Protective shell based on hydrogen fuel cell of unmanned aerial vehicle

Abstract

The utility model discloses a protective shell based on an unmanned aerial vehicle hydrogen fuel cell, which relates to the technical field of battery protection and comprises a blocking cover, one end of the blocking cover is sleeved and connected with a protective shell, and a ceramic shell is embedded in the inner side of the protective shell. Through the arranged protective shell assembly structure, a cushion frame assembly on the surface of the protective shell assembly structure and a cushion plate assembly on the inner side of a blocking cover, the protective effect of elastic damping on the exterior of the battery can be achieved, so that when the unmanned aerial vehicle is impacted, the hydrogen fuel battery in the unmanned aerial vehicle can still be kept stable, and through the arranged ceramic shell assembly structure, a user can adjust the temperature of the unmanned aerial vehicle according to the temperature of the flight environment. And the surface of the hydrogen fuel cell can be heated or cooled, so that the hydrogen fuel cell is kept at a proper operating temperature, and the service life of the hydrogen fuel cell is prolonged.

Description

Technical Field

[0001] The utility model relates to the technical field of battery protection, and in particular to a protective shell based on a hydrogen fuel cell of an unmanned aerial vehicle. Background Art

[0002] The utility model with publication number CN209515798U discloses a hydrogen fuel cell housing. By setting a fixing plate, when the hydrogen fuel cell housing is used, after the hydrogen fuel cell is fixed on the base, the limit rod on the fixing plate is rotated to the top end surface of the hydrogen fuel cell, and the first spring on the bottom end surface of the limit rod is pulled at the same time, so that the first spring moves finely toward the limit rod. After the limit rod is at the top end surface of the hydrogen fuel cell after movement, the operator loosens the first spring so that the first spring squeezes and limits the hydrogen fuel cell, which is convenient for fixing and installing the hydrogen fuel cell and preventing external hard collision from causing damage to the hydrogen fuel cell. However, when the battery of this battery housing is installed in a drone for use, the battery may flip over with the aircraft during flight, and the bottom spring alone cannot achieve a good protection effect, and this battery housing cannot adjust the external temperature of the battery according to the external environment, resulting in the battery being unable to be at the optimal operating temperature for a long time, thereby affecting the service life. Utility Model Content

[0003] The purpose of the utility model is to provide a protective shell based on a hydrogen fuel cell for an unmanned aerial vehicle to solve the above-mentioned technical problems.

[0004] The purpose of the utility model can be achieved through the following technical solutions:

[0005] A protective shell based on a hydrogen fuel cell for an unmanned aerial vehicle comprises a baffle, one end of the baffle is sleeved and connected with a protective shell, and a ceramic shell is embedded and placed inside the protective shell;

[0006] A hollow groove is opened at one end of the blocking cover, and springs are fixedly connected to the surface of the hollow groove at equal intervals. A pad is fixedly connected to the other end of the spring, and the material of the pad is set to be sponge. A pad frame is welded and fixed to the cross-section of the protective shell, and airbags are embedded and installed on the facing surfaces of two groups of the pad frames.

[0007] Preferably, one end of the blocking cover is glued and fixed with a surrounding block on the outside of the empty slot, an output end is fixedly installed on a long side surface of the blocking cover near both sides, and hooks are fixedly installed in the middle of the two long side surfaces of the blocking cover.

[0008] Preferably, a radiator is embedded and installed in the middle of the two short side surfaces of the protective shell, docking grooves are provided at both ends of the protective shell, the surrounding block is embedded and connected to the docking grooves, and buckle seats are symmetrically fixedly installed on the two long side surfaces of the protective shell near the two ends.

[0009] Preferably, two short side surfaces of the ceramic shell are provided with grooves in the middle, two short side surfaces inside the ceramic shell are welded and fixed with copper sheets at the grooves, semiconductor cooling plates are embedded and fixed on the surfaces of the grooves, and two long side surfaces of the ceramic shell are provided with installation grooves in the middle, and heaters are fixedly installed on the surfaces of the installation grooves.

[0010] Preferably, a screw hole is provided on the surface of the heater at the edge of the dead angle, an electric heating rod is fixedly installed inside the heater, and water is provided inside the heater.

[0011] Beneficial effects of the utility model:

[0012] (1) Through the protective shell assembly structure, the pad assembly on its surface and the pad assembly inside the cover, the drone will inevitably impact the outside of the battery during flight. The pads at both ends will play a buffering and shock-absorbing role under the action of the springs. At the same time, the sponge material will further weaken the transmission of the impact. The pad covering the outside of the battery and the airbag embedded in its surface will also prevent the hard impact from being directly transmitted to the battery surface;

[0013] (2) Through the ceramic shell component structure, when the flight environment temperature is high, the user can start the semiconductor cooling plate, and the copper sheet attached to its surface will transfer the low temperature to the battery surface to cool it down. At the same time, the radiator is started to dissipate heat from the surface of the semiconductor cooling plate. When the flight environment temperature is low, the user can start the electric heating rod to heat the water, so that the temperature around the battery gradually rises. When the temperature is close to 20 degrees, the temperature rise can be stopped. Thereafter, the waste heat of the water and the self-heating of the battery can be used to maintain a suitable operating temperature. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] The utility model is further described below in conjunction with the accompanying drawings.

[0015] Figure 1 It is a schematic diagram of the overall structure of the utility model;

[0016] Figure 2 It is a schematic diagram of the overall structure disassembly of the utility model;

[0017] Figure 3 It is a schematic diagram of the cover structure of the utility model;

[0018] Figure 4 It is a schematic diagram of the structure of the protective shell and ceramic shell assembly of the utility model.

[0019] In the figure: 1. blocking cover; 2. surrounding block; 3. pad; 4. output terminal; 5. hanging buckle; 6. protective shell; 7. pad frame; 8. radiator; 9. docking groove; 10. buckle seat; 11. ceramic shell; 12. slot; 13. copper sheet; 14. semiconductor cooling sheet; 15. installation groove; 16. heater. 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 of 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] Embodiment 1

[0022] A protective shell based on a hydrogen fuel cell for an unmanned aerial vehicle comprises a stop cover 1, one end of the stop cover 1 is sleeved and connected with a protective shell 6, and a ceramic shell 11 is embedded and placed inside the protective shell 6; one end of the stop cover 1 is provided with an empty groove, and a spring is fixedly connected to the surface of the empty groove at equal intervals, and a pad 3 is fixedly connected to the other end of the spring, and the material of the pad 3 is set as sponge, and a pad frame 7 is welded and fixed to the cross-section of the protective shell 6, and air bags are embedded and installed on the facing surfaces of two groups of the pad frames 7. When the battery is placed and used, the unmanned aerial vehicle will inevitably produce an impact on the outside of the battery during flight. The pads 3 at both ends will play a buffering and shock-absorbing effect under the action of the springs, and the sponge material will further weaken the transmission of the impact, and the pad frame 7 covering the outside of the battery and the air bag embedded in its surface will also prevent the hard impact from being directly transmitted to the battery surface;

[0023] One end of the blocking cover 1 is located outside the empty slot and is glued and fixed with a surrounding block 2. An output terminal 4 is fixedly installed near both sides of a long side surface of the blocking cover 1. A hanging buckle 5 is fixedly installed in the middle of the two long side surfaces of the blocking cover 1. After the power line of the battery is connected to the output terminal 4, the drone can be powered inside the shell;

[0024] A radiator 8 is embedded and installed in the middle of the two short side surfaces of the protective shell 6, and docking grooves 9 are provided at both ends of the protective shell 6. The surrounding block 2 is embedded and connected with the docking grooves 9. Buckle seats 10 are symmetrically fixedly installed on the two long side surfaces of the protective shell 6 near both ends. The battery can be easily disassembled and assembled by connecting the hanging buckle 5 and the buckle seat 10, and during the shell connection process, the protruding surrounding block 2 will be embedded in the docking groove 9 to prevent moisture from entering the interior and corroding the battery.

[0025] Embodiment 2

[0026] On the basis of the first embodiment, the two short side surfaces of the ceramic shell 11 are provided with a groove 12 in the middle, the two short side surfaces inside the ceramic shell 11 are located at the groove 12 and a copper sheet 13 is welded and fixed, a semiconductor cooling sheet 14 is embedded and fixed on the surface of the groove 12, and the two long side surfaces of the ceramic shell 11 are provided with a mounting groove 15 in the middle, and a heater 16 is fixedly installed on the surface of the mounting groove 15. When the flight environment temperature is high, the user can start the semiconductor cooling sheet 14, and the copper sheet 13 attached to its surface will transfer the low temperature to the battery surface to cool it down, and at the same time start the radiator 8 to dissipate heat from the surface of the semiconductor cooling sheet 14.

[0027] Embodiment 3

[0028] On the basis of the second embodiment, a screw hole is provided on the surface of the heater 16 at the edge of the dead angle, and an electric heating rod is fixedly installed inside the heater 16. Water is provided inside the heater 16. When the flight environment temperature is low, the user can start the electric heating rod to heat the water, so that the temperature around the battery gradually rises. When the temperature approaches about 20 degrees, the heating can be stopped, and then the waste heat of the water and the self-heating of the battery can be used to maintain a suitable operating temperature.

[0029] The working principle of the utility model: the battery can be easily disassembled and assembled by connecting the hanging buckle 5 and the buckle seat 10, and in the process of connecting the shell, the protruding surrounding block 2 will be embedded in the docking groove 9 to prevent moisture from entering the interior and corroding the battery. When the battery is placed and used, the drone will inevitably impact the outside of the battery during flight. The pads 3 at both ends will play a buffering and shock-absorbing effect under the action of the spring. At the same time, the sponge material will further weaken the transmission of the impact, and the pad frame 7 wrapped around the outside of the battery and the airbag embedded in its surface will also prevent the hard impact from being directly transmitted to the battery surface. When the flight environment temperature is high, the user can start the semiconductor refrigeration sheet 14, and the copper sheet 13 attached to its surface will transfer the low temperature to the battery surface to cool it down. At the same time, the radiator 8 is started to dissipate heat on the surface of the semiconductor refrigeration sheet 14. When the flight environment temperature is low, the user can start the electric heating rod to heat the water, so that the temperature around the battery gradually rises. When the temperature is close to about 20 degrees, the temperature rise can be stopped. After that, the waste heat of the water and the self-heating of the battery can be used to maintain a suitable operating temperature.

[0030] The above is a detailed description of an embodiment of the utility model, but the content is only a preferred embodiment of the utility model and cannot be considered to limit the scope of implementation of the utility model. All equivalent changes and improvements made within the scope of application of the utility model should still fall within the scope of the patent coverage of the utility model.

Claims

1. A protective housing based on a hydrogen fuel cell for an unmanned aerial vehicle, comprising a cover (1), characterized in that: One end of the blocking cover (1) is sleeved and connected with a protective shell (6), and a ceramic shell (11) is embedded and placed inside the protective shell (6); A hollow groove is formed at one end of the blocking cover (1), a spring is fixedly connected to the surface of the hollow groove at equal intervals, a pad (3) is fixedly connected to the other end of the spring, the material of the pad (3) is sponge, a pad frame (7) is welded and fixed to the cross-section of the protective shell (6), and air bags are embedded and installed on the facing surfaces of two groups of the pad frames (7).

2. The protective shell based on the hydrogen fuel cell of the drone according to claim 1 is characterized in that: One end of the blocking cover (1) is glued and fixed with a surrounding block (2) on the outside of the empty slot, an output end (4) is fixedly mounted on a long side surface of the blocking cover (1) near both sides, and a hanging buckle (5) is fixedly mounted on the middle of the two long side surfaces of the blocking cover (1).

3. The protective shell based on the hydrogen fuel cell of the drone according to claim 2 is characterized in that: A radiator (8) is embedded and installed in the middle of the two short side surfaces of the protective shell (6), and docking grooves (9) are provided at both ends of the protective shell (6), and the surrounding block (2) is embedded and connected with the docking grooves (9).

4. The protective shell based on the hydrogen fuel cell of the drone according to claim 3 is characterized in that: Buckle seats (10) are symmetrically fixedly mounted on the two long side surfaces of the protective shell (6) near both ends.

5. The protective shell based on the hydrogen fuel cell of the drone according to claim 1 is characterized in that: The ceramic shell (11) has two short side surfaces with grooves (12) in the middle, the two short side surfaces inside the ceramic shell (11) are welded and fixed at the grooves (12), a semiconductor cooling plate (14) is embedded and fixed on the surface of the groove (12), and the ceramic shell (11) has two long side surfaces with mounting grooves (15) in the middle, and a heater (16) is fixedly installed on the surface of the mounting groove (15).

6. The protective shell based on the hydrogen fuel cell of the drone according to claim 5 is characterized in that: The surface of the heater (16) is provided with a screw hole at the edge of a dead angle, an electric heating rod is fixedly installed inside the heater (16), and water is provided inside the heater (16).

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