Multi-rotor unmanned aerial vehicle fuselage structure

Abstract

The utility model provides a fuselage structure of a multi-rotor unmanned aerial vehicle. The fuselage structure comprises a fuselage main frame and a plurality of fuselage battery frames arranged outside the fuselage main frame in a surrounding mode. The fuselage battery frame comprises a plurality of framework assemblies and a plurality of sealing plate assemblies; according to the fuselage structure of the multi-rotor unmanned aerial vehicle, the air outlet holes in the two sides of the rotor arm pipes are matched with the air inlet holes in the sealing plate B, negative pressure airflow generated by the rotors is utilized, cold air can enter the interior of a fuselage battery frame through the air inlet holes, heat generated by electronic elements is taken away, the heat is discharged through the air outlet holes, and therefore the efficient heat dissipation effect is achieved; and the stable performance of internal electronic components in the long-time operation process is effectively guaranteed.

Description

TECHNICAL FIELD

[0001] The utility model relates to unmanned plane technical field, concretely relates to a multirotor unmanned plane fuselage structure. BACKGROUND

[0002] With the rapid development of unmanned plane technology, multirotor unmanned plane has been widely applied in aerial photography, agricultural plant protection, surveying and mapping, logistics distribution and many other fields. The fuselage structure of multirotor unmanned plane is the key part of bearing each component and ensuring its stable flight, and its performance directly affects the overall performance of unmanned plane.

[0003] The traditional multirotor unmanned plane fuselage structure often has the problem that strength and weight are difficult to balance, part of fuselage structure is easy to be damaged when flying in complex environment or being impacted by external force, and also has the deficiency in heat dissipation, equipment installation convenience and the like. For example, the fuselage lacks effective heat dissipation design, and the internal electronic components are easy to be degraded in performance or even damaged due to overheating when the unmanned plane runs for a long time. Therefore, it is necessary to develop a new type of multirotor unmanned plane fuselage structure to overcome the above-mentioned defects. SUMMARY

[0004] The utility model provides a multirotor unmanned plane fuselage structure, solved the fuselage of prior art lacks effective heat dissipation design, when the unmanned plane runs for a long time, internal electronic components are easy to be degraded in performance or even damaged due to overheating.

[0005] The technical scheme of the utility model is realized as follows:

[0006] A multirotor unmanned plane fuselage structure, including fuselage main frame and surrounding the multiple fuselage battery frames arranged outside it, the fuselage battery frame includes multiple skeleton assemblies and multiple sealing plate assemblies, wherein the skeleton assembly includes rectangular rotor arm pipe, each side of the polygonal frame is respectively provided with mounting port, and one end of the rotor arm pipe is inserted into the mounting port and fixed through bolt, the sealing plate assembly includes sealing plate A, sealing plate B and slot keel, sealing plate A and sealing plate B are respectively arranged on the upper and lower sides of the adjacent two rotor arm pipes and fixed through bolt, wherein the slot keel faces the fuselage main frame, and the slot edge of the slot keel is fixed at the end between sealing plate A and sealing plate B through bolt, the both sides of the rotor arm pipe are respectively provided with multiple air outlet holes corresponding to sealing plate A and sealing plate B, the middle of sealing plate B is provided with multiple air inlet holes, and the negative pressure airflow generated by the rotor makes cold air enter the fuselage battery frame through the air inlet hole and discharge through the air outlet hole.

[0007] Further, it further includes the positioning structure corresponding to each rotor arm pipe, and the positioning structure includes the T-shaped block fixed between the adjacent sealing plate B, and the T-shaped block fixes the sealing plate B on the rotor arm pipe through bolt.

[0008] Further, the positioning structure further comprises two positioning blocks respectively arranged at the adjacent positions of the two sealing plates B, and the bottoms of the two positioning blocks are fixed with a semicircular shock-absorbing sleeve surrounding the landing gear through bolts.

[0009] Further, the skeleton assembly further comprises a plurality of fastening rings for fixing the rotor arm, and the outer part of the fastening ring is polygonal and is fixed on the inner wall of the rotor arm pipe through bolts.

[0010] Further, the sealing plate A and the sealing plate B are fan-shaped, and the adjacent sealing plate A and the adjacent sealing plate B are arranged in parallel with each other through the fan-shaped bevels; wherein the side of the sealing plate A and the sealing plate B close to the polygonal frame is concave, and corresponds to the adjacent two sides and the corners of the polygonal frame.

[0011] The technical scheme provided by the application has the beneficial effects that:

[0012] The air outlet holes on both sides of the rotor arm pipe and the air inlet holes in the sealing plate B are matched with each other, the negative pressure airflow generated by the rotor is used to make the cold air enter the inside of the battery frame of the machine body through the air inlet holes, take away the heat generated by the electronic elements, and is discharged through the air outlet holes, so that the high-efficiency heat dissipation effect is realized, and the performance stability of the internal electronic elements in the long-time operation process is effectively ensured. BRIEF DESCRIPTION OF DRAWINGS

[0013] In order to more clearly illustrate the technical scheme in the embodiments of the present application or the prior art, the drawings needed to be used in the following embodiment or prior art description will be briefly introduced. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can also be obtained by those skilled in the art without creative labor.

[0014] Fig. 1 It is a front view of the machine body structure of the multi-rotor unmanned aerial vehicle of the present application.

[0015] Fig. 2 It is a back view of the machine body structure of the multi-rotor unmanned aerial vehicle of the present application.

[0016] Fig. 3 It is a partial view of the machine body structure of the multi-rotor unmanned aerial vehicle of the present application.

[0017] In the figure: 10 is a machine body main frame, 11 is a mounting port, 12 is a heat dissipation fin, 20 is a skeleton assembly, 21 is a rotor arm pipe, 22 is a fastening ring, 23 is an air outlet hole, 30 is a sealing plate assembly, 31 is a sealing plate A, 32 is a groove keel, 33 is a sealing plate B, 34 is an air inlet hole, 40 is a positioning structure, 41 is a T-shaped block, 42 is a positioning block, and 43 is a semicircular shock-absorbing sleeve. DETAILED DESCRIPTION

[0018] The technical solutions of the utility model will be clearly and completely described below in combination with the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments of the utility model, all other embodiments obtained by the ordinary skilled in the art without creative labor belong to the protection scope of the utility model.

[0019] Referring to Figs. 1-3 A multi-rotor unmanned aerial vehicle body structure, comprising a body main frame 10 and a plurality of body battery frames arranged around the outside thereof; the body main frame 10 serves as the core support structure of the unmanned aerial vehicle, not only bearing the main components of the unmanned aerial vehicle, but also providing fixation and support for the plurality of body battery frames arranged around the outside thereof. Such a design enhances the structural stability and carrying capacity of the unmanned aerial vehicle, while providing protection for key components such as batteries. The arrangement of the body battery frames helps to reasonably distribute the weight of the unmanned aerial vehicle, optimizing the center of gravity of the unmanned aerial vehicle, thereby improving the stability and maneuverability of flight. The bottom of the body main frame 10 is also provided with a heat dissipation fin 12, which is made of a metal material with high thermal conductivity, such as copper or aluminum, and its surface is specially treated to increase the heat dissipation area.

[0020] The body battery frame comprises a plurality of skeleton assemblies 20 and a plurality of sealing plate assemblies 30, wherein the skeleton assembly 20 comprises a rectangular rotor arm pipe 21, each side of the polygonal frame is provided with a mounting port 11, one end of the rotor arm pipe 21 is inserted into the mounting port 11 and fixed by a bolt; the rectangular rotor arm pipe 21 of the skeleton assembly 20 is connected with the polygonal frame through the precisely designed mounting port 11. This design allows the rotor arm pipe 21 to be aligned with the frame during installation and fixed by a bolt, ensuring the tightness and firmness of the connection. When the unmanned aerial vehicle is running, the rotor arm pipe 21 not only supports the rotor, but also bears the thrust and vibration generated by the rotor. The sealing plate assembly 30 covers the outside of the skeleton assembly 20, further enhancing the rigidity of the body and protecting the internal electronic elements.

[0021] The sealing plate assembly 30 comprises a sealing plate A 31, a sealing plate B 33 and a channel keel 32, the sealing plate A 31 and the sealing plate B 33 are respectively arranged on the upper and lower sides of the adjacent two rotor arm pipes 21 and fixed by a bolt, wherein the channel keel 32 faces the body main frame 10, and the groove edge of the channel keel 32 is fixed by a bolt at the end between the sealing plate A 31 and the sealing plate B 33; the sealing plate A 31 and the sealing plate B 33 in the sealing plate assembly 30 are fixed by a bolt on the upper and lower sides of the rotor arm pipe 21, forming a stable structural support, which helps to resist external impact and vibration during flight. The arrangement of the channel keel 32 not only enhances the rigidity of the body frame. In addition, the channel keel 32 is also provided with heat dissipation holes (not marked in the figure) for improving the heat dissipation effect of the batteries in the sealing plate assembly 30.

[0022] A plurality of air outlet holes 23 are provided on both sides of the rotor arm pipe 21 between the sealing plate A 31 and the sealing plate B 33. A plurality of air inlet holes 34 are provided in the sealing plate B 33. The negative pressure air flow generated by the rotor causes cold air to enter the battery frame of the fuselage through the air inlet holes 34 and carry away heat, and then be discharged through the air outlet holes 23. During the flight of the unmanned aerial vehicle, the high-speed rotation of the rotor generates negative pressure around the rotor arm pipe 21. The negative pressure area functions to attract external cold air to enter the interior of the fuselage through the air inlet holes 34 in the sealing plate B 33. The cold air entering the interior of the fuselage will pass through the heat generating components such as electronic components during the flow process, and absorb the heat generated by these components. As the temperature of the air rises, the air carrying heat will flow along the direction of the rotor arm pipe 21 through the air outlet holes 23 on both sides of the rotor arm pipe 21, and finally be discharged from the fuselage

[0023] In some embodiments, a positioning structure 40 corresponding to each rotor arm pipe 21 is further included. The positioning structure 40 includes a T-shaped block 41 fixed between adjacent sealing plates B 33. The T-shaped block 41 fixes the sealing plate B 33 on the rotor arm pipe 21 through bolts. The positioning structure 40 realizes accurate positioning and fixing of the rotor arm pipe 21 through the T-shaped block 41. The T-shaped block 41 is designed to be embedded between adjacent sealing plates B 33 and fixed by bolts, so as to ensure that the sealing plate B 33 is firmly connected to the rotor arm pipe 21. When the unmanned aerial vehicle encounters vibration or impact during flight, this fixing mode can reduce the relative movement between the rotor arm pipe 21 and the sealing plate B 33, thereby reducing the risk of structural damage. In addition, the positioning structure 40 also helps to maintain the alignment of the rotor arm pipe 21.

[0024] In some embodiments, the positioning structure 40 further includes two positioning blocks 42 respectively arranged adjacent to the two sealing plates B 33. The bottoms of the two positioning blocks 42 are fixed with a semicircular shock-absorbing sleeve 43 surrounding the landing gear through bolts. The positioning structure 40 includes two positioning blocks 42, which are respectively located adjacent to the two sealing plates B 33. The bottoms of the two positioning blocks 42 are fixed with a semicircular shock-absorbing sleeve 43 through bolts, forming a stable support structure. When the unmanned aerial vehicle lands, the landing gear will first contact the ground, at which time the semicircular shock-absorbing sleeve 43 will play its shock-absorbing role, absorbing the impact force and reducing the vibration and impact directly transmitted to the fuselage. This design not only protects the fuselage structure of the unmanned aerial vehicle, but also helps to maintain the stability of the unmanned aerial vehicle during landing, preventing structural damage or damage to electronic components caused by hard landing.

[0025] In some embodiments, the skeleton assembly 20 further comprises a plurality of fastening rings 22 for fixing the rotor arms, the fastening rings 22 are polygonal in shape and are fixed on the inner wall of the rotor arm tube 21 by bolts. The function of the fastening ring 22 is to fix the rotor arm and ensure its stability during flight. The fastening ring 22 is designed as a polygon, which is fixed on the inner wall of the rotor arm tube 21 by bolts. This fixing method provides strong fixing force and prevents the rotor arm from displacement due to vibration or impact during flight.

[0026] In some embodiments, the sealing plates A31 and B33 are fan-shaped, and adjacent sealing plates A31 and B33 are arranged in parallel with each other using fan-shaped bevels. The side of the sealing plates A31 and B33 close to the polygonal frame is concave, and corresponds to the adjacent two sides and corners of the polygonal frame. The fan-shaped design of the sealing plates A31 and B33 allows them to be closely arranged along the edges of the polygonal frame, forming a connection mode similar to a jigsaw puzzle. This arrangement not only improves the sealing performance of the fuselage, but also enhances the overall structure. The concave design of the sealing plates A31 and B33 allows them to better match the geometric shape of the polygonal frame, especially at the corners of the frame. This matching helps to improve the tightness and stability of the connection.

[0027] The above is only a preferred embodiment of the present application, and is not intended to limit the present application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the present application shall be included in the protection scope of the present application.

Claims

1. A multi-rotor unmanned aerial vehicle body structure, comprising a body main frame (10) and a plurality of body battery frames arranged outside the body main frame (10); characterized in that, the body battery frame comprises a plurality of skeleton assemblies (20) and a plurality of sealing plate assemblies (30), wherein the skeleton assembly (20) comprises a rectangular rotor arm pipe (21), each side of the polygonal frame is provided with a mounting port (11), one end of the rotor arm pipe (21) is inserted into the mounting port (11) and fixed by a bolt; the sealing plate assembly (30) comprises a sealing plate A (31), a sealing plate B (33) and a channel keel (32), the sealing plate A (31) and the sealing plate B (33) are arranged on the upper and lower sides of the adjacent two rotor arm pipes (21) respectively and fixed by a bolt, wherein the channel keel (32) faces the body main frame (10), and the groove edge of the channel keel (32) is fixed at the end between the sealing plate A (31) and the sealing plate B (33) by a bolt; a plurality of air outlet holes (23) are arranged on both sides of the rotor arm pipe (21) corresponding to the sealing plate A (31) and the sealing plate B (33); a plurality of air inlet holes (34) are arranged in the sealing plate B (33), and the negative pressure airflow generated by the rotor makes cold air enter the body battery frame through the air inlet holes (34) and carry away heat and be discharged from the air outlet holes (23).

2. The multi-copter drone body structure of claim 1, wherein, a positioning structure (40) corresponding to each rotor arm pipe (21) is further included, the positioning structure (40) comprises a T-shaped block (41) fixed between the adjacent sealing plate B (33), and the T-shaped block (41) fixes the sealing plate B (33) on the rotor arm pipe (21) by a bolt.

3. The multi-copter drone body structure of claim 2, wherein, the positioning structure (40) further comprises two positioning blocks (42) arranged adjacent to each other at two sealing plate B (33), and the bottom of the two positioning blocks (42) is fixed with a semicircular shock-absorbing sleeve (43) surrounding the landing gear by a bolt.

4. The multi-copter drone body structure of claim 1, wherein, the skeleton assembly (20) further comprises a plurality of fastening rings (22) for fixing the rotor arm, the outer part of the fastening ring (22) is polygonal and fixed on the inner wall of the rotor arm pipe (21) by a bolt.

5. The multi-copter drone body structure of claim 1, wherein, the sealing plate A (31) and the sealing plate B (33) are fan-shaped, the adjacent sealing plate A (31) and the adjacent sealing plate B (33) are arranged in a flat manner by using the fan-shaped bevels, wherein the side of the sealing plate A (31) and the sealing plate B (33) close to the polygonal frame is concave, and corresponds to the adjacent two sides and the corners of the polygonal frame.

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