CN210139956U - Screw, power component and aircraft - Google Patents

Abstract

The utility model provides a screw, power component and aircraft, include: the propeller comprises a propeller hub and at least two blades which are arranged at equal intervals along the circumferential direction of the propeller hub; the blades are rotationally connected with the hub through the rotating shaft so as to fold the blades towards the rotating axis of the hub or unfold the blades towards the rotating axis far away from the hub, and a preset included angle is formed between the axis of the rotating shaft and the rotating axis; the propeller hub is in transmission connection with a driving device so as to drive the propeller hub to rotate around the rotation axis; 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.

Description

Screw, power component and aircraft

Technical Field

The utility model relates to an aircraft manufacturing technology especially relates to a screw, power component and aircraft.

Background

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

In the prior art, a propeller comprises a hub in transmission connection with an engine of an aircraft and at least two blades arranged at equal intervals along the circumferential direction of the hub, and the blades and the hub are integrally formed; when the engine works, the propeller hub and the blades are driven to rotate, so that power is provided for the aircraft.

However, the blades extend in a direction perpendicular to the axis of the propeller, and after the aircraft lands on the ground, the blades are easily scratched by external objects and easily damaged.

SUMMERY OF THE UTILITY MODEL

An embodiment of the utility model provides a screw, power component and aircraft to solve the paddle and extend along the direction of perpendicular to screw axis, it is great to occupy the space, and after the aircraft descends to subaerial, the paddle is cut with external object easily and is rubbed, damages the paddle easily.

An embodiment of the utility model provides a propeller, include: 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 utility model provides a propeller, 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.

The propeller as described above, preferably, the rotation state of the blades with respect to the hub includes a folded state after being folded toward the rotation axis and an unfolded state before being folded; when the paddles are in the unfolded state, the plane in which each of the paddles lies is perpendicular to the horizontal plane.

The propeller as described above, preferably, the preset included angle is 90 °.

The propeller as described above, preferably, the propeller further includes an elastic member connected to the hub and the blades for driving the blades to fold toward the rotation axis.

The propeller as described above, preferably, the elastic member includes an annular spring, a notch is formed in a side wall of the annular spring, the annular spring is sleeved outside the rotating shaft, one end of the notch is connected to the propeller hub, and the other end of the notch is connected to the propeller blade.

The propeller is characterized in that the mounting end of the blade facing the propeller hub is provided with an annular groove, the center line of the annular groove is collinear with the axis of the rotating shaft, a convex part matched with the notch is arranged in the annular groove, and the annular reed 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.

The propeller as described above, preferably, when the blade is folded to the folded state toward the rotation axis, both ends of the notch are in contact with the projection.

The propeller as described above, preferably, when the hub rotates, the blades rotate in a direction away from the rotation axis by a centrifugal force.

The propeller as described above, preferably, 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.

In the propeller as described above, preferably, a mounting opening penetrating to the annular groove is provided on an outer surface of the mounting end, and the mounting opening faces the protruding portion.

The propeller as described above, preferably, the elastic member includes 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.

The propeller as described above, preferably, the elastic member includes an elastic sheet, the elastic sheet is disposed on the hub, and the elastic sheet has a curved portion, and the curved portion abuts against the blade.

The propeller as described above, preferably, the elastic sheet is disposed on a side of the hub facing away from the fuselage.

The embodiment of the utility model also provides a power component, which comprises a motor and the propeller; the motor is in transmission connection with the propeller.

An embodiment of the utility model provides an aircraft is still provided, include: a fuselage and a power assembly as described above.

The utility model provides a propeller, a power assembly and an aircraft, wherein, a blade is rotationally connected with a propeller hub through a 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

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.

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

fig. 2 is a first schematic structural diagram of a propeller blade in an unfolded 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 illustrating an installation between a ring-shaped reed and a hub in a propeller according to an 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 ii of a propeller blade according to an embodiment of the present invention in a folded state;

fig. 7 is a schematic structural diagram ii of a propeller blade in an extended 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 third schematic structural diagram of the propeller blade in the unfolded state according to the 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 embodiments of the present invention will be clearly and completely described below with reference to the accompanying 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. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to 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.

Example 1

Fig. 1 is a first schematic structural diagram of a propeller blade according to an embodiment of the present invention in a folded state; fig. 2 is a schematic structural diagram of a propeller blade in a deployed state according to an embodiment of the present invention.

Please refer to fig. 1 and fig. 2. The present embodiment provides a propeller, which can be used for an unmanned aerial vehicle, including: a hub 20 rotatable about an axis of rotation; at least two blades 10 rotatably connected to hub 20, and the rotation state of blades 10 with respect to hub 20 includes an unfolded state and a folded state; wherein, in the unfolded state, the length direction of the blade 10 forms a first included angle compared with the rotation axis; in the folded state, the length direction of the blade 10 forms a second included angle compared to the rotation axis, and the second included angle is not equal to the first included angle.

Specifically, the hub 20 is used to connect with a driving device of the unmanned aerial vehicle, so that the hub 20 is driven to rotate by the driving device. The unfolding state is the state when the paddle provides power for unmanned vehicles, and the folding state is the state when unmanned vehicles will land on the ground and need not to provide power for unmanned vehicles.

With continued reference to fig. 2, in the deployed state, the length direction of the blade 10 forms a first included angle compared to the rotation axis, and the first included angle may be 90 °, although the first included angle may also be 85 °, and the like. In the folded state, the length direction of the blade 10 forms a second included angle compared to the rotation axis, and the second included angle may be 0 ° or 5 °. When the length direction of the blade 10 forms a first included angle with the rotation axis, the blade 10 is in an unfolded state, the blade 10 can be driven to rotate to provide power for the unmanned aerial vehicle, and when the blade 10 is rotated relative to the hub 20 to enable the length direction of the blade 10 to form a second included angle with the rotation axis, the blade 10 is in a folded state, so that the blade 10 is prevented from being scratched by external objects, and the blade 10 is prevented from being damaged.

In the propeller of the unmanned aerial vehicle provided by the present embodiment, the blades 10 are rotatably connected to the hub 20, and the rotation state of the blades 10 relative to the hub 20 includes an unfolded state and a folded state; when the unmanned aerial vehicle does not need to fly, the blades 10 can be rotated to the folded state relative to the hub 20, so that the blades 10 are prevented from being scratched on the ground or objects on the ground, and the blades 10 are prevented from being damaged.

Example 2

Referring to fig. 1 and fig. 2, the present embodiment provides a propeller, including: a hub 20 and at least two blades 10 arranged at equal intervals along the circumferential direction of the hub 20; blade 10 is rotatably connected to hub 20 by means of a rotation shaft 104 to fold blade 10 towards the rotation axis of hub 20 or to unfold blade 10 away from the rotation axis of hub 20, and the axis of rotation shaft 104 and the rotation axis have a preset angle therebetween, the preset angle being greater than 0 °.

In particular, hub 20 is used to connect the drive means of the aircraft to blades 10, hub 20 may be cylindrical or plate-shaped, and corresponding hub 20 needs to have a structure that is centrosymmetric with respect to the rotation axis in order to avoid inducing vibrations of the aircraft fuselage under the effect of centrifugal forces when hub 20 rotates. Wherein the driving means may be any means capable of driving hub 20 in rotation about the rotation axis, such as: the driving device may be an electric motor, an internal combustion engine, or the like.

Illustratively, the hubs 20 may be disk-shaped, with the center of the respective disk-shaped hub 20 being located on the axis of rotation, and the axis of rotation being disposed perpendicular to the hub 20; of course, the hub 20 may also have a rectangular plate shape, and accordingly, the intersection of the diagonals of the hub 20 is located on the rotation axis and the rotation axis is arranged perpendicular to the hub 20.

In this embodiment, the number of the blades 10 may be various, for example, the number of the blades 10 may be two, three, four, and the like. Notably, when hub 20 is turned to power the fuselage, each blade 10 is in a deployed state, i.e., each blade 10 lies substantially in the same plane perpendicular to the axis of rotation; in addition, each blade 10 is symmetrical with respect to the center of the rotation axis, so as to prevent the blades 10 from being unevenly distributed to cause vibration of the fuselage or unstable flight when the hub 20 drives the blades 10 to rotate.

In this embodiment, the blades 10 are rotatably connected to the hub 20 through the rotating shaft 104, and the preset included angle between the axis of the rotating shaft 104 and the rotation axis of the hub 20 may be various, so long as the blades 10 can be folded toward the rotation axis of the hub 20 when the aircraft does not need to fly, so as to increase the distance between the blades 10 and the ground and avoid scraping between the blades 10 and the ground or objects on the ground. Illustratively, the preset included angle may be 45 °, 60 °, and the like, but the preset included angle may be other included angles.

Specifically, the rotation state of the blade 10 with respect to the hub 20 includes a folded state after being folded toward the rotation axis and an unfolded state before being folded; when the blade 10 is in the deployed state, it is possible to provide the aircraft with a motive force perpendicular to the plane of deployment of the blade 10.

With continued reference to fig. 1, the present embodiment preferably has a predetermined included angle of 90 °. It should be noted that the axis of the shaft 104 and the axis of rotation of the hub 20 are not coplanar.

In this embodiment, one end of the hub 20 is connected to a driving device located on the aircraft body, and when the aircraft does not need to fly, the blade 10 may rotate towards the aircraft body or the blade 10 rotates towards a direction departing from the aircraft body, so that the blade 10 is folded, and the blade 10 is prevented from being scratched by an external object. Taking a fixed wing aircraft as an example, when a propeller is installed at the front end of an aircraft body, and a plane of each unfolded blade 10 is vertical to a horizontal plane, the blade 10 can be folded towards the front end of the aircraft body, so that the blade 10 extends towards the front end of the aircraft body, the distance between the blade 10 and the ground is increased, and the blade 10 is prevented from being scratched by objects on the ground; certainly also can fold paddle 10 to the rear end of fuselage, make paddle 10 stretch out to the rear end of fuselage, compare with paddle 10 stretches out to the front end of fuselage, on the basis of the distance between increase paddle 10 and the ground, can avoid paddle 10 to stretch out to the fuselage outside to avoid paddle 10 and the anterior object contact of fuselage, and reduce the shared space of aircraft.

Of course, the propeller may also be installed at the rear end of the fuselage, and the plane of each blade 10 after being unfolded is perpendicular to the horizontal plane, at this time, the blade 10 may be folded toward the rear end of the fuselage, so that the blade 10 extends toward the rear end of the fuselage; the blade 10 can also be folded towards the front end of the fuselage, and compared with the blade 10 folded towards the rear end of the fuselage, on the basis of increasing the distance between the blade 10 and the ground, the blade 10 can be prevented from extending out of the fuselage, so that the blade 10 is prevented from contacting objects at the rear part of the fuselage.

When the aircraft is a rotor craft and the rotor craft does not need to fly, the blades 10 can be folded in the direction away from the ground; it is of course also possible to fold the blade 10 towards the ground, reducing the space taken up by the aircraft in the direction of deployment of the blade 10.

With continuing reference to fig. 1 and 2, the working process of the propeller provided in this embodiment is as follows: when a driving device arranged on the fuselage of the aircraft is operated, the driving device drives the hub 20 to rotate, and further drives the blades 10 to rotate around the rotation axis of the hub 20, in the process, the blades 10 rotate in the direction away from the rotation axis of the hub 20 under the action of centrifugal force, so that each blade 10 is approximately positioned in a plane perpendicular to the rotation axis of the hub 20, namely each blade 10 is in a deployed state; thereby driving the air flow to power the fuselage. When the aircraft does not need to fly, the blades 10 can be rotated around the rotating shaft 104, so that the blades 10 are folded towards the rotating shaft, and the blades 10 are in a folded state; it should be noted that when the blade 10 is in the folded state, a certain included angle may be formed between the blade 10 and the rotation axis, and the included angle may be 5 ° or 10 °, so as to prevent the blade 10 from being scratched from the fuselage.

The propeller provided by the present embodiment is configured such that the blades 10 are rotatably connected to the hub 20 through the rotating shaft 104, and an axis of the rotating shaft 104 and a rotation axis of the hub 20 have a preset included angle therebetween; when the aircraft is not flying, the blades 10 can be rotated around the rotating shaft 104, so that the blades 10 are folded towards the rotating axis of the hub 20, and the blades 10 are prevented from being scratched against the ground or objects on the ground, so that the blades 10 are prevented from being damaged.

In this embodiment, the propeller further comprises an elastic member connected to hub 20 and blades 10 to drive blades 10 to fold towards the axis of hub 20. When the propeller stops rotating, the elastic element drives the blade 10 to rotate around the rotating shaft 104 of the blade 10 and the hub 20 under the action of the elastic force of the elastic element, so that the blade 10 is folded towards the rotating axis, and no manual operation or few manual operations are needed.

Fig. 3 is a schematic view illustrating an installation of a ring-shaped reed in a propeller according to an embodiment of the present invention; fig. 4 is a schematic view illustrating an installation between a ring-shaped reed and a hub in a propeller according to an embodiment of the present invention; fig. 5 is a partial enlarged view of a portion a in fig. 4. Please refer to fig. 1-5. Specifically, the elastic member may include an annular spring 30, a notch is formed in a side wall of the annular spring 30, the annular spring 30 is sleeved outside the rotation shaft 104 between the blade 10 and the hub 20, and when the annular spring 30 drives the blade 10 to expand, one end of the notch is connected to the hub 20, and the other end of the notch is connected to the blade 10.

Illustratively, when the driving device drives the hub 20 and the blades 10 to rotate, the blades 10 rotate in a direction away from the rotation axis under the action of centrifugal force, so that the annular spring leaves 30 are elastically deformed, and the width of the notch is increased until each blade 10 is in an unfolded state; when the driving device stops working, under the action of the elasticity of the annular spring leaf 30, the annular spring leaf 30 recovers deformation, the width of the notch is reduced, and the blade 10 is driven to fold towards the rotation axis of the hub 20.

With continued reference to fig. 3-5, specifically, the mounting end of the blade 10 facing the hub 20 is provided with an annular groove 101 having a center line collinear with the axis of the rotating shaft 104, a protrusion 103 matched with the notch is arranged in the annular groove 101, and the annular spring leaf 30 is accommodated in the annular groove 101; the propeller hub 20 is provided with an extension part 201 extending into the notch, when the annular spring leaf 30 drives the propeller blade 10 to fold, the extension part 201 abuts against one end of the notch of the annular spring leaf 30, the protruding part 103 abuts against the other end of the notch, and the width of the notch is reduced.

In an achievable manner, when the blade 10 is in the folded state, the protrusion 103 and the extension 201 may be arranged in sequence in a direction parallel to the center line of the ring spring 30 within the slot, i.e. the protrusion 103 and the extension 201 are arranged oppositely; alternatively, the width of the extension 201 is equal to the width of the protrusion 103, and both ends of the notch contact with the protrusion 103 or both ends of the extension 201 along the width. In other embodiments, the width of extension 201 may be slightly less than or slightly greater than the width of protrusion 103. When the hub 20 rotates, the blade 10 rotates around the rotating shaft 104 under the action of centrifugal force, at this time, the protrusion 103 and the extension 201 are staggered, the extension 201 gradually slides into the annular groove 101, one end of the notch is in contact with the protrusion 103, the other end of the notch is in contact with the extension 201, the width of the notch is increased, and the annular spring 30 is elastically deformed. When the rotation speed of hub 20 is reduced or stops, annular reed 30 drives extension 201 and projection 103 close to each other by its own elastic force, and the width of the notch is reduced to fold blade 10 toward the rotation axis.

In other implementations, when the blade 10 is in the folded state, the protrusion 103 and the extension 201 may also be arranged side by side; and, one end of the notch is in contact with only the extension 201, and the other end of the notch is in contact with only the projection 103. When the hub 20 rotates, the blade 10 rotates around the rotating shaft 104 under the action of centrifugal force, the protrusion 103 and the extension 201 are away from each other, the width of the notch is increased, and the annular spring plate 30 is elastically deformed; when the rotation speed of hub 20 is reduced or stops, annular reed 30 drives extension 201 and projection 103 close to each other by its own elastic force, and the width of the notch is reduced to fold blade 10 toward the rotation axis.

The annular reed 30 is accommodated in the annular groove 101, so that the contact between an external object and the annular reed 30 can be avoided; in addition, the annular groove 101 can also play a role in positioning the annular reed 30 so as to prevent the annular reed 30 from moving.

In this embodiment, hub 20 comprises a body and first and second connecting plates disposed at the edges 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 connected with the first connecting plate and the second connecting plate through a rotating shaft 104; the first connecting plate is used for closing the annular groove 101, and the extension part 201 is arranged on one side of the first connecting plate facing the annular groove 101. The mounting end is hinged to both the first and second attachment plates, which may improve the attachment strength between the blade 10 and the hub 20.

Specifically, a first hinge hole may be formed in the first connecting plate, a second hinge hole may be formed in the second connecting plate, and a center line of the first hinge hole, a center line of the second hinge hole, and an axis of the rotating shaft 104 are arranged in a collinear manner; a third hinge hole is formed in the mounting end of the blade 10 facing the hub 20, and the rotating shaft 104 penetrates through the first hinge hole, the second hinge hole and the third hinge hole to realize the hinge connection between the blade 10 and the hub 20. The annular groove 101 is arranged on the side of the mounting end facing the first connecting plate, correspondingly, the extension part 201 is arranged on the side of the first connecting plate facing the mounting end, when the mounting end is arranged between the first connecting plate and the second connecting plate, the extension part 201 extends into the annular groove 101 and is positioned in the notch of the annular spring leaf 30, and the protrusion part 103 and the extension part 201 are arranged at intervals along the direction parallel to the central line of the annular groove 101, namely, the protrusion part 103 and the extension part 201 are arranged oppositely.

With continued reference to fig. 3-5, further, the outer surface of the mounting end is provided with a mounting opening 102 extending through to the annular groove 101, the mounting opening 102 faces the protrusion 103, and the width of the mounting opening 102 is equal to or slightly greater than the width of the extension 102. During installation, the extension part 201 can be aligned to the installation opening 102, and then the installation end is pushed, so that the extension part 201 enters the annular groove 101 through the installation opening 102, and meanwhile, the extension part 201 enters the groove opening of the annular spring leaf 30, the contact between the extension part 201 and the outer surface of the installation end during installation is avoided, and the installation between the blade 10 and the hub 20 is facilitated.

It should be noted that the shape of the extension 201 is reasonably set so that the width of the extension 201 along the radial direction of the annular groove 101 is smaller than or equal to the width of the annular groove 101 along the radial direction, and the extension 201 can smoothly slide into the annular groove 101, so that the blade 10 can rotate around the rotating shaft 104.

In the present embodiment, when the blade 10 is folded toward the rotation axis to the folded state, both ends of the notch are in contact with the protrusion 103 or the extension 201. The blade 10 is prevented from moving due to the annular reed 30 swinging in the annular groove 101. Specifically, the width of the protrusion 103 or the extension 201 may be equal to the width of the notch, that is, two ends of the notch just fit with the protrusion 103 or the extension 201; or the width of the protrusion 103 or the extension 201 is slightly larger than that of the notch so that both ends of the notch are interference-fitted with the protrusion 103 or the extension 201.

Alternatively, the width of the extension 201 is equal to the width of the protrusion 103, so that when the blade 10 is in the folded state, both ends of the notch are in contact with the extension 201 and the protrusion 103, and the protrusion 103 and the extension 201 are disposed at an interval in a direction parallel to the rotation axis 104, that is, the protrusion 103 overlaps the extension 201. When the hub 20 rotates, the blade 10 rotates under the action of centrifugal force, so that the protrusion 103 and the extension 201 are staggered, in the process that the extension 201 gradually slides into the annular groove 101, the extension 201 abuts against one end of the notch, the protrusion 103 abuts against the other end of the notch, and the annular spring leaf 30 elastically deforms.

In this embodiment, when the hub 20 rotates, the blades 10 rotate away from the rotation axis under the centrifugal force, and the blades 10 can be automatically deployed under the centrifugal force.

It is noted that as the rotation speed of hub 20 increases, the centrifugal force to which blades 10 are subjected increases, and when the rotation speed of hub 20 reaches a preset rotation speed, each blade 10 rotates in a direction away from the rotation axis to a deployed state; the predetermined speed should be no greater than the speed required for aircraft takeoff so that each blade 10 can be fully deployed prior to aircraft takeoff.

Fig. 6 is a schematic structural diagram ii of a propeller blade according to an embodiment of the present invention in a folded state; fig. 7 is a schematic structural diagram of a propeller blade in a deployed state according to an embodiment of the present invention, please refer to fig. 6 and 7. In this embodiment, the elastic member further includes a spring 40; the body is provided with a rotating part 60 in transmission connection with the hub 20, one end of the spring 40 is connected with the rotating part 60, and the other end of the spring 40 is connected with the blade 10. The blade 10 is driven to rotate around the rotating shaft 104 of the blade 10 and the hub 20 by the spring 40, and the structure is simple. In addition, the rotor 60 rotates in synchronization with the hub 20, and the spring 40 connected to the rotor 60 and the blade 10 does not prevent the blade 10 from rotating together with the hub 20.

The present embodiment does not limit the rotating portion 60, as long as the rotating portion 60 can rotate synchronously with the hub 20; illustratively, the rotating portion 60 may be a driving device. With continued reference to fig. 1-7, the rotating portion 60 is provided with a main shaft 601, and correspondingly, the hub 20 is provided with a shaft hole, and the main shaft 601 is inserted into the shaft hole to realize the connection between the main shaft 601 and the hub 20. Further, the main shaft 601 and the hub 20 may be connected by a key connection to rotate the hub 20 when the main shaft 601 rotates.

With continued reference to fig. 6 and 7. The working process of the propeller provided by the embodiment is as follows: when the driving device arranged on the aircraft fuselage works, the driving device drives the hub 20 to rotate through the rotating part 60, and further drives the blade 10 to rotate around the axis of the hub 20, in the process, the blade 10 rotates in the direction away from the rotating axis of the hub 20 under the action of centrifugal force, and the spring 40 is pulled to enable the spring 40 to generate elastic deformation; when each blade 10 is rotated to the deployed condition, each blade 10 lies substantially in a plane perpendicular to the axis of rotation of hub 20, thereby driving air flow in a direction perpendicular to blades 10 to power the aircraft. When the aircraft is landing, under the action of the elastic force of the spring 40, the spring 40 contracts, causing the blade 10 to rotate about the rotation axis 104, folding the blade 10 towards the rotation axis of the hub 20, so as to reduce the space occupied by the blade 10 in its deployment direction. For a fixed wing aircraft, the propeller can be arranged at the nose or the tail, and the rotation axis of the blade 10 is parallel to the ground, so that when the blade 10 is folded, the distance between the blade 10 and the ground can be reduced, and the blade 10 is prevented from being scratched on the ground, thereby damaging the blade 10.

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 third schematic structural diagram of a propeller blade in a deployed state according to an embodiment of the present invention, please refer to fig. 8 and 9. In this embodiment, the elastic element includes an elastic sheet 50, the elastic sheet 50 is disposed between the hub 20 and the blade 10, the elastic sheet 50 has a curved portion 502, and the curved portion 502 abuts against the blade 10.

Specifically, the elastic piece 50 may include a mounting piece 501 connected to the hub 20, and a curved portion 502 disposed at a distal end of the mounting piece 501, where the curved portion 502 may be in an arc shape or an angle is formed between the curved portion 502 and the mounting piece 501, where the curved portion 502 is curved toward the blade when the blade 10 is in the initial folded state, and further, the curved portion 502 is in contact with or attached to the blade 10; the mounting piece 501 may be connected to the hub 20 by bonding, welding, or bolting, and the bent portion 502 and the mounting piece 501 are integrally formed.

With continued reference to fig. 8 and 9, the working process of the propeller provided in this embodiment is as follows: when a driving device arranged on the aircraft fuselage works, the driving device drives the hub 20 to rotate, and further drives the blades 10 to rotate around the rotation axis of the hub 20, in the process, the blades 10 rotate in the direction away from the rotation axis of the hub 20 under the action of centrifugal force, and the blades 10 abut against the bent part 502 to enable the bent part 502 to generate elastic deformation; when each blade 10 is rotated to the deployed condition, each hub 20 lies substantially in a plane perpendicular to the axis of hub 20, thereby driving air flow in a direction perpendicular to blades 10 to power the airframe. After the aircraft has landed, under the force of the resilience of the bend 502, the blade 10 rotates about the axis of rotation 104 between the blade 10 and the hub 20, thereby causing the blade 10 to fold towards the axis of rotation of the hub 20 to reduce the space occupied along the blade 10 in its direction of deployment. For a fixed wing aircraft, the propeller can be arranged at the nose or the tail, and the rotation axis of the blade 10 is parallel to the ground, so that when the blade 10 is folded, the distance between the blade 10 and the ground can be reduced, and the blade 10 is prevented from being scratched on the ground, thereby damaging the blade 10.

Further, a spring plate 50 is arranged on the side of the hub 20 facing away from the fuselage. So that when the aircraft lands, the elastic sheet 50 drives the blade 10 to fold towards the fuselage, so as to prevent the blade 10 from extending in a direction away from the fuselage, and occupying a larger space.

Further, as with the propellers shown in embodiments 1 and 2 above, the blades 10 lie substantially in the same plane perpendicular to the axis of rotation of the hub 20 when the propellers are deployed, the propeller may also include a stop formation (not shown) which may be provided on either the hub 20 or the blades 10 to prevent the blades from being deployed too far apart during deployment such that the blades do not lie in the same plane.

Example 3

With continued reference to fig. 1-9, the present embodiment provides a power assembly including a motor and a propeller; the motor is connected with the screw drive. To drive the propeller to rotate.

The structure of the propeller is substantially similar to that of the propeller in embodiment 2, and is not described herein again. The power assembly provided by the present embodiment is configured such that the blades 10 are rotatably connected to the hub 20 through the rotating shaft 104, and an axis of the rotating shaft 104 and a rotation axis of the hub 20 have a preset included angle; after the aircraft has landed on the ground, the blades 10 may be rotated about the rotation axis 104, so that the blades 10 are folded towards the rotation axis of the hub 20, so as to prevent the blades 10 from extending in the direction of deployment thereof, thereby preventing the blades 10 from being cut against the ground or objects on the ground, so as to prevent the blades 10 from being damaged.

Example 4

With continued reference to fig. 1-9, the present embodiment provides an aircraft including a power assembly as described above.

The aircraft provided by the embodiment is formed by rotatably connecting the blades 10 and the hub 20 through the rotating shaft 104, and the axis of the rotating shaft 104 and the rotation axis of the hub 20 have a preset included angle; after the aircraft has landed on the ground, the blades 10 can be rotated about the rotation axis 104, so that the blades 10 are folded towards the rotation axis of the hub 20, thereby avoiding the blades 10 from being scratched against the ground or objects on the ground, so as to prevent the blades 10 from being damaged.

In the present invention, unless explicitly stated otherwise, the terms "mounting," "connecting," "fixing," and the like are to be understood in a broad sense, and for example, may be fixedly connected, detachably connected, or integrally formed, mechanically connected, electrically connected, or communicable with each other; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected internally or in any other manner known to those skilled in the art, unless otherwise specifically limited. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.

Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention.

Claims (16)

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. 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.

3. The propeller of claim 2 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.

4. The propeller of claim 2 wherein said predetermined included angle is 90 °.

5. The propeller of claim 2 further comprising a resilient member coupled to the hub and the blades for driving the blades to collapse toward the axis of rotation.

6. The propeller as claimed in claim 5, 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 the rotating shaft, one end of the slot is connected with the hub, and the other end of the slot is connected with the blade.

7. The propeller of claim 6 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 cooperating with 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.

8. The propeller of claim 7 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.

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

10. The propeller of claim 7 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.

11. The propeller of claim 10 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.

12. The propeller of claim 5, 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.

13. The propeller of claim 5 wherein the resilient member comprises a resilient tab disposed on the hub, the tab having a bend therein that abuts the blade.

14. The propeller of claim 13 wherein the clips are disposed on a side of the hub facing away from the fuselage.

15. A power assembly comprising an electric motor and a propeller as claimed in any one of claims 2 to 14;

the motor is in transmission connection with the propeller.

16. An aircraft, characterized in that it comprises: a fuselage and a power assembly as claimed in claim 15.

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