阅读说明：本技术 一种双向无人机 (Bidirectional unmanned aerial vehicle ) 是由 李伟琴 于 2019-10-12 设计创作，主要内容包括：本发明公开了一种双向无人机,包括第一撑板、主轴和若干翼臂,所述第一撑板的底部与所述主轴相连,所述主轴上设有若干纵向的第一滑槽,所述主轴上设有若干横向的第二滑槽,所述第一滑槽分布的间距相同,所述第一滑槽的纵向长度不同,所述第二滑槽在所述主轴上分布的长度不同,所述第一滑槽与所述第二滑槽相连通,所述第一滑槽内设有滑块,所述滑块与所述翼臂相连,所述翼臂外部设有与之铰连接的第一弹簧,所述第一弹簧的另一端与相邻的翼臂相卡接,所述主轴的外部设有用于锁紧所述滑块的锁紧机构,所述翼臂上设有驱动机构,本装置便于运输、便于折叠携带以及能够避免翼臂之间出现相对运动而导致飞行状态不够稳定。(The invention discloses a bidirectional unmanned aerial vehicle, which comprises a first supporting plate, a main shaft and a plurality of wing arms, wherein the bottom of the first supporting plate is connected with the main shaft, the main shaft is provided with a plurality of longitudinal first sliding chutes, the main shaft is provided with a plurality of transverse second sliding chutes, the first sliding chutes are distributed at the same interval, the longitudinal lengths of the first sliding chutes are different, the lengths of the second sliding chutes distributed on the main shaft are different, the first sliding groove is communicated with the second sliding groove, a sliding block is arranged in the first sliding groove and is connected with the wing arm, the outer part of the wing arm is provided with a first spring which is hinged with the wing arm, the other end of the first spring is clamped with the adjacent wing arm, the locking mechanism for locking the sliding block is arranged outside the main shaft, the wing arms are provided with driving mechanisms, and the device is convenient to transport, fold and carry and can avoid the situation that the flying state is not stable enough due to relative motion between the wing arms.)

1. The utility model provides a two-way unmanned aerial vehicle, its characterized in that, includes first fagging, main shaft and a plurality of wing arm, the bottom of first fagging with the main shaft links to each other, be equipped with a plurality of fore-and-aft first spouts on the main shaft, be equipped with a plurality of horizontal second spouts on the main shaft, the interval that first spout distributes is the same, the longitudinal length of first spout is different, the second spout is in the length that distributes on the main shaft is different, first spout with the second spout is linked together, be equipped with the slider in the first spout, the slider with the wing arm links to each other, the wing arm outside is equipped with the first spring of hinge connection with it, the other end and the adjacent wing arm looks joint of first spring, the outside of main shaft is equipped with and is used for locking the locking mechanism of slider, be equipped with actuating mechanism on the wing arm.

2. The two-way unmanned aerial vehicle of claim 1, wherein the locking mechanism comprises a sleeve, a clamping block and an insert block, the outer periphery of the bottom of the main shaft is in threaded connection with the inner periphery of the sleeve, the clamping block is arranged on the outer side of the sleeve, a plurality of arc-shaped openings are formed in the top of the first supporting plate, the insert block can freely penetrate through the openings, and protrusions are arranged at the bottom of the insert block and are clamped with the clamping block.

3. The two-way unmanned aerial vehicle of claim 1, wherein a second supporting plate is arranged below the sleeve, a through hole is formed in the second supporting plate, the sleeve can pass through the through hole, and a handle is further arranged on the periphery of the sleeve and located below the second supporting plate.

4. The two-way unmanned aerial vehicle of claim 1, wherein a controller and an attitude sensor are arranged on the top of the second supporting plate, the attitude sensor is in signal connection with the controller, the controller is in signal connection with the driving mechanism, and the driving mechanism is respectively in electrical connection with the controller and the attitude sensor.

5. The two-way unmanned aerial vehicle of claim 1, wherein the driving mechanism comprises a plurality of motors and a power supply, blades are arranged at output ends of the motors, the motors are in signal connection with the controller, the power supply is arranged at the top of the second supporting plate, and the power supply is respectively electrically connected with the motors, the controller and the attitude sensor.

6. The two-way unmanned aerial vehicle of claim 1, wherein a telescopic rod is arranged at the bottom of the motor, the telescopic rod is connected with the wing arm, and a second spring is arranged outside the telescopic rod.

7. The two-way drone of claim 1, wherein the sliding blocks are arc-shaped and can abut against each other.

8. The two-way unmanned aerial vehicle of claim 1, wherein the wing arm is further provided with a groove, and the other end of the first spring is provided with a projection which can be inserted into the groove.

9. The bi-directional drone of claim 1, wherein the first and second springs are both light springs.

Technical Field

The invention relates to the field of unmanned aerial vehicles, in particular to a bidirectional unmanned aerial vehicle.

Background

Current unmanned aerial vehicle often all is integrated into one piece's structure, in the process of using, because unmanned aerial vehicle's size is great, it is difficult to carry, and in the in-process of transportation, because unmanned aerial vehicle's external structure leads to damaging at the extruded in-process easily, thereby cause the too high problem of spoilage of transportation, furthermore, because when launching into unmanned aerial vehicle's user state, because unmanned aerial vehicle is at the in-process of using, relative motion can appear between the different wing arms under the disturbance of air current, thereby lead to flight state unstable, thereby the condition of falling takes place easily, thereby lead to the not good and damaged probability greatly increased of effect of use.

Disclosure of Invention

In view of the above existing problems, the technical problem to be solved by the present invention is to provide a bidirectional unmanned aerial vehicle which is convenient to transport, fold and carry, and can avoid the unstable flight state caused by the relative motion between the wing arms.

The invention provides a bidirectional unmanned aerial vehicle which comprises a first supporting plate, a main shaft and a plurality of wing arms, wherein the bottom of the first supporting plate is connected with the main shaft, a plurality of longitudinal first sliding grooves are formed in the main shaft, a plurality of transverse second sliding grooves are formed in the main shaft, the distribution intervals of the first sliding grooves are the same, the longitudinal lengths of the first sliding grooves are different, the lengths of the second sliding grooves distributed on the main shaft are different, the first sliding grooves are communicated with the second sliding grooves, sliding blocks are arranged in the first sliding grooves and connected with the wing arms, first springs hinged with the wing arms are arranged outside the wing arms, the other ends of the first springs are connected with adjacent wing arms in a clamping mode, a locking mechanism used for locking the sliding blocks is arranged outside the main shaft, and driving mechanisms are arranged on the wing arms.

Further, locking mechanism includes sleeve, joint piece and inserted block, the periphery of main shaft bottom with telescopic internal peripheral threaded connection, the joint piece is located the telescopic outside, the top of first fagging is equipped with a plurality of curved openings, the inserted block can freely pass the opening, the bottom of inserted block is equipped with protrudingly, protruding with joint piece looks joint.

Further, telescopic below is equipped with the second fagging, be equipped with the through-hole on the second fagging, the sleeve can pass the through-hole, telescopic periphery still is equipped with the handle, the handle is located the below of second fagging, first fagging with be equipped with the elastic material layer between the second fagging.

Further, the top of second fagging is equipped with controller and attitude sensor, attitude sensor with controller signal connection, the controller with actuating mechanism signal connection, actuating mechanism respectively with controller and attitude sensor electricity are connected.

Further, actuating mechanism includes a plurality of motors and power, the output of motor is equipped with the blade, the motor with controller signal connection, the power is located the top of second fagging, the power respectively with motor, controller and attitude sensor electricity are connected.

Furthermore, the bottom of the motor is provided with a telescopic rod, the telescopic rod is connected with the wing arm, and a second spring is arranged outside the telescopic rod.

Further, the sliders are arc-shaped, and the sliders can abut against each other.

Furthermore, a groove is further formed in the wing arm, a protruding block is arranged at the other end of the first spring, and the protruding block can be inserted into the groove.

Further, the first spring and the second spring are both light springs.

The invention has the beneficial effects that:

according to the bidirectional unmanned aerial vehicle, the sliding block can slide to the topmost part of the first sliding groove through the sliding of the sliding block in the first sliding groove, so that the wing arms are horizontally aligned, the mass distribution balance of the device is ensured, the problem of poor stability caused by uneven mass distribution is solved in the using process, the position of the sliding block can be fixed through the matching of the first supporting plate and the locking mechanism, the reliability of the device in the using process is ensured, the locking mechanism can be released through the action of the second sliding groove communicated with the first sliding groove when the device needs to be transported or carried, so that the sliding block slides into the corresponding second sliding groove, and then the wing arms can be vertically overlapped through the sliding of the sliding block in the second sliding groove, the size of the device is greatly reduced, then the coincident wing arms are locked through the locking action of the locking mechanism, so that the transportation is more convenient, the device is not easy to damage due to extrusion in the transportation process as a traditional unmanned aerial vehicle, so that the safety of the device in the transportation process is ensured, when the device is used as the unmanned aerial vehicle, the situation that relative motion occurs between the wing arms can be avoided through the matching action of the locking mechanism and the first spring, so that the stability of the device in the flying process is ensured, the serious swinging phenomenon in the flying process is avoided, in addition, the first spring can always provide reverse acting force according to the swinging of the wing arms in the swinging process possibly occurring to the wing arms, and the situation that the wing arms are close to each other due to strong airflow is avoided, thereby causing the phenomenon of the device turning over.

Drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only preferred embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to these drawings without inventive exercise.

Fig. 1 is a schematic view of a partial structure of a bidirectional drone according to the present invention;

fig. 2 is a schematic view of the overall structure of a bidirectional unmanned aerial vehicle according to the present invention;

fig. 3 is a partial enlarged view of fig. 1A of a bi-directional drone of the present invention;

FIG. 4 is a schematic diagram of the position relationship between the sliding blocks of the two-way UAV of the present invention in the same horizontal plane;

fig. 5 is a schematic view of the two-way drone of the present invention with the sliders in the same vertical plane.

In the figure, 1 is a first supporting plate, 2 is a main shaft, 3 is a wing arm, 4 is a first sliding groove, 5 is a second sliding groove, 6 is a sliding block, 7 is a first spring, 8 is a sleeve, 9 is a clamping block, 10 is an insertion block, 11 is an opening, 12 is a protrusion, 13 is a second supporting plate, 14 is a through hole, 15 is a handle, 16 is a convex block, 17 is a controller, 18 is an attitude sensor, 19 is a motor, 20 is a power supply, 21 is a blade, 22 is a telescopic rod, 23 is a second spring, and 24 is a groove.

Detailed Description

In order to better understand the technical content of the invention, specific embodiments are provided below, and the invention is further described with reference to the accompanying drawings.

Referring to fig. 1 to 5, the invention provides a bidirectional unmanned aerial vehicle, which comprises a first supporting plate 1, a main shaft 2 and a plurality of wing arms 3, wherein the bottom of the first supporting plate 1 is connected with the main shaft 2, the main shaft 2 is provided with a plurality of longitudinal first sliding grooves 4, the main shaft 2 is provided with a plurality of transverse second sliding grooves 5, the first sliding grooves 4 are distributed at the same interval, the longitudinal lengths of the first sliding grooves 4 are different, the lengths of the second sliding grooves 5 distributed on the main shaft 2 are different, the first sliding grooves 4 are communicated with the second sliding grooves 5, the first sliding grooves 4 are internally provided with sliding blocks 6, the sliding blocks 6 are connected with the wing arms 3, first springs 7 hinged with the wing arms 3 are arranged outside the wing arms 3, the other ends of the first springs 7 are clamped with the adjacent wing arms 3, the main shaft 2 is externally provided with a locking mechanism for locking the sliding blocks 6, the wing arms 3 are provided with a driving mechanism, the sliding block 6 can slide to the topmost part of the first sliding groove 4 by the sliding of the sliding block 6 on the first sliding groove 4, so that the wing arms 3 are horizontally aligned, the mass distribution balance of the device is ensured, the problem of poor stability caused by uneven mass distribution is avoided in the use process, the position of the sliding block 6 can be fixed by the matching of the first supporting plate 1 and the locking mechanism, the reliability of the device in the use process is ensured, and the locking mechanism can be released by the action of the second sliding groove 5 communicated with the first sliding groove 4 in the transportation or carrying process of the device, so that the sliding block 6 slides into the corresponding second sliding groove 5 and then slides in the second sliding groove 5 through the sliding of the sliding block 6, the wing arms 3 can be mutually overlapped in the vertical direction, so that the volume of the device is greatly reduced, then the overlapped wing arms 3 are locked through the locking action of the locking mechanism, the transportation is more convenient, the device can not be damaged easily due to extrusion in the transportation process like a traditional unmanned aerial vehicle, so that the safety of the device in the transportation process is ensured, when the device is used as the unmanned aerial vehicle, the relative motion between the wing arms 3 can be avoided through the matching action of the locking mechanism and the first spring 7, so that the stability of the device in the flying process is ensured, the serious swinging phenomenon in the flying process is avoided, and the first spring 7 can always provide reverse acting force in real time according to the swinging of the wing arms 3 in the possible swinging process of the wing arms 3, the phenomenon that the wing arms 3 are close to each other due to the fact that the wing arms 3 are subjected to strong airflow, and therefore the device is turned over is avoided.

Specifically, the locking mechanism comprises a sleeve 8, a clamping block 9 and an inserting block 10, the outer periphery of the bottom of the main shaft 2 is in threaded connection with the inner periphery of the sleeve 8, the clamping block 9 is arranged on the outer side of the sleeve 8, a plurality of arc-shaped openings 11 are arranged at the top of the first supporting plate 1, the insertion block 10 can freely pass through the opening 11, the bottom of the insertion block 10 is provided with a protrusion 12, the protrusion 12 is clamped with the clamping block 9, when the sliding blocks 6 are unfolded to the same plane, the sliding blocks 6 are clamped by the action of the sleeves 8, the insert blocks 10 can be connected with each other and can freely move in the opening 11, and after the insert blocks 10 are inserted into the opening 11, due to the limiting effect of the insertion block 10, the swinging of the wing arm 3 can be limited to a certain extent, so that the unstable flying condition caused by the swinging of the wing arm 3 is avoided.

Specifically, the below of sleeve 8 is equipped with second fagging 13, be equipped with through-hole 14 on the second fagging 13, sleeve 8 can pass through-hole 14, sleeve 8's periphery still is equipped with handle 15, handle 15 is located the below of second fagging 13, through handle 15's effect, the user of this device can be according to actual needs elasticity at the in-process that uses sleeve 8, and through handle 15 can make the elasticity sleeve 8's process is more convenient.

Specifically, the top of second fagging 13 is equipped with controller 17 and attitude sensor 18, attitude sensor 18 with controller 17 signal connection, controller 17 with actuating mechanism signal connection, actuating mechanism respectively with controller 17 and attitude sensor 18 electricity are connected, through attitude sensor 18 can know the flight angle of aircraft in real time, thereby pass through controller 17 controls the operation of the actuating mechanism of aircraft according to actual need, ensures the steady and safety of this device flight process.

Specifically, actuating mechanism includes a plurality of motors 19 and power 20, motor 19's output is equipped with blade 21, motor 19 with controller 17 signal connection, power 20 locates the top of second fagging 13, power 20 respectively with motor 19, controller 17 and attitude sensor 18 electricity are connected, through controller 17 can control power 20's current direction to make motor 19 can positive and negative direction rotate, improved the flight flexibility of this device, through attitude sensor 18's real-time induction and with signal transmission extremely controller 17, thereby pass through controller 17 control motor 19 begins to work to ensure the reliability of this device work.

Specifically, the bottom of motor 19 is equipped with telescopic link 22, telescopic link 22 with wing arm 3 links to each other, telescopic link 22's outside is equipped with second spring 23, through telescopic link 22 with the cooperation of second spring 23 can play certain cushioning effect in the twinkling of an eye of this device and ground contact to avoid the phenomenon that the mechanism damaged appears just descending the process many times of the whole frame of this device.

Specifically, slider 6 is circular-arc, and can butt each other between the slider 6, through butt each other between the slider 6, thereby can improve to a certain extent the firm degree between the wing arm 3 has also avoided the condition of rocking to take place moreover.

Specifically, still be equipped with recess 24 on the wing arm 3, the other end of first spring 7 is equipped with lug 16, lug 16 can insert in the recess 24, through recess 24 with looks joint between the lug 16 to it is more convenient to make this device at the in-process of dismantling, and also can pass through the cooperation between recess 24 and the lug 16, will first spring 7's position is fixed, in addition, recess 24 with can adopt interference fit between the lug 16, thereby avoids lug 16 is in the condition of rocking takes place in the recess 24.

Specifically, the first spring 7 and the second spring 23 are both light springs, and the weight of the device can be reduced by adopting the light springs, so that the cruising ability of the device is improved.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.