Flying wing hidden type air cylinder temperature control air inlet system of piston engine unmanned aerial vehicle

Abstract

The utility model provides a flying wing hidden type air cylinder temperature control air inlet system of a piston engine unmanned aerial vehicle. The flying wing hidden type air cylinder temperature control air inlet system comprises a right air inlet device and a left air inlet device. Each of the right air inlet device and the left air inlet device comprises an air duct fusion body, an air guide cover and a power assembly; when the wind scooper opens the air inlet, the wind scooper and the edge of the air inlet of the air duct fusion body surround to form a wind guide inlet communicated with the air inlet; when the wind scooper closes the air inlet, part of the wind scooper is contained in the air duct fusion body. According to the flying wing hidden type air cylinder temperature control air inlet system of the piston engine unmanned aerial vehicle, the air inlet of the air duct fusion body can be opened or closed through the air guide cover, the temperature of the piston engine is controlled, the overall structure is simple, and the overall energy consumption is extremely low; the hidden design of the wind scooper enables the overall appearance design of the unmanned aerial vehicle to be smooth, reduces wind resistance, and effectively ensures that the unmanned aerial vehicle continuously and stably flies in a high-altitude alpine region and a low-temperature environment.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, and in particular to a flying wing hidden cylinder temperature control air intake system of a piston engine unmanned aerial vehicle. Background Art

[0002] In recent years, drones have been used more and more widely as a new technology in mineral exploration, anti-terrorism support, military reconnaissance, environmental monitoring, medical search and rescue and other fields. In the future, unmanned systems in various fields will play an important auxiliary role. When drones fly in high altitudes, cold and extreme areas, it is a great challenge for the power system of drones. At present, most small and medium-sized drones use lithium batteries as power sources. Lithium batteries have poor low-temperature resistance and short battery life, which cannot meet the future industrialization needs and hinder the development of the drone industry.

[0003] Among them, small and medium-sized fixed-wing UAVs weighing 30-200 kg are mostly fuel-powered UAVs, and the operating temperature of fuel piston engines has temperature range requirements, and the current temperature control system consumes a lot of energy. Utility Model Content

[0004] The purpose of the utility model is to overcome the shortcomings and deficiencies in the prior art and to provide a flying wing hidden cylinder temperature control air intake system for a piston engine UAV.

[0005] One embodiment of the utility model provides a flying wing hidden cylinder temperature control air intake system for a piston engine UAV, comprising: a right air intake device and a left air intake device;

[0006] The right air intake device and the left air intake device both include an air duct fusion body, an air guide cover and a power assembly. The air duct fusion body of the right air intake device and the air duct fusion body of the left air intake device are arranged on both sides of the flying wing of the UAV. The air outlet of the air duct fusion body faces the cylinder of the UAV. The air guide cover is rotatably arranged on the air duct fusion body to open or close the air inlet of the air guide cover. The power assembly is arranged on the air duct fusion body for driving connection;

[0007] When the air guide cover opens the air inlet, the edges of the air guide cover and the air inlet surround to form an air guide inlet connected to the air inlet, and the air guide inlet protrudes outside the wing of the drone;

[0008] When the air guide cover closes the air inlet, part of the air guide cover is received in the air duct fusion body.

[0009] In some optional embodiments, a limiter is provided at the air inlet of the air duct fusion body, and when the air guide cover opens or closes the air inlet, the air guide cover abuts against the limiter.

[0010] In some optional embodiments, the limiter includes a limit plate, a side of the limit plate facing outside the air inlet is provided with a blocking side edge, and a side of the limit plate facing inside the air inlet is provided with a blocking block;

[0011] When the air guide cover opens the air inlet, the air guide cover abuts against the blocking block;

[0012] When the air guide cover closes the air inlet, the air guide cover abuts against the blocking side.

[0013] In some optional embodiments, the wind guide cover includes a wind guide plate, two side plates and a middle limit rod, and the wind guide plate and the middle limit rod are connected between the two side plates;

[0014] When the air guide cover opens the air inlet, the air guide plate, the two side plates and the edge of the air inlet surround to form the air guide inlet, and the middle limiting rod abuts against the blocking block;

[0015] When the air guide cover closes the air inlet, the air guide plate abuts against the blocking side.

[0016] In some optional embodiments, the limiter includes a plurality of limit plates, and the plurality of limit plates are arranged side by side at the air inlet.

[0017] In some optional embodiments, the power assembly includes a servo and a connecting rod mechanism, the servo is disposed on the air duct fusion body, and is drivingly connected to the air guide cover via the connecting rod mechanism.

[0018] In some optional embodiments, the connecting rod mechanism includes a first connecting rod and a second connecting rod, the servo motor is drivingly connected to the first connecting rod, the first connecting rod and the second connecting rod are rotationally matched, and the second connecting rod is connected to the air guide cover.

[0019] In some optional embodiments, the power assembly includes a servo and a connecting rod mechanism, the servo is disposed on the air duct fusion body, and is drivingly connected to the middle limit rod of the air guide cover through the connecting rod mechanism.

[0020] In some optional embodiments, the air duct fusion body and the flying wing of the UAV are integrally formed.

[0021] Compared with the prior art, the flying wing hidden cylinder temperature control air intake system of the piston engine UAV of the utility model can open or close the air inlet of the air duct fusion body through the air guide cover, thereby controlling the airflow to dissipate heat to the cylinder, and further realizing the temperature control of the piston engine. The overall structure is simple, and the airflow during the flight of the UAV can be used for heat dissipation, and the overall energy consumption is extremely low. Moreover, the hidden design of the air guide cover makes the overall appearance of the UAV smooth, reduces wind resistance and effectively ensures the continuous and stable flight of the UAV in high-altitude and cold areas and low-temperature environments.

[0022] In order to more clearly understand the present invention, the specific implementation of the present invention will be described below in conjunction with the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is a schematic diagram of the structure of a flying wing hidden cylinder temperature control air intake system of a piston engine UAV and a flying wing when the air inlet is closed by the air guide cover in one embodiment of the utility model;

[0024] Figure 2 This is a structural schematic diagram of a flying wing hidden cylinder temperature control air intake system of a piston engine UAV according to an embodiment of the utility model when the air inlet is closed by the air guide cover;

[0025] Figure 3 It is a schematic diagram of the structure of a flying wing hidden cylinder temperature control air intake system of a piston engine UAV and a flying wing when the air inlet is opened by the air guide cover in one embodiment of the utility model;

[0026] Figure 4 This is a schematic diagram of a flying wing hidden cylinder temperature control air intake system of a piston engine UAV according to an embodiment of the utility model and a structural diagram when the air inlet of the air guide cover is opened;

[0027] Figure 5 for Figure 4 An enlarged view of A is shown.

[0028] 10. Right air intake device; 11. Air duct fusion body; 12. Air guide cover; 121. Air guide inlet; 122. Air guide plate; 123. Side plate; 124. Middle limit rod; 13. Power assembly; 131. Servo; 132. Connecting rod mechanism; 133. First connecting rod; 134. Second connecting rod; 14. Limiter; 141. Limiting plate; 142. Blocking side; 143. Blocking block; 20. Left air intake device; 30. Flying wing. DETAILED DESCRIPTION

[0029] The following will clearly and completely describe the technical solutions in the embodiments of the utility model in conjunction with the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the utility model. In the description of the utility model, unless otherwise specified, "multiple" means 2 or more, and "several" means 1 or more. In addition, unless otherwise specified, the terms "first" and "second" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated.

[0030] 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 orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0031] In the description of the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", and "fixed" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0032] In the description of the utility model, the description with reference to the terms "one embodiment", "some optional implementations" or "some optional embodiments" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner.

[0033] See also Figure 1 An embodiment of the utility model provides a flying wing hidden cylinder temperature control air intake system for a piston engine UAV, comprising: a right air intake device 10 and a left air intake device 20.

[0034] The right air intake device 10 and the left air intake device 20 both include an air duct fusion body 11, an air guide cover 12 and a power assembly 13. The air duct fusion body 11 of the right air intake device 10 and the air duct fusion body 11 of the left air intake device 20 are arranged on the left and right wings of the flying wing 30 of the UAV. The air outlet of the air duct fusion body 11 faces the cylinder of the UAV. The air guide cover 12 is rotatably arranged on the air duct fusion body 11 for opening or closing the air inlet of the air guide cover 12. The power assembly 13 is arranged in a driving connection with the air duct fusion body 11 for driving the air guide cover 12 to rotate.

[0035] When the air guide cover 12 opens the air inlet, the edges of the air guide cover 12 and the air inlet surround to form an air guide inlet 121 connected to the air inlet. The air guide inlet 121 protrudes out of the flying wing 30 of the drone, thereby facilitating the introduction of airflow into the air duct fusion body 11.

[0036] When the air guide cover 12 closes the air inlet, part of the air guide cover 12 is received in the air duct fusion body 11 , so that the air guide cover 12 is hidden, thereby preventing the air guide cover 12 from disturbing the airflow around the flying wing 30 .

[0037] When the piston engine needs to be cooled, the airflow around the flying wing 30 of the UAV enters the air inlet through the air guide inlet 121, then flows out from the air outlet of the air duct fusion body 11 and blows to the cylinder head of the piston engine, thereby dissipating the heat of the cylinder and cooling the piston engine. After the cylinder temperature drops, the air guide cover 12 is closed to stop the heat dissipation, thereby facilitating the maintenance of the temperature of the piston engine within the operating temperature range. The overall structure is simple, and the airflow during the flight of the UAV can be used to dissipate heat, and the overall energy consumption is extremely low.

[0038] In some optional embodiments, a limiter 14 is provided at the air inlet of the air duct fusion body 11. When the air guide cover 12 opens or closes the air inlet, the air guide cover 12 abuts against the limiter 14, so that the air guide cover 12 can be stably maintained in the position of opening or closing the air inlet, avoiding the air guide cover 12 from shaking and disturbing the airflow.

[0039] The specific structure of the limiter 14 can be designed according to actual needs. For example, in some optional embodiments, the limiter 14 includes a limit plate 141, and the side of the limit plate 141 facing the outside of the air inlet is provided with a blocking side edge 142, and the side of the limit plate 141 facing the inside of the air inlet is provided with a blocking block 143; when the air guide cover 12 opens the air inlet, the air guide cover 12 abuts against the blocking block 143, so that the air guide cover 12 cannot continue to rotate outside the air inlet; when the air guide cover 12 closes the air inlet, the air guide cover 12 abuts against the blocking side edge 142, so that the air guide cover 12 cannot continue to rotate into the air inlet.

[0040] The specific structure of the air guide cover 12 can be designed according to actual needs. For example, in some optional embodiments, the air guide cover 12 includes an air guide plate 122, two side plates 123 and a middle limiting rod 124, and the air guide plate 122 and the middle limiting rod 124 are connected between the two side plates 123. When the air guide cover 12 opens the air inlet, the air guide plate 122, the two side plates 123 and the edge of the air inlet surround to form the air guide inlet 121, and the middle limiting rod 124 abuts against the blocking block; when the air guide cover 12 closes the air inlet, the air guide plate 122 abuts against the blocking side edge 142.

[0041] In some optional embodiments, the limiter 14 includes a plurality of limit plates 141 , and the plurality of limit plates 141 are arranged side by side at the air inlet. The plurality of limit plates 141 jointly limit the air guide cover 12 to improve the limiting stability.

[0042] The specific structure of the power assembly 13 can be designed according to actual needs. For example, in some optional embodiments, the power assembly 13 includes a steering gear 131 and a connecting rod mechanism 132. The steering gear 131 is arranged on the air duct fusion body 11 and is drivingly connected to the air guide cover 12 through the connecting rod mechanism 132. The steering gear 131 drives the connecting rod mechanism 132 to rotate, thereby driving the air guide cover 12 to rotate. In this embodiment, the connecting rod mechanism 132 is drivingly connected to the limit rod of the air guide cover 12.

[0043] The specific structure of the connecting rod mechanism 132 can be designed according to actual needs. For example, in some optional embodiments, the connecting rod mechanism 132 includes a first connecting rod 133 and a second connecting rod 134. The steering gear 131 is drivingly connected to the first connecting rod 133. The first connecting rod 133 and the second connecting rod 134 are rotationally matched. The second connecting rod 134 is connected to the wind scoop 12. After the steering gear 131 drives the first connecting rod 133 to rotate, the first connecting rod 133 drives the wind scoop 12 to rotate through the second connecting rod 134. In this embodiment, the second connecting rod 134 is connected to the middle limit rod 124 of the wind scoop 12, wherein the second connecting rod 134 is bonded to the middle limit rod 124 of the wind scoop 12. Of course, the second connecting rod 134 and the middle limit rod 124 of the wind scoop 12 can also be detachably connected through a threaded structure or a buckle structure.

[0044] In some optional embodiments, the air duct fusion body 11 and the flying wing 30 of the UAV are integrally formed, thereby improving the overall structural strength and stability of the flying wing 30 and the air duct fusion body 11.

[0045] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A flying wing hidden cylinder temperature control air intake system for a piston engine drone, characterized in that: include: right air intake and left air intake; The right air intake device and the left air intake device both include an air duct fusion body, an air guide cover and a power assembly. The air duct fusion body of the right air intake device and the air duct fusion body of the left air intake device are arranged on both sides of the flying wing of the UAV. The air outlet of the air duct fusion body faces the cylinder of the UAV. The air guide cover is rotatably arranged on the air duct fusion body to open or close the air inlet of the air guide cover. The power assembly is arranged on the air duct fusion body for driving connection; When the air guide cover opens the air inlet, the edges of the air guide cover and the air inlet surround to form an air guide inlet connected to the air inlet, and the air guide inlet protrudes outside the wing of the drone; When the air guide cover closes the air inlet, part of the air guide cover is received in the air duct fusion body.

2. The flying wing hidden cylinder temperature control air intake system of a piston engine UAV according to claim 1, characterized in that: A limiter is arranged at the air inlet of the air duct fusion body, and when the air guide cover opens or closes the air inlet, the air guide cover abuts against the limiter.

3. The flying wing hidden cylinder temperature control air intake system of a piston engine UAV according to claim 2, characterized in that: The limiter comprises a limit plate, a side of the limit plate facing the outside of the air inlet is provided with a blocking side edge, and a side of the limit plate facing the inside of the air inlet is provided with a blocking block; When the air guide cover opens the air inlet, the air guide cover abuts against the blocking block; When the air guide cover closes the air inlet, the air guide cover abuts against the blocking side.

4. The flying wing hidden cylinder temperature control air intake system of a piston engine UAV according to claim 3, characterized in that: The wind guide cover comprises a wind guide plate, two side plates and a middle limit rod, and the wind guide plate and the middle limit rod are connected between the two side plates; When the air guide cover opens the air inlet, the air guide plate, the two side plates and the edge of the air inlet surround to form the air guide inlet, and the middle limiting rod abuts against the blocking block; When the air guide cover closes the air inlet, the air guide plate abuts against the blocking side.

5. The flying wing hidden cylinder temperature control air intake system of a piston engine UAV according to claim 3, characterized in that: The limiter includes a plurality of limit plates, and the plurality of limit plates are arranged side by side at the air inlet.

6. A flying wing hidden cylinder temperature control air intake system for a piston engine UAV according to any one of claims 1 to 5, characterized in that: The power assembly includes a steering gear and a connecting rod mechanism. The steering gear is arranged on the air duct fusion body and is drivingly connected to the air guide cover through the connecting rod mechanism.

7. The flying wing hidden cylinder temperature control air intake system of a piston engine UAV according to claim 6, characterized in that: The connecting rod mechanism comprises a first connecting rod and a second connecting rod, the steering gear is drivingly connected to the first connecting rod, the first connecting rod and the second connecting rod are rotationally matched, and the second connecting rod is connected to the air guide cover.

8. The flying wing hidden cylinder temperature control air intake system of a piston engine UAV according to claim 4, characterized in that: The power assembly includes a steering gear and a connecting rod mechanism. The steering gear is arranged on the air duct fusion body and is drivingly connected to the middle limit rod of the air guide cover through the connecting rod mechanism.

9. A flying wing hidden cylinder temperature control air intake system for a piston engine UAV according to any one of claims 1 to 5, characterized in that: The air duct fusion body and the flying wing of the UAV are formed in one piece.

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