An airborne hybrid refrigeration system, aircraft and control method

Abstract

The present invention relates to the field of aircraft heat dissipation technology, and in particular, to an airborne hybrid refrigeration system, an aircraft and a control method. The airborne hybrid refrigeration system includes a power assembly, a motor assembly, an air circulation assembly and a liquid cooling circulation assembly. The motor, the compressor and the gas turbine are coaxially connected. The air circulation assembly includes a cooling turbine, a first heat exchanger and a first water separator. The compressor, the cooling turbine and the first water separator are connected in sequence to form an air supply path. The outlet of the cooling turbine is connected to the inlet of the first heat exchanger to form a refrigeration air circuit. In the liquid cooling circulation assembly, a liquid cooling pump, a heat load heat exchanger, a first isolation pipeline and a second isolation pipeline are connected to form a liquid cooling circuit. In the liquid cooling circuit, the evaporator and the first isolation pipeline are connected in parallel, and the first heat exchanger and the second isolation pipeline are connected in parallel. The aircraft includes an airborne hybrid refrigeration system, and the control method is applied to the aircraft, thereby solving the problems of design redundancy and high energy consumption in the airborne hybrid refrigeration system.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft heat dissipation, and in particular to an airborne hybrid refrigeration system, an aircraft and a control method. Background Art

[0002] For example, the power supply, hydraulic action, environmental control, and auxiliary / emergency power functions of aircraft such as special operations drones are all undertaken by the electromechanical system, which is like the "blood, muscles, and five internal organs" of the aircraft. It plays a key role in the energy management of the aircraft and directly affects the flight safety and aviation efficiency of the aircraft. Among the functions of the electromechanical system, the energy supply and heat dissipation capabilities of environmental control and auxiliary / emergency power directly affect the functional realization of the mission system. In addition to ensuring a stable supply of electricity, a good energy supply system can also greatly improve the utilization rate of energy, reduce the energy consumption of the aircraft, and extend the working time. The heat dissipation system can dissipate the heat generated by the operation of various parts of the aircraft, ensuring that the mission system maintains a suitable temperature during long-term operation, avoiding damage caused by failures during the operation of the aircraft, and thus extending the service life.

[0003] The energy supply form of traditional aircraft electromechanical systems is generally an engine-driven generator, and the heat dissipation form is commonly an air circulation system or an evaporative circulation liquid cooling system. These traditional electromechanical systems are independent of each other, and there is no interactive interface between the systems. They can only be designed according to the maximum capacity and run according to the load requirements. In the working background of the aircraft's extremely high peak-to-average power demand, it often results in design redundancy, heavy system weight, and high comprehensive fuel consumption, which can no longer meet the development requirements of new aircraft. Summary of the invention

[0004] In order to solve the problems of design redundancy and high energy consumption of an airborne hybrid refrigeration system, the present invention provides an airborne hybrid refrigeration system, an aircraft and a control method.

[0005] In a first aspect, the present invention provides an airborne hybrid refrigeration system, the airborne hybrid refrigeration system comprising:

[0006] A power assembly, the power assembly comprising a compressor, an air intake, a combustion chamber and a gas turbine; the inlet of the air intake is connected to the atmosphere; the outlet of the air intake is connected to the inlet of the compressor; the compressor, the combustion chamber and the gas turbine are detachably connected in sequence; the outlet of the compressor is connected to the combustion chamber to form a driving air path; the compressor is coaxially connected to the gas turbine;

[0007] A motor assembly, the motor assembly comprising a starter-generator integrated motor; the starter-generator integrated motor is coaxially connected to the compressor;

[0008] An air circulation component, the air circulation component includes a cooling turbine, a first heat exchanger and a first water separator; the cooling turbine is coaxially connected to the starting-integrated motor; the outlet of the compressor is connected to the inlet of the cooling turbine to form a first air supply path; the first air supply path is provided with a first valve; the outlet of the cooling turbine is connected to the inlet of the first heat exchanger to form a refrigeration air path; the outlet of the cooling turbine is connected to the first water separator to form a second air supply path; the refrigeration air path is provided with a second valve; the outlet of the first heat exchanger is connected to the atmosphere to form an exhaust path; the exhaust path is provided with an exhaust valve; the outlet of the first heat exchanger is connected to the inlet of the compressor to form a return path;

[0009] An evaporation cycle assembly, the evaporation cycle assembly includes a compressor, an evaporator, an expansion valve, and a first condenser; the compressor is coaxially connected to the cooling turbine; the compressor, the evaporator, the expansion valve and the first condenser are connected end to end in sequence to form a compression refrigeration circuit; the evaporation cycle assembly also includes a refrigeration regulating valve; the refrigeration regulating valve and the compressor are connected in parallel in the compression refrigeration circuit; a fuel delivery assembly, the fuel delivery assembly includes a fuel pipeline; the fuel pipeline passes through the first condenser;

[0010] A liquid cooling circulation component, the liquid cooling circulation component includes a liquid cooling pump, a heat load heat exchanger, a first isolation pipeline and a second isolation pipeline; the liquid cooling pump, the heat load heat exchanger, the first isolation pipeline and the second isolation pipeline are connected to form a liquid cooling circuit; the evaporator and the first isolation pipeline are connected in parallel in the liquid cooling circuit; the first heat exchanger and the second isolation pipeline are connected in parallel in the liquid cooling circuit; the liquid cooling circulation component also includes a first isolation valve and a second isolation valve; the first isolation valve is detachably connected to the first isolation pipeline; the second isolation valve is detachably connected to the second isolation pipeline.

[0011] In some embodiments, the fuel delivery assembly further comprises a temperature sensor, the temperature sensor being detachably connected to the fuel pipeline; the temperature sensor detecting the fuel temperature;

[0012] The refrigeration regulating valve, the first isolation valve and the second isolation valve can adjust the opening degree; the temperature sensor is electrically connected to the refrigeration regulating valve, the first isolation valve and the second isolation valve respectively.

[0013] In some embodiments, the air circulation component also includes a second condenser and a second water separator; the second condenser has a first channel and a second channel isolated from each other; heat exchange can be performed between the first channel and the second channel; the second water separator is detachably connected to the second condenser; the second water separator is used to separate gas and liquid from the medium passing through the first channel and the second channel; the outlet of the compressor is connected to the inlet of the cooling turbine through the first channel; the outlet of the first heat exchanger is connected to the atmosphere through the second channel; the outlet of the first heat exchanger is connected to the inlet of the compressor through the second channel.

[0014] In some embodiments, the air circulation component also includes a second heat exchanger; the second heat exchanger has a third channel and a fourth channel isolated from each other; the third channel and the fourth channel are capable of heat exchange; the outlet of the compressor is connected to the first channel through the third channel; the outlet of the first heat exchanger is connected to the atmosphere through the second channel and the fourth channel in sequence; the outlet of the first heat exchanger is connected to the inlet of the compressor through the second channel and the fourth channel in sequence.

[0015] In some embodiments, the onboard hybrid refrigeration system includes an engine air compressor assembly;

[0016] The power assembly also includes an air bleed pipeline; the inlet of the air bleed pipeline is detachably connected to the engine compressor assembly; the outlet of the air bleed pipeline is communicated with the combustion chamber; and an air bleed valve is arranged on the air bleed pipeline.

[0017] In some embodiments, the power assembly further includes an air supply pipeline; the inlet of the air supply pipeline is detachably connected to the engine air compressor assembly; the outlet of the air supply pipeline is connected to the return path; and an air supply valve is provided on the air supply pipeline.

[0018] In a second aspect, the present invention provides an aircraft, the aircraft comprising any one of the onboard hybrid refrigeration systems of the first aspect, the aircraft comprising:

[0019] Rack system; the onboard hybrid refrigeration system is detachably connected to the rack system.

[0020] In a third aspect, the present invention provides an aircraft control method, the aircraft control method is applied to the aircraft of the second aspect, the aircraft control method comprising:

[0021] Step S10, wherein step S10 includes steps S11 to S16;

[0022] Step S11, based on the fact that the engine of the aircraft is in a shut-down state, obtaining a first working instruction of the aircraft;

[0023] Step S12, based on the first working instruction including air supply and cooling, opening the air intake part and the driving air path; until the speed of the gas turbine reaches a first preset speed;

[0024] Step S13, based on the rotation speed of the gas turbine reaching the first preset rotation speed, obtaining a cooling gear in the first working instruction;

[0025] Step S14, based on the refrigeration gear in the first working instruction being the first gear, opening the first air supply path, the second air supply path, the refrigeration gas path, the exhaust path and the liquid cooling circuit, opening the first isolation pipeline and closing the second isolation pipeline;

[0026] Step S15, based on the refrigeration gear in the first working instruction being the second gear, opening the first air supply path, the second air supply path, the compression refrigeration circuit and the liquid cooling circuit, closing the first isolation pipeline and opening the second isolation pipeline;

[0027] Step S16, based on the refrigeration gear in the first working instruction being the third gear, open the first air supply path, the second air supply path, the refrigeration gas path, the exhaust path, the compression refrigeration circuit and the liquid cooling circuit, and close the first isolation pipeline and the second isolation pipeline.

[0028] In some embodiments, the aircraft control method further includes:

[0029] Step S20, wherein step S20 includes steps S21 to S26;

[0030] Step S21, based on the engine of the aircraft being in an on state, obtaining a second working instruction of the aircraft;

[0031] Step S22, based on the second working instruction including air supply and cooling, opening the bleed air pipeline; until the speed of the gas turbine reaches a second preset speed;

[0032] Step S23, based on the rotation speed of the gas turbine reaching the second preset rotation speed, obtaining the cooling gear in the second working instruction;

[0033] Step S24, based on the cooling gear in the second working instruction being the first gear, opening the air supply pipeline, the first air supply path, the second air supply path, the cooling gas path, the return path and the liquid cooling circuit, opening the first isolation pipeline and closing the second isolation pipeline;

[0034] Step S25, based on the refrigeration gear in the second working instruction being the second gear, opening the air supply pipeline, the first air supply path, the second air supply path, the compression refrigeration circuit and the liquid cooling circuit, closing the first isolation pipeline and opening the second isolation pipeline;

[0035] Step S26, based on the refrigeration gear in the second working instruction being the third gear, open the air supply pipeline, the first air supply path, the second air supply path, the refrigeration gas circuit, the return path, the compression refrigeration circuit and the liquid cooling circuit, and close the first isolation pipeline and the second isolation pipeline.

[0036] In some embodiments, the aircraft control method further includes:

[0037] Step S30, wherein step S30 includes step S31 and step S32;

[0038] Step S31, based on the first isolation pipeline and the second isolation pipeline being in a closed state and the compression refrigeration circuit being in an open state, obtaining the fuel temperature detected by the temperature sensor at a preset frequency;

[0039] Step S32, based on the change of the fuel temperature within a preset detection period, adjusting the opening of the refrigeration regulating valve, the first isolation valve and the second isolation valve until the fuel temperature is between 100°C and 103°C.

[0040] In order to solve the problems of design redundancy and high energy consumption of the airborne hybrid refrigeration system, the present invention has the following advantages:

[0041] 1. The two refrigeration systems commonly used in traditional aircraft: the air circulation refrigeration system and the evaporative circulation liquid cooling system are integrated together. Compared with the independent electromechanical systems of the two, the structure is simplified, the weight of the motor and motor controller is saved, and the refrigeration efficiency of the onboard hybrid refrigeration system is improved.

[0042] 2. By connecting the evaporator in parallel with the first isolation pipeline and the first heat exchanger in parallel with the second isolation pipeline, and by controlling the on-off of the first isolation pipeline and the second isolation pipeline, mode switching and economic control between large refrigeration capacity, medium refrigeration capacity and small refrigeration capacity can be achieved, thereby improving the economy of system operation.

[0043] 3. Some embodiments design the first and second refrigeration drive modes: the first mode is to switch the starter motor to the electric motor mode, use the engine to extract electric power to drive the starter motor to rotate, and then drive the compressor and gas turbine to rotate; the second mode is to draw air from the atmosphere into the combustion chamber through the air intake part to independently burn and expand to drive, which can adapt to different working scenarios to achieve economic operation goals;

[0044] 4. Some embodiments also design a third and fourth refrigeration drive form: using the bleed air line to draw air from the engine compressor assembly and then drive the gas turbine to rotate after passing through the combustion chamber for combustion, or the gas in the bleed air line passes through the combustion chamber without combustion and flows directly to the gas turbine to drive the gas turbine to rotate. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] Figure 1 A schematic diagram of an onboard hybrid refrigeration system according to an embodiment is shown;

[0046] Figure 2 A schematic flow chart of an aircraft control method according to an embodiment is shown.

[0047] Figure numerals: 10 power assembly; 11 compressor; 12 air intake; 13 combustion chamber; 14 gas turbine; 20 motor assembly; 30 air circulation assembly; 31 cooling turbine; 32 first heat exchanger; 33 first water separator; 34 first valve; 35 second valve; 36 exhaust valve; 37 second condenser; 38 second water separator; 39 second heat exchanger; 40 evaporation cycle assembly; 41 compressor; 42 evaporator; 43 expansion valve; 44 first condenser; 45 refrigeration regulating valve; 50 fuel delivery assembly; 51 fuel pipeline; 52 temperature sensor; 60 liquid cooling cycle assembly; 61 liquid cooling pump; 62 heat load heat exchanger; 63 first isolation valve; 64 second isolation valve; 70 engine compressor assembly. DETAILED DESCRIPTION

[0048] 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, rather than implying any limitation on the scope of the present disclosure.

[0049] As used herein, the term "including" and its variants are to be interpreted as open-ended terms meaning "including but not limited to". The term "based on" is to be interpreted as "based at least in part 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 orientation or position relationship indicated by the terms "upper", "lower", "left", "right", "front", "back", "top", "bottom", "inner", "outer", "vertical", "horizontal", "lateral", "longitudinal" and the like is based on the orientation or position relationship shown in the accompanying drawings. These terms are mainly for better describing the present application and its embodiments, and are not used to limit the indicated devices, elements or components to have a specific orientation, or to be constructed and operated in a specific orientation. In addition, in addition to being used to indicate an orientation or position relationship, some of the above terms may also be used to indicate other meanings, such as the term "upper" may also be used to indicate a certain dependency or connection relationship in some cases. For those of ordinary skill in the art, the specific meanings of these terms in this application can be understood according to the specific circumstances. In addition, the terms "install", "set", "provided with", "connected" and "connected" should be understood in a broad sense. 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 directly connected, or indirectly connected through an intermediate medium, or it can be an internal connection between two devices, elements or components. For those of ordinary skill in the art, the specific meanings of the above terms in this application can be understood according to the specific circumstances. In addition, 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 and quantity of the indicated devices, elements or components. Unless otherwise specified, "plurality" means two or more.

[0050] The aviation electromechanical system of aircraft, such as airplanes and special operation drones, undertakes the functions of power supply, hydraulic actuation, environmental control and auxiliary / emergency power of the aircraft. It is like the "blood, muscles and five internal organs" of the aircraft, and plays a key role in airborne energy management, especially for special aircraft, which directly affects the flight safety and operational efficiency of the aircraft. Among the functions of the electromechanical system, the energy supply and heat dissipation capabilities of environmental control and auxiliary / emergency power directly affect the functional realization of the mission system.

[0051] The problems of "energy" and "heat" in special aircraft are particularly prominent. The main reason is that the ability of aircraft engines to extract shaft power for power generation is limited under high speed and operating conditions. When flying at high speed, the speed of aircraft engines will increase significantly. When extracting power from the engine shaft for power generation, the transmission device (such as the gearbox, etc.) will be subjected to huge mechanical stress, thus limiting the ability to stably extract shaft power for power generation; in order to meet operational requirements, special aircraft need to strictly control their own electromagnetic signals. The system for extracting shaft power from the engine for power generation will also generate certain electromagnetic radiation.

[0052] Due to the aerodynamic requirements during high-speed flight, the heat dissipation space and heat dissipation efficiency of the aircraft are affected; during high-speed flight, the pressure and temperature of the ram air will rise sharply. This will lead to two problems. First, excessive pressure may cause structural damage to the intake duct and radiator and other components of the cooling system. For example, the intake duct may rupture because it cannot withstand excessive pressure. Second, the high temperature of the ram air will greatly reduce the heat dissipation effect. Therefore, the technical approach of using ram air heat sinks to dissipate heat can no longer be used in special aircraft.

[0053] Under heavy mission loads, more equipment on special aircraft will be working at high loads, generating a lot of heat. The flow rate of fuel is limited, and the speed at which it absorbs and removes heat cannot keep up with the speed at which heat is generated. At the same time, the thermal capacity of the fuel itself is certain, which means that the amount of heat that can be absorbed by a unit mass of fuel is limited. When too much heat is generated, the fuel temperature will continue to rise. Using fuel to dissipate heat often makes it impossible for the aircraft to completely dissipate heat under heavy mission loads, which has a great impact on the reliability of the mission system.

[0054] Many functions of aircraft are undertaken by electromechanical systems. The energy supply is generally an engine-driven generator, and the heat dissipation is usually an air circulation system or an evaporative circulation liquid cooling system. These traditional electromechanical systems are independent of each other, and there is no interactive interface between the systems. They can only be designed according to the maximum capacity and run according to the load requirements. In the context of the extremely high peak-to-average power demand of aircraft, this often results in design redundancy, heavy system weight, and high comprehensive fuel consumption, which can no longer meet the new development requirements.

[0055] In this embodiment, an onboard hybrid refrigeration system is provided. Figure 1 As shown, the onboard hybrid refrigeration system includes a power assembly 10 , a motor assembly 20 , an air circulation assembly 30 , an evaporation circulation assembly 40 , a fuel delivery assembly 50 and a liquid cooling circulation assembly 60 .

[0056] The power assembly 10 includes a compressor 11, an air intake 12, a combustion chamber 13 and a gas turbine 14. The inlet of the air intake 12 is directly connected to the atmosphere, and the outlet of the air intake 12 is connected to the inlet of the compressor 11. The compressor 11, the combustion chamber 13 and the gas turbine 14 are detachably connected in sequence. The outlet of the compressor 11 is connected to the combustion chamber 13 to form a driving air path, and the compressor 11 is coaxially connected to the gas turbine 14. External air can enter the compressor 11 through the air intake 12, and the gas enters the combustion chamber 13 through the driving air path after being pressurized by the compressor 11. The gas in the combustion chamber 13 can drive the gas turbine 14 to operate after combustion and expansion.

[0057] The motor assembly 20 includes a starter-generator integrated motor, which is coaxially connected to the compressor 11. Through the motor assembly 20 and the power assembly 10, two driving modes of the refrigeration system can be realized, which are driven by the starter-generator integrated motor or driven by the power assembly 10 for air intake, combustion and expansion, so as to adapt to different working scenes and achieve the purpose of energy saving.

[0058] The air circulation component 30 includes a cooling turbine 31, a first heat exchanger 32 and a first water separator 33. The cooling turbine 31 is coaxially connected to the starter motor. The outlet of the compressor 11 is connected to the inlet of the cooling turbine 31 to form a first air supply path, and the gas discharged from the compressor 11 can enter the cooling turbine 31 for cooling. The first air supply path can also be provided with a first valve 34, and the amount of gas passing through the cooling turbine 31 can be adjusted by adjusting the opening of the first valve 34, thereby controlling the air supply capacity and refrigeration capacity of the system. The outlet of the cooling turbine 31 is connected to the inlet of the first heat exchanger 32 to form a refrigeration gas path, and the cooling gas passing through the first heat exchanger 32 can absorb the heat transferred by the first heat exchanger 32 to realize the air circulation cooling function. The outlet of the cooling turbine 31 is connected to the first water separator 33 to form a second air supply path, and the gas cooled by the cooling turbine 31 can separate water through the first water separator 33, and then the cooling gas is discharged into the gas-using components and the aircraft cabin to achieve the purpose of air supply. The first air supply path and the second air supply path jointly meet the air supply demand of the aircraft. The refrigeration air circuit is provided with a second valve 35. By controlling the opening and closing of the second valve 35, the mixed refrigeration system can be controlled to only supply air or to supply air and refrigerate at the same time. The outlet of the first heat exchanger 32 is connected to the atmosphere to form an exhaust path. An exhaust valve 36 is provided on the exhaust path. The outlet of the first heat exchanger 32 is connected to the inlet of the compressor 11 to form a return path. By controlling the opening and closing of the exhaust valve 36, the gas that absorbs the heat of the first heat exchanger 32 can be controlled to be discharged into the atmosphere or to flow back to the inlet of the compressor 11 to enter the power assembly 10.

[0059] The evaporation cycle assembly 40 includes a compressor 41, an evaporator 42, an expansion valve 43, and a first condenser 44. The compressor 41 is coaxially connected to the cooling turbine 31; the compressor 41, the evaporator 42, the expansion valve 43 and the first condenser 44 are connected end to end in sequence to form a compression refrigeration circuit. The compressor 41 can compress the coolant, and then it returns to the compressor 41 after absorbing heat through the evaporator 42, expanding through the expansion valve 43, and releasing heat through the condenser to form a closed cycle. The evaporation cycle assembly 40 can also include a refrigeration regulating valve 45, which is connected in parallel with the compressor 41 in the compression refrigeration circuit. The cooling efficiency of the compression refrigeration circuit can be controlled by controlling the opening of the refrigeration regulating valve 45. Among them, the compressor 41 is coaxially arranged with the gas turbine 14, and the traditional electric drive compressor 41 is changed to a shaft drive compressor 41 and integrated in the refrigeration circuit, which not only simplifies the structure and reduces the weight of the motor, making the high-power compression drive benefit obvious, but also reduces the energy loss of the two links of power generation and electric drive, and further improves the system operation efficiency.

[0060] The fuel delivery assembly 50 includes a fuel line 51 that passes through the condenser.

[0061] Liquid cooling circulation component 60, liquid cooling circulation component 60 includes liquid cooling pump 61, heat load heat exchanger 62, first isolation pipeline and second isolation pipeline. Liquid cooling pump 61, heat load heat exchanger 62, first isolation pipeline and second isolation pipeline are connected to form a liquid cooling circuit. Evaporator 42 and first isolation pipeline are connected in parallel in the liquid cooling circuit, and first heat exchanger 32 and second isolation pipeline are connected in parallel in the liquid cooling circuit. Liquid cooling pump 61 can drive the refrigerant to flow through heat load heat exchanger 62, evaporator 42, first heat exchanger 32 in sequence, and then return to liquid cooling pump 61 to form a closed cycle. Liquid cooling circulation component 60 also includes first isolation valve 63 and second isolation valve 64. The first isolation valve 63 is detachably connected to the first isolation pipeline, and the second isolation valve 64 is detachably connected to the second isolation pipeline. Therefore, by controlling the opening and closing of the first isolation valve 63, it is possible to control whether the liquid cooling circuit passes through the evaporator 42. By controlling the opening and closing of the second isolation valve 64, it is possible to control whether the liquid cooling circuit passes through the first heat exchanger 32. Alternatively, the first isolation valve 63 and the second isolation valve 64 are each adjusted in opening degree to control the distribution ratio of compression refrigeration and air circulation refrigeration.

[0062] The evaporation cycle component 40 and the air circulation component 30 are integrated in the onboard hybrid refrigeration system, which simplifies the structure and reduces the weight. In addition, by controlling the first isolation valve 63 and the second isolation valve 64, three refrigeration conditions can be achieved: air circulation refrigeration formed by only the refrigeration gas circuit, or compression refrigeration formed by only the compression refrigeration circuit, or compression refrigeration and air circulation refrigeration at the same time. Applying appropriate refrigeration solutions in different scenarios can avoid resource waste and improve the operating efficiency of the refrigeration system.

[0063] In this embodiment, if Figure 1 As shown, the fuel delivery assembly 50 may further include a temperature sensor 52. The temperature sensor 52 is detachably connected to the fuel pipeline 51, and the temperature sensor 52 can detect the fuel temperature in real time.

[0064] The refrigeration regulating valve 45 , the first isolation valve 63 , and the second isolation valve 64 can adjust the opening degree, and the temperature sensor 52 is electrically connected to the refrigeration regulating valve 45 , the first isolation valve 63 , and the second isolation valve 64 , respectively.

[0065] According to the detected fuel temperature, the first isolation valve 63, the second isolation valve 64 and the refrigeration regulating valve 45 can be opened to prevent the fuel temperature from being too high. When the refrigeration regulating valve 45 and the first isolation valve 63 are fully closed, the compression refrigeration efficiency can be maximized. If the fuel temperature is too high, it will affect the temperature of the fuel nozzle entering the engine. If the fuel temperature is too high, it is easy to coke and deposit, affecting the engine performance.

[0066] Through electrical connection, the first isolation valve 63, the second isolation valve 64 and the refrigeration regulating valve 45 can be opened and controlled according to the signal of the temperature sensor 52 to ensure that the fuel temperature is between 100 and 103° C. The effect of compression refrigeration can better meet the aerodynamic design requirements of the stealth performance of special aircraft than the refrigeration effect of air circulation refrigeration. Therefore, when the fuel temperature is controlled, the maximum output capacity of the compression refrigeration cycle can be guaranteed as much as possible, and then the opening of the second regulating valve can be controlled, and the air circulation system can be used to meet the remaining refrigeration needs.

[0067] In this embodiment, if Figure 1As shown, the air circulation component 30 may also include a second condenser 37 and a second water separator 38. The second condenser 37 has a first channel and a second channel isolated from each other, and heat exchange can be performed between the first channel and the second channel. The second water separator 38 is detachably connected to the second condenser 37. The second water separator 38 is used to separate the gas and liquid of the medium passing through the first channel and the second channel. The outlet of the compressor 11 is connected to the inlet of the cooling turbine 31 through the first channel, so that the high-temperature and high-pressure gas discharged from the compressor 11 can enter the cooling turbine 31 through the second condenser 37 and the second water separator 38, and then supply air to the air-using components and the aircraft cabin of the aircraft through the first water separator 33. The outlet of the first heat exchanger 32 is connected to the atmosphere through the second channel, and the outlet of the first heat exchanger 32 is connected to the inlet of the compressor 11 through the second channel. After the gas that absorbs the heat of the first heat exchanger 32 is discharged, it can be discharged to the atmosphere through the second channel or reflux to the inlet of the compressor 11 to enter the power component 10. The gas in the first channel and the second channel of the second condenser 37 perform heat exchange. Since the gas temperature in the second channel is relatively low, the gas in the first channel can be condensed, thereby utilizing the residual cold capacity of the gas flowing through the first channel and reducing the refrigeration requirements of the cooling turbine 31. The second water separator 38 separates liquid from the two gas paths respectively, thereby ensuring the dryness of the gas.

[0068] In this embodiment, if Figure 1 As shown, the air circulation component 30 also includes a second heat exchanger 39. The second heat exchanger 39 has a third channel and a fourth channel isolated from each other, and the third channel and the fourth channel can perform heat exchange. The outlet of the compressor 11 is connected to the first channel through the third channel, so that the gas discharged from the compressor 11 can enter the second heat exchanger 39 through the third channel, release a part of the heat, then enter the first channel to release a part of the heat, and finally enter the cooling turbine 31 to reduce the refrigeration work of the cooling turbine 31, and finally discharge the cooling gas to the gas-using original and the aircraft cabin. The outlet of the first heat exchanger 32 is connected to the atmosphere through the second channel and the fourth channel in turn, and the outlet of the first heat exchanger 32 is connected to the inlet of the compressor 11 through the second channel and the fourth channel in turn. After the gas in the refrigeration gas path absorbs the heat of the first heat exchanger 32, it can be discharged to the atmosphere or reflux to the inlet of the compressor 11 to enter the power component 10. In the process of discharging or reflux of the cooling gas, two preliminary heat dissipations of the first air supply path are achieved, thereby improving the refrigeration efficiency of the refrigeration system.

[0069] In other embodiments, the airborne hybrid refrigeration system also includes a heat dissipation channel, which is a channel on the aircraft shell for heat exchange with the atmosphere. The outlet of the compressor 11 is connected to the third channel through the heat dissipation channel, so that the first air supply path first exchanges heat with the atmosphere to achieve initial cooling, and then the cooled gas is refluxed for two times for cooling, thereby fully ensuring the initial cooling efficiency of the first air supply path and reducing the refrigeration work of the cooling turbine 31.

[0070] In this embodiment, if Figure 1 As shown, the onboard hybrid refrigeration system includes an engine air compressor assembly 70. The engine air compressor assembly 70 can provide sufficient gas for the engine in the thin air environment at high altitudes.

[0071] The power assembly 10 further includes an air bleed line. The inlet of the air bleed line is detachably connected to the engine air compressor assembly 70, and the outlet of the air bleed line is communicated with the combustion chamber 13. An air bleed valve is provided on the air bleed line.

[0072] When the aircraft is in the sky, the atmosphere is relatively thin, and the air entering the combustion chamber 13 through the air intake 12 is less and consumes more energy, which is not enough to support the operation of the gas turbine 14. At this time, the bleed valve can be opened, and the engine compressor assembly 70 can introduce the gas attracted by the engine during operation into the combustion chamber 13 through the bleed pipeline, and burn it through the combustion chamber 13 or blow it directly to the gas turbine 14 without burning it through the combustion chamber 13, thereby driving the gas turbine 14 to operate. When the aircraft is on the ground, the bleed valve can be closed. In addition, when flying at high altitude, the engine can also be used to extract electric power to do work and drive the starter-integrated motor to rotate. At this time, the starter-integrated motor is an electric motor, and the starter-integrated motor is used to drive the gas turbine 14 to operate, thereby realizing power compensation for driving the gas turbine 14. Thus, the present invention realizes four driving modes of the airborne hybrid refrigeration system: engine extraction electric power drive, engine bleed combustion drive, engine bleed direct drive, and autonomous air intake combustion expansion work from the atmosphere. Selecting a suitable driving mode according to different working scenarios can achieve the goal of economic operation.

[0073] In this embodiment, the power assembly 10 may also include an air supply pipeline. The inlet of the air supply pipeline is detachably connected to the engine compressor assembly 70, the outlet of the air supply pipeline is connected to the return path, and an air supply valve is provided on the air supply pipeline. Therefore, when the aircraft is flying at high altitude, opening the air supply valve can allow the engine compressor assembly 70 to replenish the gas sucked in when the engine is running into the return path through the air supply pipeline. Through the confluence of the return path and the air supply pipeline, the cooling gas in the return path can be used to cool down the high-temperature engine bleed air in the air supply pipeline, thereby avoiding the excessively high temperature of the gas entering the compressor 11 and damaging the compressor 11.

[0074] In this embodiment, an aircraft is provided, the aircraft includes any of the airborne hybrid refrigeration systems in the above embodiments, and the aircraft also includes a rack system. The airborne hybrid refrigeration system is detachably connected to the rack system, and the cooling gas discharged from the airborne hybrid refrigeration system can flow into the rack system, and the airborne hybrid refrigeration system can also dissipate heat for the rack system. The aircraft can be an airplane, a drone for special operations, etc., especially a special aircraft that performs complex and diverse tasks, which can realize reasonable adjustment of multi-speed refrigeration and air supply, reduce energy waste, and ensure special function design.

[0075] In this embodiment, a method for controlling an aircraft is provided. The method for controlling an aircraft is applied to the aircraft in the above embodiment. Figure 2 As shown, the aircraft control method may include step S10, which is described in detail as follows:

[0076] Step S10: Step S10 may include steps S11 to S16.

[0077] Step S11: Based on the fact that the engine of the aircraft is in a shut-down state, a first working instruction of the aircraft is obtained.

[0078] Step S12, based on the first working instruction including air supply and refrigeration, the air intake 12 and the driving air path can be opened until the speed of the gas turbine 14 reaches the first preset speed. The first preset speed can be 95% of the rated speed, and the power system at this time has the ability to integrate air supply and refrigeration. Among them, the gas sucked by the air intake 12 can enter the driving air path through the compressor 11, and enter the combustion chamber 13 from the outlet of the compressor 11, and the combustion and expansion gas can drive the gas turbine 14 to rotate.

[0079] Step S13, based on the rotation speed of the gas turbine 14 reaching the first preset rotation speed, the cooling gear in the first working instruction is obtained.

[0080] Step S14, based on the refrigeration gear in the first working instruction being the first gear, open the first air supply path, the second air supply path, the refrigeration gas path, the exhaust path and the liquid cooling circuit, open the first isolation pipeline and close the second isolation pipeline.

[0081] The gas discharged from the compressor 11 can be supplied to the aircraft cabin and gas-using components through the first gas supply path and the second gas supply path. At the same time, the second isolation valve 64 is disconnected, and the liquid cooling circuit passes through the first heat exchanger 32. Part of the gas can absorb the heat transferred by the first heat exchanger 32 through the refrigeration gas path to achieve air circulation cooling, and finally be discharged to the atmosphere through the exhaust path. The first gear refrigeration can meet the refrigeration demand when the aircraft heat load is 0-10% of the maximum heat load.

[0082] Step S15, based on the refrigeration gear in the first working instruction being the second gear, the first air supply path, the second air supply path, the compression refrigeration circuit and the liquid cooling circuit are opened, the first isolation pipeline is closed and the second isolation pipeline is opened.

[0083] The gas discharged from the compressor 11 can be supplied to the aircraft cabin and gas-using components through the first gas supply path and the second gas supply path. At the same time, the first isolation valve 63 is disconnected, the liquid cooling circuit passes through the evaporator 42, the compression refrigeration circuit is connected, and the compressor 41 can compress the coolant, and then it returns to the compressor 41 after absorbing heat through the evaporator 42, expanding through the expansion valve 43, and releasing heat through the condenser to form a closed cycle. The second gear is enough to meet the refrigeration demand when the aircraft heat load is 10%-40% of the maximum heat load.

[0084] Step S16, based on the refrigeration gear in the first working instruction being the third gear, open the first air supply path, the second air supply path, the refrigeration gas path, the exhaust path, the compression refrigeration circuit and the liquid cooling circuit, close the first isolation pipeline and the second isolation pipeline, the liquid cooling circuit passes through the first heat exchanger 32 and the evaporator 42, and the liquid cooling circulation circuit, the refrigeration gas path and the compression refrigeration circuit are all connected.

[0085] The gas discharged from the compressor 11 can be supplied to the aircraft cabin and gas-using components through the first gas supply path and the second gas supply path. At the same time, part of the gas can absorb the energy transferred by the first heat exchange through the refrigeration gas path to achieve air circulation cooling, and finally be discharged to the atmosphere through the exhaust path. At the same time, in the compression refrigeration circuit, the compressor 41 can compress the coolant, and then it returns to the compressor 41 after absorbing heat through the evaporator 42, expanding through the expansion valve 43, and releasing heat through the condenser to form a closed cycle. The third gear can meet the refrigeration demand when the aircraft heat load is 40%-60% of the maximum heat load.

[0086] In this embodiment, the aircraft control method further includes step S20, which is described in detail as follows:

[0087] Step S20, step S20 includes steps S21 to S26.

[0088] Step S21, based on the fact that the engine of the aircraft is in an on state, obtaining a second working instruction of the aircraft.

[0089] Step S22, based on the second working instruction including air supply and cooling, the bleed air pipeline is opened until the speed of the gas turbine 14 reaches the second preset speed. The bleed air valve is opened, and the engine air compressor assembly 70 can introduce the gas sucked when the engine is running into the combustion chamber 13 through the bleed air pipeline, thereby driving the gas turbine 14 to operate. The gas can be burned through the combustion chamber 13, or it can be blown directly to the gas turbine 14 through the combustion chamber 13 without burning.

[0090] Step S23, based on the rotation speed of the gas turbine 14 reaching the second preset rotation speed, the cooling gear in the second working instruction is obtained. The second preset rotation speed may be 85% of the rated working rotation speed. Under high altitude conditions, the turbine speed reaches 75% of the rated rotation speed before it has the ability to supply air, and the turbine speed reaches 85% of the rated rotation speed before it has the ability to supply air and refrigerate in one.

[0091] Step S24, based on the refrigeration gear in the second working instruction being the first gear, open the air supply pipeline, the first air supply path, the second air supply path, the refrigeration gas path, the refrigeration path and the liquid cooling circuit, open the first isolation pipeline and close the second isolation pipeline.

[0092] Among them, when the air supply valve is opened, the engine air compressor assembly 70 can supply the gas sucked in when the engine is running into the return path through the air supply pipeline, and then flow into the inlet of the compressor 11 through the fourth channel. The gas discharged from the compressor 11 can be supplied to the aircraft cabin and gas-using components through the first air supply path and the second air supply path. At the same time, the second isolation valve 64 is disconnected, and the liquid cooling circuit passes through the first heat exchanger 32. Part of the gas can absorb the heat transferred by the first heat exchanger 32 through the refrigeration gas path to achieve air circulation cooling, and finally return to the compressor 11 through the return path to participate in the circulation. In the confluence of the return path and the air supply pipeline, the cooling gas in the return path can cool down the high-temperature engine bleed air in the air supply pipeline to avoid the air temperature entering the compressor 11 being too high to damage the compressor 11. The first gear can meet the refrigeration demand when the aircraft heat load is 0-10% of the maximum heat load.

[0093] Step S25, based on the refrigeration gear in the second working instruction being the second gear, open the air supply pipeline, the first air supply path, the second air supply path, the compression refrigeration circuit and the liquid cooling circuit, close the first isolation pipeline and open the second isolation pipeline.

[0094] Among them, when the air supply valve is opened, the engine air compressor assembly 70 can replenish the gas sucked in when the engine is running into the return path through the air supply pipeline, and then flow into the inlet of the compressor 11 through the fourth channel. The gas discharged from the compressor 11 can supply air to the aircraft cabin and gas-using components through the first air supply path and the second air supply path. At the same time, the first isolation valve 63 is disconnected, the liquid cooling circuit passes through the evaporator 42, the compression refrigeration circuit is connected, the compressor 41 can compress the coolant, and then it returns to the compressor 41 after absorbing heat through the evaporator 42, expanding through the expansion valve 43, and releasing heat through the condenser to form a closed cycle. The second gear can meet the refrigeration demand when the aircraft heat load is 10%-60% of the maximum heat load.

[0095] Step S26, based on the refrigeration gear in the second working instruction being the third gear, open the air supply pipeline, the first air supply path, the second air supply path, the refrigeration gas path, the return path, the compression refrigeration circuit and the liquid cooling circuit, and close the first isolation pipeline and the second isolation pipeline.

[0096] Among them, when the air supply valve is opened, the engine air compressor assembly 70 can replenish the gas sucked in when the engine is running into the return path through the air supply pipeline, and then flow into the inlet of the compressor 11 through the fourth channel. The gas discharged by the compressor 11 can supply air to the aircraft cabin and gas-using components through the first air supply path and the second air supply path. At the same time, the second isolation valve 64 is disconnected, the liquid cooling circuit passes through the first heat exchanger 32, and part of the gas can absorb the heat transferred by the first heat exchanger 32 through the refrigeration gas path to achieve air circulation cooling, and finally return to the compressor 11 through the return path to participate in the circulation. The first isolation valve 63 is disconnected, the liquid cooling circuit passes through the evaporator 42, the compression refrigeration circuit is connected, the compressor 41 can compress the coolant, and then it returns to the compressor 41 after absorbing heat through the evaporator 42, expanding through the expansion valve 43, and releasing heat through the condenser to form a closed cycle. In the confluence of the return path and the air supply line, the cooling gas in the return path can cool down the high-temperature engine bleed air in the air supply line to prevent the air temperature entering the compressor 11 from being too high and damaging the compressor 11. The third gear can meet the refrigeration demand when the aircraft heat load is 60%-100% of the maximum heat load.

[0097] In this embodiment, the aircraft control method further includes step S30, which is described in detail as follows:

[0098] Step S30: Step S30 includes step S31 and step S32.

[0099] Step S31, based on the first isolation pipeline and the second isolation pipeline being in a closed state and the compression refrigeration circuit being in an open state, the fuel temperature detected by the temperature sensor 52 is obtained at a preset frequency.

[0100] Step S32, based on the change of the fuel temperature within the preset detection period, adjust the opening of the refrigeration regulating valve 45, the first isolation valve 63 and the second isolation valve 64 until the fuel temperature is between 100°C and 103°C.

[0101] When the refrigeration regulating valve 45 and the first isolation valve 63 are fully closed, the compression refrigeration efficiency can be maximized, and the fuel temperature will also increase. At this time, according to the detected fuel temperature, the opening of the first isolation valve 63, the second isolation valve 64 and the refrigeration regulating valve 45 can be controlled to keep the fuel temperature between 100 and 103°C. If the fuel temperature is too high, it will affect the temperature of the fuel nozzle entering the engine, which will cause coking and carbon deposition, affecting the engine performance. When the fuel temperature is controlled, the maximum output capacity of the compression refrigeration cycle can be guaranteed as much as possible, and then the opening of the second regulating valve can be controlled, and the air circulation system can be used to meet the remaining refrigeration needs.

[0102] In addition, during the function execution of the hybrid refrigeration system, the exhaust temperature sensor 52 at the rear end of the gas turbine 14 can collect the exhaust temperature. When the flight altitude of the aircraft is within 0-11km, if the detected exhaust temperature is greater than 650℃, the starter-integrated motor can be controlled to be connected in an electric state, and the power of the motor is adjusted according to the signal transmitted by the speed sensor. At the same time, the flow rate of the fuel pump and the opening of the air induction valve are controlled to compensate for the speed, thereby preventing the system from overheating and damaging the power turbine. When the flight altitude of the aircraft is above 11km, the starter-integrated motor can be directly controlled to drive at maximum power (60kW), and the fuel pump flow control and the air induction valve opening control are also feedback controlled by the speed sensor. These two control modes can determine whether the maximum input capacity is from the engine air induction or the engine's electricity, which can not only ensure the economy of the aircraft operation, but also ensure the safety and stability of the system operation.

[0103] Those skilled in the art will appreciate that the above-mentioned embodiments are specific examples for implementing the present disclosure, and in actual applications, various changes may be made thereto in form and detail without departing from the scope of the present disclosure.

Claims

1. An airborne hybrid refrigeration system, characterized in that: The onboard hybrid refrigeration system comprises: A power assembly, the power assembly comprising a compressor, an air intake, a combustion chamber and a gas turbine; the inlet of the air intake is connected to the atmosphere; the outlet of the air intake is connected to the inlet of the compressor; the compressor, the combustion chamber and the gas turbine are detachably connected in sequence; the outlet of the compressor is connected to the combustion chamber to form a driving air path; the compressor is coaxially connected to the gas turbine; A motor assembly, the motor assembly comprising a starter-generator integrated motor; the starter-generator integrated motor is coaxially connected to the compressor; An air circulation component, the air circulation component includes a cooling turbine, a first heat exchanger and a first water separator; the cooling turbine is coaxially connected to the starting-integrated motor; the outlet of the compressor is connected to the inlet of the cooling turbine to form a first air supply path; the first air supply path is provided with a first valve; the outlet of the cooling turbine is connected to the inlet of the first heat exchanger to form a refrigeration air path; the outlet of the cooling turbine is connected to the first water separator to form a second air supply path; the refrigeration air path is provided with a second valve; the outlet of the first heat exchanger is connected to the atmosphere to form an exhaust path; the exhaust path is provided with an exhaust valve; the outlet of the first heat exchanger is connected to the inlet of the compressor to form a return path; An evaporation cycle assembly, the evaporation cycle assembly includes a compressor, an evaporator, an expansion valve, and a first condenser; the compressor is coaxially connected to the cooling turbine; the compressor, the evaporator, the expansion valve and the first condenser are connected end to end in sequence to form a compression refrigeration circuit; the evaporation cycle assembly also includes a refrigeration regulating valve; the refrigeration regulating valve and the compressor are connected in parallel in the compression refrigeration circuit; a fuel delivery assembly, the fuel delivery assembly includes a fuel pipeline; the fuel pipeline passes through the first condenser; A liquid cooling circulation component, the liquid cooling circulation component includes a liquid cooling pump, a heat load heat exchanger, a first isolation pipeline and a second isolation pipeline; the liquid cooling pump, the heat load heat exchanger, the first isolation pipeline and the second isolation pipeline are connected to form a liquid cooling circuit; the evaporator and the first isolation pipeline are connected in parallel in the liquid cooling circuit; the first heat exchanger and the second isolation pipeline are connected in parallel in the liquid cooling circuit; the liquid cooling circulation component also includes a first isolation valve and a second isolation valve; the first isolation valve is detachably connected to the first isolation pipeline; the second isolation valve is detachably connected to the second isolation pipeline.

2. The onboard hybrid refrigeration system according to claim 1, characterized in that: The fuel delivery assembly further comprises a temperature sensor, which is detachably connected to the fuel pipeline; the temperature sensor detects the fuel temperature; The refrigeration regulating valve, the first isolation valve and the second isolation valve can adjust the opening degree; the temperature sensor is electrically connected to the refrigeration regulating valve, the first isolation valve and the second isolation valve respectively.

3. The onboard hybrid refrigeration system according to claim 1, characterized in that: The air circulation component also includes a second condenser and a second water separator; the second condenser has a first channel and a second channel isolated from each other; heat exchange can be performed between the first channel and the second channel; the second water separator is detachably connected to the second condenser; the second water separator is used to separate gas and liquid from the medium passing through the first channel and the second channel; the outlet of the compressor is connected to the inlet of the cooling turbine through the first channel; the outlet of the first heat exchanger is connected to the atmosphere through the second channel; the outlet of the first heat exchanger is connected to the inlet of the compressor through the second channel.

4. The onboard hybrid refrigeration system according to claim 3, characterized in that: The air circulation component also includes a second heat exchanger; the second heat exchanger has a third channel and a fourth channel isolated from each other; the third channel and the fourth channel can perform heat exchange; the outlet of the compressor is connected to the first channel through the third channel; the outlet of the first heat exchanger is connected to the atmosphere through the second channel and the fourth channel in turn; the outlet of the first heat exchanger is connected to the inlet of the compressor through the second channel and the fourth channel in turn.

5. The onboard hybrid refrigeration system according to claim 1, characterized in that: The onboard hybrid refrigeration system includes an engine air compressor assembly; The power assembly also includes an air bleed pipeline; the inlet of the air bleed pipeline is detachably connected to the engine compressor assembly; the outlet of the air bleed pipeline is communicated with the combustion chamber; and an air bleed valve is arranged on the air bleed pipeline.

6. The onboard hybrid refrigeration system according to claim 5, characterized in that: The power assembly also includes an air supply pipeline; the inlet of the air supply pipeline is detachably connected to the engine air compressor assembly; the outlet of the air supply pipeline is connected to the return path; and an air supply valve is arranged on the air supply pipeline.

7. An aircraft, characterized in that: The aircraft comprises: Rack systems; The airborne hybrid refrigeration system according to any one of claims 1 to 6; the airborne hybrid refrigeration system is detachably connected to the rack system.

8. An aircraft control method, applied to the aircraft according to claim 7, characterized in that: The aircraft control method comprises: Step S10, wherein step S10 includes steps S11 to S16; Step S11, based on the fact that the engine of the aircraft is in a shut-down state, obtaining a first working instruction of the aircraft; Step S12, based on the first working instruction including air supply and cooling, opening the air intake part and the driving air path; until the speed of the gas turbine reaches a first preset speed; Step S13, based on the rotation speed of the gas turbine reaching the first preset rotation speed, obtaining a cooling gear in the first working instruction; Step S14, based on the refrigeration gear in the first working instruction being the first gear, opening the first air supply path, the second air supply path, the refrigeration gas path, the exhaust path and the liquid cooling circuit, opening the first isolation pipeline and closing the second isolation pipeline; Step S15, based on the refrigeration gear in the first working instruction being the second gear, opening the first air supply path, the second air supply path, the compression refrigeration circuit and the liquid cooling circuit, closing the first isolation pipeline and opening the second isolation pipeline; Step S16, based on the refrigeration gear in the first working instruction being the third gear, open the first air supply path, the second air supply path, the refrigeration gas path, the exhaust path, the compression refrigeration circuit and the liquid cooling circuit, and close the first isolation pipeline and the second isolation pipeline.

9. The aircraft control method according to claim 8, characterized in that: The aircraft control method further comprises: Step S20, wherein step S20 includes steps S21 to S26; Step S21, based on the engine of the aircraft being in an on state, obtaining a second working instruction of the aircraft; Step S22, based on the second working instruction including air supply and refrigeration, open the bleed air pipeline; until the speed of the gas turbine reaches a second preset speed; wherein the onboard hybrid refrigeration system includes an engine air compressor assembly; the power assembly also includes a bleed air pipeline; the inlet of the bleed air pipeline is detachably connected to the engine air compressor assembly; the outlet of the bleed air pipeline is communicated with the combustion chamber; and an bleed air valve is provided on the bleed air pipeline; Step S23, based on the rotation speed of the gas turbine reaching the second preset rotation speed, obtaining the cooling gear in the second working instruction; Step S24, based on the cooling gear in the second working instruction being the first gear, opening the air supply pipeline, the first air supply path, the second air supply path, the cooling air path, the return path and the liquid cooling circuit, opening the first isolation pipeline and closing the second isolation pipeline; wherein the power assembly further comprises an air supply pipeline; the inlet of the air supply pipeline is detachably connected to the engine air compressor assembly; the outlet of the air supply pipeline is connected to the return path; and an air supply valve is provided on the air supply pipeline; Step S25, based on the refrigeration gear in the second working instruction being the second gear, opening the air supply pipeline, the first air supply path, the second air supply path, the compression refrigeration circuit and the liquid cooling circuit, closing the first isolation pipeline and opening the second isolation pipeline; Step S26, based on the refrigeration gear in the second working instruction being the third gear, open the air supply pipeline, the first air supply path, the second air supply path, the refrigeration gas circuit, the return path, the compression refrigeration circuit and the liquid cooling circuit, and close the first isolation pipeline and the second isolation pipeline.

10. The aircraft control method according to claim 9, characterized in that: The aircraft control method further comprises: Step S30, wherein step S30 includes step S31 and step S32; Step S31, based on the first isolation pipeline and the second isolation pipeline being in a closed state and the compression refrigeration circuit being in an open state, obtaining the fuel temperature detected by the temperature sensor at a preset frequency; Step S32, based on the change of the fuel temperature within a preset detection period, adjusting the opening of the refrigeration regulating valve, the first isolation valve and the second isolation valve until the fuel temperature is between 100°C and 103°C.

Images