of the radius of the propeller from the center of the hub is 2.6% to 7.0% of the radius of the propeller; and/or
The distance between a horizontal plane where the airfoil rotation center of the blade is located and a horizontal plane where the airfoil rotation center of the blade is located at a distance of 95.8% of the radius of the propeller from the center of the hub and a horizontal plane where the airfoil rotation center of the blade is located at a distance of 50% of the radius of the propeller from the center of the hub is 1.4% to 5.4% of the radius of the propeller; and/or
The distance between a horizontal plane where the airfoil rotation center of the blade is located and a horizontal plane where the airfoil rotation center of the blade is located at a distance of 93.8% of the radius of the propeller from the center of the hub and a horizontal plane where the airfoil rotation center of the blade is located at a distance of 50% of the radius of the propeller from the center of the hub is 1.1% to 3.2% of the radius of the propeller; and/or
The distance between a horizontal plane where the airfoil rotation center of the blade is located and a horizontal plane where the airfoil rotation center of the blade is located at a distance of 91.7% of the radius of the propeller from the center of the hub and a horizontal plane where the airfoil rotation center of the blade is located at a distance of 50% of the radius of the propeller from the center of the hub is 0.2% to 2.1% of the radius of the propeller; and/or
The distance between a horizontal plane where the airfoil rotation center of the blade is located and a horizontal plane where the airfoil rotation center of the blade is located at a position 50% of the radius of the propeller from the center of the hub is 0.2% to 0.6% of the radius of the propeller at a position 89.2% of the radius of the propeller from the center of the hub; and/or
The distance between a horizontal plane in which the airfoil rotation center of the blade is located and a horizontal plane in which the airfoil rotation center of the blade is located at a distance of 87.5% of the radius of the propeller from the center of the hub and a horizontal plane in which the airfoil rotation center of the blade is located at a distance of 50% of the radius of the propeller from the center of the hub is 0.02% to 0.04% of the radius of the propeller; and/or
The distance between a horizontal plane where the airfoil rotation center of the blade is located and a horizontal plane where the airfoil rotation center of the blade is located at a position which is 120mm away from the center of the hub and is 50% of the radius of the propeller from the center of the hub is 7.00mm +/-3 mm; and/or
The distance between the horizontal plane where the airfoil rotation center of the blade is located and the horizontal plane where the airfoil rotation center of the blade is located at the position which is 50% of the radius of the propeller from the center of the hub is 5.40mm +/-3 mm at 117.5mm from the center of the hub; and/or
The distance between the horizontal plane of the airfoil rotation center of the blade at a position 115mm away from the center of the hub and the horizontal plane of the airfoil rotation center of the blade at a position 50% of the radius of the propeller away from the center of the hub is 3.86mm +/-2 mm; and/or
The distance between the horizontal plane of the airfoil rotation center of the blade at 112.5mm from the center of the hub and the horizontal plane of the airfoil rotation center of the blade at 50% of the radius of the propeller from the center of the hub is 2.46mm +/-1 mm; and/or
At a distance of 110mm from the center of the hub, the distance between the horizontal plane of the airfoil rotation center of the blade and the horizontal plane of the airfoil rotation center of the blade at a distance of 50% of the radius of the propeller from the center of the hub is 1.29mm +/-1 mm; and/or
The distance between the horizontal plane where the airfoil rotation center of the blade is located and the horizontal plane where the airfoil rotation center of the blade is located at the position which is at a distance of 107.5mm from the center of the hub and is at 50% of the radius of the propeller from the center of the hub is 0.45mm +/-0.2 mm; and/or
And at a distance of 105mm from the center of the hub, the distance between the horizontal plane where the airfoil rotation center of the blade is located and the horizontal plane where the airfoil rotation center of the blade is located at a distance of 50% of the radius of the propeller from the center of the hub is 0.03mm +/-0.01 mm.
24. The aircraft of claim 22, wherein:
the angle of attack of the blades is 17.50 ° ± 2.5 ° at a distance of 41.7% of the radius of the propeller from the center of the hub; and/or
The angle of attack of the blades is 16.54 ° ± 2.5 ° at a distance from the centre of the hub of 50% of the radius of the propeller; and/or
At 58.3% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 15.45 ° ± 2.5 °; and/or
At 66.7% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 14.25 ° ± 2.5 °; and/or
The angle of attack of the blades is 12.97 ° ± 2.5 ° at a distance from the center of the hub of 75% of the radius of the propeller.
25. The aircraft of claim 24, wherein:
the angle of attack of the blades is 18.95 ° ± 2.5 ° at a distance from the centre of the hub of 25% of the radius of the propeller; and/or
At 33.3% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 18.38 ° ± 2.5 °; and/or
The angle of attack of the blades is 11.49 ° ± 2.5 ° at 83.3% of the radius of the propeller from the center of the hub; and/or
The angle of attack of the blades is 9.47 ° ± 2.5 ° at 91.7% of the radius of the propeller from the center of the hub; and/or
The angle of attack of the blades is 5.94 ° ± 2.5 ° at a distance from the centre of the hub of 100% of the radius of the propeller; and/or
At 30mm from the centre of the hub, the angle of attack of the blade is 18.95 °; and/or
At 40mm from the centre of the hub, the angle of attack of the blade is 18.38 °; and/or
At 50mm from the centre of the hub, the angle of attack of the blade is 17.50 °; and/or
At 60mm from the centre of the hub, the angle of attack of the blade is 16.54 °; and/or
At 70mm from the centre of the hub, the angle of attack of the blade is 15.45 °; and/or
At 80mm from the centre of the hub, the angle of attack of the blade is 14.25 °; and/or
At 90mm from the center of the hub, the angle of attack of the blade is 12.97 °; and/or
At 100mm from the centre of the hub, the angle of attack of the blade is 11.49 °; and/or
At 110mm from the centre of the hub, the angle of attack of the blade is 9.47 °; and/or
At 120mm from the centre of the hub, the angle of attack of the blade is 5.94 °.
26. The aircraft of claim 24, wherein:
the chord length of the blade is 29.80mm ± 5mm at a distance of 41.7% of the radius of the propeller from the centre of the hub; and/or
The chord length of the blade is 28.54mm + -5 mm at a distance of 50% of the radius of the propeller from the center of the hub; and/or
The chord length of the blade is 27.27mm ± 5mm at 58.3% of the radius of the propeller from the centre of the hub; and/or
The chord length of the blade is 25.98mm ± 5mm at 66.7% of the radius of the propeller from the centre of the hub; and/or
The chord length of the blade is 24.71mm ± 5mm at a distance of 75% of the radius of the propeller from the centre of the hub.
27. The aircraft of claim 26, wherein:
the chord length of the blade is 32.01mm + -5 mm at a distance of 25% of the radius of the propeller from the center of the hub; and/or
The chord length of the blade is 31.05mm + -5 mm at a distance of 33.3% of the radius of the propeller from the center of the hub; and/or
The chord length of the blade is 21.48mm ± 5mm at a distance of 83.3% of the radius of the propeller from the center of the hub; and/or
The chord length of the blade is 15.40mm + -5 mm at a distance of 91.7% of the radius of the propeller from the center of the hub; and/or
The chord length of the blade is 3.61mm ± 2mm at a distance from the centre of the hub of 100% of the radius of the propeller.
At 30mm from the centre of the hub, the chord length of the blade is 32.01 mm; and/or
The chord length of the blade is 31.05mm at 40mm from the centre of the hub; and/or
At 50mm from the centre of the hub, the chord length of the blade is 29.80 mm; and/or
At 60mm from the centre of the hub, the chord length of the blade is 28.54 mm; and/or
At 70mm from the centre of the hub, the chord length of the blade is 27.27 mm; and/or
At 80mm from the centre of the hub, the chord length of the blade is 25.98 mm; and/or
The chord length of the blade is 24.71mm at 90mm from the centre of the hub; and/or
At 100mm from the centre of the hub, the chord length of the blade is 21.48 mm; and/or
At 110mm from the centre of the hub, the chord length of the blade is 15.40 mm; and/or
The chord length of the blade is 3.61mm at 120mm from the centre of the hub.
28. The aircraft of claim 22, wherein:
the diameter of the propeller is 240mm +/-24 mm; and/or
The pitch of the blade is 5.36 + -0.5 inches.
29. The aircraft according to any one of claims 22 to 28, wherein:
the blade also comprises a front edge connected to one side of the pressure surface and the suction surface, a rear edge connected to the other side of the pressure surface and the suction surface, and a swept-back part formed at the blade tip, wherein the swept-back part extends from the front edge to the rear edge in an inclined manner; and/or
The rear edge is convexly provided with a curved rear edge arch part close to the paddle root.
30. The aircraft of claim 29, wherein:
the blade forms a return bend at the position of the blade tip, the front edge extends obliquely from the return bend along the span direction of the blade towards the side where the pressure surface is located, the sweepback extends obliquely from the return bend from the front edge to the rear edge, and the distance from the return bend to the center of the hub is 87.5% of the radius of the propeller.
31. The aircraft of claim 29, wherein:
the number of the blades is at least two, and the at least two blades are connected to the hub and are in central symmetry with respect to the center of the hub; and/or
The blade having a central axis passing through the center of the hub, the leading edge having a leading edge tangent parallel to the central axis, the trailing edge having a trailing edge tangent parallel to the central axis, the sweep being located between the leading edge tangent and the trailing edge tangent; and/or
The suction surface and the pressure surface are both curved surfaces.
32. The aircraft according to any one of claims 22 to 31, wherein said drive element is an electric motor having KV values of 720 ± 72 revolutions/(min-volt).
33. The vehicle according to any one of claims 22 to 32, wherein said vehicle comprises a plurality of power modules, said plurality of power modules being rotated in different directions, said vehicle being a multi-rotor vehicle.
Technical Field
The invention relates to the field of aircrafts, in particular to a propeller, a power assembly and an aircraft.
Background
Propellers on aircraft, which are important key components of aircraft, are used to convert the rotation of a rotating shaft in a motor or an engine into thrust or lift. The turbulence of the blade sections and the impingement of the downwash air on the aircraft skin structure during rotation of prior art propellers can produce loud noise. The noise of the aircraft, the motor noise and the structural vibration noise are often superposed together, and the noise of certain frequency bands is amplified, so that the overall noise of the aircraft is high, and the use experience is poor.
Disclosure of Invention
The embodiment of the invention provides a propeller, a power assembly and an aircraft.
A propeller of an embodiment of the present invention comprises a hub and blades attached to the hub, wherein: the paddle comprises a paddle root, a paddle tip, a pressure surface and a suction surface, wherein the paddle tip is deviated from the paddle root; the blade tip extends towards one side of the pressure surface along the spanwise direction of the blade in an inclined mode; the distance between a horizontal plane in which the airfoil-shaped rotation center of the blade is located and a horizontal plane in which the airfoil-shaped rotation center of the blade is located at a position that is located at a distance of 100% of the radius of the propeller from the center of the hub and a horizontal plane in which the airfoil-shaped rotation center of the blade is located at a distance of 50% of the radius of the propeller from the center of the hub is 3.0% to 9.3% of the radius of the propeller.
In some embodiments, the distance between a horizontal plane at which the centre of rotation of the airfoil of the blade lies and a horizontal plane at which the centre of rotation of the airfoil of the blade lies at 50% of the radius of the propeller from the centre of the hub is from 2.6% to 7.0% of the radius of the propeller at 97.9% of the radius of the propeller from the centre of the hub; and/or
The distance between a horizontal plane where the airfoil rotation center of the blade is located and a horizontal plane where the airfoil rotation center of the blade is located at a distance of 95.8% of the radius of the propeller from the center of the hub and a horizontal plane where the airfoil rotation center of the blade is located at a distance of 50% of the radius of the propeller from the center of the hub is 1.4% to 5.4% of the radius of the propeller; and/or
The distance between a horizontal plane where the airfoil rotation center of the blade is located and a horizontal plane where the airfoil rotation center of the blade is located at a distance of 93.8% of the radius of the propeller from the center of the hub and a horizontal plane where the airfoil rotation center of the blade is located at a distance of 50% of the radius of the propeller from the center of the hub is 1.1% to 3.2% of the radius of the propeller; and/or
The distance between a horizontal plane where the airfoil rotation center of the blade is located and a horizontal plane where the airfoil rotation center of the blade is located at a distance of 91.7% of the radius of the propeller from the center of the hub and a horizontal plane where the airfoil rotation center of the blade is located at a distance of 50% of the radius of the propeller from the center of the hub is 0.2% to 2.1% of the radius of the propeller; and/or
The distance between a horizontal plane where the airfoil rotation center of the blade is located and a horizontal plane where the airfoil rotation center of the blade is located at a
The distance between a horizontal plane in which the airfoil rotation center of the blade is located and a horizontal plane in which the airfoil rotation center of the blade is located at a distance of 87.5% of the radius of the propeller from the center of the hub and a horizontal plane in which the airfoil rotation center of the blade is located at a distance of 50% of the radius of the propeller from the center of the hub is 0.02% to 0.04% of the radius of the propeller; and/or
The distance between a horizontal plane where the airfoil rotation center of the blade is located and a horizontal plane where the airfoil rotation center of the blade is located at a position which is 120mm away from the center of the hub and is 50% of the radius of the propeller from the center of the hub is 7.00mm +/-3 mm; and/or
The distance between the horizontal plane where the airfoil rotation center of the blade is located and the horizontal plane where the airfoil rotation center of the blade is located at the position which is 50% of the radius of the propeller from the center of the hub is 5.40mm +/-3 mm at 117.5mm from the center of the hub; and/or
The distance between the horizontal plane of the airfoil rotation center of the blade at a position 115mm away from the center of the hub and the horizontal plane of the airfoil rotation center of the blade at a
The distance between the horizontal plane of the airfoil rotation center of the blade at 112.5mm from the center of the hub and the horizontal plane of the airfoil rotation center of the blade at 50% of the radius of the propeller from the center of the hub is 2.46mm +/-1 mm; and/or
At a distance of 110mm from the center of the hub, the distance between the horizontal plane of the airfoil rotation center of the blade and the horizontal plane of the airfoil rotation center of the blade at a distance of 50% of the radius of the propeller from the center of the hub is 1.29mm +/-1 mm; and/or
The distance between the horizontal plane where the airfoil rotation center of the blade is located and the horizontal plane where the airfoil rotation center of the blade is located at the position which is at a distance of 107.5mm from the center of the hub and is at 50% of the radius of the propeller from the center of the hub is 0.45mm +/-0.2 mm; and/or
And at a distance of 105mm from the center of the hub, the distance between the horizontal plane where the airfoil rotation center of the blade is located and the horizontal plane where the airfoil rotation center of the blade is located at a distance of 50% of the radius of the propeller from the center of the hub is 0.03mm +/-0.01 mm.
In certain embodiments, the angle of attack of the blades is 17.50 ° ± 2.5 ° at a distance from the center of the hub of 41.7% of the radius of the propeller; and/or
The angle of attack of the blades is 16.54 ° ± 2.5 ° at a distance from the centre of the hub of 50% of the radius of the propeller; and/or
At 58.3% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 15.45 ° ± 2.5 °; and/or
At 66.7% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 14.25 ° ± 2.5 °; and/or
The angle of attack of the blades is 12.97 ° ± 2.5 ° at a distance from the center of the hub of 75% of the radius of the propeller.
In certain embodiments, the angle of attack of the blades is 18.95 ° ± 2.5 ° at a distance from the center of the hub of 25% of the radius of the propeller; and/or
At 33.3% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 18.38 ° ± 2.5 °; and/or
The angle of attack of the blades is 11.49 ° ± 2.5 ° at 83.3% of the radius of the propeller from the center of the hub; and/or
The angle of attack of the blades is 9.47 ° ± 2.5 ° at 91.7% of the radius of the propeller from the center of the hub; and/or
The angle of attack of the blades is 5.94 ° ± 2.5 ° at a distance from the centre of the hub of 100% of the radius of the propeller; and/or
At 30mm from the centre of the hub, the angle of attack of the blade is 18.95 °; and/or
At 40mm from the centre of the hub, the angle of attack of the blade is 18.38 °; and/or
At 50mm from the centre of the hub, the angle of attack of the blade is 17.50 °; and/or
At 60mm from the centre of the hub, the angle of attack of the blade is 16.54 °; and/or
At 70mm from the centre of the hub, the angle of attack of the blade is 15.45 °; and/or
At 80mm from the centre of the hub, the angle of attack of the blade is 14.25 °; and/or
At 90mm from the center of the hub, the angle of attack of the blade is 12.97 °; and/or
At 100mm from the centre of the hub, the angle of attack of the blade is 11.49 °; and/or
At 110mm from the centre of the hub, the angle of attack of the blade is 9.47 °; and/or the angle of attack of the blades is 5.94 ° at 120mm from the centre of the hub.
In some embodiments, the chord length of the blade is 29.80mm ± 5mm at 41.7% of the radius of the propeller from the center of the hub; and/or
The chord length of the blade is 28.54mm + -5 mm at a distance of 50% of the radius of the propeller from the center of the hub; and/or
The chord length of the blade is 27.27mm ± 5mm at 58.3% of the radius of the propeller from the centre of the hub; and/or
The chord length of the blade is 25.98mm ± 5mm at 66.7% of the radius of the propeller from the centre of the hub; and/or
The chord length of the blade is 24.71mm ± 5mm at a distance of 75% of the radius of the propeller from the centre of the hub.
In some embodiments, the chord length of the blade is 32.01mm ± 5mm at a distance of 25% of the radius of the propeller from the center of the hub; and/or
The chord length of the blade is 31.05mm + -5 mm at a distance of 33.3% of the radius of the propeller from the center of the hub; and/or
The chord length of the blade is 21.48mm ± 5mm at a distance of 83.3% of the radius of the propeller from the center of the hub; and/or
The chord length of the blade is 15.40mm + -5 mm at a distance of 91.7% of the radius of the propeller from the center of the hub; and/or
The chord length of the blade is 3.61mm ± 2mm at a distance from the centre of the hub of 100% of the radius of the propeller.
At 30mm from the centre of the hub, the chord length of the blade is 32.01 mm; and/or
The chord length of the blade is 31.05mm at 40mm from the centre of the hub; and/or
At 50mm from the centre of the hub, the chord length of the blade is 29.80 mm; and/or
At 60mm from the centre of the hub, the chord length of the blade is 28.54 mm; and/or
At 70mm from the centre of the hub, the chord length of the blade is 27.27 mm; and/or
At 80mm from the centre of the hub, the chord length of the blade is 25.98 mm; and/or
The chord length of the blade is 24.71mm at 90mm from the centre of the hub; and/or
At 100mm from the centre of the hub, the chord length of the blade is 21.48 mm; and/or
At 110mm from the centre of the hub, the chord length of the blade is 15.40 mm; and/or
The chord length of the blade is 3.61mm at 120mm from the centre of the hub.
In certain embodiments, the diameter of the propeller is 240mm ± 24 mm; and/or the pitch of the blade is 5.36 plus or minus 0.5 inches.
In some embodiments, the blade further comprises a leading edge connected to one side of the pressure surface and the suction surface, a trailing edge connected to the other side of the pressure surface and the suction surface, and a swept back portion formed at the tip of the blade, the swept back portion extending obliquely from the leading edge to the trailing edge; and/or
The rear edge is convexly provided with a curved rear edge arch part close to the paddle root.
In some embodiments, the blade forms a return bend at the tip, the leading edge extends obliquely from the return bend along the span of the blade towards the side on which the pressure surface is located, the sweep extends obliquely from the return bend from the leading edge towards the trailing edge, and the return bend is 87.5% of the radius of the propeller from the centre of the hub.
In some embodiments, the number of blades is at least two, and at least two of the blades are attached to the hub and are centrosymmetric about the center of the hub; and/or
The blade having a central axis passing through the center of the hub, the leading edge having a leading edge tangent parallel to the central axis, the trailing edge having a trailing edge tangent parallel to the central axis, the sweep being located between the leading edge tangent and the trailing edge tangent; and/or
The suction surface and the pressure surface are both curved surfaces.
The power assembly of the embodiment of the invention comprises a driving piece and the propeller of any one of the above embodiments, wherein the propeller is connected with the driving piece through the propeller hub.
In certain embodiments, the drive member is an electric motor having KV values of 720 ± 72 revolutions/(min-volt).
The aircraft of the embodiment of the invention comprises a fuselage and the power assembly of any one of the above embodiments, wherein the power assembly is connected with the fuselage.
In some embodiments, the aircraft includes a plurality of power assemblies that rotate in different directions, and the aircraft is a multi-rotor aircraft.
According to the propeller, the power assembly and the aircraft provided by the embodiment of the invention, the tip of the propeller extends obliquely towards one side of the pressure surface along the span direction of the propeller blade, and the distance between the horizontal plane where the airfoil-shaped rotating center of the propeller blade is located and the center of the propeller hub is 50% of the radius of the propeller blade is 3.0-9.3% of the radius of the propeller blade at the position where the center of the propeller blade is located; therefore, the propeller with the specific shape is defined by the parameters, on one hand, the propeller with the propeller can reduce the air resistance of the propeller, improve the pulling force and the efficiency, increase the secondary flight distance of the aircraft so as to improve the flight performance of the aircraft, and on the other hand, the propeller can reduce the noise generated by the propeller during working, so that the aircraft is quieter when hovering, and the user experience is improved.
Additional aspects and advantages of embodiments of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of embodiments of the invention.
Drawings
The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which: newly-added figure modification, illustration in description
Fig. 1 is a perspective view of a propeller according to an embodiment of the present invention.
Fig. 2 is a schematic plan view of a propeller according to an embodiment of the present invention.
Fig. 3 is a schematic plan view of a propeller according to an embodiment of the present invention.
Fig. 4 is a schematic plan view of a propeller according to an embodiment of the present invention.
FIG. 5 is a schematic diagram of frequency response curves of the propeller of the present invention and the existing propeller I and propeller II under the same test conditions of hovering condition acoustic performance.
Fig. 6 is a schematic coordinate diagram of a rotation center of an airfoil of a blade provided by an embodiment of the invention.
Fig. 7 is a schematic plan view of the tip in the propeller of the embodiment shown in fig. 4.
Fig. 8 is a cross-sectional view of the section K-K at 15mm from the free end of the propeller of the embodiment shown in fig. 7.
Figure 9 is a cross-sectional view of the O-O section at 12.5mm from the free end of the propeller of the embodiment shown in figure 7.
Fig. 10 is a cross-sectional view of the L-L section at 10mm from the free end of the propeller of the embodiment shown in fig. 7.
Figure 11 is a cross-sectional view of the section P-P at 7.5mm from the free end of the propeller of the embodiment shown in figure 7.
Fig. 12 is a cross-sectional view of the section N-N at 5mm from the free end of the propeller of the embodiment shown in fig. 7.
Fig. 13 is a cross-sectional view of the section Q-Q at 2.5mm from the free end of the propeller of the embodiment shown in fig. 7.
Figure 14 is a cross-sectional view of section a-a at 30mm from the hub center in the propeller of the embodiment shown in figure 4.
Figure 15 is a cross-sectional view of the section B-B in the propeller of the embodiment shown in figure 4 at 40mm from the centre of the hub.
Figure 16 is a cross-sectional view of the C-C section at 50mm from the center of the hub in the propeller of the embodiment shown in figure 4.
Figure 17 is a cross-sectional view of the D-D section at 60mm from the center of the hub in the propeller of the embodiment shown in figure 4.
Figure 18 is a cross-sectional view of the section E-E in the propeller of the embodiment shown in figure 4 at 70mm from the centre of the hub.
Figure 19 is a cross-sectional view of the F-F section at 80mm from the center of the hub in the propeller of the embodiment shown in figure 4.
Figure 20 is a cross-sectional view of the G-G section in the propeller of the embodiment shown in figure 4 at 90mm from the center of the hub.
Figure 21 is a cross-sectional view of the section H-H at 100mm from the hub centre in the propeller of the embodiment shown in figure 4.
Figure 22 is a cross-sectional view of the section I-I at 110mm from the hub centre in the propeller of the embodiment shown in figure 4.
Figure 23 is a cross-sectional view of the J-J section at 120mm from the hub center of the propeller of the embodiment shown in figure 4.
Fig. 24 is a schematic plan view of an aircraft according to an embodiment of the invention.
Detailed Description
Reference will now be made in detail to the exemplary embodiments, examples of which are illustrated in the accompanying drawings. When the following description refers to the accompanying drawings, like numbers in different drawings represent the same or similar elements unless otherwise indicated. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present invention. Rather, they are merely examples of apparatus and methods consistent with certain aspects of the invention, as detailed in the appended claims.
The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used in this specification and the appended claims, the singular forms "a", "an", and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It should also be understood that the term "and/or" as used herein refers to and encompasses any and all possible combinations of one or more of the associated listed items.
It is to be understood that although the terms first, second, third, etc. may be used herein to describe various information, these information should not be limited to these terms. These terms are only used to distinguish one type of information from another. For example, first information may also be referred to as second information, and similarly, second information may also be referred to as first information, without departing from the scope of the present invention. The word "if" as used herein may be interpreted as "at … …" or "when … …" or "in response to a determination", depending on the context.
The terms upper, lower, etc. are used in this embodiment with reference to the propeller after it is mounted on the aircraft and to the normal operating attitude of the aircraft and should not be considered limiting.
The propeller, the power assembly and the aircraft according to the embodiments of the present invention will be described in detail below with reference to the accompanying drawings. The features of the following examples and embodiments may be combined with each other without conflict.
Referring to fig. 1 to 4, an embodiment of the present invention provides a
In the
Referring to table 1, a comparison between the test results of the
TABLE 1
Referring to fig. 5, the
With continued reference to fig. 1-4, in the present embodiment, optionally, the
In this embodiment, the
In this embodiment, optionally, the
In this embodiment, the
In this embodiment, the
In the present embodiment, at least two
In this embodiment, optionally,
Referring to fig. 1, in the present embodiment, the
Referring to table 2, Blade Radius (mm) indicates the X-axis coordinate position of the airfoil rotation center of
TABLE 2
As can be seen from table 2, when the distance of the
As can be seen from table 2, when the distance from the
Referring also to fig. 7-13, in this embodiment, the swept back
referring to fig. 8, in the present embodiment, optionally, the diameter of the propeller 100 is 240mm ± 24mm, when the distance between the blade 20 and the free end 222 is 15mm, that is, the distance between the blade 20 and the center of the hub 10 is 105mm, that is, when the distance between the blade 20 and the center of the propeller 100 is 87.5% of the radius D11 from the center of the hub 10, the distance between the horizontal plane on which the airfoil rotation center of the blade 20 is located and the center of the propeller 100 is 50% of the radius of the propeller 100 is 0.03mm ± 0.01mm, the angle of attack α of the blade 20 is 10.52 ° ± 2.5 °, the chord length L11 of the blade 20 is 18.71mm ± 5mm, so as to further reduce the air resistance of the propeller 100, improve the drag force and efficiency, and reduce the noise, wherein the distance between the two horizontal planes may be 0.02mm, 0.03mm, 0.04mm, 0.02mm, 71mm, 13.0313.71 mm, 13.71mm, 13.02 mm, 13.71mm, 14.19 mm, 13.19 mm, 14.19 mm, 14 mm, 14.19 mm, 14.5 mm, 14.02 mm, 14 mm, 14.02 mm, 14.19 mm, 14.5 mm, 14 mm, 14.02 mm, 14.5 mm, 14.02 mm, 14.19 mm, 13.5 mm, 14.19 mm, 14.5 mm, 13.9.9.9.9.9.5 mm, 14.9.9.9.9.9 mm, 14.9.9 mm, 14.9.9.5 mm, 14 mm, 14.9.9.9.9.9 mm, 14.9.9 mm, 14 mm, or 13.9.
Referring to fig. 9, in the present embodiment, optionally, the diameter of the propeller 100 is 240mm ± 24mm, when the distance between the blade 20 and the free end 222 is 12.5mm, that is, the distance between the blade 20 and the center of the hub 10 is 107.5mm, that is, when the distance between the blade 20 and the center of the propeller 100 is D12 at 89.2% D11, the distance between the horizontal plane on which the airfoil rotation center of the blade 20 is located and the horizontal plane on which the airfoil rotation center of the blade 20 is located at 50% of the radius of the propeller 100 from the center of the hub 10 is 0.45mm ± 0.2mm, the angle of attack α of the blade 20 is 9.95 ° ± 2.5mm, and the chord length L12 of the blade 20 is 17.10mm ± 5mm, so as to further reduce the air resistance of the propeller 100, improve the efficiency and reduce the noise, and the angle of attack may be any one of 0.25mm, 0.45mm, 0.65mm, 0.29mm, 0.34.34 mm, 0.34mm, 0.42mm, 10.45 mm, 10.9 mm, 10mm, 10.5 mm, 10mm, 10.9.9 mm, 10mm, 10.9.9.9.9 mm, 10mm, 10.9.9.9 mm, 10mm, 10.9.9.9.5 mm, 10 mm.
Referring to fig. 10, in the present embodiment, optionally, when the diameter of the
Referring to fig. 11, in the present embodiment, optionally, the diameter of the
Referring to fig. 12, in the present embodiment, optionally, when the diameter of the propeller 100 is 240mm ± 24mm, and the distance between the blade 20 and the free end 222 is 5mm, that is, the distance between the blade 20 and the center of the hub 10 is 115mm, that is, the distance between the blade 20 and the horizontal plane at which the airfoil rotation center of the blade 20 is located at 50% of the radius of the propeller 100 is located at 95.8% D15 from the center of the hub 10 is 3.86mm ± 2mm, the angle of attack α of the blade 20 is 7.72 ° ± 2.5 °, and the chord length L15 of the blade 20 is 11.80mm ± 5mm, so as to further reduce the air resistance of the propeller 100, improve the pulling force and the efficiency, and reduce the noise, the distance between the two horizontal planes may be 1.86mm, 3.86mm, or 5.86mm, or 2.80mm, or 4.9.9 mm, 9.9 mm, or 4.9.9.9 mm, or 10.6 mm, 7.7.7.5 mm, or 10.7.5 mm, 14 mm, or 7.5.5 mm, 14.7.5%, or 7.7.7.5%, or 7.5%, or 7, 14.6, 7.5% of the angle of the above-7.7.5, 10.7.5, 14, 7.5, 7.7.5, 7.5, 7, 7.5, 7.7, 7.5, 7, 7.5, 7.7.5, 7.5, 7, or two of the above-7.9, 7, 7.7..
Referring to fig. 13, in the present embodiment, optionally, the diameter of the propeller 100 is 240mm ± 24mm, when the distance between the blade 20 and the free end 222 is 2.5mm, that is, the distance between the blade 20 and the center of the hub 10 is 117.5mm, that is, when the distance between the blade 20 and the radius of the propeller 100 is 97.9% D16% from the center of the hub 10, the distance between a horizontal plane on which the airfoil rotation center of the blade 20 is located and a horizontal plane on which the airfoil rotation center of the blade 20 is located 50% of the radius of the propeller 100 from the center of the hub 10 is 5.40mm ± 3mm, the angle of attack α of the blade 20 is 6.25 ° ± 2.5 °, and the chord length L16 of the blade 20 is 9.92mm ± 5mm, so as to further reduce the air resistance of the propeller 100, improve the drag and efficiency, and reduce the noise, wherein the distance between the two horizontal planes may be 2.40mm, 5.40mm, 8mm, 8.40mm, 7.40mm, 7.75 mm, 7.92mm, 14.75 mm, 14.92mm, 7.92mm, 7.75 mm, 14.92mm, 8.5 mm, 7.5mm, or 7.75 mm, 14.92mm, 14.5 mm, or 7.5mm, and the like, and the angle of the above-8.12 mm may be any of the above-8.92 mm, 7.92mm, 10.92mm, 7.75 mm, 7.92, 12 mm, 7.92mm, or 7.92mm, 7.75 mm, or 7.12 mm, or 7.92mm, 12 mm, 7.92mm, or 7.75 mm, 7.92 mm.
Referring to fig. 7, in the present embodiment, the diameter of the
Referring again to fig. 7 to 13, in the present embodiment, optionally, the diameter of the propeller 100 is 240mm ± 24mm, the distance between the horizontal plane where the airfoil rotation center of the blade 20 is located and the horizontal plane where the airfoil rotation center of the blade 20 is located at 50% of the radius of the propeller 100 is 0.03mm, the angle of attack α of the blade 20 is 10.52 mm, the chord length L11 of the blade 20 is 18.71mm, the distance between the blade 20 and the free end 222 is 12.5mm, the distance between the horizontal plane where the airfoil rotation center of the blade 20 is located and the horizontal plane where the airfoil rotation center of the blade 20 is located at 50% of the radius of the propeller 10 is 0.45mm, the angle of attack α of the blade 20 is 9.95 mm, the chord length L12 of the blade 20 is 17.10mm, the distance between the blade 20 and the horizontal plane where the airfoil rotation center of the blade 20 is located at 50% of the radius of the propeller 100, the propeller 100mm, the blade 20 is 260.8 mm, the horizontal plane where the airfoil rotation center of the blade 20 is located at 20mm, the distance between the horizontal plane 20mm, the horizontal plane rotation center of the airfoil rotation center of the propeller 20 is 2mm, the propeller rotation center of the propeller 20 is 2mm, the blade 20, the distance between the horizontal plane 20, the horizontal plane 20 is 2mm, the propeller rotation center of the propeller 20 is 2mm, the propeller rotation center of the propeller 20 is 2mm, the propeller rotation distance between the propeller 20 is 2mm, the propeller rotation center of the propeller 20 is 2mm, the propeller rotation center of the propeller 20 is 120mm, the propeller rotation center of the propeller rotation distance between the propeller rotation center of the propeller 20 is 120mm, the propeller rotation center of the propeller rotation distance between the propeller rotation center of the propeller 20 is 2mm, the propeller rotation center of the propeller 20 is 2mm, the propeller rotation distance between the propeller 20 is 120mm, the propeller rotation center of the propeller rotation distance between the propeller 20, the propeller rotation center of the propeller rotation distance between the propeller rotation center of the propeller 20 is 2mm, the propeller rotation center of the propeller rotation distance of the propeller rotation center of the propeller 20 is 120mm, the propeller rotation center of the propeller 20 is 2mm, the propeller rotation center of the propeller rotation distance between the propeller rotation center of the propeller 20 is 2mm, the propeller rotation distance of the propeller 20 is 2mm, the propeller rotation center of the propeller 20 is 120mm, the propeller rotation distance of the propeller 20 is 2mm, the propeller rotation center of the propeller 20.
Referring to fig. 14, in the present embodiment, optionally, at a
Referring to fig. 15, in the present embodiment, optionally, at a distance of 33.3% of the radius of the
Referring to fig. 16, in the present embodiment, optionally, at a position D3 that is 41.7% of the radius of the
Referring to fig. 17, in the present embodiment, optionally, at a
Referring to fig. 18, in the present embodiment, optionally, at a position 58.3% of the radius of the
Referring to fig. 19, in the present embodiment, optionally, at a position 66.7% of the radius of the
Referring to fig. 20, in the present embodiment, optionally, at a
Referring to fig. 21, in the present embodiment, optionally, D8 is located 83.3% of the radius of the
Referring to fig. 22, in the present embodiment, optionally, at a position 91.7% of the radius of the
Referring to fig. 23, in the present embodiment, optionally, at a position D10 which is 100% of the radius of the
Referring again to fig. 14 to 23, in the present embodiment, optionally, the diameter of the propeller 100 is 240mm ± 24mm, D1 at 30mm from the center of the hub 10, the angle of attack α of the blade 20 is 18.95 °, the chord length L1 of the blade 20 is 32.01mm, D2 at 40mm from the center of the hub 10, the angle of attack α 2 of the blade 20 is 18.38 °, the chord length L2 of the blade 20 is 31.05mm, D3 at 50mm from the center of the hub 10, the angle of attack α of the blade 20 is 17.50 °, the chord length L3 of the blade 20 is 29.80mm, D4 at 60mm from the center of the hub 10, the angle of attack 4 of the blade 20 is 16.54 °, the chord length L72 of the blade 20 is 28.54mm, D4 at 70mm from the center of the hub 10, D4 mm, the chord length L4 mm of the blade 20 is 28.54mm, the chord length L4 mm at 70mm from the center of the hub 10, the center of the blade 72 mm, the angle of the blade 72 mm is 36mm, the chord length L36 mm, the angle of the blade 72 mm is 240mm, the angle of the blade 72 mm, the angle of the blade 72 mm is 3.28.28.28.28 mm, the angle of the blade 72 mm, the angle of the center of the angle of the blade 72 mm, the angle of the center of the angle of the blade 72 mm, the angle of the blade 72 mm is 36mm, the angle of the blade 72 mm, the angle of the angle.
In this embodiment, the pitch of the
In conclusion, the
In some embodiments, the distance between a horizontal plane in which the airfoil center of rotation of the
The distance between the horizontal plane where the airfoil rotation center of the
The distance between the horizontal plane where the airfoil rotation center of the
The distance between the horizontal plane where the airfoil rotation center of the
The distance between the horizontal plane where the airfoil rotation center of the
The distance between the horizontal plane where the airfoil rotation center of the
At a distance of 120mm from the center of the
The distance between the horizontal plane where the airfoil rotation center of the
The distance between the horizontal plane of the airfoil rotation center of the
The distance between the horizontal plane of the airfoil rotation center of the
At a distance of 110mm from the center of the
At a distance of 107.5mm from the center of the
The distance between the horizontal plane in which the centre of rotation of the airfoil of the
The discussion herein includes, but is not limited to, the following:
(1) the distance between the horizontal plane where the airfoil rotation center of the
(2) the distance between the horizontal plane where the airfoil rotation center of the
(3) the distance between the horizontal plane where the airfoil rotation center of the
(4) the distance between the horizontal plane where the airfoil rotation center of the
(5) the distance between the horizontal plane where the airfoil rotation center of the
(6) the distance between the horizontal plane where the airfoil rotation center of the
(1) at a distance of 120mm from the center of the
(7) the distance between the horizontal plane where the airfoil rotation center of the
(8) the distance between the horizontal plane of the airfoil rotation center of the
(9) the distance between the horizontal plane of the airfoil rotation center of the
(10) at a distance of 110mm from the center of the
(11) at a distance of 107.5mm from the center of the
(12) at a distance of 105mm from the center of the
(13) the distance between the horizontal plane where the airfoil rotation center of the blade 20 is located and the horizontal plane where the airfoil rotation center of the blade 20 is located at a distance of 97.9% of the radius of the propeller 100 from the center of the hub 10 and the horizontal plane where the airfoil rotation center of the blade 20 is located at a distance of 50% of the radius of the propeller 100 from the center of the hub 10 is 2.6% to 7.0% of the radius of the propeller 100; and, at a distance of 95.8% of the radius of the propeller 100 from the center of the hub 10, the distance between a horizontal plane on which the airfoil-shaped rotation center of the blade 20 is located and a horizontal plane on which the airfoil-shaped rotation center of the blade 20 at a distance of 50% of the radius of the propeller 100 from the center of the hub 10 is located is 1.4% to 5.4% of the radius of the propeller 100; and, at a distance of 93.8% of the radius of the propeller 100 from the center of the hub 10, the distance between a horizontal plane on which the airfoil-shaped rotation center of the blade 20 is located and a horizontal plane on which the airfoil-shaped rotation center of the blade 20 at a distance of 50% of the radius of the propeller 100 from the center of the hub 10 is located is 1.1% to 3.2% of the radius of the propeller 100; and, at a distance of 91.7% of the radius of the propeller 100 from the center of the hub 10, the distance between a horizontal plane on which the airfoil-shaped rotation center of the blade 20 is located and a horizontal plane on which the airfoil-shaped rotation center of the blade 20 at a distance of 50% of the radius of the propeller 100 from the center of the hub 10 is located is 0.2% to 2.1% of the radius of the propeller 100; and, at a distance of 89.2% of the radius of the propeller 100 from the center of the hub 10, the distance between the horizontal plane on which the airfoil-shaped rotation center of the blade 20 is located and the horizontal plane on which the airfoil-shaped rotation center of the blade 20 at a distance of 50% of the radius of the propeller 100 from the center of the hub 10 is located is 0.2% to 0.6% of the radius of the propeller 100; and, at 87.5% of the radius of the propeller 100 from the center of the hub 10, the distance between the horizontal plane on which the airfoil rotation center of the blade 20 is located and the horizontal plane on which the airfoil rotation center of the blade 20 at 50% of the radius of the propeller 100 from the center of the hub 10 is located is 0.02% to 0.04% of the radius of the propeller 100; and, at a distance of 120mm from the center of the hub 10, the distance between the horizontal plane on which the airfoil rotation center of the blade 20 is located and the horizontal plane on which the airfoil rotation center of the blade 20 at a distance of 50% of the radius of the propeller 100 from the center of the hub 10 is located is 7.00mm ± 3 mm; and, at 117.5mm from the center of the hub 10, the distance between the horizontal plane on which the airfoil rotation center of the blade 20 is located and the horizontal plane on which the airfoil rotation center of the blade 20 at 50% of the radius of the propeller 100 is located from the center of the hub 10 is 5.40mm ± 3 mm; and, at a distance of 115mm from the center of the hub 10, the distance between the horizontal plane on which the airfoil rotation center of the blade 20 is located and the horizontal plane on which the airfoil rotation center of the blade 20 at a distance of 50% of the radius of the propeller 100 from the center of the hub 10 is located is 3.86mm ± 2 mm; and, at 112.5mm from the center of the hub 10, the distance between the horizontal plane on which the airfoil rotation center of the blade 20 is located and the horizontal plane on which the airfoil rotation center of the blade 20 at 50% of the radius of the propeller 100 is located from the center of the hub 10 is 2.46mm ± 1 mm; and, at a distance of 110mm from the center of the hub 10, the distance between the horizontal plane on which the airfoil rotation center of the blade 20 is located and the horizontal plane on which the airfoil rotation center of the blade 20 at a distance of 50% of the radius of the propeller 100 from the center of the hub 10 is located is 1.29mm ± 1 mm; and, at a distance of 107.5mm from the center of the hub 10, the distance between the horizontal plane on which the airfoil rotation center of the blade 20 is located and the horizontal plane on which the airfoil rotation center of the blade 20 at a distance of 50% of the radius of the propeller 100 from the center of the hub 10 is located is 0.45mm ± 0.2 mm; and, at a distance of 105mm from the center of the hub 10, the distance between the horizontal plane on which the airfoil rotation center of the blade 20 is located and the horizontal plane on which the airfoil rotation center of the blade 20 at a distance of 50% of the radius of the propeller 100 from the center of the hub 10 is located is 0.03mm ± 0.01 mm.
In some embodiments, the
The angle of
The angle of
The angle of
At a distance D7 of 75% of the radius of the
The discussion herein includes, but is not limited to, the following:
(1) the
(2) the
(3) the
(4)
(5)
(6)
In some embodiments, the
The angle of
The angle of
The angle of
The angle of attack α 10 of the
An angle of attack α 1 of the
An angle of
An angle of
An angle of
An angle of
An angle of
An angle of
An angle of
An angle of
At 120mm from the center of the
The discussion herein includes, but is not limited to, the following:
(1)
(2)
(3) the
(4)
(5) the
(6)
(7)
(8)
(9)
(10) the
(11)
(12)
(13)
(14)
(15) the
(16) The rotor 100 has an angle of attack α of 18.95 ° ± 2.5 ° at a distance of 25% of the radius of the rotor 100 from the center of the hub 10, D2 at a distance of 33.3% of the radius of the rotor 100 from the center of the hub 10, the angle of attack α of the blades 20 is 18.38 ° ± 2.5 ° at the angle of attack α of 18.38 ° ± 2.5 ° at a distance of 83.3% of the radius of the rotor 100 from the center of the hub 10, the angle of attack α 08 of the blades 20 is 11.49 ° ± 2.5 ° at the angle of attack 3.3% of the radius of the rotor 100, D9 at a distance of 91.7% of the radius of the rotor 100 from the center of the hub 10, the angle of attack α of the blades 20 is 9.47 ° ± 2.5 ° at the angle of attack 10, D10 at a distance of 100% of the radius of the rotor 100 from the center of the hub 10, the angle α mm of the blade 72 mm at the angle of the center of the rotor 10, the angle of the rotor 72 mm, the center of the angle of the rotor 72 mm, the rotor 72 mm at the angle of the center of the rotor 72 mm, the angle of the rotor 72 mm at the rotor 10mm, the center of the rotor 10mm, the angle of the rotor 72 mm, the rotor 72 mm at the rotor 10mm, the angle of the rotor 72 mm at the angle of the rotor 10mm, the angle of the rotor 72 mm, the rotor 10mm, the rotor 72 mm at the rotor 10mm, the angle of the rotor 72 mm, the angle of the rotor 10mm, the rotor 72 mm, the rotor 10mm, the angle of the rotor 10mm, the rotor 72 mm, the rotor 10mm, the rotor 72 mm, the angle of the rotor 72.
In certain embodiments, the
At a distance D4 of 50% of the radius of the
At a distance D5 of 58.3% of the radius of the
At 66.7% of the radius of the
At a distance D7 of 75% of the radius of the
At a distance D3 of 50mm from the centre of the
At 60mm from the centre of the
At 70mm from the centre of the
At 80mm from the centre of the
At 90mm from the centre of the
The discussion herein includes, but is not limited to, the following:
(1) the
(2) the
(3) the
(4) the
(5) the
(6) the
(7) the
(8) the
(9) the
(10) the
(11) the propeller 100 is D3 at a distance of 41.7% of the radius of the propeller 100 from the center of the hub 10, and the chord length L3 of the blades 20 is 29.80mm +/-5 mm; and, at a distance D4 of 50% of the radius of the propeller 100 from the center of the hub 10, the chord length L4 of the blade 20 is 28.54mm ± 5 mm; and D5 at a distance of 58.3% of the radius of the propeller 100 from the center of the hub 10, the chord length L5 of the blades 20 is 27.27mm ± 5 mm; and D6 at 66.7% of the radius of the propeller 100 from the center of the hub 10, the chord length L6 of the blades 20 is 25.98mm ± 5 mm; and, at a distance D7 of 75% of the radius of the propeller 100 from the center of the hub 10, the chord length L7 of the blades 20 is 24.71mm ± 5 mm; and, at a distance of 50mm from the centre of the hub 10, D3, the chord length L3 of the blade 20 is 29.80 mm; and, at a distance of 60mm from the centre of the hub 10, D4, the chord length L4 of the blade 20 is 28.54 mm; and, at a distance of 70mm from the centre of the hub 10, D5, the chord length L5 of the blade 20 is 27.27 mm; and, at a distance of 80mm from the centre of the hub 10, D6, the chord length L6 of the blade 20 is 25.98 mm; and a chord length L7 of the blade 20 of 24.71mm at a distance D7 of 90mm from the center of the hub 10.
In certain embodiments, the
At a distance D2 of 33.3% of the radius of the
At a distance D8 of 83.3% of the radius of the
At a distance D9 of 91.7% of the radius of the
At a distance D10 from the centre of the
At 30mm from the centre of the hub 10D 1, the chord length L1 of the
At 40mm from the centre of the
At a distance of 100mm from the centre of the
At a distance D9 of 110mm from the centre of the
At 120mm from the centre of the
The discussion herein includes, but is not limited to, the following:
(1) the
(2) the
(3) the
(4) the
(5) the
(6) the
(7) the
(8) the
(9) the
(10) the
(11) the propeller 100 is D1 at a distance of 25% of the radius of the propeller 100 from the center of the hub 10, and the chord length L1 of the blades 20 is 32.01mm +/-5 mm; and D2 at 33.3% of the radius of the propeller 100 from the center of the hub 10, the chord length L2 of the blades 20 is 31.05mm ± 5 mm; and D8 at a distance D of 83.3% of the radius of the propeller 100 from the center of the hub 10, the chord length L8 of the blade 20 being 21.48mm ± 5 mm; and D9 at a distance of 91.7% of the radius of the propeller 100 from the center of the hub 10, the chord length L9 of the blades 20 is 15.40mm ± 5 mm; and, at a distance D10 from the center of the hub 10 of 100% of the radius of the propeller 100, the chord length L10 of the blade 20 is 3.61mm ± 2 mm; and, at a distance of 30mm from the centre of the hub 10, D1, the chord length L1 of the blade 20 is 32.01 mm; and, at a distance of 40mm from the centre of the hub 10, D2, the chord length L2 of the blade 20 is 31.05 mm; and, at a distance of 100mm from the centre of the hub 10, D8, the chord length L8 of the blade 20 is 21.48 mm; and, at a distance of 110mm from the centre of the hub 10, D9, the chord length L9 of the blade 20 is 15.40 mm; and a chord length L10 of the blade 20 of 3.61mm at a distance D10 of 120mm from the center of the hub 10.
Referring to fig. 24, an embodiment of the present invention provides a
In the
In this embodiment, the driving
Referring again to fig. 24, an embodiment of the present invention provides an
In this embodiment, the
In this embodiment, optionally, the
In the
Although the present invention has been described with reference to a preferred embodiment, it should be understood that various changes, substitutions and alterations can be made herein without departing from the spirit and scope of the invention as defined by the appended claims.
The disclosure of this patent document contains material which is subject to copyright protection. The copyright is owned by the copyright owner. The copyright owner has no objection to the facsimile reproduction by anyone of the patent document or the patent disclosure, as it appears in the patent and trademark office official records and records.
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