An unmanned aerial vehicle with a flexible connection mechanism

Abstract

The utility model discloses a kind of unmanned aerial vehicle with flexible connecting mechanism, unmanned aerial vehicle includes: fuselage, engine and several flexible connecting mechanisms;Flexible connecting mechanism includes: mounting plate assembly and support column, mounting plate assembly includes the first mounting plate and the second mounting plate of parallel arrangement, support column is set between the first mounting plate and the second mounting plate, buffer assembly is provided in mounting plate assembly, buffer assembly includes first buffer and second buffer, the end face middle part of first buffer is protruded and forms insertion shaft sleeve, second buffer is provided with cooperation slot hole, second buffer is based on cooperation slot hole and is connected on first buffer;First buffer and second buffer form the preset interval of accommodating board between them. By setting buffer assembly at the both ends of support column, prolongs buffering stroke, effectively improves the absorption capacity of flexible connecting mechanism to engine working vibration, reduces the influence of engine vibration, prolongs the service life of unmanned aerial vehicle body structure.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) structural technology, specifically to a UAV with a flexible connection mechanism. Background Technology

[0002] The engine is one of the power components of a drone, providing power to the drone's rotor. Since the engine vibrates during operation, the connection structure between the engine and the drone fuselage needs to have a certain buffering capacity to reduce the impact of engine vibration on the drone fuselage. Patent application CN 215622739 U discloses a thrust system and an electric aircraft, which discloses that an elastic element and a bushing are used to form a buffer structure at the connection between the motor and the bracket to buffer the vibration of the motor. However, this buffer mechanism has a short buffer stroke and its vibration absorption and filtering are limited, affecting the service life of the drone fuselage structure. Utility Model Content

[0003] The purpose of this utility model is to overcome the shortcomings of the prior art. This utility model provides a drone with a flexible connection mechanism. By setting buffer components at both ends of the support column, the flexible connection mechanism can improve its ability to absorb engine vibration and extend the buffer stroke. This can significantly reduce the impact of engine vibration on the drone fuselage and extend the service life of the drone fuselage structure.

[0004] This utility model provides a drone with a flexible connection mechanism. The drone includes: a fuselage, an engine, and a plurality of flexible connection mechanisms disposed between the fuselage and the engine.

[0005] The flexible connection mechanism includes: a mounting plate assembly and a support column, wherein the mounting plate assembly includes a first mounting plate and a second mounting plate arranged in parallel, and the support column is disposed between the first mounting plate and the second mounting plate;

[0006] The mounting plate assembly is provided with a buffer assembly, which includes a first buffer and a second buffer. The first buffer has a protrusion at the middle of one end face to form a plug-in bushing. The second buffer has a mating slot and is sleeved on the first buffer based on the mating slot.

[0007] A preset gap for accommodating the plate is formed between the first buffer member and the second buffer member. One end of the support column abuts against the buffer assembly of the first mounting plate, and the other end of the support column abuts against the buffer assembly of the second mounting plate.

[0008] Furthermore, the insertion bushing of the first buffer member is provided with a first toothed surface and a second toothed surface;

[0009] The first toothed surface is disposed on the outer circumferential wall of the insert bushing, and the second toothed surface is disposed on the inner wall of the slot of the insert bushing.

[0010] Furthermore, the end face of the first buffer member is provided with a third toothed surface, and the groove of the insertion bushing is provided with a transition section.

[0011] The transition section is disposed between the second tooth profile and the third tooth profile.

[0012] Furthermore, the second buffer is configured as a ring structure, with the mating slot formed in the middle of the ring structure.

[0013] Furthermore, one end face of the second buffer member is provided with a fourth toothed surface, and the end face of the support column abuts against the fourth toothed surface.

[0014] Furthermore, the other end face of the second buffer member is provided with a fifth toothed surface, and a plurality of racks on the fourth toothed surface and a plurality of racks on the fifth toothed surface are staggered.

[0015] Furthermore, the flexible connection mechanism also includes bolts, and the support column and the buffer assembly cooperate to form a connecting through groove for installing the bolts.

[0016] Furthermore, the flexible connection mechanism also includes a gasket disposed between the bolt and the second buffer member.

[0017] Furthermore, the flexible connection mechanism also includes a locking nut, which is threaded onto one end of the bolt.

[0018] Furthermore, the buffer component is made of rubber.

[0019] This invention provides a drone with a flexible connection mechanism. A buffer component and a support column are arranged between two mounting plates to form a flexible connection mechanism. The buffer stroke of the flexible connection mechanism can be extended based on the support column, thereby reducing the impact of engine vibration on the drone fuselage. By setting a first buffer and a second buffer component to cooperate, the first buffer component forms an insert bushing, which enables the first buffer component to absorb and deform radial vibration forces. Based on the cooperation of the first buffer and the second buffer component, the axial buffering performance of the buffer component is improved, which can reduce the transmission of engine vibration to the drone fuselage, thereby reducing the impact of engine vibration on the drone fuselage structure and extending the service life of the drone fuselage structure. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0021] Figure 1 This is a schematic diagram of the structure of the UAV with a flexible connection mechanism in an embodiment of this utility model;

[0022] Figure 2 This is an example of the embodiments of this utility model. Figure 1 Enlarged schematic diagram of the structure at point A;

[0023] Figure 3 This is an exploded view of the flexible connection mechanism in an embodiment of this utility model;

[0024] Figure 4 This is an exploded view of the structure of the support column and buffer assembly in an embodiment of this utility model;

[0025] Figure 5 This is a schematic diagram of the structure of the first buffer component in an embodiment of this utility model;

[0026] Figure 6 This is a cross-sectional view of the structure of the first buffer component in an embodiment of this utility model;

[0027] Figure 7 This is a schematic diagram of the structure of the second buffer component in an embodiment of this utility model. Detailed Implementation

[0028] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of the present utility model.

[0029] refer to Figures 1 to 7 This utility model provides a structural diagram of a drone with a flexible connection mechanism. The drone includes a fuselage 10, an engine 20, and a plurality of flexible connection mechanisms disposed between the fuselage 10 and the engine 20. In this embodiment, the engine 20 is disposed at the front end of the drone fuselage 10. The engine 20 drives the propellers at the front end of the drone fuselage 10 to rotate, providing traction for the drone's flight.

[0030] The flexible connection mechanism includes a mounting plate assembly and a support column 1. The mounting plate assembly includes a first mounting plate 6 and a second mounting plate 7 arranged in parallel. The support column 1 is disposed between the first mounting plate 6 and the second mounting plate 7. The first mounting plate 6 is fixed to the front end of the UAV fuselage 10. The engine 20 is mounted and fixed on the second mounting plate 7. Based on several flexible connection mechanisms, a long-distance buffer structure is formed between the first mounting plate 6 and the second mounting plate 7, so that the vibration generated by the engine 20 on the second mounting plate 7 during operation can be buffered and absorbed based on the buffer structure, reducing the impact of the engine 20's operating vibration on the UAV structure.

[0031] Specifically, the mounting plate assembly includes a buffer component 2, which comprises a first buffer member 21 and a second buffer member 22. A protruding insert sleeve 211 is formed at the center of one end face of the first buffer member 21. The second buffer member 22 has a mating groove and is fitted onto the first buffer member 21 based on the mating groove. The first buffer member 21 is located on one side of the first mounting plate 6, and the second buffer member 22 is located on the other side of the first mounting plate 6. A preset distance for accommodating the plate is formed between the first buffer member 21 and the second buffer member 22, allowing the first mounting plate 6 to be located within the preset distance. The buffer component 2 is positioned at the mounting hole of the first mounting plate 6. The insert sleeve 211 of the first buffer member 21 passes through the mounting hole, allowing the first buffer member 21 and the second buffer member 22 to cooperate and form the buffer component 2 on the mounting hole of the first mounting plate 6, thus meeting the buffer structure requirements of the flexible connection mechanism.

[0032] Furthermore, the buffer component 2 on the second mounting plate 7 is configured in the same way as the buffer component 2 on the first mounting plate 6, and will not be described in detail here.

[0033] Specifically, one end of the support column 1 abuts against the buffer component 2 of the first mounting plate 6, and the other end of the support column 1 abuts against the buffer component 2 of the second mounting plate 7. The material of the support column 1 can be the same as that of the buffer component 2. Based on the support column 1, the overall buffering performance of the flexible connection mechanism can be improved, and the stability of the structural fit between the first mounting plate 6 and the second mounting plate 7 can be effectively improved.

[0034] By setting the buffer assembly 2 on the first mounting plate 6 and the second mounting plate 7, the buffer assembly 2 can form a buffer base on the mounting plate and form a flexible connection mechanism with the support rod. This can extend the force transmission path between the UAV engine 20 and the UAV fuselage 10, thereby improving the effective buffer path between the UAV engine 20 and the UAV fuselage 10 and improving the structural connection stability of the UAV.

[0035] Specifically, the insertion bushing 211 of the first buffer member 21 is provided with a first toothed surface 2111 and a second toothed surface 2112; the first toothed surface 2111 is disposed on the outer circumferential wall of the insertion bushing 211, and the second toothed surface 2112 is disposed on the inner wall of the slot of the insertion bushing 211. Based on the first toothed surface 2111 and the second toothed surface 2112, the axial deformation capability of the flexible connection mechanism can be improved, so that the first buffer member 21 and the second buffer member 22 have good bushing support capability, and the connection position between the buffer assembly 2 and the mounting plate can have good buffer absorption capability. The first buffer member 21 deforms when subjected to vibration based on the first toothed surface 2111 and the second toothed surface 2112, realizing the force transmission absorption and buffering of the vibration of the engine 20 workstation, so that the high-frequency vibration of the engine 20 during operation can be converted into the deformation and deformation recovery process of the first buffer member 21, effectively improving the buffering effect of the UAV.

[0036] Specifically, the end face of the first buffer member 21 is provided with a third toothed surface, and the groove of the insertion bushing 211 is provided with a transition section 2113. The transition section 2113 is located between the second toothed surface 2112 and the third toothed surface. The third toothed surface is perpendicular to the insertion bushing 211, so that the third toothed surface can meet the axial force absorption deformation of the first buffer member 21, that is, improve the axial buffering capacity of the first buffer member 21.

[0037] Furthermore, the second buffer 22 is configured as an annular structure, with the mating groove formed in the middle of the annular structure, so that the second buffer 22 can be sleeved on the insertion bushing 211 of the first buffer 21, and cooperate with the first buffer 21 to form a buffer assembly 2 mounted on the mounting hole position of the mounting plate assembly, thereby improving the buffering capacity of the flexible connection mechanism.

[0038] Specifically, one end face of the second buffer member 22 is provided with a fourth toothed surface 221, and the end face of the support column 1 abuts against the fourth toothed surface 221. The second buffer member 22 contacts the end face of the support column 1 based on the fourth toothed surface 221, so that the axial vibration transmitted by the support column 1 can be buffered and absorbed based on the rack structure of the fourth toothed surface 221. The other end face of the second buffer member 22 is provided with a fifth toothed surface 222. Several racks of the fourth toothed surface 221 and several racks of the fifth toothed surface 222 are staggered. When the second buffer member 22 is subjected to axial vibration pressure, the racks between the fourth toothed surface 221 and the fifth toothed surface 222 can deform based on the space reserved by the staggered arrangement, thereby improving the absorption performance of the fourth toothed surface 221 and the fifth toothed surface 222 for axial vibration.

[0039] Furthermore, a connecting portion 11 is provided at any end of the support column 1. The wire diameter of the connecting portion 11 gradually increases along the end face direction, so that the end face size of the support column 1 is larger than the column body cross-sectional size of the support column 1, and the end face size of the support column 1 matches the end face size of the second buffer member 22. The support column 1 achieves a tight connection with the buffer assembly 2 of the first mounting plate 6 and the buffer assembly 2 of the second mounting plate 7 based on the connecting portion 11, so as to satisfy the setting of the flexible connection mechanism between the engine 20 and the UAV fuselage 10.

[0040] Specifically, the flexible connection mechanism also includes a bolt 4. The support column 1 and the buffer assembly 2 cooperate to form a connecting slot for installing the bolt 4. The bolt 4 is inserted into the connecting slot. Based on the bolt 4, the buffer assembly 2 and the support column 1 are connected in series for support, so that the flexible connection mechanism forms an integral structure to meet the installation connection between the UAV fuselage 10 and the engine 20.

[0041] Furthermore, the flexible connection mechanism also includes a gasket 3, which is disposed between the bolt 4 and the second buffer 22. The gasket 3 is used to protect the second buffer 22, reduce frictional damage between the bolt 4 and the second buffer 22, ensure the structural stability and safety of the second buffer 22, ensure that the buffer assembly 2 has good vibration absorption performance, and extend the service life of the buffer assembly 2.

[0042] Specifically, the flexible connection mechanism also includes a locking nut 5, which is threaded onto one end of the bolt 4. Through the cooperation of the bolt 4 and the locking nut 5, the bolt 4 can connect and fix the first mounting plate 6 and the second mounting plate 7, and form a flexible connection mechanism between the first mounting plate 6 and the second mounting plate 7, which is composed of the buffer component 2 and the support column 1. This satisfies the flexible connection requirements between the first mounting plate 6 and the second mounting plate 7, absorbs the operating vibration of the engine 20, and reduces the impact of the engine 20 vibration on the structure of the UAV fuselage 10.

[0043] Furthermore, the buffer component 2 is made of rubber, which has good deformation capacity and can effectively absorb the kinetic energy of the engine 20's operating vibration, reducing the impact of the engine 20's operating vibration. The rubber material has good elastic deformation capacity and good contact friction, which improves the structural stability of the buffer component 2 and also meets the flexible buffering energy absorption effect of the flexible connection mechanism.

[0044] This utility model embodiment provides a drone with a flexible connection mechanism. A buffer assembly 2 and a support column 1 are arranged between two mounting plates to form a flexible connection mechanism. The buffer stroke of the flexible connection mechanism can be extended based on the support column 1, thereby reducing the impact of engine 20 operating vibration on the drone fuselage 10. By setting a first buffer 21 and a second buffer 22 to cooperate, a plug-in bushing 211 is formed in the first buffer 21, so that the first buffer 21 can absorb and deform radial vibration force. Based on the cooperation of the first buffer 21 and the second buffer 22, the axial buffering performance of the buffer assembly 2 is improved, which can reduce the vibration transmission from the engine 20 to the drone fuselage 10, thereby reducing the impact of engine 20 vibration on the structure of the drone fuselage 10 and extending the service life of the drone body structure.

[0045] Furthermore, the above provides a detailed description of a drone with a flexible connection mechanism provided by the embodiments of this utility model. Specific examples have been used to illustrate the principle and implementation of this utility model. The description of the above embodiments is only for the purpose of helping to understand the method and core idea of ​​this utility model. At the same time, for those skilled in the art, there will be changes in the specific implementation and application scope based on the idea of ​​this utility model. Therefore, the content of this specification should not be construed as a limitation of this utility model.

Claims

1. An unmanned aerial vehicle with a flexible connection mechanism, characterized in that, The drone includes: a fuselage, an engine, and several flexible connecting mechanisms disposed between the fuselage and the engine; The flexible connection mechanism includes: a mounting plate assembly and a support column, wherein the mounting plate assembly includes a first mounting plate and a second mounting plate arranged in parallel, and the support column is disposed between the first mounting plate and the second mounting plate; The mounting plate assembly is provided with a buffer assembly, which includes a first buffer and a second buffer. The first buffer has a protrusion at the middle of one end face to form a plug-in bushing. The second buffer has a mating slot and is sleeved on the first buffer based on the mating slot. A preset gap for accommodating the plate is formed between the first buffer member and the second buffer member. One end of the support column abuts against the buffer assembly of the first mounting plate, and the other end of the support column abuts against the buffer assembly of the second mounting plate.

2. The UAV with a flexible connection mechanism as described in claim 1, characterized in that, The first buffer member's insertion bushing is provided with a first toothed surface and a second toothed surface; The first toothed surface is disposed on the outer circumferential wall of the insert bushing, and the second toothed surface is disposed on the inner wall of the slot of the insert bushing.

3. The UAV with a flexible connection mechanism as described in claim 2, characterized in that, The end face of the first buffer member is provided with a third toothed surface, and the groove of the insertion bushing is provided with a transition section; The transition section is disposed between the second tooth profile and the third tooth profile.

4. The UAV with a flexible connection mechanism as described in claim 1, characterized in that, The second buffer is configured as a ring structure, and the mating slot is formed in the middle of the ring structure.

5. The UAV with a flexible connection mechanism as described in claim 1, characterized in that, The second buffer member has a fourth toothed surface on one end face, and the end face of the support column abuts against the fourth toothed surface.

6. The UAV with a flexible connection mechanism as described in claim 5, characterized in that, The other end face of the second buffer member is provided with a fifth toothed surface, and several racks of the fourth toothed surface and several racks of the fifth toothed surface are staggered.

7. The UAV with a flexible connection mechanism as described in claim 1, characterized in that, The flexible connection mechanism also includes bolts, and the support column and the buffer assembly cooperate to form a connecting through groove for installing the bolts.

8. The UAV with a flexible connection mechanism as described in claim 7, characterized in that, The flexible connection mechanism further includes a gasket disposed between the bolt and the second buffer member.

9. The UAV with a flexible connection mechanism as described in claim 8, characterized in that, The flexible connection mechanism also includes a locking nut, which is threaded onto one end of the bolt.

10. The UAV with a flexible connection mechanism as described in claim 1, characterized in that, The buffer component is made of rubber.

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