A method and system for cooling airborne fuel cells

Abstract

This invention relates to the field of fuel cell technology, and more specifically, to an airborne fuel cell cooling control method and system. The method includes: responding to a takeoff command from an aircraft and acquiring the aircraft's takeoff status in real time; when the aircraft is in the takeoff preparation phase, activating the battery heat dissipation circuit and the auxiliary cooling circuit respectively; when the aircraft is in the takeoff phase, acquiring the temperature parameters of the hydrogen fuel cell in the battery heat dissipation circuit in real time; adjusting the first and second opening degrees of a thermostat according to a first temperature; adjusting the first rotational speed of the auxiliary liquid cooling pump according to the first temperature; and adjusting the second rotational speed of the battery liquid cooling pump according to the temperature difference between the first and second temperatures. This invention can solve the heat dissipation problem of airborne fuel cells during takeoff.

Description

Technical Field

[0001] This invention relates to the field of fuel cell technology, and more specifically, to an airborne fuel cell cooling control method and system. Background Technology

[0002] Hydrogen fuel cells, as a power system, have the advantages of high energy density, high power generation efficiency, and green and low carbon emissions. As a power source for aircraft, they have the advantages of being pollution-free, having long flight time, and being easy to refuel.

[0003] However, the efficiency of converting chemical energy into electrical energy in hydrogen fuel cell systems is only around 50%, with the remaining energy dissipated as heat. Furthermore, the stack temperature is not high (e.g., 80℃~100℃), resulting in a small temperature difference with the ambient temperature (e.g., 25℃~40℃), leading to low heat dissipation efficiency and a complex cooling system. While high-speed ram airflow can be used for heat dissipation during high-altitude flight, the high output power, high ambient temperature, and low flight speed during takeoff make it difficult to meet the cooling requirements during takeoff. Summary of the Invention

[0004] To address the heat dissipation problem of airborne fuel cells during takeoff, this invention provides an airborne fuel cell cooling control method and system.

[0005] In a first aspect, the present invention provides an airborne fuel cell cooling control method, comprising:

[0006] In response to the takeoff command of the aircraft, the takeoff status of the aircraft is acquired in real time; the takeoff status includes the takeoff preparation phase, the takeoff in progress phase, and the ascent phase;

[0007] When the aircraft is in the takeoff preparation phase, the battery heat dissipation circuit and the auxiliary cooling circuit are activated respectively, so that the battery heat dissipation circuit and the auxiliary cooling circuit exchange heat through the mixer; in the battery heat dissipation circuit, the hydrogen fuel cell, the battery liquid cooling pump, the air radiator, the thermostat and the mixer are connected by pipelines; in the auxiliary cooling circuit, the auxiliary water tank, the auxiliary liquid cooling pump, the thermostat and the mixer are connected by pipelines.

[0008] When the aircraft is in the takeoff phase, the temperature parameters of the hydrogen fuel cell in the battery heat dissipation circuit are acquired in real time; the temperature parameters include the first temperature of the coolant outlet and the second temperature of the coolant inlet of the hydrogen fuel cell.

[0009] The thermostat adjusts the first opening degree of the thermostat on the inlet side of the battery heat dissipation circuit and the second opening degree of the thermostat on the inlet side of the auxiliary cooling circuit according to the first temperature; wherein, the first opening degree is negatively correlated with the first temperature; and the second opening degree is positively correlated with the first temperature.

[0010] The first rotational speed of the auxiliary liquid cooling pump is adjusted according to the first temperature; the first rotational speed is positively correlated with the first temperature.

[0011] The second rotational speed of the battery liquid cooling pump is adjusted according to the temperature difference between the first temperature and the second temperature; the second rotational speed is positively correlated with the temperature difference.

[0012] Optionally, the airborne fuel cell cooling control method further includes:

[0013] When the aircraft is in the takeoff phase, the battery heat dissipation circuit and the auxiliary cooling circuit are shut down, and the battery air cooling circuit is turned on; in the battery air cooling circuit, the hydrogen fuel cell, the battery liquid cooling pump, the air radiator and the bypass valve are connected through pipelines.

[0014] Optionally, the airborne fuel cell cooling control method further includes:

[0015] The cumulative flight time while the aircraft is in the takeoff phase;

[0016] The inlet temperature of the coolant in the hydrogen fuel cell when the flight duration reaches the preset duration is determined as the reference temperature;

[0017] When the reference temperature is lower than the preset temperature, the placement type of the auxiliary water tank is determined to be the first type that can be detached from the aircraft.

[0018] Optionally, the airborne fuel cell cooling control method further includes:

[0019] When the placement type is the first type, obtain the third temperature of the coolant in the auxiliary water tank;

[0020] When the third temperature is lower than the preset temperature, the spray pipeline is turned on to spray cooling water onto the air radiator; in the spray pipeline, the auxiliary water tank, the auxiliary liquid cooling pump and the nozzle are connected in sequence; the spray direction of the nozzle is set towards the air radiator.

[0021] Optionally, the airborne fuel cell cooling control method further includes:

[0022] When the third temperature is higher than the preset temperature, the battery air cooling circuit is shut down, the battery heat dissipation circuit and the auxiliary cooling circuit are turned on, and the fourth temperature of the coolant in the auxiliary water tank is obtained in real time.

[0023] When the fourth temperature is lower than the preset temperature, the battery heat dissipation circuit and the auxiliary cooling circuit are shut down, and the battery air cooling circuit and the spray pipe are turned on.

[0024] Optionally, the airborne fuel cell cooling control method further includes:

[0025] When the spray pipeline is in the open state, the remaining coolant level in the auxiliary water tank is obtained in real time.

[0026] After the coolant in the auxiliary water tank is drained, the auxiliary water tank is detached from the aircraft.

[0027] Optionally, the airborne fuel cell cooling control method further includes:

[0028] When the reference temperature is higher than the preset temperature, the placement type of the auxiliary water tank is determined to be a second type that can be retained on the aircraft.

[0029] Optionally, the airborne fuel cell cooling control method further includes:

[0030] Once the thermostat, the battery liquid cooling pump, and the auxiliary liquid cooling pump have all completed one adjustment, determine whether the first temperature is lower than the target temperature.

[0031] When the first temperature is higher than the target temperature, the process returns to the previous state, which involves adjusting the first opening of the thermostat on the inlet side of the battery heat dissipation circuit and the second opening on the inlet side of the auxiliary cooling circuit according to the first temperature, and repeats this cycle until the first temperature is lower than the target temperature.

[0032] In a second aspect, the present invention provides an airborne fuel cell cooling system, applied to the airborne fuel cell cooling control method described in any one of the first aspects, wherein the airborne fuel cell cooling system comprises:

[0033] A battery heat dissipation assembly includes a hydrogen fuel cell, a battery liquid cooling pump, an air radiator, and a bypass valve; the hydrogen fuel cell, the battery liquid cooling pump, the air radiator, and the bypass valve are connected by pipelines.

[0034] A heat transfer assembly includes a thermostat and a mixer; the thermostat has a first regulating inlet, a second regulating inlet, and a regulating outlet; the first regulating inlet is connected to the outlet of the battery liquid cooling pump; the mixer has a mixing inlet, a first mixing outlet, and a second mixing outlet; the regulating outlet is connected to the mixing inlet; the first mixing outlet is connected to the inlet of the hydrogen fuel cell.

[0035] An auxiliary cooling assembly includes an auxiliary water tank and an auxiliary liquid cooling pump; the outlet of the auxiliary water tank is connected to the inlet of the auxiliary liquid cooling pump; the outlet of the auxiliary liquid cooling pump is connected to a second regulating inlet; and the second mixed-flow outlet is connected to the inlet of the auxiliary water tank.

[0036] Optionally, the first regulating inlet is connected to the outlet of the battery liquid cooling pump via the air radiator.

[0037] Optionally, the auxiliary cooling assembly further includes a nozzle; the nozzle is connected to the outlet of the auxiliary liquid cooling pump; the spray direction of the nozzle is directed toward the air radiator.

[0038] To address the heat dissipation problem of airborne fuel cells during takeoff, this invention offers the following advantages:

[0039] 1. The auxiliary cooling circuit works in conjunction with the air radiator to dissipate heat from the hydrogen fuel cell during takeoff. Based on the hydrogen fuel cell outlet temperature (a first temperature), the opening degree of the thermostat at the inlet side of the battery cooling circuit and the opening degree of the thermostat at the inlet side of the auxiliary cooling circuit are adjusted. This regulates the mixing ratio of the coolant entering the mixer in the battery cooling circuit, thereby controlling the coolant temperature. The first rotational speed of the auxiliary liquid-cooled pump is adjusted based on the first temperature to further control the heat dissipation of the hydrogen fuel cell. Based on the temperature difference between the first and second temperatures, the second rotational speed of the battery liquid-cooled pump is adjusted, thereby regulating the coolant flow rate through the hydrogen fuel cell to meet the temperature uniformity requirements of the hydrogen fuel cell. By controlling the temperature and flow rate of the coolant flowing through the hydrogen fuel cell, the coolant temperature at the hydrogen fuel cell outlet can be monitored in real time during takeoff, thus compensating for the insufficient heat dissipation capacity of the air radiator during takeoff and solving the heat dissipation problem of the airborne fuel cell during takeoff.

[0040] 2. Once the aircraft is in the takeoff phase, the air radiator uses high-speed ram airflow for heat dissipation, significantly improving its heat dissipation capacity. At this time, the mixed-flow heat exchange between the battery cooling circuit and the auxiliary cooling circuit can be suspended, and the heat dissipation effect of the hydrogen fuel cell can generally be met through the battery air cooling circuit.

[0041] 3. When the hydrogen fuel cell is cooled by the battery air-cooling circuit for a preset time, i.e., when the flight time reaches the preset duration, the air radiator's cooling capacity for the hydrogen fuel cell in the air is accurately determined by checking whether the temperature of the coolant inlet of the hydrogen fuel cell is lower than the preset temperature. When the air cooling capacity meets the standard, the cooling water tank in the auxiliary cooling circuit can be installed in the first type, which can be detached from the aircraft, thereby reducing the aircraft's weight and flight energy consumption. Attached Figure Description

[0042] Figure 1 A schematic flowchart of an airborne fuel cell cooling control method according to Embodiment 1 is shown;

[0043] Figure 2 A schematic diagram of an airborne fuel cell cooling system according to Embodiment 2 is shown;

[0044] Figure 3 A schematic diagram of the auxiliary water tank in Embodiment 2 is shown;

[0045] Figure 4 A cross-sectional view of the mixer in Embodiment 2 is shown;

[0046] Figure 5 A schematic diagram of the structure of the first perforated plate in Embodiment 2 is shown;

[0047] Figure 6 A schematic diagram of the structure of the second perforated plate in Embodiment 2 is shown.

[0048] Reference numerals: 10, Battery heat dissipation assembly; 11, Hydrogen fuel cell; 12, Battery liquid cooling pump; 13, Air radiator; 14, Bypass valve; 20, Heat transfer assembly; 21, Thermostat; 22, Mixer; 221, Housing; 222, Outlet pipe; 223, Inlet pipe; 224, First orifice plate; 225, Second orifice plate; 226, First through hole; 227, Second through hole; 30, Auxiliary cooling assembly; 31, Auxiliary water tank; 32, Auxiliary liquid cooling pump; 33, Nozzle; 34, Heat dissipation fins; 40, Valve unit; 41, First shut-off valve; 42, Second shut-off valve; 43, Third shut-off valve; 50, Temperature sensing unit; 51, First temperature sensor; 52, Second temperature sensor; 53, Third temperature sensor. Detailed Implementation

[0049] The present disclosure will now be discussed with reference to several exemplary embodiments. It should be understood that these embodiments are discussed only to enable those skilled in the art to better understand and thus implement the present disclosure, and are not intended to imply any limitation on the scope of the disclosure.

[0050] As used herein, the term "comprising" and its variations are to be interpreted as open-ended terms meaning "including but not limited to". The term "based on" is to be interpreted as "at least partially based on". The terms "one embodiment" and "an embodiment" are to be interpreted as "at least one embodiment". The term "another embodiment" is to be interpreted as "at least one other embodiment". The terms "upper", "lower", "left", "right", "front", "rear", "top", "bottom", "inner", "outer", "vertical", "horizontal", "lateral", "longitudinal", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings. These terms are primarily for the purpose of better describing this application and its embodiments and are not intended to limit the indicated devices, elements, or components to having a specific orientation or being constructed and operated in a specific orientation. Furthermore, some of the above terms may be used to indicate other meanings besides orientations or positional relationships; for example, the term "upper" may in some cases indicate a dependency or connection relationship. Those skilled in the art can understand the specific meaning of these terms in this application according to the specific circumstances. In addition, the terms "installed", "set up", "equipped with", "connected", and "linked" should be interpreted broadly. For example, it can be a fixed connection, a detachable connection, or an integral structure; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, or an internal connection between two devices, elements, or components. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances. Furthermore, the terms "first," "second," etc., are mainly used to distinguish different devices, elements, or components (the specific types and structures may be the same or different), and are not used to indicate or imply the relative importance or quantity of the indicated devices, elements, or components. Unless otherwise stated, "a plurality of" means two or more.

[0051] To address the heat dissipation problem of airborne fuel cells during takeoff, this invention provides an airborne fuel cell cooling control method and system.

[0052] Example 1:

[0053] like Figure 1 As shown, the airborne fuel cell cooling control method provided by the present invention includes steps S10 to S30.

[0054] Step S10: In response to the aircraft's takeoff command, the aircraft's takeoff status is acquired in real time. The takeoff status includes the takeoff preparation phase, the takeoff mid-takeoff phase, and the ascent phase. It should be understood that during the takeoff preparation phase, it is necessary to check whether the aircraft meets the conditions for safe takeoff, and the power system preheats and starts up. During the takeoff mid-takeoff phase, the aircraft's power begins to increase, and the fuselage gradually lifts off the ground, but has not yet entered stable cruise. During the ascent phase, the aircraft has successfully left the ground and reached the preset safe altitude or preset safe speed, entering a stable climb or about to enter cruise, and the flight status is controllable.

[0055] In step S20, when the aircraft is in the takeoff preparation stage, the battery heat dissipation circuit and the auxiliary cooling circuit are turned on respectively, so that the battery heat dissipation circuit and the auxiliary cooling circuit can exchange heat through the mixer 22.

[0056] like Figure 2 As shown, in the battery heat dissipation circuit, the hydrogen fuel cell 11, battery liquid cooling pump 12, air radiator 13, thermostat 21, and mixer 22 are connected by pipelines. It should be understood that the connection order of the components in the battery heat dissipation circuit can be adaptively adjusted. In this embodiment, as a preferred embodiment, the air radiator 13 is connected between the outlet of the battery liquid cooling pump 12 and the inlet of the thermostat 21. That is, the coolant at the outlet of the hydrogen fuel cell 11 first exchanges heat with the ambient atmosphere through the air radiator 13, and then exchanges heat with the coolant in the auxiliary cooling circuit, so as to save the cooling capacity in the auxiliary cooling circuit.

[0057] like Figure 2 As shown, in the auxiliary cooling circuit, the auxiliary water tank 31, auxiliary liquid cooling pump 32, thermostat 21, and mixer 22 are connected by pipelines. In this embodiment, the outlet of the auxiliary liquid cooling pump 32 and the outlet of the battery liquid cooling pump 12 are both connected to the inlet side of the thermostat 21, so that the two streams of coolant in the battery heat dissipation circuit and the auxiliary cooling circuit flow in the same direction in the mixer 22, thereby making it less likely to lose fluid kinetic energy and reducing the energy consumption of the auxiliary liquid cooling pump 32 and the battery liquid cooling pump 12.

[0058] Step S30 includes steps S31 to S34.

[0059] Step S31: When the aircraft is in the takeoff phase, the temperature parameters of the hydrogen fuel cell 11 in the battery heat dissipation circuit are acquired in real time; the temperature parameters include the first temperature of the coolant outlet and the second temperature of the coolant inlet of the hydrogen fuel cell 11. This allows for real-time monitoring of the heat dissipation of the hydrogen fuel cell 11.

[0060] Step S32: Adjust the thermostat 21 according to the first temperature, setting a first opening degree on the inlet side of the battery heat dissipation circuit and a second opening degree on the inlet side of the auxiliary cooling circuit; wherein, the first opening degree is negatively correlated with the first temperature; and the second opening degree is positively correlated with the first temperature.

[0061] Step S33: Adjust the first rotation speed of the auxiliary liquid cooling pump 32 according to the first temperature; the first rotation speed is positively correlated with the first temperature.

[0062] Step S34: Adjust the second rotation speed of the battery liquid cooling pump 12 according to the temperature difference between the first temperature and the second temperature; the second rotation speed is positively correlated with the temperature difference.

[0063] In this embodiment, the first opening degree, second opening degree, and first rotation speed are adjusted according to the first temperature to regulate the mixing ratio of the coolant in the battery heat dissipation circuit and the coolant in the auxiliary cooling circuit entering the mixer 22. When the hydrogen fuel cell 11 generates a lot of heat, the first temperature rises. At this time, the first opening degree is reduced to decrease the mixing ratio of the coolant in the battery heat dissipation circuit in the mixer 22, and the second opening degree and first rotation speed are increased to increase the mixing ratio of the coolant in the auxiliary cooling circuit in the mixer 22. The second rotation speed of the battery liquid cooling pump 12 is adjusted according to the temperature difference between the second temperature at the inlet and the first temperature at the outlet of the hydrogen fuel cell 11, thereby regulating the flow rate of the coolant flowing through the hydrogen fuel cell 11. When the temperature difference is high, it is difficult to meet the temperature uniformity of the hydrogen fuel cell 11. Therefore, the second rotation speed is increased to increase the flow rate of the coolant flowing through the hydrogen fuel cell 11 to reduce the temperature difference. By controlling the mixing ratio and flow rate of the battery heat dissipation circuit and the auxiliary cooling circuit, the coolant temperature at the outlet of the hydrogen fuel cell 11 can be controlled in real time during takeoff, thereby compensating for the insufficient heat dissipation capacity of the air radiator 13 during takeoff and solving the heat dissipation problem of the airborne fuel cell during takeoff.

[0064] Furthermore, the airborne fuel cell cooling control method also includes step S40. Step S40 includes step S41.

[0065] Step S41: When the aircraft is in the takeoff phase, shut down the battery heat dissipation circuit and auxiliary cooling circuit, and activate the battery air cooling circuit. For example... Figure 2 As shown, in the battery air-cooling circuit, the hydrogen fuel cell 11, the battery liquid-cooled pump 12, the air radiator 13, and the bypass valve 14 are connected by pipelines. It should be understood that the connection sequence of the devices in the battery air-cooling circuit can be adaptively adjusted.

[0066] Once the aircraft is in the takeoff phase, the air radiator 13 uses high-speed ram airflow for heat dissipation, significantly improving its heat dissipation capacity. At this time, the mixed-flow heat exchange between the battery cooling circuit and the auxiliary cooling circuit can be suspended. The heat dissipation effect of the hydrogen fuel cell 11 can generally be met through the battery air cooling circuit.

[0067] Furthermore, step S40 also includes steps S42 to S44.

[0068] Step S42: While the aircraft is in the takeoff phase, the cumulative flight time is recorded. This cumulative flight time is used to measure the duration during which the battery air-cooling circuit provides heat dissipation for the hydrogen fuel cell 11 during the takeoff phase.

[0069] Step S43: The coolant inlet temperature of the hydrogen fuel cell 11 when the flight duration reaches the preset duration is determined as the reference temperature. The reference temperature can be used to determine whether the cooling effect of the air radiator 13 meets the requirements after the preset flight duration.

[0070] Step S44 includes step S441.

[0071] In step S441, when the reference temperature is lower than the preset temperature, the placement type of the auxiliary water tank 31 is determined to be the first type, which allows it to be detached from the aircraft. It should be understood that the preset temperature can be set according to actual needs. When the reference temperature is lower than the preset temperature, it indicates that the cooling effect of the air radiator 13 meets the requirements. At this time, the auxiliary water tank 31 can be detached from the aircraft to reduce the aircraft's weight, thereby providing higher flight performance for special-operation aircraft.

[0072] Furthermore, step S44 also includes steps S442 and S443.

[0073] Step S442: When the installation type is type one, obtain the third temperature of the coolant in the auxiliary water tank 31. By judging the level of the third temperature, it can be determined whether the coolant in the auxiliary water tank 31 is suitable for spray cooling, or the cooling effect of spray cooling.

[0074] Step S443: When the third temperature is lower than the preset temperature, the spray pipe is turned on to spray cooling water onto the air radiator 13. Figure 2 As shown, in the spray pipeline, the auxiliary water tank 31, the auxiliary liquid cooling pump 32, and the nozzle 33 are connected in sequence; the spray direction of the nozzle 33 is set towards the air radiator 13. When the third temperature is lower than the preset temperature, the coolant in the auxiliary water tank 31 is released by spraying, which can maximize the use of the coolant in the auxiliary water tank 31 to cool the hydrogen fuel cell 11.

[0075] Furthermore, step S44 also includes steps S444 and S445.

[0076] In step S444, when the third temperature is higher than the preset temperature, the battery air-cooling circuit is shut down, the battery heat dissipation circuit and the auxiliary cooling circuit are turned on, and the fourth temperature of the coolant in the auxiliary water tank 31 is acquired in real time. When the temperature of the coolant in the auxiliary water tank 31 is too high, i.e., higher than the preset temperature, heat exchange is performed by turning on the battery heat dissipation circuit and the auxiliary cooling circuit again. At this time, the air radiator 13 with strong heat dissipation capacity is used to cool down both the hydrogen fuel cell 11 and the coolant in the auxiliary water tank 31 to meet the temperature requirements of the spray. In some embodiments, the coolant outlet temperature of the hydrogen fuel cell 11 can be determined so that the coolant in the auxiliary water tank 31 is cooled down when the heat dissipation capacity of the air radiator 13 is excessive, thereby reducing the heat dissipation load of the air radiator 13.

[0077] In step S445, when the fourth temperature is lower than the preset temperature, the battery heat dissipation circuit and auxiliary cooling circuit are shut down, and the battery air cooling circuit and spray pipe are turned on. The sprayed coolant has a lower temperature, thereby maximizing the cooling effect on the hydrogen fuel cell 11.

[0078] Furthermore, step S44 also includes steps S446 and S447.

[0079] Step S446: When the spray pipeline is in the open state, the remaining coolant level in the auxiliary water tank 31 is obtained in real time. The spraying end time can be determined based on the remaining coolant level.

[0080] In step S447, after the coolant in the auxiliary water tank 31 is drained, the auxiliary water tank 31 is detached from the aircraft. This reduces the weight of the aircraft and greatly helps improve the performance of small special-purpose aircraft. When the auxiliary water tank 31 is detached from the aircraft, a recovery device such as a safety net can be set up on the ground to ensure the safety and environmental protection requirements of the recovery process.

[0081] Furthermore, step S40 also includes step S45.

[0082] Step S45: When the reference temperature is higher than the preset temperature, the placement type of the auxiliary water tank 31 is determined to be the second type, which allows it to be retained on the aircraft. For example... Figure 3 As shown, the auxiliary water tank 31 is surrounded by a heat dissipation fin structure 34. When the auxiliary water tank 31 is left on the aircraft, the heat dissipation fins 34 play a role in heat dissipation during flight. The temperature of the coolant inside the auxiliary water tank 31 is cooled down by the heat dissipation fins 34 and then kept on standby to supplement heat dissipation when the aircraft is in a state of emergency.

[0083] Furthermore, step S30 also includes steps S35 and S36.

[0084] Step S35: After the thermostat 21, battery liquid cooling pump 12, and auxiliary liquid cooling pump 32 have all completed one adjustment, determine whether the first temperature is lower than the target temperature. The heat dissipation of the hydrogen fuel cell 11 is determined by the level of the first temperature.

[0085] In step S36, when the first temperature is higher than the target temperature, the process returns to the step of adjusting the thermostat 21 according to the first temperature at the first opening on the inlet side of the battery heat dissipation circuit and the second opening on the inlet side of the auxiliary cooling circuit, respectively, and repeats until the first temperature is lower than the target temperature, that is, the process returns to steps S32 to S34. Thus, by repeating steps S32 to S35, the coolant outlet temperature of the hydrogen fuel cell 11 is reduced to the preset target, thereby ensuring the reliable operation of the hydrogen fuel cell 11.

[0086] Example 2:

[0087] This embodiment provides an airborne fuel cell cooling system, which is applied to an airborne fuel cell cooling control method in any of the above embodiments.

[0088] like Figure 2 As shown, the airborne fuel cell cooling system includes a battery heat dissipation assembly 10, a heat transfer assembly 20, and an auxiliary cooling assembly 30. The battery heat dissipation assembly 10 includes a hydrogen fuel cell 11, a battery liquid cooling pump 12, an air radiator 13, and a bypass valve 14; the hydrogen fuel cell 11, the battery liquid cooling pump 12, the air radiator 13, and the bypass valve 14 are connected by pipelines.

[0089] like Figure 2 As shown, the heat transfer assembly 20 includes a thermostat 21 and a mixer 22; the thermostat 21 has a first regulating inlet, a second regulating inlet and a regulating outlet; the first regulating inlet is connected to the outlet of the battery liquid cooling pump 12; the mixer 22 has a mixing inlet, a first mixing outlet and a second mixing outlet; the regulating outlet is connected to the mixing inlet; the first mixing outlet is connected to the inlet of the hydrogen fuel cell 11.

[0090] like Figure 2 As shown, the auxiliary cooling assembly 30 includes an auxiliary water tank 31 and an auxiliary liquid cooling pump 32; the outlet of the auxiliary water tank 31 is connected to the inlet of the auxiliary liquid cooling pump 32; the outlet of the auxiliary liquid cooling pump 32 is connected to the second regulating inlet; and the second mixed flow outlet is connected to the inlet of the auxiliary water tank 31.

[0091] The hydrogen fuel cell 11, battery liquid cooling pump 12, air radiator 13, thermostat 21, and mixer 22 are sequentially connected through pipelines to form a battery heat dissipation circuit. The connection order of each component in the battery heat dissipation circuit can also be adjusted according to actual needs. The auxiliary water tank 31, auxiliary liquid cooling pump 32, thermostat 21, and mixer 22 are sequentially connected through pipelines to form an auxiliary cooling circuit. The connection order of each component in the auxiliary cooling circuit can also be adjusted according to actual needs.

[0092] By using the auxiliary cooling circuit to dissipate heat from the battery cooling circuit during flight, the insufficient heat dissipation capacity of the air radiator 13 during takeoff is compensated, thus solving the heat dissipation problem of the airborne fuel cell during takeoff.

[0093] Furthermore, such as Figure 3 As shown, the auxiliary cooling assembly 30 also includes heat dissipation fins 34, which are fixed to the outer surface of the auxiliary water tank 31. This allows the external air to be used to cool the coolant in the auxiliary water tank 31.

[0094] Furthermore, such as Figure 2 As shown, the first regulating inlet is connected to the outlet of the battery liquid cooling pump 12 via the air radiator 13. Before the coolant flowing through the hydrogen fuel cell 11 reaches the mixer 22, it is cooled first by the air radiator 13, saving coolant cooling capacity in the auxiliary water tank 31. This maximizes the heat dissipation effect of the hydrogen fuel cell 11 during aircraft takeoff.

[0095] Furthermore, such as Figure 4 , Figure 5 and Figure 6 As shown, the mixer 22 includes a housing 221, an outlet pipe 222, an inlet pipe 223, a first orifice plate 224, and a second orifice plate 225. The outlet pipe 222 and the inlet pipe 223 are connected to opposite sides of the housing 221. The outlet pipe 222 can be connected to a tee pipe to form a first mixing outlet and a second mixing outlet. The first orifice plate 224 and the second orifice plate 225 are located in the housing 221 and are fixedly connected to the housing 221. The first orifice plate 224 and the second orifice plate 225 are located between the outlet pipe 222 and the inlet pipe 223. The first orifice plate 224 and the second orifice plate 225 are parallel; both the first orifice plate 224 and the second orifice plate 225 are perpendicular to the axis of the outlet pipe 222 or the inlet pipe 223. The first orifice plate 224 has multiple first through holes 226; the second orifice plate 225 has multiple second through holes 227. The first through-hole 226 and the second through-hole 227 are offset in projection along the axial direction of the inlet pipe 223. This offset arrangement of the first through-hole 226 and the second through-hole 227 improves the mixed-flow heat transfer effect.

[0096] Furthermore, such as Figure 2 As shown, the airborne fuel cell cooling system also includes a valve unit 40 and a temperature sensing unit 50. The valve unit 40 includes a first shut-off valve 41 and a second shut-off valve 42. The first shut-off valve 41 is connected to the inlet of the auxiliary water tank 31, and the second shut-off valve 42 is connected to the outlet of the auxiliary water tank 31. The temperature sensing unit 50 includes a first temperature sensor 51 and a second temperature sensor 52. The first temperature sensor 51 is connected to the coolant outlet of the hydrogen fuel cell 11, and the second temperature sensor 52 is connected to the coolant inlet of the hydrogen fuel cell 11.

[0097] Furthermore, such as Figure 2 As shown, the auxiliary cooling assembly 30 also includes a nozzle 33; the nozzle 33 is connected to the outlet of the auxiliary liquid cooling pump 32; the spray direction of the nozzle 33 is set towards the air radiator 13. Before the auxiliary water tank 31 needs to be detached from the aircraft, the coolant in the auxiliary water tank 31 is sprayed towards the air radiator 13 to assist in cooling. Finally, the empty auxiliary water tank 31 is detached from the aircraft, which can improve the heat dissipation effect of the hydrogen fuel cell 11 and reduce the difficulty of recovering the auxiliary water tank 31.

[0098] Furthermore, such as Figure 2 As shown, the valve unit 40 also includes a third shut-off valve 43, which is connected to the inlet of the nozzle 33; the temperature sensing unit 50 also includes a third temperature sensor 53, which is connected to the auxiliary water tank 31. It should be understood that the third shut-off valve 43 can also be integrated into the nozzle 33.

[0099] Those skilled in the art will understand that the above embodiments are specific examples of implementing this disclosure, and in practical applications, various changes can be made in form and detail without departing from the scope of this disclosure.

Claims

1. A method for cooling and controlling an airborne fuel cell, characterized in that, The airborne fuel cell cooling control method includes: In response to the takeoff command of the aircraft, the takeoff status of the aircraft is acquired in real time; the takeoff status includes the takeoff preparation phase, the takeoff in progress phase, and the ascent phase; When the aircraft is in the takeoff preparation phase, the battery heat dissipation circuit and the auxiliary cooling circuit are activated respectively, so that the battery heat dissipation circuit and the auxiliary cooling circuit exchange heat through the mixer; in the battery heat dissipation circuit, the hydrogen fuel cell, the battery liquid cooling pump, the air radiator, the thermostat and the mixer are connected by pipelines; in the auxiliary cooling circuit, the auxiliary water tank, the auxiliary liquid cooling pump, the thermostat and the mixer are connected by pipelines. When the aircraft is in the takeoff phase, the temperature parameters of the hydrogen fuel cell in the battery heat dissipation circuit are acquired in real time; the temperature parameters include the first temperature of the coolant outlet and the second temperature of the coolant inlet of the hydrogen fuel cell. The thermostat adjusts the first opening degree of the thermostat on the inlet side of the battery heat dissipation circuit and the second opening degree of the thermostat on the inlet side of the auxiliary cooling circuit according to the first temperature; wherein, the first opening degree is negatively correlated with the first temperature; and the second opening degree is positively correlated with the first temperature. The first rotational speed of the auxiliary liquid cooling pump is adjusted according to the first temperature; the first rotational speed is positively correlated with the first temperature. The second rotational speed of the battery liquid cooling pump is adjusted according to the temperature difference between the first temperature and the second temperature; the second rotational speed is positively correlated with the temperature difference.

2. The airborne fuel cell cooling control method according to claim 1, characterized in that, The airborne fuel cell cooling control method further includes: When the aircraft is in the takeoff phase, the battery heat dissipation circuit and the auxiliary cooling circuit are shut down, and the battery air cooling circuit is turned on; in the battery air cooling circuit, the hydrogen fuel cell, the battery liquid cooling pump, the air radiator and the bypass valve are connected through pipelines.

3. The airborne fuel cell cooling control method according to claim 2, characterized in that, The airborne fuel cell cooling control method further includes: The cumulative flight time while the aircraft is in the takeoff phase; The inlet temperature of the coolant in the hydrogen fuel cell when the flight duration reaches the preset duration is determined as the reference temperature; When the reference temperature is lower than the preset temperature, the placement type of the auxiliary water tank is determined to be the first type that can be detached from the aircraft.

4. The airborne fuel cell cooling control method according to claim 3, characterized in that, The airborne fuel cell cooling control method further includes: When the placement type is the first type, obtain the third temperature of the coolant in the auxiliary water tank; When the third temperature is lower than the preset temperature, the spray pipeline is turned on to spray cooling water onto the air radiator; in the spray pipeline, the auxiliary water tank, the auxiliary liquid cooling pump and the nozzle are connected in sequence; the spray direction of the nozzle is set towards the air radiator.

5. The airborne fuel cell cooling control method according to claim 4, characterized in that, The airborne fuel cell cooling control method further includes: When the third temperature is higher than the preset temperature, the battery air cooling circuit is shut down, the battery heat dissipation circuit and the auxiliary cooling circuit are turned on, and the fourth temperature of the coolant in the auxiliary water tank is obtained in real time. When the fourth temperature is lower than the preset temperature, the battery heat dissipation circuit and the auxiliary cooling circuit are shut down, and the battery air cooling circuit and the spray pipe are turned on.

6. The airborne fuel cell cooling control method according to claim 4, characterized in that, The airborne fuel cell cooling control method further includes: When the spray pipeline is in the open state, the remaining coolant level in the auxiliary water tank is obtained in real time. After the coolant in the auxiliary water tank is drained, the auxiliary water tank is detached from the aircraft.

7. The airborne fuel cell cooling control method according to claim 3, characterized in that, The airborne fuel cell cooling control method further includes: When the reference temperature is higher than the preset temperature, the placement type of the auxiliary water tank is determined to be a second type that can be retained on the aircraft.

8. The airborne fuel cell cooling control method according to claim 1, characterized in that, The airborne fuel cell cooling control method further includes: Once the thermostat, the battery liquid cooling pump, and the auxiliary liquid cooling pump have all completed one adjustment, determine whether the first temperature is lower than the target temperature. When the first temperature is higher than the target temperature, the process returns to the previous state, which involves adjusting the first opening of the thermostat on the inlet side of the battery heat dissipation circuit and the second opening on the inlet side of the auxiliary cooling circuit according to the first temperature, and repeats this cycle until the first temperature is lower than the target temperature.

9. An airborne fuel cell cooling system, applied to the airborne fuel cell cooling control method according to any one of claims 1-8; characterized in that, The airborne fuel cell cooling system includes: A battery heat dissipation assembly includes a hydrogen fuel cell, a battery liquid cooling pump, an air radiator, and a bypass valve; the hydrogen fuel cell, the battery liquid cooling pump, the air radiator, and the bypass valve are connected by pipelines. A heat transfer assembly, comprising a thermostat and a mixer; the thermostat having a first regulating inlet, a second regulating inlet, and a regulating outlet; the first regulating inlet being connected to the outlet of the battery liquid cooling pump; the mixer having a mixing inlet, a first mixing outlet, and a second mixing outlet; the regulating outlet being connected to the mixing inlet; and the first mixing outlet being connected to the inlet of the hydrogen fuel cell. An auxiliary cooling assembly includes an auxiliary water tank and an auxiliary liquid cooling pump; the outlet of the auxiliary water tank is connected to the inlet of the auxiliary liquid cooling pump; the outlet of the auxiliary liquid cooling pump is connected to a second regulating inlet; and the second mixed-flow outlet is connected to the inlet of the auxiliary water tank.

10. An airborne fuel cell cooling system according to claim 9, characterized in that, The first regulating inlet is connected to the outlet of the battery liquid cooling pump through the air radiator.

11. An airborne fuel cell cooling system according to claim 9, characterized in that, The auxiliary cooling assembly also includes a nozzle; the nozzle is connected to the outlet of the auxiliary liquid cooling pump; the spray direction of the nozzle is directed toward the air radiator.

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