Ventilation, heat insulation and heat dissipation mechanism for turbojet-powered unmanned aerial vehicle

Abstract

The utility model discloses a kind of ventilation heat insulation, heat dissipation mechanism for turbojet power unmanned aerial vehicle, including unmanned aerial vehicle, the unmanned aerial vehicle tail is equipped with turbojet engine, turbojet engine includes combustion chamber, combustion chamber is connected with tail nozzle, flow passage is formed between combustion chamber and unmanned aerial vehicle side wall, the inside of the unmanned aerial vehicle is fixedly connected with air inlet cavity corresponding to the outside of combustion chamber, air inlet cavity is annular, the side wall of air inlet cavity is throughly provided with the air inlet connected with unmanned aerial vehicle side wall, the side wall of air inlet cavity close to tail nozzle is throughly provided with air inlet cover, the utility model is provided with air inlet cavity, air inlet cavity is set by air inlet for air intake, air inlet cover is set in the side wall of air inlet cavity, gas fills in air inlet cavity inside after by air inlet cover and is sprayed, whereby it can guarantee that gas fills flow passage, guarantee heat dissipation and heat insulation effect.

Description

Technical Field

[0001] This utility model relates to the technical field of heat insulation and heat dissipation devices for aircraft, specifically a ventilation, heat insulation, and heat dissipation mechanism for a turbojet-powered unmanned aerial vehicle. Background Technology

[0002] When the engine is running, compressed air mixes with fuel in the combustion chamber, and the resulting high-temperature, high-pressure flame is ejected through the nozzle to generate thrust. The nozzle is in direct contact with the flame, and its surface temperature reaches thousands of degrees Celsius. This heat is transferred to the drone's airframe through convection and radiation. Currently, due to the advantages of composite materials, such as light weight and high specific strength, drone airframe components are generally made of composite materials. However, the heat resistance temperature of commonly used composite materials is generally around 100°C. If no measures are taken, the heat transferred from the engine nozzle will cause the temperature of the airframe components to exceed their heat resistance temperature, resulting in a decrease in airframe strength and affecting flight performance. If high-temperature resistant composite materials are used for the airframe components, it will increase the cost of the drone.

[0003] Patent CN201920936840.7, entitled "Ventilation, Heat Insulation, and Heat Dissipation Mechanism for Turbojet-Powered Unmanned Aerial Vehicles," discloses a device in which a jet engine is embedded in the tail section of the drone's fuselage. The jet engine has a combustion chamber, and a tail nozzle for ejecting high-speed airflow is located behind the combustion chamber. The inner wall of the drone's fuselage is rigidly connected to the outer surface of the jet engine's combustion chamber, with a gap between the inner wall and the combustion chamber forming a general airflow channel. An air inlet is provided on the front surface of the drone's fuselage, and a heat insulation pipe is fixedly installed on the outer wall of the tail nozzle. An air guide port is located between the front end of the heat insulation pipe and the engine's combustion chamber, leading to a split airflow channel between the heat insulation pipe and the tail nozzle. The front end of the heat insulation pipe is flared to increase the air intake at the air guide port between the tail nozzle and the heat insulation pipe. However, the gas entering the device only passes through the air inlet and cannot fill the general airflow channel before flowing out, limiting its heat dissipation and insulation effects. Therefore, a ventilation, heat insulation, and heat dissipation mechanism for turbojet-powered unmanned aerial vehicles is proposed. Utility Model Content

[0004] The purpose of this invention is to provide a ventilation, heat insulation, and heat dissipation mechanism for turbojet-powered unmanned aerial vehicles (UAVs) to solve the problems mentioned in the background art.

[0005] To solve the above-mentioned technical problems, this utility model provides the following technical solution: a ventilation, heat insulation and heat dissipation mechanism for a turbojet-powered unmanned aerial vehicle (UAV), including a UAV, a turbojet engine at the tail of the UAV, the turbojet engine including a combustion chamber, the combustion chamber being connected to a tail nozzle, a flow channel being formed between the combustion chamber and the side wall of the UAV, an air intake chamber being fixedly connected to the outside of the combustion chamber inside the UAV, the air intake chamber being annular, an air inlet connected to the side wall of the air intake chamber being provided through the side wall of the air intake chamber, and an air intake shroud being provided through the side wall of the air intake chamber near the tail nozzle.

[0006] According to the above technical solution, a number of annular baffles are fixedly connected inside the air intake cavity, and a number of through holes are provided through the end face of the annular baffles.

[0007] According to the above technical solution, the side wall of the UAV is provided with an air outlet on the outer side of the tail nozzle near the combustion chamber.

[0008] According to the above technical solution, a guide shroud is fixedly connected to the outer wall of the tail nozzle. The guide shroud has an annular cavity structure, and the side of the guide shroud near the combustion chamber is open. A through groove is provided through the side wall of the guide shroud at the air outlet.

[0009] According to the above technical solution, the side wall of the air guide shroud is provided with a plurality of first air inlet slots, which are evenly distributed in a ring. The air guide shroud is provided with a rotating plate inside, and the side wall of the rotating plate is provided with a second air inlet slot corresponding to the first air inlet slot.

[0010] According to the above technical solution, a baffle is fixedly connected to the surface of the rotating plate, and the baffle is located at the through groove.

[0011] Compared with the prior art, the beneficial effects achieved by this utility model are as follows: This utility model, by providing an air intake cavity with an air inlet for air intake and an air intake hood on the side wall of the air intake cavity, ensures that the gas fills the flow channel, thus guaranteeing heat dissipation and heat insulation effects. Specifically, it has the following advantages:

[0012] 1. By setting up an annular air intake chamber, the gas is sprayed out from the air intake hood after filling the air intake chamber, ensuring that the gas fully surrounds the combustion chamber, resulting in good heat dissipation and insulation effects;

[0013] 2. An annular baffle is installed inside the air intake chamber, and through holes are provided to slow down the gas flow speed and ensure that the gas can fill the air intake chamber before being ejected.

[0014] 3. An air outlet is provided. The high-speed flow of external air generates negative pressure, allowing cooling gas to be drawn out through the air outlet, thus accelerating the gas flow.

[0015] 4. Install an air guide shroud. Inside the air guide shroud is a rotating plate. Corresponding air intake slots are installed on the rotating plate and the air guide shroud to control the opening and closing of the air guide shroud. The air guide shroud can be opened when it is necessary to cool the tail nozzle. Attached Figure Description

[0016] The accompanying drawings are provided to further illustrate the present invention and form part of the specification. They are used together with the embodiments of the present invention to explain the present invention, but do not constitute a limitation thereof. In the drawings:

[0017] Figure 1 This is a schematic diagram of the main cross-sectional structure of this utility model;

[0018] Figure 2 This is a schematic diagram of the disassembled structure of the air guide cover of this utility model;

[0019] Figure 3 This is a schematic diagram of the structure of the first through slot on the air guide cover of this utility model in the open state;

[0020] Figure 4 This is a schematic diagram of the structure of the second through slot on the air guide cover of this utility model in the open state;

[0021] In the diagram: 1-UAV, 2-Combustion chamber, 3-Tail nozzle, 4-Flow channel, 5-Intake chamber, 6-Intake port, 7-Intake shroud, 8-Annular baffle, 9-Through hole, 10-Outlet, 11-Air guide shroud, 12-Passway, 13-First intake passway, 14-Rotating plate, 15-Second intake passway, 16-Baffle. Detailed Implementation

[0022] 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 of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0023] Please see Figure 1-4 This utility model provides a technical solution: a ventilation, heat insulation, and heat dissipation mechanism for a turbojet-powered unmanned aerial vehicle (UAV), comprising a UAV 1, such as... Figure 1 As shown, the UAV 1 is equipped with a turbojet engine at its tail. The turbojet engine includes a combustion chamber 2, which is connected to a tail nozzle 3. A flow channel 4 is formed between the combustion chamber 2 and the side wall of the UAV 1. An air intake chamber 5 is fixedly connected to the outside of the combustion chamber 2 inside the UAV 1. Figure 1As shown, the air intake cavity 5 is annular, and an air inlet 6 connected to the side wall of the UAV 1 is provided through the side wall of the air intake cavity 5. An air intake cover 7 is provided through the side wall of the air intake cavity 5 near the tail nozzle 3. In order to ensure the strength of the UAV 1, the volume of the air inlet 6 is limited. Therefore, the gas entering through the air inlet 6 must fill the annular air intake cavity 5 to ensure that the gas flows through the flow channel 4 in an annular manner, so as to achieve good heat insulation and heat dissipation effects.

[0024] Specifically, the air intake cavity 5 is fixedly connected with several annular partitions 8. The annular partitions 8 are coaxially arranged with the air intake cavity 5. Several through holes 9 are provided through the end face of the annular partitions 8. The gas flowing in through the air inlet 6 flows out through the through holes 9. This process will slow down the gas flow rate, so that the gas fills the air intake cavity 5 and then flows out through the air intake cover 7.

[0025] Specifically, the side wall of the UAV 1 is provided with an air outlet 10 on the outer side of the tail nozzle 3 near the combustion chamber 2. The air outlet 10 is located on the side wall of the UAV 1. When the UAV is flying, the gas flows over the surface at high speed, generating negative pressure, thereby accelerating the gas entering the flow channel 4 to flow out through the air outlet 10, ensuring the heat dissipation effect.

[0026] Specifically, a wind guide shroud 11 is fixedly connected to the outer wall of the tail nozzle 3, such as... Figure 2 As shown, the air guide shroud 11 has an annular cavity structure. The side of the air guide shroud 11 near the combustion chamber 2 is open. A through groove 12 is provided through the side wall of the air guide shroud 11 at the air outlet 10. Gas can flow through the through groove 12 into the flow channel formed between the tail nozzle 3 and the UAV 1 to dissipate heat and insulate the tail nozzle 3.

[0027] Specifically, the side wall of the air guide shroud 11 is provided with a plurality of first air intake slots 13, which are evenly distributed in a ring. The air guide shroud 11 is provided with a rotating plate 14 inside, and the side wall of the rotating plate 14 is provided with a second air intake slot 15 corresponding to the first air intake slots 13. The rotating plate 14 can rotate inside the air guide shroud 11. The drive mechanism for controlling the rotation of the rotating plate 14 is not specifically shown, but can be flexibly selected according to the actual situation. Controlling the rotation of the rotating plate 14 can control the first air intake slots 13 and the second air intake slots 15 to intersect or stagger, and control the opening and closing of the first air intake slots 13. Thus, at the initial stage of takeoff of the UAV 1, the first air intake slots 13 can be closed, allowing gas to flow out from the air outlet 10 to accelerate the heat dissipation of the combustion 2. After a long flight time, the first air intake slots 13 can be opened again to dissipate heat from the tail nozzle 3.

[0028] Specifically, a baffle 16 is fixedly connected to the surface of the rotating plate 14. The baffle 16 is located at the through groove 12. When the first air inlet through groove 13 is in the open state, the baffle 16 is exactly located at the through groove 12 to close the air outlet 10, so that all the gas can flow through the tail nozzle 3 to dissipate heat and insulate the tail nozzle 3. It should be noted that the tail of the UAV 1 needs to be provided with a nozzle for gas to flow out.

[0029] When this utility model is in use, the combustion chamber 2 generates a large amount of heat. When the drone is flying, the gas flows at high speed through the outlet 10, creating negative pressure. The gas enters the intake chamber 5 through the inlet 6, passes through the through hole 9, and is evenly sprayed out by the intake shroud 7 to dissipate heat and insulate the heat generated during combustion. When it is necessary to dissipate heat from the tail nozzle 3, the rotating plate 14 is controlled to rotate, the first intake channel 13 intersects with the second intake channel 15, and at the same time the baffle 16 blocks the inlet 6, and the gas is sprayed out from the tail nozzle 3 to complete the heat dissipation of the tail nozzle 3.

[0030] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0031] Finally, it should be noted that the above description is merely a preferred embodiment of this utility model and is not intended to limit the utility model. Although the utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. A ventilation, heat insulation, and heat dissipation mechanism for a turbojet-powered unmanned aerial vehicle (UAV), comprising the UAV (1), characterized in that: The UAV is equipped with a turbojet engine at its tail. The turbojet engine includes a combustion chamber (2) and a tail nozzle (3) connected to the combustion chamber (2). A flow channel (4) is formed between the combustion chamber (2) and the side wall of the UAV (1). An air intake chamber (5) is fixedly connected to the outside of the combustion chamber (2) inside the UAV (1). The air intake chamber (5) is annular. An air inlet (6) connected to the side wall of the air intake chamber (5) is provided through the side wall of the air intake chamber (5). An air intake shroud (7) is provided through the side wall of the air intake chamber (5) near the tail nozzle (3).

2. The ventilation, heat insulation, and heat dissipation mechanism for a turbojet-powered unmanned aerial vehicle according to claim 1, characterized in that: The air intake cavity (5) is fixedly connected with several annular partitions (8), and several through holes (9) are provided through the end face of the annular partitions (8).

3. The ventilation, heat insulation, and heat dissipation mechanism for a turbojet-powered unmanned aerial vehicle according to claim 2, characterized in that: The side wall of the UAV (1) has an air outlet (10) on the outer side of the end of the tail nozzle (3) near the combustion chamber (2).

4. The ventilation, heat insulation, and heat dissipation mechanism for a turbojet-powered unmanned aerial vehicle according to claim 3, characterized in that: The outer wall of the tail nozzle (3) is fixedly connected to a wind guide shroud (11). The wind guide shroud (11) has an annular cavity structure. The side of the wind guide shroud (11) near the combustion chamber (2) is open. A through groove (12) is provided through the side wall of the wind guide shroud (11) at the air outlet (10).

5. A ventilation, heat insulation, and heat dissipation mechanism for a turbojet-powered unmanned aerial vehicle according to claim 4, characterized in that: The side wall of the air guide shroud (11) is provided with a plurality of first air inlet slots (13), which are evenly distributed in a ring. The air guide shroud (11) is provided with a rotating plate (14) inside, and the side wall of the rotating plate (14) is provided with a second air inlet slot (15) corresponding to the first air inlet slots (13).

6. The ventilation, heat insulation, and heat dissipation mechanism for a turbojet-powered unmanned aerial vehicle according to claim 5, characterized in that: A baffle (16) is fixedly connected to the surface of the rotating plate (14), and the baffle (16) is located at the through groove (12).

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