CN110626502B - A quick-detachable structure and aircraft - Google Patents
A quick-detachable structure and aircraft Download PDFInfo
- Publication number
- CN110626502B CN110626502B CN201911033355.XA CN201911033355A CN110626502B CN 110626502 B CN110626502 B CN 110626502B CN 201911033355 A CN201911033355 A CN 201911033355A CN 110626502 B CN110626502 B CN 110626502B
- Authority
- CN
- China
- Prior art keywords
- lock
- piece
- lock cylinder
- release structure
- slide
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 230000007246 mechanism Effects 0.000 claims abstract description 47
- 238000003780 insertion Methods 0.000 claims abstract description 15
- 230000037431 insertion Effects 0.000 claims abstract description 15
- 230000002093 peripheral effect Effects 0.000 claims description 3
- 230000001681 protective effect Effects 0.000 abstract description 29
- 238000009434 installation Methods 0.000 abstract description 3
- 238000005452 bending Methods 0.000 description 6
- 238000004891 communication Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 241000251468 Actinopterygii Species 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000013013 elastic material Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000003756 stirring Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/006—Safety devices
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Snaps, Bayonet Connections, Set Pins, And Snap Rings (AREA)
Abstract
本发明涉及飞行器技术领域，具体公开了一种快拆结构及飞行器。快拆结构包括第一件；第二件，所述第一件和所述第二件中的一个上设置有凸块，另一个上设置有插槽，所述凸块沿第一方向插接于或脱离所述插槽，使所述第一件和所述第二件安装或拆卸；锁机构，设置于所述第二件上，能够选择性地沿插入方向插入所述第一件，且所述插入方向与所述第一方向呈夹角设置。通过将锁机构插入到螺旋桨内，以及沿第一方向将螺旋桨凸块插入到凹槽内，从而限制保护罩与螺旋桨沿六个方向上的相对运动，实现了保护罩的快速安装。当需要拆卸保护罩时，使锁机构脱离螺旋桨，沿与第一方向相反的方向使凸块脱离凹槽，实现保护罩的快速拆卸。
The present invention relates to the field of aircraft technology, and specifically discloses a quick-release structure and an aircraft. The quick-release structure includes a first piece; a second piece, one of the first piece and the second piece is provided with a protrusion, and the other is provided with a slot, the protrusion is inserted into or disengaged from the slot along a first direction, so that the first piece and the second piece are installed or removed; a locking mechanism is provided on the second piece, and can selectively insert the first piece along an insertion direction, and the insertion direction is set at an angle to the first direction. By inserting the locking mechanism into the propeller, and inserting the propeller protrusion into the groove along the first direction, the relative movement of the protective cover and the propeller in six directions is limited, thereby realizing the rapid installation of the protective cover. When it is necessary to remove the protective cover, the locking mechanism is disengaged from the propeller, and the protrusion is disengaged from the groove in a direction opposite to the first direction, so as to realize the rapid removal of the protective cover.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a quick-dismantling structure and an aircraft.
Background
Unmanned aerial vehicles are unmanned vehicles that are manipulated by a radio remote control or remote control to perform tasks.
Unmanned aerial vehicle generally includes the fuselage and from the horn that the fuselage stretched is provided with the screw on each horn, and the rotation of screw drives unmanned aerial vehicle flies. But sometimes because control the mistake or unmanned aerial vehicle is out of control, can collide with the hard thing and lead to the screw to damage when the screw is rotatory, perhaps screw fish tail people or thing, consequently be connected with the safety cover on the screw, avoid the screw to contact other objects.
The existing connection structure of the protection cover and the propeller is complex to assemble and disassemble, and is not easy to assemble and disassemble rapidly.
Disclosure of Invention
An object of the present invention is to provide a quick-dismantling structure, so that the connection structure is easy to disassemble and the quick-dismantling is realized.
To achieve the purpose, the invention adopts the following technical scheme:
a quick release structure comprising:
A first member;
The second piece, one of the said first piece and said second piece has projections, there are slots on another one, the said projections are inserted into or break away from the said slot along the first direction, make the said first piece and said second piece mount or dismount;
The lock mechanism is arranged on the second piece, can be selectively inserted into the first piece along the inserting direction, and is arranged at an included angle with the first direction in the inserting direction.
Preferably, the first member includes a first arc portion, the second member includes a second arc portion, the second arc portion is capable of being fastened to an outer peripheral surface of the first arc portion, one of the first arc portion and the second arc portion is provided with the bump, and the other is provided with the slot.
Preferably, one of the first arc portion and the second arc portion is provided with the projection and an annular groove located at the outer periphery of the projection, and the other is provided with the slot and an annular protrusion located at the outer periphery of the slot, and the annular protrusion can be inserted into or separated from the annular groove.
Preferably, the quick release structure comprises two lock mechanisms, the insertion directions of the two lock mechanisms are arranged at an included angle, and the slot or the lug is positioned between the two lock mechanisms.
Preferably, the second member further includes a connecting arm, one end of the connecting arm is connected to the second circular arc portion, and the lock mechanism is disposed on the connecting arm.
Preferably, the lock mechanism includes:
the fixing frame is fixed on the connecting arm and provided with a slideway;
The toggle key is arranged in the slideway in a sliding way;
the lock cylinder is connected with the poking key, and the poking key is configured to slide in the slideway so that the lock cylinder is switched between a locking position for locking the first piece and the second piece and an unlocking position for unlocking the first piece and the second piece.
Preferably, the lock mechanism further comprises:
And one end of the elastic piece is fixedly connected with the fixing frame or the connecting arm, and the other end of the elastic piece is fixedly connected with the lock cylinder so that the lock cylinder is kept at the locking position.
Preferably, the slide is L-shaped, including being angle setting and the first horizontal slide and the first slide of indulging of intercommunication each other, the length direction of first vertical slide with insert the direction unanimity, first horizontal slide is located first vertical slide is kept away from the one end of second circular arc portion.
Preferably, a limit bump is arranged at the joint of the first transverse slideway and the first longitudinal slideway.
Preferably, a lock plate is arranged at the end part of the lock cylinder, the lock plate is in a first state to be inserted into or separated from the first piece when the lock cylinder is in the unlocking position, and is in a second state to be abutted with the inner wall of the first piece when the lock cylinder is in the locking position.
Preferably, the slide is L-shaped, including being the angle setting and the second horizontal slide and the second vertical slide of intercommunication each other, the second horizontal slide is located the second vertical slide is close to the one end of second circular arc portion, stir the key and be in slide in the second horizontal slide, can make the lock core rotates around self axis.
Preferably, at least one end of the second circular arc portion is bent upward or downward along the axial direction thereof to form a bent portion, the lock mechanism includes a snap protrusion provided on the inner side of the bent portion, a bayonet is provided on the first circular arc portion, and the bent portion is configured to be deformable in a direction opposite to the bending direction thereof to snap-fit the snap protrusion with the bayonet.
Another object of the present invention is to provide an aircraft, so as to improve the efficiency of assembling and disassembling the propeller and the protective cover.
To achieve the purpose, the invention adopts the following technical scheme:
An aircraft comprises the quick release structure.
The invention has the beneficial effects that:
The lug is inserted into the slot and can limit the relative movement of the propeller and the protective cover along the direction perpendicular to the first direction. Since the insertion direction of the lock mechanism is arranged at an angle to the first direction, the movement of the protective cover in the first direction can be restricted after the lock mechanism is inserted into the propeller. By inserting the lock mechanism into the propeller and inserting the propeller projection into the groove in the first direction, thereby restricting the relative movement of the protective cover and the propeller in six directions, i.e. fixing the protective cover to the propeller, a quick installation of the protective cover is achieved. When the protective cover needs to be detached, the lock mechanism is separated from the propeller, and the convex blocks are separated from the grooves along the direction opposite to the first direction, so that the protective cover is quickly detached. The quick-dismantling structure provided by the invention is simple and quick to assemble and disassemble.
Drawings
FIG. 1 is a schematic view of a propeller and a protective cover according to a first embodiment of the present invention;
FIG. 2 is a schematic view of a propeller and a protective cover according to a first embodiment of the present invention;
FIG. 3 is a schematic view of a propeller and a protective cover according to an embodiment of the present invention after being mounted;
FIG. 4 is a cross-sectional view taken along the direction A-A in FIG. 3;
FIG. 5 is a schematic view of the structure at A in FIG. 4;
FIG. 6 is a cross-sectional view in the B-B direction of FIG. 3 when the lock mechanism is locking the propeller;
FIG. 7 is a cross-sectional view in the B-B direction of FIG. 3 when the lock mechanism unlocks the propeller;
FIG. 8 is an exploded view of a lock mechanism and a protective cover according to a first embodiment of the present invention;
Fig. 9 is a schematic structural view of a lock mechanism according to a second embodiment of the present invention when unlocking a propeller;
fig. 10 is a schematic view of a lock mechanism according to a second embodiment of the present invention when a propeller is locked;
fig. 11 is a schematic structural view of a lock mechanism according to a third embodiment of the present invention.
In the figure:
1. screw propeller 11, motor 12, rotating shaft 13, blade 14, horn 15, first arc part 151, protruding block 152, annular groove 153, lock hole 154, bayonet;
2. The protective cover comprises a protective cover body, a connecting arm, a protective rod, a second arc part, a 231, a slot, a 232, an annular bulge, a 233 and a bending part, wherein the protective cover body comprises a connecting arm, a protective rod and a second arc part;
3. The lock comprises a lock mechanism, 31, a fixing frame, 32, a toggle key, 33, a lock cylinder, 331, a groove, 332, a lock plate, 34, an elastic piece, 35, a slideway, 351, a first transverse slideway, 352, a first longitudinal slideway, 36, a first connecting piece, 37, a second connecting piece, 38 and a clamping protrusion.
Detailed Description
The technical scheme of the invention is further described below by the specific embodiments with reference to the accompanying drawings. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting thereof. It should be further noted that, for convenience of description, only some, but not all of the drawings related to the present invention are shown.
In the present invention, some azimuth words are defined, and unless otherwise indicated, azimuth words such as "upper", "lower", "left" and "right" are defined in the case that the quick release structure provided by the present invention is being used for a long time, and "inner" and "outer" are defined with respect to the inner and outer sides of the outline of each part. These directional terms are used for ease of understanding and thus do not limit the scope of the invention.
In the present invention, unless expressly stated or limited otherwise, a first feature "above" or "below" a second feature may include both the first and second features being in direct contact, as well as the first and second features not being in direct contact but being in contact with each other through additional features therebetween. Moreover, a first feature being "above," "over" and "on" a second feature includes the first feature being directly above and obliquely above the second feature, or simply indicating that the first feature is higher in level than the second feature. The first feature being "under", "below" and "beneath" the second feature includes the first feature being directly under and obliquely below the second feature, or simply means that the first feature is less level than the second feature.
In the description of the present invention, unless explicitly stated or limited otherwise, the terms "connected," "connected," and "fixed" are to be construed broadly, and may, for example, be fixedly connected, detachably connected, or integrally formed, mechanically connected, electrically connected, directly connected, indirectly connected through an intervening medium, or in communication between two elements or in an interaction relationship between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
Example 1
The embodiment provides a quick-dismantling structure, which is used in connection between a propeller 1 and a protective cover 2 of an unmanned aerial vehicle, but is not limited to the connection, and can be also used in other devices, so that the disassembly and assembly processes of two parts are simplified, and quick disassembly and assembly are realized.
As shown in fig. 1and 2, the quick release structure provided in this embodiment includes a first member, a second member, and a lock structure. In the present embodiment, a first member is taken as a propeller 1, and a second member is taken as a shield 2. Of course, when the first member and the second member are other members, the quick release structure is also within the scope of the present invention.
The screw propeller 1 is provided with a bump 151, the protecting cover 2 is provided with a slot 231, and the bump 151 is inserted into or separated from the slot 231 along a first direction (L direction shown by an arrow in fig. 2), so that the screw propeller 1 and the protecting cover 2 are installed or detached along the first direction (L direction shown by the arrow in fig. 2). The protrusion 151 is inserted into the slot 231 to limit the relative movement of the propeller 1 and the protective cover 2 in the direction perpendicular to the first direction, that is, the slot 231 and the insert block can limit the relative movement of the propeller 1 and the protective cover 2 in the up-down direction and the front-back direction (the direction perpendicular to the paper surface).
The lock mechanism 3 is provided on the protection cover 2, the propeller 1 can be selectively inserted, and the insertion direction of the lock mechanism 3 into the propeller 1 is set at an angle to the first direction. Since the insertion direction of the lock mechanism 3 is disposed at an angle to the first direction, the movement of the shield case 2 in the first direction can be restricted after the lock mechanism 3 is inserted into the propeller 1. By inserting the lock mechanism 3 into the propeller 1 and inserting the projection 151 of the propeller 1 into the recess 331 in the first direction, the relative movement of the shield 2 and the propeller 1 in six directions is restricted, i.e. the shield 2 is fixed to the propeller 1, a quick installation of the shield 2 is achieved. When the protective cover 2 needs to be detached, the lock mechanism 3 is separated from the propeller 1, and the projection 151 is separated from the groove 331 along the direction opposite to the first direction, so that the protective cover 2 is quickly detached. The quick-dismantling structure provided by the embodiment is simple and quick to assemble and disassemble.
Further, the propeller 1 includes a motor 11, a rotation shaft 12, a blade 13, and a horn 14. Wherein, motor 11 is connected with pivot 12 drive, paddle 13 fixed connection is on pivot 12, and link arm 21 is connected on pivot 12 through parts such as bearing rotation. The horn 14 comprises a horn body and a first arc part 15, the first arc part 15 is connected with one end of the horn body and is enclosed to form a round hole, and the bearing penetrates through the round hole, so that the horn 14 is connected with the bearing.
The protection cover 2 includes a connection arm 21, an arc-shaped protection rod 22, and a second arc portion 23. The connecting arms 21 are connected to both ends of the protection rod 22, and one end of the connecting arms 21, which is not connected to the protection rod 22, is connected to the outer side of the second circular arc portion 23. The second circular arc portion 23 can be engaged with the outer peripheral surface of the first circular arc portion 15, wherein the bump 151 is disposed on the first circular arc portion 15, and the slot 231 is disposed on the second circular arc portion 23.
As shown in fig. 2 to 5, in the present embodiment, the outer circumference of the protruding block 151 is provided with an annular groove 152, the outer circumference of the insertion slot 231 is provided with an annular protrusion 232, and the annular protrusion 232 can be inserted into or separated from the annular groove 152. The annular protrusion 232 and the annular groove 152 form a second mating barrier, which further limits movement of the boot 2 and the propeller 1 in a direction perpendicular to the first direction.
Of course, in other embodiments, the propeller 1 may be provided with a slot 231, and the protecting cover 2 may be provided with a bump 151. That is, the bump 151 is provided on the second circular arc portion 23, and the slot 231 is provided on the first circular arc portion 15. The slot wall of the slot 231 extends to the side of the second arc part 23 to form an annular protrusion 232, the protruding block 151 is arranged on the second arc part 23, and the second arc part 23 is provided with an annular groove 152 matched with the annular protrusion 232.
Preferably, the locking means 3 are provided on the connecting arms 21, wherein the locking means 3 may be provided on only one of the connecting arms 21 or one locking means 3 may be provided on both connecting arms 21.
In this embodiment, one lock mechanism 3 is provided on each of the two connecting arms 21, and the slot 231 is located between the two lock mechanisms 3. The inserting direction of the two lock mechanisms 3 is arranged at an included angle, and the inserting direction of the two lock mechanisms 3 is arranged at an included angle in the first direction, so that the screw propeller 1 and the protective cover 2 are prevented from being separated along the first direction after the screw propeller 1 and the protective cover 2 are fixed.
The two lock mechanisms 3 can make the distance between the second circular arc part 23 and the first circular arc part 15 consistent, and avoid the downward inclination of the end part of the second circular arc part 23.
As shown in fig. 6 to 8, further, the lock mechanism 3 includes a fixing frame 31, a toggle key 32, a lock cylinder 33, and an elastic member 34. The fixing frame 31 is fixed on the connecting arm 21 through a first connecting piece 36, and a slide way 35 is arranged on the fixing frame 31. The toggle key 32 is configured to slide on a slide 35 to switch the lock cylinder 33 between a locked position for locking the propeller 1 and the boot 2 and an unlocked position for unlocking the propeller 1 and the boot 2. Specifically, the elastic member 34 may be a spring or a shrapnel, and in this embodiment, the elastic member 34 is a spring.
The lock cylinder 33 is connected to the toggle key 32 by a second connector 37. The first and second connectors 36, 37 may be screws, or other connectors. Preferably, the connecting arm 21 has a hollow structure, and the lock cylinder 33 is located in the connecting arm 21 and is capable of reciprocating relative to the connecting arm 21 in a longitudinal direction of the lock cylinder 33, wherein the longitudinal direction of the lock cylinder 33 coincides with an insertion direction of the lock mechanism 3. In order to insert the lock cylinder 33 into the propeller 1, the first arcuate portion 15 is provided with a lock hole 153 through which the lock cylinder 33 can pass, and the second arcuate portion 23 is also provided with a keyhole through which the lock cylinder 33 can pass. The toggle key 32 slides in the slide way 35 to enable the lock cylinder 33 to penetrate into the lock hole 153, the lock cylinder 33 is in a locking position for locking the propeller 1, and the lock cylinder 33 is separated from the lock hole 153, and the lock cylinder 33 is in an unlocking position for unlocking the propeller 1.
In this embodiment, to effect the transition of lock cylinder 33 between the locked and unlocked positions, slide 35 includes a first transverse slide 351 and a first longitudinal slide 352 disposed at an angle and in communication with each other. Preferably, the slide 35 has an L-shaped structure, the length direction of the first longitudinal slide 352 coincides with the insertion direction of the lock mechanism 3, and the first transverse slide 351 is located at one end of the first longitudinal slide 352 away from the second circular arc portion 23. A limit bump is provided at the junction of the first transverse slide 351 and the first longitudinal slide 352 to limit the sliding of the toggle key 32 from the first transverse slide 351 to the first longitudinal slide 352.
One end of the elastic member 34 is fixedly connected with the fixing frame 31 or the connecting arm 21, and the other end is fixedly connected with the lock cylinder 33. So that the elastic force of the elastic member 34 acts on the lock cylinder 33 to maintain the lock cylinder 33 in the locking position, and in this embodiment, a groove 331 is provided at the rear end of the lock cylinder 33, and the elastic member 34 is connected to the lock cylinder 33 through the groove 331.
When the toggle key 32 is located on the first longitudinal slide way 352, the elastic member 34 is in a compressed state, and the lock core 33 is subjected to the elastic force towards the second circular arc portion 23, so that the elastic member 34 can make the lock core 33 always be in the locking position for locking the propeller 1. When the toggle key 32 moves from the first longitudinal slide way 352 to the end of the first transverse slide way 351, the lock cylinder 33 is separated from the lock hole 153, and the lock cylinder 33 is in the unlocking position for unlocking the propeller 1. The lock core 33 can be rotationally connected with the fixing frame 31 or the connecting arm 21, the toggle key 32 moves along the first transverse slideway 351, the lock core 33 rotates around the axis of the lock core 33, and the toggle key 32 is abutted to the side wall or the limit protruding block of the first transverse slideway 351, so that the toggle key 32 can be limited to move in the slideway 35, namely, the lock core 33 is ensured to be always in the unlocking position of the unlocking propeller 1. Or the lock core 33 can be in sliding connection with the fixing frame 31 or the connecting arm 21, the toggle key 32 moves along the first transverse slideway 351, the movement track of the lock core 33 is the same as that of the toggle key 32, and the toggle key 32 is abutted to the side wall of the first transverse slideway 351 or the limit lug, so that the movement of the toggle key 32 and the lock core 33 can be limited.
The embodiment also provides an aircraft, which may be an unmanned aerial vehicle. The aircraft comprises the quick-dismantling structure, so that the propeller 1 and the protective cover 2 are quickly assembled and disassembled.
Example two
As shown in fig. 9 and 10, the quick release structure of the second embodiment is substantially the same as that of the first embodiment, and differs from the first embodiment in that the specific structures of the lock mechanism 3 and the slide 35 are different.
The lock mechanism 3 includes a mount 31, a toggle key 32, and a lock cylinder 33. The lock cylinder 33 is provided with a lock plate 332 at an end portion thereof, and preferably, the lock plate 332 has a rectangular parallelepiped structure, and the lock hole 153 provided in the first arc portion 15 is a waist-shaped hole, and the lock cylinder 33 reciprocates along a length direction thereof, so that the lock plate 332 can be inserted into the lock hole 153 or separated from the lock hole 153.
As shown in fig. 9, during insertion or removal of the lock plate 332 from the lock plate 332, the lock cylinder 33 is in an unlock position for unlocking the propeller 1, the lock plate 332 is in the first state, and the lock plate 332 is able to pass through the lock hole 153. As shown in fig. 10, after the lock plate 332 is inserted into the lock hole 153, the lock cylinder 33 can be rotated by 90 °, the lock cylinder 33 is in the locked position for locking the propeller 1, the lock plate 332 is in the second state, the length of the lock plate 332 is greater than the width of the lock hole 153, and the lock plate 332 abuts against the inner wall of the propeller 1, thereby restricting the lock plate 332 from being separated from the lock hole 153.
Further, in order to realize the conversion of the lock cylinder 33 between the locking position and the unlocking position, the slide 35 includes a second transverse slide and a second longitudinal slide which are disposed at an angle, preferably, the second transverse slide and the second longitudinal slide are L-shaped, and the second transverse slide is located at an end of the second longitudinal slide, which is close to the second circular arc portion 23, and the toggle key 32 slides in the second transverse slide, so that the lock cylinder 33 can rotate around its own axis. In order to enable the lock cylinder 33 to rotate 90 °, the second cross slide is preferably of circular arc configuration with a circular arc angle of 90 °.
When the toggle key 32 is located on the second longitudinal slide, the lock cylinder 33 is located at an unlocking position for unlocking the propeller 1, and the lock plate 332 is located at the first state (as shown in fig. 9). When the toggle key 32 slides from the second longitudinal slide to the second transverse slide, the lock plate 332 of the lock cylinder 33 is inserted into the first circular arc portion 15 through the lock hole 153. The toggle key 32 is located on the second transverse slideway and slides along the second transverse slideway in a direction away from the second longitudinal slideway, so that the lock cylinder 33 rotates by 90 °, the lock plate 332 is in the second state (as shown in fig. 10), and the lock cylinder 33 is in the locking position of the locking protection cover 2.
Example III
As shown in fig. 11, the quick release structure of this third embodiment is substantially the same as that of the first embodiment described above, and differs therefrom in that the specific structure of the lock mechanism 3 is different.
At least one end of the second circular arc portion 23 is bent upward or downward along its axis to form a bent portion 233 (as shown by a broken line in fig. 11), the lock mechanism 3 includes a click protrusion 38, the click protrusion 38 is disposed inside the bent portion 233, the first circular arc portion 15 is provided with a bayonet 154, and the bent portion 233 is configured to be deformable in a direction opposite to its bending direction to cause the click protrusion 38 to be click-fitted with the bayonet 154. After the clamping protrusion 38 is inserted into the buckle, the bending portion 233 applies pressure to the first circular arc portion 15, so that friction force between the clamping protrusion 38 and the side wall of the clamping opening 154 is improved, connection strength between the clamping opening 154 and the clamping protrusion 38 is improved, and the propeller 1 and the protection cover 2 are locked. In order to allow the bending portion 233 to be deformed in a direction opposite to the bending direction thereof, the second circular arc portion 23 is made of an elastic material.
It is to be understood that the above examples of the present invention are provided for clarity of illustration only and are not limiting of the embodiments of the present invention. Other variations or modifications of the above teachings will be apparent to those of ordinary skill in the art. It is not necessary here nor is it exhaustive of all embodiments. Any modification, equivalent replacement, improvement, etc. which come within the spirit and principles of the invention are desired to be protected by the following claims.
Claims (10)
1. A quick release structure, comprising:
A first member;
A second member, wherein one of the first member and the second member is provided with a protruding block (151), the other is provided with a slot (231), and the protruding block (151) is inserted into or separated from the slot (231) along a first direction so as to enable the first member and the second member to be mounted or dismounted;
a lock mechanism (3) arranged on the second piece, capable of selectively inserting the first piece along an insertion direction, and arranged at an included angle with the first direction;
The first piece comprises a first circular arc part (15), the second piece comprises a second circular arc part (23), the second piece further comprises a connecting arm (21), one end of the connecting arm (21) is connected to the second circular arc part (23), and the lock mechanism (3) is arranged on the connecting arm (21);
the lock mechanism (3) comprises:
the fixing frame (31) is fixed on the connecting arm (21), and a slide way (35) is arranged on the fixing frame (31);
The toggle key (32) is arranged in the slideway (35) in a sliding way;
A lock cylinder (33) connected to the toggle key (32), the toggle key (32) being configured to be slidable within the slide (35) to switch the lock cylinder (33) between a locking position locking the first and second members and an unlocking position unlocking the first and second members.
2. The quick-release structure according to claim 1, wherein the fixing frame is fixed on the connecting arm through a first connecting piece, the lock cylinder is connected with the toggle key through a second connecting piece, the first connecting piece and the second connecting piece are screws, the second arc portion (23) can be buckled on the outer peripheral surface of the first arc portion (15), one of the first arc portion (15) and the second arc portion (23) is provided with the protruding block (151), and the other is provided with the slot (231).
3. The quick release structure according to claim 2, wherein one of the first arc portion (15) and the second arc portion (23) is provided with the projection (151) and an annular groove (152) located at the outer periphery of the projection (151), and the other is provided with the insertion groove (231) and an annular protrusion (232) located at the outer periphery of the insertion groove (231), and the annular protrusion (232) can be inserted into or separated from the annular groove (152).
4. The quick release structure according to claim 1, characterized in that it comprises two lock mechanisms (3), and in that the insertion direction of the two lock mechanisms (3) is arranged at an angle, and the slot (231) or the projection (151) is located between the two lock mechanisms (3).
5. The quick release structure according to claim 1, characterized in that the lock mechanism (3) further comprises:
and one end of the elastic piece (34) is fixedly connected with the fixing frame (31) or the connecting arm (21), and the other end of the elastic piece is fixedly connected with the lock cylinder (33), so that the lock cylinder (33) is kept at the locking position.
6. The quick release structure according to claim 1 or 5, wherein the slide (35) is an L-shaped structure, and comprises a first transverse slide (351) and a first longitudinal slide (352) which are arranged at an angle and are mutually communicated, the length direction of the first longitudinal slide (352) is consistent with the insertion direction, and the first transverse slide (351) is positioned at one end of the first longitudinal slide (352) away from the second circular arc part (23).
7. The quick release structure of claim 6, wherein a limit bump is provided at a junction of the first transverse slideway (351) and the first longitudinal slideway (352).
8. The quick release structure according to claim 1, characterized in that the lock cylinder (33) is provided with a lock plate (332) at an end portion thereof, the lock plate (332) being in a first state to be inserted into or removed from the first member when the lock cylinder (33) is in the unlocked position, and the lock plate (332) being in a second state to be abutted against an inner wall of the first member when the lock cylinder (33) is in the locked position.
9. The quick release structure according to claim 8, wherein the slide way (35) is an L-shaped structure, and comprises a second transverse slide way and a second longitudinal slide way which are arranged at an angle and are mutually communicated, the second transverse slide way is positioned at one end of the second longitudinal slide way, which is close to the second circular arc part (23), and the toggle key (32) slides in the second transverse slide way, so that the lock cylinder (33) can rotate around the axis of the lock cylinder.
10. An aircraft comprising a quick release structure according to any one of claims 1 to 9.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911033355.XA CN110626502B (en) | 2019-10-28 | 2019-10-28 | A quick-detachable structure and aircraft |
| PCT/CN2020/124056 WO2021083152A1 (en) | 2019-10-28 | 2020-10-27 | Quick-release structure and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911033355.XA CN110626502B (en) | 2019-10-28 | 2019-10-28 | A quick-detachable structure and aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110626502A CN110626502A (en) | 2019-12-31 |
| CN110626502B true CN110626502B (en) | 2025-01-24 |
Family
ID=68977945
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911033355.XA Active CN110626502B (en) | 2019-10-28 | 2019-10-28 | A quick-detachable structure and aircraft |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN110626502B (en) |
| WO (1) | WO2021083152A1 (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110626502B (en) * | 2019-10-28 | 2025-01-24 | 深圳市道通智能航空技术股份有限公司 | A quick-detachable structure and aircraft |
| CN113844646B (en) * | 2021-10-13 | 2023-12-29 | 云南交通运输职业学院(云南交通技师学院、云南省交通高级技工学校) | Damage-preventing unmanned aerial vehicle for training |
| CN116853565A (en) * | 2023-05-31 | 2023-10-10 | 北京机械设备研究所 | Selector locking mechanism suitable for unmanned aerial vehicle catapult and use method thereof |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN206617458U (en) * | 2017-03-09 | 2017-11-07 | 东莞冠唯电子科技有限公司 | A kind of quick detachable driving member of vertical collecting machine |
| CN206871349U (en) * | 2017-03-10 | 2018-01-12 | 深圳市道通智能航空技术有限公司 | Propeller protection device, horn and Multi-axis aircraft |
| CN211468775U (en) * | 2019-10-28 | 2020-09-11 | 深圳市道通智能航空技术有限公司 | Quick detach structure and aircraft |
Family Cites Families (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2530859Y (en) * | 2001-08-29 | 2003-01-15 | 古正辉 | Quick-release wheel installation and fixing structure |
| US7390025B2 (en) * | 2004-03-31 | 2008-06-24 | Ti Group Automotive Systems, Llc | Secondary latch/verifier for a quick connector |
| CN100581875C (en) * | 2007-03-08 | 2010-01-20 | 广明光电股份有限公司 | Fixture structure |
| KR101329208B1 (en) * | 2012-09-03 | 2013-11-13 | 김성문 | Locking apparatus for sliding door |
| US20170043869A1 (en) * | 2015-08-11 | 2017-02-16 | Intellitrax, Inc. | Protection element and device for camera drone |
| US20170283090A1 (en) * | 2016-04-04 | 2017-10-05 | Skycatch, Inc. | Unmanned aerial vehicle battery swapping system |
| CN205952307U (en) * | 2016-08-19 | 2017-02-15 | 北京臻迪机器人有限公司 | Connecting piece of rotor fender bracket, unmanned many rotor crafts |
| CN206273679U (en) * | 2016-10-25 | 2017-06-23 | 深圳市大疆创新科技有限公司 | Protective cover and unmanned vehicle |
| CN207106851U (en) * | 2017-06-15 | 2018-03-16 | 深圳智航无人机有限公司 | Wing quick-disassembly structure and unmanned plane |
| CN207510708U (en) * | 2017-07-26 | 2018-06-19 | 歌尔科技有限公司 | A kind of unmanned plane fender bracket and a kind of unmanned plane |
| CN107628238A (en) * | 2017-10-24 | 2018-01-26 | 深圳市高巨创新科技开发有限公司 | Unmanned vehicle |
| CN108058818A (en) * | 2017-12-26 | 2018-05-22 | 昆山优尼电能运动科技有限公司 | Unmanned plane paddle fender bracket |
| CN208291470U (en) * | 2018-05-31 | 2018-12-28 | 上海歌尔泰克机器人有限公司 | Quick-disassembly structure and aircraft |
| CN118457967A (en) * | 2018-12-28 | 2024-08-09 | 深圳市道通智能航空技术股份有限公司 | Unmanned vehicles and wing subassembly thereof |
| CN110626502B (en) * | 2019-10-28 | 2025-01-24 | 深圳市道通智能航空技术股份有限公司 | A quick-detachable structure and aircraft |
-
2019
- 2019-10-28 CN CN201911033355.XA patent/CN110626502B/en active Active
-
2020
- 2020-10-27 WO PCT/CN2020/124056 patent/WO2021083152A1/en not_active Ceased
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN206617458U (en) * | 2017-03-09 | 2017-11-07 | 东莞冠唯电子科技有限公司 | A kind of quick detachable driving member of vertical collecting machine |
| CN206871349U (en) * | 2017-03-10 | 2018-01-12 | 深圳市道通智能航空技术有限公司 | Propeller protection device, horn and Multi-axis aircraft |
| CN211468775U (en) * | 2019-10-28 | 2020-09-11 | 深圳市道通智能航空技术有限公司 | Quick detach structure and aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110626502A (en) | 2019-12-31 |
| WO2021083152A1 (en) | 2021-05-06 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110626502B (en) | A quick-detachable structure and aircraft | |
| US11390396B2 (en) | Connecting apparatus and unmanned aerial vehicle comprising connecting apparatus | |
| CN106715264B (en) | Locking mechanical system, screw, motor, driving system subassembly and aircraft | |
| CN102326004B (en) | Fastening devices for modular elements in aircraft | |
| CN106628165B (en) | Aircraft and screw quick detach device, quick detach formula screw and screw base subassembly thereof | |
| CN109070993B (en) | Unmanned aerial vehicle's frame subassembly and unmanned aerial vehicle | |
| KR101625582B1 (en) | Rotary connector device | |
| CN109502033B (en) | Screw locking mechanism, screw, motor, power component and unmanned vehicles | |
| CN110294117A (en) | Rotor assemblies and unmanned vehicle with rotor assemblies | |
| WO2018113202A1 (en) | Detachable pan-tilt connection device and unmanned aerial vehicle | |
| WO2021035631A1 (en) | Quick release member, propeller assembly, and multi-rotor unmanned aerial vehicle | |
| CN211468775U (en) | Quick detach structure and aircraft | |
| CN112119009A (en) | Locking structure, screw, power device, power component and unmanned aerial vehicle | |
| CN207416679U (en) | Actuator and the electronic equipment with the actuator | |
| CN206417195U (en) | Propeller and its retaining mechanism, motor, Power Component and unmanned vehicle | |
| CN208217015U (en) | A kind of interface structure of unmanned plane | |
| CN210592415U (en) | Screw safety cover and aircraft | |
| CN220206016U (en) | Shell assembly and air conditioner | |
| CN218877582U (en) | Mechanism and unmanned aerial vehicle call | |
| WO2020220202A1 (en) | Quick-release connecting assembly, airscrew, power device, power assembly and unmanned aerial vehicle | |
| CN222380083U (en) | Unlocking structure, fan module and chassis | |
| CN219029751U (en) | Docking device and unmanned aerial vehicle using same | |
| CN223031309U (en) | Quick-release joint and unmanned aerial vehicle landing gear | |
| CN212448129U (en) | Nacelle rapid disassembly structure and unmanned aerial vehicle | |
| CN110406685B (en) | A connection device for quick installation and disassembly of a rotary-wing drone and a manipulator |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB02 | Change of applicant information |
Address after: 518055 Shenzhen, Guangdong, Nanshan District Xili street, No. 1001, Zhiyuan Road, B1 9. Applicant after: Shenzhen daotong intelligent Aviation Technology Co.,Ltd. Address before: 518055 Shenzhen, Guangdong, Nanshan District Xili street, No. 1001, Zhiyuan Road, B1 9. Applicant before: AUTEL ROBOTICS Co.,Ltd. |
|
| CB02 | Change of applicant information | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |