Control system of airplane auxiliary cooling system and airplane auxiliary cooling system

Abstract

The invention provides a control system of an airplane auxiliary cooling system and the airplane auxiliary cooling system.The airplane auxiliary cooling control system comprises a comprehensive modular avionics system and more than one control unit, comprising at least one of a central refrigeration unit control unit, an electronic equipment cooling unit control unit, a liquid distribution unit control unit and a kitchen cooling unit control unit. The comprehensive modular avionics system is used for judging the current aircraft operation state of the aircraft and sending corresponding target instructions to the more than one control unit according to the current aircraft operation state of the aircraft and the operation state of each electronic device needing to be cooled; and the more than one control unit is used for receiving a target instruction sent by the integrated modular avionics system, executing corresponding operation according to the target instruction and feeding back to the integrated modular avionics system. According to the scheme provided by the invention, the control of the aircraft auxiliary cooling system can be realized.

Description

Technical Field

[0001] The present invention relates to the field of control, and in particular to a control system of an aircraft auxiliary cooling system and an aircraft auxiliary cooling system. Background Art

[0002] A large amount of heat will be released during the operation of the aircraft. To ensure its normal operation, an auxiliary cooling system is required to cool the terminal heat loads such as the kitchen dining cart and large electronic equipment. The commonly used auxiliary cooling system uses indirect cooling to generate cold air from the evaporative refrigeration unit, and the refrigerant carries the cold air to the front and rear cabin terminal equipment. Since the aircraft auxiliary cooling system has many components, it often includes multiple central refrigeration units (CRU), liquid distribution units (LDU), kitchen cooling units (GACU), electronic equipment cooling units (ECU), power drive units (PE), IMA (resident application software) and other accessories. It is usually required that each device be dynamically adjusted according to the target instructions to meet the cooling and temperature requirements. The aircraft auxiliary cooling system in the related technology has poor fault tolerance and ease of maintenance during operation. Summary of the invention

[0003] The main purpose of the present invention is to overcome the defects of the above-mentioned related technologies and provide a control system of an aircraft auxiliary cooling system and an aircraft auxiliary cooling system to solve the problems of poor fault tolerance and ease of maintenance of the aircraft auxiliary cooling system during operation in the related technologies.

[0004] On one hand, the present invention provides a control system for an aircraft auxiliary cooling system, which is used to control the aircraft auxiliary cooling system. The aircraft auxiliary cooling system includes a plurality of subsystem units, and the plurality of subsystem units include: at least one central refrigeration unit CRU, at least one liquid distribution unit LDU, at least one kitchen cooling unit GACU, at least one electronic equipment cooling unit ECU and at least one power drive device PE; the aircraft auxiliary cooling control system includes: an integrated modular avionics system IMA and one or more control units, and the one or more control units include: at least one of a central refrigeration unit control unit, an electronic equipment cooling unit control unit, a liquid distribution unit control unit and a kitchen cooling unit control unit; the central control The cooling unit control unit, the electronic equipment cooling unit control unit, the liquid distribution unit control unit and the kitchen cooling unit control unit are respectively used to control the central cooling unit, the electronic equipment cooling unit, the liquid distribution unit and the kitchen cooling unit; the integrated modular avionics system IMA is used to determine the current aircraft operating status of the aircraft, and issue corresponding target instructions to the at least one control unit according to the current aircraft operating status of the aircraft and the operating status of each electronic equipment that needs to be cooled; the one or more control units are used to receive the target instructions issued by the integrated modular avionics system IMA, perform corresponding operations according to the received target instructions, and provide feedback to the integrated modular avionics system IMA.

[0005] Optionally, the integrated modular avionics system IMA sends corresponding instructions to each control unit, including at least one of the following: sending a refrigerant target outlet temperature instruction to the central refrigeration unit control unit; sending a target liquid supply pressure instruction to the liquid distribution unit control unit; sending a target return air temperature instruction to the kitchen cooling unit control unit; sending a target temperature instruction to the electronic equipment cooling unit control unit.

[0006] Optionally, the at least one control unit receives a target instruction issued by the integrated modular avionics system IMA, performs corresponding operations according to the received target instruction, and feeds back to the integrated modular avionics system IMA, including: after receiving the target return air temperature instruction, the kitchen cooling unit control unit opens the flow valve and the fan and feeds back a flow valve opening signal to the integrated modular avionics system IMA; after receiving the target temperature instruction, the electronic equipment cooling unit control unit opens the flow valve and feeds back a flow valve opening signal to the integrated modular avionics system IMA; after receiving the target liquid supply pressure instruction, the liquid distribution unit control unit starts the coolant pump, performs PI adjustment on the frequency of the coolant pump according to the difference between the actual liquid supply pressure and the target liquid supply pressure, and feeds back a coolant pump in place instruction to the integrated modular avionics system IMA;

[0007] After receiving the refrigerant target outlet temperature instruction, the central refrigeration unit control unit starts the compressor, performs PI adjustment on the compressor frequency according to the difference between the refrigerant target outlet temperature and the refrigerant actual outlet temperature, and feeds back the CRU in place instruction to the integrated modular avionics system IMA.

[0008] Optionally, the integrated modular avionics system IMA first sends a target return air temperature instruction to the kitchen cooling unit control unit and a target water inlet temperature instruction to the electronic equipment cooling unit control unit, and after receiving the flow valve in place signal fed back by the kitchen cooling unit control unit and the electronic equipment cooling unit control unit, sends a target liquid supply pressure instruction to the liquid distribution unit control unit, and after receiving the refrigerant pump in place signal fed back by the liquid distribution unit control unit, sends a refrigerant target outlet temperature instruction to the central refrigeration unit control unit.

[0009] Optionally, the integrated modular avionics system IMA includes: a periodic execution mode, periodically judging the current aircraft operating status of the aircraft, and issuing corresponding target instructions to the at least one control unit according to the current aircraft operating status of the aircraft and the operating status of each electronic equipment that needs to be cooled.

[0010] Optionally, the integrated modular avionics system IMA is also used to: perform fault diagnosis and processing of each subsystem unit of the aircraft auxiliary cooling system; if it is determined that any component of the central refrigeration unit CRU, electronic equipment cooling unit ECU, liquid distribution unit LDU and kitchen cooling unit GACU is faulty, perform fault processing.

[0011] Optionally, the control logic of the central refrigeration unit control unit includes: if a refrigerant target outlet temperature instruction is received, the compressor is controlled to start and operate according to a preset frequency of the compressor, and after the operation is normal and stable, the normal operation control mode is entered, and the compressor frequency and the electronic expansion valve opening are dynamically adjusted by PI according to the refrigerant target outlet temperature instruction and the actual refrigerant outlet temperature fed back by the refrigerant outlet temperature sensor.

[0012] Optionally, the control logic of the central refrigeration unit control unit also includes: determining the oil return condition, if the oil return condition is met, entering the oil return operation mode, and returning to the normal operation mode after the oil return is completed; if the oil return condition is not met, determining the protection condition, if the protection condition is met, performing protection operation, otherwise returning to the normal operation mode; if a protection abnormality occurs during the protection operation, entering the standby control mode.

[0013] Optionally, the control logic of the liquid distribution unit control unit includes: if a target liquid supply pressure instruction is received, controlling the refrigerant pump to start and operate according to a preset frequency of the refrigerant pump, and after the operation is normal and stable, entering the normal operation control mode, and performing PI dynamic adjustment on the refrigerant pump frequency according to the target liquid supply pressure instruction and the pressure value fed back by the refrigerant pump outlet pressure sensor and / or inlet pressure sensor.

[0014] Optionally, the control logic of the liquid distribution unit control unit also includes: before controlling the refrigerant pump to start and run at the preset frequency of the refrigerant pump, determining whether the LDU control unit on the other side is faulty; if it is determined that the LDU control unit on the other side is faulty, then controlling the LDU on the other side and then performing rotation and status checks on the pump group on that side; if it is determined that the LDU control unit on the other side is not faulty, then directly performing rotation and status checks on the pump group on that side, and then entering the startup control mode, controlling the refrigerant pump to start and run at the preset frequency of the refrigerant pump; and / or, the control logic of the liquid distribution unit control unit also includes: after performing PI dynamic adjustment on the refrigerant pump frequency according to the target liquid supply pressure instruction and the pressure values ​​fed back by the refrigerant outlet pressure sensor and / or the inlet pressure sensor, determining whether the protection conditions are met; if the protection conditions are met, performing protection operation; otherwise, returning to the normal operation mode; if a protection abnormality occurs, entering the standby control mode.

[0015] Optionally, the control logic of the kitchen cooling unit control unit includes: if a target return air temperature instruction is received, the fan frequency is controlled according to the number of dining carts and environmental requirements, the flow valve is opened to the maximum value, and a flow valve in place signal is fed back to the integrated modular avionics system IMA, and then normal operation control is entered, and the flow valve opening is dynamically adjusted by PI according to the target return air temperature and the actual return air temperature fed back by the return air temperature sensor.

[0016] Optionally, the control logic of the kitchen cooling unit control unit also includes: after PI dynamic adjustment of the flow valve opening according to the target return air temperature and the feedback result of the measuring element, abnormality judgment is performed. If it is judged to be abnormal, abnormality processing is performed, otherwise, returning to the normal operation control mode.

[0017] Optionally, the control logic of the electronic equipment cooling unit control unit includes: if a target temperature instruction is received, the flow valve is opened to the maximum value, and a flow valve in place signal is fed back to the integrated modular avionics system IMA, and then normal operation control is entered, and the flow valve opening is dynamically adjusted by PI according to the target return air temperature and the actual return air temperature fed back by the return air temperature sensor.

[0018] Optionally, the control logic of the electronic equipment cooling unit control unit also includes: after performing PI dynamic adjustment on the flow valve opening according to the target return air temperature and the actual return air temperature fed back by the return air temperature sensor, performing abnormality judgment, if it is judged to be abnormal, performing abnormal processing, otherwise, returning to the normal operation control mode.

[0019] Optionally, the aircraft auxiliary cooling system further includes: a communication unit; the integrated modular avionics system IMA communicates with the liquid distribution unit control unit and / or the galley cooling unit control unit via the communication unit.

[0020] Another aspect of the present invention provides an aircraft auxiliary cooling system, comprising any of the control systems described above.

[0021] According to the technical solution of the present invention, the integrated modular avionics system IMA determines the current aircraft operating state of the aircraft, and sends corresponding target instructions to the at least one control unit according to the current aircraft operating state of the aircraft and the operating state of each electronic device that needs to be cooled; the one or more control units receive the target instructions sent by the integrated modular avionics system IMA, perform corresponding operations according to the received target instructions, and feedback to the integrated modular avionics system IMA, so as to realize the control of the aircraft auxiliary cooling system. Each sub-component control unit can be dynamically adjusted according to the target instructions to realize the cooling requirements of the kitchen dining cart and large electronic equipment under different stages and working conditions.

[0022] According to the technical solution of the present invention, the status information of each subsystem unit can be monitored periodically and fault handling can be performed. The periodic execution operation program should include the LDU control program, CRU control program, ECU control program, GACU control program, and alarm program. The aircraft auxiliary cooling control system can realize full automatic control to meet the cooling needs of the kitchen dining car and large electronic equipment under different stages and working conditions.

[0023] According to the technical solution of the present invention, the IMA resident software of the aircraft auxiliary cooling system of the integrated modular avionics system includes "periodic execution operation mode", "ground maintenance mode" and "software maintenance mode", and can realize switching between each mode.

[0024] According to the technical solution of the present invention, the IMA resident software of the aircraft auxiliary cooling system of the integrated modular avionics system can not only realize the functions of auxiliary cooling system working mode conversion, logic processing and subsystem unit instruction judgment, but also can exchange information with the external avionics cross-linking system.

[0025] According to the technical solution of the present invention, a modular design and an open architecture are adopted to greatly reduce power consumption and cost while improving the reliability of the avionics control system. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] The drawings described herein are used to provide a further understanding of the present invention and constitute a part of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings:

[0027] Figure 1 It is a structural block diagram of a control system of an aircraft auxiliary cooling system provided by the present invention;

[0028] Figure 2 The control logic of the central refrigeration unit control unit is shown;

[0029] Figure 3 The control logic of the liquid dispensing unit control unit is shown;

[0030] Figure 4 The control logic of the kitchen cooling unit control unit is shown;

[0031] Figure 5 The control logic of the electronic equipment cooling unit control unit is shown;

[0032] Figure 6 It is a control logic diagram of a specific embodiment of a control system of an aircraft auxiliary cooling system provided by the present invention;

[0033] Figure 7 The present invention is a schematic diagram of the communication relationship of the control system of the aircraft auxiliary cooling system. DETAILED DESCRIPTION

[0034] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the specific embodiments of the present invention and the corresponding drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0035] It should be noted that the terms "first", "second", etc. in the specification and claims of the present invention and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the data used in this way can be interchanged where appropriate, so that the embodiments of the present invention described herein can be implemented in an order other than those illustrated or described herein. In addition, the terms "including" and "having" and any variations thereof are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device that includes a series of steps or units is not necessarily limited to those steps or units that are clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0036] The present invention provides an aircraft auxiliary cooling control system. The aircraft auxiliary cooling control system is used to control an aircraft auxiliary cooling system.

[0037] The aircraft auxiliary cooling system includes multiple subsystem units, including: at least one central refrigeration unit CRU (Central Refrigeration Unit), at least one liquid dispensing unit LDU (Liquid Dispensing Unit), at least one galley cooling unit GACU (Galley Air Cooling Unit), at least one electronic equipment cooling unit ECU (Electronics Cooling Unit) and at least one power driven device PE (Power driven device); also includes: an integrated modular avionics system IMA and other accessories.

[0038] For example, the number of central refrigeration units CRU can be two or more, determined according to different models; the number of liquid distribution units LDU can be two, determined according to the number of flow paths, the kitchen cooling unit GACU and the electronic equipment cooling unit ECU are set according to the model requirements, the number of power drive devices PE can be two, determined according to the number of flow paths, and PE is the control unit of CRU and ECU.

[0039] The central refrigeration unit CRU includes a compressor that can generate cold air. The liquid distribution unit LDU can transport the cold air generated by the central refrigeration unit to the kitchen cooling unit GACU and the electronic equipment cooling unit ECU through a refrigerant pump, thereby cooling the kitchen environment and the electronic equipment on the aircraft respectively.

[0040] The control system of the aircraft auxiliary cooling system includes: an integrated modular avionics system IMA and one or more control units, and the one or more control units include: at least one of a central refrigeration unit (CRU) control unit, an electronic equipment cooling unit (ECU) control unit, a liquid distribution unit (LDU) control unit, and a galley cooling unit (GACU) control unit.

[0041] In a specific embodiment, each of the liquid distribution units LDU has a liquid distribution unit control unit, and each liquid distribution control unit can be set on the controller of the corresponding liquid distribution unit LDU, each of the kitchen cooling units GACU has a kitchen cooling unit control unit, and each of the kitchen cooling unit control units can be set on the controller of the corresponding kitchen cooling unit GACU, each of the central refrigeration units CRU has a central refrigeration unit control unit, and each of the electronic equipment cooling units ECU has an electronic equipment cooling unit control unit. The central refrigeration unit control unit and the electronic equipment cooling unit control unit can be set on the power drive device PE, and each power drive device PE can be used as a central refrigeration unit control unit and an electronic equipment cooling unit control unit to control at least one central refrigeration unit and at least one electronic equipment cooling unit, respectively. For example, referring to Figure 6 As shown, the aircraft auxiliary cooling system includes two power drive devices PE, one of which is responsible for controlling a CRU and an ECU, and the other CRUs and ECUs are controlled by another PE.

[0042] Figure 1 FIG. 2 shows a structural block diagram of a control system of an aircraft auxiliary cooling system according to an embodiment of the present invention. Figure 1 As shown, the control system of the aircraft auxiliary cooling system includes an integrated modular avionics system IMA, a central refrigeration unit control unit, an electronic equipment cooling unit control unit, a liquid distribution unit control unit and a galley cooling unit control unit, which are respectively used to control the central refrigeration unit, the electronic equipment cooling unit, the liquid distribution unit and the galley cooling unit.

[0043] The central refrigeration unit (CRU) control unit, referred to as the CRU control unit, is used to control the central refrigeration unit CRU.

[0044] For example, it includes: at least one of compressor frequency PI adjustment, electronic expansion valve opening PI adjustment and central refrigeration unit status monitoring. The aircraft auxiliary cooling system includes at least one central refrigeration unit CRU; the central refrigeration unit CRU may specifically include a compressor, a liquid storage device, a subcooler, an electronic expansion valve, a condenser, an evaporator, a radiator, a temperature sensor and a pressure sensor. Each central refrigeration unit CRU can be controlled by a power drive device PE. Each power drive device PE controls at least one central refrigeration unit CRU and an electronic equipment cooling unit ECU. The CRU control unit receives the refrigerant target outlet temperature instruction issued by the integrated modular avionics system IMA, and dynamically adjusts the compressor frequency according to the received refrigerant target outlet temperature instruction (for example, compare the refrigerant target outlet temperature with the refrigerant actual outlet temperature, and perform PI adjustment on the compressor frequency), and monitors the status of the central refrigeration unit CRU, and feeds back to the integrated modular avionics system IMA.

[0045] The electronic equipment cooling unit (ECU) control unit, referred to as the ECU control unit, is used to control the electronic equipment cooling unit ECU; for example, it includes: PI adjustment of the flow control valve opening and / or electronic equipment cooling unit status monitoring. The aircraft auxiliary cooling system includes at least one electronic equipment cooling unit ECU; the electronic equipment cooling unit ECU includes a temperature sensor, a quick detachable joint, a heat regenerator, a flow control valve, and a patch heat exchanger for cooling the electronic equipment; the ECU control unit receives a target temperature instruction issued by the integrated modular avionics system IMA, and dynamically adjusts the flow control valve opening angle according to the received target temperature instruction (comparing the target temperature and the actual temperature to perform PI adjustment on the flow valve opening), and can exchange information with cooling electronic equipment (such as the center wing override pump motor controller and the electric pump motor controller).

[0046] The liquid dispensing unit LDU control unit, referred to as LDU control unit, is used to control the liquid dispensing unit LDU; for example, it includes: at least one of pump component frequency PI regulation, control of pressure relief valve, filter status and liquid dispensing unit status monitoring. The aircraft auxiliary cooling system includes at least one liquid distribution unit LDU; each of the liquid distribution units may correspond to a liquid distribution unit control unit; the liquid distribution unit LDU mainly includes a refrigerant pump, a pressure relief valve, and a filter; the aircraft auxiliary cooling system may include refrigerant flow paths on both sides, one side corresponding to an LDU controller and a refrigerant pump; the liquid distribution unit LDU control unit receives a target liquid supply pressure instruction issued by the integrated modular avionics system IMA, and dynamically adjusts the refrigerant pump frequency according to the target liquid supply pressure instruction (compares the refrigerant target outlet temperature with the actual refrigerant outlet temperature to perform PI adjustment on the refrigerant pump frequency), can control the normal logic switching of the refrigerant pump group, and has a cross control function. When the LDU controller on one side fails, the LDU controller on the other side can respectively control the motor speed of one of the refrigerant pumps of the LDUs on both sides, monitor the liquid supply pressure signal of the LDUs on both sides (specifically, it can be the difference between the outlet pressure and the inlet pressure of the refrigerant pump group), and the pressure difference signal between the outlet pressure of the refrigerant pump group and the inlet of the refrigerant pump group.

[0047] The galley cooling unit (GACU) control unit, referred to as the GACU control unit, is used to control the galley cooling unit GACU, for example, including: flow valve opening PI adjustment, fan speed adjustment and galley cooling unit status monitoring. The aircraft auxiliary cooling system includes at least one galley cooling unit GACU; each galley cooling unit GACU may correspond to a galley cooling unit GACU control unit; the galley cooling unit GACU mainly includes a heat exchanger, a fan and a flow valve; the galley cooling unit GACU control unit receives the target return air temperature instruction issued by the integrated modular avionics system IMA, and dynamically adjusts the flow valve opening and the fan speed according to the received target return air temperature instruction.

[0048] The integrated modular avionics system IMA is used to determine the current aircraft operating state of the aircraft, and send corresponding target instructions to the at least one control unit according to the current aircraft operating state of the aircraft and the operating state of each electronic device that needs to be cooled.

[0049] Specifically, after power-on, when all subsystem units have entered the pre-start preparation, the current aircraft operating status of the aircraft is determined. Within a preset time after IMA is powered on (for example, within 1 minute after power-on), the CRU control unit, LDU control unit, GACU control unit and ECU control unit are periodically executed to call the roll call, and determine whether each subsystem unit has entered the pre-start preparation. If a unit feedback is not ready, the component is reset and restarted, and can be reset twice. If it is still not ready, an alarm is issued and fault processing is performed; if each unit has entered the pre-start preparation, IMA determines the current aircraft operating status and will issue corresponding instructions according to different statuses. The aircraft operating status includes at least one of ground operation, start-up, taxiing out, climbing, cruising, descending, landing and taxiing in.

[0050] Send corresponding instructions to each control unit, including at least one of the following:

[0051] Sending a refrigerant target outlet temperature instruction to the central refrigeration unit (CRU) control unit;

[0052] sending a target liquid supply pressure instruction to the liquid distribution unit (LDU) control unit;

[0053] sending a target return air temperature instruction to the kitchen cooling unit (GACU) control unit;

[0054] A target temperature instruction is sent to the electronic equipment cooling unit (ECU) control unit.

[0055] After receiving the target return air temperature instruction, the kitchen cooling unit control unit opens the flow valve and the fan and feeds back the flow valve opening signal to the integrated modular avionics system IMA; after receiving the target temperature instruction, the electronic equipment cooling unit control unit opens the flow valve and feeds back the flow valve opening signal to the integrated modular avionics system IMA; after receiving the target liquid supply pressure instruction, the liquid distribution unit control unit starts the refrigerant pump, performs PI adjustment on the frequency of the refrigerant pump according to the difference between the actual liquid supply pressure and the target liquid supply pressure, so that the difference between the actual liquid supply pressure and the target liquid supply pressure is less than a preset difference threshold (wherein the actual liquid supply pressure is equal to the difference between the outlet pressure and the inlet pressure of the refrigerant pump), and feeds back the refrigerant pump in place instruction to the integrated modular avionics system IMA; after receiving the refrigerant target outlet temperature instruction, the central refrigeration unit control unit starts the compressor, performs PI adjustment on the compressor frequency according to the difference between the refrigerant target outlet temperature and the refrigerant actual outlet temperature, and feeds back the CRU in place instruction to the integrated modular avionics system IMA.

[0056] Preferably, after the integrated modular avionics system IMA (IMA resident application software) calculates the target instructions of each control unit according to the aircraft operating status, it first sends a target return air temperature instruction to the kitchen cooling unit (GACU) control unit, and sends a target water inlet temperature instruction to the electronic equipment cooling unit (ECU) control unit.

[0057] Wherein, after receiving the target return air temperature instruction, the galley cooling unit (GACU) control unit opens the flow valve and the fan and feeds back the flow valve opening signal to the integrated modular avionics system IMA; after receiving the target inlet water temperature instruction, the electronic equipment cooling unit (ECU) control unit opens the flow valve and feeds back the flow valve opening signal to the integrated modular avionics system IMA;

[0058] After receiving the flow valve in place signal fed back by the kitchen cooling unit (GACU) control unit and the electronic equipment cooling unit ECU control unit, the integrated modular avionics system IMA (specifically, the IMA resident application software) sends a target liquid supply pressure instruction to the liquid distribution unit (LDU) control unit. After receiving the target liquid supply pressure instruction, the liquid distribution unit (LDU) control unit starts the coolant pump, performs PI adjustment on the frequency of the coolant pump according to the difference between the actual liquid supply pressure and the target liquid supply pressure, so that the difference between the actual liquid supply pressure and the target liquid supply pressure is less than the preset difference threshold, and feeds back the coolant pump in place instruction to the integrated modular avionics system IMA. After receiving the coolant pump in place signal from the integrated modular avionics system IMA, the coolant target outlet temperature instruction is sent to the central refrigeration unit (CRU) control unit. After receiving the coolant target outlet temperature instruction, the central refrigeration unit (CRU) control unit starts the compressor, performs PI adjustment on the compressor frequency according to the difference between the coolant target outlet temperature and the coolant actual outlet temperature, and feeds back the CRU in place instruction to the integrated modular avionics system IMA.

[0059] Preferably, the integrated modular avionics system IMA includes: a periodic execution mode, which periodically determines the current aircraft operating state of the aircraft, and issues corresponding target instructions to the at least one control unit according to the current aircraft operating state of the aircraft and the operating state of each electronic device that needs to be cooled; that is, periodically monitors the aircraft operating state and the operating state of each device, calculates the required target, and issues target instructions for each unit, and so on. In the periodic execution operation mode, the system can be fully automatically controlled, and each sub-component unit can be dynamically adjusted according to the target instruction to achieve the cooling requirements of the kitchen dining cart and large electronic equipment under different stages and working conditions.

[0060] Optionally, the integrated modular avionics system IMA also includes: a ground maintenance mode and / or a software maintenance mode. In a specific embodiment, the ground maintenance mode is achieved by releasing the coolant level detection alarm and / or the coolant pH value detection alarm. In the ground maintenance mode, maintenance personnel can perform coolant filling and / or draining and / or coolant pH value detection. In a specific embodiment, the software maintenance mode is achieved by releasing the control program lock. In the software maintenance mode, the IMA resident application software and other sub-component control units can be maintained and updated, and relevant personnel can check the control program.

[0061] Optionally, the integrated modular avionics system IMA is further used to: perform fault diagnosis and processing of each subsystem unit of the aircraft auxiliary cooling system.

[0062] That is, detect whether the central refrigeration unit CRU, the electronic equipment cooling unit ECU, the liquid distribution unit LDU, and the kitchen cooling unit GACU are faulty. If any component of the central refrigeration unit CRU, the electronic equipment cooling unit ECU, the liquid distribution unit LDU, and the kitchen cooling unit GACU is detected to be faulty, perform fault processing.

[0063] Preferably, fault judgment and processing of each unit of the aircraft auxiliary cooling system is performed periodically, and if a fault is detected in a component of the CRU, LDU, GACU or ECU, a fault processing operation is performed.

[0064] In a specific embodiment, the control logic of the central refrigeration unit control unit includes: if the target outlet temperature command of the refrigerant is received, the compressor is controlled to start and run according to the preset frequency of the compressor, and after the operation is normal and stable, the normal operation control mode (i.e., the refrigerant pump frequency PI adjustment mode) is entered, and the compressor frequency and the opening of the electronic expansion valve are dynamically adjusted according to the target outlet temperature command of the refrigerant and the actual outlet temperature of the refrigerant fed back by the refrigerant outlet temperature sensor. Further, it also includes: oil return condition determination, if the oil return condition is met, the oil return operation mode is entered, and the normal operation mode is returned after the oil return is completed; if the oil return condition is not met, the protection condition determination is performed (for example, whether the exhaust temperature exceeds the preset exhaust temperature threshold, whether the power module IPM current exceeds the preset current threshold), if the protection condition is met, the protection operation is performed, otherwise it returns to the normal operation mode; if a protection abnormality occurs during the protection operation, the standby control mode is entered.

[0065] Figure 2 The control logic of the central refrigeration unit control unit is shown as Figure 2As shown, after receiving the refrigerant target outlet temperature instruction or the shutdown instruction, the CRU control unit performs instruction judgment. If it is a shutdown instruction, it enters the standby control mode; if it is a refrigerant target outlet temperature instruction, it performs a status check, detects the signals of each temperature and pressure measuring element, and then enters the startup control to control the compressor to start and run at a preset frequency (low frequency, such as 20HZ). After the operation is normal and stable, it enters the normal operation control mode (i.e., the refrigerant pump frequency PI adjustment mode), and performs PI dynamic adjustment on the compressor frequency and the opening of the electronic expansion valve according to the target outlet temperature instruction and the feedback results of each measuring element (by comparing the temperature sensor feedback The compressor frequency is adjusted by PI based on the difference between the actual superheat and the target superheat), and then the oil return condition of the refrigeration oil is judged. If it is "Y", that is, the oil return condition is met, the oil return operation mode is entered, and the normal operation mode is returned after the oil return is completed; if it is "N", that is, the oil return condition is not met, the protection condition is judged (for example, whether the exhaust temperature exceeds the preset exhaust temperature threshold, whether the power module IPM current exceeds the preset current threshold). If it is "Y", that is, the protection condition is met, the protection operation is performed; if it is "N", that is, the protection condition is not met, it returns to the normal operation control; if a protection abnormality occurs during the protection operation, the standby control mode is entered.

[0066] In a specific embodiment, the control logic of the liquid distribution unit control unit includes: if a target liquid supply pressure instruction is received, the refrigerant pump is controlled to start and operate according to a preset frequency of the refrigerant pump, and after the operation is normal and stable, the normal operation control mode is entered, and the refrigerant pump frequency is dynamically adjusted by PI according to the target liquid supply pressure instruction and the pressure value fed back by the refrigerant pump outlet pressure sensor and / or inlet pressure sensor.

[0067] Preferably, the control logic of the liquid distribution unit control unit also includes: before controlling the refrigerant pump to start and run at the preset frequency of the refrigerant pump, determining whether the LDU control unit on the other side is faulty; if it is determined that the LDU control unit on the other side is faulty, then controlling the LDU on the other side and then rotating the pump group on that side and checking the status; if it is determined that the LDU control unit on the other side is not faulty, then directly rotating the pump group on that side and checking the status, and then entering the startup control mode, controlling the refrigerant pump to start and run at the preset frequency of the refrigerant pump.

[0068] Preferably, the control logic of the liquid distribution unit control unit also includes: after dynamically adjusting the refrigerant pump frequency by PI according to the target liquid supply pressure instruction and the pressure value fed back by the refrigerant outlet pressure sensor and / or the inlet pressure sensor, determining whether the protection condition is met (for example, determining whether the pressure value fed back by the pump component outlet pressure sensor and / or the inlet pressure sensor is higher than the corresponding preset safety value); if the protection condition is met, performing protection operation; otherwise, returning to the normal operation mode; if a protection abnormality occurs, entering the standby control mode.

[0069] Figure 3 The control logic of the liquid dispensing unit control unit is shown as follows: Figure 3 As shown, after receiving the LDU target liquid supply pressure instruction or the shutdown instruction, the LDU control unit performs instruction judgment. If it is a shutdown instruction, it enters the standby control mode. If it is a target liquid supply pressure instruction, it determines whether the LDU control unit on the other side is faulty. If it is faulty, the LDU on the other side is controlled and the pump group on that side is rotated and the status is checked. Otherwise, the pump group on that side is directly rotated and the status is checked, and then the startup control mode is entered to start the refrigerant pump and control the low frequency (such as 25HZ). After the operation is normal and stable, the normal operation control mode is entered. According to the target liquid supply pressure instruction and the feedback results of each measuring element, the pump frequency is dynamically adjusted by PI (incremental PI dynamic adjustment, by comparing the pressure sensor feedback data with the target data, and calculating and adjusting the pump frequency based on the set formula), and then the protection condition is determined (determining whether the feedback result of the relevant sensor exceeds the safety value, such as judging whether the outlet pressure exceeds the safety value according to the outlet pressure sensor), and returning to the normal operation control or protection operation respectively. If a protection abnormality occurs, the standby control mode is entered.

[0070] In a specific embodiment, the control logic of the kitchen cooling unit control unit includes: if a target return air temperature instruction is received, the fan frequency is controlled according to the number of dining carts and environmental requirements, the flow valve is opened to the maximum value, and the flow valve in place signal is fed back to the integrated modular avionics system IMA, and then normal operation control is entered, and the flow valve opening is dynamically adjusted by PI according to the target return air temperature and the actual return air temperature fed back by the return air temperature sensor.

[0071] Optionally, the control logic of the kitchen cooling unit control unit also includes: after PI dynamic adjustment of the flow valve opening according to the target return air temperature and the actual return air temperature fed back by the return air temperature sensor, abnormality judgment is made (for example, judging whether the return air temperature is lower than or higher than a preset return air temperature threshold value); if it is judged to be abnormal, abnormality processing is performed; otherwise, the normal operation control mode is returned to.

[0072] Figure 4The control logic of the kitchen cooling unit control unit is shown as Figure 4 As shown, the control logic of the GACU control unit is as follows: after receiving the target return air temperature command or the shutdown command, the command is judged. If it is a shutdown command, the standby control mode is entered. If it is a target return air temperature command, a status check is performed to detect the fan, flow valve, and each measuring element signal, and then the startup control is entered. The fan frequency is controlled according to the number of dining cars and environmental requirements (for example, the fan frequency is controlled according to different fan frequencies corresponding to different pre-set numbers of dining cars and environmental requirements), the flow valve is opened to the maximum value, and the flow valve in place signal is fed back (to IMA), and then the normal operation control is entered. The flow valve opening is dynamically adjusted by PI according to the target return air temperature and the feedback results of the measuring element (specifically, the flow valve opening can be adjusted by PI by comparing the actual return air temperature fed back by the temperature sensor with the target return air temperature), and finally an abnormality judgment is made, and abnormal processing is performed or the normal operation control mode is returned.

[0073] In a specific embodiment, the control logic of the electronic equipment cooling unit control unit includes: if a target temperature instruction is received, the flow valve is opened to the maximum value, and a flow valve in place signal is fed back to the integrated modular avionics system IMA, and then normal operation control is entered, that is, the flow valve opening is dynamically adjusted according to the target return air temperature and the actual return air temperature fed back by the temperature sensor.

[0074] Preferably, the control logic of the electronic equipment cooling unit control unit further includes: after dynamically adjusting the flow valve opening according to the target return air temperature and the actual return air temperature fed back by the temperature sensor, making an abnormality determination, and if it is determined to be abnormal, performing abnormal processing, otherwise, returning to the normal operation control mode. The abnormality determination may specifically include determining whether the return air temperature is lower than or higher than a preset safety threshold.

[0075] Figure 5 The control logic of the electronic equipment cooling unit control unit is shown as follows Figure 5 As shown, the control logic of the ECU control unit is as follows: after receiving the target return air temperature command or the shutdown command, the command is judged. If it is a shutdown command, the standby control mode is entered. If it is a target return air temperature command, a status check is performed to detect the flow valve and the signals of each measuring element. Then, the start-up control is entered, the flow valve is opened to the maximum value, and the flow valve in place signal is fed back to the integrated modular avionics system IMA. Then, the normal operation control is entered, and the flow valve opening is dynamically adjusted by PI according to the target return air temperature and the actual return air temperature fed back by the temperature sensor. Finally, an abnormality judgment is made, and abnormal processing is performed or the normal operation control mode is returned.

[0076] Optionally, the control system of the aircraft auxiliary cooling system further comprises: an alarm unit for providing single and double liquid circuit failure alarms and system degradation alarms for the aircraft auxiliary cooling system.

[0077] Optionally, the control system of the aircraft auxiliary cooling system further comprises: a communication unit, through which the integrated modular avionics system IMA communicates with the liquid distribution unit control unit and / or the galley cooling unit control unit.

[0078] Optionally, the communication unit is also used to: exchange information with other avionics equipment and other interconnected systems of the aircraft.

[0079] Optionally, the aircraft auxiliary cooling system also includes: a power drive device; the central refrigeration unit control unit and / or the electronic equipment cooling unit control unit are switched through the power drive device, that is, receiving the refrigerant target outlet temperature instruction issued by the integrated modular avionics system IMA, comparing the refrigerant target outlet temperature with the refrigerant actual outlet temperature, calculating the compressor frequency adjustment value, transmitting it to the central refrigeration unit CRU, and performing PI adjustment on the compressor frequency; receiving the target temperature instruction issued by the integrated modular avionics system IMA, calculating the flow valve opening adjustment value for the target return air temperature and the actual return air temperature, transmitting it to the electronic equipment cooling unit EDU, and performing PI adjustment on the flow valve opening.

[0080] In order to clearly illustrate the technical solution of the present invention, the control logic of the aircraft auxiliary cooling control system provided by the present invention is described below with reference to a specific embodiment.

[0081] Figure 6 FIG. 1 is a control logic diagram of a specific embodiment of a control system of an aircraft auxiliary cooling system provided by the present invention. Figure 6As shown in the figure, after power-on, the integrated modular avionics system IMA sets the IMA resident application software of the aircraft auxiliary cooling system, enters the "periodic execution operation mode" by default, and can realize the switching between "ground maintenance mode" and "software maintenance mode". Within 1 minute after power-on, the IMA periodic execution program cyclically calls out multiple CRU control units, LDU control units, GACU control units and ECU control units to determine whether each subsystem unit has entered the pre-start preparation. If a unit feedback is not ready, the component will be reset and restarted, and it can be reset twice. If it is still not ready, an alarm will be issued and fault handling will be performed; if each unit has entered the pre-start preparation, IMA determines the current aircraft operation status and will issue corresponding instructions according to different statuses. Among them, the operation status includes ground operation, start-up, taxiing out, climbing, cruising, descending, landing, taxiing in, etc. In each state, not only the operation status of the kitchen dining car and large electronic equipment is different, but also the cooling demand is inconsistent. Therefore, IMA needs to calculate and judge according to the flight operation status and the operation status of each equipment, and issue corresponding instructions such as CRU refrigerant target outlet temperature, LDU target liquid supply pressure, GACU target return air temperature, ECU target temperature, etc. After IMA calculates each target command according to the aircraft operation status, it first issues the GACU and ECU target commands. After receiving the target command, the GACU control unit opens the flow valve and fan and feeds back the flow valve opening signal to IMA. After receiving the target command, the ECU control unit opens the flow valve and feeds back the flow valve opening signal to IMA. After receiving the GACU and ECU flow valve in place signal, IMA issues the LDU target liquid supply pressure command. After receiving the target command, the LDU control unit starts the coolant pump, adjusts it to the appropriate frequency, and feeds back the coolant pump in place command to IMA. After receiving the coolant pump in place signal, IMA issues the CRU coolant target outlet temperature command. After receiving the target command, the CRU control unit starts the compressor, adjusts it to the appropriate frequency, and feeds back the CRU in place command to IMA. After that, IMA regularly judges the operation status of the aircraft and each equipment, calculates and judges the required target, and issues commands, and this cycle repeats. The periodic execution program also periodically monitors the status information of each sub-component and performs fault handling tasks. If a fault is detected in a component in the CRU, LDU, GAUC or ECU, a fault handling operation is performed.

[0082] Figure 7It is a schematic diagram of the communication relationship of the control system of the aircraft auxiliary cooling system provided by the present invention. IMA directly communicates with GACU and LDU control units through the communication unit, while CRU and ECU are transferred through the power drive device PE, IMA status monitoring and communication signals between control units of each component. For GACU1~GACU8 (different models and configuration numbers are different, here are 8 GACUs), each temperature measuring element, flow valve opening, fan speed, fault and other signals are sent to IMA, and instructions such as target return air temperature and working mode are received at the same time. The LDU control unit receives IMA target liquid supply pressure, working mode and other signals, and feeds back information such as liquid level, pump motor temperature, measuring element, fault, pump identification code to IMA. IMA sends CRU coolant target outlet temperature, ECU target temperature, working mode, etc. to the corresponding CRU or ECU control unit through PE, while CRU sends compressor frequency signal, frequency reduction, electronic expansion valve, solenoid valve, measuring element and other signals to IMA through PE, and ECU sends flow valve opening, temperature measuring element, fault signal, etc. to IMA through PE. Among them, IMA communicates with CRU1, ECU1, and ECU2 through the left PE (L), and communicates with CRU2 and ECU3 through the right PE (R).

[0083] a. GACU inlet and outlet temperature measuring elements, heat exchanger temperature measuring elements, flow valve opening, GACU fan speed; b. GACU fault signal; c. GACU receives target instructions sent by IMA, including GACU switch signal, target return air temperature, etc.; d. Compressor frequency signal, compressor frequency reduction, electronic expansion valve opening, solenoid valve switch, refrigerant temperature, pressure measuring element, ram air temperature measuring element, etc.; e. ECU fault information, CRU fault information, etc.; f. PE power drive device receives target instructions sent by IMA, including ECU target temperature, CRU refrigerant target outlet temperature, etc.; g. LDU target liquid supply pressure, pump assembly storage tank liquid level, pump motor temperature, pressure measuring element, LIDU maintenance signal, etc.; h. LDU control unit fault signal, LDU pump assembly identification code; i. LDU control unit receives target instructions sent by IMA, including LDU switch signal, etc.; j. Each device receives device restart, normal mode, standby mode, pre-working mode, abnormal mode signal, etc. sent by IMA.

[0084] The present invention also provides an aircraft auxiliary cooling system corresponding to the control system of the aircraft auxiliary cooling system, comprising any of the aforementioned control systems.

[0085] According to the solution provided by the present invention, the integrated modular avionics system IMA determines the current aircraft operating state of the aircraft, and sends corresponding target instructions to the at least one control unit according to the current aircraft operating state and the operating state of each device of the aircraft; the one or more control units receive the target instructions sent by the integrated modular avionics system IMA, perform corresponding operations according to the received target instructions, and feedback to the integrated modular avionics system IMA, so as to realize the control of the aircraft auxiliary cooling system. Each sub-component control unit can be dynamically adjusted according to the target instructions to realize the cooling requirements of the kitchen dining cart and large electronic equipment under different stages and working conditions.

[0086] The solution provided by the present invention can periodically monitor the status information of each subsystem unit and perform fault processing. The periodic execution operation program should include LDU control program, CRU control program, ECU control program, GACU control program, and alarm program. The aircraft auxiliary cooling control system can realize full automatic control to meet the cooling needs of kitchen dining carts and large electronic equipment under different stages and working conditions.

[0087] The IMA resident software of the aircraft auxiliary cooling system of the integrated modular avionics system of the present invention includes "periodic execution operation mode", "ground maintenance mode" and "software maintenance mode", and can realize switching of each mode.

[0088] The IMA resident software of the aircraft auxiliary cooling system of the integrated modular avionics system of the present invention can realize the functions of auxiliary cooling system working mode conversion, logic processing and subsystem unit instruction judgment, and can also exchange information with the external avionics cross-linking system.

[0089] The solution provided by the present invention adopts modular design and open architecture, which greatly reduces power consumption and cost while improving the reliability of the avionics control system.

[0090] The functions described herein may be implemented in hardware, software executed by a processor, firmware, or any combination thereof. If implemented in software executed by a processor, the functions may be stored as one or more instructions or codes on a computer-readable medium or transmitted via a computer-readable medium. Other examples and implementations are within the scope and spirit of the present invention and the appended claims. For example, due to the nature of software, the functions described above may be implemented using software executed by a processor, hardware, firmware, hard wiring, or a combination of any of these. In addition, each functional unit may be integrated into a processing unit, each unit may exist physically separately, or two or more units may be integrated into one unit.

[0091] In the several embodiments provided in this application, it should be understood that the disclosed technical content can be implemented in other ways. Among them, the device embodiments described above are only schematic. For example, the division of the units can be a logical function division. There may be other division methods in actual implementation. For example, multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the mutual coupling or direct coupling or communication connection shown or discussed can be through some interfaces, indirect coupling or communication connection of units or modules, which can be electrical or other forms.

[0092] The units described as separate components may or may not be physically separated, and the components of the control device may or may not be physical units, that is, they may be located in one place or distributed in multiple units. Some or all of the units may be selected according to actual needs to achieve the purpose of the present embodiment.

[0093] If the integrated unit is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present invention, in essence, or the part that contributes to the relevant technology or all or part of the technical solution can be embodied in the form of a software product, and the computer software product is stored in a storage medium, including a number of instructions to enable a computer device (which can be a personal computer, a server or a network device, etc.) to perform all or part of the steps of the method described in each embodiment of the present invention. The aforementioned storage medium includes: U disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), mobile hard disk, disk or optical disk and other media that can store program codes.

[0094] The above description is only an embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent substitution, improvement, etc. made within the spirit and principle of the present invention shall be included in the scope of the claims of the present invention.

Claims

1. A control system for an aircraft auxiliary cooling system, used to control an aircraft auxiliary cooling system, characterized in that: The aircraft auxiliary cooling system includes a plurality of subsystem units, including: at least one central refrigeration unit, at least one liquid distribution unit, at least one galley cooling unit, at least one electronic equipment cooling unit and at least one power drive device; The aircraft auxiliary cooling control system comprises: an integrated modular avionics system and one or more control units, wherein the one or more control units comprise: at least one of a central refrigeration unit control unit, an electronic equipment cooling unit control unit, a liquid distribution unit control unit, and a galley cooling unit control unit; the central refrigeration unit control unit, the electronic equipment cooling unit control unit, the liquid distribution unit control unit, and the galley cooling unit control unit are used to control the central refrigeration unit, the electronic equipment cooling unit, the liquid distribution unit, and the galley cooling unit, respectively; The integrated modular avionics system is used to determine the current aircraft operating state of the aircraft and issue corresponding target instructions to the one or more control units according to the current aircraft operating state of the aircraft and the operating state of each electronic device that needs to be cooled; The one or more control units are used to receive target instructions issued by the integrated modular avionics system IMA, perform corresponding operations according to the received target instructions, and provide feedback to the integrated modular avionics system IMA.

2. The control system according to claim 1, characterized in that: The integrated modular avionics system sends corresponding instructions to each control unit, including at least one of the following: Sending a refrigerant target outlet temperature instruction to the central refrigeration unit control unit; sending a target liquid supply pressure instruction to the liquid dispensing unit control unit; sending a target return air temperature instruction to the kitchen cooling unit control unit; A target temperature instruction is sent to the electronic equipment cooling unit control unit.

3. The control system according to claim 2, characterized in that: The at least one control unit receives a target instruction issued by the integrated modular avionics system, performs a corresponding operation according to the received target instruction, and feeds back to the integrated modular avionics system, including: After receiving the target return air temperature instruction, the galley cooling unit control unit opens the flow valve and the fan and feeds back a flow valve opening signal to the integrated modular avionics system; After receiving the target temperature instruction, the electronic equipment cooling unit control unit opens the flow valve and feeds back a flow valve opening signal to the integrated modular avionics system; After receiving the target liquid supply pressure instruction, the liquid distribution unit control unit starts the coolant pump, performs PI adjustment on the frequency of the coolant pump according to the difference between the actual liquid supply pressure and the target liquid supply pressure, and feeds back the coolant pump arrival instruction to the integrated modular avionics system; After receiving the refrigerant target outlet temperature instruction, the central refrigeration unit control unit starts the compressor, performs PI adjustment on the compressor frequency according to the difference between the refrigerant target outlet temperature and the refrigerant actual outlet temperature, and feeds back the CRU in place instruction to the integrated modular avionics system.

4. The control system according to claim 3, characterized in that: The integrated modular avionics system first sends a target return air temperature instruction to the kitchen cooling unit control unit and a target water inlet temperature instruction to the electronic equipment cooling unit control unit, and after receiving the flow valve in place signal fed back by the kitchen cooling unit control unit and the electronic equipment cooling unit control unit, sends a target liquid supply pressure instruction to the liquid distribution unit control unit, and after receiving the refrigerant pump in place signal fed back by the liquid distribution unit control unit, sends a refrigerant target outlet temperature instruction to the central refrigeration unit control unit.

5. The control system according to any one of claims 1 to 4, characterized in that: The integrated modular avionics system includes: a periodic execution mode, which periodically determines the current aircraft operating status of the aircraft, and issues corresponding target instructions to the at least one control unit based on the current aircraft operating status of the aircraft and the operating status of each electronic device that needs to be cooled.

6. The control system according to any one of claims 1 to 4, characterized in that: The integrated modular avionics system IMA is also used to: perform fault diagnosis and processing of each subsystem unit of the aircraft auxiliary cooling system; If it is determined that any component of the central refrigeration unit, the electronic equipment cooling unit, the liquid distribution unit and the kitchen cooling unit fails, the failure is handled.

7. The control system according to any one of claims 1 to 4, characterized in that: The control logic of the central refrigeration unit control unit includes: If the refrigerant target outlet temperature command is received, the compressor is controlled to start and run at the preset frequency of the compressor. After the operation is normal and stable, it enters the normal operation control mode. According to the refrigerant target outlet temperature command and the actual refrigerant outlet temperature fed back by the refrigerant outlet temperature sensor, the compressor frequency and the electronic expansion valve opening are dynamically adjusted by PI.

8. The control system according to claim 6, characterized in that: The control logic of the central refrigeration unit control unit also includes: The oil return condition is judged. If the oil return condition is met, the oil return operation mode is entered, and the normal operation mode is returned after the oil return is completed. If the oil return condition is not met, the protection condition is judged. If the protection condition is met, the protection operation is performed, otherwise it returns to the normal operation mode. If a protection abnormality occurs during the protection operation, the standby control mode is entered.

9. The control system according to any one of claims 1 to 4, characterized in that: The control logic of the liquid dispensing unit control unit includes: If the target liquid supply pressure command is received, the refrigerant pump is controlled to start and run according to the preset frequency of the refrigerant pump. After the operation is normal and stable, it enters the normal operation control mode. According to the target liquid supply pressure command and the pressure value fed back by the refrigerant pump outlet pressure sensor and / or inlet pressure sensor, the refrigerant pump frequency is dynamically adjusted by PI.

10. The control system according to claim 9, characterized in that: The control logic of the liquid distribution unit control unit also includes: before controlling the start of the coolant pump and running at the preset frequency of the coolant pump, determining whether the control unit of the liquid distribution unit on the other side is faulty; if it is determined that the control unit of the liquid distribution unit on the other side is faulty, then controlling the liquid distribution unit on the other side and then rotating the pump group on that side and checking the status; if it is determined that the control unit of the liquid distribution unit on the other side is not faulty, then directly rotating the pump group on that side and checking the status, and then entering the start control mode, controlling the start of the coolant pump and running at the preset frequency of the coolant pump; and / or, The control logic of the liquid distribution unit control unit also includes: after dynamically adjusting the refrigerant pump frequency according to the target liquid supply pressure instruction and the pressure value fed back by the refrigerant outlet pressure sensor and / or the refrigerant inlet pressure sensor, it is determined whether the protection conditions are met; if the protection conditions are met, a protection operation is performed; otherwise, the normal operation mode is returned; if a protection abnormality occurs, the standby control mode is entered.

11. The control system according to any one of claims 1 to 4, characterized in that: The control logic of the kitchen cooling unit control unit includes: If the target return air temperature command is received, the fan frequency is controlled according to the number of dining cars and environmental requirements, the flow valve is opened to the maximum value, and the flow valve in place signal is fed back to the integrated modular avionics system. After that, normal operation control is entered, and the flow valve opening is dynamically adjusted by PI according to the target return air temperature and the actual return air temperature fed back by the return air temperature sensor.

12. The control system according to claim 11, characterized in that: The control logic of the kitchen cooling unit control unit also includes: after PI dynamic adjustment of the flow valve opening according to the target return air temperature and the feedback result of the measuring element, abnormality judgment is performed. If it is judged to be abnormal, abnormality processing is performed, otherwise, it returns to the normal operation control mode.

13. The control system according to any one of claims 1 to 4, characterized in that: The control logic of the electronic equipment cooling unit control unit includes: If the target temperature command is received, the flow valve will be opened to the maximum value and the flow valve in place signal will be fed back to the integrated modular avionics system. Then the normal operation control will be entered and the flow valve opening will be dynamically adjusted by PI according to the target return air temperature and the actual return air temperature fed back by the return air temperature sensor.

14. The control system according to claim 13, characterized in that: The control logic of the electronic equipment cooling unit control unit also includes: After the flow valve opening is dynamically adjusted by PI according to the target return air temperature and the actual return air temperature fed back by the return air temperature sensor, an abnormality determination is made. If it is determined to be abnormal, abnormal processing is performed, otherwise, the normal operation control mode is returned to.

15. The control system according to claim 1, characterized in that: The aircraft auxiliary cooling system further includes: a communication unit; the integrated modular avionics system communicates with the liquid distribution unit control unit and / or the galley cooling unit control unit via the communication unit.

16. An aircraft auxiliary cooling system, characterized in that: Comprising a control system as described in any one of claims 1-15.

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