Heat dissipation and shock absorption structure of multi-rotor unmanned aerial vehicle

Abstract

The utility model belongs to the field of unmanned aerial vehicles, and particularly relates to a heat dissipation and shock absorption structure of a multi-rotor unmanned aerial vehicle. The power heat dissipation mechanisms are arranged on machine arms on the two sides of the multi-rotor unmanned aerial vehicle, the damping mechanism is used for damping the power heat dissipation mechanisms, and the power heat dissipation mechanisms are communicated with an engine of the multi-rotor unmanned aerial vehicle through cooling pipes. Compared with the prior art, the multi-rotor unmanned aerial vehicle has the advantages that the water-cooling radiators are arranged on the vehicle arms on the two sides of the multi-rotor unmanned aerial vehicle, rotor airflow above the vehicle arms is used for cooling the engine radiators, and the damping mechanism is designed to meet the vibration isolation requirement; the cooling pipeline is communicated with the unmanned aerial vehicle hybrid power system rectifier, heat of the hybrid power system rectifier module is reduced, and abnormal work caused by the fact that the rectifier cannot dissipate heat is prevented.

Description

Technical Field

[0001] The utility model belongs to the field of unmanned aerial vehicles, and in particular relates to a heat dissipation and shock absorption structure of a multi-rotor unmanned aerial vehicle. Background Art

[0002] Multi-rotor drones are characterized by their maneuverability and ease of use. However, given the short endurance of current pure electric powertrains, multi-rotor drones require hybrid systems equipped with fuel engines with a high power-to-weight ratio to achieve heavy payloads and long flight times, gradually evolving towards intelligent, multi-aircraft formation applications. Because multi-rotor drones must hover in the air, fuel engines generate significant heat at high speeds. Without effective cooling measures, this can cause the engine cylinder temperature to rise sharply, leading to cylinder seizure. Furthermore, because multi-rotor drone hybrid systems use rectifiers for voltage rectification, consuming 10kW-15kW of power during normal flight. Consequently, the rectifiers generate significant heat, making it difficult for the hybrid system's rectifiers to cool, causing them to malfunction. This can lead to drone crashes and significant economic losses.

[0003] A Chinese authorized invention patent (publication number CN107489513B) discloses an air cooling system for a helicopter, comprising a fan whose shaft is connected to the engine output. Rotation of the engine output drives the fan to dissipate heat from the engine. The fan provides a certain cooling effect, but it does not dissipate heat evenly from the outside. Furthermore, the fan shaft tends to vibrate during long-term use, which can negatively impact the stability of the engine output. A Chinese invention patent application (publication number CN106437997A) discloses a multi-rotor UAV engine cooling device and multi-rotor UAV. The device comprises a wing tube assembly comprising a first wing tube and a second wing tube, a water pump connected to a cooling box and the first and second wing tubes, and a controller connected to the engine and the water pump, respectively. Using the wing tube assembly for heat dissipation results in a small heat dissipation area, fails to effectively utilize the effect of the rotor's downdraft on the radiator, and cannot adapt to diverse operating environments.

[0004] None of the above existing patents achieves heat dissipation of the rectifier, and thus cannot reduce the risk of abnormal operation of the rectifier.

[0005] The vibration during flight has a significant impact on the structural stability of the drone. The inventors discovered that the vibration during flight also affects the heat dissipation of the drone. The existing patent does not describe the shock absorption method of the heat dissipation structure. Utility Model Content

[0006] In order to overcome the above-mentioned defects, the purpose of the present invention is to provide a heat dissipation and shock absorption structure for a multi-rotor UAV.

[0007] In order to achieve the above objectives, the technical solution adopted by the present invention is as follows: a heat dissipation and shock absorption structure for a multi-rotor UAV, including a power heat dissipation mechanism arranged on the arms on both sides of the multi-rotor UAV and a shock absorption mechanism for absorbing the shock of the power heat dissipation mechanism. The power heat dissipation mechanism is connected to the engine of the multi-rotor UAV (specifically the engine cooling water) through a first cooling pipe.

[0008] In a preferred embodiment, the power heat dissipation mechanism includes an engine radiator fixed to the arms on both sides of the multi-rotor drone, and the engine radiator is cooled by the downward airflow of the rotor of the multi-rotor drone, and the engine coolant (i.e., engine cooling water) is circulated through the engine radiator to dissipate heat.

[0009] Furthermore, a rectifier radiator is provided, and the rectifier radiator is connected to the engine (specifically the engine cooling water) through a second cooling pipe; the rectifier radiator is fitted to the rectifier.

[0010] In a preferred embodiment, the shock absorbing mechanism includes a first fixing mechanism connected to the engine radiator, a second fixing mechanism connected to the arms on both sides of the multi-rotor drone, and a shock absorbing pad arranged between the first fixing mechanism and the second fixing mechanism.

[0011] Furthermore, the first fixing mechanism is an L-shaped fixing seat, and the second fixing mechanism includes a circular fixing upper buckle that is tightly attached to the arms on both sides of the multi-rotor drone and a bottom fixing support located at the bottom of the circular fixing upper buckle, and the shock-absorbing pad is connected between the bottom fixing support and the L-shaped fixing seat and is vertically arranged.

[0012] In a preferred embodiment, a plurality of shock-absorbing pads are arranged in a staggered manner to reduce shock in the front-to-back and left-to-right directions of the power heat dissipation mechanism.

[0013] Furthermore, the width of the engine radiator may be adjusted according to the number of fluid channels (eg, the number of water channels) in the engine radiator.

[0014] In a preferred embodiment, the rectifier radiator inlet is connected to the water pump water inlet, and the rectifier radiator outlet is connected to the engine through a second cooling pipe.

[0015] Furthermore, the power heat dissipation mechanism is located on both sides of the engine of the multi-rotor UAV, and the engine is located in the center of the multi-rotor UAV.

[0016] In a preferred embodiment, there are two engine radiators, and each engine radiator is equipped with multiple groups of evenly distributed shock absorbing mechanisms; and the multiple groups of shock absorbing mechanisms installed on the two engine radiators are arranged symmetrically on the left and right.

[0017] Compared with the existing technology, the benefits of the present invention are as follows: water-cooled radiators are arranged on the arms on both sides of the multi-rotor drone, the rotor airflow above the arms is used to cool the engine radiator, and a shock-absorbing mechanism is designed to meet the vibration isolation requirements; the cooling pipeline is connected to the drone's hybrid system rectifier, reducing the heat of the hybrid system rectifier module and preventing the rectifier from working abnormally due to the inability to dissipate heat. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 This is a schematic diagram of the engine radiator and shock absorption mechanism of the utility model;

[0019] Figure 2 This is a schematic diagram of the heat dissipation and shock absorption structure of the multi-rotor UAV of the utility model;

[0020] Figure 3 This is a schematic diagram of the rectifier radiator connection of the utility model;

[0021] The meaning of the reference numerals in the figures:

[0022] 1-first engine radiator, 2-second engine radiator, 3-shock absorber, 4-water pump, 42-water pump outlet, 5-rectifier radiator, 51-rectifier radiator outlet, 6-L-shaped fixing seat, 61-fixing seat longitudinal part, 62-fixing seat transverse part, 7-circular fixing upper clip, 8-bottom fixing support, 81-circular fixing lower clip, 82-support bottom, 9-shock absorber pad, 10-engine, 11-machine arm, 12-rotor, 13-rectifier, 14-first cooling pipe, 15-second cooling pipe, 16-upper metal support, 17-lower metal support, 18-hole. DETAILED DESCRIPTION

[0023] The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.

[0024] like Figure 1-3 The figure shows a heat dissipation and vibration reduction structure for a multi-rotor drone. The structure includes a power heat dissipation mechanism located on each arm of the multi-rotor drone and a vibration reduction mechanism 3 for reducing vibrations within the power heat dissipation mechanism. The power heat dissipation mechanism is connected to the multi-rotor drone's engine via a first cooling pipe 14 (which can be a cooling water pipe). The vibration reduction mechanism reliably reduces vibrations within the engine radiator, effectively minimizing the impact of flight vibrations on the structure.

[0025] The multi-rotor drone has a hybrid system that includes fuel power (fuel engine) and electric power (battery). The hybrid system uses a rectifier 13 to rectify the voltage, which is a prior art and will not be described in detail.

[0026] The cooling medium may be water or other cooling media.

[0027] Specifically, the engine can be a fuel engine or an engine powered by another source of power. Conventional engines are internally provided with an engine cooling water pipeline for dissipating heat. This internal cooling water pipeline (referred to as the engine cooling water) is located within the engine cylinder block, where the cooling water circulates within the cylinder block to dissipate heat. As this is conventional technology, a detailed description is omitted. This engine cooling water pipeline is connected to the engine radiator via a first cooling pipe 14. The rectifier radiator is connected to this engine cooling water pipeline via a second cooling pipe 15 (which can be a cooling water pipe). The first cooling pipe can be arranged along the engine arm, while the second cooling pipe is arranged between the rectifier radiator and the engine.

[0028] The entire cooling water pipeline including the rectifier radiator, the second cooling pipe, the engine cooling water pipeline, the first cooling pipe, and the engine radiator is circulated through the water pump 4. The water from the water pump first enters the rectifier radiator, then comes out of the rectifier radiator and enters the water-cooled cylinder block inside the engine through the second cooling pipe. After dissipating the heat of the engine, it enters the engine radiator through the first cooling pipe, and then returns to the water pump inlet pipeline from the engine radiator.

[0029] The power heat dissipation mechanism is located on both sides of the engine of the multi-rotor UAV, and the engine is located in the center of the multi-rotor UAV.

[0030] In a preferred embodiment, the power heat dissipation mechanism includes engine radiators fixed to the arms on both sides of the multi-rotor drone (for example, fixed to the lower ends of the arms on both sides of the multi-rotor drone), and there are two engine radiators, namely the first engine radiator 1 and the second engine radiator 2 (for example, two engine radiators are arranged on the middle two side arms of the six-rotor drone, and the first engine radiator 1 and the second engine radiator 2 are respectively connected to the shock absorption mechanism), and the downward airflow of the multiple rotors 12 of the multi-rotor drone is used to perform convective heat exchange (heat dissipation cooling) on the surface of the engine radiator, and then the engine coolant (for example, cooling water) is circulated through the engine radiator to dissipate heat.

[0031] The heat dissipation and shock absorption structure of the multi-rotor UAV of the present invention is applicable to any type of multi-rotor UAV, such as a quad-rotor UAV and an octocrotor UAV. The heat dissipation and shock absorption structure of the present invention can be arranged on any arm on both sides of the fuel engine cylinder body.

[0032] Among them, the engine radiator is a water-cooled radiator, and the cooling water of the engine can be circulated through the engine radiator to dissipate heat.

[0033] In a preferred embodiment, the multi-rotor drone's heat dissipation and shock absorption structure further includes a rectifier radiator connected to the cooling water of engine 10 (e.g., a fuel engine); rectifier radiator 5 is disposed in close contact with rectifier 13. The engine cooling water refers to the cooling water in the engine cooling water pipeline.

[0034] For example, the rectifier radiator inlet is connected to the water pump inlet 42, and the rectifier radiator outlet 51 is connected to the cooling water of the fuel engine. The heat generated by the rectifier is removed by water cooling. The rectifier radiator, engine radiator, and engine cooling water form a cooling water cycle. The cooling water flows from the water pump-rectifier radiator-engine cooling water pipeline inside the fuel engine-engine radiator-water pump to form a water cycle ( Figure 3 The rectifier radiator is connected to the engine cooling water pipeline (engine cooling water) inside the fuel engine through the second cooling pipe 15, and the engine cooling water is connected to the engine radiator through the first cooling pipe 14.

[0035] In a preferred embodiment, the shock absorbing mechanism includes a first fixing mechanism connected to each engine radiator, a second fixing mechanism connected to the arms 11 on both sides of the multi-rotor drone, and a shock absorbing pad 9 arranged between the first fixing mechanism and the second fixing mechanism.

[0036] Multiple groups (for example, 2-4 groups, 3 groups in the figure) of evenly distributed shock absorbing mechanisms are installed on each engine radiator; and the multiple groups of shock absorbing mechanisms installed on the two engine radiators are arranged symmetrically on the left and right.

[0037] For example, the first fixing mechanism is an L-shaped fixing seat 6, and the second fixing mechanism includes a circular fixing upper buckle 7 that is tightly attached to the arms on both sides of the multi-rotor drone and a bottom fixing support 8 located at the bottom of the circular fixing upper buckle. The shock-absorbing pad is connected between the bottom fixing support and the L-shaped fixing seat and is vertically arranged ( Figure 1 Several shock-absorbing pads are arranged in a staggered manner to reduce shock in the front-to-back and left-to-right directions of the power cooling mechanism.

[0038] The shock absorber is made of rubber with a hollow center. It forms an integrated structure with the upper and lower metal struts (the upper metal strut 16 passes through and connects the L-shaped mounting bracket and the upper portion of the shock absorber, while the lower metal strut 17 passes through and connects the bottom mounting bracket and the lower portion of the shock absorber; the upper and lower metal struts are located on the same vertical line; the shock absorber, upper and lower metal struts, circular upper mounting clip, and bottom mounting bracket are all located above the upper surface of the engine radiator and do not contact it). The shock absorbers are installed in a staggered arrangement to ensure effective shock absorption in both the front-to-back and left-to-right directions.

[0039] Preferably, the engine radiator and the shock absorbing mechanism are connected via an L-shaped fixing seat 6 and fixed via nuts.

[0040] Preferably, the circular upper fixing buckle and the bottom fixing seat are both tightly fitted to the machine arm and are securely fixed by screws.

[0041] The L-shaped mounting bracket includes an integral longitudinal portion 61 and a transverse portion 62. The longitudinal portion 61 is secured to the side of the engine radiator; the transverse portion 62 is connected to the shock-absorbing pad via an upper metal strut. The bottom mounting bracket comprises an integrally formed circular lower fixing clip 81 and a bracket bottom 82 extending laterally forward and backward from the bottom of the circular lower fixing clip 81. The bracket bottom 82 is secured to the shock-absorbing pad via a lower metal strut. The circular lower fixing clip 81 (semicircular in cross-section) and the circular upper fixing clip 7 (semicircular in cross-section) form a circular space for securing the drone's arm. Both the circular lower fixing clip 81 and the circular upper fixing clip 7 are provided with aligned holes 18. Bolts are secured in these holes 18 to secure the circular lower fixing clip 81 and the circular upper fixing clip 7 to each other.

[0042] The width of the engine radiator of the multi-rotor drone is L. The number of water channels within the engine radiator is determined by the ambient temperature (the water channels of the engine radiator are arranged using the common water channel distribution method of water-cooled radiators in the prior art). When the ambient temperature is less than 10°C, the number of water channels can be 12-15; when the ambient temperature is greater than or equal to 10°C, the number of water channels can be 19-22. The radiator width L is also adjusted based on the number of water channels (L is water channel width * number of water channels + thickness of the radiator shell on both sides). When the ambient temperature is less than 10°C, the radiator width L can be 120-125 mm; when the ambient temperature is greater than or equal to 10°C, the radiator width L can be 150-160 mm.

[0043] This utility model's water-cooled radiator is placed on the multirotor arms on either side of the fuel engine. It utilizes the rotor airflow above the arms to cool the engine radiator, which then circulates the cooling water from the fuel engine through the engine radiator to dissipate heat. The rectifier radiator dissipates heat from the rectifier device in the hybrid system of a multirotor drone, dissipating the heat generated by the rectifier through water cooling.

[0044] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating directions or positional relationships, are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as a limitation on the present invention; in addition, the terms "first" and "second" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance.

[0045] In the description of the present invention, it should be noted that: unless otherwise clearly stipulated and limited, the terms "installation", "connection", "setting" and "formation" should be understood in a broad sense; for example, it can be a fixed connection, setting, or a detachable connection, setting, or an integrated structure; it can be a mechanical connection or an electrical connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be internal communication between two elements; for those skilled in the art, the specific meanings of the above terms in the present invention can be understood according to the specific circumstances.

[0046] In the description of the present invention, reference to terms such as "embodiment", "specific example" or "practical application" means that the specific features, structures, materials or characteristics described in combination with the embodiment are included in at least one embodiment or example of the present invention; the schematic expressions of the above terms do not necessarily refer to the same embodiment or example, and the specific features, structures, materials or characteristics described may be combined in an appropriate manner in any one or more embodiments or examples.

[0047] The above embodiments are only used to illustrate the technical solutions of the present invention. Those skilled in the art should understand that the above embodiments do not limit the present invention in any form. Any technical solutions obtained by equivalent replacement or equivalent transformation fall within the scope of protection of the present invention.

Claims

1. A heat dissipation and shock absorption structure for a multi-rotor drone, characterized in that: The invention comprises a power heat dissipation mechanism arranged on both sides of the machine arms of the multi-rotor UAV and a shock absorbing mechanism for absorbing the shock of the power heat dissipation mechanism. The power heat dissipation mechanism is connected with the engine of the multi-rotor UAV through a first cooling pipe.

2. The heat dissipation and shock absorption structure of a multi-rotor UAV according to claim 1, characterized in that: The power heat dissipation mechanism includes an engine radiator fixed to the arms on both sides of the multi-rotor drone, which utilizes the downward airflow of the rotor of the multi-rotor drone to dissipate heat and cool the engine radiator, and circulates the engine coolant through the engine radiator to dissipate heat.

3. The heat dissipation and shock absorption structure of a multi-rotor UAV according to claim 1, characterized in that: A rectifier radiator is also provided, and the rectifier radiator is connected to the engine through a second cooling pipe; the rectifier radiator is fitted to the rectifier.

4. The heat dissipation and shock absorption structure of a multi-rotor UAV according to claim 2, characterized in that: The shock-absorbing mechanism includes a first fixing mechanism connected to the engine radiator, a second fixing mechanism connected to the arms on both sides of the multi-rotor drone, and a shock-absorbing pad arranged between the first fixing mechanism and the second fixing mechanism.

5. The heat dissipation and shock absorption structure of a multi-rotor UAV according to claim 4, characterized in that: The first fixing mechanism is an L-shaped fixing seat, and the second fixing mechanism includes a circular fixing upper buckle that is tightly attached to the arms on both sides of the multi-rotor drone and a bottom fixing support located at the bottom of the circular fixing upper buckle. The shock-absorbing pad is connected between the bottom fixing support and the L-shaped fixing seat and is vertically arranged.

6. The heat dissipation and shock absorption structure of a multi-rotor UAV according to claim 5, characterized in that: Several shock-absorbing pads are arranged in a staggered manner to reduce shock in the front-to-back and left-to-right directions of the power cooling mechanism.

7. The heat dissipation and shock absorption structure of a multi-rotor UAV according to claim 2, characterized in that: The width of the engine radiator can be adjusted according to the number of fluid channels in the engine radiator.

8. The heat dissipation and shock absorption structure of a multi-rotor UAV according to claim 3, characterized in that: The inlet of the rectifier radiator is connected to the water delivery port of the water pump, and the outlet of the rectifier radiator is connected to the engine through a second cooling pipe.

9. The heat dissipation and shock absorption structure of a multi-rotor UAV according to claim 1, characterized in that: The power heat dissipation mechanism is located on both sides of the engine of the multi-rotor UAV, and the engine is located in the center of the multi-rotor UAV.

10. The heat dissipation and shock absorption structure of a multi-rotor UAV according to claim 2, characterized in that: There are two engine radiators, and each engine radiator is equipped with multiple groups of evenly distributed shock absorbing mechanisms; and the multiple groups of shock absorbing mechanisms installed on the two engine radiators are arranged symmetrically on the left and right.

Images