CN106628165B - Aircraft and screw quick detach device, quick detach formula screw and screw base subassembly thereof - Google Patents
Aircraft and screw quick detach device, quick detach formula screw and screw base subassembly thereof Download PDFInfo
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- CN106628165B CN106628165B CN201611157265.8A CN201611157265A CN106628165B CN 106628165 B CN106628165 B CN 106628165B CN 201611157265 A CN201611157265 A CN 201611157265A CN 106628165 B CN106628165 B CN 106628165B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
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Abstract
The invention provides an aircraft and a propeller quick-release device, a quick-release propeller and a propeller base assembly thereof, wherein the propeller quick-release device comprises a quick-release propeller and a propeller base assembly; the screw base subassembly includes fixing base and key switch, be equipped with the block mechanism who is connected through rotatory detachably between fixing base and the pedestal, key switch has the button body that is suitable for to press to touch and fixes the button dog on the button body, one side shaping towards the fixing base of pedestal has and is located a plurality of location structure that the block position corresponds to the button dog at the pedestal, the button dog is not being suitable for to imbed location structure by external force pressing state, and the card is held between fixing base and pedestal, make quick detach formula screw in ascending motion in circumference by button dog and constant head tank restriction, it is different with its at the ascending restriction atress of axial, mechanical strength has been improved, the good effect of stability has been brought.
Description
Technical Field
The invention relates to the field of propellers, in particular to an aircraft, a propeller quick-release device, a quick-release propeller and a propeller base assembly of the aircraft.
Background
The propeller is a device which rotates in the air or water by means of blades and converts the rotating power of an engine into propulsive force, two or more blades can be connected with a base body, the backward surface of each blade is a spiral surface or a propulsion device similar to the spiral surface, and the propeller is widely applied to aircrafts. At present, a propeller structure of a common aircraft generally includes a base and blades mounted on the base, wherein the base is connected to a rotating shaft of an engine, and the rotating shaft rotates under the action of a power machine to drive the blades to rotate together, so as to propel the aircraft to fly. For a small detachable aircraft, a mode that the rotating shaft penetrates through a through hole in the seat body and then the rotating shaft and the seat body are assembled and connected together in a threaded manner through a nut is adopted between the seat body and the rotating shaft, so that the installation and the disassembly of the small detachable aircraft need to be operated by means of a tool, and the small detachable aircraft is troublesome to use.
In contrast, as shown in fig. 1, chinese patent document CN205469777U discloses an aircraft including a base 2 'and a propeller 1' fixedly mounted on a rotating portion of a driving device. An annular groove is formed on the base 2 ', a plurality of mounting grooves 22 ' which are arranged at equal intervals and are formed by a first limiting part extending inwards in the circumferential direction and a second limiting part connected with one end of the first limiting part and extending inwards in the axial direction are formed on the outer side of the annular groove, and gaps are reserved between every two adjacent mounting grooves 22 '. A first through hole 21 'is provided at the center of the base 2', a notch portion 211 'is opened at a position corresponding to the gap on a wall between the annular groove and the first through hole 21', and one locker 3 'includes a locker body 31' axially slidably provided in the first through hole 21 'and a second protrusion 32' radially protrudingly fixed to the locker body 31 'slidably provided in the notch portion 211' and an elastic member 5 'applying a biasing force toward a direction away from the driving device to the locker body 31'. When the locker body 31 ' moves to a compressed state of the elastic member 5 ', the second protrusion 32 ' exits the annular groove, and when the locker body 31 ' moves to a released state of the elastic member 5 ', the second protrusion 32 ' is inserted into the notch 211 ' with a limited rotation and protrudes into the annular groove. The propeller 1 'has blades 11' and a blade attachment 12 'located in the center of the propeller 1'. The blade connecting portion 12 'is provided with a number of first protrusions 122' corresponding to the number of the mounting grooves 22 'at a radial position corresponding to the annular groove on a side facing the base 2', and the first protrusions 122 'are formed with radially outward protruding portions engaged with the mounting grooves 22'. The center of the blade attachment portion 12 ' is also provided with a second through hole 121 ' communicating with the first through hole 21 '. When the propeller 1 'is required to be installed, after the outward protrusion of the first protrusion 122' of the propeller 1 'is inserted into the gap, the outward protrusion of the first protrusion 122' pushes the second protrusion 32 'of the locker 3' until the outward protrusion of the first protrusion 122 'is aligned with the mounting groove 22', and after rotating a certain angle, the second protrusion 32 'moves into the annular groove with the sliding of the locker body 31' under the biasing force of the elastic member 5 'while the outward protrusion of the first protrusion 122' is inserted into the mounting groove 22 ', blocking the rotation of the first protrusion 122'. Thereby a fast mounting of the propeller 1' is achieved. When the propeller 1 ' needs to be disassembled, the latch 3 ' is pressed downwards by applying force from the second through hole 121 ', so that the second protrusion 32 ' exits from the annular groove, the first protrusion 122 ' on the propeller 1 ' can rotate reversely, the outward protrusion of the first protrusion 122 ' exits from the mounting groove 22 ', the propeller 1 ' is separated from the base 2 ', and the propeller 1 ' is rapidly disassembled and assembled.
However, after the propeller 1 ' of the above-mentioned aircraft is coupled to the base 2 ', the propeller 1 ' is restricted in the rotational direction by inserting the second protrusion 32 ' of the locker 3 ' into the notch portion 211 ' to close the first protrusion 122 ' of the blade attachment portion 12 ' installed in the base 2 '. That is, all the forces generated by the connection between the propeller 1 ' and the base 2 ' are borne by the first protrusion 122 ', which makes the structure of this portion very vulnerable to fatigue.
Disclosure of Invention
Therefore, the technical problem to be solved by the invention is to overcome the technical defect that all forces generated by the connection between the propeller and the base of the aircraft in the prior art are borne by the first protruding part, so that the first protruding part is easily damaged due to fatigue.
To achieve the above object, the present invention provides a propeller base assembly comprising: the fixed seat is fixedly connected to the rotating part of the driving device and is provided with a clamping mechanism which is detachably connected with the connected accessory through rotation; the key switch is circumferentially fixed and axially slidably arranged on the fixed seat, and is provided with a key body suitable for being pressed and a key stop block fixed on the key body, and a reset piece for applying restoring force to the key body when the key body axially slides relative to the fixed seat under the action of external force; when the key switch is not pressed by external force, the key stop block is positioned at a first position where a part of the axial direction stretches out of the fixed seat and blocks the connected accessory from rotating relative to the fixed seat, and when the key switch is pressed by external force, the key stop block is positioned at a second position where the key stop block is retracted into the fixed seat.
Preferably, the key body is cylindrical, and the plurality of key stoppers are arranged on the outer circumferential surface of the key body in a radially outward protruding manner; the fixed seat is provided with a first through hole along the axial direction; a through groove which is recessed outwards in the radial direction is formed on the side wall of the first through hole; the key body is arranged in the first through hole in a sliding mode, and the key stop block is arranged in the through groove in a sliding mode.
Preferably, the bottom of the outer surface of the key switch, which is positioned between the adjacent key stop blocks, is formed with an abutting part which protrudes outwards; the inner wall of the first through hole of the fixing seat is provided with an abutting wall which protrudes inwards corresponding to the abutting part, and the abutting part abuts against the top wall in a no-external-force state.
Preferably, the outer diameter of the abutting part is less than or equal to that of the key stop block; the abutting part is accommodated in the first through hole.
Preferably, the outer diameter of the abutting part is larger than that of the key stop block; the inner wall of the first through hole is outwards sunken corresponding to the abutting part to form a plurality of abutting grooves which downwards penetrate through the fixing base, the abutting part is correspondingly inserted in the abutting grooves, and the groove wall of each abutting groove is an abutting wall.
Preferably, the return member is a spring.
Preferably, a plurality of mounting grooves which are uniformly distributed along the circumferential direction are formed in one side, facing the connecting accessory, of the fixing seat, and a limiting wall extending towards the mounting grooves is formed at one end, located in the locking rotation direction, of the inner wall or the outer wall of each mounting groove.
In order to achieve the above object, the present invention further provides a quick release propeller, including: the base body is provided with a clamping mechanism which is detachably connected with the connected base piece through rotation; the at least two blades are circumferentially and uniformly distributed on the base body; the side of the base body facing to the base piece is formed with a positioning structure, and the positioning structure is limited by a convex part facing to the base body on the connecting base piece to block the rotation of the base body relative to the connecting base piece.
Preferably, the positioning structure is a plurality of positioning grooves which are recessed inwards from the base body towards one side of the connected base piece.
Preferably, the base body is provided with a second through hole along the axial direction.
Preferably, the side surface of the base body facing the connecting base piece is provided with a plurality of claw blocks which extend axially and then bend and extend.
Preferably, the positioning structures and the claw blocks are arranged on the side surface of the seat body facing to the connecting base piece along the circumferential direction at equal angular intervals.
In order to achieve the above object, the present invention further provides a propeller quick release device, including any one of the above propeller base assembly and a quick release propeller; the key stoppers correspond to the positioning structures in number and are respectively arranged at the corresponding positions of the fixed seat and the seat body; the key stop block is suitable for being embedded into the positioning structure at the first position and clamped between the fixed seat and the seat body.
Preferably, the first through hole on the fixed seat is axially aligned with the second through hole on the seat body; and the key body is suitable for axially moving in the second through hole.
Preferably, the claw block is rotatably inserted into the mounting groove, and in the locking position, the bent extension part of the claw block is positioned on the side of the limiting wall opposite to the seat body.
Preferably, the key switch and the reset piece are movably sleeved on a positioning shaft which axially protrudes from the rotating part, and the reset piece pushes the key switch to enable the key stop block to be correspondingly clamped in the positioning groove; fixing base fixed mounting is on the rotating part.
In order to achieve the above object, the present invention further provides an aircraft including a fuselage and a propeller quick release device as described in any one of the above.
The aircraft and the propeller quick-release device, the quick-release propeller and the propeller base assembly thereof provided by the invention have the following advantages:
1. according to the propeller base assembly provided by the invention, when the connected accessory is installed, the connected accessory is rotated to the first position, the key switch is in an external force-free state, and one part of the key stop block axially extends out of the fixed seat and blocks the connected accessory from rotating relative to the fixed seat, so that the axial fixation of the connected accessory is realized; when dismantling the annex, press key switch, the button dog is located the second position of retraction fixing base, and the button dog no longer blocks the relative fixing base rotation of annex connected this moment, and then can realize the rotatory dismantlement to the annex connected, because the flexible production through the button dog of the ascending constraint of annex in week, improved mechanical strength, brought the good effect of stability.
2. According to the propeller base assembly provided by the invention, the plurality of key stoppers are arranged on the outer circumferential surface of the key body in a radially outward protruding manner, the side wall of the first through hole of the fixing seat is formed with the through groove which is recessed radially outward, the key body is arranged in the first through hole in a sliding manner, and the key stoppers are arranged in the through groove in a sliding manner, so that when the key switch is arranged on the fixing seat, the key switch and the fixing seat are relatively fixed in the circumferential direction through the limit matching between the key stoppers and the through groove.
3. According to the propeller base assembly provided by the invention, the bottom of the outer surface of the key switch, which is positioned between the adjacent key stop blocks, is formed with the abutting part which protrudes outwards, the inner wall of the first through hole of the fixed seat is provided with the abutting wall which protrudes inwards corresponding to the abutting part, the abutting part abuts against the abutting wall in a state without external force, and then the key switch cannot be popped upwards from the fixed seat due to the elastic action of the reset piece through the matching between the abutting part and the abutting wall, so that the assembly stability and the realization of functions of the key switch are ensured.
4. According to the propeller base assembly provided by the invention, the side of the fixed seat facing the connecting accessory is provided with the plurality of mounting grooves which are uniformly distributed along the circumferential direction, the end, positioned in the locking rotation direction, of the inner wall or the outer wall of each mounting groove is provided with the limiting wall extending towards the mounting groove, and then the connecting accessory cannot move in the axial direction through the limiting action of the limiting wall, so that the connecting accessory and the fixed seat are fixed in the axial direction.
5. The quick-release propeller provided by the invention has the advantages that the clamping mechanism which is detachably connected through rotation is arranged between the base body and the base piece connected with the base body, the positioning structure is formed on one side of the base body facing to the base piece connected with the base body, the positioning structure is limited by the convex part on the base body facing to the base body on the base piece connected with the base body to prevent the base body from rotating relative to the base piece connected with the base body, so that when the quick-release propeller is disassembled and assembled through rotation, the clamping mechanism realizes the clamping function, meanwhile, the positioning structure realizes the circumferential rotation limiting function, the mechanical strength is improved while the convenience in disassembly and assembly of the quick-release propeller is ensured.
6. According to the quick-release propeller provided by the invention, the positioning structures and the claw blocks are arranged on the side surface of the base body facing the connecting base piece at equal angles along the circumferential direction, so that stress points of the quick-release propeller are uniformly distributed along the circumferential direction, the stress of the quick-release propeller is more stable, and the stability of the quick-release propeller in flight is improved.
7. The propeller quick-release device provided by the invention has the advantages as described in any one of the above items because the propeller quick-release device comprises the propeller base assembly and the quick-release propeller; meanwhile, the number of the key stop blocks corresponds to that of the positioning structures and are respectively arranged at the corresponding positions of the fixing seat and the seat body, and the key stop blocks are suitable for being embedded into the positioning structures at the first positions and clamped between the fixing seat and the seat body, so that the circumferential movement of the quick-release propeller is limited by the key stop blocks and the positioning structures and is different from the axial limiting stress of the quick-release propeller, the mechanical strength is further improved, and the effect of good stability is achieved.
8. The aircraft provided by the invention has the advantages of any one of the above advantages because the aircraft is provided with the propeller quick-release device, and the propeller quick-release device comprises the propeller base assembly and the quick-release propeller.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following further describes the invention in detail according to the embodiments of the present invention with reference to the accompanying drawings.
FIG. 1 is an exploded view of a prior art propeller quick release device for an aircraft;
FIG. 2 is a schematic view of an embodiment of a quick release device for a propeller according to the present invention;
FIG. 3 is an exploded view of the propeller quick release apparatus shown in FIG. 2;
FIG. 4 is an exploded view of the propeller quick release apparatus shown in FIG. 2 from another angle;
FIG. 5 is a schematic view of the propeller quick release apparatus shown in FIG. 2 with the propeller removed;
FIG. 6 is a schematic view of another embodiment of a fixing block of the propeller quick release apparatus shown in FIG. 2;
FIG. 7 is a longitudinal cross-sectional view of the propeller quick release apparatus shown in FIG. 2 with the blades removed.
The reference numerals in the figures are explained below:
1' -a propeller; 11' -a paddle; 12' -blade attachment; 121' -a second through hole;
122' -a first projection; 2' -a base; 21' -a first via hole; 211' -a notch portion;
22' -a limiting part; 3' -locking and buckling; 31' -a body; 32' -second projection;
4' -a drive means; 41' -rotating part; 5' -an elastic member; 1-a propeller;
100-a propeller base assembly; 1-a fixed seat; 11-a first via; 12-a through slot;
13-abutting the top wall; 14-a propping slot; 15-mounting grooves; 16-a limiting wall; 2-a key switch;
21-key body; 22-key stop; 23-a reset member; 24-a top abutment;
200-a drive device; 201-a rotating part; 202-positioning the shaft; 300-a quick release propeller;
301-base; 3011-positioning the slot; 3012-a second via; 3013-paw block; 302-a blade;
400-connecting piece.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "upper", "lower", "inside", "outside", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience in describing the present invention and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; may be directly connected or indirectly connected through an intermediate. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In addition, the technical features involved in the different embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
Example 1
One embodiment of the propeller quick release apparatus shown in fig. 2-4 includes a propeller base assembly 100 as a connection base member and a quick release propeller 300 as a connection attachment.
The quick-release propeller 300 comprises a base body 301 and at least two blades 302 which are circumferentially and uniformly distributed on the base body 301, wherein a positioning structure (not marked in the figure) is formed on one side of the base body 301 facing the propeller base assembly 100, and the positioning structure is limited by a protruding part on the propeller base assembly 100 facing the base body to block the base body 301 from rotating relative to the propeller base assembly 100;
the propeller base assembly 100 comprises a fixed seat 1 and a key switch 2, wherein the fixed seat 1 is fixedly connected to a rotating part 201 of the driving device 200, and a clamping mechanism (not shown in the figure) detachably connected through rotation is arranged between the fixed seat 1 and a base body 301; the key switch 2 is circumferentially fixed and axially slidably arranged on the fixed seat 1, and is provided with a key body 21 suitable for being pressed, a key stop 22 fixed on the key body 21, and a reset piece 23 for applying restoring force to the key body 21 when the key body 21 axially slides relative to the fixed seat 1 under the action of external force; when the key switch 2 is not pressed by external force, the key stop 22 is located at a first position where a part of the key stop axially extends out of the fixed seat 1 and stops the quick-release propeller 300 from rotating relative to the fixed seat 1; when the key switch 2 is pressed by an external force, the key stopper 22 is located at the second position of the retractable fixing base 1.
When the quick-release propeller 300 is mounted, the base body 11 of the quick-release propeller 300 is rotatably connected to the fixed base 2, the base body 11 is rotated to the first position, and a part of the key stop block 42, which is acted by the reset piece 23, axially extends out of the fixed base 1 and blocks the quick-release propeller 300 from rotating relative to the fixed base 1, so that the quick-release propeller 300 is axially fixed, and the quick mounting of the quick-release propeller 300 is realized; when the quick-release propeller 300 is disassembled, the key switch 4 is pressed downwards, the key stop block 22 is located at the second position retracted into the fixed seat 1, and at the moment, the key stop block 22 does not stop the quick-release propeller 300 from rotating relative to the fixed seat 1 any more, so that the quick-release propeller 300 rotates reversely from the fixed seat 1 and is screwed out, and the quick disassembly of the quick-release propeller 300 is realized; because the fast detachable propeller 300 is restrained in the circumferential direction by the stretching of the key stop block 22, the mechanical strength is further improved, and the effect of good stability is brought.
As an optional implementation manner, the positioning structures are a plurality of positioning grooves 3011 recessed inwards from one side of the base body 301 facing the fixing base 1; the key stoppers 22 correspond to the positioning slots 3011 in number and are respectively disposed at the corresponding positions of the fixing base 1 and the base 301; the key stopper 22 is suitable for being embedded into the positioning slot 3011 at the first position and clamped between the fixed base 1 and the base 301, and further the key stopper 22 of the key switch 2 is matched with the positioning slot 3011 of the base 301, so that the movement of the quick-release propeller 300 in the circumferential direction is limited by the key stopper 22 and the positioning slot 3011, and the limitation stress is different from that in the axial direction, thereby improving the mechanical strength.
Specifically, the key body 21 is cylindrical, and a plurality of key stoppers 22 are arranged on the outer circumferential surface of the key body 21 in a radially outward protruding manner; the fixed seat 1 and the seat body 301 are respectively provided with a first through hole 11 and a second through hole 3012 which are aligned axially along the axial direction; a through groove 12 which is recessed outwards in the radial direction is formed on the side wall of the first through hole 11; the key body 21 is at least slidably disposed in the first through hole 11 and adapted to axially move in the second through hole 3012, and the key stopper 22 is slidably disposed in the through groove 12, as shown in fig. 5, so that when the key switch 2 is disposed on the fixing base 1, the key switch 2 and the fixing base 1 are circumferentially fixed by the cooperation between the key stopper 22 and the through groove 12.
As shown in fig. 4, a top portion 24 protruding outward is formed at the bottom of the outer surface of the key switch 2 between the adjacent key stoppers 22, and the outer diameter of the top portion 24 is smaller than or equal to the outer diameter of the key stopper 22; the inner wall of the first through hole 11 of the fixing base 1 is provided with a supporting wall 13 protruding inwards corresponding to the supporting part 24, the key stopper 22 penetrates through the through groove 12 and is clamped in the positioning groove 3011, the supporting part 24 is accommodated in the first through hole 11 and correspondingly supports the supporting wall 13, the key switch 2 is limited to rotate in the fixing base 1, and then the key switch 2 cannot be upwards ejected from the fixing base 1 due to the elastic action of the resetting piece 23 through the matching between the supporting part 24 and the supporting wall 13, so that the assembly stability and the function of the key switch 2 are guaranteed.
As a modified embodiment, a top stop portion 24 protruding outwards is formed at the bottom of the outer surface of the key switch 2 between the adjacent key stop blocks 22, and the outer diameter of the top stop portion 24 is larger than that of the key stop blocks 22; the inner wall of the first through hole 11 is recessed outward corresponding to the abutting portion 24 to form a plurality of abutting grooves 14 penetrating through the fixing base 1 downward, as shown in fig. 6, the abutting portion 24 is correspondingly inserted into the abutting grooves 14, at this time, the groove wall of the abutting grooves 14 is an abutting wall 13, and the abutting portion 24 is accommodated in the first through hole 11 and correspondingly abuts against the abutting wall 13; while the first through hole 11 and the through groove 12 are formed as one through hole. In addition, the through groove 12 and the abutting groove 14 may be grooves formed on the wall of the first through hole 11 with different depths, which will not be described in detail herein.
In the process of driving the blade 302 to rotate, the driving device 200 is a rotating electrical machine (not shown in the figure), an output shaft of the rotating electrical machine is fixedly connected with the rotating portion 201, the fixing base 1 is fixedly mounted on the rotating portion 201 through the connecting piece 400, in the embodiment, the connecting piece 400 is a screw, and further, the rotation of the output shaft of the rotating electrical machine can be controlled, so as to drive the rotating portion 201 to rotate, so that the rotating portion 201 drives the fixing base 1 to rotate and drives the key switch 2 to rotate, thereby driving the quick-release propeller 300 to rotate coaxially.
As a modified embodiment, the driving device may be a mechanism having a rotation output power, such as a rotary cylinder, which is not illustrated here.
In addition, the rotating portion 201 is provided with a positioning shaft 202 projecting upward; the key switch 2 and the reset piece 23 are movably sleeved on the positioning shaft 202, and the reset piece 23 pushes the key switch 2 to enable the key stop 22 to be correspondingly clamped in the positioning slot 3011, so that the relative fixation of the base body 301 and the fixing base 1 in the rotating direction is ensured; simultaneously, again because fixing base 1 fixed mounting is on rotating part 201, and then make rotating part 201 drive fixing base 1 rotatory to it is rotatory to drive key switch 2, thereby drives the coaxial rotation of quick detach formula screw 300. In the present embodiment, the returning piece 23 is a spring.
In order to realize the detachable connection between the fixed seat 1 and the seat body 301 through rotation, the side surface of the seat body 301 facing the fixed seat 1 is provided with a plurality of claw blocks 3013 which extend axially and then bend and extend; the corresponding surface of the fixing base 1 is provided with a corresponding number of mounting grooves 15 corresponding to the claw block 3013, the inner wall of the mounting groove 15 is located in the locking rotation direction and protrudes and extends with a limiting wall 16 relative to the bending direction of the claw block 3013, the claw block 3013 is rotatably inserted into the mounting groove 15, and when in the locking position, the bending extension part of the claw block 3013 is located on the side of the limiting wall 16 opposite to the base 301, as shown in fig. 7, and further, the base 301 cannot move in the axial direction by the limiting function of the limiting wall 16 on the bending extension part of the claw block 3013, so that the quick-release propeller 300 and the fixing base 1 are fixed in the axial direction.
As an optional implementation manner, the number of the positioning slots 3011 and the claw blocks 3013 is 3, and the positioning slots 3011 and the claw blocks 3013 are arranged on the side of the base 301 facing the fixing base 1 at equal angular intervals along the circumferential direction, so that the stress points of the base 301 are uniformly distributed along the circumferential direction, and further the stress on the quick-release propeller 300 is more stable, thereby improving the stability of the quick-release propeller 300 in flight. Of course, the number of the positioning slots 3011 and the claw blocks 3013 may be other numbers, and may be specifically set according to the size of the contact surface between the seat body 301 and the fixed seat 1 and the requirement of mechanical strength.
Example 2
The present embodiment provides an aircraft (not shown) including a fuselage and a propeller quick release device as described in any one of embodiments 1.
The aircraft has the advantages of any embodiment 1 due to the adoption of the propeller quick-release device.
It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications therefrom are within the scope of the invention.
Claims (15)
1. A propeller base assembly (100) comprising:
the fixing seat (1) is fixedly connected to a rotating part (201) of the driving device (200) and is provided with a clamping mechanism which is detachably connected with a connected accessory through rotation;
the key switch (2) is circumferentially fixed and axially slidably arranged on the fixed seat (1), and is provided with a key body (21) suitable for being pressed and a key stop block (22) fixed on the key body (21), and a reset piece (23) for applying restoring force to the key body (21) when the key body (21) axially slides relative to the fixed seat (1) under the action of external force;
it is characterized in that the preparation method is characterized in that,
when the key switch (2) is in a state of not being pressed by external force, the key stop block (22) is positioned at a first position at which a part of the key stop block axially extends out of the fixed seat (1) and blocks a connected accessory from rotating relative to the fixed seat (1), and when the key switch (2) is in a state of being pressed by external force, the key stop block (22) is positioned at a second position retracted into the fixed seat (1); the key body (21) is cylindrical, and the plurality of key stoppers (22) are arranged on the outer circumferential surface of the key body (21) in a radially outward protruding manner; the fixed seat (1) is provided with a first through hole (11) along the axial direction; a through groove (12) which is recessed outwards in the radial direction is formed in the side wall of the first through hole (11); the key body (21) is arranged in the first through hole (11) in a sliding mode, and the key stopper (22) is arranged in the through groove (12) in a sliding mode.
2. The propeller base assembly (100) according to claim 1, wherein the bottom of the outer surface of the key switch (2) between the adjacent key stoppers (22) is formed with an outward projecting abutting portion (24); the inner wall of the first through hole (11) of the fixing seat (1) is provided with an inward-protruding abutting wall (13) corresponding to the abutting part (24), and the abutting part (24) abuts against the abutting wall (13) in an external force-free state.
3. The propeller mount assembly (100) of claim 2 wherein the outer diameter of the stop portion (24) is less than or equal to the outer diameter of the key stop (22); the abutting part (24) is accommodated in the first through hole (11).
4. The propeller mount assembly (100) of claim 2 wherein the outer diameter of the stop portion (24) is greater than the outer diameter of the key stop (22); the inner wall of the first through hole (11) is outwards recessed corresponding to the abutting portion (24) to form a plurality of abutting grooves (14) which downwards penetrate through the fixing seat (1), the abutting portion (24) is correspondingly inserted into the abutting grooves (14), and the wall of each abutting groove (14) is the abutting wall (13).
5. The propeller base assembly (100) according to any one of claims 1-4, wherein the return member (23) is a spring.
6. The propeller base assembly (100) according to any one of claims 1 to 4, wherein the side of the fixing base (1) facing the attachment is provided with a plurality of mounting grooves (15) uniformly distributed along the circumferential direction, and one end of the inner wall or the outer wall of the mounting groove (15) in the locking rotation direction is formed with a limiting wall (16) extending towards the mounting groove (15).
7. A fast dismounting propeller (300) comprising:
the base body (301) is provided with a clamping mechanism which is detachably connected with the connected base piece through rotation; and
the at least two blades (302) are uniformly distributed on the base body (301) in the circumferential direction;
it is characterized in that the preparation method is characterized in that,
one side of the base body (301) facing to the connecting base piece is formed with a positioning structure, and the positioning structure is limited by a protruding part facing to the base body (301) on the connecting base piece to block the rotation of the base body (301) relative to the connecting base piece; the positioning structures are a plurality of positioning grooves (3011) which are recessed inwards from the base body (301) towards one side of the connected base piece.
8. The fast-dismounting propeller (300) according to claim 7, wherein the base body (301) is axially provided with a second through hole (3012).
9. The fast dismounting propeller (300) according to any one of claims 7-8, wherein the side of the base body (301) facing the connecting base member is provided with a plurality of claw blocks (3013) which are axially extended and then bent.
10. The fast dismounting propeller (300) according to claim 9, wherein the positioning structures and the claw blocks (3013) are arranged circumferentially at equal angular intervals on the side of the base body (301) facing the connecting base member.
11. A propeller quick detach device characterized in that includes: the propeller base assembly (100) of any one of claims 1 to 6, and the fast release propeller (300) of claims 7 to 10 corresponding to any one of claims 1 to 6;
the key stoppers (22) correspond to the positioning structures in number and are respectively arranged at the corresponding positions of the fixed seat (1) and the seat body (301) which are matched with each other; the key stopper (22) is suitable for being embedded into the positioning structure at the first position and clamped between the fixed seat (1) and the seat body (301).
12. The propeller quick release device according to claim 11, wherein the first through hole (11) in the fixing base (1) is axially aligned with the second through hole (3012) in the holder body (301); and the key body (21) is suitable for axially moving in the second through hole (3012).
13. The propeller quick release device according to claim 11 or 12, wherein the claw block (3013) is rotatably inserted into the mounting groove (15), and when in the locked position, the bent extension portion of the claw block (3013) is located on the side of the limiting wall (16) opposite to the seat body (301).
14. The propeller quick release device according to any one of claims 11 to 13, wherein the push button switch (2) and the reset member (23) are movably sleeved on a positioning shaft (202) axially protruding on the rotating part (201), and the reset member (23) pushes the push button switch (2) to enable the push button stop (22) to be correspondingly clamped in the positioning groove (3011); fixing base (1) fixed mounting be in on rotating part (201).
15. An aircraft comprising a fuselage and a propeller quick release arrangement as claimed in any one of claims 11 to 14.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611157265.8A CN106628165B (en) | 2016-12-14 | 2016-12-14 | Aircraft and screw quick detach device, quick detach formula screw and screw base subassembly thereof |
| PCT/CN2017/113153 WO2018107956A1 (en) | 2016-12-14 | 2017-11-27 | Unmanned aerial vehicle and power assembly thereof, propeller and propeller base assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611157265.8A CN106628165B (en) | 2016-12-14 | 2016-12-14 | Aircraft and screw quick detach device, quick detach formula screw and screw base subassembly thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106628165A CN106628165A (en) | 2017-05-10 |
| CN106628165B true CN106628165B (en) | 2020-03-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611157265.8A Active CN106628165B (en) | 2016-12-14 | 2016-12-14 | Aircraft and screw quick detach device, quick detach formula screw and screw base subassembly thereof |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN106628165B (en) |
| WO (1) | WO2018107956A1 (en) |
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| CN106628165B (en) * | 2016-12-14 | 2020-03-10 | 深圳市道通智能航空技术有限公司 | Aircraft and screw quick detach device, quick detach formula screw and screw base subassembly thereof |
| CN107352027A (en) * | 2017-07-25 | 2017-11-17 | 成都天麒科技有限公司 | A kind of unmanned plane blade attachment structure |
| KR102410204B1 (en) * | 2017-07-28 | 2022-06-20 | 삼성전자주식회사 | Unmanned aerial vehicle |
| KR102345523B1 (en) * | 2017-08-03 | 2021-12-30 | 삼성전자주식회사 | Propulsion system comprising detachable propellar and unmanned aerial vehicle comprising the same |
| KR102344918B1 (en) * | 2017-08-03 | 2021-12-30 | 삼성전자주식회사 | Unmanned aerial vehicle including mounting structure for propeller |
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| CN109018308B (en) * | 2018-08-09 | 2021-09-21 | 上海歌尔泰克机器人有限公司 | Screw quick detach device and have its unmanned aerial vehicle |
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Also Published As
| Publication number | Publication date |
|---|---|
| CN106628165A (en) | 2017-05-10 |
| WO2018107956A1 (en) | 2018-06-21 |
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Address after: 518055 Shenzhen, Guangdong, Nanshan District Xili street, No. 1001, Zhiyuan Road, B1 9. Patentee after: Shenzhen daotong intelligent Aviation Technology Co.,Ltd. Address before: 518055 Shenzhen, Guangdong, Nanshan District Xili street, No. 1001, Zhiyuan Road, B1 9. Patentee before: AUTEL ROBOTICS Co.,Ltd. |
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