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 于 2018-09-18 设计创作，主要内容包括：一种螺旋桨(100),其中,在距离桨毂(10)的中心为螺旋桨(100)的半径的44.0％处,桨叶(20)的攻角为18.62°±2.5°；在距离桨毂(10)的中心为螺旋桨(100)的半径的52.0％处,桨叶(20)的攻角为17.58°±2.5°；在距离桨毂(10)的中心为螺旋桨(100)的半径的68.0％处,桨叶(20)的攻角为15.05°±2.5°；在距离桨毂(10)的中心为螺旋桨(100)的半径的76.0％处,桨叶(20)的攻角为13.54°±2.5°；还涉及一种动力组件及一种飞行器。采用桨叶(20)翼型渐变的螺旋桨(100)能使得螺旋桨(100)在沿着桨叶的展向的每一段都处于最佳工作段,减少了桨叶(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,同时,还减少了空气阻力,提高拉力和效率,增加飞行器(1000)的续航距离以提高飞行器(1000)的飞行性能。(A propeller (100) wherein the angle of attack of the blades (20) is 18.62 ° ± 2.5 ° at a distance from the centre of the hub (10) of 44.0% of the radius of the propeller (100); the angle of attack of the blades (20) is 17.58 ° ± 2.5 ° at a distance from the centre of the hub (10) of 52.0% of the radius of the propeller (100); the angle of attack of the blades (20) is 15.05 ° ± 2.5 ° at a distance from the centre of the hub (10) of 68.0% of the radius of the propeller (100); the angle of attack of the blades (20) is 13.54 ° ± 2.5 ° at a distance from the centre of the hub (10) of 76.0% of the radius of the propeller (100); still relate to a power component and an aircraft. The propeller (100) with the gradually changed wing profiles of the blades (20) is adopted, so that the propeller (100) is located at the optimal working section along each section of the span direction of the blades, the noise generated by the blades (20) during working is reduced, the aircraft (1000) is quieter during hovering, the user experience is improved, meanwhile, the air resistance is also reduced, the pulling force and the efficiency are improved, and the cruising distance of the aircraft (1000) is increased so as to improve the flight performance of the aircraft (1000).)

A propeller, comprising: a hub and blades attached to said hub, characterized in that:

at 44.0% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 18.62 ° ± 2.5 °;

at 52.0% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 17.58 ° ± 2.5 °;

at a distance of 68.0% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 15.05 ° ± 2.5 °;

the angle of attack of the blades is 13.54 ° ± 2.5 ° at 76.0% of the radius of the propeller from the center of the hub.

The propeller of claim 1, wherein:

at 28.0% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 20.10 ° ± 2.5 °; and/or

At 36.0% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 19.46 ° ± 2.5 °; and/or

At a distance of 84.0% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 11.47 ° ± 2.5 °; and/or

At a distance of 92.0% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 8.39 ° ± 2.5 °; and/or

The angle of attack of the blades is 5.38 ° ± 2.5 ° at a distance from the centre of the hub of 100% of the radius of the propeller; and/or

At 17.50mm from the center of the hub, the angle of attack of the blade is 20.10 °; and/or

At 22.50mm from the centre of the hub, the angle of attack of the blade is 19.46 °; and/or

At 27.50mm from the center of the hub, the angle of attack of the blade is 18.62 °; and/or

At 32.50mm from the center of the hub, the angle of attack of the blade is 17.58 °; and/or

At 37.50mm from the center of the hub, the angle of attack of the blade is 16.39 °; and/or

At 42.50mm from the center of the hub, the angle of attack of the blade is 15.05 °; and/or

At 47.50mm from the centre of the hub, the angle of attack of the blade is 13.54 °; and/or

At 52.50mm from the center of the hub, the angle of attack of the blade is 11.47 °; and/or

At 57.50mm from the centre of the hub, the angle of attack of the blade is 8.39 °; and/or

At 62.50mm from the center of the hub, the angle of attack of the blade is 5.38 °.

The propeller of claim 1, wherein:

the chord length of the blade is 16.84mm ± 5mm at a distance of 44.0% of the radius of the propeller from the center of the hub; and/or

The chord length of the blade is 16.24mm + -5 mm at a distance of 52.0% of the radius of the propeller from the center of the hub; and/or

The chord length of the blade is 15.64mm + -5 mm at a distance of 60.0% of the radius of the propeller from the center of the hub; and/or

The chord length of the blade is 15.04mm ± 5mm at a distance of 68.0% of the radius of the propeller from the center of the hub; and/or

The chord length of the blade is 14.43mm + -5 mm at 76.0% of the radius of the propeller from the center of the hub; and/or

At 27.50mm from the centre of the hub, the chord length of the blade is 16.84 mm; and/or

The chord length of the blade at 32.50mm from the center of the hub is 16.24 mm; and/or

At 37.50mm from the centre of the hub, the chord length of the blade is 15.64 mm; and/or

At 42.50mm from the centre of the hub, the chord length of the blade is 15.04 mm; and/or

The chord length of the blade was 14.43mm at 47.50mm from the center of the hub.

The propeller of claim 3, wherein:

the chord length of the blade is 18.03mm + -5 mm at a distance of 28.0% of the radius of the propeller from the center of the hub; and/or

At a distance of 36.0% of the radius of the propeller from the center of the hub, the chord length of the blade is 17.44mm ± 5 mm; and/or

The chord length of the blade is 13.83mm ± 5mm at a distance of 84.0% of the radius of the propeller from the centre of the hub; and/or

The chord length of the blade is 10.62mm + -5 mm at a distance of 92.0% of the radius of the propeller from the center of the hub; and/or

The chord length of the blade is 2.36mm + -2 mm at a distance of 100% of the radius of the propeller from the center of the hub; and/or

At 17.50mm from the centre of the hub, the chord length of the blade is 18.03 mm; and/or

At 22.50mm from the centre of the hub, the chord length of the blade is 17.44 mm; and/or

At 52.50mm from the centre of the hub, the chord length of the blade is 13.83 mm; and/or

The chord length of the blade at 57.50mm from the centre of the hub is 10.62 mm; and/or

At 62.50mm from the centre of the hub, the chord length of the blade is 2.36 mm.

The propeller of claim 1, wherein the propeller has a diameter of 125mm ± 12.5 mm; and/or

The pitch of the blade is 2.86 plus or minus 0.5 inches.

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.

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 86.4% of the radius of the propeller from the center of the hub.

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.

A power assembly comprising a drive member and a propeller, the propeller comprising: a hub and blades attached to said hub, characterized in that:

at 44.0% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 18.62 ° ± 2.5 °;

at 52.0% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 17.58 ° ± 2.5 °;

at a distance of 68.0% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 15.05 ° ± 2.5 °;

the angle of attack of the blades is 13.54 ° ± 2.5 ° at 76.0% of the radius of the propeller from the center of the hub.

The propeller is connected with the driving piece through the propeller hub.

The power assembly of claim 9, wherein:

at 28.0% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 20.10 ° ± 2.5 °; and/or

At 36.0% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 19.46 ° ± 2.5 °; and/or

At a distance of 84.0% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 11.47 ° ± 2.5 °; and/or

At a distance of 92.0% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 8.39 ° ± 2.5 °; and/or

The angle of attack of the blades is 5.38 ° ± 2.5 ° at a distance from the centre of the hub of 100% of the radius of the propeller; and/or

At 17.50mm from the center of the hub, the angle of attack of the blade is 20.10 °; and/or

At 22.50mm from the centre of the hub, the angle of attack of the blade is 19.46 °; and/or

At 27.50mm from the center of the hub, the angle of attack of the blade is 18.62 °; and/or

At 32.50mm from the center of the hub, the angle of attack of the blade is 17.58 °; and/or

At 37.50mm from the center of the hub, the angle of attack of the blade is 16.39 °; and/or

At 42.50mm from the center of the hub, the angle of attack of the blade is 15.05 °; and/or

At 47.50mm from the centre of the hub, the angle of attack of the blade is 13.54 °; and/or

At 52.50mm from the center of the hub, the angle of attack of the blade is 11.47 °; and/or

At 57.50mm from the centre of the hub, the angle of attack of the blade is 8.39 °; and/or

At 62.50mm from the center of the hub, the angle of attack of the blade is 5.38 °.

The power assembly of claim 9, wherein:

the chord length of the blade is 16.84mm ± 5mm at a distance of 44.0% of the radius of the propeller from the center of the hub; and/or

The chord length of the blade is 16.24mm + -5 mm at a distance of 52.0% of the radius of the propeller from the center of the hub; and/or

The chord length of the blade is 15.64mm + -5 mm at a distance of 60.0% of the radius of the propeller from the center of the hub; and/or

The chord length of the blade is 15.04mm ± 5mm at a distance of 68.0% of the radius of the propeller from the center of the hub; and/or

The chord length of the blade is 14.43mm + -5 mm at 76.0% of the radius of the propeller from the center of the hub; and/or

At 27.50mm from the centre of the hub, the chord length of the blade is 16.84 mm; and/or

The chord length of the blade at 32.50mm from the center of the hub is 16.24 mm; and/or

At 37.50mm from the centre of the hub, the chord length of the blade is 15.64 mm; and/or

At 42.50mm from the centre of the hub, the chord length of the blade is 15.04 mm; and/or

The chord length of the blade was 14.43mm at 47.50mm from the center of the hub.

The power assembly of claim 11, wherein:

the chord length of the blade is 18.03mm + -5 mm at a distance of 28.0% of the radius of the propeller from the center of the hub; and/or

At a distance of 36.0% of the radius of the propeller from the center of the hub, the chord length of the blade is 17.44mm ± 5 mm; and/or

The chord length of the blade is 13.83mm ± 5mm at a distance of 84.0% of the radius of the propeller from the centre of the hub; and/or

The chord length of the blade is 10.62mm + -5 mm at a distance of 92.0% of the radius of the propeller from the center of the hub; and/or

The chord length of the blade is 2.36mm + -2 mm at a distance of 100% of the radius of the propeller from the center of the hub; and/or

At 17.50mm from the centre of the hub, the chord length of the blade is 18.03 mm; and/or

At 22.50mm from the centre of the hub, the chord length of the blade is 17.44 mm; and/or

At 52.50mm from the centre of the hub, the chord length of the blade is 13.83 mm; and/or

The chord length of the blade at 57.50mm from the centre of the hub is 10.62 mm; and/or

At 62.50mm from the centre of the hub, the chord length of the blade is 2.36 mm.

A power assembly according to claim 9, wherein the propeller has a diameter of 125mm ± 12.5 mm; and/or the pitch of the blades is 2.86 plus or minus 0.5 inches.

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.

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 86.4% of the radius of the propeller from the centre of the hub.

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.

A power assembly according to any of claims 9 to 16, wherein the drive member is an electric motor having KV values of 720 ± 72 revolutions/(min-volt).

An aircraft, which is characterized by comprising a fuselage and a power assembly,

the power assembly is connected with the machine body;

the power assembly includes a drive member and a propeller, the propeller including: a hub and blades attached to said hub, characterized in that:

at 44.0% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 18.62 ° ± 2.5 °;

at 52.0% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 17.58 ° ± 2.5 °;

at a distance of 68.0% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 15.05 ° ± 2.5 °;

the angle of attack of the blades is 13.54 ° ± 2.5 ° at 76.0% of the radius of the propeller from the center of the hub.

The propeller is connected with the driving piece through the propeller hub.

The aircraft of claim 18, wherein:

at 28.0% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 20.10 ° ± 2.5 °; and/or

At 36.0% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 19.46 ° ± 2.5 °; and/or

At a distance of 84.0% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 11.47 ° ± 2.5 °; and/or

At a distance of 92.0% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 8.39 ° ± 2.5 °; and/or

The angle of attack of the blades is 5.38 ° ± 2.5 ° at a distance from the centre of the hub of 100% of the radius of the propeller; and/or

At 17.50mm from the center of the hub, the angle of attack of the blade is 20.10 °; and/or

At 22.50mm from the centre of the hub, the angle of attack of the blade is 19.46 °; and/or

At 27.50mm from the center of the hub, the angle of attack of the blade is 18.62 °; and/or

At 32.50mm from the center of the hub, the angle of attack of the blade is 17.58 °; and/or

At 37.50mm from the center of the hub, the angle of attack of the blade is 16.39 °; and/or

At 42.50mm from the center of the hub, the angle of attack of the blade is 15.05 °; and/or

At 47.50mm from the centre of the hub, the angle of attack of the blade is 13.54 °; and/or

At 52.50mm from the center of the hub, the angle of attack of the blade is 11.47 °; and/or

At 57.50mm from the centre of the hub, the angle of attack of the blade is 8.39 °; and/or

At 62.50mm from the center of the hub, the angle of attack of the blade is 5.38 °.

The aircraft of claim 18, wherein:

the chord length of the blade is 16.84mm ± 5mm at a distance of 44.0% of the radius of the propeller from the center of the hub; and/or

The chord length of the blade is 16.24mm + -5 mm at a distance of 52.0% of the radius of the propeller from the center of the hub; and/or

The chord length of the blade is 15.64mm + -5 mm at a distance of 60.0% of the radius of the propeller from the center of the hub; and/or

The chord length of the blade is 15.04mm ± 5mm at a distance of 68.0% of the radius of the propeller from the center of the hub; and/or

The chord length of the blade is 14.43mm + -5 mm at 76.0% of the radius of the propeller from the center of the hub; and/or

At 27.50mm from the centre of the hub, the chord length of the blade is 16.84 mm; and/or

The chord length of the blade at 32.50mm from the center of the hub is 16.24 mm; and/or

At 37.50mm from the centre of the hub, the chord length of the blade is 15.64 mm; and/or

At 42.50mm from the centre of the hub, the chord length of the blade is 15.04 mm; and/or

The chord length of the blade was 14.43mm at 47.50mm from the center of the hub.

The aircraft of claim 20, wherein:

the chord length of the blade is 18.03mm + -5 mm at a distance of 28.0% of the radius of the propeller from the center of the hub; and/or

At a distance of 36.0% of the radius of the propeller from the center of the hub, the chord length of the blade is 17.44mm ± 5 mm; and/or

The chord length of the blade is 13.83mm ± 5mm at a distance of 84.0% of the radius of the propeller from the centre of the hub; and/or

The chord length of the blade is 10.62mm + -5 mm at a distance of 92.0% of the radius of the propeller from the center of the hub; and/or

The chord length of the blade is 2.36mm + -2 mm at a distance of 100% of the radius of the propeller from the center of the hub; and/or

At 17.50mm from the centre of the hub, the chord length of the blade is 18.03 mm; and/or

At 22.50mm from the centre of the hub, the chord length of the blade is 17.44 mm; and/or

At 52.50mm from the centre of the hub, the chord length of the blade is 13.83 mm; and/or

The chord length of the blade at 57.50mm from the centre of the hub is 10.62 mm; and/or

At 62.50mm from the centre of the hub, the chord length of the blade is 2.36 mm.

The aircraft of claim 18 wherein the diameter of the propeller is 125mm ± 12.5 mm; and/or the pitch of the blades is 2.86 plus or minus 0.5 inches.

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.

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 86.4% of a radius of the propeller from a center of the hub.

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.

The aircraft of any one of claims 18 to 25, wherein the drive member is an electric motor having KV values of 720 ± 72 revolutions/(min-volt).

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.