Unmanned aerial vehicle with buffer structure

Abstract

The utility model relates to an unmanned aerial vehicle with a buffer structure, which comprises a vehicle bottom, a speed reducing module, a first connecting seat, rotating modules, a wind gathering module, an air bag module and a vehicle body, the first connecting seat is fixedly mounted at the bottom end of the vehicle bottom, the rotating modules are respectively arranged at two ends of the vehicle body, and the wind gathering module is arranged at the bottom ends of the rotating modules. The air bag module is arranged at the lower end of the rotating module, the air bag module is arranged at the upper end of the air gathering module, the buffering module comprises a folding spring, a sliding module, a folding module, an air cylinder and a force reducing module, the folding spring is arranged at the bottom end of the machine bottom, the sliding module is arranged on the outer side of the folding spring, and the folding module is arranged at the side end of the sliding module; according to the unmanned aerial vehicle, the impact force brought when the unmanned aerial vehicle descends to the ground can be effectively relieved, and the accident that the unmanned aerial vehicle is damaged due to the fact that the unmanned aerial vehicle descends too fast due to misoperation of a flying hand, and the impact force borne by the unmanned aerial vehicle is too large is avoided.

Description

Technical Field

[0001] The utility model belongs to the technical field of unmanned aerial vehicles, in particular to a unmanned aerial vehicle with a buffer structure. Background Art

[0002] With the gradual development of drones, drones are also being used in more and more occasions, such as aerial reconnaissance, plant protection agriculture, patrolling, and even in the field of food delivery. The cost of drones varies. Cheap drones only cost one or two hundred yuan, while larger and more expensive drones often cost hundreds of thousands. Once these expensive drones are damaged, they will cause great economic losses to users.

[0003] According to statistics and responses from industry insiders, most drone damage occurs from mid-air imbalance and improper landing. Designers often target mid-air imbalance to improve drones, but ignore the damage caused by improper landing due to rapid descent. In addition, most drone chassis today are fixed, which cannot solve the problem of damage to the fuselage caused by a drone falling too quickly.

[0004] For this purpose, a UAV with a buffer structure is proposed. Utility Model Content

[0005] The purpose of this section is to summarize some aspects of the embodiments of the utility model and briefly introduce some preferred embodiments. Some simplifications or omissions may be made in this section and the specification abstract and utility model name of this application to avoid blurring the purpose of this section, specification abstract and utility model name, and such simplifications or omissions cannot be used to limit the scope of the utility model.

[0006] In view of the following technical problems in the prior art: most of the damage to drones occurs in two aspects: imbalance in the air and improper landing, and designers often make improvements to the imbalance in the air of drones, ignoring the damage caused by the drones descending too quickly and landing improperly. Moreover, most of the drone chassis today are fixed, which cannot solve the damage to the fuselage caused by the drone falling too quickly.

[0007] In order to solve the above technical problems, the utility model provides the following technical solutions: a drone with a buffer structure, including a bottom, a deceleration module, including a first connecting seat, a rotating module, a wind gathering module, an airbag module, and a fuselage, wherein the first connecting seat is fixedly installed at the bottom end of the bottom, the rotating modules are respectively arranged at both ends of the fuselage, the wind gathering module is arranged at the bottom end of the rotating module, the airbag module is arranged at the lower end of the rotating module, and the airbag module is arranged at the upper end of the wind gathering module; the buffer module includes a folding spring, a sliding module, a folding module, an air cylinder, and a force reduction module, wherein the folding spring is arranged at the bottom end of the bottom, the sliding module is arranged on the outside of the folding spring, the folding module is arranged at the side end of the sliding module, the force reduction module is arranged at the lower end of the folding module, and the air cylinder is arranged at the bottom end of the force reduction module.

[0008] As an optimal technical solution for a drone with a buffer structure, the rotating module includes a loose-leaf, a wind block, and a limit block. The loose-leaf is rotatably arranged at both ends of the drone fuselage, the wind block is rotatably arranged on the loose-leaf, and the limit block is fixedly arranged on the upper end of the wind block.

[0009] As an optimal technical solution for a drone with a buffer structure, the wind gathering module includes a wind gathering plate, an air induction block, and an opening slot. The wind gathering plates are respectively fixed at both ends of the drone fuselage, the air induction block is fixed inside the wind gathering plate, and the opening slot is opened at the upper and lower ends of the wind gathering plate. The wind inlet at the lower end of the air induction block is 70°, and the wind outlet at the upper end is 45°.

[0010] As a preferred technical solution for a drone with a buffer structure, the airbag module includes an air inlet groove, a canvas, and an air outlet. The air inlet groove is opened at the lower end of the hinge, and the air inlet groove runs through the fuselage and the top of the drone. The canvas is fixedly arranged at the upper end of the air inlet groove, and the air outlet is opened at the front end of the canvas.

[0011] As an optimal technical solution for a drone with a buffer structure, the sliding module includes a rotating spring, a rotating slot, and a rotating block. The rotating slot is opened on the inner side of the folding spring, the rotating spring is fixedly arranged at the top of the rotating slot, the rotating block is fixedly arranged at the bottom of the rotating spring, and the rotating block is slidably arranged on the inner side of the rotating slot.

[0012] As an optimal technical solution for a drone with a buffer structure, the folding module includes a first support frame, a second support frame, a folding groove, a folding column, and a bracket block. The first support frame is fixedly arranged at the bottom end of the rotating block, the folding groove is opened at the bottom end of the first support frame, the support column is fixedly arranged inside the folding groove, the second support frame is rotatably arranged in the folding groove, and the second support frame is rotatably arranged on the outside of the folding column, and the bracket block is fixedly arranged at the bottom end of the second support frame.

[0013] As an optimal technical solution for an unmanned aerial vehicle with a buffer structure, the force reduction module includes a bottom block, an intermediate block, an intermediate groove, an air nozzle, a front end groove, and a balance bar. The intermediate block is slidably arranged at the bottom end of the bracket block, the intermediate groove is opened inside the intermediate block, the bottom block is fixedly arranged inside the intermediate groove, the air cylinder is fixedly arranged at the lower end of the bottom block, the air nozzle at the upper end of the air cylinder passes through the bottom block, and the air nozzle is arranged at the upper end of the bottom block, the front end groove is opened at the front end of the intermediate block, the second support frame is slidably arranged inside the front end groove, and the balance bar is arranged between the connected second support frames.

[0014] The beneficial effects of the drone with a buffer structure of the utility model are as follows: the drone can effectively alleviate the impact force caused by the drone descending to the ground, avoiding accidents such as the drone being damaged by excessive impact force caused by pilot error causing the drone to descend too quickly. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the following briefly introduces the drawings required for the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative labor. Among them:

[0016] Figure 1 The utility model is a schematic diagram of the overall structure of the UAV with a buffer structure.

[0017] Figure 2 It is a left side cross-sectional view of the UAV with a buffer structure according to the present invention.

[0018] Figure 3 It is a partial structural schematic diagram of the UAV with a buffer structure of the utility model.

[0019] Figure 4 This is another left side cross-sectional view of the UAV with a buffer structure according to the present invention.

[0020] Reference numerals: 1, machine bottom; 2, deceleration module; 21, first connecting seat; 22, rotating module; 22a, loose leaf; 22b, wind blocking plate; 22c, limit block; 23, wind gathering module; 23a, wind gathering plate; 23b, wind induction block; 23c, opening slot; 24, airbag module; 24a, air inlet slot; 24b, canvas; 24c, air outlet; 25, fuselage; 3, buffer module; 31, folding spring; 32 , sliding module; 32a, rotating spring; 32b, rotating slot; 32c, rotating block; 33, folding module; 33a, first supporting frame; 33b, second supporting frame; 33c, folding slot; 33d, folding column; 33e, bracket block; 34, air cylinder; 35, folding module; 35a, bottom block; 35b, middle block; 35c, middle slot; 35d, air nozzle; 35e, front end slot; 35f, balance bar. DETAILED DESCRIPTION

[0021] In order to make the above-mentioned purposes, features and advantages of the present invention more obvious and easy to understand, the specific implementation methods of the present invention are described in detail below in conjunction with the accompanying drawings.

[0022] In the following description, many specific details are set forth to facilitate a full understanding of the present invention, but the present invention may also be implemented in other ways different from those described herein, and those skilled in the art may make similar generalizations without violating the connotation of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0023] Secondly, the term "one embodiment" or "embodiment" as used herein refers to a specific feature, structure or characteristic that may be included in at least one implementation of the present invention. The term "in one embodiment" that appears in different places in this specification does not necessarily refer to the same embodiment, nor does it refer to a separate or selective embodiment that is mutually exclusive with other embodiments.

[0024] Secondly, the present invention is described in detail with reference to the schematic diagram. When describing the embodiments of the present invention, for the sake of convenience, the cross-sectional diagrams showing the device structure will not be partially enlarged according to the general scale, and the schematic diagrams are only examples, which should not limit the scope of protection of the present invention. In addition, in actual production, the three-dimensional dimensions of length, width and depth should be included.

[0025] Example 1

[0026] Reference Figures 1 to 4, which is the first embodiment of the utility model, and the embodiment provides a drone with a buffer structure, including a machine bottom 1, a deceleration module 2, including a first connecting seat 21, a rotating module 22, a wind gathering module 23, an airbag module 24, and a fuselage 25, wherein the first connecting seat 21 is fixedly installed at the bottom end of the machine bottom 1, the rotating module 22 is respectively arranged at both ends of the fuselage 25, the wind gathering module 23 is arranged at the bottom end of the rotating module 22, the airbag module 24 is arranged at the lower end of the rotating module 22, and the airbag module 24 is arranged at the upper end of the wind gathering module 23, the buffer module 3, including a folding spring 31, a sliding module 32, a folding module 33, an air cylinder 34, and a force reduction module 35, the folding spring 31 is arranged at the bottom end of the machine bottom 1, the sliding module 32 is arranged on the outside of the folding spring 31, the folding module 33 is arranged at the side end of the sliding module 32, and the force reduction module The block 35 is arranged at the lower end of the folding module 33, and the air cylinder 34 is arranged at the bottom end of the force reduction module 35. When the drone in the air needs to descend to the ground, the wind blows from the wind gathering module 23 on the fuselage 25 from bottom to top, driving the rotating module 22 to flip upward to increase the resistance of the drone when it descends. At the same time, the wind blowing from bottom to top will also pass through the wind gathering module 23 and blow into the airbag module 24 to increase the resistance of the drone when it descends, so that the descent speed of the drone slows down, preventing the drone from being damaged due to a hard landing at too fast a speed due to operational errors by the pilot. At the same time, when the drone descends to the ground, the force reduction module 25 is forced to shrink, blowing the gathered wind upward to give the drone a certain resistance, slowing down its speed when it contacts the ground. At the same time, the folding module 33 drives the sliding module 32 to flip, alleviating the impact force brought to the drone by the ground, thereby achieving the purpose of protecting the drone.

[0027] Specifically, the rotating module 22 includes a loose-leaf 22a, a wind blocking plate 22b, and a limit block 22c. The loose-leaf 22a is rotatably arranged at both ends of the UAV fuselage, the wind blocking plate 22b is rotatably arranged on the loose-leaf, and the limit block 22c is fixedly arranged at the upper end of the wind blocking plate 22b. The wind gathering module 23 includes a wind gathering plate 23a, a wind inducing block 23b, and an opening groove 23c. The wind gathering plate 23a is respectively fixed at both ends of the UAV fuselage, and the wind inducing block 23b is fixedly arranged inside the wind gathering plate 23a. The opening slot 23c is provided at the upper and lower ends of the wind gathering plate 23a, the wind inlet at the lower end of the wind induction block 23b is 70 degrees, and the wind outlet at the upper end is 45 degrees. The airbag module 24 includes an air inlet slot 24a, a canvas 24b, and an air outlet 24c. The air inlet slot 24a is provided at the lower end of the loose-leaf 22a, and the air inlet slot 24a runs through the fuselage 25 and the top of the drone. The canvas 24b is fixedly arranged at the upper end of the air inlet slot 24a, and the air outlet 24c is provided at the front end of the canvas 24b. When the drone descends, the airbag module 24a is formed. The generated wind moves from the open groove 23c at the bottom of the wind gathering plate 23a to the upper end along the wind guide block 23b (in order to make it easier for the wind to flow into the wind gathering plate 23a when the drone descends, the lower end of the wind guide plate is set to 70°), and then the upward moving wind blows the wind blocking plate 22b (in order for the gas blown upward along the wind guide block 23b to reach the approximate middle position of the wind blocking plate 22b, the upper end of the wind blocking plate 23b is set to 45°), and the wind blocking plate 22b moves to the upper end along the loose-leaf until the lower end of the limit block 22c, thereby expanding the area of ​​the drone and achieving the purpose of slowing down the descent speed of the drone. At the same time, the wind moving upward along the wind guide plate 23b will pass through the air inlet groove 24a and reach the inside of the canvas 24b, filling and expanding the inside of the canvas 24b (the canvas 24b is distributed at the four corners around the top of the drone to delay the work of the drone as little as possible), and then flows out from the air outlet 24c to cooperate with the wind blocking plate 22b to slow down the descent speed of the drone.

[0028] Example 2

[0029] Reference Figures 1 to 4As shown, it is the second embodiment of the utility model, which is different from the previous embodiment in that: the sliding module 32 includes a rotating spring 32a, a rotating slot 32b, and a rotating block 32c, the rotating slot 32b is arranged inside the folding spring 31, the rotating spring 32a is fixedly arranged at the top of the rotating slot 32b, the rotating block 32c is fixedly arranged at the bottom of the rotating spring 32a, and the rotating block 32c is slidably arranged inside the rotating slot 32b, and the folding module 33 includes a first support frame 33a, a second support frame 33b, a folding slot 33c, a folding column 33d, and a bracket block 33e, the first support frame 33a is fixedly arranged at the bottom of the rotating block 32c, the folding slot 33c is arranged at the bottom of the first support frame 33a, the support column 33d is fixedly arranged inside the folding slot 33c, and the second support frame 33b is rotatably arranged When the second support frame 33b moves upward, the folding groove 33c at the bottom of the first support frame 33a cooperates with the folding column 33d to make the first support frame 33a and the second support frame 33b flip over, thereby reducing the impact force brought by the ground. At the same time, the rotating block 32c at the upper end of the first support frame 33a slides along the rotating empty groove 32b to achieve the purpose of reducing the impact force brought by the ground again, and then resets under the action of the rotating spring 32a and the folding spring 31, so that the drone stops stably on the ground.

[0030] Furthermore, the force reduction module 35 includes a bottom block 35a, an intermediate block 35b, an intermediate groove 35c, an air nozzle 35d, a front end groove 35e, and a balance rod 35f. The intermediate block 35b is slidably arranged at the bottom end of the bracket block 33e, the intermediate groove 35c is opened inside the intermediate block 35b, the bottom block 35a is fixedly arranged inside the intermediate groove 35c, the air cylinder 34 is fixedly arranged at the lower end of the bottom block 35a, the air nozzle 35d at the upper end of the air cylinder 34 passes through the bottom block 35a, and the air nozzle 35d is arranged at the upper end of the bottom block 35a, and the front end groove 35e is opened at the intermediate block 33e. 5b front end, the second support frame 33b is slidably set inside the front end groove 35e, the balance bar 35f is set between the connected second support frames 33b, and the middle block 35b is set on the outer side of the bottom end of the support block 33e. When the UAV descends to touch the ground, the ground first contacts the lowermost air cylinder 34a. As the UAV descends, the support block 33e contacts the bottom block 35a and then squeezes the air cylinder 34, so that the air cylinder 34 releases gas through the air nozzle in the bottom block 35a to push the support block 33e upward, thereby reducing the impact force on the UAV again.

[0031] The working principle of the utility model is as follows: the wind formed when the drone descends moves from the open groove 23c at the bottom of the wind gathering plate 23a to the upper end along the wind guide block 23b, and then the wind moving upward blows the wind blocking plate 22b, and the wind blocking plate 22b moves to the upper end along the loose-leaf until the lower end of the limit block 22c, thereby expanding the area of ​​the drone and achieving the purpose of slowing down the descent speed of the drone. At the same time, the wind moving upward along the wind guide plate 23b will pass through the air inlet groove 24a and reach the inside of the canvas 24b, filling and expanding the inside of the canvas 24b, and then flow out from the air outlet 24c to cooperate with the wind blocking plate 22b to slow down the descent speed of the drone. When the drone descends to touch the ground, the ground first touches the lowest air cylinder 34a, and as the drone descends, the bracket block 33e contacts the bottom block 35a and then squeezes the air The cylinder 34 releases gas through the air nozzle in the bottom block 35a to push the support block 33e upward, thereby reducing the impact force on the drone again. Then the bottom block 35a pushes the support block 33e to move upward, thereby driving the second support frame 33b to move upward. When the second support frame 33b moves upward, the folding groove 33c at the bottom of the first support frame 33a cooperates with the folding column 33d to make the first support frame 33a and the second support frame 33b flip over, thereby reducing the impact force brought by the ground. At the same time, the rotating block 32c at the upper end of the first support frame 33a slides along the rotating empty groove 32b to achieve the purpose of reducing the impact force brought by the ground again, and then resets under the action of the rotating spring 32a and the folding spring 31, so that the drone is stably stopped on the ground.

[0032] It will be appreciated that in the development of any actual implementation, as in any engineering or design project, numerous implementation-specific decisions may be made. Such a development effort may be complex and time-consuming, but will be a routine task of design, fabrication, and production for those of ordinary skill having the benefit of this disclosure without undue experimentation.

[0033] It should be noted that the above embodiments are only used to illustrate the technical solution of the utility model rather than to limit it. Although the utility model has been described in detail with reference to the preferred embodiments, ordinary technicians in the field should understand that the technical solution of the utility model can be modified or replaced by equivalents without departing from the spirit and scope of the technical solution of the utility model, which should be included in the scope of the claims of the utility model.

Claims

1. A UAV with a buffer structure, characterized in that: include, Bottom of the machine (1); The deceleration module (2) comprises a first connection seat (21), a rotation module (22), a wind gathering module (23), an airbag module (24), and a fuselage (25), wherein the first connection seat (21) is fixedly mounted on the bottom end of the machine base (1), the rotation module (22) is respectively arranged at two ends of the fuselage (25), the wind gathering module (23) is arranged at the bottom end of the rotation module (22), the airbag module (24) is arranged at the lower end of the rotation module (22), and the airbag module (24) is arranged at the upper end of the wind gathering module (23); The buffer module (3) comprises a folding spring (31), a sliding module (32), a folding module (33), an air cylinder (34), and a force reduction module (35), wherein the folding spring (31) is arranged at the bottom end of the machine bottom (1), the sliding module (32) is arranged at the outside of the folding spring (31), the folding module (33) is arranged at the side end of the sliding module (32), the force reduction module (35) is arranged at the lower end of the folding module (33), and the air cylinder (34) is arranged at the bottom end of the force reduction module (35).

2. The UAV with a buffer structure according to claim 1, characterized in that: The rotating module (22) comprises a loose leaf (22a), a wind blocking plate (22b), and a limit block (22c); the loose leaf (22a) is rotatably arranged at two ends of the drone fuselage; the wind blocking plate (22b) is rotatably arranged on the loose leaf; and the limit block (22c) is fixedly arranged at the upper end of the wind blocking plate (22b).

3. The UAV with a buffer structure according to claim 2, characterized in that: The wind gathering module (23) comprises a wind gathering plate (23a), an air induction block (23b), and an opening slot (23c); the wind gathering plate (23a) is respectively fixed to two ends of the drone fuselage; the air induction block (23b) is fixedly arranged inside the wind gathering plate (23a); the opening slot (23c) is provided at the upper and lower ends of the wind gathering plate (23a); the wind inlet at the lower end of the wind induction block (23b) is 70 degrees, and the wind outlet at the upper end is 45 degrees.

4. The UAV with a buffer structure according to claim 2 or 3, characterized in that: The airbag module (24) comprises an air inlet groove (24a), a canvas (24b), and an air outlet (24c); the air inlet groove (24a) is opened at the lower end of the hinge (22a); the air inlet groove (24a) runs through the fuselage (25) and the top of the drone; the canvas (24b) is fixedly arranged at the upper end of the air inlet groove (24a); and the air outlet (24c) is opened at the front end of the canvas (24b).

5. The UAV with a buffer structure according to claim 4, characterized in that: The sliding module (32) comprises a rotating spring (32a), a rotating slot (32b), and a rotating block (32c); the rotating slot (32b) is opened inside the folding spring (31); the rotating spring (32a) is fixedly arranged at the top of the rotating slot (32b); the rotating block (32c) is fixedly arranged at the bottom of the rotating spring (32a); and the rotating block (32c) is slidably arranged inside the rotating slot (32b).

6. The UAV with a buffer structure according to claim 5, characterized in that: The folding module (33) comprises a first support frame (33a), a second support frame (33b), a folding groove (33c), a folding column (33d), and a bracket block (33e), wherein the first support frame (33a) is fixedly arranged at the bottom end of the rotating block (32c), the folding groove (33c) is opened at the bottom end of the first support frame (33a), the folding column (33d) is fixedly arranged inside the folding groove (33c), the second support frame (33b) is rotatably arranged in the folding groove (33c), and the second support frame (33b) is rotatably arranged outside the folding column (33d), and the bracket block (33e) is fixedly arranged at the bottom end of the second support frame (33b).

7. The UAV with a buffer structure according to claim 6, characterized in that: The force reduction module (35) comprises a bottom block (35a), an intermediate block (35b), an intermediate groove (35c), an air nozzle (35d), a front end groove (35e), and a balance bar (35f); the intermediate block (35b) is slidably arranged at the bottom end of the bracket block (33e); the intermediate groove (35c) is opened inside the intermediate block (35b); the bottom block (35a) is fixedly arranged inside the intermediate groove (35c); the air cylinder (34) is fixedly arranged at the lower end of the bottom block (35a); the air nozzle (35d) at the upper end of the air cylinder (34) penetrates the bottom block (35a), and the air nozzle (35d) is arranged at the upper end of the bottom block (35a); the front end groove (35e) is opened at the front end of the intermediate block (35b); the second support frame (33b) is slidably arranged inside the front end groove (35e); and the balance bar (35f) is arranged between the connected second support frames (33b).

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