Closed cylinder temperature control air inlet structure of conventional layout piston engine of unmanned aerial vehicle

Abstract

The utility model discloses a closed air cylinder temperature control air inlet structure of a conventional layout piston engine of an unmanned aerial vehicle, which comprises an engine body, a left side temperature adjusting mechanism and a right side temperature adjusting mechanism, and the right side temperature adjusting mechanism comprises a right air duct fusion body, a right closed cover and a right steering engine torsion mechanism. The left side temperature adjusting mechanism comprises a left steering engine torsion mechanism, a left sealing cover and a left air duct fusion body; the left side temperature adjusting mechanism and the right side temperature adjusting mechanism are installed on the two sides of the machine body, steering engines of the temperature adjusting mechanisms on the two sides control opening and closing of respective sealing covers relative to air inlets of air channels on the outer sides of the sealing covers, and the working temperature interval of the piston engine can be effectively controlled; and an effective guarantee is provided for continuous and stable flight of the carried unmanned aerial vehicle in a low-temperature high-altitude area.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a closed cylinder temperature control air intake structure of a conventional layout piston engine of an unmanned aerial vehicle. Background Art

[0002] In recent years, drones have been used as a new technical means in various fields such as mineral exploration, anti-terrorism support, military reconnaissance, environmental monitoring, medical search and rescue, etc. Unmanned systems will inevitably play an important auxiliary role in various fields in the future. 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 needs of future industrialization and hinder the development of the drone industry. Among them, 30-200 kg small and medium-sized fixed-wing drones are mostly fuel-powered drones, and the operating temperature of fuel piston engines has a temperature range requirement. When the engine cylinder temperature is too high, heat dissipation is required, and when the engine cylinder temperature is too low, insulation is required. For this reason, the utility model provides a conventional layout piston engine closed cylinder temperature control intake structure system for drones to solve this technical problem. Utility Model Content

[0003] In order to overcome the deficiencies of the prior art, the purpose of the utility model is to provide a closed cylinder temperature control intake structure for a conventionally arranged piston engine of an unmanned aerial vehicle, so as to solve the technical problems mentioned in the background technology.

[0004] In order to solve the technical problem, the utility model adopts the following technical solution:

[0005] A conventional layout of a UAV piston engine closed cylinder temperature control intake structure comprises a body, a left temperature regulating mechanism and a right temperature regulating mechanism, wherein the right temperature regulating mechanism comprises a right air duct fusion body, a right closed cover, and a right servo torsion mechanism, and the left temperature regulating mechanism comprises a left servo torsion mechanism, a left closed cover, and a left air duct fusion body; the left air duct fusion body is installed on the left rear side of the UAV body and integrated with the body, the air outlet of the left air duct fusion body is aligned with the left cylinder head of the engine, the air inlet is located on the left outer side of the body and opens forward, the left closed cover is installed in a semi-external surrounding form on the outer side of the air inlet of the left air duct fusion body and is rotated by the left servo torsion mechanism to control the opening and closing of the air inlet, the right air duct fusion body is installed on the right rear side of the UAV body and integrated with the body, the air outlet of the right air duct fusion body is aligned with the right cylinder head of the engine, the air inlet is located on the right outer side of the body and opens forward, the right closed cover is installed in a semi-external surrounding form on the outer side of the air inlet of the right air duct fusion body and is rotated by the right servo torsion mechanism to control the opening and closing of the air inlet.

[0006] The left air duct fusion body includes a left inner air duct and a left outer air duct, and the right air duct fusion body includes a right inner air duct and a right outer air duct. The two side bulkheads of the body are respectively provided with a left duct connecting hole and a right duct connecting hole. The left inner air duct is connected with the left outer air duct through the left duct connecting hole, wherein the left inner air duct and the left outer air duct have an arc transition and the left outer air duct opens forward, and the right inner air duct is connected with the right outer air duct through the right duct connecting hole, wherein the right inner air duct and the right outer air duct have an arc transition and the right outer air duct opens toward the front, the opening of the left inner air duct forms a left air outlet, and the opening of the left outer air duct forms a left air inlet, the opening of the right inner air duct forms a right air outlet, and the opening of the right outer air duct forms a right air inlet, the left closed cover is semi-enclosed on the outside of the left outer air duct, and the right closed cover is semi-enclosed on the outside of the right outer air duct.

[0007] The left inner air duct and the right inner air duct are both parallel to the body bulkhead, the left air outlet is aligned with the left cylinder head of the engine, and the right air outlet is aligned with the right cylinder head of the engine.

[0008] The left servo torsion mechanism comprises a left servo and a left servo torsion shaft, wherein the left servo is installed at the outer wall on the left side of the fuselage and its output shaft is connected to the left servo torsion shaft, the left servo torsion shaft longitudinally passes through the upper and lower walls of the left outer air duct, and the upper and lower ends of the left closed cover are respectively fixedly connected to the upper and lower ends of the left servo torsion shaft, and the right servo torsion mechanism comprises a right servo and a right servo torsion shaft, wherein the right servo is installed at the outer wall on the right side of the fuselage and its output shaft is connected to the right servo torsion shaft, the right servo torsion shaft longitudinally passes through the upper and lower walls of the right outer air duct, and the upper and lower ends of the right closed cover are respectively fixedly connected to the upper and lower ends of the right servo torsion shaft.

[0009] Compared with the prior art, the beneficial effects of the present invention are:

[0010] By installing a left-side temperature control mechanism and a right-side temperature control mechanism on both sides of the fuselage, and controlling the opening and closing of each closed cover relative to the air inlet of the outer air duct through the servos of the temperature control mechanisms on both sides, the operating temperature range of the piston engine can be effectively controlled, providing effective guarantee for the continuous and stable flight of the UAV carried in low-temperature and high-altitude areas. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 : This is one of the top views of the overall structure of the utility model patent;

[0012] Figure 2 : This is the second top view of the overall structure of the utility model patent;

[0013] Figure 3 : It is a left-side perspective stereogram of the overall structure of the utility model patent;

[0014] Figure 4: It is a right-side perspective stereogram of the overall structure of the utility model patent;

[0015] Figure 5 : This is a three-dimensional diagram of the overall structure of the utility model patent from the left rear side perspective;

[0016] Figure 6 : It is the overall structural cross-section diagram of this utility model patent;

[0017] In the figure: body 10, left temperature regulating mechanism 20, right temperature regulating mechanism 30, right air duct fusion body 1, right closed cover 3, right servo torsion mechanism 5, left servo torsion mechanism 6, left closed cover 4, left air duct fusion body 2, left inner air duct 11, left outer air duct 12, right inner air duct 21, right outer air duct 22, left duct communication hole 101, right duct communication hole 102, left air outlet 23, left air inlet 24, right air outlet 13, right air inlet 14, left servo 61, left servo torsion shaft 62, right servo 51, right servo torsion shaft 52, left closed sealing ring edge 121, right closed sealing ring edge 221. DETAILED DESCRIPTION

[0018] The present invention is further described below in conjunction with the accompanying drawings and specific implementation methods. It should be noted that, under the premise of no conflict, the various embodiments or technical features described below can be arbitrarily combined to form a new embodiment.

[0019] refer to Figures 1 to 6 :

[0020] The utility model discloses a closed cylinder temperature control air intake structure of a conventional layout piston engine of an unmanned aerial vehicle, comprising a body 10, a left temperature regulating mechanism 20 and a right temperature regulating mechanism 30, wherein the right temperature regulating mechanism 30 comprises a right air duct fusion body 1, a right closed cover 3 and a right servo torsion mechanism 5, and the left temperature regulating mechanism 20 comprises a left servo torsion mechanism 6, a left closed cover 4 and a left air duct fusion body 2; the left air duct fusion body 2 is installed on the left rear side of the unmanned aerial vehicle body 10 and is integrated with the body 10, the air outlet of the left air duct fusion body 2 is aligned with the left cylinder head of the engine to facilitate blowing air to the engine cylinder body, the air inlet is located on the left outer side of the body 10 and is opened forward to facilitate the wind to blow in quickly along the forward direction of the body 10, and the left closed cover 4 is semi-closed to the left side of the engine. The outer surrounding form is installed on the outside of the air inlet of the left air duct fusion body 2 and is rotated by the left servo torsion mechanism 6 to control the opening and closing of the air inlet. The right air duct fusion body 1 is installed on the right rear side of the UAV body 10 and is integrated with the body 10. The air outlet of the right air duct fusion body 1 is aligned with the right cylinder head of the engine, and the air inlet is located on the right outer side of the body 10 and opens forward. The right closed cover 3 is installed on the outside of the air inlet of the right air duct fusion body 1 in a semi-outer surrounding form and is rotated by the right servo torsion mechanism 5 to control the opening and closing of the air inlet. In the above, the left temperature control mechanism 20 and the right temperature control mechanism 30 can be coordinated or individually regulated. Specifically, the air duct can be opened or closed according to the cylinder head temperature value fed back by the engine ECU.

[0021] Specifically, the left air duct fusion body 2 includes a left inner air duct 11 and a left outer air duct 12, and the right air duct fusion body 1 includes a right inner air duct 21 and a right outer air duct 22, wherein the left inner air duct 11 and the right inner air duct 21 are both located in the cabin or parallel to the cabin inner wall, and are preferably parallel to the cabin inner wall or integrated with the cabin inner wall to facilitate production and save cabin space. The two side walls of the body 10 are respectively provided with a left duct connecting hole 101 and a right duct connecting hole 102, and the left inner air duct 11 is connected to the left outer air duct 12 through the left duct connecting hole 101, wherein the left inner air duct 11 and the left outer air duct 12 are arc-shaped. The right inner air duct 21 is connected with the right outer air duct 22 through the right duct connecting hole 102, wherein the right inner air duct 21 and the right outer air duct 22 have an arcuate transition and the right outer air duct 22 opens toward the front, the opening of the left inner air duct 11 forms a left air outlet 23, the opening of the left outer air duct 12 forms a left air inlet 24, the opening of the right inner air duct 21 forms a right air outlet 13, the opening of the right outer air duct 22 forms a right air inlet 14, the left closed cover 4 is semi-enclosed on the outside of the left outer air duct 12, and the right closed cover 3 is semi-enclosed on the outside of the right outer air duct 22.

[0022] Specifically, the left inner air duct 11 and the right inner air duct 21 are both parallel to the bulkhead of the engine body 10, the left air outlet 23 is aligned with the left cylinder head of the engine, and the right air outlet 13 is aligned with the right cylinder head of the engine.

[0023] Specifically, the left servo torsion mechanism 6 includes a left servo 61 and a left servo torsion shaft 62, wherein the left servo 61 is installed at the outer wall of the left side of the fuselage and its output shaft is connected to the left servo torsion shaft 62, the left servo torsion shaft 62 longitudinally passes through the upper and lower walls of the left outer air duct 12, and the upper and lower ends of the left closed cover 4 are respectively fixedly connected to the upper and lower ends of the left servo torsion shaft 62, and the right servo torsion mechanism 5 includes a right servo 51 and a right servo torsion shaft 52, wherein the right servo 51 is installed at the outer wall of the right side of the fuselage and its output shaft is connected to the right servo torsion shaft 52, the right servo torsion shaft 52 longitudinally passes through the upper and lower walls of the right outer air duct 22, and the upper and lower ends of the right closed cover 3 are respectively fixedly connected to the upper and lower ends of the right servo torsion shaft 52. In order to reduce the weight of traditional mechanical transmission components to increase the range, here, taking the left temperature regulating mechanism 20 as an example, the left outer air duct 12 is adopted. The upper and lower arms are drilled with holes, which are smoothed and cured, and are of a size equivalent to the left servo torsion shaft 62, so that the left servo torsion shaft 62 can pass through and rotate. Taking the left servo 61 installed on the upper end of the left closed cover 4 as an example, the left servo torsion shaft 62 penetrates into the left closed cover 4 and the left outer air duct 12 from top to bottom, so the upper end of the left closed cover 4 needs to be perforated and glue is needed to fix it to the left servo torsion shaft 62, and the lower side wall of the left closed cover 4 is directly glued to the end of the left servo torsion shaft 62. Such an arrangement can greatly reduce the weight of the body 10. Of course, in a certain embodiment, mechanical transmission such as gears or bearings can also be used, that is, gear transmission is used between the outer left closed cover 4 and the left servo torsion shaft 62, and bearings are used to rotate between the inner left outer air duct 12 and the left servo torsion shaft 62, which can increase its transmission efficiency, but the disadvantage is that it will increase the weight of the body 10 and shorten the range of the drone.

[0024] Specifically, the left closed cover 4 includes a left connecting arm and a left cover, the left connecting arm located at the upper and lower ends are respectively connected to the upper and lower ends of the left cover, the left cover is a curved cover body, which can just block the left air inlet 24 when closed, and a first pivot part is also provided on one side of the left connecting arm, and the upper and lower ends of the left servo torsion shaft 62 are fixedly connected to the first pivot parts at the upper and lower ends. The right closed cover 3 includes a right connecting arm and a right cover, the right connecting arm located at the upper and lower ends are respectively connected to the upper and lower ends of the right cover, and the right cover is a curved cover body, which can just block the right air inlet 14 when closed, and a second pivot part is also provided on one side of the right connecting arm, and the upper and lower ends of the right servo torsion shaft 52 are fixedly connected to the second pivot parts at the upper and lower ends.

[0025] Specifically, a left closed sealing ring edge 121 is provided at the outer side of the left air inlet 24 and the end of the left outer air duct 12, and the left closed sealing ring edge 121 matches the inner arc shape of the left cover, and a right closed sealing ring edge 221 is provided at the outer side of the right air inlet 14 and the end of the right outer air duct 22, and the right closed sealing ring edge 221 matches the inner arc shape of the right cover.

[0026] The principle of temperature regulation of this device: taking the left temperature regulating mechanism 20 as an example, when temperature regulation is needed, the left servo 61 drives the left closed cover 4 through the left servo torsion shaft 62, so that the left closed cover 4 rotates from the left outer air duct 12 from the side of the left air inlet 24 to the side away from the left air inlet 24, until the left closed cover 4 reaches the outer arc surface of the left outer air duct 12 and is limited by it. The left servo 61 detects overload and stops rotating. At this time, the left air inlet 24 is opened, and the ambient air passes through the left air inlet 24 through the left outer air duct 12 and the left inner air duct 11 into the engine cylinder body to cool the engine cylinder body. When the engine ECU detects that the temperature is too low, the left servo 61 performs the opposite action until the left closed cover 4 reaches the left air inlet 24 from the position away from the left outer air duct 12, and the partial opening and closing of the left closed cover 4 can be controlled by the torsion degree or torsion time of the left servo 61.

[0027] The above-mentioned implementation modes are only preferred implementation modes of the present invention, and cannot be used to limit the protection scope of the present invention. Any non-substantial changes and substitutions made by technicians in this field on the basis of the present invention shall fall within the scope of protection required by the present invention.

Claims

1. The conventional layout of the UAV piston engine closed cylinder temperature control intake structure is characterized by: It includes a body, a left-side temperature regulating mechanism and a right-side temperature regulating mechanism, wherein the right-side temperature regulating mechanism includes a right air duct fusion body, a right closed cover, and a right servo torsion mechanism, and the left-side temperature regulating mechanism includes a left servo torsion mechanism, a left closed cover, and a left air duct fusion body; the left air duct fusion body is installed on the left rear side of the UAV body and is integrated with the body, the air outlet of the left air duct fusion body is aligned with the left cylinder head of the engine, the air inlet is located on the left outer side of the body and is opened forward, the left closed cover is installed on the outer side of the air inlet of the left air duct fusion body in a semi-external surrounding form and is rotated by the left servo torsion mechanism to control the opening and closing of the air inlet, the right air duct fusion body is installed on the right rear side of the UAV body and is integrated with the body, the air outlet of the right air duct fusion body is aligned with the right cylinder head of the engine, the air inlet is located on the right outer side of the body and is opened forward, the right closed cover is installed on the outer side of the air inlet of the right air duct fusion body in a semi-external surrounding form and is rotated by the right servo torsion mechanism to control the opening and closing of the air inlet.

2. The closed cylinder temperature control air intake structure of the conventional layout piston engine of the unmanned aerial vehicle as claimed in claim 1, characterized in that: The left air duct fusion body includes a left inner air duct and a left outer air duct, and the right air duct fusion body includes a right inner air duct and a right outer air duct. The two side bulkheads of the body are respectively provided with a left duct connecting hole and a right duct connecting hole. The left inner air duct is connected with the left outer air duct through the left duct connecting hole, wherein the left inner air duct and the left outer air duct have an arc transition and the left outer air duct opens forward, and the right inner air duct is connected with the right outer air duct through the right duct connecting hole, wherein the right inner air duct and the right outer air duct have an arc transition and the right outer air duct opens toward the front, the opening of the left inner air duct forms a left air outlet, and the opening of the left outer air duct forms a left air inlet, the opening of the right inner air duct forms a right air outlet, and the opening of the right outer air duct forms a right air inlet, the left closed cover is semi-enclosed on the outside of the left outer air duct, and the right closed cover is semi-enclosed on the outside of the right outer air duct.

3. The closed cylinder temperature control air intake structure of the conventional layout piston engine of the unmanned aerial vehicle as claimed in claim 2, characterized in that: The left inner air duct and the right inner air duct are both parallel to the body bulkhead, the left air outlet is aligned with the left cylinder head of the engine, and the right air outlet is aligned with the right cylinder head of the engine.

4. The closed cylinder temperature control air intake structure of the conventional layout piston engine of the unmanned aerial vehicle as claimed in claim 2, characterized in that: The left servo torsion mechanism comprises a left servo and a left servo torsion shaft, wherein the left servo is installed at the outer wall on the left side of the fuselage and its output shaft is connected to the left servo torsion shaft, the left servo torsion shaft longitudinally passes through the upper and lower walls of the left outer air duct, and the upper and lower ends of the left closed cover are respectively fixedly connected to the upper and lower ends of the left servo torsion shaft, and the right servo torsion mechanism comprises a right servo and a right servo torsion shaft, wherein the right servo is installed at the outer wall on the right side of the fuselage and its output shaft is connected to the right servo torsion shaft, the right servo torsion shaft longitudinally passes through the upper and lower walls of the right outer air duct, and the upper and lower ends of the right closed cover are respectively fixedly connected to the upper and lower ends of the right servo torsion shaft.

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