Rotor wing and aircraft

Abstract

The utility model relates to a rotor wing and an aircraft. The rotor wing comprises a propeller hub assembly, propeller blades and a locking mechanism, the propeller hub assembly is provided with a first driving device and a rotating connecting part, and the first driving device is used for driving the propeller hub assembly to rotate; the paddle is rotatably connected to the rotary connecting part, and a first locking matching part is arranged at the root of the paddle; the locking mechanism comprises a second driving device and a locking piece, the locking piece is provided with a first locking part, and the second driving device is connected with the locking piece; and when the propeller blades are folded relative to the propeller hub assembly, the second driving device is used for driving the locking piece to move, so that the first locking part and the first locking matching part are locked. According to the scheme provided by the invention, the blades can be automatically stored and fixed, and compared with the prior art, the problems of time consumption and low efficiency caused by manual operation are avoided, and vibration or rotation displacement of the blades in the transportation process can be more effectively reduced or avoided.

Description

Technical Field

[0001] The present invention relates to the field of aviation technology, and in particular to rotors and aircraft. Background Art

[0002] In the related art, when a multi-rotor aircraft is not in use, the rotor blades need to be folded and stored. The related art generally uses external propeller restraint devices such as propeller straps and propeller sleeves to limit the blades and hub assembly. This solution first requires each blade to be manually pushed to the storage position, and then the propeller restraint device is installed. When the aircraft has multiple sets of rotors, the multiple sets of rotors need to be operated one by one, resulting in a long time and low efficiency in the storage of the blades. Utility Model Content

[0003] In order to solve or partially solve the problems existing in the related art, the present application provides a rotor and an aircraft that can realize automatic storage and fixation of blades. Compared with the related art, it avoids the time-consuming and inefficient problems caused by manual operation, and can more effectively reduce or avoid the vibration or rotational displacement of the blades during transportation.

[0004] A first aspect of the present application provides a rotor, comprising:

[0005] A propeller hub assembly, wherein the propeller hub assembly is provided with a first driving device and a rotating connection portion, wherein the first driving device is used to drive the propeller hub assembly to rotate;

[0006] A blade is rotatably connected to the rotating connection portion, and a first locking fitting portion is provided at the root of the blade;

[0007] The locking mechanism includes a second driving device and a locking member, wherein the locking member is provided with a first locking portion, and the second driving device is connected to the locking member; when the blade is folded relative to the hub assembly, the second driving device is used to drive the locking member to move so that the first locking portion is locked with the first locking matching portion.

[0008] In one embodiment, the first locking fitting portion is a first plug hole provided at the root of the blade, the first locking portion is a first connector provided at the locking member, and when the blade is folded relative to the hub assembly, the second driving device is used to drive the first connector to be inserted into the first plug hole.

[0009] In one embodiment, the hub assembly includes a fixed member and a rotating member, the rotating member can rotate relative to the fixed member, and the rotating connection portion is provided on the rotating member;

[0010] The locking member is provided with a second locking portion, and the fixing member is provided with a second locking matching portion. When the second driving device drives the locking member to move in the first direction, the second locking portion is locked with the second locking matching portion.

[0011] In one embodiment, the second locking fitting portion is a second plug hole provided on the fixing member, the second locking portion is a second plug connector provided on the locking member, and when the blade is folded relative to the hub assembly, the second driving device is used to drive the second plug connector to be inserted into the second plug hole.

[0012] In one embodiment, the first driving device is a motor, the motor includes a stator shaft and a rotor, the rotor is connected to a rotating part of the hub assembly, and the fixed part is the stator shaft.

[0013] In one embodiment, the second driving device is a linear push rod, which is arranged inside the hub assembly and along the central axis of the hub assembly; the linear push rod includes a main body and a telescopic rod, the main body is fixed relative to the fixing part of the hub assembly, and the telescopic rod is connected to the locking part.

[0014] In one embodiment, the locking member can rotate with the propeller hub assembly, and the locking member is limited in position with the propeller hub assembly in the rotation direction of the propeller hub assembly, and the telescopic rod is rotatably connected to the locking member.

[0015] In one embodiment, the rotating connection portion is provided with a rotating shaft, and the root of the blade is rotatably connected to the rotating connection portion via the rotating shaft. An elastic member is sleeved on the rotating shaft, one end of the elastic member abuts against the root of the blade, and the other end of the elastic member abuts against the rotating connection portion; when the rotor stops rotating, the elastic member is used to drive the blade to fold relative to the hub assembly.

[0016] In one embodiment, there are multiple rotating connecting parts and blades, and the multiple rotating connecting parts are used to be rotatably connected to corresponding blades respectively. The locking member is provided with multiple first locking parts. When the locking member moves, the multiple first locking parts are synchronously locked with the first locking matching parts of the multiple blades.

[0017] A second aspect of the present application provides an aircraft, characterized in that it includes:

[0018] the fuselage; and

[0019] The rotor as described in the first aspect above, wherein the rotor is mounted on the fuselage.

[0020] The technical solution provided by this application may have the following beneficial effects:

[0021] The rotor provided by the present application can lock the first locking portion with the first locking mating portion when the locking mechanism controls the locking member to approach the hub assembly through the driving control of the second driving device, thereby achieving the locking of the hub assembly and the blades of the rotor when the blades are in a folded state, and realizing automatic storage and fixation of the blades. Compared with the related art, it avoids the time-consuming and inefficient problems caused by manual operation, and can more effectively reduce or avoid the vibration or rotational displacement of the blades during transportation.

[0022] It should be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The above and other objects, features and advantages of the present application will become more apparent through a more detailed description of exemplary embodiments of the present application in conjunction with the accompanying drawings, wherein the same reference numerals generally represent the same components in the exemplary embodiments of the present application.

[0024] Figure 1 is a schematic diagram of the cross-sectional structure of a rotor shown in an embodiment of the present application;

[0025] Figure 2 It is a top view of the rotor shown in the embodiment of the present application.

[0026] Figure numerals: 100, hub assembly; 110, rotating connection part; 111, rotating shaft; 120, first driving device; 121, stator shaft; 1211, second locking fitting part; 122, rotor; 130, rotating member; 140, fixing member; 200, blade; 210, root; 211, first locking fitting part; 220, body; 300, locking mechanism; 310, second driving device; 311, telescopic rod; 320, locking member; 321, first locking part; 322, second locking part; 323, bearing. DETAILED DESCRIPTION

[0027] The preferred embodiments of the present application will be described in more detail below with reference to the accompanying drawings. Although the preferred embodiments of the present application are shown in the accompanying drawings, it should be understood that the present application can be implemented in various forms and should not be limited by the embodiments described herein. On the contrary, these embodiments are provided to make the present application more thorough and complete, and to fully convey the scope of the present application to those skilled in the art.

[0028] The terms used in this application are for the purpose of describing specific embodiments only and are not intended to limit this application. The singular forms of "a", "said" and "the" used in this application and the appended claims are also intended to include plural forms unless the context clearly indicates other meanings. It should also be understood that the term "and / or" used herein refers to and includes any or all possible combinations of one or more associated listed items.

[0029] It should be understood that although the terms "first", "second", "third", etc. may be used in this application to describe various information, this information should not be limited to these terms. These terms are only used to distinguish the same type of information from each other. For example, without departing from the scope of this application, the first information may also be referred to as the second information, and similarly, the second information may also be referred to as the first information. Thus, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of this application, the meaning of "multiple" is two or more, unless otherwise clearly and specifically defined.

[0030] In the description of the present application, it should be understood that the terms "length", "width", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0031] Unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0032] In the related art, when a multi-rotor aircraft is not in use, the blades of the rotors need to be folded and stored. The related art generally uses external blade restraining devices such as blade restraining belts and blade restraining sleeves to limit the blades and hub assembly. This solution first requires each blade to be manually pushed to the storage position, and then the blade restraining device is installed. When the aircraft has multiple sets of rotors, multiple sets of rotors need to be operated one by one, resulting in a long time and low efficiency in the storage of the blades. In response to the above problems, the embodiments of the present application provide a rotor and an aircraft that can realize automatic storage and fixation of the blades. Compared with the related art, it avoids the time-consuming and inefficient problems caused by manual operation, and can more effectively reduce or avoid the vibration or rotational displacement of the blades during transportation.

[0033] The technical solution of the embodiments of the present application is described in detail below with reference to the accompanying drawings.

[0034] Figure 1 is a schematic diagram of the cross-sectional structure of a rotor shown in an embodiment of the present application; Figure 2 It is a top view of the rotor shown in the embodiment of the present application.

[0035] See also Figure 1 and Figure 2 The rotor provided in the present application includes a blade 200, a hub assembly 100 and a locking mechanism 300. The hub assembly 100 is provided with a first driving device 120 and a rotating connection portion 110. The first driving device 120 is used to drive the hub assembly 100 to rotate; the blade 200 is rotatably connected to the rotating connection portion 110, and the root 210 of the blade 200 is provided with a first locking matching portion 211; the locking mechanism 300 includes a second driving device 310 and a locking member 320, the locking member 320 is provided with a first locking portion 321, and the second driving device 310 is connected to the locking member 320; when the blade 200 is folded relative to the hub assembly 100, the second driving device 310 is used to drive the locking member 320 to move so that the first locking portion 321 is locked with the first locking matching portion 211.

[0036] The rotor provided in the present application can lock the first locking portion 321 with the first locking matching portion 211 when the locking mechanism 300 controls the locking member 320 to approach the hub assembly 100 through the drive control of the second driving device 310, thereby achieving that when the blade 200 is in a folded state, the hub assembly 100 and the blade 200 of the rotor are limited in position, and the blade 200 can be automatically stored and fixed. Compared with the related art, the present application avoids the time-consuming and inefficient problems caused by manual operation, and can more effectively reduce or avoid the vibration or rotational displacement of the blade 200 during transportation.

[0037] The hub assembly 100 of this embodiment includes a fixed part 140 and a rotating part 130. The rotating part 130 can rotate relative to the fixed part 140. The rotating connection part 110 is arranged on the rotating part 130. The first driving device 120 is a motor. The motor includes a stator shaft 121 and a rotor 122. The rotor 122 is connected to the rotating part of the hub assembly 100. The fixed part 140 is the stator shaft 121 of the motor. When the rotor 122 rotates, it can drive the rotating part 130 to rotate together, thereby causing the blade 200 to rotate accordingly. The blade 200 includes a blade 200 body 220 and a root 210. The first locking fitting portion 211 is provided at the root 210. The root 210 is connected to the rotating connection portion 110. When the blade 200 needs to be unfolded, the locking mechanism 300 controls the locking member 320 to be away from the hub assembly 100 through the driving of the second driving device 310, so that the first locking portion 321 can be unlocked from the first locking fitting portion 211. At this time, the blade 200 body 220 can be unfolded relative to the hub assembly 100.

[0038] The second driving device 310 is a linear push rod, which is arranged inside the hub assembly 100 and is arranged along the central axis of the hub assembly 100; the linear push rod includes a main body and a telescopic rod 311, the main body is fixed relative to the fixing member 140 of the hub assembly 100, and the telescopic rod 311 is connected to the locking member 320. In some embodiments, the hub assembly 100 is provided with a base connected to the stator shaft 121, one end of the main body of the linear push rod away from the locking member 320 is fixed to the base, and the telescopic rod 311 is rotatably connected to the locking member 320, for example, by a bearing 323, so that the locking member 320 can move in the first direction and can also rotate with the rotating member 130 of the hub assembly 100.

[0039] In this embodiment, the locking member 320 is limited in position with the hub assembly 100 in the rotation direction of the hub assembly 100, that is, the locking member 320 does not generate displacement with the rotating member 130 in the rotation direction, so that the first locking portion 321 and the first locking matching portion 211 are always in a aligned state. When the locking member 320 moves close to the hub assembly 100, the first locking portion 321 and the first locking matching portion 211 can be locked exactly.

[0040] See also Figure 1 and Figure 2In some embodiments, the rotating connection part 110 is provided with a rotating shaft 111, and the root 210 of the blade 200 is rotatably connected to the rotating connection part 110 through the rotating shaft 111. An elastic member (not shown) is sleeved on the rotating shaft 111, and the elastic member is used to drive the blade 200 to fold relative to the hub assembly 100. The elastic member can be a torsion spring, one end of which abuts against the root 210 of the blade 200, and the other end of which abuts against the rotating connection part 110; the torsion spring can generate a rotation torque centered on the rotating shaft 111, and the torque direction is the direction of folding and retracting the blade 200. When the rotor stops rotating, the blade 200 is not affected by the centrifugal force. At this time, the torque applied by the torsion spring to the root 210 of the blade 200 causes the blade 200 to rotate around the rotating shaft 111, thereby causing the blade 200 to automatically fold and retract to a position locked with the locking member 320.

[0041] In some embodiments, the locking member 320 is provided with a second locking portion 322, and the fixing member 140 is provided with a second locking matching portion 1211. When the second driving device 310 drives the locking member 320 to move in the first direction, the second locking portion 322 is locked with the second locking matching portion 1211. With such a configuration, when the blade 200 is folded, the entirety formed by the blade 200 and the rotating member 130 of the hub assembly 100 will not rotate relative to the fixing member 140 of the hub assembly 100, so that the rotor as a whole is fixed relative to the fuselage of the aircraft.

[0042] See also Figure 1 In some embodiments, the first locking fitting portion 211 is a first plug hole provided at the root 210 of the blade 200, the first locking portion 321 is a first plug connector provided at the locking member 320, and when the blade 200 is folded relative to the hub assembly 100, the second driving device 310 is used to drive the first plug connector to be inserted into the first plug hole. In some embodiments, the second locking fitting portion 1211 is a second plug hole provided at the fixing member 140, the second locking portion 322 is a second plug connector provided at the locking member 320, and when the blade 200 is folded relative to the hub assembly 100, the second driving device 310 is used to drive the second plug connector to be inserted into the second plug hole. The length direction of the first plug connector and the second plug connector can be along the first direction, and the opening direction of the first plug hole and the second plug hole is the same as the length direction of the first plug connector and the second plug connector. The first connector and the second connector may be rod-shaped structures, such as a pin or a rod. This embodiment adopts a matching structure of the connector and the plug hole, which can simplify the structure of the locking mechanism 300 and make the locking process faster and more effective.

[0043] In this embodiment, the locking member 320 includes a cover body, which is arranged at the upper end of the hub assembly 100, and the first connector and the second connector are both arranged at the bottom of the cover body, the first connector and the second connector are parallel, the second connector is arranged close to the first driving device 120 of the hub assembly 100, and the second connector is arranged close to the rotating connection part 110, and the lengths of the first connector and the second connector can be coordinated with the position settings of the first plug hole and the second plug hole. For example, when the position of the first plug hole is lower, the length of the first connector is longer, and when the position of the second plug hole is higher, the length of the second connector is shorter.

[0044] In some embodiments, the rotor has multiple blades 200, and accordingly, the rotating connection parts 110 on the hub assembly 100 are also set to multiple. The multiple rotating connection parts 110 are used to be rotatably connected to the corresponding blades 200 respectively, and the locking member 320 is provided with multiple first locking parts 321. When the locking member 320 moves, the multiple first locking parts 321 are synchronously locked with the first locking matching parts 211 of the multiple blades 200. In this way, when the locking member 320 is driven, the multiple blades 200 can be synchronously locked or unlocked, which improves the locking speed and efficiency, and can avoid the defect of low efficiency in locking each blade 200 one by one in the related technology.

[0045] The locking and unlocking process of the rotor of this embodiment is as follows:

[0046] When the rotor rotates, the blade 200 rotates along the central axis of the hub assembly 100, and the linear push rod pushes the locking member 320 to the maximum position away from the hub assembly 100 along the first direction. At this time, the first connector and the second connector are respectively disengaged from the first plug hole and the second plug hole of the propeller, and the cover of the locking member 320 is disengaged from the limit position and rotates with the hub assembly 100. At this time, it is in the released state, that is, the blade 200 is in the unlocked state. When the speed of the blade 200 decreases to 0, the centrifugal force on the blade 200 and the hub assembly 100 gradually decreases to 0. At this time, the blade 200 stops rotating, and the blade 200 is folded by the force of the torsion spring 210 at the root of the blade 200, and is stored in the set limit position. At this time, the first connector is aligned with the first plug hole, and the second connector is aligned with the second plug hole, and the locking condition is met. Then the linear push rod receives the start signal from the control device of the aircraft, drives the locking member 320 to move towards the direction close to the hub assembly 100, so that the first connector is inserted into the first plug hole, and the second connector is inserted into the second plug hole, thereby locking the blade 200 and the hub assembly 100.

[0047] The present application also provides an aircraft, which includes: a fuselage; and a rotor as described in the above embodiment, wherein the rotor is installed on the fuselage.

[0048] The aircraft provided in the present application can realize automatic folding, storage and fixation of the blades 200 by driving the locking member 320 through the second driving device 310. Compared with the related art, it avoids the time-consuming and inefficient problems caused by manual operation, and can more effectively reduce or avoid the vibration or rotational displacement of the blades 200 during the transportation of the aircraft.

[0049] The embodiments of the present application have been described above, and the above description is exemplary, not exhaustive, and is not limited to the disclosed embodiments. Many modifications and changes will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments. The selection of terms used herein is intended to best explain the principles of the embodiments, practical applications, or improvements to the technology in the market, or to enable other persons of ordinary skill in the art to understand the embodiments disclosed herein.

Claims

1. A rotor, characterized in that: include: A propeller hub assembly, wherein the propeller hub assembly is provided with a first driving device and a rotating connection portion, wherein the first driving device is used to drive the propeller hub assembly to rotate; A blade is rotatably connected to the rotating connection portion, and a first locking fitting portion is provided at the root of the blade; The locking mechanism includes a second driving device and a locking member, wherein the locking member is provided with a first locking portion, and the second driving device is connected to the locking member; when the blade is folded relative to the hub assembly, the second driving device is used to drive the locking member to move so that the first locking portion is locked with the first locking matching portion.

2. The rotor according to claim 1, characterized in that: The first locking fitting portion is a first plug hole arranged at the root of the blade, and the first locking portion is a first connector arranged on the locking member. When the blade is folded relative to the hub assembly, the second driving device is used to drive the first connector to be inserted into the first plug hole.

3. The rotor according to claim 1, characterized in that: The hub assembly comprises a fixed member and a rotating member, the rotating member can rotate relative to the fixed member, and the rotating connection portion is arranged on the rotating member; The locking member is provided with a second locking portion, and the fixing member is provided with a second locking matching portion. When the second driving device drives the locking member to move in the first direction, the second locking portion is locked with the second locking matching portion.

4. The rotor according to claim 3, characterized in that: The second locking fitting portion is a second plug hole provided on the fixing member, the second locking portion is a second plug connector provided on the locking member, and when the blade is folded relative to the hub assembly, the second driving device is used to drive the second plug connector to be inserted into the second plug hole.

5. The rotor according to claim 4, characterized in that: The first driving device is a motor, which includes a stator shaft and a rotor. The rotor is connected to the rotating part of the hub assembly, and the fixed part is the stator shaft.

6. The rotor according to claim 1, characterized in that: The second driving device is a linear push rod, which is arranged inside the hub assembly and along the central axis of the hub assembly; the linear push rod includes a main body and a telescopic rod, the main body is fixed relative to the fixing part of the hub assembly, and the telescopic rod is connected to the locking part.

7. The rotor according to claim 6, characterized in that: The locking member can rotate with the propeller hub assembly, and the locking member is limited in position with the propeller hub assembly in the rotation direction of the propeller hub assembly, and the telescopic rod is rotatably connected to the locking member.

8. The rotor according to claim 2, characterized in that: The rotating connection part is provided with a rotating shaft, and the root of the blade is rotatably connected to the rotating connection part through the rotating shaft. An elastic member is sleeved on the rotating shaft, one end of the elastic member abuts against the root of the blade, and the other end of the elastic member abuts against the rotating connection part; when the rotor stops rotating, the elastic member is used to drive the blade to fold relative to the hub assembly.

9. The rotor according to any one of claims 1 to 8, characterized in that: There are multiple rotating connecting parts and blades, and the multiple rotating connecting parts are used to be rotatably connected to the corresponding blades respectively. The locking member is provided with multiple first locking parts. When the locking member moves, the multiple first locking parts are synchronously locked with the first locking matching parts of the multiple blades.

10. An aircraft, characterized in that: include: body; as well as The rotor according to any one of claims 1 to 9, wherein the rotor is mounted on the fuselage.

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