High-temperature-resistant fire scene surveying unmanned aerial vehicle

Abstract

The utility model discloses a high-temperature-resistant fire scene surveying unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles. The unmanned aerial vehicle comprises an unmanned aerial vehicle body and further comprises a heat insulation cover, the heat insulation cover covers the outer side of the unmanned aerial vehicle body, a camera visual angle hole and four mechanical transmission arm passing holes are formed in the heat insulation cover, and a visual angle of a camera on the unmanned aerial vehicle body is right opposite to the camera visual angle hole. A mechanical transmission arm passing hole is formed in the unmanned aerial vehicle body and used for allowing a transmission arm on the unmanned aerial vehicle body to pass through and allowing a propeller at the end of the mechanical transmission arm to be located on the outer side of the heat insulation cover, and a cooling assembly is further arranged on the unmanned aerial vehicle body; and the cooling assembly is used for releasing cooling gas into the heat insulation cover under the control of the unmanned aerial vehicle body. The unmanned aerial vehicle has the advantages of high temperature resistance, relatively low cost and the like.

Description

TECHNICAL FIELD

[0001] The utility model relates to an unmanned plane technical field especially uses convenient high temperature resistant fire reconnaissance unmanned plane. BACKGROUND

[0002] Whenever there is a fire, the on-site commander will use an unmanned plane to detect the fire situation, but the existing unmanned plane reconnaissance relies on unmanned plane equipment and related sensors. Due to the high temperature of the fire, the image or data transmitted by the unmanned plane is unstable or interrupted, in addition, other electronic components of the unmanned plane, especially the battery, are prone to failure or damage, and there will be a great impact on the structural stress. Therefore, the flight height and speed of the unmanned plane may be limited, and even the unmanned plane may lose control, which not only affects the completion of the reconnaissance task, but also easily causes additional economic losses. In order to avoid the above problems, the unmanned plane in the prior art mainly solves the high temperature resistance problem of the unmanned plane by using high temperature resistant materials and improving battery technology. However, the protection of electronic components has not been greatly improved, especially the aircraft motor is installed outside the aircraft, and the high temperature influence received by the motor cannot be solved. SUMMARY

[0003] The technical problem to be solved by the utility model is how to provide a high temperature resistant fire reconnaissance unmanned plane with relatively low cost.

[0004] To solve the above technical problems, the utility model adopts the technical scheme of a high temperature resistant fire reconnaissance unmanned plane, which comprises an unmanned plane body, characterized in that: a heat shield is further arranged outside the unmanned plane body, a camera view angle hole and four mechanical transmission arm through holes are formed in the heat shield, the view angle of a camera on the unmanned plane body is arranged opposite to the camera view angle hole, the mechanical transmission arm through holes are used to make the transmission arm on the unmanned plane body pass through and make the propeller at the end of the mechanical transmission arm located outside the heat shield, and a cooling assembly is further arranged on the unmanned plane body and used to release cooling gas into the heat shield under the control of the unmanned plane body.

[0005] Four driving motors are arranged on the unmanned plane body, a first driving shaft arranged horizontally is connected to the power output end of each driving motor, a first bevel gear is arranged at the free end of the first driving shaft, a second driving shaft arranged vertically is rotatably connected to the driving shaft support shell, a second bevel gear is fixed to the second driving shaft in the driving shaft support shell, the second bevel gear is engaged with the first bevel gear, and the upper end of the second driving shaft extends to the outside of the driving shaft support shell, and a propeller is fixed to the end.

[0006] The cooling assembly includes multiple compressed gas cylinders. The upper opening of one of the compressed gas cylinders is closed and connected to one end of a gas connecting pipe, and the other end of the gas connecting pipe is closed by a rotary vent valve. The gas connecting pipe is closed by one compressed gas cylinder in cooperation with the rotary vent valve. The upper ends of the remaining compressed gas cylinders extend into the closed gas connecting pipe and are connected to it. The vent end of the rotary vent valve is connected to a vent pipe. The drive end of the rotary vent valve is connected to the power output shaft of a servo motor. The servo motor is used to drive the rotary vent valve to open or close via the power output shaft.

[0007] The beneficial effects of adopting the above technical solution are as follows: The UAV described in this application has multiple high-temperature resistant structures. First, a heat insulation cover is provided on the outside of the UAV body to isolate high temperatures and effectively reduce the impact of high temperatures on the UAV body. Second, a protective shell is provided on the outer part of the heat insulation cover to protect the corresponding components and further reduce the impact of high temperatures on the corresponding components. Third, a cooling component is provided inside the heat insulation cover, which can release cooling gas into the heat insulation cover as needed, further reducing the temperature of the UAV body. Using this UAV, close-range reconnaissance and surveying in fire scenes can be achieved, allowing for direct acquisition of fire scene information, enabling rescue personnel to fully understand the fire situation and formulate scientific and reasonable rescue plans. This not only improves rescue efficiency but also ensures the safety of rescue personnel, greatly improving the effectiveness of fire rescue. In addition, the fire-resistant structure of the UAV is simple, has low manufacturing cost, and is easy to modify. Attached Figure Description

[0008] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments.

[0009] Figure 1 This is a schematic diagram of the structure of the UAV described in this embodiment of the utility model;

[0010] Figure 2 This is a schematic diagram of the structure of the drone described in this embodiment of the utility model after removing part of the heat shield;

[0011] Figure 3 This is a schematic diagram of the structure of the UAV described in this embodiment of the utility model after removing some components;

[0012] Figure 4 This is a partially enlarged structural schematic diagram of the UAV described in this embodiment of the utility model;

[0013] Figure 5 This is a schematic diagram of the cooling component in the UAV described in this embodiment of the utility model;

[0014] Figure 6 This is a schematic diagram of the cooling component in the UAV described in this embodiment of the utility model;

[0015] The components include: 1. UAV body; 2. Heat shield; 3. Camera viewing aperture; 4. Camera; 5. Propeller; 6. First drive shaft; 7. First bevel gear; 8. Second drive shaft; 9. Drive shaft support shell; 10. Second bevel gear; 11. Drive shaft outer cover; 12. Upper support plate; 13. Lower support plate; 14. Compressed gas cylinder; 15. Gas connection pipeline; 16. Knob-type vent valve; 17. Vent pipe; 18. Servo motor; 19. Vent port. Detailed Implementation

[0016] 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 a part of the embodiments of the present utility model, and not all of them. 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.

[0017] Many specific details are set forth in the following description in order to provide a full understanding of the present invention. However, the present invention may also be implemented in other ways different from those described herein. Those skilled in the art can make similar extensions without departing from the spirit of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0018] like Figures 1-4 As shown in the figure, this utility model discloses a high-temperature fire scene reconnaissance drone, including a drone body 1. The specific structure of the drone body 1 can be a drone mechanism in the prior art, which is not the inventive point of this application. Therefore, its specific structure will not be described in detail here. Its specific structure only needs to meet the installation requirements of other components in this application. The specific structure of this application differs from the prior art in that the drone in this application also includes a heat insulation cover 2. The heat insulation cover 2 can be made of high-temperature heat-insulating materials in the prior art. The specific materials will not be described in detail here.

[0019] The heat shield 2 covers the outside of the drone body 1. The heat shield 2 has a camera viewing aperture 3 and four mechanical transmission arm passage holes. The camera 4 on the drone body 1 is positioned directly opposite the camera viewing aperture 3, allowing it to capture images of the usage environment. Furthermore, to withstand high-temperature environments, the camera 4 can be a fixed-focus camera made of high borosilicate glass. The mechanical transmission arm passage holes allow the transmission arms on the drone body 1 to pass through, and position the propellers 5 at the ends of the mechanical transmission arms outside the heat shield 2. The drone body 1 also has a cooling assembly that releases cooling gas into the heat shield 2 under the control of the drone body 1.

[0020] The UAV body 1 is equipped with four drive motors (this part is prior art). The difference between this application and the prior art lies in: Figures 2-4 As shown, each of the drive motors has a horizontally arranged first drive shaft 6 connected to its power output end. A first bevel gear 7 is provided at the free end of the first drive shaft 6. A vertically arranged second drive shaft 8 is rotatably connected to a drive shaft support housing 9. A second bevel gear 10 is fixed on the second drive shaft 8 located inside the drive shaft support housing 9. The second bevel gear 10 meshes with the first bevel gear 7. The upper end of the second drive shaft 8 extends to the outside of the drive shaft support housing 9, and a propeller 5 (this part is prior art) is fixed on this end. Preferably, the propeller 5 is made of refractory material.

[0021] Furthermore, the drone also includes a drive shaft cover 11. The upper inner part of the drive shaft cover 11 is fixedly connected to the upper support plate 12 via an upper support seat, and the lower inner part of the drive shaft cover 11 is fixedly connected to the lower support plate 13 via a lower support seat. The outer end of the drive shaft cover 11 is fixedly connected to the drive shaft support shell 9 to form a protective cover for the first drive shaft 6 and the second drive shaft 8. This application uses bevel gears for transmission, which improves the stability of the transmission. In addition, by setting the drive shaft support shell 9 and the drive shaft cover 11, high temperature can be effectively prevented from affecting the first drive shaft 6 and the second drive shaft 8, thereby improving the heat resistance temperature of the drone.

[0022] Furthermore, this application differs from the prior art in that: Figures 5-6As shown, the cooling assembly includes multiple compressed gas cylinders 14. Preferably, three compressed gas cylinders 14 are provided. The upper opening of the first compressed gas cylinder 14 is closed and connected to one end of the gas connecting pipe 15, and the two cylinders are interconnected. The other end of the gas connecting pipe 15 is closed by a knob-type vent valve 16, which is fixed to the lower support plate 13. The compressed gas cylinders 14, the gas connecting pipe 15, and the knob-type vent valve 16 constitute a cooling gas receiving cavity, which is filled with carbon dioxide or liquid nitrogen.

[0023] The gas connection pipeline 15 is fixed to the lower support plate 13 by two U-shaped brackets. A compressed gas cylinder 14, in conjunction with the rotary vent valve 16, seals the gas connection pipeline 15. The upper ends of the other two compressed gas cylinders 14 extend into the sealed gas connection pipeline 15 and are connected to it. The venting end of the rotary vent valve 16 is connected to a vent pipe 17, which has several vent ports 19, allowing for rapid and uniform venting. The drive end of the rotary vent valve 16 is connected to the power output shaft of a servo motor 18, which is fixed to the upper support plate 12. The servo motor 18 drives the rotary vent valve 16 to open or close via the power output shaft.

[0024] The UAV described in this application can effectively improve its heat resistance temperature by setting up a heat shield 2 and cooling components, adapt to various complex environments in the fire scene, realize close reconnaissance and survey in the fire scene, intuitively obtain information about the fire scene, and enable rescuers to fully understand the fire scene situation and formulate scientific and reasonable rescue plans.

Claims

1. A high-temperature-resistant fire scene investigation unmanned aerial vehicle, comprising a unmanned aerial vehicle body (1), characterized in that: Further comprising a heat shield (2) which is covered to the outside of the UAV body (1), a camera view hole (3) and four mechanical transmission arm through holes are formed on the heat shield (2), the view angle of the camera (4) on the UAV body (1) is arranged opposite to the camera view hole (3), the mechanical transmission arm through holes are used for the transmission arm on the UAV body (1) to pass through, and the propeller (5) at the end of the mechanical transmission arm is located outside the heat shield (2), a cooling assembly is further arranged on the UAV body (1), and the cooling assembly is used for releasing cooling gas into the heat shield (2) under the control of the UAV body (1).

2. The high-temperature fire scene investigation drone of claim 1, wherein: The UAV body (1) is provided with four driving motors, the power output end of each driving motor is connected with a horizontally arranged first driving shaft (6), the free end of the first driving shaft (6) is provided with a first bevel gear (7), a vertically arranged second driving shaft (8) is rotatably connected into a driving shaft support shell (9), a second bevel gear (10) is fixed on the second driving shaft (8) in the driving shaft support shell (9), the second bevel gear (10) is engaged with the first bevel gear (7), and the upper end of the second driving shaft (8) extends to the outside of the driving shaft support shell (9), and a propeller (5) is fixed on the end.

3. The high-temperature fire scene investigation drone of claim 2, wherein: The propeller (5) is made of refractory material.

4. The high-temperature fire scene investigation drone of claim 2, wherein: The UAV further comprises a driving shaft cover (11), the inner side upper part of the driving shaft cover (11) is fixedly connected with an upper support plate (12) through an upper support seat, the inner side lower part of the driving shaft cover (11) is fixedly connected with a lower support plate (13) through a lower support seat, and the outer side end of the driving shaft cover (11) is fixedly connected with the driving shaft support shell (9) to form a protective cover of the first driving shaft (6) and the second driving shaft (8).

5. The high-temperature fire scene investigation drone of claim 1, wherein: The cooling assembly comprises a plurality of compressed gas cylinders (14), the upper end opening of one of the compressed gas cylinders (14) is closedly connected with one end of a gas communication pipeline (15) and is communicated with each other, the other end of the gas communication pipeline (15) is closed through a rotary knob type gas discharge valve (16), the gas communication pipeline (15) is closed through cooperation of one compressed gas cylinder (14) and the rotary knob type gas discharge valve (16), the upper end of the remaining compressed gas cylinders (14) extends into the closed gas communication pipeline (15) and is communicated with the gas communication pipeline (15), a gas discharge pipe (17) is connected to the gas discharge end of the rotary knob type gas discharge valve (16), the driving end of the rotary knob type gas discharge valve (16) is connected with the power output shaft of a rudder (18), and the rudder (18) is used for driving the rotary knob type gas discharge valve (16) to be opened or closed through the power output shaft.

6. The high-temperature fire scene investigation drone of claim 5, wherein: A plurality of gas discharge ports (19) are formed on the gas discharge pipe (17).

7. The high-temperature fire scene investigation drone of claim 5, wherein: The gas communication pipeline (15) is fixed on the lower support plate (13) through two U-shaped supports, the rudder is fixed on the upper support plate (12), and the rotary knob type gas discharge valve (16) is fixed on the lower support plate (13).

8. The high-temperature fire scene investigation drone of claim 1, wherein: The camera (4) is a fixed-focus camera made of high borosilicate glass.

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