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 2018-09-30 设计创作,主要内容包括:一种螺旋桨、动力组件及飞行器。其中,在距离桨毂(10)的中心为螺旋桨(100)的半径的41.7%处,桨叶(20)的攻角为17.57°±2.5°;在距离桨毂(10)的中心为螺旋桨(100)的半径的50%处,桨叶(20)的攻角为16.65°±2.5°;在距离桨毂(10)的中心为螺旋桨(100)的半径的58.3%处,桨叶(20)的攻角为15.62°±2.5°;在距离桨毂(10)的中心为螺旋桨(100)的半径的66.7%处,桨叶(20)的攻角为14.48°±2.5°;在距离桨毂(10)的中心为螺旋桨(100)的半径的75%处,桨叶(20)的攻角为13.21°±2.5°。采用桨叶翼型渐变的螺旋桨能使得螺旋桨在沿着桨叶的展向的每一段都处于最佳工作段,在减少空气阻力、提高拉力和效率、增加飞行器的继航距离以提高飞行性能的同时,还减少了桨叶在工作时产生的噪声,使得飞行器在悬停时更安静。(A propeller, a power assembly and an aircraft are provided. Wherein the angle of attack of the blades (20) is 17.57 ° ± 2.5 ° at a distance from the centre of the hub (10) of 41.7% of the radius of the propeller (100); the angle of attack of the blades (20) is 16.65 ° ± 2.5 ° at a distance from the centre of the hub (10) of 50% of the radius of the propeller (100); the angle of attack of the blades (20) is 15.62 ° ± 2.5 ° at a distance from the centre of the hub (10) of 58.3% of the radius of the propeller (100); the angle of attack of the blades (20) is 14.48 ° ± 2.5 ° at a distance of 66.7% of the radius of the propeller (100) from the centre of the hub (10); the angle of attack of the blades (20) is 13.21 DEG + -2.5 DEG at a distance from the centre of the hub (10) of 75% of the radius of the propeller (100). The propeller with the gradually changed blade wing profiles can enable the propeller to be in the best working section along each section of the span direction of the blades, reduce air resistance, improve pulling force and efficiency, increase the secondary flight distance of an aircraft to improve flight performance, and simultaneously reduce noise generated by the blades during working, so that the aircraft is quieter when hovering.)
1. A propeller, comprising: a hub and blades attached to said hub, characterized in that:
the angle of attack of the blades is 17.57 ° ± 2.5 ° at a distance of 41.7% of the radius of the propeller from the center of the hub;
the angle of attack of the blades is 16.65 ° ± 2.5 ° at a distance from the centre of the hub of 50% of the radius of the propeller;
at 58.3% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 15.62 ° ± 2.5 °;
at 66.7% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 14.48 ° ± 2.5 °;
the angle of attack of the blades is 13.21 ° ± 2.5 ° at a distance from the center of the hub of 75% of the radius of the propeller.
2. The propeller of claim 1, wherein:
the angle of attack of the blades is 19.02 ° ± 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 18.40 ° ± 2.5 °; and/or
The angle of attack of the blades is 11.68 ° ± 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 9.56 ° ± 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 5.96 ° ± 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 19.02 °; and/or
At 40mm from the centre of the hub, the angle of attack of the blade is 18.40 °; and/or
At 50mm from the centre of the hub, the angle of attack of the blade is 17.57 °; and/or
At 60mm from the centre of the hub, the angle of attack of the blade is 16.65 °; and/or
At 70mm from the centre of the hub, the angle of attack of the blade is 15.62 °; and/or
At 80mm from the centre of the hub, the angle of attack of the blade is 14.48 °; and/or
At 90mm from the center of the hub, the angle of attack of the blade is 13.21 °; and/or
At 100mm from the centre of the hub, the angle of attack of the blade is 11.68 °; and/or
At 110mm from the centre of the hub, the angle of attack of the blade is 9.56 °; and/or
The angle of attack of the blade is 5.96 ° at 120mm from the centre of the hub.
3. The propeller of claim 1, wherein:
the chord length of the blade is 29.79mm ± 5mm at 41.7% of the radius of the propeller from the centre of the hub; and/or
The chord length of the blade is 28.53mm + -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 27.26mm ± 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 25.99mm ± 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 + -5 mm at a distance of 75% of the radius of the propeller from the center of the hub; and/or
The chord length of the blade at 50mm from the centre of the hub is 29.79 mm; and/or
At 60mm from the centre of the hub, the chord length of the blade is 28.53 mm; and/or
At 70mm from the centre of the hub, the chord length of the blade is 27.26 mm; and/or
The chord length of the blade is 25.99mm at 80mm from the centre of the hub; and/or
The chord length of the blade is 24.71mm at 90mm from the centre of the hub.
4. The propeller of claim 3, wherein:
the chord length of the blade is 32.12mm + -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 21.33mm ± 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 14.83mm + -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 3.83mm + -2 mm at a distance of 100% of the radius of the propeller from the center of the hub; and/or
At 30mm from the centre of the hub, the chord length of the blade is 32.12 mm; and/or
The chord length of the blade is 31.05mm at 40mm from the centre of the hub; and/or
At 100mm from the centre of the hub, the chord length of the blade is 21.33 mm; and/or
At 110mm from the centre of the hub, the chord length of the blade is 14.83 mm; and/or
At 120mm from the centre of the hub, the chord length of the blade is 3.83 mm.
5. The propeller of claim 1, wherein the propeller has a diameter of 240mm ± 24 mm; and/or
The pitch of the blade is 5.467 + -0.5 inches.
6. The propeller of any one of claims 1 to 5, wherein:
the blade comprises a blade root, a blade tip, a pressure surface and a suction surface, wherein the blade tip is deviated from the blade root, the pressure surface and the suction surface are opposite, the front edge is connected with one side edge of the pressure surface and the suction surface, the rear edge is connected with the other side edge of the pressure surface and the suction surface, and the sweepback part is formed on the blade tip and extends from the front edge to the rear edge in an inclined mode;
the blade tip extends obliquely towards the side of the pressure surface along the span direction of the blade.
7. The propeller of claim 6 wherein the blade forms a return bend proximate the tip, the leading edge extending obliquely from the return bend along the span of the blade toward the side on which the pressure surface is located, the sweep extending obliquely from the return bend from the leading edge to the trailing edge, the return bend being 87.5% of the radius of the propeller from the center of the hub.
8. The propeller as recited in claim 6, wherein said trailing edge is convexly formed with a curved trailing edge camber proximate said root; and/or
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.
9. A power assembly comprising a drive member and a propeller, the propeller comprising: a hub and blades attached to said hub, characterized in that:
the angle of attack of the blades is 17.57 ° ± 2.5 ° at a distance of 41.7% of the radius of the propeller from the center of the hub;
the angle of attack of the blades is 16.65 ° ± 2.5 ° at a distance from the centre of the hub of 50% of the radius of the propeller;
at 58.3% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 15.62 ° ± 2.5 °;
at 66.7% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 14.48 ° ± 2.5 °;
at a distance of 75% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 13.21 ° ± 2.5 °;
characterized in that the propeller is connected with the driving member through the hub.
10. The power assembly of claim 9, wherein:
the angle of attack of the blades is 19.02 ° ± 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 18.40 ° ± 2.5 °; and/or
The angle of attack of the blades is 11.68 ° ± 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 9.56 ° ± 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 5.96 ° ± 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 19.02 °; and/or
At 40mm from the centre of the hub, the angle of attack of the blade is 18.40 °; and/or
At 50mm from the centre of the hub, the angle of attack of the blade is 17.57 °; and/or
At 60mm from the centre of the hub, the angle of attack of the blade is 16.65 °; and/or
At 70mm from the centre of the hub, the angle of attack of the blade is 15.62 °; and/or
At 80mm from the centre of the hub, the angle of attack of the blade is 14.48 °; and/or
At 90mm from the center of the hub, the angle of attack of the blade is 13.21 °; and/or
At 100mm from the centre of the hub, the angle of attack of the blade is 11.68 °; and/or
At 110mm from the centre of the hub, the angle of attack of the blade is 9.56 °; and/or
The angle of attack of the blade is 5.96 ° at 120mm from the centre of the hub.
11. The power assembly of claim 9, wherein:
the chord length of the blade is 29.79mm ± 5mm at 41.7% of the radius of the propeller from the centre of the hub; and/or
The chord length of the blade is 28.53mm + -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 27.26mm ± 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 25.99mm ± 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 + -5 mm at a distance of 75% of the radius of the propeller from the center of the hub; and/or
The chord length of the blade at 50mm from the centre of the hub is 29.79 mm; and/or
At 60mm from the centre of the hub, the chord length of the blade is 28.53 mm; and/or
At 70mm from the centre of the hub, the chord length of the blade is 27.26 mm; and/or
The chord length of the blade is 25.99mm at 80mm from the centre of the hub; and/or
The chord length of the blade is 24.71mm at 90mm from the centre of the hub.
12. The power assembly of claim 11, wherein:
the chord length of the blade is 32.12mm + -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 21.33mm ± 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 14.83mm + -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 3.83mm + -2 mm at a distance of 100% of the radius of the propeller from the center of the hub; and/or
At 30mm from the centre of the hub, the chord length of the blade is 32.12 mm; and/or
The chord length of the blade is 31.05mm at 40mm from the centre of the hub; and/or
At 100mm from the centre of the hub, the chord length of the blade is 21.33 mm; and/or
At 110mm from the centre of the hub, the chord length of the blade is 14.83 mm; and/or
At 120mm from the centre of the hub, the chord length of the blade is 3.83 mm.
13. A power assembly according to claim 9, wherein the propeller has a diameter of 240mm ± 24 mm; and/or
The pitch of the blade is 5.467 + -0.5 inches.
14. A power assembly according to any one of claims 9 to 13, wherein:
the blade comprises a blade root, a blade tip, a pressure surface and a suction surface, wherein the blade tip is deviated from the blade root, the pressure surface and the suction surface are opposite, the front edge is connected with one side edge of the pressure surface and the suction surface, the rear edge is connected with the other side edge of the pressure surface and the suction surface, and the sweepback part is formed on the blade tip and extends from the front edge to the rear edge in an inclined mode;
the blade tip extends obliquely towards the side of the pressure surface along the span direction of the blade.
15. A power assembly according to claim 14, wherein the blade forms a return bend near the tip, the leading edge extending obliquely from the return bend in the span-wise direction of the blade towards the side on which the pressure face is located, the sweep extending obliquely from the return bend from the leading edge to the trailing edge, the return bend being 87.5% of the radius of the propeller from the centre of the hub.
16. A power assembly according to claim 14, wherein the trailing edge is convexly formed with a curved trailing edge camber proximate the root; and/or
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.
17. A power assembly according to any of claims 9 to 16, wherein the drive member is an electric motor having KV values of 790 to 845 revs/(min-volt).
18. An aircraft, comprising a fuselage and a power assembly, the power assembly being connected to the fuselage; the power assembly includes a drive member and a propeller, the propeller including: a hub and blades attached to said hub, characterized in that:
the angle of attack of the blades is 17.57 ° ± 2.5 ° at a distance of 41.7% of the radius of the propeller from the center of the hub;
the angle of attack of the blades is 16.65 ° ± 2.5 ° at a distance from the centre of the hub of 50% of the radius of the propeller;
at 58.3% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 15.62 ° ± 2.5 °;
at 66.7% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 14.48 ° ± 2.5 °;
at a distance of 75% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 13.21 ° ± 2.5 °;
characterized in that the propeller is connected with the driving member through the hub.
19. The aircraft of claim 18, wherein:
the angle of attack of the blades is 19.02 ° ± 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 18.40 ° ± 2.5 °; and/or
The angle of attack of the blades is 11.68 ° ± 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 9.56 ° ± 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 5.96 ° ± 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 19.02 °; and/or
At 40mm from the centre of the hub, the angle of attack of the blade is 18.40 °; and/or
At 50mm from the centre of the hub, the angle of attack of the blade is 17.57 °; and/or
At 60mm from the centre of the hub, the angle of attack of the blade is 16.65 °; and/or
At 70mm from the centre of the hub, the angle of attack of the blade is 15.62 °; and/or
At 80mm from the centre of the hub, the angle of attack of the blade is 14.48 °; and/or
At 90mm from the center of the hub, the angle of attack of the blade is 13.21 °; and/or
At 100mm from the centre of the hub, the angle of attack of the blade is 11.68 °; and/or
At 110mm from the centre of the hub, the angle of attack of the blade is 9.56 °; and/or
The angle of attack of the blade is 5.96 ° at 120mm from the centre of the hub.
20. The aircraft of claim 18, wherein:
the chord length of the blade is 29.79mm ± 5mm at 41.7% of the radius of the propeller from the centre of the hub; and/or
The chord length of the blade is 28.53mm + -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 27.26mm ± 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 25.99mm ± 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 + -5 mm at a distance of 75% of the radius of the propeller from the center of the hub; and/or
The chord length of the blade at 50mm from the centre of the hub is 29.79 mm; and/or
At 60mm from the centre of the hub, the chord length of the blade is 28.53 mm; and/or
At 70mm from the centre of the hub, the chord length of the blade is 27.26 mm; and/or
The chord length of the blade is 25.99mm at 80mm from the centre of the hub; and/or
The chord length of the blade is 24.71mm at 90mm from the centre of the hub.
21. The aircraft of claim 20, wherein:
the chord length of the blade is 32.12mm + -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 21.33mm ± 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 14.83mm + -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 3.83mm + -2 mm at a distance of 100% of the radius of the propeller from the center of the hub; and/or
At 30mm from the centre of the hub, the chord length of the blade is 32.12 mm; and/or
The chord length of the blade is 31.05mm at 40mm from the centre of the hub; and/or
At 100mm from the centre of the hub, the chord length of the blade is 21.33 mm; and/or
At 110mm from the centre of the hub, the chord length of the blade is 14.83 mm; and/or
At 120mm from the centre of the hub, the chord length of the blade is 3.83 mm.
22. The aircraft of claim 18 wherein the diameter of the propeller is 240mm ± 24 mm; and/or
The pitch of the blade is 5.467 + -0.5 inches.
23. The aircraft of any one of claims 18 to 22, wherein:
the blade comprises a blade root, a blade tip, a pressure surface and a suction surface, wherein the blade tip is deviated from the blade root, the pressure surface and the suction surface are opposite, the front edge is connected with one side edge of the pressure surface and the suction surface, the rear edge is connected with the other side edge of the pressure surface and the suction surface, and the sweepback part is formed on the blade tip and extends from the front edge to the rear edge in an inclined mode;
the blade tip extends obliquely towards the side of the pressure surface along the span direction of the blade.
24. The aircraft of claim 23 wherein the blade forms a return bend proximate the tip, the leading edge extending obliquely from the return bend along a span of the blade toward a side on which the pressure surface is located, the sweep extending obliquely from the return bend from the leading edge to the trailing edge, the return bend being 87.5% of a radius of the propeller from a center of the hub.
25. The aircraft of claim 23 wherein said trailing edge is convexly formed with a curved trailing edge camber proximate said root; and/or
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.
26. The aircraft of any one of claims 18 to 25, wherein the drive member is an electric motor having a KV value of 790 to 845 revs/(min-volt).
27. The vehicle according to any one of claims 18 to 26, wherein said vehicle comprises a plurality of power modules, said plurality of power modules being rotatable 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 angle of attack of the blades is 17.57 ° ± 2.5 ° at a distance of 41.7% of the radius of the propeller from the center of the hub;
the angle of attack of the blades is 16.65 ° ± 2.5 ° at a distance from the centre of the hub of 50% of the radius of the propeller;
at 58.3% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 15.62 ° ± 2.5 °;
at 66.7% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 14.48 ° ± 2.5 °;
the angle of attack of the blades is 13.21 ° ± 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 19.02 ° ± 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 18.40 ° ± 2.5 °; and/or
The angle of attack of the blades is 11.68 ° ± 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 9.56 ° ± 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 5.96 ° ± 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 19.02 °; and/or
At 40mm from the centre of the hub, the angle of attack of the blade is 18.40 °; and/or
At 50mm from the centre of the hub, the angle of attack of the blade is 17.57 °; and/or
At 60mm from the centre of the hub, the angle of attack of the blade is 16.65 °; and/or
At 70mm from the centre of the hub, the angle of attack of the blade is 15.62 °; and/or
At 80mm from the centre of the hub, the angle of attack of the blade is 14.48 °; and/or
At 90mm from the center of the hub, the angle of attack of the blade is 13.21 °; and/or
At 100mm from the centre of the hub, the angle of attack of the blade is 11.68 °; and/or
At 110mm from the centre of the hub, the angle of attack of the blade is 9.56 °; and/or
The angle of attack of the blade is 5.96 ° at 120mm from the centre of the hub.
In certain embodiments, the chord length of the blade is 29.79mm ± 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 28.53mm + -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 27.26mm ± 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 25.99mm ± 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 + -5 mm at a distance of 75% of the radius of the propeller from the center of the hub; and/or
The chord length of the blade at 50mm from the centre of the hub is 29.79 mm; and/or
At 60mm from the centre of the hub, the chord length of the blade is 28.53 mm; and/or
At 70mm from the centre of the hub, the chord length of the blade is 27.26 mm; and/or
The chord length of the blade is 25.99mm at 80mm from the centre of the hub; and/or
The chord length of the blade is 24.71mm at 90mm from the centre of the hub.
In some embodiments, the chord length of the blade is 32.12mm ± 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 21.33mm ± 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 14.83mm + -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 3.83mm + -2 mm at a distance of 100% of the radius of the propeller from the center of the hub; and/or
At 30mm from the centre of the hub, the chord length of the blade is 32.12 mm; and/or
The chord length of the blade is 31.05mm at 40mm from the centre of the hub; and/or
At 100mm from the centre of the hub, the chord length of the blade is 21.33 mm; and/or
At 110mm from the centre of the hub, the chord length of the blade is 14.83 mm; and/or
At 120mm from the centre of the hub, the chord length of the blade is 3.83 mm.
In certain embodiments, the diameter of the propeller is 240mm ± 24 mm; and/or
The pitch of the blade is 5.467 + -0.5 inches.
In some embodiments, the blade comprises a blade root, a blade tip facing away from the blade root, opposite pressure and suction surfaces, a leading edge connected to one side of the pressure and suction surfaces, a trailing edge connected to the other side of the pressure and suction surfaces, and a sweep formed at the blade tip, the sweep extending obliquely from the leading edge to the trailing edge;
the blade tip extends obliquely towards the side of the pressure surface along the span direction of the blade.
In some embodiments, the blade forms a return bend near the tip, the leading edge extends obliquely from the return bend in the span direction 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 to the trailing edge, and the return bend is 87.5% of the radius of the propeller from the center of the hub.
In some embodiments, the trailing edge is convexly formed with a curved trailing edge camber proximate the root; and/or
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.
The power assembly of an embodiment of the invention comprises a drive member and the propeller of any of the above embodiments, the propeller being connected to the drive member via the hub.
In certain embodiments, the driving member is an electric motor having a KV value of 790 to 845 revolutions/(minute-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 attack angle of the blades is 17.57 degrees +/-2.5 degrees at the position which is 41.7% of the radius of the propeller away from the center of the propeller hub; the angle of attack of the blades is 16.65 ° ± 2.5 ° at a distance from the centre of the hub of 50% of the radius of the propeller; the angle of attack of the blades is 15.62 ° ± 2.5 ° at a distance from the centre of the hub of 58.3% of the radius of the propeller; the angle of attack of the blades is 14.48 ° ± 2.5 ° at a distance of 66.7% of the radius of the propeller from the center of the hub; the angle of attack of the blades is 13.21 ° ± 2.5 ° at a distance from the centre of the hub that is 75% of the radius of the propeller; therefore, the propeller with the gradually changed blade airfoil profile can enable the propeller to be in the best working section along each section of the span direction of the blades, reduce air resistance, improve pulling force and efficiency, increase the secondary flight distance of the aircraft so as to improve the flight performance of the aircraft, reduce noise generated by the blades during working, enable the aircraft to be quieter during hovering, and improve user experience.
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 schematic plan view of a propeller according to an embodiment of the present invention.
Figure 2 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 1.
Figure 3 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 1.
Figure 4 is a cross-sectional view of the section E-E in the propeller of the embodiment shown in figure 1 at a distance of 70mm from the centre of the hub.
Figure 5 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 1.
Figure 6 is a cross-sectional view of the G-G section in the propeller of the embodiment shown in figure 1 at 90mm from the center of the hub.
FIG. 7 is a schematic frequency response curve of the propeller of the present invention and the existing propeller under the same test condition of hovering condition acoustic performance.
Figure 8 is a cross-sectional view of section a-a at 30mm from the hub center in the propeller of the embodiment shown in figure 1.
Figure 9 is a cross-sectional view of the section B-B in the propeller of the embodiment shown in figure 1 at a distance of 40mm from the centre of the hub.
Figure 10 is a cross-sectional view of the H-H section at 100mm from the hub center in the propeller of the embodiment shown in figure 1.
Figure 11 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 1.
Figure 12 is a cross-sectional view of the J-J section at 120mm from the hub center in the propeller of the embodiment shown in figure 1.
Fig. 13 is a perspective view of a propeller according to an embodiment of the present invention.
Fig. 14 is a schematic plan view of a propeller according to an embodiment of the present invention.
Fig. 15 is a schematic plan view of a propeller according to an embodiment of the present invention.
Fig. 16 is a schematic plan view of the tip in the propeller of the embodiment shown in fig. 1.
Fig. 17 is a cross-sectional view of the section M-M at 15mm from the free end of the propeller of the embodiment shown in fig. 16.
Fig. 18 is a cross-sectional view of the N-N section at 12.5mm from the free end of the propeller of the embodiment shown in fig. 16.
Fig. 19 is a cross-sectional view of the O-O section at 10mm from the free end of the propeller of the embodiment shown in fig. 16.
Figure 20 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 16.
Fig. 21 is a cross-sectional view of the section Q-Q at 5mm from the free end of the propeller of the embodiment shown in fig. 16.
Figure 22 is a cross-sectional view of the R-R section at 2.5mm from the free end of the propeller of the embodiment of figure 16.
Fig. 23 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 "when or" responsive 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 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 6, an embodiment of the present invention provides a
In the present embodiment, since D3 is located at 41.7% of the radius of
With continued reference to fig. 1-6, an embodiment of the present invention provides a
D3 at a distance of 41.7% of the radius of the
In the embodiment, the angle of attack α of the blade 20 is 17.57 degrees +/-2.5 degrees from the center of the hub 10 at D3 at 41.7% of the radius of the propeller 100, the angle of attack 5394 of the blade 20 is 16.65 degrees +/-2.5 degrees, the chord length L3 of the blade 20 is 29.79mm +/-5 mm, the angle of attack α of the blade 20 is 16.65 degrees +/-2.5 degrees from the center of the hub 10 at 50% of the radius of the propeller 100, the angle of attack α of the blade 20 is 15.62 degrees +/-2.5 degrees from the center of the hub 10 at L4 mm +/-5 mm, the chord length L5 of the blade 20 is 27.26mm +/-5 mm, the angle of attack 735 at 66.7% of the radius of the propeller 100 from the center of the hub 10 at 15.62 degrees +/-2.5 degrees from the center of the hub 10 at L5 of the center of the propeller 100 is 66.26 mm +/-5 mm, the angle of the blade 466 percent at the center of the propeller 100 from the center of the hub 10 at the center of the propeller at the center of the radius of the propeller 32.7 mm at the center of the D6, the blade 466 of the blade is 14.48 degrees at the angle of the propeller 20, the blade 80mm, the propeller 20, the blade is 84 the blade 60mm, the chord length L of the propeller 100, the propeller 20 is 27.5 mm, the propeller is capable of the performance of the improved when the performance of the propeller is improved, the propeller performance of the improved when the propeller performance of the.
Referring to table 1, a comparison between the test results of the
TABLE 1
Referring to fig. 7, the
The angle of attack α ° of the blade 20 may be 15.07 °, 17.57 °, 17.07 °, 18.07 °, 18.57 °, 19.07 °, 19.57 °, etc. at 41.7% of the radius of the propeller 100 from the center of the hub 10, or 20.07 °, or 15.57 °, or 15.7 mm, or 19.57 °, or 15.7 mm, or 16.7 mm, or 19.79 mm, 31.79mm, 32.79mm, 33.79mm, or 14.65 mm, or 14.7 mm, or 14.14, 14.15 °, 16.65 °, or 19.65 mm, or 14.7.7 mm, or 14.7.9.9.9.9 mm, 28.9.9.9 mm, 28.9.27 mm, 28mm, 28.27 mm, 28mm, 28.27 mm, or 14.27 mm, 28.14.14.14.14.14.14.14.14.14.14.14.14.7 mm, 28mm, 28.14.7 mm, 28.27 mm, 28.14.14.14.14.14.14.14.14.14 mm, 28mm, 28.14.7 mm, 28.7 mm, 28mm, 28.27 mm, 28mm, or 28mm, 28.27 mm, 28mm, 28.27 mm, 28mm, or 20mm, 28mm, 28.27 mm, 28mm, or 20mm, 28mm, 28.27.27 mm, 28mm, 28.27.27.27 mm, 28.27 mm, 28.27.27 mm, 28.27.27.27 mm, 28mm, 28.27 mm, 28.27.27 mm, 28mm, or 20.27.27.27.27 mm, 28.27.27 mm, or 20mm, 28mm, 28.27 mm, 28mm, 28.14.14.14.14.14.14.14.14.27 mm, 28mm, or 20mm, 28mm, 28.14.14.14.14.14.14.14.14.14.14.14.14.14.14.14.14.14.14.14.27 mm, 28.
The
Referring to fig. 8, in the present embodiment, optionally, at a
Referring to fig. 9, in the present embodiment, optionally, at a distance of 33.3% of the radius of the
Referring to fig. 10, in the present embodiment, optionally, D8 is located 83.3% of the radius of the
Referring to fig. 11, in this embodiment, optionally, at a distance of 91.7% of the radius of the
Referring to fig. 12, in the present embodiment, optionally, at a position D10 which is 100% of the radius of the
Referring again to fig. 1 to 6, in this embodiment, optionally, the diameter of the propeller 100 is 240mm ± 24mm, D3 at 50mm from the center of the hub 10, the angle of attack α of the blade 20 is 17.57 °, the chord length L3 of the blade 20 is 29.79mm, D4 at 60mm from the center of the hub 10, the angle of attack α of the blade 20 is 16.65 °, the chord length L4 of the blade 20 is 28.53mm, D5 at 70mm from the center of the hub 10, the angle of attack α of the blade 20 is 15.62 °, the chord length L5 of the blade 20 is 27.26mm, D6 at 80mm from the center of the hub 10, the angle of attack α of the blade 20 is 14.48 °, the chord length L6 of the blade 20 is 25.99mm, D45 at 90mm from the center of the hub 10, the angle of attack α of the blade 20 is 13.21 °, the chord length L of the blade 20 is 25.99mm, the chord length L7 mm from the center of the hub 10, the diameter of the propeller 100mm, the propeller diameter of the propeller 20, the propeller diameter of the propeller 220mm, the propeller diameter of the propeller 220mm, the propeller diameter of the propeller, the propeller 220mm, the propeller diameter of the propeller, the propeller.
Referring again to fig. 8, in the present embodiment, optionally, the diameter of the
Referring again to fig. 9, in this embodiment, optionally, the diameter of the
Referring again to fig. 10, in the present embodiment, optionally, the diameter of the
Referring again to fig. 11, in this embodiment, optionally, the diameter of the
Referring again to fig. 12, in this embodiment, optionally, the diameter of the
Referring to fig. 13-15, in the present embodiment, optionally, the
In this 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, 13 and table 2, in the present embodiment, the
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 to fig. 1 and 16, in the present embodiment, the swept back
referring to fig. 17, in the present embodiment, optionally, when the distance between the
Referring to fig. 18, in the present embodiment, optionally, when the distance from the
Referring to fig. 19, in the present embodiment, optionally, when the distance from the
Referring to fig. 20, in the present embodiment, optionally, when the distance between the
Referring to fig. 21, in the present embodiment, optionally, when the distance from the
Referring to fig. 22, in the present embodiment, optionally, when the distance from the
Referring again to fig. 17 to 22, in this embodiment, optionally, the diameter of the propeller 100 is 240mm ± 24mm, the distance from the free end 222 of the blade 20 is 15mm, the angle of attack α of the blade 20 is 11.05 ° ± 2.5 °, the chord length L11 of the blade 20 is 18.38mm, the distance from the free end 222 of the blade 20 is 12.5mm, the angle of attack α of the blade 20 is 10.06 °, the chord length L12 of the blade 20 is 16.67mm, the distance from the free end 222 of the blade 20 is 10mm, the angle of attack α of the blade 20 is 9.56 °, the chord length L13 of the blade 20 is 14.83mm, the distance from the free end 222 of the blade 20 is 7.5mm, the angle of attack α of the blade 20 is 8.66 °, the chord length L4 of the blade 20 is 12.95mm, the distance from the free end 222 of the blade 20 is 5mm, the angle of attack 15 is 7.76 mm, the chord length L4 of the blade 20 is 12.95mm, the chord length L of the blade 20 is 5mm, the chord length L220 mm, the blade 20mm, the chord length of the blade 20 is 260mm, the chord length of the blade 20mm, the length of the blade 20mm, the blade 20 is equal to the length of the blade 220 mm.
In this embodiment, the pitch of the
In conclusion, the
In addition, the
In some embodiments, the
The angle of
The angle of
The angle of
The angle of attack α 10 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
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 the blade 20 of 19.02 DEG + -2.5 DEG 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 blade 20 is 18.40 DEG + -2.5 DEG, D8 at 83.3% of the radius of the rotor 100 from the center of the hub 10, the angle of attack α 08 of the blade 20 is 11.68 DEG + -2.5 DEG, D9 at 91.7% of the radius of the rotor 100 from the center of the hub 10, the angle of attack α of the blade 20 is 9.56 DEG + -2.5 DEG, D10 at 100% of the radius of the rotor 100 from the center of the hub 10, the angle α of the blade 72 mm, the angle α mm at the center of the hub 10, the angle of the blade 72 mm at the center of the hub 10, the angle of the blade 72 mm, the angle of the center of the rotor 72 mm, the blade 72 mm, the angle of the rotor 72 mm, the angle of the rotor 10, the rotor 10mm, the angle of the rotor 10mm, the angle of the rotor 72 mm, the rotor 10mm, the rotor 72 mm, the angle of the rotor 72 mm, the angle of the rotor 72 mm, the rotor 10mm, the angle of the rotor 72 mm, the rotor 10mm, the angle of the rotor 10mm, the angle of the.
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 29.79mm +/-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 blades 20 is 28.53mm ± 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 27.26mm ± 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 25.99mm ± 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, D3 at a distance of 50mm from the centre of the hub 10, the chord length L3 of the blade 20 is 29.79 mm; and, at a distance of 60mm from the centre of the hub 10, D4, the chord length L4 of the blade 20 is 28.53 mm; and, at a distance of 70mm from the centre of the hub 10, D5, the chord length L5 of the blade 20 is 27.26 mm; and, at a distance of 80mm from the centre of the hub 10, D6, the chord length L6 of the blade 20 is 25.99 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
At 40mm from the centre of the
At a distance D8 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 32.12mm +/-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 21.33mm ± 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 blade 20 is 14.83mm ± 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 blades 20 is 3.83mm ± 2 mm; and, at 30mm from the centre of the hub 10D 1, the chord length L1 of the blade 20 is 32.12 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 21.33 mm; and, at a distance of 110mm from the centre of the hub 10, D9, the chord length L9 of the blade 20 is 14.83 mm; and a chord length L10 of the blade 20 of 3.83mm at 120mm from the center of the hub 10D 10.
Referring to fig. 23, an embodiment of the present invention provides a
In the power assembly 200 of the present invention, the angle of attack 3578 of the blades 20 is 17.57 ° ± 2.5 ° due to D3 at 41.7% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 3 of the blades 20 is 17.57 ° ± 2.5 ° due to D4 at 50% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 4 of the blades 20 is 16.65 ° ± 2.5 ° due to D5 at 58.3% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 5 of the blades 20 is 15.62 ° ± 2.5 ° due to D6 at 66.7% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 6 of the blades 20 is 14.48 ° ± 2.5 °, the angle of the blades 20 is D7 at 75% of the radius of the propeller 100 from the center of the hub 10, the angle of the blades α 7 of the blades 20 is 13.21 ° ± 2.5 °, the airfoil blades are used, the blades are thus leading to an increase in the noise experienced by the aircraft at 1000, and at the increased aerodynamic drag of the aircraft, at the increased performance of the rotor when the rotor 100, and the increased aerodynamic performance of the propeller at the increased flight of the aircraft.
In this embodiment, the driving
Referring again to fig. 23, an
In this embodiment, the
In this embodiment, optionally, the
In this embodiment, since D3 is located 41.7% of the radius of
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.
- 上一篇:一种医用注射器针头装配设备
- 下一篇:螺旋桨、动力组件及飞行器