Thermal insulation structure of cabin of polar region monitoring unmanned aerial vehicle

Abstract

The utility model belongs to the technical field of unmanned aerial vehicle cabins, and particularly relates to a polar region monitoring unmanned aerial vehicle cabin heat preservation structure which comprises a cabin shell, heat preservation cotton is connected to the surface of the inner side of the cabin shell, and a temperature sensor is connected to the surface of one side in the cabin shell. Through mutual cooperation of the heat preservation cotton, the temperature sensor, the protruding block, the heating block and the fan, when the temperature sensor detects that the temperature in the cabin shell is low, the PLC control switch can start the heating block and the fan, so that hot air is conveyed into the cabin shell, the temperature in the cabin shell can be increased, and the heat preservation effect of the cabin shell is improved. The temperature of the cabin shell is ensured not to be too low, heat preservation cotton can improve the heat preservation effect in the cabin shell, a shielding mechanism is arranged to enable a first baffle and a second baffle to shield a through groove and a through hole, hot air in the cabin shell is prevented from being emitted out from an air inlet and an air outlet, and the heat preservation effect in the cabin shell is improved. And the temperature reduction speed in the cabin shell is slowed down.

Description

Technical Field

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

[0002] Polar monitoring is the process of continuous and systematic observation and research of polar regions, aiming to understand the dynamic changes in the polar environment, predict future trends, and assess the impact of these changes on the global climate and environment.

[0003] At present, when conducting polar monitoring, operators generally use drones for monitoring operations, which can more conveniently monitor the polar regions. When drones are in use, drone cabins are generally used to store the drones. Various components are installed inside the cabin shell, and the temperature in the polar regions is relatively low, so the cabin shell temperature will be relatively low. If the temperature inside the shell is not increased in time and the temperature is not kept within a certain range, the internal components of the shell will be affected by the low temperature, resulting in failure to operate normally.

[0004] Therefore, the utility model provides a polar monitoring UAV cabin insulation structure to solve the above problems. Utility Model Content

[0005] The purpose of the utility model is to provide a cabin insulation structure for a polar monitoring UAV, aiming to solve the problem in the prior art that if the temperature inside the shell is not timely increased and the temperature is not maintained within a certain range, the internal components of the shell will be affected by the low temperature.

[0006] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a polar monitoring UAV cabin insulation structure, including a cabin shell, the inner surface of the cabin shell is connected with insulation cotton, and the inner surface of the cabin shell is connected with a temperature sensor, one side surface of the cabin shell is provided with an air inlet, and the side surface of the cabin shell outside the air inlet is connected with a protrusion, and the side surface of the protrusion is provided with a through groove, the inner surface at one end of the through groove is connected with a heating block, and the inner surface at the other end of the through groove is connected with a fan, the other side surface of the cabin shell is provided with an air outlet, the inner surfaces of the air inlet and the air outlet are both connected with protective nets, and shielding mechanisms are also provided at both ends of the cabin shell.

[0007] In order to achieve shielding of the air inlet and the air outlet, as a preferred insulation structure of a polar monitoring drone cabin of the utility model, the shielding mechanism includes: a first baffle, a connecting block, a first electric push rod, a vertical block, a through hole, a slide groove, a second baffle and a second electric push rod, the first baffle is connected to the first baffle on one side surface of the protrusion, the connecting blocks are connected to the connecting blocks on both end surfaces of the first baffle, the movable end of the first electric push rod is connected to the surface of one side of the connecting block, the vertical block is connected to the surface of one side of the cabin shell outside the air inlet, a through hole is formed on one side surface of the vertical block, and a slide groove is formed on the top surface of the vertical block, the second baffle is connected to the inner surface of the slide groove, and the movable end of the second electric push rod is connected to the top surface of the second baffle.

[0008] In order to ensure that the thermal insulation cotton does not block the air inlet and the air outlet, as a preferred thermal insulation structure of a polar monitoring UAV cabin of the utility model, the surfaces of both sides of the thermal insulation cotton are provided with grooves that match the size and position of the air inlet and the air outlet.

[0009] In order to achieve normal operation control of the temperature sensor, heating block, fan, first electric push rod and second electric push rod, as a preferred insulation structure of a polar monitoring UAV cabin of the utility model, the temperature sensor, heating block, fan, first electric push rod and second electric push rod are electrically connected to an external power supply through a PLC control switch.

[0010] In order to cover the through groove, as a preferred thermal insulation structure of a polar monitoring UAV cabin of the utility model, the size of the first baffle is larger than the size of the through groove.

[0011] In order to achieve the movement of the second baffle and cover the through hole, as a preferred insulation structure of a polar monitoring UAV cabin of the utility model, the second baffle is slidably connected to the vertical block through a slide groove, and the size of the second baffle is larger than the size of the through hole.

[0012] Compared with the prior art, the beneficial effects of the utility model are:

[0013] 1. The utility model cooperates with the thermal insulation cotton, the temperature sensor, the convex block, the heating block and the fan. When the temperature sensor detects that the temperature inside the cabin shell is low, the PLC control switch will start the heating block and the fan to transport hot air to the inside of the cabin shell, thereby increasing the temperature inside the cabin shell and ensuring that the temperature of the cabin shell will not be too low. The thermal insulation cotton can also improve the thermal insulation effect inside the cabin shell.

[0014] 2. The utility model has a shielding mechanism. When the internal temperature of the cabin shell reaches a set value, the PLC control switch will start the first electric push rod and the second electric push rod, so that the first baffle plate and the second baffle plate will shield the through groove and the through hole, thereby preventing the hot air inside the cabin shell from being emitted from the air inlet and the air outlet, and slowing down the speed at which the internal temperature of the cabin shell decreases. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] 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:

[0016] Figure 1 This is a first side structural schematic diagram of the utility model;

[0017] Figure 2 This is a second side structural schematic diagram of the utility model;

[0018] Figure 3 This is a schematic diagram of the local explosion structure of the convex block of the utility model;

[0019] Figure 4 This is a schematic diagram of the partial explosion structure of the standing block of the utility model;

[0020] Figure 5 It is a schematic diagram of the partial cross-sectional structure of the temperature sensor of the utility model.

[0021] In the figure: 1. Cabin shell; 2. Insulation cotton; 3. Temperature sensor; 4. Air inlet; 5. Bump; 6. Through groove; 7. Heating block; 8. Fan; 9. Air outlet; 10. Protective net; 11. First baffle; 12. Connecting block; 13. First electric push rod; 14. Vertical block; 15. Through hole; 16. Slide groove; 17. Second baffle; 18. Second electric push rod. DETAILED DESCRIPTION

[0022] 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.

[0023] See also Figure 1-Figure 5The utility model provides the following technical solutions: a polar monitoring UAV cabin insulation structure, including a cabin shell 1, an inner surface of the cabin shell 1 is connected with a thermal insulation cotton 2, and a temperature sensor 3 is connected to the inner surface of the cabin shell 1, the temperature sensor 3 model is MD-HT100, an air inlet 4 is provided on one side surface of the cabin shell 1, a bump 5 is connected to the one side surface of the cabin shell 1 outside the air inlet 4, a through groove 6 is provided on one side surface of the bump 5, a heating block 7 is connected to the inner surface at one end of the through groove 6, the heating block 7 is a PTC heating plate, and a fan 8 is connected to the inner surface at the other end of the through groove 6, an air outlet 9 is provided on the other side surface of the cabin shell 1, and a protective net 10 is connected to the inner surfaces of the air inlet 4 and the air outlet 9, and shielding mechanisms are also provided at both ends of the cabin shell 1.

[0024] Preferably: the shielding mechanism includes: a first baffle 11, a connecting block 12, a first electric push rod 13, a vertical block 14, a through hole 15, a slide groove 16, a second baffle 17 and a second electric push rod 18, one side surface of the protrusion 5 is connected to the first baffle 11, both end surfaces of the first baffle 11 are connected to the connecting blocks 12, one side surface of the connecting block 12 is connected to the movable end of the first electric push rod 13, one side surface of the cabin shell 1 outside the air inlet 4 is connected to the vertical block 14, one side surface of the vertical block 14 is provided with a through hole 15, and the top surface of the vertical block 14 is provided with a slide groove 16, the inner surface of the slide groove 16 is connected to the second baffle 17, and the top surface of the second baffle 17 is connected to the movable end of the second electric push rod 18.

[0025] During specific use, the movable end of the first electric push rod 13 will drive the connecting block 12 to move, so that the first baffle 11 will move to one side of the protrusion 5, so that the first baffle 11 can cover the through groove 6, and at the same time the movable end of the second electric push rod 18 will drive the second baffle 17 to slide in the slide groove 16, when the second baffle 17 completely slides into the slide groove 16, the second baffle 17 will cover one end of the through hole 15, so that the through groove 6 and the through hole 15 connecting the air inlet 4 and the air outlet 9 will not be connected to the external environment.

[0026] Preferably, the surfaces of both sides of the thermal insulation cotton 2 are provided with notches that match the size and position of the air inlet 4 and the air outlet 9 .

[0027] During specific use, the heat-insulating cotton 2 will not block the air inlet 4 and the air outlet 9 .

[0028] Preferably, the temperature sensor 3, the heating block 7, the fan 8, the first electric push rod 13 and the second electric push rod 18 are electrically connected to an external power supply via a PLC control switch.

[0029] During specific use, the temperature sensor 3, the heating block 7, the fan 8, the first electric push rod 13 and the second electric push rod 18 can be controlled by a PLC control switch. The outer sides of the first electric push rod 13 and the second electric push rod 18 are both provided with an insulation shell. The heating block 7 is a PTC heating plate, so the transported wind will be heated when passing through the gap of the PTC heating plate, so that the generated hot air will continue to be transported.

[0030] Preferably, the size of the first baffle 11 is larger than that of the through slot 6 , the second baffle 17 is slidably connected to the upright block 14 via the slide slot 16 , and the size of the second baffle 17 is larger than that of the through hole 15 .

[0031] During specific use, the first baffle 11 can cover the through slot 6 , and the second baffle 17 can slide in the slide slot 16 , so that the second baffle 17 can cover or open the through hole 15 .

[0032] Working principle: When the cabin insulation structure of the polar monitoring drone is used, the PLC control switch is programmed. When the temperature sensor 3 inside the cabin shell 1 detects that the temperature inside the cabin shell 1 is too low, the PLC control switch will start the first electric push rod 13 and the second electric push rod 18, so that the movable end of the first electric push rod 13 will drive the first baffle 11 on the connecting block 12 to move, so that the first baffle 11 no longer blocks the through slot 6, and the movable end of the second electric push rod 18 will drive the second baffle 17 to move in the slide slot 16. The through hole 15 is slidable so that the through hole 15 is no longer blocked by the second baffle 17. At this time, the heating block 7 and the fan 8 are started. The fan 8 transmits the external air to the heating block 7 through the opening on one side of the through slot 6. At this time, the heating block 7 heats the air, so that the heated air is transmitted to the inside of the cabin shell 1 from the air inlet 4, and the cold air inside the cabin shell 1 is transmitted out from the air outlet 9. After a period of air circulation, the temperature inside the cabin shell 1 will rise, ensuring that the temperature of the cabin shell 1 will not be too low, resulting in the inside The internal components are affected, and the provided insulation cotton 2 can improve the insulation effect inside the cabin shell 1. When the temperature sensor 3 detects that the temperature inside the cabin shell 1 remains at the set value for a long time, the PLC control switch starts the first electric push rod 13 and the second electric push rod 18 again, so that the movable end of the first electric push rod 13 drives the connecting block 12 to move, so that the first baffle 11 moves to one side of the protrusion 5, so that the first baffle 11 can cover the through groove 6, and at the same time the movable end of the second electric push rod 18 drives the first electric push rod 13 to move to the side of the protrusion 5, so that the first baffle 11 can cover the through groove 6. The second baffle 17 slides in the slide groove 16. When the second baffle 17 completely slides into the slide groove 16, the second baffle 17 will cover one end of the through hole 15, so that the through groove 6 and the through hole 15 connecting the air inlet 4 and the air outlet 9 will not be connected to the external environment, so that the hot air inside the cabin shell 1 will not be emitted from the air inlet 4 and the air outlet 9, slowing down the speed at which the temperature inside the cabin shell 1 decreases, avoiding the situation where the heating block 7 and the fan 8 are frequently started due to the internal temperature of the cabin shell 1 dropping too fast, resulting in waste of electric energy.

[0033] Finally, it should be noted that the above description is only a preferred embodiment of the utility model and is not intended to limit the utility model. Although the utility model is described in detail with reference to the above embodiments, those skilled in the art can still modify the technical solutions recorded 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 utility model shall be included in the protection scope of the utility model.

Claims

1. A cabin insulation structure for a polar monitoring drone, comprising a cabin shell (1), characterized in that: The inner surface of the cabin shell (1) is connected with a heat preservation cotton (2), and the inner surface of one side of the cabin shell (1) is connected with a temperature sensor (3). The inner surface of one side of the cabin shell (1) is provided with an air inlet (4). The outer surface of the cabin shell (1) is connected with a protrusion (5). The protrusion (5) is provided with a through groove (6) on one side. The inner surface of one end of the through groove (6) is connected with a heating block (7), and the inner surface of the other end of the through groove (6) is connected with a fan (8). The inner surface of the other side of the cabin shell (1) is provided with an air outlet (9). The inner surfaces of the air inlet (4) and the air outlet (9) are both connected with a protective net (10). Shielding mechanisms are also provided at both ends of the cabin shell (1).

2. The polar monitoring drone cabin insulation structure according to claim 1 is characterized by: The shielding mechanism comprises: a first baffle (11), a connecting block (12), a first electric push rod (13), a vertical block (14), a through hole (15), a slide groove (16), a second baffle (17) and a second electric push rod (18); one side surface of the protruding block (5) is connected to the first baffle (11); both end surfaces of the first baffle (11) are connected to the connecting block (12); one side surface of the connecting block (12) is connected to the movable end of the first electric push rod (13); one side surface of the cabin shell (1) outside the air inlet (4) is connected to the vertical block (14); one side surface of the vertical block (14) is provided with a through hole (15) penetrating therethrough; and a slide groove (16) is provided on the top surface of the vertical block (14); the inner side surface of the slide groove (16) is connected to the second baffle (17); and the top surface of the second baffle (17) is connected to the movable end of the second electric push rod (18).

3. The polar monitoring drone cabin insulation structure according to claim 1 is characterized by: The surfaces of both sides of the thermal insulation cotton (2) are provided with slots that match the size and position of the air inlet (4) and the air outlet (9).

4. The polar monitoring drone cabin insulation structure according to claim 1 is characterized by: The temperature sensor (3), the heating block (7), the fan (8), the first electric push rod (13) and the second electric push rod (18) are electrically connected to an external power supply via a PLC control switch.

5. The polar monitoring drone cabin insulation structure according to claim 2 is characterized by: The size of the first baffle (11) is greater than the size of the through slot (6).

6. The polar monitoring drone cabin insulation structure according to claim 2 is characterized by: The second baffle plate (17) is slidably connected to the upright block (14) via the sliding groove (16); the size of the second baffle plate (17) is larger than the size of the through hole (15).

Images