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 陈鹏 李建芳 于 2019-04-18 设计创作，主要内容包括：提供了一种螺旋桨、动力组件及飞行器。其中螺旋桨包括：桨毂(20)以及沿桨毂(20)的周向等间隔设置的至少两个桨叶(10)；桨叶(10)通过转动轴(104)与桨毂(20)转动连接,以向桨毂(20)的旋转轴线折叠桨叶(10)或向远离桨毂(20)的旋转轴线展开桨叶(10),并且转动轴(104)的轴线与旋转轴线之间具有预设夹角；桨毂(20)用于与驱动装置传动连接,以驱动桨毂(20)绕旋转轴线转动；在飞行器降落到地面上之后,桨叶(10)绕转动轴(104)转动,使桨叶(10)向桨毂(20)的旋转轴线折叠。具有这种螺旋桨的飞行器通过折叠桨叶有效避免桨叶与地面或者地面上的物体剐蹭,以免桨叶损坏。(A propeller, a power assembly and an aircraft are provided. Wherein the screw includes: a hub (20) and at least two blades (10) arranged at equal intervals along the circumferential direction of the hub (20); the blade (10) is rotationally connected with the hub (20) through a rotating shaft (104) so as to fold the blade (10) towards the rotating axis of the hub (20) or unfold the blade (10) away from the rotating axis of the hub (20), and the axis of the rotating shaft (104) and the rotating axis form a preset included angle; the propeller hub (20) is used for being in transmission connection with a driving device so as to drive the propeller hub (20) to rotate around the rotation axis; after the aircraft lands on the ground, the blades (10) are rotated about the axis of rotation (104), causing the blades (10) to fold toward the axis of rotation of the hub (20). The aircraft with the propeller effectively prevents the blades from being scratched against the ground or objects on the ground by folding the blades so as to prevent the blades from being damaged.)

1. A propeller, comprising:

a hub rotatable about an axis of rotation;

at least two blades rotatably connected to the hub and having rotational states relative to the hub including a deployed state and a collapsed state;

wherein, in the deployed state, the length direction of the blade forms a first angle with respect to the axis of rotation; when folded state, the length direction of paddle compare in the rotation axis forms the second contained angle, the second contained angle is not equal to first contained angle.

2. The propeller of claim 1 wherein the plane in which each of said blades lies is perpendicular to the horizontal plane when said blades are in the deployed state.

3. The propeller of claim 1 further comprising a resilient member coupled to the hub and the blades for driving the blades to collapse toward the axis of rotation.

4. The propeller as claimed in claim 3, wherein the elastic member comprises an annular spring, a slot is formed on a side wall of the annular spring, the annular spring is sleeved outside a rotating shaft between the blade and the hub, one end of the slot is connected with the hub, and the other end of the slot is connected with the blade.

5. The propeller as claimed in claim 4, wherein the mounting end of the blade facing the hub is provided with an annular groove having a centerline collinear with the axis of the rotating shaft, the annular groove is provided with a projection cooperating with the notch, and the annular spring is accommodated in the annular groove; the hub is provided with an extension part extending into the notch, the extension part abuts against one end of the notch, and the protrusion part abuts against the other end of the notch so as to drive the blade to fold towards the rotating axis.

6. The propeller of claim 5 wherein both ends of the notch are in contact with the protrusion when the blade is folded toward the axis of rotation to a folded state.

7. The propeller of claim 5 wherein said blades rotate in a direction away from said axis of rotation under centrifugal force when said hub rotates.

8. The propeller of claim 5 wherein the hub includes a body and first and second connecting plates disposed at an edge of the body, the first and second connecting plates being disposed in parallel and spaced apart relation; the mounting end is arranged between the first connecting plate and the second connecting plate, and the mounting end is hinged with the first connecting plate and the second connecting plate through the rotating shaft; the first connecting plate is used for closing the annular groove, and the extension part is arranged on one side, facing the annular groove, of the first connecting plate.

9. The propeller of claim 8 wherein an outer surface of the mounting end is provided with a mounting opening extending through to the annular groove, the mounting opening facing the protrusion.

10. The propeller of claim 3, wherein the resilient member comprises a spring; the body is provided with a rotating part in transmission connection with the propeller hub, one end of the spring is connected with the rotating part, and the other end of the spring is connected with the propeller blade.

11. The propeller of claim 3 wherein the resilient member comprises a resilient tab disposed on the hub, the tab having a bend therein that abuts the blade.

12. The propeller of claim 11 wherein the resilient tab is disposed on a side of the hub facing away from the fuselage.

13. A propeller, comprising: the propeller comprises a hub and at least two blades which are arranged at equal intervals along the circumferential direction of the hub;

the blade is rotatably connected with the hub through a rotating shaft so as to fold the blade towards the rotating axis of the hub, and a preset included angle is formed between the axis of the rotating shaft and the rotating axis and is larger than 0 degree.

14. The propeller of claim 13 wherein the rotational position of the blades relative to the hub includes a folded position folded toward the axis of rotation and an unfolded position prior to folding; when the paddles are in the unfolded state, the plane in which each of the paddles lies is perpendicular to the horizontal plane.

15. The propeller of claim 13 wherein said predetermined included angle is 90 °.

16. The propeller of claim 13 further comprising a resilient member coupled to the hub and the blades for driving the blades to collapse toward the axis of rotation.

17. The propeller of claim 16, wherein the resilient member comprises an annular spring, a slot is formed in a side wall of the annular spring, the annular spring is sleeved outside the rotating shaft, one end of the slot is connected to the hub, and the other end of the slot is connected to the blade.

18. The propeller of claim 17 wherein the mounting end of the blade toward the hub is provided with an annular groove having a centerline collinear with the axis of the shaft, the annular groove being provided with a projection for engaging the notch, the annular spring being received in the annular groove; the hub is provided with an extension part extending into the notch, the extension part abuts against one end of the notch, and the protrusion part abuts against the other end of the notch so as to drive the blade to fold towards the rotating axis.

19. The propeller of claim 18 wherein both ends of the notch are in contact with the protrusion when the blade is folded toward the axis of rotation to a folded state.

20. The propeller of claim 18 wherein said blades rotate in a direction away from said axis of rotation under centrifugal force when said hub rotates.

21. The propeller of claim 18 wherein the hub includes a body and first and second connecting plates disposed at an edge of the body, the first and second connecting plates being disposed in parallel and spaced apart relation; the mounting end is arranged between the first connecting plate and the second connecting plate, and the mounting end is hinged with the first connecting plate and the second connecting plate through the rotating shaft; the first connecting plate is used for closing the annular groove, and the extension part is arranged on one side, facing the annular groove, of the first connecting plate.

22. The propeller of claim 21 wherein an outer surface of the mounting end is provided with a mounting opening extending through to the annular groove, the mounting opening facing the protrusion.

23. The propeller of claim 16, wherein the resilient member comprises a spring; the body is provided with a rotating part in transmission connection with the propeller hub, one end of the spring is connected with the rotating part, and the other end of the spring is connected with the propeller blade.

24. The propeller of claim 16 wherein the resilient member comprises a resilient tab disposed on the hub, the tab having a bend therein that abuts the blade.

25. The propeller of claim 24 wherein the clips are disposed on a side of the hub facing away from the fuselage.

26. A power assembly is characterized by comprising a motor and a propeller;

the motor is in transmission connection with the propeller;

the spiral will include: the propeller comprises a hub and at least two blades which are arranged at equal intervals along the circumferential direction of the hub;

the blade is rotatably connected with the hub through a rotating shaft so as to fold the blade towards the rotating axis of the hub, and a preset included angle is formed between the axis of the rotating shaft and the rotating axis and is larger than 0 degree.

27. A power assembly according to claim 26, wherein the rotational positions of the blades relative to the hub include a folded position, folded towards the axis of rotation, and an unfolded position, before folding; when the paddles are in the unfolded state, the plane in which each of the paddles lies is perpendicular to the horizontal plane.

28. A power assembly according to claim 26, wherein the predetermined included angle is 90 °.

29. A power assembly according to claim 26, wherein the propeller further comprises a resilient member connected to the hub and the blades for urging the blades to fold towards the axis of rotation.

30. The power assembly according to claim 29, wherein the elastic member comprises an annular spring, a side wall of the annular spring is provided with a notch, the annular spring is sleeved on the outer side of the rotating shaft, one end of the notch is connected with the hub, and the other end of the notch is connected with the blade.

31. A power assembly according to claim 30, wherein the mounting end of the blade towards the hub is provided with an annular groove having a centre line collinear with the axis of the shaft, the annular groove being provided with a projection for engaging the notch, the annular spring being received in the annular groove; the hub is provided with an extension part extending into the notch, the extension part abuts against one end of the notch, and the protrusion part abuts against the other end of the notch so as to drive the blade to fold towards the rotating axis.

32. A power assembly according to claim 31, wherein both ends of the slot are in contact with the projection when the blade is folded towards the rotational axis to a folded condition.

33. A power assembly according to claim 31, wherein the blades rotate under centrifugal force away from the axis of rotation when the hub rotates.

34. A power assembly according to claim 31, wherein the hub includes a body and first and second connecting plates disposed at an edge of the body, the first and second connecting plates being disposed in parallel and spaced apart relation; the mounting end is arranged between the first connecting plate and the second connecting plate, and the mounting end is hinged with the first connecting plate and the second connecting plate through the rotating shaft; the first connecting plate is used for closing the annular groove, and the extension part is arranged on one side, facing the annular groove, of the first connecting plate.

35. A power assembly according to claim 34, wherein the mounting end has a mounting opening provided on an outer surface thereof extending through to the annular groove, the mounting opening facing the protrusion.

36. A power assembly according to claim 29, wherein the resilient member comprises a spring; the body is provided with a rotating part in transmission connection with the propeller hub, one end of the spring is connected with the rotating part, and the other end of the spring is connected with the propeller blade.

37. A power assembly according to claim 29, wherein the resilient member comprises a resilient tab provided on the hub, the tab having a bend therein which abuts against the blade.

38. A power assembly according to claim 37, wherein the clip is provided on a side of the hub facing away from the fuselage.

39. An aircraft, characterized in that it comprises: a fuselage and a power assembly according to any one of claims 26 to 38.

Technical Field

The embodiment of the invention relates to the manufacturing technology of an aircraft, in particular to a propeller, a power assembly and an aircraft.

Background

The aircraft comprises a propeller and a driving device, wherein the propeller is in transmission connection with the driving device so as to drive the propeller to rotate when the driving device works to provide power for the aircraft.

Disclosure of Invention

The embodiment of the invention provides a propeller, a power assembly and an aircraft, aiming at solving the problems that the blades extend along the direction vertical to the axis of the propeller, the occupied space is large, and after the aircraft lands on the ground, the blades are easy to scratch with external objects and damage the blades.

An embodiment of the present invention provides a propeller, including: a hub rotatable about an axis of rotation; at least two paddles; a hub rotatably connected to the hub and including a deployed state and a collapsed state in which the blades rotate relative to the hub; wherein, in the deployed state, the length direction of the blade forms a first angle with respect to the axis of rotation; when folded state, the length direction of paddle compare in the rotation axis forms the second contained angle, the second contained angle is not equal to first contained angle.

An embodiment of the present invention provides a propeller, including: the propeller comprises a hub and at least two blades which are arranged at equal intervals along the circumferential direction of the hub; the blade is rotatably connected with the hub through a rotating shaft so as to fold the blade towards the rotating axis of the hub, and a preset included angle is formed between the axis of the rotating shaft and the rotating axis and is larger than 0 degree.

The embodiment of the invention also provides a power assembly, which comprises a motor and a propeller; the motor is in transmission connection with the propeller; the spiral will include: the propeller comprises a hub and at least two blades which are arranged at equal intervals along the circumferential direction of the hub; the blade is rotatably connected with the hub through a rotating shaft so as to fold the blade towards the rotating axis of the hub, and a preset included angle is formed between the axis of the rotating shaft and the rotating axis and is larger than 0 degree.

An embodiment of the present invention further provides an aircraft, including: a fuselage and a power assembly as described above.

According to the propeller, the power assembly and the aircraft provided by the invention, the blades are rotatably connected with the propeller hub through the rotating shaft, and a preset included angle is formed between the axis of the rotating shaft and the rotating axis of the propeller hub; after the aircraft lands on the ground, the blades rotate around the rotating shaft, so that the blades are folded towards the rotating axis of the hub, and the blades are prevented from being scratched to the ground or objects on the ground, so that the blades are prevented from being damaged.

Drawings

FIG. 1 is a first schematic structural view of a propeller blade according to an embodiment of the present invention in a folded state;

FIG. 2 is a first schematic structural view of a propeller blade in a deployed state according to an embodiment of the present invention;

fig. 3 is a schematic view illustrating an installation of a ring-shaped reed and a blade in a propeller according to an embodiment of the present invention;

fig. 4 is a schematic view of the installation between the ring reed and the hub in the propeller according to the embodiment of the present invention;

FIG. 5 is an enlarged view of a portion of FIG. 4 at A;

fig. 6 is a schematic structural diagram of a second embodiment of the present invention illustrating a folded propeller blade;

fig. 7 is a schematic structural diagram ii of a propeller blade in a deployed state according to an embodiment of the present invention;

FIG. 8 is a third schematic structural view of a propeller blade according to an embodiment of the present invention in a folded state;

fig. 9 is a schematic structural diagram three of a propeller blade in a deployed state according to an embodiment of the present invention.

Description of reference numerals:

10. a paddle;

101. an annular groove;

102. an installation port;

103. a projection;

104. a rotating shaft;

20. a hub;

201. an extension portion;

30. an annular reed;

40. a spring;

50. a spring plate;

501. mounting a sheet;

502. a bending section;

60. a rotating part;

601. a main shaft.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. The embodiments described below and the features of the embodiments can be combined with each other without conflict.

The aircraft comprises a fuselage, a driving device and a propeller, wherein the driving device and the propeller are arranged on the fuselage; the driving device may be an electric motor or an internal combustion engine, etc. For example, when the aircraft is a fixed-wing aircraft, the driving device and the propeller may both be disposed at the front end of the fuselage or both the driving device and the propeller may be disposed at the rear end of the fuselage; each blade on the propeller is approximately positioned in the same plane which is vertical to the rotation axis of the propeller; the propeller is in transmission connection with the driving device, and when the driving device works, the propeller is driven to rotate, so that air flows to the rear part of the machine body, and the machine body obtains forward thrust. Of course, the aircraft may also be a rotorcraft.