WO2020220202A1 - 快拆连接组件、螺旋桨、动力装置、动力组件和无人机 - Google Patents
快拆连接组件、螺旋桨、动力装置、动力组件和无人机 Download PDFInfo
- Publication number
- WO2020220202A1 WO2020220202A1 PCT/CN2019/085009 CN2019085009W WO2020220202A1 WO 2020220202 A1 WO2020220202 A1 WO 2020220202A1 CN 2019085009 W CN2019085009 W CN 2019085009W WO 2020220202 A1 WO2020220202 A1 WO 2020220202A1
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- Prior art keywords
- insert
- propeller
- hole
- connecting member
- convex portion
- Prior art date
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- 238000009434 installation Methods 0.000 claims description 49
- 238000003780 insertion Methods 0.000 claims description 16
- 230000037431 insertion Effects 0.000 claims description 16
- 230000000149 penetrating effect Effects 0.000 claims description 6
- 230000008878 coupling Effects 0.000 claims description 5
- 238000010168 coupling process Methods 0.000 claims description 5
- 238000005859 coupling reaction Methods 0.000 claims description 5
- 230000013011 mating Effects 0.000 claims description 3
- 230000004308 accommodation Effects 0.000 abstract 4
- 238000010586 diagram Methods 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 238000000926 separation method Methods 0.000 description 4
- 230000009471 action Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000002265 prevention Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000004891 communication Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
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- 230000001788 irregular Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
- B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
- B64U30/291—Detachable rotors or rotor supports
- B64U30/292—Rotors or rotor supports specially adapted for quick release
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
- B64C27/14—Direct drive between power plant and rotor hub
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
- B64U10/13—Flying platforms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/20—Transmission of mechanical power to rotors or propellers
- B64U50/23—Transmission of mechanical power to rotors or propellers with each propulsion means having an individual motor
Definitions
- This application relates to the field of mechanical technology, and in particular to a quick-release connection assembly, a propeller, a power plant, a power assembly and an unmanned aerial vehicle.
- the propeller is an important component of the UAV. Due to the portability of the UAV, other user experience and the protection of the propeller, it is necessary to design the connection device between the propeller and the power source components (such as motors, etc.) to make the propeller and the power.
- the source parts are quickly connected or separated, and the device should have a certain degree of reliability to ensure the stability of the propeller during operation, and prevent the propeller from being separated from the power source part during operation while transmitting power.
- the present application provides a quick disconnect connection assembly, propeller, power plant, power assembly and unmanned aerial vehicle.
- the quick-release connection assembly of the embodiment of the present application is used to connect a propeller and a power device.
- the quick-release connection structure includes a first connection piece, a second connection piece and an insert piece, the first connection piece and the second connection piece One of the parts is used for mechanical coupling with the propeller, and the other is used for mechanical coupling with the power unit;
- One of the first connecting piece and the second connecting piece is provided with a convex portion, and the other of the first connecting piece and the second connecting piece is provided with a receiving portion, and the receiving portion is provided with An installation through hole penetrating in one direction, the convex portion is provided with a recess, the convex portion is at least partially installed in the receiving portion along a second direction, and the recess of the convex portion corresponds to the through hole;
- the insertion part penetrates the installation through hole and the recess, and the insertion part restricts the protrusion and the receiving part from being separated from each other in the second direction, and the first direction and the second direction The directions intersect.
- the quick-release connection assembly in the embodiment of the present application transmits torque and realizes the locking function through different structures, so as to disperse the force, and effectively avoid the concentrated force that may cause wear or breakage.
- the insert is separated from the first connecting piece and the second connecting piece. Even if the insert is damaged, there is no need to replace the entire propeller or the power unit, and only the insert needs to be replaced.
- the propeller of the embodiment of the present application is used to provide flight power to the drone.
- the propeller includes a first connecting piece and a blade connected to the first connecting piece, and the first connecting piece is used to connect to the inserting piece. And the second connecting piece of the power plant is matched;
- One of the first connecting piece and the second connecting piece is provided with a convex portion, and the other of the first connecting piece and the second connecting piece is provided with a receiving portion, and the receiving portion is provided with An installation through hole penetrating in one direction, the convex portion is provided with a recess, the convex portion is at least partially installed in the receiving portion along a second direction, and the recess of the convex portion corresponds to the through hole;
- the insertion part penetrates the installation through hole and the recess, and the insertion part restricts the protrusion and the receiving part from being separated from each other in the second direction, and the first direction and the second direction The directions intersect.
- the quick-release connection assembly in the embodiment of the present application transmits torque and realizes the locking function through different structures, so as to disperse the force, and effectively avoid the concentrated force that may cause wear or breakage.
- the insert is separated from the first connecting piece and the second connecting piece. Even if the insert is damaged, there is no need to replace the entire propeller or the power unit, and only the insert needs to be replaced.
- the power device of the embodiment of the present application includes a rotor and a second connecting member that rotates with the rotor, and the second connecting member is used to cooperate with the insert and the first connecting member of the propeller;
- One of the first connecting piece and the second connecting piece is provided with a convex portion, and the other of the first connecting piece and the second connecting piece is provided with a receiving portion, and the receiving portion is provided with An installation through hole penetrating in one direction, the convex portion is provided with a recess, the convex portion is at least partially installed in the receiving portion along a second direction, and the recess of the convex portion corresponds to the through hole;
- the insertion part penetrates the installation through hole and the recess, and the insertion part restricts the protrusion and the receiving part from being separated from each other in the second direction, and the first direction and the second direction The directions intersect.
- the quick-release connection assembly in the embodiment of the present application transmits torque and realizes the locking function through different structures, so as to disperse the force, and effectively avoid the concentrated force that may cause wear or breakage.
- the insert is separated from the first connecting piece and the second connecting piece. Even if the insert is damaged, there is no need to replace the entire propeller or the power unit, and only the insert needs to be replaced.
- the power assembly of the embodiment of the present application includes a power plant, a propeller, and the quick-release connection assembly in the above embodiment, the second connector is installed in the power plant, and the first connector is connected to the propeller.
- the quick-release connection assembly in the embodiment of the present application transmits torque and realizes the locking function through different structures, so as to disperse the force, and effectively avoid the concentrated force that may cause wear or breakage.
- the insert is separated from the first connecting piece and the second connecting piece. Even if the insert is damaged, there is no need to replace the entire propeller or the power unit, and only the insert needs to be replaced.
- the unmanned aerial vehicle of the embodiment of the present application includes a fuselage and an arm, the arm is connected to the fuselage, and the power assembly in the above embodiment is installed on the arm.
- the quick-release connection assembly in the embodiment of the present application transmits torque and realizes the locking function through different structures, so as to disperse the force, and effectively avoid the concentrated force that may cause wear or breakage.
- the insert is separated from the first connecting piece and the second connecting piece. Even if the insert is damaged, there is no need to replace the entire propeller or the power unit, and only the insert needs to be replaced.
- FIG. 1 is a schematic structural diagram of a quick-release connection assembly according to an embodiment of the present application
- Figure 2 is an exploded schematic diagram of the quick-release connection assembly of the embodiment of the present application.
- FIG. 3 is a schematic cross-sectional view of the quick-release connection assembly of the embodiment of the present application.
- Fig. 5 is a schematic structural diagram of an insert of a quick-release connection assembly according to an embodiment of the present application
- FIG. 6 is another schematic diagram of the structure of the insert of the quick-release connection assembly of the embodiment of the present application.
- Fig. 7 is a schematic structural diagram of an unmanned aerial vehicle according to an embodiment of the present application.
- Quick release connecting assembly 100 first connecting piece 10, convex portion 11, recess 111, mounting portion 12, clamping arm 121, second connecting piece 20, receiving portion 21, mounting through hole 211, mounting seat 22, mounting seat through Hole 221, insert 30, first clamping portion 31, second clamping portion 32, body 33, clamping arm 34, spring clamping member 35, connecting portion 351, clamping leg 352, protruding portion 353, elastic member 40, fixing member 50.
- first and second are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of indicated technical features. Therefore, the features defined with “first” and “second” may explicitly or implicitly include one or more of the features. In the description of this application, “multiple” means two or more than two, unless otherwise specifically defined.
- connection should be interpreted broadly unless otherwise clearly specified and limited.
- it can be a fixed connection or a detachable connection.
- Connect, or connect in one piece It can be a mechanical connection or an electrical connection.
- It can be directly connected, or indirectly connected through an intermediate medium, and it can be a communication between two elements or an interaction relationship between two elements.
- the quick release connection assembly 100 of the embodiment of the present application includes a first connection member 10, a second connection member 20, and an insert 30.
- One of the first connection member 10 and the second connection member 20 is used It is mechanically coupled with the propeller 200, and the other is used to mechanically couple with the power unit 300;
- One of the first connecting piece 10 and the second connecting piece 20 is provided with a convex portion 11, and the other of the first connecting piece 10 and the second connecting piece 20 is provided with a receiving portion 21, which is opened along the first direction X
- the convex portion 11 is provided with a recess 111, the convex portion 11 is at least partially installed in the receiving portion 21 along the second direction Y, and the recess 111 of the convex portion 11 corresponds to the installation through hole 211.
- the insert 30 penetrates the installation through hole 211 and the recess 111, and the insert 30 restricts the protrusion 11 and the receiving portion 21 from being separated from each other in the second direction Y, and the first direction X and the second direction Y intersect.
- the first connecting member 10 is mechanically coupled with the propeller 200
- the second connecting member 20 is mechanically coupled with the power device 300
- the first connecting member 10 is provided with a convex portion 11
- the second connecting member 20 With a receiving part 21.
- the second connecting member 20 may be mechanically coupled with the propeller 200
- the first connecting member 10 may be mechanically coupled with the power device 300
- the second connecting member 20 is provided with a convex portion 11
- the first connecting member 20 The piece 10 is provided with a receiving portion 21, and the specific setting method is not limited here.
- the above-mentioned mechanical coupling may mean that the two are directly fixedly connected, indirectly fixedly connected through other components, or detachably connected.
- the recess 111 may be a through hole or a groove, that is, the convex portion 11 may form a through hole or a groove.
- the recess 111 is a through hole opened on the convex portion 11 along the first direction X, and the through hole corresponds to the mounting through hole 211 on the receiving portion 21, and the insert 30 sequentially passes through the mounting through hole
- the through holes 211 and the convex portion 11 restrict the convex portion 11 and the receiving portion 21 from being separated from each other in the second direction Y.
- first direction X and the second direction Y intersect (that is, not parallel), and the angle between the first direction X and the second direction Y is 60 to 120 degrees.
- first direction X is perpendicular to the second direction Y
- first direction X is a horizontal direction
- second direction Y is a vertical direction.
- the screw is usually used to directly connect the propeller and the power source component, and the screw is used to transmit and pull force, or the specific structure on the propeller (for example, L-shaped hook) and the concave on the power source component are used.
- the grooves are matched, and the matching structure of the two is used to lock the propeller at the same time, and transmit torque and pulling force.
- the matching structure of the propeller and the power source component plays a role of transmitting torque and locking at the same time, and its force is relatively concentrated, resulting in easy wear or breakage, and reliability problems when used for a long time ,
- the propeller may detach from the power source component when transmitting power, which affects the safety of the UAV.
- the quick-release connection assembly 100 of the embodiment of the present application since the insert 30 is penetrated and locked in the installation through hole 211 and the recess 111, on the one hand, when the first connecting member 10 or the second connecting member 20 rotates, Torque can be transmitted through the cooperation of the convex portion 11 and the receiving portion 21.
- the locking function is realized by the insert 30, which prevents the first connecting member 10 and the second connecting member 20 from being separated from each other, and improves the reliability of the connection. Therefore, the quick-release connection assembly 100 in the embodiment of the present application transmits torque and realizes the locking function through different structures, so as to disperse the force, and effectively avoid the concentrated force from being easily worn or broken.
- the insert 30 is separated from the first connecting member 10 and the second connecting member 20. Even if the insert 30 is damaged, there is no need to replace the entire propeller 200 or the power unit 300, only the insert 30 needs to be replaced.
- the first connecting member 10 is provided with a convex portion 11
- the second connecting member 20 is provided with a receiving portion 21
- the second connecting member 20 includes a mounting seat 22, and the receiving portion 21 is convex
- the mounting seat 22 is installed on the power device 300.
- the mounting base 22 is fixedly installed in the power device 300 through a fixing member 50, and the fixing member 50 includes fixing elements such as screws and pins.
- the power device 300 may be a motor, and the motor may be an outer rotor motor or an inner rotor motor.
- the mounting base 22 is installed on the rotor of the motor and can rotate with the following rotor. In this way, the mounting base 22 is fixedly installed on the power unit 300 and can rotate together with the power unit 300, so that the second connection member 20 and the first connection member 10 can drive the propeller 200 to rotate when the power unit 300 rotates.
- one of the first connecting member 10 and the second connecting member 20 is the rotor housing of the motor or a component that rotates with the rotor of the motor, and the other is the hub or the rotor of the propeller 200.
- the specific arrangement of the components that rotate with the hub is not limited here.
- the mounting seat 22 is provided with a mounting seat through hole 221, the mounting seat through hole 221 contains an elastic member 40, and the elastic member 40 presses the insert 30 in Install the through hole 211 and the recess 111.
- the power device 300 may be a motor, and the motor shaft 301 of the motor penetrates the mounting seat through hole 221, the elastic member 40 is sleeved on the motor shaft 301, and one end of the elastic member 40 resists the power. The other end of the device 300 abuts the insert 30, and the elastic member 40 is in a compressed state to apply elastic force to the insert 30 to compress the insert 30 in the installation through hole 211 and the recess 111.
- the elastic member 40 can press the insert 30 into the mounting through hole 211 and the recess 111, thereby preventing the insert 30 from detaching from the mounting through hole 211 and/or the recess 111, thereby improving the reliability and stability of the connection .
- the insert 30 is elongated, and both ends of the insert 30 along the length of the insert 30 are respectively provided with a first clamping portion 31 and a second clamping portion 32.
- the elastic member 40 presses the inserting member 30 toward the first connecting member 10, and the first clamping portion 31 and the second clamping portion 32 are clamped on the outer wall of the receiving portion 21.
- the insert 30 includes a main body 33 and two clamping arms 34 connected to one end of the main body 33.
- the two clamping arms 34 are spaced apart.
- the end of the main body 33 and the clamping arm 34 is provided with the aforementioned first clamping portion 31.
- the end of the arm 34 opposite to the main body 33 is provided with the second clamping portion 32 described above. In other words, there is a space between the two clamping arms 34, and one end of each clamping arm 34 is provided with a second clamping portion 32.
- the motor shaft 301 of the motor is located between the two clamping arms 34.
- the elastic member 40 presses the insert 30 toward the first connecting member 10 to clamp the first clamping portion 31 and the second clamping portion 32 to the outer wall of the receiving portion 21.
- the first card portion 31 and the second card portion 32 can prevent the insertion member 30 from moving in the first direction X after being inserted into the mounting through hole 211 and the recess 111 to cause separation.
- the insert 30 may be a spring clip 35.
- the spring clip 35 has two clamping legs 352 and a connecting portion 351 connecting the two clamping legs 352.
- the clamping legs 352 are elastic, and the width of the gap between the two clamping legs 352 can be reduced under the action of external force. And can recover when the external force is removed.
- you need to insert the spring clip 35 you can pinch the two clips 352 from the outside, then insert the spring clip 35 into the installation through hole 211 and the recess 111, and then release the clip 352 to place the spring clip 35
- the convex portion 11 and the receiving portion 21 are clamped under the action of the elastic force.
- the above-mentioned elastic member 40 may not be provided.
- an elastic member 40 may also be selected to press the spring clip 35 on the first connecting member 10. The specific arrangement is not limited here.
- the spring clamping member 35 in FIG. 5 is in a normal state where the clamping leg 352 is not pinched, and the spring clamping member 35 in FIG. 6 is in a compressed state where the clamping leg 352 is pinched.
- the mounting through hole 211 may include a threaded section through hole
- the recess 111 may include a threaded section
- the insert 30 may include a threaded portion. The threaded section is screwed on the threaded section through hole and the threaded section to connect the insert 30 is locked in the installation through hole 211 and the recess 111.
- the threaded connection of the insert 30 with the installation through hole 211 and the recess 111 can also reliably connect the first connecting member 10 and the second connecting member 20 and facilitate disassembly.
- the shape of the convex portion 11 is non-cylindrical, and the receiving portion 21 is formed with a cavity 212 for receiving the convex portion 11, and the shape of the cavity 212 matches the shape of the convex portion 11.
- the convex portion 11 is made into a non-cylindrical shape and the shape of the cavity 212 of the receiving portion 21 receiving the convex portion 11 is made to match the shape of the convex portion 11 to prevent unsafeness, so that the first connector 10 and the first connector 10 are installed
- the installation through hole 211 and the recess 111 can be aligned quickly and accurately, and the insert 30 can be inserted into the installation through hole 211 and the recess 111 accurately and quickly.
- the convex portion 11 has a regular hexagon shape. It can be understood that, in other embodiments, the convex portion 11 may also have a regular shape such as a regular octagon or other irregular shapes, which is not specifically limited here.
- the first connector 10 is provided with a convex portion 11
- the second connector 20 is provided with a receiving portion 21
- the first connector 10 includes a mounting portion connecting the convex portion 11 12.
- the mounting portion 12 is located on the side of the convex portion 11 away from the receiving portion 21, and the blade 201 of the propeller 200 is mounted on the mounting portion 12.
- the mounting part 12 includes a clamping arm 121, and the clamping arm 121 clamps one end of the blade 201.
- the number of blades 201 is two
- the number of clamping arms 121 is two
- every two clamping arms 121 clamp a blade 201.
- the clamping arm and the blade can be rotatably connected by a shaft connection, which facilitates the storage of the blade 201.
- the insert 30 is provided with a limiting portion, which is used to cooperate with the first connecting member 10 and/or the second connecting member 20 to prevent the insert 30 from passing through the installation through hole 211 and/or The recess 111 comes out.
- the limiting portion can be matched with the first connecting member 10 and/or the second connecting member 20 to prevent the insert 30 from falling out.
- the limiting portion may include a first fastener, and the second connector 20 is provided with a second fastener.
- the first The buckle member cooperates with the second buckle member to clamp the limiting portion to prevent the insertion member 30 from falling out.
- the limiting portion can also be a protrusion 353 formed on the clip 352, and the spring clip 35 is pinched and inserted into the installation through hole 211 and When the recess 111 is released and then released, the locking leg 352 can clamp the spring clip 35 tightly, and the protruding portion 353 of the locking leg 352 is locked on the outer wall of the receiving portion to prevent the spring clip 35 from falling off.
- the above-mentioned limiting part may also include the first card part 31 and the second card part 32 mentioned in the above embodiment, and the specific structure will not be repeated here.
- the elastic member 40 is used to provide an elastic force to the insert member 30, so that the insert member 30 keeps mating with the first connecting member 10 and/or the second connecting member 20 status.
- the elastic force provided by the elastic member 40 can urge the insertion member 30 to move in the second direction Y until the insertion member 30 remains mated with the first connecting member 10 and/or the second connecting member 20.
- the elastic member 40 can urge the insert 30 to move in the second direction Y so that the insert 30 can resist the first connecting member 10 or the second connecting member 20, and then It is possible to prevent the insert 30 from coming out of the installation through hole 211 and the recess 111.
- the insert 30 may also be engaged with the first connecting member 10 and/or the second connecting member 20.
- the insert 30 and the first connecting member 10 and/or the second connecting member 20 can be buckled in a snap connection to prevent the insert 30 from falling out.
- the propeller 200 of the embodiment of the present application is used to provide flight power to the drone 1000.
- the propeller 200 includes a first connecting member 10 and a blade 201 connected to the first connecting member 10, and the first connecting member 10 is used to connect to an insert. 30 and the second connecting member 20 of the power device 300 cooperate.
- One of the first connecting piece 10 and the second connecting piece 20 is provided with a convex portion 11, and the other of the first connecting piece 10 and the second connecting piece 20 is provided with a receiving portion 21, which is opened along the first direction X
- the convex portion 11 is provided with a recess 111
- the convex portion 11 is at least partially installed in the receiving portion 21 along the second direction Y
- the recess 111 of the convex portion 11 corresponds to the through hole.
- the insert 30 penetrates the installation through hole 211 and the recess 111, and the insert 30 restricts the protrusion 11 and the receiving portion 21 from being separated from each other in the second direction Y, and the first direction X and the second direction Y intersect.
- the insert 30 since the insert 30 is inserted through and locked in the installation through hole 211 and the recess 111, on the one hand, when the first connecting member 10 or the second connecting member 20 rotates, the insert 30 can pass through 30 transmits torque. On the other hand, the tensile force can also be transmitted through the insert 30 to prevent the first connecting member 10 and the second connecting member 20 from being separated from each other, thereby improving the reliability of the connection.
- the power plant 300 of the embodiment of the present application includes a rotor and a second connecting member 20 that rotates with the rotor, and the second connecting member 20 is used to cooperate with the insert 30 and the first connecting member 10 of the propeller 200;
- One of the first connecting piece 10 and the second connecting piece 20 is provided with a convex portion 11, and the other of the first connecting piece 10 and the second connecting piece 20 is provided with a receiving portion 21, which is opened along the first direction X
- the convex portion 11 is provided with a recess 111, the convex portion 11 is at least partially installed in the receiving portion 21 along the second direction Y, and the recess 111 of the convex portion 11 corresponds to the through hole;
- the insert 30 penetrates the installation through hole 211 and the recess 111, and the insert 30 restricts the protrusion 11 and the receiving portion 21 from being separated from each other in the second direction Y, and the first direction X and the second direction Y intersect.
- the insert 30 since the insert 30 is penetrated and locked in the installation through hole 211 and the recess 111, on the one hand, when the first connector 10 or the second connector 20 rotates, it can be inserted The member 30 transmits torque. On the other hand, the tensile force can also be transmitted through the insert 30 to prevent the first connecting member 10 and the second connecting member 20 from being separated from each other, thereby improving the reliability of the connection.
- the aforementioned power device 300 includes, but is not limited to, an outer rotor motor and an inner rotor motor.
- the power assembly 600 of the embodiment of the present application includes the power plant 300, the propeller 200 in any of the above embodiments, and the quick-release connection assembly 100 in any of the above embodiments.
- the second connector 20 is installed in the power plant 300, and the first connection The piece 10 is connected to the propeller 200.
- the power device 300 includes a limit shaft, and the limit shaft passes through the quick-release connection assembly 100.
- the power device 300 can be a motor.
- the limit shaft is the motor shaft 301, and the second connecting member 20 can be connected to the rotor of the motor. In this way, the rotation drives the second connecting member 20 to rotate, and the insert 30 can The first connecting member 10 is driven to rotate, thereby driving the blade 201 of the propeller 200 to rotate.
- the insert 30 since the insert 30 penetrates and is locked in the installation through hole 211 and the recess 111, on the one hand, when the first connecting member 10 or the second connecting member 20 rotates, the insert can pass through 30 transmits torque. On the other hand, the tensile force can also be transmitted through the insert 30 to prevent the first connecting member 10 and the second connecting member 20 from being separated from each other, thereby improving the reliability of the connection.
- the drone 1000 includes a fuselage 400 and an arm 500, the arm 500 is connected to the fuselage 400, and the power assembly described in the above embodiment is installed on the arm 500.
- the drone 1000 is a multi-rotor aircraft.
- the drone 1000 includes a plurality of arms 500, and each arm 500 is equipped with a power unit including a propeller 200.
- the propeller 200 can be driven to rotate, thereby providing the drone 1000 Provide flight power.
- the insert 30 since the insert 30 is inserted through and locked in the installation through hole 211 and the recess 111, on the one hand, when the first connecting member 10 or the second connecting member 20 rotates, it can pass through The insert 30 transmits torque. On the other hand, the tensile force can also be transmitted through the insert 30 to prevent the first connecting member 10 and the second connecting member 20 from being separated from each other, thereby improving the reliability of the connection.
- the number of the power components 600 is multiple, including a first power component and a second power component (see FIG. 7).
- the power device 300 of the first power component is used to drive a propeller. 200 rotates in a clockwise direction
- the power device 300 of the second power assembly is used to drive the propeller 200 to rotate in a counterclockwise direction.
- the embodiments of the present application The mutual matching relationship between the convex portion 11 and the receiving portion 21 is used, that is, the convex portion is adapted to the shape or/and size of the receiving portion, so as to realize the function of "folly prevention".
- the shape of the convex portion 11 of the first power assembly is different from the shape of the convex portion 11 of the second power assembly, so that the propeller 200 of the first power assembly can only It is connected to the power unit 300 of the first power unit, but cannot be connected to the power unit 300 of the second power unit; so that the propeller 200 of the second power unit can only be connected to the power unit 300 of the second power unit, and It cannot be connected with the power unit of the first power assembly, thereby avoiding the problem of aircraft bombing caused by incorrect assembly of the propeller.
- the size of the convex portion 11 of the first power assembly is different from the size of the convex portion 11 of the second power assembly, so that the propeller 200 of the first power assembly can only It is connected to the power unit 300 of the first power unit, but cannot be connected to the power unit 300 of the second power unit; so that the propeller 200 of the second power unit can only be connected to the power unit 300 of the second power unit, and It cannot be connected with the power unit of the first power assembly, thereby avoiding the problem of aircraft bombing caused by incorrect assembly of the propeller.
- the size may be selected according to the shape of the convex portion, for example, the size may be length, width, radius, or curvature.
- the present application may also utilize the mutual cooperation relationship between the limit shaft of the power plant and the limit hole of the propeller, that is, the shape or/and size of the limit shaft and the limit hole are adapted to realize the "prevention" Stay” function.
- the shape of the limiting shaft of the first power assembly is different from the shape of the limiting shaft of the second power assembly, so that the propeller of the first power assembly can only be
- the power unit of the first power unit is connected, but cannot be connected to the power unit of the second power unit; thus, the propeller of the second power unit can only be connected to the power unit of the second power unit, but not the first power unit.
- the power devices of the components are connected, thereby avoiding the problem of aircraft bombing caused by incorrect assembly of the propeller.
- the size of the limiting shaft of the first power assembly is different from the size of the limiting shaft of the second power assembly, so that the propeller of the first power assembly can only be
- the power unit of the first power unit is connected, but cannot be connected to the power unit of the second power unit; thus, the propeller of the second power unit can only be connected to the power unit of the second power unit, but not the first power unit.
- the power devices of the components are connected, thereby avoiding the problem of aircraft bombing caused by incorrect assembly of the propeller.
- the "on” or “under” of the first feature of the second feature may include the first and second features in direct contact, or may include the first and second features Not in direct contact but through other features between them.
- “above”, “above” and “above” the second feature of the first feature include the first feature being directly above and obliquely above the second feature, or it simply means that the level of the first feature is higher than the second feature.
- the “below”, “below” and “below” the first feature of the second feature include the first feature directly below and obliquely below the second feature, or it simply means that the level of the first feature is smaller than the second feature.
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Abstract
一种快拆连接组件（100）、螺旋桨（200）、动力装置（300）、动力组件和无人机（1000）。快拆连接组件（100）包括第一连接件（10）、第二连接件（20）和插入件（30），第一连接件（10）以及第二连接件（20）中的一个用于与螺旋桨（200）机械耦合，另外一个用于与动力装置（300）机械耦合。第一连接件（10）和第二连接件（20）的其中一个设有凸部（11），第一连接件（10）和第二连接件（20）的另外一个设有收容部（21），收容部（21）开设有沿第一方向（X）贯穿的安装通孔（211），凸部（11）开设有凹陷（111），凸部（11）沿第二方向（Y）至少部分地安装于收容部（21）中，并且凸部（11）的凹陷（111）与安装通孔（211）相对应。插入件（30）穿设安装通孔（211）以及凹陷（111）中，插入件（30）限制凸部（11）和收容部（21）沿第二方向（Y）相互分离，第一方向（X）与第二方向（Y）相交。
Description
本申请涉及机械技术领域，特别涉及一种快拆连接组件、螺旋桨、动力装置、动力组件和无人机。
螺旋桨是无人机的重要部件，出于无人机的便携性和其他用户体验以及对螺旋桨的保护需求，需要设计螺旋桨与动力源部件(如电机等)之间的连接装置，使螺旋桨与动力源部件快速连接或分离，且该装置应具备一定的可靠性，保证螺旋桨工作时的稳定，在传递动力的同时能够防止螺旋桨在工作时从动力源部件上脱离。
同时，由于螺旋桨和动力源部件是两个独立的部件，无人机飞行时，螺旋桨和动力源部件之间的连接需要承担拉力和扭矩。
发明内容
有鉴于此，本申请提供一种快拆连接组件、螺旋桨、动力装置、动力组件和无人机。
本申请的实施方式的快拆连接组件用于连接螺旋桨和动力装置，所述快拆连接结构包括第一连接件、第二连接件和插入件，所述第一连接件以及所述第二连接件中的一个用于与螺旋桨机械耦合，另外一个用于与动力装置机械耦合；
所述第一连接件和所述第二连接件的其中一个设有凸部，所述第一连接件和所述第二连接件的另外一个设有收容部，所述收容部开设有沿第一方向贯穿的安装通孔，所述凸部开设有凹陷，所述凸部沿第二方向至少部分地安装于所述收容部中，并且所述凸部的凹陷与所述通孔相对应；
所述插入件穿设所述安装通孔以及所述凹陷中，所述插入件限制所述凸部和所述收容部沿所述第二方向相互分离，所述第一方向与所述第二方向相交。
上述实施方式的快拆连接组件中，由于插入件穿设并锁紧在安装通孔和凹陷中，一方面，当第一连接件或第二连接件转动时，可通过插入件传递扭矩，另一方面，也可通过插入件传递拉力，避免第一连接件和第二连接件相互分离。因此，在本申请实施方式的快拆连接组件，分别通过不同的结构传递扭矩和实现锁紧功能，从而分散受力情况，有效避免受力较为集中而导致容易磨损或折断。并且，插入件与第一连接件和第二连接件分离设置，即使插入件损坏，也无需更换整个螺旋桨或动力装置，仅需更换插入件即可。
本申请的实施方式的螺旋桨用于给无人机提供飞行动力，所述螺旋桨包括第一连接件 与以及与所述第一连接件连接的桨叶，所述第一连接件用于与插入件以及动力装置的第二连接件配合；
所述第一连接件和所述第二连接件的其中一个设有凸部，所述第一连接件和所述第二连接件的另外一个设有收容部，所述收容部开设有沿第一方向贯穿的安装通孔，所述凸部开设有凹陷，所述凸部沿第二方向至少部分地安装于所述收容部中，并且所述凸部的凹陷与所述通孔相对应；
所述插入件穿设所述安装通孔以及所述凹陷中，所述插入件限制所述凸部和所述收容部沿所述第二方向相互分离，所述第一方向与所述第二方向相交。
上述实施方式的螺旋桨中，由于插入件穿设并锁紧在安装通孔和凹陷中，一方面，当第一连接件或第二连接件转动时，可通过插入件传递扭矩，另一方面，也可通过插入件传递拉力，避免第一连接件和第二连接件相互分离。因此，在本申请实施方式的快拆连接组件，分别通过不同的结构传递扭矩和实现锁紧功能，从而分散受力情况，有效避免受力较为集中而导致容易磨损或折断。并且，插入件与第一连接件和第二连接件分离设置，即使插入件损坏，也无需更换整个螺旋桨或动力装置，仅需更换插入件即可。
本申请的实施方式的动力装置包括转子以及跟随所述转子一起转动的第二连接件，所述第二连接件用于与插入件以及螺旋桨的第一连接件配合；
所述第一连接件和所述第二连接件的其中一个设有凸部，所述第一连接件和所述第二连接件的另外一个设有收容部，所述收容部开设有沿第一方向贯穿的安装通孔，所述凸部开设有凹陷，所述凸部沿第二方向至少部分地安装于所述收容部中，并且所述凸部的凹陷与所述通孔相对应；
所述插入件穿设所述安装通孔以及所述凹陷中，所述插入件限制所述凸部和所述收容部沿所述第二方向相互分离，所述第一方向与所述第二方向相交。
上述实施方式的动力装置中，由于插入件穿设并锁紧在安装通孔和凹陷中，一方面，当第一连接件或第二连接件转动时，可通过插入件传递扭矩，另一方面，也可通过插入件传递拉力，避免第一连接件和第二连接件相互分离。因此，在本申请实施方式的快拆连接组件，分别通过不同的结构传递扭矩和实现锁紧功能，从而分散受力情况，有效避免受力较为集中而导致容易磨损或折断。并且，插入件与第一连接件和第二连接件分离设置，即使插入件损坏，也无需更换整个螺旋桨或动力装置，仅需更换插入件即可。
本申请的实施方式的动力组件包括动力装置、螺旋桨和上述实施方式中的快拆连接组件，所述第二连接件安装在所述动力装置，所述第一连接件与所述螺旋桨连接。
上述实施方式的动力组件中，由于插入件穿设并锁紧在安装通孔和凹陷中，一方面，当第一连接件或第二连接件转动时，可通过插入件传递扭矩，另一方面，也可通过插入件传 递拉力，避免第一连接件和第二连接件相互分离。因此，在本申请实施方式的快拆连接组件，分别通过不同的结构传递扭矩和实现锁紧功能，从而分散受力情况，有效避免受力较为集中而导致容易磨损或折断。并且，插入件与第一连接件和第二连接件分离设置，即使插入件损坏，也无需更换整个螺旋桨或动力装置，仅需更换插入件即可。
本申请的实施方式的无人机包括包括机身和机臂，所述机臂连接所述机身，所述机臂上安装有上述实施方式中的动力组件。
由于插入件穿设并锁紧在安装通孔和凹陷中，一方面，当第一连接件或第二连接件转动时，可通过插入件传递扭矩，另一方面，也可通过插入件传递拉力，避免第一连接件和第二连接件相互分离。因此，在本申请实施方式的快拆连接组件，分别通过不同的结构传递扭矩和实现锁紧功能，从而分散受力情况，有效避免受力较为集中而导致容易磨损或折断。并且，插入件与第一连接件和第二连接件分离设置，即使插入件损坏，也无需更换整个螺旋桨或动力装置，仅需更换插入件即可。
本申请的附加方面和优点将在下面的描述中部分给出，部分将从下面的描述中变得明显，或通过本申请的实践了解到。
本申请的上述和/或附加的方面和优点从结合下面附图对实施方式的描述中将变得明显和容易理解，其中：
图1是本申请实施方式的快拆连接组件的结构示意图；
图2是本申请实施方式的快拆连接组件的分解示意图；
图3是本申请实施方式的快拆连接组件的截面示意图；
图4是本申请实施方式的快拆连接组件的另一截面示意图；
图5是本申请实施方式的快拆连接组件的插入件的结构示意图；
图6是本申请实施方式的快拆连接组件的插入件的另一结构示意图；
图7是本申请实施方式的无人机的结构示意图。
主要元件符号说明：
无人机1000；
快拆连接组件100、第一连接件10、凸部11、凹陷111、安装部12、夹持臂121、第二连接件20、收容部21、安装通孔211、安装座22、安装座通孔221、插入件30、第一卡部31、第二卡部32、本体33、卡臂34、弹簧卡件35、连接部351、卡脚352、凸出部353、弹性件40、固定件50、第一方向X、第二方向Y；
螺旋桨200、桨叶201、动力装置300、电机轴301、机身400、机臂500。
下面详细描述本申请的实施方式，所述实施方式的示例在附图中示出，其中自始至终相同或类似的标号表示相同或类似的元件或具有相同或类似功能的元件。下面通过参考附图描述的实施方式是示例性的，仅用于解释本申请，而不能理解为对本申请的限制。
在本申请的描述中，需要理解的是，术语“中心”、“纵向”、“横向”、“长度”、“宽度”、“厚度”、“上”、“下”、“前”、“后”、“左”、“右”、“竖直”、“水平”、“顶”、“底”、“内”、“外”、“顺时针”、“逆时针”等指示的方位或位置关系为基于附图所示的方位或位置关系，仅是为了便于描述本申请和简化描述，而不是指示或暗示所指的装置或元件必须具有特定的方位、以特定的方位构造和操作，因此不能理解为对本申请的限制。此外，术语“第一”、“第二”仅用于描述目的，而不能理解为指示或暗示相对重要性或者隐含指明所指示的技术特征的数量。由此，限定有“第一”、“第二”的特征可以明示或者隐含地包括一个或者更多个所述特征。在本申请的描述中，“多个”的含义是两个或两个以上，除非另有明确具体的限定。
在本申请的描述中，需要说明的是，除非另有明确的规定和限定，术语“安装”、“相连”、“连接”应做广义理解，例如，可以是固定连接，也可以是可拆卸连接，或一体地连接。可以是机械连接，也可以是电连接。可以是直接相连，也可以通过中间媒介间接相连，可以是两个元件内部的连通或两个元件的相互作用关系。对于本领域的普通技术人员而言，可以根据具体情况理解上述术语在本申请中的具体含义。
请参阅图1至图4，本申请实施方式的快拆连接组件100包括第一连接件10、第二连接件20和插入件30，第一连接件10以及第二连接件20中的一个用于与螺旋桨200机械耦合，另外一个用于与动力装置300机械耦合；
第一连接件10和第二连接件20的其中一个设有凸部11，第一连接件10和第二连接件20的另外一个设有收容部21，收容部21开设有沿第一方向X贯穿的安装通孔211，凸部11开设有凹陷111，凸部11沿第二方向Y至少部分地安装于收容部21中，并且凸部11的凹陷111与安装通孔211相对应。
插入件30穿设安装通孔211以及凹陷111中，插入件30限制凸部11和收容部21沿第二方向Y相互分离，第一方向X与第二方向Y相交。
具体地，在图示的实施方式中，第一连接件10与螺旋桨200机械耦合，第二连接件20与动力装置300机械耦合，第一连接件10设有凸部11，第二连接件20设有收容部21。可 以理解的是，在其他实施方式中，可以是第二连接件20与螺旋桨200机械耦合，第一连接件10与动力装置300机械耦合，第二连接件20设有凸部11，第一连接件10设有收容部21，具体设置方式在此不作限制。上述机械耦合可以是指两者直接固定连接或者是通过其他部件间接固定连接或者是可拆卸地连接。
需要说明的是，凹陷111可以为通孔也可以为凹槽，也即是说，凸部11可形成通孔或者凹槽。在图示的实施方式中，凹陷111为在凸部11上沿第一方向X开设的通孔，通孔与收容部21上的安装通孔211相对应，插入件30依次穿设安装通孔211和凸部11上的通孔以限制凸部11和收容部21沿第二方向Y相互分离。
此外，在本实施方式中，上述第一方向X与第二方向Y相交(即非平行)，第一方向X和第二方向Y的夹角为60～120度。在图示的实施方式中，第一方向X与第二方向Y垂直，第一方向X为水平方向，第二方向Y为竖直方向。
目前，在传统技术中通常直接用螺纹将螺旋桨和动力源部件直接连接，利用螺纹配合传递和拉力，或者是利用螺旋桨上的特定的结构(例如，L型卡勾)与动力源部件上的凹槽相配合，利用二者的配合结构同时对螺旋桨进行锁定，以及传递扭矩和拉力。然而，在上述两种方式中，螺旋桨和动力源部件的配合结构同时起到传递扭矩和锁紧的作用，其受力较为集中，导致容易磨损或折断，使用时间较长时容易出现可靠性问题，在传递动力是螺旋桨可能从动力源部件上脱离，影响无人机的安全性。
在本申请实施方式的快拆连接组件100中，由于插入件30穿设并锁紧在安装通孔211和凹陷111中，一方面，当第一连接件10或第二连接件20转动时，可通过凸部11与收容部21相配合而传递扭矩，另一方面，通过插入件30实现锁紧功能，避免第一连接件10和第二连接件20相互分离，提高了连接的可靠性。因此，在本申请实施方式的快拆连接组件100，分别通过不同的结构传递扭矩和实现锁紧功能，从而分散受力情况，有效避免受力较为集中而导致容易磨损或折断。
并且，插入件30与第一连接件10和第二连接件20分离设置，即使插入件30损坏，也无需更换整个螺旋桨200或动力装置300，仅需更换插入件30即可。
请参阅图2至图4，在本实施方式中，第一连接件10设有凸部11，第二连接件20设有收容部21，第二连接件20包括安装座22，收容部21凸设在安装座22，安装座22用于安装在动力装置300。
具体地，安装座22通过固定件50固定安装在动力装置300中，固定件50包括螺钉、销轴等固定元件。动力装置300可为电机，电机可以为外转子电机或者内转子电机，安装座22安装在电机的转子上并能够跟跟随转子一起转动。如此，安装座22固定安装在动力装置300上并能够跟随动力装置300一起转动，从而使得在动力装置300转动时能够通过第二连 接件20和第一连接件10带动螺旋桨200转动。
可以理解的是，在某些实施方式中，第一连接件10以及第二连接件20中的一个为电机的转子壳或与电机的转子一起转动的部件，另外一个为螺旋桨200的桨毂或与桨毂一起转动的部件，具体设置方式在此不作限制。
请继续参阅图2至图4，进一步地，在本实施方式中，安装座22开设有安装座通孔221，安装座通孔221收容有弹性件40，弹性件40将插入件30压紧在安装通孔211和凹陷111中。
具体地，在图示的实施方式中，动力装置300可为电机，电机的电机轴301穿设安装座通孔221，弹性件40套设在电机轴301上，弹性件40的一端抵持动力装置300，另一端抵持插入件30，弹性件40处于压缩状态以给插入件30施加弹性力以将插入件30压紧在安装通孔211和凹陷111中。
这样，弹性件40能够将插入件30压紧在安装通孔211和凹陷111中，从而防止插入件30从安装通孔211和/或凹陷111中脱离出来，提高了连接的可靠性和稳定性。
请参阅图2和图4，在某些实施方式中，插入件30呈长条状，插入件30沿插入件30长度方向的两端分别凸设有第一卡部31和第二卡部32，弹性件40将插入件30压向第一连接件10，第一卡部31和第二卡部32卡紧在收容部21的外壁。
具体地，插入件30包括本体33和连接在本体33一端的两个卡臂34，两个卡臂34间隔设置，本体33与卡臂34相背的一端设有上述第一卡部31，卡臂34与本体33相背的一端设有上述第二卡部32。也即是说，两个卡臂34之间留有间隔，每个卡臂34的一端均设有一个第二卡部32。
请参阅图3和图4，在将插入件30穿设插入至安装通孔211和凹陷111中时，电机的电机轴301位于两个卡臂34之间。在将插入件30插入后，弹性件40将插入件30压向第一连接件10以将第一卡部31和第二卡部32卡紧在收容部21的外壁。这样，第一卡部31和第二卡部32可以防止在插入件30插入安装通孔211和凹陷111后沿第一方向X运动而出现脱离现象。
请参阅图5和图6，在某些实施方式中，插入件30可以是弹簧卡件35。如图所示，弹簧卡件35具有两个卡脚352和连接两个卡脚352的连接部351，卡脚352具有弹性，两个卡脚352之间的间隙宽度可以在外力的作用下缩小并能够在撤去外力时恢复。在需要将弹簧卡件35插入，可将两个卡脚352从外侧捏住，然后将弹簧卡件35插入安装通孔211和凹陷111中，然后松开卡脚352即可在弹簧卡件35的弹性力的作用下卡紧凸部11和收容部21。由于弹簧卡件35具有弹性，因此，本实施方式中，也可以不设置上述的弹性件40。当然，为了更进一步的保证连接的稳定性和可靠性，也可以选择设置弹性件40将弹簧卡件35压紧 在第一连接件10上，具体设置方式在此不作限制。图5中的弹簧卡件35处于卡脚352没有被捏住的常规状态，图6中的弹簧卡件35处于卡脚352被捏住的压缩状态。
另外，在一些实施方式中，安装通孔211可包括螺纹段通孔，凹陷111可包括螺纹段，插入件30可包括螺纹部，螺纹部螺合在螺纹段通孔和螺纹段而将插入件30锁紧在安装通孔211和凹陷111中。
如此，利用插入件30与安装通孔211和凹陷111螺纹连接也同样可以将第一连接件10和第二连接件20可靠的连接并且方便拆卸。
请参阅图2，在某些实施方式中，凸部11的形状为非圆柱形，收容部21形成有收容凸部11的空腔212，空腔212形状与凸部11的形状相匹配。
如此，将凸部11制造成非圆柱形并将收容部21收容凸部11的空腔212的形状制作成与凸部11的形状相匹配可以防呆，使得在安装第一连接件10和第二连接件20时可以快速准确地将安装通孔211和凹陷111对准，进而能够准确快速的将插入件30穿设插入至安装通孔211和凹陷111中。
具体地，在图2所示的示例中，凸部11呈正六边形。可以理解的是，在其他实施方式中，凸部11也可呈正八边形等规则的形状或者是其他不规则形状，具体在此不作限制。
请参阅图2至图4，在某些实施方式中，第一连接件10设有凸部11，第二连接件20设有收容部21，第一连接件10包括连接凸部11的安装部12，安装部12位于凸部11远离收容部21的一侧，安装部12安装有螺旋桨200的桨叶201。
具体地，安装部12包括夹持臂121，夹持臂121夹持桨叶201的一端。在图示的实施方式中，桨叶201的数量为两个，夹持臂121的数量是2个，每两个夹持臂121夹持一个桨叶201。另外，可通过轴连接的方式将夹持臂与桨叶可转动地连接，这样方便桨叶201的收纳。
在某些实施方式中，插入件30设有限位部，限位部用于与第一连接件10和/或第二连接件20相配合，以阻止插入件30从安装通孔211和/或凹陷111内脱出。
如此，在插入件30插入安装通孔211和凹陷111中时，限位部能够与第一连接件10和/或第二连接件20向配合以防止插入件30脱出。
具体地，在一些实施方式中，限位部可包括第一卡扣件，第二连接件20设有第二卡扣件，在插入件30插入安装通孔211和凹陷111中时，第一卡扣件与第二卡扣件配合以将限位部卡紧以防止插入件30脱出。
可以理解的是，在插入件30为弹簧卡件35时，限位部也可以是形成在卡脚352上的凸出部353，在弹簧卡件35位被捏住后插入安装通孔211和凹陷111中后松开时，卡脚352可将弹簧卡件35卡紧，卡脚352的凸出部353卡在收容部的外壁上以防止弹簧 卡件35脱落。当然，上述限位部也可以是包括在上述实施方式提到的第一卡部31和第二卡部32，具体结构在此不做重复阐述。
此外，请参阅图4，在本实施方式中，弹性件40用于提供一个弹性力给插入件30，以使插入件30保持与第一连接件10和/或第二连接件20相配合的状态。
具体地，弹性件40提供的弹力能够促使插入件30沿第二方向Y运动，直至插入件30保持与第一连接件10和/或第二连接件20相配合。
这样，在插入件30插入安装通孔211和凹陷111时，弹性件40可以促使插入件30沿第二方向Y运动从而使得插入件30抵持第一连接件10或者第二连接件20，进而可以防止插入件30从安装通孔211和凹陷111中脱出。
另外，在一些实施方式中，插入件30也可与第一连接件10和/或第二连接件20相卡合。具体地，插入件30与第一连接件10和/或第二连接件20可通过卡扣连接的方式扣合以防止插入件30脱出。
本申请实施方式的螺旋桨200用于给无人机1000提供飞行动力，螺旋桨200包括第一连接件10与以及与第一连接件10连接的桨叶201，第一连接件10用于与插入件30以及动力装置300的第二连接件20配合。第一连接件10和第二连接件20的其中一个设有凸部11，第一连接件10和第二连接件20的另外一个设有收容部21，收容部21开设有沿第一方向X贯穿的安装通孔211，凸部11开设有凹陷111，凸部11沿第二方向Y至少部分地安装于收容部21中，并且凸部11的凹陷111与通孔相对应。插入件30穿设安装通孔211以及凹陷111中，插入件30限制凸部11和所述收容部21沿所述第二方向Y相互分离，所述第一方向X与所述第二方向Y相交。
在上述实施方式的螺旋桨200中，由于插入件30穿设并锁紧在安装通孔211和凹陷111中，一方面，当第一连接件10或第二连接件20转动时，可通过插入件30传递扭矩，另一方面，也可通过插入件30传递拉力，避免第一连接件10和第二连接件20相互分离，提高了连接的可靠性。
本申请实施方式的动力装置300包括转子以及跟随转子一起转动的第二连接件20，第二连接件20用于与插入件30以及螺旋桨200的第一连接件10配合；
第一连接件10和第二连接件20的其中一个设有凸部11，第一连接件10和第二连接件20的另外一个设有收容部21，收容部21开设有沿第一方向X贯穿的安装通孔211，凸部11开设有凹陷111，凸部11沿第二方向Y至少部分地安装于收容部21中，并且凸部11的凹陷111与通孔相对应；
插入件30穿设安装通孔211以及凹陷111中，插入件30限制凸部11和收容部21沿第二方向Y相互分离，第一方向X与第二方向Y相交。
在上述实施方式的动力装置300中，由于插入件30穿设并锁紧在安装通孔211和凹陷111中，一方面，当第一连接件10或第二连接件20转动时，可通过插入件30传递扭矩，另一方面，也可通过插入件30传递拉力，避免第一连接件10和第二连接件20相互分离，提高了连接的可靠性。上述动力装置300包括但不限于外转子电机和内转子电机。
本申请实施方式的动力组件600包括上述任一实施方式中的动力装置300、螺旋桨200和上述任一实施方式中的快拆连接组件100，第二连接件20安装在动力装置300，第一连接件10与螺旋桨200连接。
具体地，动力装置300包括限位轴，限位轴穿设快拆连接组件100。动力装置300可为电机，在动力装置300为电机时，限位轴为电机轴301，第二连接件20可与电机的转子连接，这样，转动带动第二连接件20转动，插入件30可以带动第一连接件10转动，从而带动螺旋桨200的桨叶201转动。
在上述实施方式的动力组件中，由于插入件30穿设并锁紧在安装通孔211和凹陷111中，一方面，当第一连接件10或第二连接件20转动时，可通过插入件30传递扭矩，另一方面，也可通过插入件30传递拉力，避免第一连接件10和第二连接件20相互分离，提高了连接的可靠性。
请参阅图7，本申请实施方式的无人机1000包括机身400和机臂500，机臂500连接机身400，机臂500上安装有上述实施方式所述的动力组件。具体在图示的实施例中，无人机1000为多旋翼飞行器。
具体地，无人机1000包括多个机臂500，每个机臂500都安装有包括螺旋桨200的动力组件，动力组件的动力装置300转动时可带动能够螺旋桨200转动，从而为无人机1000提供飞行动力。
在上述实施方式的无人机1000中，由于插入件30穿设并锁紧在安装通孔211和凹陷111中，一方面，当第一连接件10或第二连接件20转动时，可通过插入件30传递扭矩，另一方面，也可通过插入件30传递拉力，避免第一连接件10和第二连接件20相互分离，提高了连接的可靠性。
具体在图示的实施例中，所述动力组件600的数量为多个，包括第一动力组件以及第二动力组件(见图7)，所述第一动力组件的动力装置300用于驱动螺旋桨200沿顺时针方向转动，所述第二动力组件的动力装置300用于驱动螺旋桨200沿逆时针方向转动。
为了避免用户将第一动力组件的螺旋桨错误地安装在第二动力组件的动力装置上，或者，将第二动力组件的螺旋桨错误地安装在第一动力组件的动力装置上，本申请的实施方式利用凸部11与收容部21的相互配合的关系，即，所述凸部与所述收容部的形状或/及尺寸相适配，以实现“防呆”的功能。例如：
在其中一个实施例中，所述第一动力组件的所述凸部11的形状与所述第二动力组件的所述凸部11的形状不相同，从而使得第一动力组件的螺旋桨200只能与第一动力组件的动力装置300相连接，而不能与第二动力组件的动力装置300相连接；从而使得第二动力组件的螺旋桨200只能与第二动力组件的动力装置300相连接，而不能与第一动力组件的动力装置相连接，进而避免螺旋桨装配错误而引起飞行器炸机的问题。
在其中一个实施例中，所述第一动力组件的所述凸部11的尺寸与所述第二动力组件的所述凸部11的尺寸不相同，从而使得第一动力组件的螺旋桨200只能与第一动力组件的动力装置300相连接，而不能与第二动力组件的动力装置300相连接；从而使得第二动力组件的螺旋桨200只能与第二动力组件的动力装置300相连接，而不能与第一动力组件的动力装置相连接，进而避免螺旋桨装配错误而引起飞行器炸机的问题。所述尺寸可根据所述凸部形状来选择，例如，所述尺寸可以为长度，宽度，半径，或曲率。
另外，为了避免用户将第一动力组件的螺旋桨错误地安装在第二动力组件的动力装置上，或者，将第二动力组件的螺旋桨错误地安装在第一动力组件的动力装置上，本申请的实施方式也可以利用动力装置的限位轴与螺旋桨的限位孔的相互配合的关系，即，所述限位轴与所述限位孔的形状或/及尺寸相适配，以实现“防呆”的功能。例如：
在其中一个实施例中，所述第一动力组件的所述限位轴的形状与所述第二动力组件的所述限位轴的形状不相同，从而使得第一动力组件的螺旋桨只能与第一动力组件的动力装置相连接，而不能与第二动力组件的动力装置相连接；从而使得第二动力组件的螺旋桨只能与第二动力组件的动力装置相连接，而不能与第一动力组件的动力装置相连接，进而避免螺旋桨装配错误而引起飞行器炸机的问题。
在其中一个实施例中，所述第一动力组件的所述限位轴的尺寸与所述第二动力组件的所述限位轴的尺寸不相同，从而使得第一动力组件的螺旋桨只能与第一动力组件的动力装置相连接，而不能与第二动力组件的动力装置相连接；从而使得第二动力组件的螺旋桨只能与第二动力组件的动力装置相连接，而不能与第一动力组件的动力装置相连接，进而避免螺旋桨装配错误而引起飞行器炸机的问题。
在本申请中，除非另有明确的规定和限定，第一特征在第二特征之“上”或之“下”可以包括第一和第二特征直接接触，也可以包括第一和第二特征不是直接接触而是通过它们之间的另外的特征接触。而且，第一特征在第二特征“之上”、“上方”和“上面”包括第一特征在第二特征正上方和斜上方，或仅仅表示第一特征水平高度高于第二特征。第一特征在第二特征“之下”、“下方”和“下面”包括第一特征在第二特征正下方和斜下方，或仅仅表示第一特征水平高度小于第二特征。
本文的公开提供了许多不同的实施方式或例子用来实现本申请的不同结构。为了简 化本申请的公开，本文中对特定例子的部件和设置进行描述。当然，它们仅仅为示例，并且目的不在于限制本申请。此外，本申请可以在不同例子中重复参考数字和/或参考字母，这种重复是为了简化和清楚的目的，其本身不指示所讨论各种实施方式和/或设置之间的关系。此外，本申请提供了的各种特定的工艺和材料的例子，但是本领域普通技术人员可以意识到其他工艺的应用和/或其他材料的使用。
在本说明书的描述中，参考术语“一个实施方式”、“一些实施方式”、“示意性实施方式”、“示例”、“具体示例”、或“一些示例”等的描述意指结合实施方式或示例描述的具体特征、结构、材料或者特点包含于本申请的至少一个实施方式或示例中。在本说明书中，对上述术语的示意性表述不一定指的是相同的实施方式或示例。而且，描述的具体特征、结构、材料或者特点可以在任何的一个或多个实施方式或示例中以合适的方式结合。尽管已经示出和描述了本申请的实施方式，本领域的普通技术人员可以理解：在不脱离本申请的原理和宗旨的情况下可以对这些实施方式进行多种变化、修改、替换和变型，本申请的范围由权利要求及其等同物限定。
Claims (65)
- 一种快拆连接组件，用于连接螺旋桨和动力装置，其特征在于，所述快拆连接组件包括第一连接件、第二连接件和插入件，所述第一连接件以及所述第二连接件中的一个用于与螺旋桨机械耦合，另外一个用于与动力装置机械耦合；所述第一连接件和所述第二连接件的其中一个设有凸部，所述第一连接件和所述第二连接件的另外一个设有收容部，所述收容部开设有沿第一方向贯穿的安装通孔，所述凸部开设有凹陷，所述凸部沿第二方向至少部分地安装于所述收容部中，并且所述凸部的凹陷与所述通孔相对应；所述插入件穿设所述安装通孔以及所述凹陷中，所述插入件限制所述凸部和所述收容部沿所述第二方向相互分离，所述第一方向与所述第二方向相交。
- 根据权利要求1所述的快拆连接组件，其特征在于，所述第一连接件设有所述凸部，所述第二连接件设有所述收容部，所述第二连接件包括安装座，所述收容部凸设在所述安装座，所述安装座用于安装在所述动力装置。
- 根据权利要求2所述的快拆连接组件，其特征在于，所述安装座开设有安装座通孔，所述安装座通孔收容有弹性件，所述弹性件将所述插入件压紧在所述安装通孔和所述凹陷中。
- 根据权利要求3所述的快拆连接组件，其特征在于，所述插入件呈长条状，所述插入件沿所述插入件长度方向的两端分别凸设有第一卡部和第二卡部，所述弹性件将所述插入件压向所述第一连接件，所述第一卡部和所述第二卡部卡紧在所述收容部的外壁。
- 根据权利要求4所述的快拆连接组件，其特征在于，所述插入件包括本体和连接在所述本体一端的两个卡臂，所述两个卡臂间隔设置，所述本体与所述卡臂相背的一端设有所述第一卡部，所述卡臂与所述本体相背的一端设有所述第二卡部。
- 根据权利要求3所述的快拆连接组件，其特征在于，所述动力装置为电机，所述弹性件套设在所述电机的电机轴上。
- 根据权利要求1所述的快拆连接组件，其特征在于，所述凸部的形状为非圆柱形，所述收容部形成有收容所述凸部的空腔，所述空腔的形状与所述凸部的形状相匹配。
- 根据权利要求1所述的快拆连接组件，其特征在于，所述插入件包括弹簧卡件。
- 根据权利要求1所述的快拆连接组件，其特征在于，所述第一连接件设有所述凸部，所述第二连接件设有所述收容部，所述第一连接件包括连接所述凸部的安装部，所述安装部位于所述凸部远离所述收容部的一侧，所述安装部用于安装所述螺旋桨的桨叶。
- 根据权利要求9所述的快拆连接组件，其特征在于，所述安装部包括夹持臂，所述夹持臂用于夹持所述桨叶的一端。
- 根据权利要求1所述的快拆连接组件，其特征在于，所述安装通孔包括螺纹段通孔，所述凹陷包括螺纹段，所述插入件包括螺纹部，所述螺纹部螺合在所述螺纹段通孔和所述螺纹段而将所述插入件锁紧在所述安装通孔和所述凹陷中。
- 根据权利要求1所述的快拆连接组件，其特征在于，所述第一方向与所述第二方向垂直。
- 根据权利要求1所述的快拆连接组件，其特征在于，所述第一连接件以及所述第二连接件中的一个为电机的转子壳或与所述电机的转子一起转动的部件，另外一个为所述螺旋桨的桨毂或与所述桨毂一起转动的部件。
- 根据权利要求13所述的快拆连接组件，其特征在于，所述电机为外转子电机，或者内转子电机。
- 根据权利要求1所述的快拆连接组件，其特征在于，所述插入件设有限位部，所述限位部用于与所述第一连接件和/或所述第二连接件相配合，以阻止所述插入件从所述安装通孔和/或所述凹陷内脱出。
- 根据权利要求15所述的快拆连接组件，其特征在于，所述快拆连接组件包括弹性件，所述弹性件用于提供一个弹性力给所述插入件，以使所述插入件保持与所述第一连接件和/或所述第二连接件相配合的状态。
- 根据权利要求16所述的快拆连接组件，其特征在于，所述弹性件提供的弹力能够促使所述插入件沿所述第二方向运动，直至所述插入件保持与所述第一连接件和/或所述第二连接件相配合。
- 根据权利要求1所述的快拆连接组件，其特征在于，所述插入件与所述第一连接件和/或所述第二连接件相卡合。
- 根据权利要求1所述的快拆连接组件，其特征在于，所述第一方向与所述第二方向的夹角为60～120度。
- 一种螺旋桨，其特征在于，所述螺旋桨用于给无人机提供飞行动力，所述螺旋桨包括第一连接件与以及与所述第一连接件连接的桨叶，所述第一连接件用于与插入件以及动力装置的第二连接件配合；所述第一连接件和所述第二连接件的其中一个设有凸部，所述第一连接件和所述第二连接件的另外一个设有收容部，所述收容部开设有沿第一方向贯穿的安装通孔，所述凸部开设有凹陷，所述凸部沿第二方向至少部分地安装于所述收容部中，并且所述凸部的凹陷与所述通孔相对应；所述插入件穿设所述安装通孔以及所述凹陷中，所述插入件限制所述凸部和所述收容部沿所述第二方向相互分离，所述第一方向与所述第二方向相交。
- 根据权利要求20所述的螺旋桨，其特征在于，所述第一连接件设有所述凸部，所述第二连接件设有所述收容部，所述第二连接件包括安装座，所述收容部凸设在所述安装座，所述安装座用于安装在所述动力装置。
- 根据权利要求21所述的螺旋桨，其特征在于，所述安装座开设有安装座通孔，所述安装座通孔收容有弹性件，所述弹性件将所述插入件压紧在所述安装通孔和所述凹陷中。
- 根据权利要求22所述的螺旋桨，其特征在于，所述插入件呈长条状，所述插入件沿所述插入件长度方向的两端分别凸设有第一卡部和第二卡部，所述弹性件将所述插入件压向所述第一连接件，所述第一卡部和所述第二卡部卡紧在所述收容部的外壁。
- 根据权利要求23所述的螺旋桨，其特征在于，所述插入件包括本体和连接在所述本体一端的两个卡臂，所述两个卡臂间隔设置，所述本体与所述卡臂相背的一端设有所述第一卡部，所述卡臂与所述本体相背的一端设有所述第二卡部。
- 根据权利要求22所述的螺旋桨，其特征在于，所述动力装置为电机，所述弹性件套设在所述电机的电机轴上。
- 根据权利要求20所述的螺旋桨，其特征在于，所述凸部的形状为非圆柱形，所述收容部形成有收容所述凸部的空腔，所述空腔的形状与所述凸部的形状相匹配。
- 根据权利要求20所述的螺旋桨，其特征在于，所述插入件包括弹簧卡件。
- 根据权利要求20所述的螺旋桨，其特征在于，所述第一连接件设有所述凸部，所述第二连接件设有所述收容部，所述第一连接件包括连接所述凸部的安装部，所述安装部位于所述凸部远离所述收容部的一侧，所述安装部用于安装所述螺旋桨的桨叶。
- 根据权利要求28所述的螺旋桨，其特征在于，所述安装部包括夹持臂，所述夹持臂用于夹持所述桨叶的一端。
- 根据权利要求20所述的螺旋桨，其特征在于，所述安装通孔包括螺纹段通孔，所述凹陷包括螺纹段，所述插入件包括螺纹部，所述螺纹部螺合在所述螺纹段通孔和所述螺纹段而将所述插入件锁紧在所述安装通孔和所述凹陷中。
- 根据权利要求20所述的螺旋桨，其特征在于，所述第一方向与所述第二方向垂直。
- 根据权利要求20所述的螺旋桨，其特征在于，所述第一连接件以及所述第二连接件中的一个为电机的转子壳或与所述电机的转子一起转动的部件，另外一个为所述螺旋桨的桨毂或与所述桨毂一起转动的部件。
- 根据权利要求32所述的螺旋桨，其特征在于，所述电机为外转子电机，或者内转子电机。
- 根据权利要求20所述的螺旋桨，其特征在于，所述插入件设有限位部，所述限位部用于与所述第一连接件和/或所述第二连接件相配合，以阻止所述插入件从所述安装通孔 和/或所述凹陷内脱出。
- 根据权利要求34所述的螺旋桨，其特征在于，还包括弹性件，所述弹性件用于提供一个弹性力给所述插入件，以使所述插入件保持与所述第一连接件和/或所述第二连接件相配合的状态。
- 根据权利要求35所述的螺旋桨，其特征在于，所述弹性件提供的弹力能够促使所述插入件沿所述第二方向运动，直至所述插入件保持与所述第一连接件和/或所述第二连接件相配合。
- 根据权利要求20所述的螺旋桨，其特征在于，所述插入件与所述第一连接件和/或所述第二连接件相卡合。
- 根据权利要求20所述的螺旋桨，其特征在于，所述第一方向与所述第二方向的夹角为60～120度。
- 一种动力装置，其特征在于，包括转子以及跟随所述转子一起转动的第二连接件，所述第二连接件用于与插入件以及螺旋桨的第一连接件配合；所述第一连接件和所述第二连接件的其中一个设有凸部，所述第一连接件和所述第二连接件的另外一个设有收容部，所述收容部开设有沿第一方向贯穿的安装通孔，所述凸部开设有凹陷，所述凸部沿第二方向至少部分地安装于所述收容部中，并且所述凸部的凹陷与所述通孔相对应；所述插入件穿设所述安装通孔以及所述凹陷中，所述插入件限制所述凸部和所述收容部沿所述第二方向相互分离，所述第一方向与所述第二方向相交。
- 根据权利要求39所述的动力装置，其特征在于，所述第一连接件设有所述凸部，所述第二连接件设有所述收容部，所述第二连接件包括安装座，所述收容部凸设在所述安装座，所述安装座用于安装在所述动力装置。
- 根据权利要求40所述的动力装置，其特征在于，所述安装座开设有安装座通孔，所述安装座通孔收容有弹性件，所述弹性件将所述插入件压紧在所述安装通孔和所述凹陷中。
- 根据权利要求42所述的动力装置，其特征在于，所述插入件呈长条状，所述插入件沿所述插入件长度方向的两端分别凸设有第一卡部和第二卡部，所述弹性件将所述插入件压向所述第一连接件，所述第一卡部和所述第二卡部卡紧在所述收容部的外壁。
- 根据权利要求43所述的动力装置，其特征在于，所述插入件包括本体和连接在所述本体一端的两个卡臂，所述两个卡臂间隔设置，所述本体与所述卡臂相背的一端设有所述第一卡部，所述卡臂与所述本体相背的一端设有所述第二卡部。
- 根据权利要求42所述的动力装置，其特征在于，所述动力装置为电机，所述弹性件套设在所述电机的电机轴上。
- 根据权利要求39所述的动力装置，其特征在于，所述凸部的形状为非圆柱形，所述收容部形成有收容所述凸部的空腔，所述空腔的形状与所述凸部的形状相匹配。
- 根据权利要求39所述的动力装置，其特征在于，所述插入件包括弹簧卡件。
- 根据权利要求39所述的动力装置，其特征在于，所述第一连接件设有所述凸部，所述第二连接件设有所述收容部，所述第一连接件包括连接所述凸部的安装部，所述安装部位于所述凸部远离所述收容部的一侧，所述安装部用于安装所述螺旋桨的桨叶。
- 根据权利要求48所述的动力装置，其特征在于，所述安装部包括夹持臂，所述夹持臂用于夹持所述桨叶的一端。
- 根据权利要求39所述的动力装置，其特征在于，所述安装通孔包括螺纹段通孔，所述凹陷包括螺纹段，所述插入件包括螺纹部，所述螺纹部螺合在所述螺纹段通孔和所述螺纹段而将所述插入件锁紧在所述安装通孔和所述凹陷中。
- 根据权利要求39所述的动力装置，其特征在于，所述第一方向与所述第二方向垂直。
- 根据权利要求39所述的动力装置，其特征在于，所述第一连接件以及所述第二连接件中的一个为电机的转子壳或与所述电机的转子一起转动的部件，另外一个为所述螺旋桨的桨毂或与所述桨毂一起转动的部件。
- 根据权利要求51所述的动力装置，其特征在于，所述电机为外转子电机，或者内转子电机。
- 根据权利要求39所述的动力装置，其特征在于，所述插入件设有限位部，所述限位部用于与所述第一连接件和/或所述第二连接件相配合，以阻止所述插入件从所述安装通孔和/或所述凹陷内脱出。
- 根据权利要求53所述的动力装置，其特征在于，还包括弹性件，所述弹性件用于提供一个弹性力给所述插入件，以使所述插入件保持与所述第一连接件和/或所述第二连接件相配合的状态。
- 根据权利要求54所述的动力装置，其特征在于，所述弹性件提供的弹力能够促使所述插入件沿所述第二方向运动，直至所述插入件保持与所述第一连接件和/或所述第二连接件相配合。
- 根据权利要求39所述的动力装置，其特征在于，所述插入件与所述第一连接件和/或所述第二连接件相卡合。
- 根据权利要求39所述的动力装置，其特征在于，所述第一方向与所述第二方向的夹角为60～120度。
- 一种动力组件，其特征在于，包括动力装置、螺旋桨和权利要求39-57任一项所述 的快拆连接组件，所述第二连接件安装在所述动力装置，所述第一连接件与所述螺旋桨连接。
- 根据权利要求58所述的动力组件，其特征在于，所述动力装置包括限位轴，所述限位轴穿设所述快拆连接组件。
- 一种无人机，其特征在于，包括机身和机臂，所述机臂连接所述机身，所述机臂上安装有权利要求58所述的动力组件。
- 根据权利要求60所述的无人机，其特征在于，所述动力组件为多个，包括第一动力组件以及第二动力组件，所述第一动力组件的动力装置用于驱动螺旋桨沿顺时针方向转动，所述第二动力组件的动力装置用于驱动螺旋桨沿逆时针方向转动。
- 根据权利要求61所述的无人机，其特征在于，所述第一动力组件的所述凸部的形状与所述第二动力组件的所述凸部的形状不相同。
- 根据权利要求61所述的无人机，其特征在于，所述第一动力组件的所述凸部的尺寸与所述第二动力组件的所述凸部的尺寸不相同。
- 根据权利要求61所述的无人机，其特征在于，所述尺寸包括如下至少一种：长度，宽度，半径，曲率。
- 根据权利要求61所述的无人机，其特征在于，所述无人机为多旋翼飞行器。
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| CN107839871A (zh) * | 2017-11-30 | 2018-03-27 | 歌尔股份有限公司 | 螺旋桨连接结构以及无人飞行器 |
| CN207550508U (zh) * | 2017-08-15 | 2018-06-29 | 深圳市道通智能航空技术有限公司 | 一种螺旋桨、动力系统以及无人飞行器 |
| CN208233359U (zh) * | 2018-05-04 | 2018-12-14 | 深圳市大疆创新科技有限公司 | 动力套装 |
| US20190039719A1 (en) * | 2017-08-03 | 2019-02-07 | Samsung Electronics Co., Ltd. | Unmanned aerial vehicle including mounting structure for propeller |
| CN209870735U (zh) * | 2019-04-29 | 2019-12-31 | 深圳市大疆创新科技有限公司 | 快拆连接组件、螺旋桨、动力装置及组件和多旋翼飞行器 |
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| US20190039719A1 (en) * | 2017-08-03 | 2019-02-07 | Samsung Electronics Co., Ltd. | Unmanned aerial vehicle including mounting structure for propeller |
| CN207550508U (zh) * | 2017-08-15 | 2018-06-29 | 深圳市道通智能航空技术有限公司 | 一种螺旋桨、动力系统以及无人飞行器 |
| CN107672796A (zh) * | 2017-09-25 | 2018-02-09 | 安徽瓦尔特机械贸易有限公司 | 一种组合式旋翼无人机 |
| CN107839871A (zh) * | 2017-11-30 | 2018-03-27 | 歌尔股份有限公司 | 螺旋桨连接结构以及无人飞行器 |
| CN208233359U (zh) * | 2018-05-04 | 2018-12-14 | 深圳市大疆创新科技有限公司 | 动力套装 |
| CN209870735U (zh) * | 2019-04-29 | 2019-12-31 | 深圳市大疆创新科技有限公司 | 快拆连接组件、螺旋桨、动力装置及组件和多旋翼飞行器 |
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