Heat preservation shell structure of polar region monitoring unmanned aerial vehicle

Abstract

The utility model belongs to the technical field of unmanned aerial vehicle shells, and particularly relates to a polar region monitoring unmanned aerial vehicle heat preservation shell structure which comprises a fuselage, an upper shell abutting against the surface of the fuselage, protruding blocks installed on the inner wall surface of the upper shell, aerogel plates slidably connected to the surfaces of the protruding blocks, the inner wall surface of the aerogel plates abutting against the fuselage, and clamping blocks connected to the bottom surface of the upper shell. The surface of the clamping block is connected to the limiting block in a clamped mode, the surface of the clamping block is connected to the lower shell, a protruding block is arranged on the surface of the inner wall of the lower shell, the surface of the aerogel plate abuts against the machine body, and the surface of the top of the lower shell abuts against the upper shell. And the polar region monitoring work of the unmanned aerial vehicle is prevented from being influenced by the risks of power failure and motor damage of the unmanned aerial vehicle caused by too low temperature in the polar region environment.

Description

Technical Field

[0001] The utility model belongs to the technical field of unmanned aerial vehicle shells, and in particular relates to a thermal insulation shell structure of a polar monitoring unmanned aerial vehicle. Background Art

[0002] With the advancement of electronic equipment technology, drones are widely used in various occasions. In order to meet the growing market demand, the improvement of drone structural performance has become a development trend. Among them, the "drone shell structure" disclosed by the application number "CN201620919726.X" is also an increasingly mature technology. When it is necessary to monitor the polar environment, drones are used to monitor the environment at high altitudes. At the same time, the drone shell protects the components inside the fuselage. However, the device still has the following defects: When the above-mentioned equipment is in use, the existing drone shell can only protect the internal components of the drone. When the environment is polar low temperature, the normal operation of the drone is easily affected by the low temperature. In addition, the terrains of existing drones are different when they land. Long-term direct use of the drone shell to touch the ground is likely to damage the drone shell and affect its service life. Utility Model Content

[0003] The utility model aims to provide a thermal insulation shell structure for a polar monitoring UAV, aiming to solve the problem in the prior art that when the above-mentioned equipment is in use, the existing UAV shell can only protect the internal components of the UAV. When the environment is polar low temperature, the normal operation of the UAV is easily affected by the low temperature. In addition, the terrains for the landing of existing UAVs are different. Long-term direct use of the UAV shell to touch the ground is likely to damage the UAV shell and affect its service life.

[0004] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a thermal insulation shell structure of a polar monitoring UAV, comprising: a fuselage, the surface of the fuselage abuts against an upper shell, a protrusion is installed on the inner wall surface of the upper shell, the surface of the protrusion is slidably connected to an aerogel plate, the inner wall surface of the aerogel plate abuts against the fuselage, the bottom surface of the upper shell is connected to a card block, the surface of the card block is snap-connected to a limit block, the surface of the card block is connected to a lower shell, the inner wall surface of the lower shell is provided with a protrusion, the surface of the aerogel plate abuts against the fuselage, and the top surface of the lower shell abuts against the upper shell.

[0005] In order to make it possible to utilize the protrusions installed on the inner walls of the upper and lower shells to conveniently install the aerogel plates on the inner walls of the upper and lower shells to provide thermal insulation protection for the body therein, the utility model provides a thermal insulation outer shell structure for a polar monitoring UAV, the upper shell, the protrusions and the aerogel plates form a sliding connection structure, the protrusions, the aerogel plates and the lower shell form a sliding connection structure, and a "T"-shaped groove is provided on the surface of the aerogel plate to match the shape and size of the protrusions.

[0006] In order to make use of the card block to engage in the limit block to quickly connect and fix the upper shell and the lower shell, as a thermal insulation shell structure of a polar monitoring UAV according to the utility model, the upper shell, the card block, the limit block and the lower shell form a card-engaging connection structure, and the inner wall of the limit block is provided with an "L"-shaped groove that matches the shape and size of the card block.

[0007] In order to utilize the spring damper installed at the bottom of the lower shell and the anti-skid pad connected to the bottom thereof to cushion the lower shell when it touches the ground and prevent the shell from directly contacting the ground, the utility model provides a thermal insulation shell structure for a polar monitoring UAV, an installation groove is provided on the bottom surface of the lower shell, a spring damper is fixedly installed on the surface of the installation groove, the bottom surface of the spring damper is connected to a connecting plate, and the bottom surface of the connecting plate is threadedly connected to the anti-skid pad.

[0008] In order to make the lower shell land smoothly by using the spring damper and connecting plate installed at the bottom of the lower shell, the utility model provides a thermal insulation shell structure of a polar monitoring UAV, in which the lower shell, the mounting groove, the spring damper and the connecting plate form an elastic connection structure, and the connecting plate is a "well" type integrated structure.

[0009] In order to increase the friction of the position in contact with the ground by connecting the anti-skid pad to the bottom of the connecting plate to avoid unstable parking, the utility model provides a polar monitoring UAV thermal insulation shell structure, the connecting plate and the anti-skid pad form a threaded connection structure, and a threaded groove is provided on the bottom surface of the connecting plate that matches the shape and size of the upper end of the anti-skid pad, and eight anti-skid pads are evenly spaced at the bottom of the connecting plate.

[0010] Compared with the prior art, the beneficial effects of the utility model are:

[0011] Aerogel plates installed in the upper and lower shells are used to insulate the fuselage in the middle, thus avoiding the risk of power failure and motor damage to the UAV due to low temperature in the polar environment, which would affect the UAV's polar monitoring work.

[0012] The spring damper installed in the installation groove at the bottom of the lower shell of the drone and the anti-skid pad threaded on the connecting block at the bottom protect the bottom of the lower shell to avoid the impact of the lower shell directly contacting the ground during landing, which may cause damage to the bottom of the lower shell and extend the service life of the drone shell. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] The accompanying drawings are used to provide a further understanding of the present invention and constitute a part of the specification. Together with the embodiments of the present invention, they are used to explain the present invention and do not constitute a limitation of the present invention. In the accompanying drawings:

[0014] Figure 1 This is a schematic diagram of the main structure of the utility model;

[0015] Figure 2 This is a schematic diagram of the main cross-sectional structure of the utility model;

[0016] Figure 3 It is a side cross-sectional structural schematic diagram of the utility model;

[0017] Figure 4 It is a schematic diagram of the enlarged cross-sectional structure of the bump and aerogel plate of the utility model;

[0018] Figure 5 For the utility model Figure 3 A schematic diagram of the enlarged structure of part A.

[0019] In the figure: 1, fuselage; 2, upper shell; 3, protrusion; 4, aerogel plate; 5, clamping block; 6, limit block; 7, lower shell; 8, mounting groove; 9, spring damper; 10, connecting plate; 11, anti-slip pad. DETAILED DESCRIPTION

[0020] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions 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 creative work are within the scope of protection of the utility model.

[0021] See also Figure 1-5 The utility model provides the following technical solutions: a thermal insulation shell structure of a polar monitoring UAV, comprising: a fuselage 1, the surface of the fuselage 1 abuts against an upper shell 2, a protrusion 3 is installed on the inner wall surface of the upper shell 2, the surface of the protrusion 3 is slidably connected to an aerogel plate 4, the inner wall surface of the aerogel plate 4 abuts against the fuselage 1, the bottom surface of the upper shell 2 is connected to a card block 5, the surface of the card block 5 is snap-connected to a limit block 6, the surface of the card block 5 is connected to a lower shell 7, the inner wall surface of the lower shell 7 is provided with a protrusion 3, the surface of the aerogel plate 4 abuts against the fuselage 1, and the top surface of the lower shell 7 abuts against the upper shell 2.

[0022] Preferably: the upper shell 2, the protrusion 3 and the aerogel plate 4 form a sliding connection structure, the protrusion 3, the aerogel plate 4 and the lower shell 7 form a sliding connection structure, and a "T"-shaped groove is provided on the surface of the aerogel plate 4 to match the shape and size of the protrusion 3.

[0023] During specific use, the aerogel plate 4 can be quickly installed on the inner walls of the upper shell 2 and the lower shell 7 by using the protrusions 3 installed inside the upper shell 2 and the lower shell 7 to insulate the fuselage 1 placed therebetween to avoid low temperature damaging the motor inside the fuselage 1.

[0024] Preferably, the upper shell 2 , the clamping block 5 , the limiting block 6 and the lower shell 7 form a clamping connection structure, and an “L”-shaped groove is provided on the inner wall of the limiting block 6 to match the shape and size of the clamping block 5 .

[0025] When in use, the four clamping blocks 5 installed at the bottom of the upper shell 2 are clamped into the limiting blocks 6 installed on the surface of the lower shell 7 to quickly fix the connection between the upper shell 2 and the lower shell 7.

[0026] Preferably, a mounting groove 8 is provided on the bottom surface of the lower shell 7, a spring damper 9 is fixedly installed on the surface of the mounting groove 8, a connecting plate 10 is connected to the bottom surface of the spring damper 9, and an anti-slip pad 11 is threadedly connected to the bottom surface of the connecting plate 10.

[0027] During specific use, the bottom of the lower shell 7 is blocked and protected by the spring damper 9 installed in the installation groove 8 opened at the bottom of the lower shell 7 and the anti-skid pad 11 threadedly connected to the bottom of the connecting plate 10 connected to the bottom thereof, so as to prevent it from directly contacting the ground and causing damage when falling.

[0028] Preferably, the lower shell 7, the mounting groove 8, the spring damper 9 and the connecting plate 10 form an elastic connecting structure, and the connecting plate 10 is a "well" type integrated structure.

[0029] When in use, the lower shell 7 can fall to the ground smoothly by utilizing the connecting plate 10 connected to the bottom of the spring damper 9 installed at the bottom of the lower shell 7 .

[0030] Preferably, the connecting plate 10 and the anti-skid pad 11 form a threaded connection structure, a thread groove is provided on the bottom surface of the connecting plate 10 to match the shape and size of the upper end of the anti-skid pad 11 , and eight anti-skid pads 11 are evenly spaced and distributed on the bottom of the connecting plate 10 .

[0031] During specific use, the threaded groove at the bottom of the connecting plate 10 is used to facilitate installation and removal of the anti-skid pad 11 , and the worn anti-skid pad 11 can be easily replaced after long-term use.

[0032] Working principle: When using a drone for monitoring in the polar regions, the aerogel plate 4 slidingly connected to the bump 3 installed on the inner wall of the upper shell 2 abutting against the surface of the fuselage 1 is used to insulate the internal fuselage 1. At the same time, the bottom of the fuselage 1 is protected by the lower shell 7 and the bump 3 and aerogel plate 4 inside it to prevent the fuselage 1 from being powered off and the motor from being damaged by low temperature. At the same time, the block 5 connected to the bottom surface of the upper shell 2 is snapped into the limit block 6 on the surface of the lower shell 7 to quickly fix the connection between the upper shell 2 and the lower shell 7. It can also be easily disassembled to replace the internal aerogel plate 4 and to inspect and maintain the fuselage 1. After installation, After completion, a spring damper 9 is installed in the installation groove 8 opened at the bottom of the lower shell 7, and a threaded groove is opened on the bottom surface of the connecting plate 10 connected to the bottom, so that the anti-skid pad 11 can be quickly installed and disassembled. After long-term use of the anti-skid pad 11 for landing anti-skid, the anti-skid pad 11 can be easily replaced with a new one due to wear. When the fuselage 1 lands, the spring damper 9 at the bottom of the lower shell 7 and the anti-skid pad 11 installed under the bottom connecting plate 10 are used to block the lower shell 7 and the ground, so as to avoid damage caused by direct contact of the lower shell 7 during landing. This is a characteristic of the thermal insulation shell structure of a polar monitoring UAV.

[0033] Finally, it should be noted that the above are only preferred embodiments of the present invention and are not intended to limit the present invention. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art can still modify the technical solutions described in the above embodiments or replace some of the technical features therein by equivalents. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A thermal insulation shell structure for a polar monitoring UAV, comprising: A fuselage (1), characterized in that: the surface of the fuselage (1) abuts against an upper shell (2), a protrusion (3) is installed on the inner wall surface of the upper shell (2), the surface of the protrusion (3) is slidably connected to an aerogel plate (4), the inner wall surface of the aerogel plate (4) abuts against the fuselage (1), the bottom surface of the upper shell (2) is connected to a clamping block (5), the surface of the clamping block (5) is clamped and connected to a limit block (6), the surface of the clamping block (5) is connected to a lower shell (7), the inner wall surface of the lower shell (7) is provided with a protrusion (3), the surface of the aerogel plate (4) abuts against the fuselage (1), and the top surface of the lower shell (7) abuts against the upper shell (2).

2. The thermal insulation shell structure of a polar monitoring UAV according to claim 1 is characterized in that: The upper shell (2), the protrusion (3) and the aerogel plate (4) form a sliding connection structure, and the protrusion (3), the aerogel plate (4) and the lower shell (7) form a sliding connection structure. A "T"-shaped groove is provided on the surface of the aerogel plate (4) and matches the shape and size of the protrusion (3).

3. The thermal insulation shell structure of a polar monitoring UAV according to claim 1 is characterized in that: The upper shell (2), the clamping block (5), the limiting block (6) and the lower shell (7) form a clamping connection structure, and the inner wall of the limiting block (6) is provided with an "L"-shaped groove that matches the shape and size of the clamping block (5).

4. The thermal insulation shell structure of a polar monitoring UAV according to claim 1 is characterized in that: The bottom surface of the lower shell (7) is provided with a mounting groove (8), a spring damper (9) is fixedly mounted on the surface of the mounting groove (8), the bottom surface of the spring damper (9) is connected to a connecting plate (10), and the bottom surface of the connecting plate (10) is threadedly connected to an anti-slip pad (11).

5. The thermal insulation shell structure of a polar monitoring UAV according to claim 4, characterized in that: The lower shell (7), the mounting groove (8), the spring damper (9) and the connecting plate (10) form an elastic connection structure, and the connecting plate (10) is a "well"-shaped integrated structure.

6. The thermal insulation shell structure of a polar monitoring UAV according to claim 4, characterized in that: The connecting plate (10) and the anti-skid pad (11) form a threaded connection structure; a threaded groove is provided on the bottom surface of the connecting plate (10) and matches the shape and size of the upper end of the anti-skid pad (11); eight anti-skid pads (11) are distributed at equal intervals on the bottom of the connecting plate (10).

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