Intelligent power supply and charging system for take-off and landing platform of vertical manned aircraft

Abstract

The intelligent vertical manned aircraft take-off and landing platform power supply and charging system comprises a charging pile body, a control panel is fixedly mounted at the top of the charging pile body, charger mounting bases are fixedly mounted on the left side and the right side of the front face of the charging pile body correspondingly, and charging guns are arranged on the front faces of the charger mounting bases; the input end of the charging gun is electrically connected with a charging wire, and the input end of the charging wire is electrically connected with the output end of the charging pile body. The cooling system has the advantage of good cooling effect, and solves the problems that the temperature of the battery is too high in the charging and discharging process, the aging of the battery is accelerated, the cycle life of the battery is shortened, and the service life of the battery is shortened due to the fact that the energy storage battery in the existing power supply and charging system for the take-off and landing platform of the intelligent vertical manned aircraft is inconvenient to efficiently cool in the using process. And moreover, the charging efficiency of the battery is reduced, so that the battery can reach a full-charge state after longer charging time, and the rapid turnover and operation efficiency of the aircraft are influenced.

Description

Technical Field

[0001] The present invention relates to the technical field of power supply, and in particular to a power supply and charging system for a take-off and landing platform of an intelligent vertical manned aircraft. Background Art

[0002] The power supply and charging system for the take-off and landing platform of an intelligent vertical manned aircraft is an infrastructure that integrates intelligent management and efficient energy supply technologies, and is designed specifically for electric vertical take-off and landing aircraft. Such systems are designed to provide safe and automated charging solutions, and may also have the functions of monitoring, maintaining and optimizing the charging process. Energy storage units, such as supercapacitors or large battery packs, will be integrated into the power supply and charging system to store excess renewable energy and power the aircraft during peak demand. At the same time, technologies that recover energy during take-off and landing, such as kinetic energy recovery systems, are explored to reduce energy consumption.

[0003] The existing power supply and charging system for the take-off and landing platform of an intelligent vertical manned aircraft is not convenient for efficient cooling of the energy storage batteries inside during use, resulting in excessively high temperatures in the battery during charging and discharging, accelerating battery aging and shortening its cycle life. In addition, the battery charging efficiency will decrease, requiring a longer charging time to reach a fully charged state, affecting the rapid turnover and operational efficiency of the aircraft. Summary of the invention

[0004] The purpose of the present invention is to provide a power supply and charging system for a take-off and landing platform of an intelligent vertical manned aircraft, which has the advantage of good cooling effect and solves the problem that the existing power supply and charging system for a take-off and landing platform of an intelligent vertical manned aircraft is not convenient for efficient cooling of the energy storage battery inside during use, resulting in excessively high temperature of the battery during charging and discharging, accelerating battery aging, shortening its cycle life, and reducing the charging efficiency of the battery, requiring a longer charging time to reach a fully charged state, affecting the rapid turnover and operational efficiency of the aircraft.

[0005] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a power supply and charging system for a take-off and landing platform of an intelligent vertical manned aircraft, comprising a charging pile body, a control panel is fixedly installed on the top of the charging pile body, charger mounting seats are fixedly installed on the left and right sides of the front of the charging pile body, a charging gun is provided on the front of the charger mounting seat, a charging cable is electrically connected to the input end of the charging gun, and the input end of the charging cable is electrically connected to the output end of the charging pile body;

[0006] A charge and discharge control module and a liquid cooling circulation module are fixedly installed on the top of the inner cavity of the charging pile body, and a plurality of energy storage mechanisms are fixedly installed in the inner cavity of the charging pile body.

[0007] As a preferred power supply and charging system for an intelligent vertical manned aircraft take-off and landing platform of the present invention, a mounting base is fixedly connected to the bottom of the charging pile body, and a reinforcing rib fixed to the surface of the charging pile body is provided on the top of the mounting base.

[0008] As a preferred power supply and charging system for an intelligent vertical manned aircraft take-off and landing platform of the present invention, a placement seat is fixedly connected to the bottom of the front side of the charging pile body, and the charging cable is wound around the placement seat.

[0009] As a preferred power supply and charging system for an intelligent vertical manned aircraft take-off and landing platform of the present invention, mesh plates are fixedly connected to the tops of the left and right sides of the charging pile body.

[0010] As a preferred power supply and charging system for an intelligent vertical manned aircraft take-off and landing platform of the present invention, the liquid cooling circulation module is connected with a connecting pipe, the bottom of the connecting pipe is connected with a coolant storage cylinder, and the coolant storage cylinder is fixedly installed at the bottom of the inner cavity of the charging pile body.

[0011] As a preferred power supply and charging system for the take-off and landing platform of an intelligent vertical manned aircraft of the present invention, the energy storage mechanism includes a battery box, and a liquid outlet channel and a liquid inlet channel are respectively opened on the left and right sides of the battery box. The top of the liquid outlet channel is connected to a liquid outlet head, and the top of the liquid inlet channel is connected to a liquid inlet head, and the liquid outlet head and the liquid inlet head are both connected to a liquid cooling circulation module.

[0012] As a preferred power supply and charging system for the take-off and landing platform of an intelligent vertical manned aircraft of the present invention, a plurality of groups of cylindrical batteries are fixedly installed in the inner cavity of the battery box, and a cooling element is fixedly connected to the opposite side of two groups of cylindrical batteries, and a liquid outlet flow hole and a liquid inlet flow hole are respectively provided on the left and right sides of the cooling element, and the liquid outlet flow hole is connected to the liquid outlet channel, and the liquid inlet flow hole is connected to the liquid inlet channel.

[0013] As a preferred power supply and charging system for the take-off and landing platform of an intelligent vertical manned aircraft of the present invention, a plurality of rubber membranes are fixedly installed at the middle end of the inner cavity of the cooling element, an elastic supporting metal piece is fixedly connected to the left side of the rubber membrane, and the end of the elastic supporting metal piece away from the rubber membrane is fixedly connected to the inner wall of the cooling element.

[0014] As a preferred power supply and charging system for the take-off and landing platform of an intelligent vertical manned aircraft of the present invention, a sealing component is installed on the right side of the inner cavity of the cooling part, and the sealing component includes a sealing head, and the sealing head is located on the left side of the liquid inlet flow hole. An installation cavity is opened inside the sealing head, and a sliding rod is fixedly connected to the inner wall of the installation cavity. A movable sleeve on the surface of the sliding rod is provided with a spring and a limit sleeve, and the upper and lower ends of the limit sleeve are fixedly connected to the inner wall of the cooling part.

[0015] As a preferred embodiment of the power supply and charging system for the take-off and landing platform of an intelligent vertical manned aircraft of the present invention, the spring is located on the opposite side of the limiting sleeve and the sealing head.

[0016] Compared with the prior art, the present invention has the following beneficial effects:

[0017] 1. The present invention can store electric energy by setting an energy storage mechanism. The charge and discharge control module stores the electric energy inside the cylindrical battery. When the aircraft needs to be charged, the charge and discharge control module calls the electric energy inside the cylindrical battery and outputs it through the charging line and the charging gun. The charging gun is installed in the charging port of the electric aircraft to realize the power supply of the electric aircraft. The user can continue to control the charge and discharge control module through the control panel and input control instructions.

[0018] 2. The present invention can cool the inside of the energy storage mechanism by setting up a liquid cooling circulation module. The liquid cooling circulation module outputs cooling liquid through the liquid inlet head and the liquid inlet channel. The cooling liquid enters the cooling element through the liquid inlet flow hole. When passing through the liquid inlet flow hole, the plugging head is squeezed. The plugging head drives the slide bar to slide inside the limit sleeve and squeezes the spring, so that the cooling liquid enters the cooling element and absorbs the heat of the cylindrical battery. The cooling liquid squeezes the rubber membrane and the elastic supporting metal part, causing them to deform to the left. The cooling liquid after absorbing heat enters the liquid outlet channel through the liquid outlet flow hole and flows back to the liquid cooling circulation module through the liquid outlet head, thereby realizing the recycling of the cooling liquid.

[0019] 3. The present invention can replace the coolant circulating inside the liquid cooling circulation module by setting a coolant storage cylinder. When the temperature of the coolant inside the coolant storage cylinder is too high, the low-temperature coolant inside the coolant storage cylinder is extracted through the connecting pipe, and the high-temperature coolant is input into the coolant storage cylinder through the connecting pipe to realize the replacement of the coolant, so as to improve the cooling efficiency. In addition, during the operation of the liquid cooling circulation module, the heat dissipation structure on its surface can dissipate the coolant, and the heat is dissipated into the air and flows to the outside through the mesh plate. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is the front view of the present invention;

[0021] Figure 2 This is a front cross-sectional view of the charging pile of the present invention;

[0022] Figure 3 It is a partial cross-sectional view of the energy storage mechanism of the present invention from the front view;

[0023] Figure 4 This is a front and cross-sectional view of the elastic sealing component of the present invention.

[0024] In the figure: 1. Charging pile body; 2. Energy storage mechanism; 201. Battery box; 202. Liquid inlet channel; 203. Liquid inlet head; 204. Liquid outlet head; 205. Liquid outlet channel; 206. Cylindrical battery; 207. Cooling part; 208. Liquid outlet flow hole; 209. Elastic supporting metal part; 210. Rubber membrane; 211. Sealing head; 212. Liquid inlet flow hole; 213. Installation cavity; 214. Limiting sleeve; 215. Spring; 216. Slide rod; 3. Control panel; 4. Charging gun; 5. Charging cable; 6. Mounting base; 7. Placement seat; 8. Charger mounting seat; 9. Mesh plate; 10. Charge and discharge control module; 11. Liquid cooling circulation module; 12. Connecting pipe; 13. Coolant storage cylinder. DETAILED DESCRIPTION

[0025] See also Figure 1-Figure 4 A power supply and charging system for a take-off and landing platform of an intelligent vertical manned aircraft includes a charging pile body 1, a control panel 3 is fixedly installed on the top of the charging pile body 1, charger mounting seats 8 are fixedly installed on the left and right sides of the front of the charging pile body 1, a charging gun 4 is arranged on the front of the charger mounting seat 8, the input end of the charging gun 4 is electrically connected to a charging line 5, and the input end of the charging line 5 is electrically connected to the output end of the charging pile body 1.

[0026] Furthermore, a mounting base 6 is fixedly connected to the bottom of the charging pile body 1 , and a reinforcing rib fixed to the surface of the charging pile body 1 is provided on the top of the mounting base 6 .

[0027] Furthermore, a placement seat 7 is fixedly connected to the bottom of the front side of the charging pile body 1 , and the charging cable 5 is wound around the placement seat 7 .

[0028] Furthermore, mesh plates 9 are fixedly connected to the tops of both left and right sides of the charging pile body 1 .

[0029] Furthermore, a charge and discharge control module 10 and a liquid cooling circulation module 11 are fixedly installed on the top of the inner cavity of the charging pile body 1, and a plurality of energy storage mechanisms 2 are fixedly installed in the inner cavity of the charging pile body 1.

[0030] Furthermore, the liquid cooling circulation module 11 is connected with a connecting pipe 12 , and the bottom of the connecting pipe 12 is connected with a coolant storage cylinder 13 , and the coolant storage cylinder 13 is fixedly installed at the bottom of the inner cavity of the charging pile body 1 .

[0031] By setting up a coolant storage cylinder 13, the coolant circulating inside the liquid cooling circulation module 11 can be replaced. When the temperature of the coolant inside the coolant storage cylinder 13 is too high, the low-temperature coolant inside the coolant storage cylinder 13 is extracted through the connecting tube 12, and the high-temperature coolant is input into the coolant storage cylinder 13 through the connecting tube 12 to realize the replacement of the coolant, thereby improving the cooling efficiency. In addition, during the operation of the liquid cooling circulation module 11, the heat dissipation structure on its surface can dissipate the heat of the coolant, and the heat is dissipated into the air and flows to the outside through the mesh plate 9.

[0032] Furthermore, the energy storage mechanism 2 includes a battery box 201, and a liquid outlet channel 205 and a liquid inlet channel 202 are respectively opened on the left and right sides inside the battery box 201. The top of the liquid outlet channel 205 is connected to a liquid outlet head 204, and the top of the liquid inlet channel 202 is connected to a liquid inlet head 203. Both the liquid outlet head 204 and the liquid inlet head 203 are connected to the liquid cooling circulation module 11.

[0033] Furthermore, a plurality of groups of cylindrical batteries 206 are fixedly installed in the inner cavity of the battery box 201, and a cooling member 207 is fixedly connected to the opposite side of two groups of cylindrical batteries 206. The cooling member 207 has a liquid outlet flow hole 208 and a liquid inlet flow hole 212 on the left and right sides respectively. The liquid outlet flow hole 208 is connected to the liquid outlet channel 205, and the liquid inlet flow hole 212 is connected to the liquid inlet channel 202.

[0034] Furthermore, a plurality of rubber membranes 210 are fixedly installed at the middle end of the inner cavity of the cooling member 207 , an elastic supporting metal member 209 is fixedly connected to the left side of the rubber membrane 210 , and one end of the elastic supporting metal member 209 away from the rubber membrane 210 is fixedly connected to the inner wall of the cooling member 207 .

[0035] Furthermore, the cooling element 207 is provided with arc-shaped surfaces on both the upper and lower sides for use with the cylindrical battery 206 .

[0036] Furthermore, there are a plurality of rubber membranes 210 in a petal shape, and a plurality of petal-shaped rubber membranes 210 form a circular barrier.

[0037] Furthermore, a sealing assembly is installed on the right side of the inner cavity of the cooling member 207, and the sealing assembly includes a sealing head 211. The sealing head 211 is located on the left side of the liquid inlet flow hole 212. An installation cavity 213 is opened inside the sealing head 211. A slide rod 216 is fixedly connected to the inner wall of the installation cavity 213. A spring 215 and a limit sleeve 214 are movablely sleeved on the surface of the slide rod 216. The upper and lower ends of the limit sleeve 214 are fixedly connected to the inner wall of the cooling member 207.

[0038] Furthermore, the spring 215 is located on the opposite side of the limiting sleeve 214 and the blocking head 211 .

[0039] By setting up the energy storage mechanism 2, it is convenient to store electric energy. The charge and discharge control module 10 stores the electric energy inside the cylindrical battery 206. When the aircraft needs to be charged, the charge and discharge control module 10 calls the electric energy inside the cylindrical battery 206 and outputs it through the charging line 5 and the charging gun 4. The charging gun 4 is installed in the charging port of the electric aircraft to realize power supply to the electric aircraft. The user can continue to control the charge and discharge control module 10 through the control panel 3 and input control instructions.

[0040] By setting up a liquid cooling circulation module 11, the interior of the energy storage mechanism 2 can be cooled. The liquid cooling circulation module 11 outputs cooling liquid through the liquid inlet head 203 and the liquid inlet channel 202. The cooling liquid enters the cooling member 207 through the liquid inlet flow hole 212. When passing through the liquid inlet flow hole 212, the plugging head 211 is squeezed. The plugging head 211 drives the sliding rod 216 to slide inside the limiting sleeve 214 and squeezes the spring 215, so that the cooling liquid enters the cooling member 207 and absorbs the heat of the cylindrical battery 206. The cooling liquid squeezes the rubber membrane 210 and the elastic supporting metal part 209, causing them to deform to the left. The cooling liquid after absorbing heat enters the liquid outlet channel 205 through the liquid outlet flow hole 208, and flows back to the liquid cooling circulation module 11 through the liquid outlet head 204, thereby realizing the recycling of the cooling liquid.

[0041] The operator sets the charging parameters or monitors the charging status through the control panel 3. When the aircraft needs to be charged, the charging gun 4 is connected to the charging interface of the aircraft, and the charging line 5 transmits the charging energy from the charging pile body 1 to the aircraft battery.

[0042] The charge and discharge control module 10 is responsible for monitoring the entire charging process and intelligently adjusting the charging current and voltage according to the battery status to ensure charging efficiency and battery safety.

[0043] The energy storage mechanism 2 installed inside the charging pile body 1 can be used for charging the aircraft, and the cylindrical batteries 206 inside the energy storage mechanism 2 are arranged neatly to provide a stable source of electricity for charging.

[0044] The liquid cooling circulation module 11 is connected to the coolant storage cylinder 13 through the connecting pipe 12. When working, the coolant flows from the coolant storage cylinder 13 into the liquid inlet channel 202 under the action of the pump, enters the cooling element 207, flows through the cylindrical batteries 206, absorbs heat and turns into hot liquid, and then returns to the liquid cooling circulation module 11 through the liquid outlet 204. In this circulation process, the coolant continuously takes away the heat generated by the battery and keeps the battery at a suitable working temperature.

[0045] The cooling member 207 ensures that the coolant can effectively flow between each group of cylindrical batteries 206. At the same time, the rubber membrane 210 and the elastic supporting metal member 209 help maintain the stability of the liquid flow and the pressure balance between the batteries. The sealing component is used to adjust or control the flow path of the coolant to ensure the cooling effect.

[0046] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A power supply and charging system for a take-off and landing platform of an intelligent vertical manned aircraft, comprising a charging pile body (1), characterized in that: A control panel (3) is fixedly mounted on the top of the charging pile body (1); a charger mounting seat (8) is fixedly mounted on both the left and right sides of the front of the charging pile body (1); a charging gun (4) is arranged on the front of the charger mounting seat (8); an input end of the charging gun (4) is electrically connected to a charging line (5); and an input end of the charging line (5) is electrically connected to an output end of the charging pile body (1); A charge and discharge control module (10) and a liquid cooling circulation module (11) are fixedly mounted on the top of the inner cavity of the charging pile body (1), and a plurality of energy storage mechanisms (2) are fixedly mounted on the inner cavity of the charging pile body (1).

2. The power supply and charging system for the take-off and landing platform of an intelligent vertical manned aircraft according to claim 1, characterized in that: The bottom of the charging pile body (1) is fixedly connected to a mounting base (6), and the top of the mounting base (6) is provided with reinforcing ribs fixed to the surface of the charging pile body (1).

3. The power supply and charging system for the take-off and landing platform of an intelligent vertical manned aircraft according to claim 1 is characterized in that: A placement seat (7) is fixedly connected to the bottom of the front side of the charging pile body (1), and the charging line (5) is wound around the placement seat (7).

4. The power supply and charging system for the take-off and landing platform of an intelligent vertical manned aircraft according to claim 1, characterized in that: The tops of the left and right sides of the charging pile body (1) are both fixedly connected with mesh plates (9).

5. The power supply and charging system for the take-off and landing platform of an intelligent vertical manned aircraft according to claim 1, characterized in that: The liquid cooling circulation module (11) is connected to a connecting pipe (12), the bottom of the connecting pipe (12) is connected to a cooling liquid storage cylinder (13), and the cooling liquid storage cylinder (13) is fixedly installed at the bottom of the inner cavity of the charging pile body (1).

6. The power supply and charging system for the take-off and landing platform of an intelligent vertical manned aircraft according to claim 1, characterized in that: The energy storage mechanism (2) comprises a battery box (201), wherein a liquid outlet channel (205) and a liquid inlet channel (202) are respectively provided on the left and right sides of the battery box (201), the top of the liquid outlet channel (205) is connected to a liquid outlet head (204), the top of the liquid inlet channel (202) is connected to a liquid inlet head (203), and both the liquid outlet head (204) and the liquid inlet head (203) are connected to a liquid cooling circulation module (11).

7. The power supply and charging system for the take-off and landing platform of an intelligent vertical manned aircraft according to claim 6, characterized in that: A plurality of groups of cylindrical batteries (206) are fixedly installed in the inner cavity of the battery box (201), and a cooling member (207) is fixedly connected to the opposite side of two groups of cylindrical batteries (206). The cooling member (207) is provided with a liquid outlet flow hole (208) and a liquid inlet flow hole (212) on the left and right sides respectively, and the liquid outlet flow hole (208) is connected to the liquid outlet channel (205), and the liquid inlet flow hole (212) is connected to the liquid inlet channel (202).

8. The power supply and charging system for the take-off and landing platform of an intelligent vertical manned aircraft according to claim 7, characterized in that: A plurality of rubber membranes (210) are fixedly installed at the middle end of the inner cavity of the cooling member (207), an elastic supporting metal member (209) is fixedly connected to the left side of the rubber membrane (210), and one end of the elastic supporting metal member (209) away from the rubber membrane (210) is fixedly connected to the inner wall of the cooling member (207).

9. The power supply and charging system for the take-off and landing platform of an intelligent vertical manned aircraft according to claim 7, characterized in that: A plugging assembly is installed on the right side of the inner cavity of the cooling member (207), and the plugging assembly includes a plugging head (211). The plugging head (211) is located on the left side of the liquid inlet flow hole (212). An installation cavity (213) is provided inside the plugging head (211). A sliding rod (216) is fixedly connected to the inner wall of the installation cavity (213). A spring (215) and a limiting sleeve (214) are movablely sleeved on the surface of the sliding rod (216). The limiting sleeve (214) is fixedly connected to the inner wall of the cooling member (207) at its upper and lower ends.

10. The power supply and charging system for the take-off and landing platform of an intelligent vertical manned aircraft according to claim 9, characterized in that: The spring (215) is located on the side opposite to the limiting sleeve (214) and the blocking head (211).

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