Instantaneous heat energy storage device for aircraft

Abstract

The utility model discloses an instantaneous heat energy storage device for an aircraft. Comprising a liquid storage tank (1), the liquid storage tank (1) comprises a box-type shell (1.1), an interlayer cavity (1.2) is formed in the periphery of an inner cavity (1.2) of the box-type shell (1.1), and the inner cavity (1.2) is communicated with an inlet and an outlet of the liquid storage tank (1); the interlayer cavity (1.2) is filled with a crystal hydrated salt phase change material (1.3), and the inner cavity (1.2) of the liquid storage tank (1) is filled with cooling liquid. According to the utility model, the problems of large battery volume, low heat efficiency and long service life caused by phase-change materials are solved while the high-power heat of the aircraft battery is increased.

Description

TECHNICAL FIELD

[0001] The utility model belongs to the technical field of instantaneous heat energy storage control of aviation aircraft, specifically relates to an instantaneous heat energy storage device of aircraft. BACKGROUND

[0002] An electric vertical takeoff and landing (eVTOL) aircraft is an aircraft that relies on electric power for propulsion. They typically use batteries as their energy source. Battery thermal management systems are crucial for ensuring the safety and performance of the aircraft, as batteries generate heat during charging and discharging. If the battery temperature is too high, it can reduce battery efficiency, shorten its lifespan, and even pose safety risks.

[0003] During the battery thermal management process, when the battery is rapidly charged, heat is generated as electrical energy is converted into chemical energy and stored inside the battery, causing the battery temperature to rise rapidly. During takeoff or climb, eVTOLs require a large amount of electrical energy, and the battery will be discharged under heavy load at this time. Similarly, this high-power output will cause the battery to generate more heat. As the internal resistance of the battery increases, part of the electrical energy will be converted into heat energy, especially during high-current charging and discharging, due to the internal resistance effect of the battery, significant heat will be generated.

[0004] To address these challenges, battery thermal management systems typically use cooling fluids, air cooling, or phase change materials to regulate battery temperature. In the event of a sudden surge in high-power heat, the system may need to take emergency cooling measures, such as increasing the flow of cooling fluid, starting additional cooling fans, etc., to ensure that the battery temperature is within a safe range.

[0005] Currently, the main method of using phase change materials in battery thermal management is to place the phase change material in contact with or encapsulated together with the battery cells or rely solely on the cooling fluid to remove heat. In the cooling method of phase change materials, when the battery temperature rises, the PCM absorbs heat and undergoes a phase change (e.g., from solid to liquid), helping to cool the battery. Conversely, when the battery temperature drops, the PCM can release the previously stored heat energy, providing heat to the battery and helping to maintain its optimal operating temperature. This phase change material needs to be encapsulated inside the battery pack, which mainly has the following problems:

[0006] (1) The phase change material needs to be encapsulated together with the battery pack, resulting in a significant increase in the overall volume of the battery pack, and there is not enough space on the aircraft to install the battery pack.

[0007] (2) Low thermal efficiency: the battery is a regular cubic solid, and the phase change material is a small granular solid. The only basic heat transfer method between the two solids is thermal conduction, and the two cannot be completely in contact, resulting in a large thermal resistance.

[0008] (3) service life problem, the phase change material can greatly reduce with time life, its phase change temperature etc. change greatly, and cannot be taken out after being packed with the whole battery, cause the whole battery pack life to reduce;

[0009] The traditional cooling liquid cooling mode can only deal with the temperature rise of the battery caused by the high-power discharge of the instantaneous battery by increasing the cooling liquid. SUMMARY

[0010] The utility model discloses a kind of instantaneous heat energy storage devices of aircraft, the utility model is in solving the battery high-power heat increase of aircraft, avoid the battery volume of phase change material appearance, thermal efficiency is low, service life problem.

[0011] The technical scheme of the utility model is: an instantaneous heat energy storage device of aircraft, including liquid storage tank;Liquid storage tank includes box type shell, the inner cavity of box type shell is provided with interlayer cavity, and the inner cavity is communicated with the entrance and exit of liquid storage tank;Interlayer cavity is filled with crystalline hydrated salt phase change material, and the inner cavity of liquid storage tank is provided with cooling liquid.

[0012] In the foregoing instantaneous heat energy storage device of aircraft, the inner wall of the interlayer cavity is distributed with convex cavity protruding to the inner cavity direction.

[0013] In the foregoing instantaneous heat energy storage device of aircraft, the outer wall of the interlayer cavity is provided with phase change material injection port.

[0014] In the foregoing instantaneous heat energy storage device of aircraft, the outer wall of the interlayer cavity is provided with vacuum extraction port.

[0015] In the foregoing instantaneous heat energy storage device of aircraft, support rib is arranged between the inner wall and the outer wall of the interlayer cavity.

[0016] In the foregoing instantaneous heat energy storage device of aircraft, the cooling liquid is No. 65 cooling liquid.

[0017] The utility model discloses a kind of instantaneous heat energy storage devices of aircraft, the utility model is in solving the battery high-power heat increase of aircraft, avoid the battery volume of phase change material appearance, thermal efficiency is low, service life problem.

[0018] The core idea of the utility model is to integrate an energy storage device with a partition cavity in the battery energy storage system, and the partition cavity is filled with phase change material. By phase change of the phase change material, such as from solid to liquid, this process can absorb a large amount of heat energy, so when the battery pack generates heat during charging or discharging, the heat will be absorbed and stored by the phase change material, effectively managing the heat generated by the battery and improving the overall efficiency and performance of the battery.

[0019] The phase change material filling and maintenance opening setting is a convenient innovation, which allows quick and simple replacement when the service life of the phase change material reaches a certain degree. In this way, when the performance of the phase change material decreases to a certain degree, the user does not need to scrap the entire battery or energy storage device, but can replace the failed phase change material through simple operation. The structure not only prolongs the service life of the battery and the energy storage device, but also avoids unnecessary waste, thereby reducing the long-term use cost of the user. BRIEF DESCRIPTION OF DRAWINGS

[0020] Figure 1 is a structural schematic diagram of the utility model;

[0021] Figure 2 is a liquid storage tank structure schematic diagram;

[0022] Figure 3 is a liquid storage tank top view;

[0023] Figure 4 is a schematic diagram of an aircraft battery thermal management system using the utility model. DETAILED DESCRIPTION

[0024] In order to make the purpose, technical scheme and advantages of the embodiments of the utility model clearer, the technical scheme in the embodiments of the utility model will be described clearly and completely below in combination with the drawings in the embodiments of the utility model. Obviously, the described embodiments are part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor belong to the scope of protection of the utility model.

[0025] The features and illustrative embodiments of each aspect of the utility model will be described in detail below. In the following detailed description, many specific details are proposed in order to provide a comprehensive understanding of the utility model. However, it is obvious for those skilled in the art that the utility model can be implemented without some of these specific details. The following description of the embodiments is only to provide a better understanding of the utility model by showing examples of the utility model. The utility model is by no means limited to any specific settings and methods proposed below, but covers any improvements, replacements and modifications of structure, method and device without departing from the spirit of the utility model. In the drawings and the following description, the known structures and technologies are not shown to avoid unnecessary obscuring of the utility model.

[0026] It should be noted that the features in the embodiments of the utility model and the embodiments can be combined with each other without conflict, and each embodiment can be mutually referenced and quoted. The utility model will be described in detail below with reference to the drawings and in combination with the embodiments.

[0027] Embodiment 1. An aircraft instantaneous heat energy storage device, see Figures 1-3 , comprising a liquid storage tank 1, the liquid storage tank 1 comprises a box-shaped shell 1.1, a sandwich cavity is arranged on the periphery of the inner cavity 1.2 of the box-shaped shell 1.1, and the inner cavity 1.2 is communicated with the inlet and outlet of the liquid storage tank 1; the sandwich cavity is filled with crystalline hydrated salt phase change material 1.3, and the inside of the liquid storage tank is 65# cooling liquid. In the utility model, the function of the liquid storage tank 1 is to absorb and store the heat generated by the battery during the large-rate discharge process of the battery. The phase change material in the liquid storage tank can absorb and release heat within a certain temperature range, thereby realizing the temporary storage of heat. After the battery discharge process is completed, the cooling liquid will take away the heat in the liquid storage tank, so that the temperature of the battery gradually decreases. By designing a liquid cooling storage tank in the liquid cooling circuit, the heat generated by the battery during the large-rate discharge process is effectively absorbed and stored by combining the phase change material and the cooling liquid, thereby reducing the risk of instantaneous temperature rise of the battery. The design of the liquid cooling storage tank enables the battery to maintain stable temperature under complex working conditions such as long-time hovering, repeated take-off and landing, etc., thereby improving the working performance and safety of the battery.

[0028] The inner wall of the aforementioned sandwich cavity is distributed with convex cavities 1.4 protruding towards the inner cavity 1.2. The heat exchange area is increased, the cooling liquid is disturbed when flowing in the box body, and the heat transfer between the cooling liquid and the energy storage material is improved.

[0029] The outer wall of the aforementioned sandwich cavity is provided with a phase change material injection port 1.5. The phase change material in the phase change material injection port 1.5 can be replaced when the phase change material reaches the service life or decays, thereby avoiding the overall scrap of the liquid storage tank.

[0030] The outer wall of the aforementioned sandwich cavity is provided with a vacuum extraction port 1.6. When filling the phase change material, the inner cavity of the box body is kept in a vacuum and negative pressure environment, thereby facilitating the filling of the phase change material.

[0031] Supporting ribs 1.7 are arranged between the inner and outer walls of the aforementioned sandwich cavity. The supporting ribs 1.7 support the strength of the box body and prevent the box body from deforming under positive pressure or negative pressure.

[0032] An aircraft battery thermal management system using the aforementioned aircraft instantaneous heat energy storage device, see Figure 4 , comprising an evaporator 5, a liquid cooling circuit connected between the hot side medium inlet and outlet of the evaporator 5, and an evaporation circulation circuit connected between the cold side medium inlet and outlet of the evaporator 5; the liquid cooling circuit comprises a liquid storage tank 1, a booster pump 2, a cold plate A 3 and a cold plate B 4 connected in sequence between the hot side medium inlet and outlet of the evaporator 5; the evaporation circulation circuit comprises a compressor 6, a condenser 7 and an expansion valve 8 connected in sequence between the cold side medium inlet and outlet of the evaporator 5; the cold plate A 3 is installed on the electronic control system of the aircraft, and the cold plate B 4 is installed on the battery system and motor system of the aircraft.

[0033] By the cooperative matching of the liquid cooling circulation path and the evaporation circulation path, the problems of comprehensive cooling and heating of the battery, the motor and the electronic control system are solved, and the problems of system redundancy and aircraft weight overweight caused by the traditional three sets of systems are solved. In the utility model, the liquid storage tank 1 is used for storing the cooling liquid, and provides continuous cooling liquid supply for the liquid cooling circulation path, and meanwhile, the phase change energy storage material is arranged in the liquid storage tank to realize instantaneous large heat collection. The function of the booster pump 2 is to make the cooling liquid flow in the liquid cooling circulation path, so as to improve the cooling efficiency. The cold plate A is installed on the surface of the electronic control system, and the cold plate B is installed on the surface of the battery and the motor system, which is used for absorbing the heat generated during the operation of the equipment, and the heat is transmitted to the evaporator 5 through the cooling liquid. The evaporator 5 is responsible for transmitting the heat of the cooling liquid to the external environment, so that the primary cooling of the equipment is realized. The condenser 7 is used for condensing the steam in the evaporator into liquid, so as to enter the liquid cooling circulation path again. The function of the expansion valve 8 is to adjust the pressure and flow of the cooling liquid between the condenser and the evaporator 5, so as to ensure the stable operation of the system. Through the matching design of the liquid cooling circulation path and the evaporation circulation path, the efficient cooling and heating of the battery, the motor, the electronic control system and other equipment are realized, and the working stability of the electronic equipment is improved. By adopting a unified set of cooling and heating systems, the problems of system redundancy and aircraft weight overweight caused by the traditional three sets of systems respectively for the battery, the motor and the electronic control system are solved (by canceling the oil circulation path, the heating circuit, the motor controller liquid cooling circuit, crosslinking the generator controller cooling circuit and the battery liquid cooling path, and finally dissipating heat through the energy storage liquid tank and the evaporation circulation, canceling the air oil cooler, the motor fan, the controller liquid cooling pump, the valve and other components, and reducing the weight by more than 30%), the space occupied by the system is reduced. The utility model has the advantages of simple structure, easy realization, and wide application prospect in temperature control of various types of battery, motor, electronic control system and other electronic equipment.

[0034] The outlet and the inlet of the aforementioned liquid storage tank 1 are respectively provided with isolation valves A9 and B10; and a cooling liquid heater 11 is arranged between the outlet of the isolation valve A9 and the inlet of the isolation valve B10. Two isolation valves are arranged beside the liquid storage tank body, and a cooling liquid heater is arranged between the two isolation valves. In the extremely cold condition, when the temperature of the battery is low, the isolation valve 200 automatically bypasses, and the cooling liquid in the loop no longer passes through the liquid storage tank body 100, and flows through the heater to heat the battery.

[0035] The outlet of the aforementioned booster pump 2 is provided with a temperature and pressure sensor A12, the inlet and the outlet of the cold plate B4 are provided with temperature and pressure sensors B13 and C14, the outlet of the evaporator 5 is provided with a temperature and pressure sensor D15, and the outlet of the condenser is provided with a temperature and pressure sensor E16. The temperature and pressure values at different positions are mainly detected, and are transmitted to the thermal management control box.

[0036] The aforementioned cooling liquid heater 11 is detachably connected between the outlet of the isolation valve A 9 and the inlet of the isolation valve B 10 through a self-sealing joint. When the aircraft starts in extremely cold conditions, the temperature of the battery, motor and electronic control system is too low, at this time the cooling liquid heater 11 can be connected to the liquid cooling circuit through the quick-connection self-sealing joint, and at the same time the isolation valves A and B are automatically isolated from the liquid storage tank 1, the cooling liquid in the liquid cooling circuit is heated, thereby realizing the high-power rapid heating of the cooling liquid. When the temperature of the battery, motor and electronic control system reaches the preset value, the cooling liquid heater 11 will automatically shut down, at this time the cooling liquid heater 11 can be detached, the isolation valves A and B are reopened, and the liquid cooling circuit resumes normal operation. By adding the detachable cooling liquid heater 11 in the liquid cooling circuit, the rapid heating function of the battery is realized, and the working performance of the battery in a low temperature environment is effectively improved. At the same time, the cooling liquid heater 11 and its pipeline of about 8kg are detachable, which effectively reduces the flight weight of the aircraft. The design of the detachable cooling liquid heater 11 makes the heating process unnecessary to disassemble the battery or interrupt the liquid cooling circuit, which is simple and time-saving. Moreover, the cooling liquid heater 11 can automatically control the heating process, improve the accuracy of temperature control, and reduce energy waste.

[0037] The thermal management method of the aforementioned aircraft battery thermal management system:

[0038] When the aircraft hovers for a long time or repeatedly takes off and lands, causing the battery to discharge at a large rate, the cooling method of the battery and motor is as follows: When the aircraft hovers for a long time or repeatedly takes off and lands, causing the battery to discharge at a large rate, a large amount of instantaneous heat of about 68kW is transferred from the battery and motor to the cooling liquid, the cooling liquid is evaporated and circulated in the first-stage heat exchange, 8kW of heat is output to the air, and the remaining 60kW of heat is transferred to the liquid storage tank through the liquid cooling circuit, and the second-stage heat exchange is performed with the phase change material in the liquid storage tank, a large amount of heat is transferred to the phase change material, and the phase change material changes from solid to liquid and stores a large amount of heat by using the latent heat of phase change;

[0039] When the aircraft hovers for a long time or repeatedly takes off and lands, the cooling method of the battery and motor is as follows:

[0040] When the aircraft hovers for a long time or repeatedly takes off and lands, the cooling method of the battery and motor is as follows:

[0041] When the aircraft hovers for a long time or repeatedly takes off and lands, the cooling method of the battery and motor is as follows:

[0042] Under the extremely cold condition, the temperature of the refrigerant inside the liquid storage tank is low, the thermal management control box controls the isolation valves A and B to be closed, the low-temperature coolant inside the liquid storage tank no longer participates in the circulation, and the coolant in the pipeline rises in temperature under the action of the heater 11, thereby heating the motor, the motor controller and the battery in the circulation process, so that the motor, the motor controller and the battery work at a suitable temperature. When the temperature of the motor, the motor controller and the battery rises to a certain temperature, the isolation valves are opened, and the low-temperature coolant inside the liquid storage tank cools the motor, the motor controller and the battery.

[0043] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application, but the protection scope of the present application is not limited thereto, and any person skilled in the art can easily think of various equivalent modifications or replacements within the technical range disclosed by the present application, and these modifications or replacements should be covered within the protection scope of the present application.

Claims

1. An aircraft transient heat energy storage device, comprising: The application relates to a liquid storage tank (1), which comprises a tank shell (1.1), a peripheral sandwich cavity of an inner cavity (1.2) of the tank shell (1.1), and an outlet of the liquid storage tank (1) in communication with the inner cavity (1.2); the sandwich cavity is filled with crystalline hydrated salt phase change material (1.3), and the inner cavity (1.2) of the liquid storage tank (1) is provided with cooling liquid.

2. The aircraft transient heat storage device of claim 1, wherein, The inner wall of the sandwich cavity is provided with convex cavities (1.4) protruding towards the inner cavity (1.2).

3. The aircraft transient heat storage device of claim 1, wherein, The outer wall of the sandwich cavity is provided with a phase change material injection port (1.5).

4. The aircraft transient heat storage device of claim 1, wherein, The outer wall of the sandwich cavity is provided with a vacuum extraction port (1.6).

5. The aircraft transient heat storage device of claim 1, wherein, Support ribs (1.7) are arranged between the inner and outer walls of the sandwich cavity.

6. The aircraft transient heat storage device of claim 1, wherein, The cooling liquid is No. 65 cooling liquid.

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