CN109484610B - Electric unmanned aerial vehicle's cantilever mistake proofing of inserting mechanism - Google Patents

Abstract

A cantilever misplug prevention mechanism of an electric unmanned aerial vehicle comprises a first part connected with a body; a second portion connected to the cantilever; a cantilever rotating shaft; the second part is provided with a clamping head corresponding to the elastic pressing plate; the clamping head is provided with a plurality of mounting holes, and the elastic pressing plate is provided with a plurality of slots corresponding to the mounting holes; the mounting hole is selectively provided with a bulge which can be inserted into the slot; the insertion groove is provided with a filler for preventing the protrusion from being inserted into the insertion groove at a position corresponding to a position where the protrusion is not mounted. This application can distinguish the mounting structure of every cantilever one by one through selectively installing protruding thing in a plurality of mounting holes on the dop, and the slot that corresponds on the cooperation elastic pressure plate lets the correct position on the fuselage is installed uniquely to every different mounting structure's of can corresponding cantilever, can avoid installing the wrong fuselage position with the cantilever, has improved the security of cantilever installation, has avoided the emergence of crash accident.

Description

Electric unmanned aerial vehicle's cantilever mistake proofing of inserting mechanism

Technical Field

The invention relates to the technical field of unmanned aerial vehicles, in particular to a cantilever mounting structure of an electric unmanned aerial vehicle, and particularly relates to a cantilever misplug prevention mechanism capable of preventing a cantilever of the electric unmanned aerial vehicle from being wrongly mounted.

Background

With the development of the global general aviation industry, the development of various rotor airplanes is increasing day by day, and particularly, the rotor electric unmanned aircraft is widely applied to tasks such as agricultural protection, forest fire monitoring, aerial photography, land survey, post-disaster loss assessment and the like. Electric unmanned aerial vehicle simple structure, the noise is little, has advantages such as flexible, quick, the operation requirement of reaction is low, and is very big in the occupation ratio in consumption level market. However, the power of the electric unmanned aerial vehicle is provided by the battery, the weight of the battery cannot be consumed like fuel oil, so that the effective load of the electric unmanned aerial vehicle is very limited, the cruising time is short, and the electric unmanned aerial vehicle is rarely used as a weapon striking platform.

Most of the electric unmanned aerial vehicles in the current consumer-grade market are multi-axis unmanned aerial vehicles, such as four-axis, six-axis and the like, the whole take-off weight is very small, the cruising time is very short, the strength and the weight reduction problem are not fully considered in various fuselage structural designs, the load level is low, the structural layout is unreasonable, the unmanned aerial vehicle is difficult to exert the control and safety advantages, and the development and application of the unmanned rotor wing aircraft in the military and monitoring fields are limited.

Present electronic unmanned aerial vehicle is multiaxis unmanned aerial vehicle mostly, like four-axis, six axles etc. the complete machine weight of taking off is very little, but the cantilever expansion is very big, brings certain difficulty for unmanned aerial vehicle's transportation, carry and save etc.. Therefore, in order to improve the portability of use of drones and to reduce the cost of transportation, many folding cantilever drones have emerged.

For example, a variety of boom fold mechanisms for drones are disclosed in CN 205440846U, CN205661646U, CN205891210U, CN203975225U, CN 206358349U, CN 206358350U, CN 206374964U, CN 205952286U, CN105691590A, CN106081056A, which basically comprise four major parts: a first portion coupled to the fuselage; a second portion connected to the cantilever; a cantilever pivot connecting the first and second portions together such that the first and second portions are relatively rotatable about the cantilever pivot; and a detachable structure connecting the first and second portions together. These prior art folding mechanisms all have a problem that the first part and the second part are basically positioned by the cantilever rotating shaft, the cantilever rotating shaft always has a certain gap because the cantilever rotating shaft rotates relative to the two parts, so that the two parts positioned by the cantilever rotating shaft are easy to relatively displace, and therefore, other connecting methods such as bolts have to be considered for reinforcement, in addition, the force generated by the displacement of the two parts is transferred to the detachable structure, the detachable structure is loosened after long-term use because the detachable structure is originally used for convenient connection and detachment, the connection is not very tight, and therefore the probability of loosening is very high, which leads the existing folding mechanisms to be used for preventive reinforcement of the detachable structure, leads the existing folding mechanisms to be complicated in structure and heavy in weight, reliability is also relatively low.

In order to solve the above-mentioned drawbacks of the prior art, the applicant of the present application discloses a cantilever folding mechanism of an electric unmanned aerial vehicle in a previously applied chinese patent application CN 107600385 a, comprising a first part connected with a body of the electric unmanned aerial vehicle; a second part connected with a cantilever of the electric unmanned aerial vehicle; a cantilever pivot connecting the first and second portions together; and a resilient platen connecting the first and second portions together; the first portion has a first concave portion and a first convex portion opposite the second portion; the second portion has a second convex portion and a second concave portion opposite to the first portion; the first concave part corresponds to the second convex part in shape, and the first convex part corresponds to the second concave part in shape. This cantilever folding mechanism of prior art forms the interlock relation through convex-concave structure closure, has avoided taking place the possibility of dislocation in the circumferencial direction, need not increase extra reinforcing weight, can not influence detachable construction's connection moreover, has improved folding mechanism's connection reliability.

This prior art effectively overcomes the deficiencies of the prior art, but there is still room for improvement. Especially when needing to dismantle whole cantilevers and get off to overhaul, change, transport, current folding mechanism is difficult to accomplish quick dismantlement, is difficult to be suitable for the rapid application in military field.

Disclosure of Invention

The technical problem to be solved by the invention is to provide a cantilever misplug prevention mechanism of an electric unmanned aerial vehicle, so as to reduce or avoid the problems mentioned above.

In order to solve the technical problem, the invention provides a cantilever misplug prevention mechanism of an electric unmanned aerial vehicle, which is used for avoiding that a cantilever is installed at a wrong body position; the cantilever misplug prevention mechanism comprises a first part connected with the body of the electric unmanned aerial vehicle; a second part connected with a cantilever of the electric unmanned aerial vehicle; the cantilever rotating shaft is fixedly connected to the first part, and the second part can rotate around the cantilever rotating shaft relative to the first part; the elastic pressing plate is used for clamping the second part on the first part, the elastic pressing plate is connected to the first part, and the second part is provided with a clamping head corresponding to the elastic pressing plate; the clamping head is provided with a plurality of mounting holes, and the elastic pressing plate is provided with a plurality of slots corresponding to the mounting holes; the mounting hole is selectively provided with a bulge which can be inserted into the slot; and a filler for preventing the bulge from being inserted into the slot is arranged in the slot corresponding to the position where the bulge is not installed.

Preferably, the number of the slots is the same as the number of the mounting holes.

Preferably, the number of the slots is 4-7.

Preferably, the structure of the slots is identical, and the structure of the protrusions is identical; the structure of the filler is completely the same.

Preferably, the second part is provided with a hook member which is caught on the cantilever rotation shaft, the hook member being protruded from the second part and extended in a direction opposite to the elastic pressing plate, the hook member being detachable from the cantilever rotation shaft after the second part is rotated at an angle about the cantilever rotation shaft.

Preferably, the clamping head and the hook part of the second part are clamped on the first part through the corresponding elastic pressure plate and the corresponding cantilever rotating shaft respectively; the elastic pressing plate is pressed to release the clamping head.

Preferably, the first part is provided with two limiting pieces extending towards the second part, the two limiting pieces are arranged corresponding to the width positions of the clamping heads, and the distance between the two limiting pieces is larger than the width of the clamping heads.

Preferably, the upper surface of the elastic pressure plate is provided with an anti-loose screw button for detachably connecting the elastic pressure plate and the first part together.

The utility model provides an electric unmanned aerial vehicle's cantilever mistake proofing mechanism of inserting is through selectively installing protruding thing in a plurality of mounting holes on the dop, can distinguish the mounting structure one by one of every cantilever, the slot that corresponds on the cooperation elastic pressure board, the correct position on the fuselage is installed uniquely to the cantilever that lets every different mounting structure that can correspond, cantilever position installation mistake in the time of can preventing to reinstall after cantilever assembly or maintenance, avoid installing the wrong fuselage position with the cantilever, the security of cantilever installation has been improved, the emergence of crash accident has been avoided.

Drawings

The drawings are only for purposes of illustrating and explaining the present invention and are not to be construed as limiting the scope of the present invention. Wherein,

fig. 1 shows a schematic view of a boom mounting structure of an electric drone according to an embodiment of the present invention;

fig. 2 is a schematic view showing an opened state of a cantilever mounting structure of an electric drone according to another embodiment of the present application;

fig. 3 is a schematic view showing a disassembled state of a cantilever mounting structure of an electric unmanned aerial vehicle according to another embodiment of the present application;

fig. 4 is a schematic exploded view of a cantilever misplug prevention mechanism of an electric drone according to an embodiment of the present application;

FIG. 5 is a schematic view showing an assembled state of the second part of FIG. 4;

fig. 6 is a schematic view showing an assembled and disassembled state of the elastic pressing plate of fig. 4.

Detailed Description

In order to more clearly understand the technical features, objects, and effects of the present invention, embodiments of the present invention will now be described with reference to the accompanying drawings. Wherein like parts are given like reference numerals.

As described in the background art, the present invention provides an improved structure for overcoming the drawbacks of the cantilever folding mechanism disclosed in CN 107600385 a in the prior art, so that the folding mechanism in the prior art has a quick disassembling and assembling function, and is suitable for quick application in the military field, and all the cantilevers can be disassembled for maintenance, replacement and transportation when needed. Meanwhile, the cantilever can be prevented from being installed mistakenly to avoid accidents.

Specifically, the cantilever misplug prevention mechanism of the electric unmanned aerial vehicle is a further improvement proposed on the basis of the folding mechanism of CN 107600385 a, the application refers to the prior art in the whole, and a person skilled in the art can understand other structures related to the electric unmanned aerial vehicle based on the disclosure of the prior art. As shown in fig. 1, the cantilever mounting structure 11 of the electric unmanned aerial vehicle of the present invention is disposed at a joint between the cantilever 3 and the vehicle body (not shown in the figure), and the cantilever 3 can be quickly detached from the vehicle body by the cantilever mounting structure 11. Fig. 1 is a schematic structural diagram of a cantilever mounting structure of an electric drone according to an embodiment of the present application. It should be understood by those skilled in the art that the cantilever mounting structure 11 of the present application may be disposed on the same electric drone disclosed in CN 107600385 a, or may be disposed between the body and the cantilever of any electric drone.

As mentioned above and referring to the drawings, the cantilever 3 is provided with a cantilever mounting structure 11 at the connection with the body, wherein the connection with the body of the electric unmanned aerial vehicle is a first part 111; connected to the boom 3 of the electric drone is a second part 112; a cantilever rotating shaft 113 is fixedly connected to the first part 111, and the second part 112 can rotate around the cantilever rotating shaft 113 relative to the first part 111; capturing the second portion 112 to the first portion 111 is a resilient pressure plate 114.

The second portion 112 is a cylindrical structure having an inner diameter larger than an outer diameter of the cantilever 3, and a root portion of the cantilever 3 is inserted into the second portion 112 and fixedly coupled by a screw. Cantilever 3 of this application is pegged graft through tubular structure with cantilever mounting structure 11's second part 112, can obtain bigger area of contact and obtain bigger frictional force, firm in connection just easily through bolted connection and dismouting, and the reliability is high, the dismouting of being convenient for operation such as maintenance.

The specific structure of the cantilever mounting structure of the electric unmanned aerial vehicle of the present application is further specifically described below with reference to fig. 2-3, wherein fig. 2 is a schematic diagram showing an open state of the cantilever mounting structure of the electric unmanned aerial vehicle according to another specific embodiment of the present application; fig. 3 is a schematic view showing a disassembled state of a cantilever mounting structure of an electric unmanned aerial vehicle according to another embodiment of the present application.

As shown in fig. 3 in particular, unlike the prior art, in the present application, the second portion 112 is provided with a hook 201 that is hooked on the cantilever rotation shaft 113, the hook 201 extends from the second portion 112 and extends in a direction opposite to the elastic pressing plate 114, and the hook 201 can be disengaged from the cantilever rotation shaft 113 after the second portion 112 is rotated at an angle about the cantilever rotation shaft 113. When the electric unmanned aerial vehicle is subjected to daily maintenance and other operations, the front end of the elastic pressing plate 114 is lifted only by pressing the rear end of the elastic pressing plate 114, the upper end of the second part 112 clamped by the elastic pressing plate 114 can be separated, and the second part 112 is rotated around the cantilever rotating shaft 113, so that the second part 112 is rotated by a certain angle, as shown in the state of fig. 2. Then, the second portion 112 connected to the arm 3 is lifted obliquely upward, and the hook 201 can be released from the state of being overlapped on the arm rotation shaft 113, as shown in fig. 3.

It should be understood by those skilled in the art that regarding the angle of rotation of the second portion 112, the length and angle of the downward extension of the hook 201 and the related structural dimensions, such as the distance between the center of the cantilever rotation shaft 113 and the hook 201, those skilled in the art can easily obtain the angle of rotation of the second portion 112 for the component dimensions in different situations based on the principle of mechanical design according to the specific embodiments disclosed in the drawings, and it is obvious to those skilled in the art to obtain the required specific angle based on the disclosure of the present application, and therefore, the detailed description is omitted here.

In the cantilever folding mechanism in the prior art, the cantilever rotating shaft is used for inserting and connecting the first part and the second part together, and the cantilever rotating shaft needs to be detached when the cantilever is detached. In view of the purpose of avoiding disconnection, the cantilever rotation shaft needs to be inserted very firmly, so that it takes a certain time to disassemble and assemble the cantilever rotation shaft. In the cantilever mounting structure of the present application, the cantilever rotating shaft 113 is fixed on the first portion 111, when the cantilever 3 is disassembled, the cantilever rotating shaft 113 does not need to be loosened at all, only the upper end of the second portion 112 clamped by the elastic pressing plate 114 needs to be loosened, and then the second portion 112 is rotated, so that the second portion 112 can be lifted to disassemble the whole cantilever 3 from the machine body.

Further, an elastic pressing plate 114 is disposed on the first portion 111, and a chuck 115 corresponding to the elastic pressing plate 114 is disposed on the second portion 112. The elastic pressing plate 114 can press its rear end to open its front end under the action of external force, and then close downward by the elastic force of a spring (see the related structure in CN 107600385 a) to catch the clip 115, so as to form a snap-fit relationship to snap-fit the first part 111 and the second part 112 together, resulting in the state shown in fig. 1. When the cantilever 3 needs to be detached, the rear part of the elastic pressing plate 114 is also pressed under the action of external force, so that the front end of the elastic pressing plate 114 is opened, the cantilever 3 is pressed down, the second part 112 rotates around the cantilever rotating shaft 113, the chuck 115 is separated from the buckling position, the cantilever mounting structure 11 is completely opened, and the state shown in fig. 2 can be formed.

That is, in the above-described embodiment of the present application, the second portion 112 is integrally connected to the first portion 111 by means of snap-fitting. Wherein, the chuck 115 and the hook 201 of the second part 112 are respectively clamped on the first part 111 by the corresponding elastic pressing plate 114 and the cantilever rotating shaft 113. More specifically, the clip 115 of the second part 112 and the elastic pressing plate 114 of the first part 111 form a clamping structure, and the hook 201 of the second part 112 and the cantilever rotating shaft 113 fixedly connected to the first part 111 form a clamping structure. The elastic pressing plate 114 catches the chuck 115 by a spring or the like, and the chuck 115 can be released by pressing the elastic pressing plate 114.

Hook 201 and chuck 115 form an oppositely directed flange structure, and hook 201 rides on cantilevered pivot 113. In the case where the chuck 115 is caught by the elastic pressing plate 114, the entire second portion 112 is firmly caught by the first portion 111 and cannot be released. After the elastic pressing plate 114 is lifted and the chuck 115 is released, the hook 201 can be obliquely and upwardly taken down from the cantilever rotating shaft 113 by rotating the second part 112, so that the cantilever 3 connected with the second part 112 can be integrally taken down from the machine body, a quick-release structure with simple structure and easy disassembly and assembly is formed, the application of the quick-release structure in the military field is facilitated, and all cantilevers can be disassembled for overhaul, replacement and transportation when needed.

In another preferred embodiment, the first portion 111 is provided with two position-limiting pieces 118 extending out facing the second portion 112, the two position-limiting pieces 118 are arranged corresponding to the width position of the chuck 115, and the distance between the two position-limiting pieces 118 is larger than the width of the chuck 115. In this embodiment, by providing two spacing pieces 118 with a distance larger than the width of the chuck 115, the chuck 115 can be limited between the two spacing pieces 118 after the snap-fit state shown in fig. 1 is formed, so that the left and right displacement of the second portion 112 along the length direction of the cantilever rotation shaft 113 can be further prevented. That is, the limiting piece 118 provided in this embodiment can prevent the lateral sliding misalignment of the first portion 111 and the second portion 112, further improving the connection firmness of the folding mechanism of the present application, ensuring that the looseness caused by the misalignment does not occur, and thus the reinforcing weight will not be increased, and the added limiting piece 118 has a small structure, and will not affect the connection of the elastic pressing plate 114, and will not affect the connection reliability of the folding mechanism.

Further, the upper surface of the elastic pressing plate 114 is provided with a locking screw 102 for detachably connecting the elastic pressing plate 114 with the first portion 111, so that the elastic pressing plate 114 can be fixed to prevent the rotation thereof, thereby avoiding the accident that the cantilever 3 is disconnected from the body due to the accidental release of the elastic pressing plate 114 under the condition of vibration or unintentional touch, and providing the reliability of the mechanism.

Just as the background art part said, there is the problem that the cantilever was dismantled to current multiaxis electric unmanned aerial vehicle, and this application provides the mounting structure that can dismantle the cantilever fast, but has also brought another technical problem that needs the solution simultaneously. Because the structure of the holohedral symmetry is hardly accomplished to electronic unmanned aerial vehicle, load overall arrangement also can cause focus asymmetry moreover, consequently the motor of installation on every cantilever all need carry out calibration one by one to full quick-witted focus, lift condition, and electronic unmanned aerial vehicle's flight control system stores the motor timing data of different positions. The flight control system can set different control signals for motors at different positions so as to coordinate lift balance of the whole unmanned aerial vehicle, can coordinate parameters such as rotating speed and propeller pitch of the motors at different positions, and controls the flight direction and flight height of the whole unmanned aerial vehicle.

Due to the fact that the quick-release structure is adopted, the whole cantilever can be completely detached from the machine body. When the cantilever that will dismantle is reinstalled on the fuselage when needs, need notice the cantilever of different positions very much and install original position correctly, in case the position installation is wrong, the unmanned aerial vehicle will lose balance once starting and cause the crash. Because the cantilevers of the multi-axis electric unmanned aerial vehicle are numerous, and the general appearance of each cantilever is almost the same and is difficult to distinguish in appearance, the problem of installation errors particularly needs to be worried about.

One possible solution is to provide identification marks at the corresponding mounting positions of the boom and the body. But the parts coated with the marks can be replaced when in overhaul; frequent disassembly and assembly can also obscure the mark; there is a possibility of recognition errors at night or in poor lighting. Both of these problems result in the way the identification mark is placed not being particularly reliable. In addition, in the actual situation, the problems of insufficient responsibility of operators, lack of safety consciousness and operation of non-specialized trained operators in emergency exist, even if the identification mark is arranged, the equipment is not a decoration, and the function of preventing installation errors is not achieved at all. Therefore, the cantilever misplug prevention mechanism with the reliable misplug prevention function is provided without special training.

The specific structure of the cantilever misplug prevention mechanism of the electric unmanned aerial vehicle of the present application is further specifically described with reference to fig. 4 to 6, wherein fig. 4 is a schematic exploded view of the cantilever misplug prevention mechanism of the electric unmanned aerial vehicle according to an embodiment of the present application; FIG. 5 is a schematic view showing an assembled state of the second part of FIG. 4; fig. 6 is a schematic view showing an assembled and disassembled state of the elastic pressing plate of fig. 4.

Referring to fig. 4-6, the cantilever misplug prevention mechanism of the electric unmanned aerial vehicle of the present application is a mechanism for preventing the installation of the cantilever to a wrong fuselage position; the cantilever misplug prevention mechanism comprises the first part 111 connected with the body of the electric unmanned aerial vehicle; a second part 112 connected to the boom 3 of the electric drone; a cantilever rotating shaft 113 fixedly connected to the first part 111, the second part being rotatable around the cantilever rotating shaft 113 relative to the first part 111; and an elastic pressing plate 114 for clamping the second part 112 on the first part 111, wherein the elastic pressing plate 114 is connected to the first part 111, and the second part 112 is provided with a chuck 115 corresponding to the elastic pressing plate 114. As shown in fig. 4-6, the chuck 115 is provided with a plurality of mounting holes 1151, and the elastic pressing plate 114 is provided with a plurality of slots 1141 corresponding to the mounting holes 1151; a projection 1152 insertable into the slot 1141 is selectively installed in the installation hole 1151; a filling 1142 for preventing the protrusion 1152 from being inserted into the slot 1141 is provided in the slot 1141 at a position corresponding to a position where the protrusion 1152 is not mounted.

The basic operation principle of the cantilever misplug prevention mechanism of the present application is explained in detail below.

At the time of production processing of a product part, a plurality of mounting holes 1151 are previously processed on all the chucks 115 of the production processing, and the number of the mounting holes 1151 is 5 as seen in the embodiment of fig. 4. Meanwhile, on all the production-processed elastic pressing plates 114, the same number of slots 1141 as the number of the mounting holes 1151 are also pre-processed, and it can be seen in fig. 6 that the number of the slots 1141 is also 5. That is, during the manufacturing process, each of the chucks 115 of the suspension arm has 5 mounting holes 1151, and each of the resilient pressing plates 1141 has 5 slots 1141, which is convenient for mass production, reduces the manufacturing cost, and reduces the number of manufacturing processes.

When different cantilever arms 3 are mounted to the body at corresponding positions, a first portion 111 provided with a spring pressing plate 114 is mounted to the body, and a second portion 112 provided with a chuck 115 is mounted to the cantilever arm 3. At this time, in order to distinguish the installation position of each cantilever arm 3, it is possible to select to install the protrusions 1152 in the two leftmost installation holes 1151 of the collet 115 as shown in fig. 5, and correspondingly, three fillers 1142 for preventing the protrusions 1152 from being inserted into the slots 1141 may be provided in the slots 1141 corresponding to the positions where the protrusions 1152 are not installed.

Thus, when the cantilever arm 3 is installed, as shown in FIGS. 5 and 6 in cooperation, the two slots 1141 without the filler 1142 are empty and fit just enough to allow the two protrusions 1152 of the collet 115 to be inserted therein. This is the situation that should occur when the boom 3 is mounted in the correct position.

If the wrong cantilever 3 is mounted in the position shown in fig. 6, the two protrusions 1152 of the chuck 115 of the second part 112 of the cantilever 3 are not positioned as shown in fig. 5, at least one of the two protrusions 1152 is misaligned, and the misaligned protrusion 1152 corresponds to the slot 1141 of the elastic pressing plate 114, in which the filler 1142 is mounted. Thus, during installation, the dislocated protrusion 1152 cannot be inserted into the slot 1141 with the filler 1142, so that the cantilever 3 cannot be normally installed, the occurrence of cantilever misinsertion is avoided, and the safety of cantilever installation is improved.

Since the chuck 115 is pre-formed with 5 mounting holes 1151, if two protrusions 1152 are mounted as shown in fig. 5, there are theoretically 10 different combinations, so that it is ensured that the mounting structures of 10 cantilevers 3 are all different. Of course, the same combination of filling 3 fillings 1142 into 5 slots 1141 on the elastic pressing plate 114 is also 10 corresponding to the 10 structures, and exactly 10 different structures of the cantilever 3 can be correspondingly installed. Therefore, the number of mounting holes 1151 and slots 1141 of the embodiment shown in fig. 4-6 can be applied to the structure of the 10-axis and below-10-axis electric unmanned aerial vehicle for uniquely distinguishing all the cantilevers 3.

For more multi-axis electric drones, the number of pre-machined mounting holes 1151 and slots 1141 may be increased. For example, if there are 6 mounting holes 1151 and 6 slots 1141, respectively, and 3 protrusions 1152 and 3 fillers 1142 are provided, a maximum of 20 combinations can be provided. And if there are 7 mounting holes 1151 and 7 slots 1141 respectively, set up 3 protrusions 1152 and 4 fillers 1142, can provide 35 combination modes at most, can cover the extreme quantity of cantilever of the electronic unmanned aerial vehicle of existing multiaxis basically. Of course, if there are only 4 mounting holes 1151 and 4 slots 1141, and there are 2 protrusions 1152 and 2 fillers 1142, there are only 6 combinations at most, and the method is also applicable to electric drones with 6 shafts and less than 6 shafts.

Of course, it should be understood by those skilled in the art that the number of the mounting holes 1151 and the slots 1141 may be different, and the extra mounting holes 1151 or slots 1141 may be temporarily unavailable for extended use. For example, the projection 1152 is not temporarily installed in the extra mounting hole 1151 only when the extra mounting hole does not exist; the filler 1142 is temporarily installed in the extra slot 1141, and the extra slot 1141 does not exist. Of course, it is preferable that the number of the mounting holes 1151 and the number of the slots 1141 are the same, thereby avoiding unnecessary trouble due to an operation error.

Further preferably, all slots 1141 are identical in structure, and all protrusions 1152 are identical in structure; all the fillers 1142 have the same structure. The advantages are that the number of parts can be reduced, the universality of parts is improved, the adaptation problem of related parts is less, the adjustment and processing are convenient, the production cost can be reduced, and the assembly efficiency of products is improved.

Through the description of the above-mentioned cantilever error-insertion-prevention mechanism of the present application, a person skilled in the art should further find that, the cantilever error-insertion-prevention mechanism of the present application not only can be applied to the cantilever mounting structure with the quick-release function shown in fig. 1-3, but also can be applied to the mounting structure of the electric unmanned aerial vehicle with the foldable cantilever in the prior art, and can prevent the installation error of the cantilever position when the cantilever is re-installed after being assembled or overhauled, thereby avoiding the installation of the cantilever to the wrong body position, improving the safety of the installation of the cantilever, and avoiding the occurrence of crash accidents.

To sum up, electric unmanned aerial vehicle's cantilever mistake proofing mechanism of this application is through selectively installing protruding thing in a plurality of mounting holes on the dop, can distinguish the mounting structure of every cantilever one by one, the slot that corresponds on the cooperation elastic pressure board, the correct position on the fuselage is installed uniquely to the cantilever that lets every different mounting structure that can correspond, cantilever position mistake in installation after can preventing cantilever assembly or overhauing reinstallation, avoid installing the wrong fuselage position with the cantilever, cantilever installation's security has been improved, the emergence of crash accident has been avoided.

It should be appreciated by those of skill in the art that while the present invention has been described in terms of several embodiments, not every embodiment includes only a single embodiment. The description is given for clearness of understanding only, and it is to be understood that all matters in the embodiments are to be interpreted as including technical equivalents which are related to the embodiments and which are combined with each other to illustrate the scope of the present invention.

The above description is only an exemplary embodiment of the present invention, and is not intended to limit the scope of the present invention. Any equivalent alterations, modifications and combinations can be made by those skilled in the art without departing from the spirit and principles of the invention.

Claims (6)

1. A cantilever misplug prevention mechanism of an electric unmanned aerial vehicle is used for avoiding mounting a cantilever at a wrong body position; the cantilever misplug prevention mechanism comprises a first part (111) connected with the body of the electric unmanned aerial vehicle; a second part (112) connected to a boom (3) of the electric drone; a cantilever pivot (113) fixedly attached to the first portion (111), the second portion being rotatable relative to the first portion (111) about the cantilever pivot (113); the elastic pressing plate (114) is used for clamping the second part (112) on the first part (111), the elastic pressing plate (114) is connected to the first part (111) in a set mode, and the second part (112) is provided with clamping heads (115) corresponding to the elastic pressing plate (114); the clamping head is characterized in that a plurality of mounting holes (1151) are formed in the clamping head (115), and a plurality of slots (1141) which correspond to the mounting holes (1151) in position and have the same structure are formed in the elastic pressing plate (114); the mounting hole (1151) is selectively provided with a bulge (1152) which can be inserted into the slot (1141) and has the same structure; a position, corresponding to the position where the bulge (1152) is not installed, in the slot (1141) is provided with a filler (1142) which is identical in structure and prevents the bulge (1152) from being inserted into the slot (1141); the number of the slots (1141) is the same as the number of the mounting holes (1151).

2. The cantilever misplug prevention mechanism of the electric unmanned aerial vehicle of claim 1, wherein the number of the slots (1141) is 4-7.

3. The boom misplug prevention mechanism of the electric unmanned aerial vehicle according to claim 1, characterized in that the second portion (112) is provided with a hook member (201) which rides on the boom spindle (113), the hook member (201) extends from the second portion (112) and extends in a direction opposite to the elastic pressing plate (114), and the hook member (201) can be disengaged from the boom spindle (113) after the second portion (112) rotates around the boom spindle (113) by an angle.

4. The cantilever misplug prevention mechanism of the electric unmanned aerial vehicle of claim 3, wherein the chuck (115) and the hook (201) of the second part (112) are respectively clamped on the first part (111) through the elastic pressure plate (114) and the cantilever rotating shaft (113) corresponding to the chuck and the hook; the elastic pressing plate (114) is pressed to release the clamping head (115).

5. The cantilever misplug prevention mechanism of the electric unmanned aerial vehicle as claimed in claim 4, wherein the first portion (111) is provided with two limiting pieces (118) protruding towards the second portion (112), the two limiting pieces (118) are arranged corresponding to the width position of the chuck (115), and the distance between the two limiting pieces (118) is greater than the width of the chuck (115).

6. The cantilever misplug prevention mechanism of the electric unmanned aerial vehicle of claim 5, wherein the upper surface of the elastic pressure plate (114) is provided with a lock screw button (102) for detachably connecting the elastic pressure plate (114) and the first part (111).

Images