Aircraft auxiliary cooling system and control device and method thereof

Abstract

The invention discloses a control device of an airplane auxiliary cooling system, the airplane auxiliary cooling system and a control method of the airplane auxiliary cooling system, and the device comprises a switching unit of each controlled part, and the switching unit obtains the state data of a controller of each controlled part and transmits the state data to a communication unit; the IMA control unit obtains state data of the controller of the first controlled part from the communication unit, and if it is determined that the controller of the first controlled part breaks down, a target control instruction of the first controlled part is sent to the switching unit of the second controlled part through the communication unit; and the switching unit of the second controlled component acquires the target control instruction of the first controlled component and transmits the target control instruction to the controller of the second controlled component to perform cross control on the operation process of the first controlled component. According to the scheme, the universal control device composed of the communication unit and the IMA control unit is used for achieving cross control between controllers of different pump assemblies, and the operation reliability of the aircraft auxiliary cooling system is improved.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft auxiliary cooling systems, and specifically relates to a control device for an aircraft auxiliary cooling system, an aircraft auxiliary cooling system and a control method thereof, and more particularly to an automatic liquid supply pressure control device suitable for multiple components (such as multiple pump assemblies), an aircraft auxiliary cooling system and a control method thereof. 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 carts and large electronic equipment. Due to the large front-to-back span of the aircraft fuselage, the aircraft auxiliary cooling system adopts multi-component control, such as using multi-flow liquid to cool each dining cart or equipment. Each flow involves a pump assembly to ensure the head and flow of each flow. However, although each pump assembly only provides liquid driving function for its own flow, if the controller of the pump assembly on one side (i.e., one flow) fails, the refrigeration function on that side will fail, greatly reducing the reliability of the aircraft auxiliary cooling system.

[0003] The above contents are only used to assist in understanding the technical solution of the present invention and do not constitute an admission that the above contents are prior art. Summary of the invention

[0004] The object of the present invention is to provide a control device for an aircraft auxiliary cooling system, an aircraft auxiliary cooling system and a control method thereof, so as to solve the problem that if the controller of a pump assembly in a flow path fails, the refrigeration function of the flow path will fail, greatly reducing the reliability of the aircraft auxiliary cooling system. By utilizing a universal control device composed of a communication unit and an IMA control unit, when the controller of one pump assembly fails, cross-control can be achieved through the controllers of other pump assemblies, thereby preventing the failure of the controller of one pump assembly from affecting the cooling function of that side, and improving the reliability of the operation of the aircraft auxiliary cooling system.

[0005] The present invention provides a control device for an aircraft auxiliary cooling system, wherein the aircraft auxiliary cooling system has controlled components, and the number of the controlled components is more than two; for each of the more than two controlled components, a sampling unit, a switching unit and a controller are provided; the control device for the aircraft auxiliary cooling system comprises: a communication unit and an IMA control unit; wherein the sampling unit of each of the controlled components is used to sample data at the location of the sampling unit of each of the controlled components as detection data of each of the controlled components; the IMA control unit is used to generate a target control instruction for each of the controlled components according to the detection data of each of the controlled components, and send the target control instruction of each of the controlled components to the switching unit of each of the controlled components through the communication unit, so as to transmit the target control instruction to the controller of each of the controlled components via the switching unit of each of the controlled components to realize control of the operation process of each of the controlled components; each of the controlled components The switching unit of the controlled component is used to obtain the status data of the controller of each controlled component from the controller of each controlled component and transmit it to the communication unit; the IMA control unit is also used to obtain the status data of the controller of each controlled component from the communication unit, and determine whether the controller of each controlled component is faulty according to the status data of the controller of each controlled component; and if it is determined that the controller of each controlled component is faulty, it is recorded as a controller failure of the first controlled component, and the target control instruction of the first controlled component is sent to the switching unit of the second controlled component among the two or more controlled components through the communication unit; the switching unit of the second controlled component is used to obtain the target control instruction of the first controlled component from the communication unit and transmit it to the controller of the second controlled component, so that the controller of the second controlled component can realize cross-control of the operation process of the first controlled component.

[0006] In some embodiments, the control device of the aircraft auxiliary cooling system further includes: a detection unit; wherein the detection unit is used to receive the detection data of all the controlled components and upload them to the communication unit; the IMA control unit is also used to extract the detection data of each controlled component from the detection data of all the controlled components at the communication unit, generate a target control instruction for each controlled component according to the detection data of each controlled component, and send the target control instruction of each controlled component to the switching unit of each controlled component through the communication unit, so as to transmit the target control instruction to the controller of each controlled component via the switching unit of each controlled component to realize the control of the operation process of each controlled component; each controlled component A switching unit is used to obtain the detection data of each controlled component and the target control instruction of each controlled component from the communication unit; the detection data of each controlled component is switched to obtain the switching processing data of each controlled component; and the switching processing data of each controlled component and the target control instruction of each controlled component are transmitted to the controller of each controlled component; the controller of each controlled component is used to obtain the switching processing data of each controlled component and the target control instruction of each controlled component from the switching unit of each controlled component; and the operation process of each controlled component is controlled in combination with the switching processing data of each controlled component and the target control instruction of each controlled component.

[0007] In some embodiments, each of the controlled components includes any one of a pump assembly, a heating unit, a radiator, and a bypass valve.

[0008] Matching the above device, the present invention provides an aircraft auxiliary cooling system on another aspect, including: the control device of the aircraft auxiliary cooling system mentioned above.

[0009] Matching the above-mentioned aircraft auxiliary cooling system, the present invention provides a control method for an aircraft auxiliary cooling system on another aspect, comprising: sampling data at the location of the sampling unit of each controlled component itself through the sampling unit of each controlled component as detection data of each controlled component; generating a target control instruction of each controlled component according to the detection data of each controlled component through the IMA control unit, and sending the target control instruction of each controlled component to the switching unit of each controlled component through the communication unit, so as to transmit the target control instruction to the controller of each controlled component via the switching unit of each controlled component to realize control of the operation process of each controlled component; obtaining the controller of each controlled component from the controller of each controlled component through the switching unit of each controlled component. status data and transmit it to the communication unit; through the IMA control unit, the status data of the controller of each of the controlled components is obtained from the communication unit, and whether the controller of each of the controlled components is faulty is determined according to the status data of the controller of each of the controlled components; and if it is determined that the controller of each of the controlled components is faulty, it is recorded as a controller failure of the first controlled component, and the target control instruction of the first controlled component is sent to the switching unit of the second controlled component among the two or more controlled components through the communication unit; through the switching unit of the second controlled component, the target control instruction of the first controlled component is obtained from the communication unit and transmitted to the controller of the second controlled component, so that the controller of the second controlled component can realize cross-control of the operation process of the first controlled component.

[0010] In some embodiments, it also includes: receiving the detection data of all the controlled components and uploading them to the communication unit through the detection unit; extracting the detection data of each controlled component from the detection data of all the controlled components at the communication unit through the IMA control unit, generating a target control instruction for each controlled component according to the detection data of each controlled component, and sending the target control instruction of each controlled component to the switching unit of each controlled component through the communication unit, so as to transmit it to the controller of each controlled component via the switching unit of each controlled component to realize the control of the operation process of each controlled component; and The method comprises the following steps: obtaining the detection data of each controlled component and the target control instruction of each controlled component from the switching unit; performing transfer processing on the detection data of each controlled component to obtain the transfer processing data of each controlled component; and transmitting the transfer processing data of each controlled component and the target control instruction of each controlled component to the controller of each controlled component; obtaining the transfer processing data of each controlled component and the target control instruction of each controlled component from the transfer unit of each controlled component through the controller of each controlled component; and controlling the operation process of each controlled component in combination with the transfer processing data of each controlled component and the target control instruction of each controlled component.

[0011] In some embodiments, each of the controlled components includes a pump assembly; the sampling unit of each of the pump assemblies includes at least one of the following: an inlet pressure measuring element, an outlet pressure measuring element, and a flow monitoring unit; the detection data of each of the pump assemblies includes: at least one of the inlet pressure, outlet pressure, and flow rate; the detection data of each of the controlled components is transferred and processed by the transfer unit of each of the controlled components to obtain the transferred processing data of each of the controlled components, including: determining the difference between the outlet pressure and the inlet pressure of each of the pump assemblies as the current actual supply of each of the pump assemblies Liquid pressure; through the controller of each of the controlled components, combined with the transfer processing data of each of the controlled components and the target control instructions of each of the controlled components, the operation process of each of the controlled components is controlled, including: determining the target liquid supply pressure of each pump component carried by the target control instructions of each pump component; and determining the liquid supply pressure difference between the target liquid supply pressure of each pump component and the current actual liquid supply pressure of each pump component to obtain the liquid supply pressure difference of each pump component; according to the liquid supply pressure difference of each pump component, the pump frequency of each pump component is PI-adjusted.

[0012] In some embodiments, when each of the controlled components includes a pump assembly, the pump frequency of each of the pump assemblies is PI-regulated according to the difference in the liquid supply pressure of each of the pump assemblies by the controller of each of the controlled components, including: determining the change in the pump frequency of the pump assembly according to the following formula, and controlling the pump frequency of the pump assembly to change according to the change in the pump frequency of the pump assembly:

[0013]

[0014] Wherein, ΔFp(n) is the change in the pump frequency of each pump assembly, T1 is the reading cycle, T2 is the calculation cycle, Δe is the difference between the current actual fluid supply pressure and the target fluid supply pressure in each calculation cycle, e i It is the difference between the current actual supply pressure and the target supply pressure for each reading cycle, A is the proportional coefficient, and B is the integral coefficient.

[0015] In some embodiments, each of the controlled components includes a pump assembly; through the controller of each of the controlled components, combined with the transfer processing data of each of the controlled components and the target control instructions of each of the controlled components, the operation process of each of the controlled components is controlled, and it also includes: setting the initial value of the pump frequency of each of the pump components to the set frequency; during the operation process after each of the pump components is started with the initial value of the pump frequency of each of the pump components, when the target liquid supply pressure carried by the target control instruction of each of the pump components is 0: if the pump frequency of each of the pump components is 0, maintain the current state of each of the pump components; if the pump frequency of each of the pump components is not 0, then when the pump frequency of each of the pump components is less than or equal to the set frequency, control each of the pump components to shut down; when the pump frequency of each of the pump components is greater than the set frequency, control the pump frequency of each of the pump components to decrease from the set value to the set frequency, and then control each of the pump components to shut down.

[0016] In some embodiments, each of the controlled components includes a pump assembly, and an auxiliary measurement unit is also provided at each of the pump assemblies; the auxiliary measurement unit includes at least one of the following: a pump motor temperature measuring element, a filter signal measuring element, and a hydraulic valve signal measuring element; the auxiliary measurement unit of each of the pump assemblies is used to obtain an auxiliary measurement signal of each of the pump assemblies; the auxiliary measurement signal of each of the pump assemblies includes: at least one of the pump motor temperature, the filter signal, and the hydraulic valve signal of each of the pump assemblies; wherein the control method of the aircraft auxiliary cooling system further includes: through the controller of each of the pump assemblies, when the pump motor temperature of each of the pump assemblies is greater than or equal to a first set temperature, controlling the pump frequency of each of the pump assemblies to decrease from a set value to a set frequency; until the pump motor temperature of each of the pump assemblies decreases to less than or equal to a second set temperature, restoring the preset control of the pump frequency of each of the pump assemblies;

[0017] And / or, the control method of the aircraft auxiliary cooling system further includes: uploading the auxiliary measurement signal of each pump component to the communication unit through the adapter unit of each pump component, so as to transmit it to the IMA control unit through the communication unit; acquiring the auxiliary measurement signal of each pump component from the communication unit through the IMA control unit, and monitoring the auxiliary measurement signal of each pump component;

[0018] And / or, the operation process of each controlled component is controlled by the controller of each controlled component, including: when each controlled component includes a pump assembly, each pump assembly includes a first pump and a second pump; when controlling the operation of the first pump, if the first pump fails, switch to controlling the operation of the second pump: start the second pump, make the pump frequency of the second pump run at a set frequency for a set time, then restore the pump frequency of the second pump to the pump frequency of each pump assembly before the failure of the first pump, and then perform PI adjustment on the pump frequency of the second pump.

[0019] Therefore, the solution of the present invention is to set a universal control device mainly composed of a detection unit and a communication unit for multiple components that need to be controlled in the aircraft auxiliary cooling system (such as multiple pump assemblies, multiple heating units, etc.), the detection unit is used to receive the detection data sampled by the measuring element and the monitoring unit at each component in the multiple components and then upload it to the communication unit, the communication unit is used to receive the control instruction of the IMA and transmit it together with the corresponding detection data to the controller of the corresponding component through the corresponding adapter unit to realize the control of the multiple components; for the pump assembly in the multiple components, redundant control can be realized for the two pumps inside the pump assembly, and for different pump assemblies, when the controller of one pump assembly fails, cross control can be realized through the controllers of other pump assemblies; thus, by utilizing the universal control device composed of the communication unit and the IMA control unit, when the controller of one pump assembly fails, cross control can be realized through the controllers of other pump assemblies, so as to prevent the failure of the controller of the pump assembly on one side from affecting the cooling function of that side, and improve the reliability of the operation of the aircraft auxiliary cooling system.

[0020] Other features and advantages of the present invention will be set forth in the description which follows, and in part will be apparent from the description, or may be learned by practice of the present invention.

[0021] The technical solution of the present invention is further described in detail below through the accompanying drawings and embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 A schematic structural diagram of an embodiment of a control device for an auxiliary cooling system of an aircraft according to the present invention;

[0023] Figure 2 It is a control flow diagram of a multi-pump component control system;

[0024] Figure 3 It is a control flow diagram of a multi-heating unit control system;

[0025] Figure 4 It is a flow chart of a multi-pump component control method;

[0026] Figure 5 A schematic flow chart of an embodiment of a control method for an aircraft auxiliary cooling system of the present invention;

[0027] Figure 6 A schematic diagram of a flow chart of an embodiment of general processing of detection data in the method of the present invention;

[0028] Figure 7 A flow chart of an embodiment of the process of controlling the operation of each controlled component in the method of the present invention;

[0029] Figure 8A schematic flow chart of an embodiment of controlling the pump frequency of each pump assembly in the method of the present invention;

[0030] Fig. 9 The figure is a flow chart of an embodiment of monitoring the auxiliary measurement signal in the method of the present invention. DETAILED DESCRIPTION

[0031] 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.

[0032] Considering that for the pump components involved in each of the multiple flow paths of the aircraft auxiliary cooling system, each pump component is equipped with a set of controllers, and each controller has a main control module and a drive module; the controller's program failure, hardware failure, environmental, electromagnetic, voltage and other factors may affect the controller, causing the controller to fail. For the multiple flow paths of the aircraft auxiliary cooling system, if the controller of the pump component in one side (i.e., one flow path) fails, the refrigeration function on that side will fail, greatly reducing the reliability of the aircraft auxiliary cooling system. For example: the current control software and algorithm have a low degree of automation and insufficient reliability. If the controller of the pump component on one side fails, the cooling effect of the kitchen dining cart and large electronic equipment on that side cannot be guaranteed. However, there are no control devices and methods suitable for components such as pump components of the aircraft auxiliary cooling system in the relevant schemes.

[0033] Therefore, the scheme of the present invention proposes a control device for an aircraft auxiliary cooling system, specifically a liquid supply pressure automatic control device suitable for multiple components (such as multiple pump assemblies), which is provided with a universal detection unit, a switching unit and a communication unit, and calculates the actual liquid supply pressure according to the feedback results of the pressure measuring element and the flow monitoring unit, and through IMA (i.e., resident application control software) and other related control components, dynamically adjusts multiple pump assemblies and monitors fault status at the same time according to target instructions, thereby realizing fully automated control and status monitoring of aviation products, and the aircraft auxiliary cooling system IMA can exchange information with the aircraft IMA and perform corresponding processing to realize reliable operation of the entire aircraft.

[0034] According to an embodiment of the present invention, a control device for an aircraft auxiliary cooling system is provided. Figure 1The structure diagram of an embodiment of the device of the present invention is shown in FIG. The aircraft auxiliary cooling system has a controlled component, and the number of the controlled components is more than two; for each of the more than two controlled components, a sampling unit, a switching unit and a controller are provided; in the solution of the present invention, Figure 1 As shown, the control device of the aircraft auxiliary cooling system includes: a communication unit and an IMA control unit.

[0035] The sampling unit of each controlled component is used to sample the data at the location of the sampling unit of each controlled component as the detection data of each controlled component; thereby, the detection data of all the controlled components among more than two controlled components are obtained.

[0036] The IMA control unit is used to generate a target control instruction for each controlled component based on the detection data of each controlled component, and send the target control instruction of each controlled component to the switching unit of each controlled component through the communication unit, so as to transmit it to the controller of each controlled component via the switching unit of each controlled component to realize control of the operation process of each controlled component.

[0037] The switching unit of each of the controlled components is used to obtain the status data of the controller of each of the controlled components from the controller of each of the controlled components and transmit the status data to the communication unit.

[0038] The IMA control unit is also used to obtain status data of the controller of each of the controlled components from the communication unit, and determine whether the controller of each of the controlled components is faulty based on the status data of the controller of each of the controlled components; and if it is determined that the controller of each of the controlled components is faulty, it is recorded as a controller failure of the first controlled component, and the target control instruction of the first controlled component is sent to the switching unit of the second controlled component among the two or more controlled components through the communication unit; the second controlled component is one of the other controlled components among the two or more controlled components except the first controlled component.

[0039] The switching unit of the second controlled component is used to obtain the target control instruction of the first controlled component from the communication unit and transmit it to the controller of the second controlled component, so that the controller of the second controlled component can realize cross-control of the operation process of the first controlled component, prevent the failure of the controller of the first controlled component from affecting the cooling function of the first controlled component, and improve the reliability of the operation of the aircraft auxiliary cooling system.

[0040] The solution of the present invention is to set a universal control device consisting of a communication unit and an IMA control unit for multiple controlled components of the aircraft auxiliary refrigeration system, such as pump assemblies. When the controller of one pump assembly fails, cross-control can be achieved through the controllers of other pump assemblies for different pump assemblies, thereby preventing the failure of the controller of one pump assembly from affecting the cooling function of that side, thereby improving the reliability of the operation of the aircraft auxiliary cooling system.

[0041] like Figure 4 As shown, the control process of the pump assembly 1 also includes: f. The controllers of the pump assemblies on both sides regularly transmit status signals to IMA through the adapter unit 1 and the communication unit. If the controller of the pump assembly on one side fails, IMA immediately transmits the pressure and flow signals on that side to the controller of the pump assembly on the other side. The controller on the other side will dynamically control the two pump assemblies at the same time according to the feedback results of the relevant measuring elements.

[0042] In the scheme of the present invention, the controller of the pump assembly has a cross-control function. When the controller of the pump assembly on one side fails, the controller of the pump assembly on the other side can simultaneously control the operation of the pump assemblies on both sides and perform status monitoring. Each pump assembly has two refrigerant pumps. When one of the pumps is damaged, the other pump will provide a pressurization function, thereby realizing synchronous automatic control and fault status monitoring of multiple pump assemblies, greatly improving the intelligence and automation of the pumps, and greatly improving the operational reliability of the aircraft auxiliary cooling system.

[0043] In some embodiments, the control device of the aircraft auxiliary cooling system further includes: a detection unit.

[0044] The detection unit is used to receive the detection data of all the controlled components and upload the detection data to the communication unit, so as to transmit the detection data of all the controlled components to the IMA control unit through the communication unit.

[0045] The IMA control unit is also used to extract the detection data of each controlled component from the detection data of all the controlled components at the communication unit, generate a target control instruction for each controlled component according to the detection data of each controlled component, and send the target control instruction of each controlled component to the switching unit of each controlled component through the communication unit, so as to transmit the target control instruction of each controlled component to the switching unit of each controlled component through the communication unit, so as to transmit the target control instruction of each controlled component to the controller of each controlled component via the switching unit of each controlled component to realize control of the operation process of each controlled component.

[0046] The switching unit of each controlled component is used to obtain the detection data of each controlled component and the target control instruction of each controlled component from the communication unit; perform switching processing on the detection data of each controlled component to obtain the switching processing data of each controlled component; and transmit the switching processing data of each controlled component and the target control instruction of each controlled component to the controller of each controlled component.

[0047] The controller of each controlled component is used to obtain the transfer processing data of each controlled component and the target control instructions of each controlled component from the transfer unit of each controlled component; and control the operation process of each controlled component in combination with the transfer processing data of each controlled component and the target control instructions of each controlled component.

[0048] Specifically, in the solution of the present invention, the control device of the aircraft auxiliary cooling system includes: a detection unit, a communication unit and an IMA control unit.

[0049] The sampling unit of each controlled component is used to sample the data at the location of the sampling unit of each controlled component as the detection data of each controlled component; thereby, the detection data of all the controlled components among more than two controlled components are obtained.

[0050] The detection unit is used to receive the detection data of all the controlled components and upload the detection data to the communication unit, so as to transmit the detection data of all the controlled components to the IMA control unit through the communication unit.

[0051] The IMA control unit is used to extract the detection data of each controlled component from the detection data of all the controlled components at the communication unit, generate a target control instruction for each controlled component according to the detection data of each controlled component, and send the target control instruction of each controlled component to the switching unit of each controlled component through the communication unit, so as to transmit the target control instruction of each controlled component to the switching unit of each controlled component through the communication unit.

[0052] The switching unit of each controlled component is used to obtain the detection data of each controlled component and the target control instructions of each controlled component from the communication unit; perform switching processing on the detection data of each controlled component to obtain the switching processing data of each controlled component; and transmit the switching processing data of each controlled component and the target control instructions of each controlled component to the controller of each controlled component; and, obtain the status data of the controller of each controlled component from the controller of each controlled component and transmit it to the communication unit.

[0053] The controller of each controlled component is used to obtain the switching processing data of each controlled component from the switching unit of each controlled component; and control the operation process of each controlled component in combination with the switching processing data of each controlled component and the target control instruction of each controlled component.

[0054] The IMA control unit is also used to obtain status data of the controller of each of the controlled components from the communication unit, and determine whether the controller of each of the controlled components is faulty based on the status data of the controller of each of the controlled components; and if it is determined that the controller of each of the controlled components is faulty, it is recorded as a controller failure of the first controlled component, and the target control instruction of the first controlled component is sent to the switching unit of the second controlled component among the two or more controlled components through the communication unit; the second controlled component is one of the other controlled components among the two or more controlled components except the first controlled component.

[0055] The switching unit of the second controlled component is used to obtain the target control instruction of the first controlled component from the communication unit and transmit it to the controller of the second controlled component, so that the controller of the second controlled component can realize cross-control of the operation process of the first controlled component, prevent the failure of the controller of the first controlled component and affect the cooling function of the first controlled component, and improve the reliability of the operation of the aircraft auxiliary cooling system. That is to say, in the case that the controller of the first controlled component among the two or more controlled components fails, the controller of the second controlled component among the two or more controlled components can realize cross-control of the operation process of the first controlled component, prevent the failure of the controller of the first controlled component and affect the cooling function of the first controlled component, and improve the reliability of the operation of the aircraft auxiliary cooling system. In the case where each of the controlled components includes a pump assembly, in the event that the controller of the first pump assembly among the two or more pump assemblies fails, cross-control of the operation process of the first pump assembly is achieved through the controller of the second pump assembly among the two or more pump assemblies, thereby preventing the failure of the controller of the first pump assembly from affecting the cooling function of the first pump assembly, thereby improving the reliability of the operation of the aircraft auxiliary cooling system.

[0056] In the scheme of the present invention, a universal control device consisting of a detection unit, a communication unit and an IMA control unit is provided for multiple controlled components of the aircraft auxiliary refrigeration system, such as pump assemblies. When a controller of one pump assembly fails, cross-control can be achieved through the controllers of other pump assemblies for different pump assemblies, thereby preventing the failure of the controller of the pump assembly on one side from affecting the cooling function of that side, thereby improving the reliability of the operation of the aircraft auxiliary cooling system.

[0057] In some embodiments, each of the controlled components includes a pump assembly; in the case where each of the controlled components includes a pump assembly, the sampling unit of each of the pump assemblies includes at least one of: an inlet pressure measuring element, an outlet pressure measuring element, and a flow monitoring unit; the detection data of each of the pump assemblies includes: at least one of the inlet pressure, outlet pressure, and flow rate.

[0058] The switching unit of each controlled component performs switching processing on the detection data of each controlled component to obtain switching processing data of each controlled component, including: when each controlled component includes a pump assembly, the difference between the outlet pressure and the inlet pressure of each pump assembly is determined as the current actual liquid supply pressure of each pump assembly.

[0059] The controller of each of the controlled components controls the operation process of each of the controlled components in combination with the transfer processing data of each of the controlled components and the target control instructions of each of the controlled components, including: when each of the controlled components includes a pump component, determining the target fluid supply pressure of each of the pump components carried by the target control instructions of each of the pump components; and determining the fluid supply pressure difference between the target fluid supply pressure of each of the pump components and the current actual fluid supply pressure of each of the pump components to obtain the fluid supply pressure difference of each of the pump components. Furthermore, when each of the controlled components includes a pump component, the pump frequency of each of the pump components is PI-regulated according to the fluid supply pressure difference of each of the pump components.

[0060] Figure 2 FIG. 1 is a control flow diagram of a multi-pump assembly control system. The solution of the present invention is described in detail by taking two sets of pump assemblies as an example. Figure 2 As shown. Figure 2 As shown, the controlled components related to pump assembly 1 and the controlled components related to pump assembly 2 are set. For pump assembly 1, the detection unit monitors the data of its inlet pressure measuring element Pin1, outlet pressure measuring element Pout1, and flow monitoring unit F1 to obtain detection data, and uploads the detection data to the communication unit; the communication unit can transmit the detection data to the adapter unit 1 associated with the pump assembly 1 (including the controller).

[0061] Figure 4 FIG. 1 is a flow chart of a multi-pump component control method. Figure 4 As shown, the control process of the pump assembly 1 includes:

[0062] Step 1, data monitoring: Pump assembly 1 inlet pressure measuring element Pin1 monitors pressure P in1 , outlet pressure measuring element Pout1 monitors pressure P out1 , flow monitoring unit F1 monitors flow m q1 , the obtained detection data is uploaded to the detection unit, and the detection unit transmits the detection data to the switching unit 1 and IMA respectively via the communication unit.

[0063] Step 2: Target setting: IMA is based on the current monitoring flow m q1Set the target liquid supply pressure P1 and give the target instruction; the target instruction is transmitted to the adapter unit 1 through the communication unit, and the adapter unit 1 then transmits the target instruction to the pump assembly 1. Among them, IMA combines the current flight status, coolant temperature, and current monitoring flow to set a given value as the target liquid supply pressure P1. The given value is obtained from the results of previous experimental tests and then integrated into the IMA program; different flight states and monitoring flows will correspond to a certain target liquid supply pressure value. For example: the aircraft is in the cruising stage, the altitude is 40,000ft, and the coolant temperature is -9°C. At this time, IMA will combine the above three and find the corresponding target liquid supply pressure value in the program as the target liquid supply pressure P1. The adapter unit 1 calculates the current actual liquid supply pressure P through detection data. ac1 , as shown in formula (1):

[0064] P ac1 =P out1 -P in1 (1).

[0065] Where P ac1 is the current actual liquid supply pressure, in Pa; P out1 is the outlet pressure of pump assembly 1, in Pa; P in1 It is the inlet pressure of pump component 1, in Pa.

[0066] In the solution of the present invention, through IMA (resident application software) and other related control components, multiple pump components are dynamically adjusted and fault status monitored at the same time according to target instructions, so as to realize full automatic control and status monitoring of aviation products, and the aircraft auxiliary cooling system IMA can exchange information with the aircraft IMA and perform corresponding processing to realize reliable operation of the whole aircraft.

[0067] Step 3, PI adjustment: The adapter unit 1 adjusts the current actual liquid supply pressure P ac1 The pressure is transmitted to the pump assembly 1, and the controller of the pump assembly 1 compares the target liquid supply pressure P1 with the current actual liquid supply pressure P ac1 , the pump frequency H1 of the pump assembly 1 is PI-regulated.

[0068] Among them, after receiving the above detection data, the adapter unit 1 automatically processes and calculates the actual liquid pressurization of the pump component 1, and then transmits the detection data to the pump component 1. The adapter unit also transmits the target pressurization (such as the target liquid supply pressure of the pump component 1) instruction sent by IMA through the communication unit to the pump component 1; the pump component 1 compares the difference between the actual liquid pressurization and the target liquid pressurization, and performs PI dynamic adjustment on the pump motor frequency, thereby achieving precise control of the liquid heating amount. IMA can also monitor the status of each pump component. If the controller of the pump component on one side fails, the controller of the pump component on the other side can dynamically control the pump motor frequency according to the feedback results of the pressure measurement element and flow monitoring unit on that side, thereby realizing the cross-control function of the pump component. Among them, the pump assembly 1 integrates the pump assembly controller, which regularly feeds back the operation status information with the adapter unit 1. If the adapter unit 1 does not receive the normal operation information fed back by the pump assembly 1 controller or receives the control abnormality information fed back for several consecutive cycles (such as three consecutive cycles), it indicates that the pump assembly 1 control fails, and the adapter unit 1 sends the failure information and the calculated actual liquid supply pressure Pac1 of the pump assembly 1 to the IMA through the communication unit. After receiving the control failure information of the pump assembly 1, the IMA notifies the pump assembly 2 of the information and the actual liquid supply pressure P1 of the pump assembly 1 through the communication unit and the adapter unit 2. The pump assembly 2 compares the liquid target supply pressure P1 and the current actual liquid supply pressure Pac1, calculates the PI adjustment change value, and transmits the value to the pump assembly 1 through the referral unit 2, the communication unit, and the adapter unit 1 for control. In general, there are two flow paths in the aircraft auxiliary cooling system. If the controller of the pump assembly on one side of the flow path fails, the controller on the other side can control the pump assemblies on both sides at the same time to prevent the cooling function of one side from being affected by the failure of the controller, thereby greatly improving the operational reliability of the aircraft auxiliary cooling system.

[0069] In some embodiments, when each of the controlled components includes a pump assembly, the controller of each of the controlled components performs PI regulation on the pump frequency of each of the pump assemblies according to the difference in the liquid supply pressure of each of the pump assemblies, including: determining the change in the pump frequency of the pump assembly according to the following formula, and controlling the pump frequency of the pump assembly to change according to the change in the pump frequency of the pump assembly:

[0070]

[0071] Wherein, ΔFp(n) is the change in the pump frequency of each pump assembly, T1 is the reading cycle, T2 is the calculation cycle, Δe is the difference between the current actual fluid supply pressure and the target fluid supply pressure in each calculation cycle, e i It is the difference between the current actual supply pressure and the target supply pressure for each reading cycle, A is the proportional coefficient, and B is the integral coefficient.

[0072] like Figure 4 As shown, the control process of the pump assembly 1 also includes: in step 3, the calculation method of the change amount ΔFp(n) of the pump frequency of the pump assembly 1 is as shown in formula (2):

[0073]

[0074] Wherein, Δe=e(n)-e(n-1); e represents the difference between the actual liquid supply pressure and the target liquid supply pressure in each calculation cycle T2, in Pa, e=P ac1 -P1, current actual liquid supply pressure P ac1 , set the target liquid supply pressure P1; A is the proportional coefficient, B is the integral coefficient; e(n) represents the e calculated in the current calculation cycle T2, and e(n-1) represents the e calculated in the previous calculation cycle T2.

[0075] The liquid supply pressure deviation e is read once every 1 second (reading cycle T1) and calculated once every 10 seconds (calculation cycle T2). During normal operation, after the integral gain term is discretized, the change ΔFp(n) of the pump frequency of the pump assembly 1 is calculated as shown in formula (3):

[0076]

[0077] In the formula, e i The liquid supply pressure difference of each reading cycle T1 (i.e., the difference between the current actual liquid supply pressure and the target liquid supply pressure), in Pa. Δe represents the liquid supply pressure difference of each calculation cycle T2 (i.e., the difference between the current actual liquid supply pressure and the target liquid supply pressure). Here, the proportional coefficient can be A=-0.5, and the integral coefficient B=-1 (for illustration only).

[0078] In the solution of the present invention, the pump frequency is dynamically adjusted by PI according to the actual liquid pressurization amount and the target liquid pressurization amount, so as to improve the accuracy and adaptability of the liquid pressurization of the pump component and solve the problem of large deviation in the pressurization amount.

[0079] In some embodiments, each of the controlled components comprises a pump assembly.

[0080] In the case where each of the controlled components includes a pump assembly, the controller of each of the controlled components, in combination with the transfer processing data of each of the controlled components and the target control instruction of each of the controlled components, controls the operation process of each of the controlled components, and also includes: in the case where each of the controlled components includes a pump assembly, the initial value of the pump frequency of each of the pump assemblies is set to a set frequency (such as 20 Hz). Thereafter, in the operation process after each of the pump assemblies is started with the initial value of the pump frequency of each of the pump assemblies, in the case where the target liquid supply pressure carried by the target control instruction of each of the pump assemblies is 0: if the pump frequency of each of the pump assemblies is 0, the current state of each of the pump assemblies is maintained; if the pump frequency of each of the pump assemblies is not 0, then in the case where the pump frequency of each of the pump assemblies is less than or equal to the set frequency, each of the pump assemblies is controlled to shut down; in the case where the pump frequency of each of the pump assemblies is greater than the set frequency, the pump frequency of each of the pump assemblies is controlled to decrease to the set frequency by the set value, and then each of the pump assemblies is controlled to shut down.

[0081] like Figure 4 As shown, the control process of the pump assembly 1 also includes:

[0082] a. The initial value of the pump component frequency output is set to 20Hz.

[0083] b. When the IMA instruction sets the target liquid supply pressure to 0: if the pump frequency of pump assembly 1 is 0, it remains unchanged; if pump assembly 1 is running, the controller of pump assembly 1 must first determine the current pump operating frequency. If the current pump operating frequency of pump assembly 1 is ≤20Hz, it will be shut down directly. If the current pump operating frequency of pump assembly 1 is >20Hz, the pump frequency of pump assembly 1 is controlled to decrease by 2Hz to 20Hz, and then shut down.

[0084] In the scheme of the present invention, by controlling the state of each pump component in different ways according to the pump frequency range of each pump component (such as the range of 0HZ, the range of 0-20HZ, and the range above 20HZ) when the target liquid supply pressure carried by the target control instruction of each pump component is 0, on the one hand, it can avoid the pump frequency adjustment span of each pump component being too large, and on the other hand, it is conducive to slowly changing the environmental state to improve the user experience and protect the pump motor from being damaged due to excessive frequency changes.

[0085] In some embodiments, each of the controlled components includes a pump assembly; in the case where each of the controlled components includes a pump assembly, an auxiliary measurement unit is also provided at each of the pump assemblies; the auxiliary measurement unit includes at least one of the following: a pump motor temperature measuring element, a filter signal measuring element, and a hydraulic valve signal measuring element; the auxiliary measurement unit of each of the pump assemblies is used to obtain an auxiliary measurement signal of each of the pump assemblies; the auxiliary measurement signal of each of the pump assemblies includes: at least one of the pump motor temperature, the filter signal, and the hydraulic valve signal of each of the pump assemblies.

[0086] Wherein, in the control device of the aircraft auxiliary cooling system, it also includes: the controller of each pump assembly is also used to control the pump frequency of each pump assembly to decrease from a set value to a set frequency when the pump motor temperature of each pump assembly is greater than or equal to a first set temperature under the condition of preset control (i.e. normal control) of the pump frequency of each pump assembly; until the pump motor temperature of each pump assembly decreases to less than or equal to a second set temperature, the preset control (i.e. normal control) of the pump frequency of each pump assembly is restored, that is, the control before the pump frequency of each pump assembly is decreased from a set value is restored. Figure 4 As shown, the control process of the pump component 1 also includes: c. The pump component 1 monitors the temperature signal of the pump motor in real time. When the temperature is ≥80°C, the pump frequency decreases from 2Hz to 20Hz, and when the temperature is ≤60°C, normal control is restored.

[0087] In the scheme of the present invention, by controlling the pump frequency of each pump component according to the pump motor temperature of each pump component, the pump frequency can be matched with the pump motor temperature, which is beneficial to protecting each pump component to extend the service life of each pump component.

[0088] The control device of the aircraft auxiliary cooling system also includes:

[0089] The adapter unit of each pump assembly is also used to upload the auxiliary measurement signal of each pump assembly to the communication unit, so as to be transmitted to the IMA control unit via the communication unit.

[0090] The IMA control unit is further used to obtain the auxiliary measurement signal of each pump component from the communication unit and monitor the auxiliary measurement signal of each pump component.

[0091] For example: the IMA control unit is also used to determine whether the temperature of each pump component is normal according to the temperature signal of each pump component, determine whether the filter of each pump component is normal according to the filter signal of each pump component, and determine whether the hydraulic valve of each pump component is normal according to the hydraulic valve signal of each pump component, so as to obtain the fault data of each pump component; and upload the fault data of each pump component to the communication unit.

[0092] The communication unit is also used to transmit the fault data of each pump component to the IMA control unit.

[0093] The IMA control unit is also used to obtain fault data of each pump component from the communication unit, generate a fault control instruction for each pump component according to the fault data of each pump component, and transmit the fault control instruction of each pump component to the communication unit; wherein, in the case where each of the controlled components includes a pump component, in the case where the controller of one of the two pump components fails, the IMA control unit generates a fault control instruction for controlling the operation process of one pump component by using the controller of the other of the two pump components based on the data of the failure of the controller of one of the pump components in the fault data of the pump component.

[0094] The communication unit is also used to transmit a fault control instruction for controlling the operation process of one of the two pump assemblies to the switching unit of the other of the two pump assemblies.

[0095] The adapter unit of the other pump assembly of the two pump assemblies is also used to obtain a fault control instruction for controlling the operation process of one pump assembly from the communication unit, and transmit it to the controller of the other pump assembly; thereby, the operation process of one pump assembly is controlled through the adapter unit of the other pump assembly, the communication unit, the adapter unit of one pump assembly, and the pump assembly.

[0096] like Figure 4 As shown, the control process of the pump component 1 also includes: d. The pump component 1 transmits the signals or fault feedback of the pump motor temperature, filter, pressure relief valve, etc. to the communication unit through the adapter unit 1, and then transmits it to the IMA, so as to realize the aircraft auxiliary cooling system pump component fully automatic safety pressure relief, coolant filtration, pressure stabilization, filter bypass, pump motor overheat protection, pump outlet overpressure protection, pump outlet low pressure protection, fault monitoring, fault storage data and other functions.

[0097] like Figure 2As shown, the pump group 1 monitors the operating status of the pump motor, filter 1, pressure relief valve 1, etc. in real time (such as monitoring the pump motor temperature measuring element PT1, filter 1, and pressure relief valve 1 signal), and transmits it to the adapter unit 1. The adapter unit 1 feeds back the data and faults (such as the pump component 1 body temperature, faults, etc.) to the IMA through the communication unit, so as to realize the aircraft auxiliary cooling system pump component fully automatic safety pressure relief, coolant filtration, pressure stabilization, filter bypass, pump motor overheat protection, pump outlet overpressure protection, pump outlet low pressure protection, fault monitoring, fault storage data and other functions, not only to realize the aircraft auxiliary cooling system The controlled components (such as the pump component described here) are fully automatically controlled and monitored, and related processing is performed according to the status, and information exchange can be realized with the aircraft IMA through the aircraft auxiliary cooling system IMA, thereby improving the reliability of the entire aircraft operation. For example: if the pump outlet pressure exceeds a given safety value, the pump group controls the pressure relief valve to open to realize automatic safety pressure relief function and outlet overpressure protection; if the filter realizes refrigerant filtration, the filter bypass valve is controlled to realize the filtration bypass function; if the pump motor is overheated, the pump component controls the pump frequency to be reduced to 20Hz, and when the motor temperature drops to the normal value, the pump frequency is restored and PI control is performed; if the pump outlet pressure is too low, the pump frequency is gradually increased; the fault information monitored by the pump component controller will be fed back to the IMA storage.

[0098] In the control device of the aircraft auxiliary cooling system, the controller of each controlled component realizes control over the operation process of each controlled component, including: when each controlled component includes a pump assembly, each pump assembly includes a first pump and a second pump; when controlling the operation of the first pump, if the first pump fails, switch to controlling the operation of the second pump: start the second pump, make the pump frequency of the second pump run at a set frequency for a set time, then restore the pump frequency of the second pump to the pump frequency of each pump assembly before the failure of the first pump, and then perform PI regulation on the pump frequency of the second pump.

[0099] like Figure 4 As shown, the control process of the pump component 1 also includes: e. The pump component includes two pumps, one for backup and one for use (that is, during operation, pump 1 is started and pump 2 is on backup), and the controller monitors the pump operation status or fault signal in turn and regularly (such as every 20 minutes); if pump 1 is damaged during operation, the controller will immediately start pump 2 and first control it to run at 20Hz for 30s, then restore to the frequency before pump 1 was damaged, and finally PI dynamically adjusts the frequency.

[0100] In the scheme of the present invention, by providing a universal control device consisting of a detection unit, a communication unit and an IMA control unit for multiple controlled components of the aircraft auxiliary refrigeration system, such as a pump assembly, redundant control can be achieved for the two pumps inside the pump assembly, thereby improving the reliability of the operation of the aircraft auxiliary cooling system.

[0101] In the scheme of the present invention, the multi-pump assembly control system is composed of a pressure measuring element, a flow monitoring unit, a detection unit, a communication unit, a switching unit, a pump assembly and an IMA, which can realize automatic and independent dynamic adjustment and fault status monitoring of the multi-pump assembly (which can be replaced by a bypass valve, a radiator, a heating unit, etc.), greatly improving the intelligence and automation of the system, and at the same time ensuring the high accuracy of relevant data. In addition, for a single set of pump assemblies (two pumps, one for backup and one for use), if pump 1 fails, pump 2 can be started to provide a pressurization function; when the controller of a pump assembly on one side is damaged, the pump assembly on the other side can control and monitor the status of the pump assembly on that side, greatly improving the reliability of system operation.

[0102] For pump assembly 2 (including controller), the related controlled components are inlet pressure measuring element Pin2, outlet pressure measuring element Pout2, flow monitoring unit F2, adapter unit 2, pump motor temperature measuring element PT2, filter 2, hydraulic valve 2, and related data include pump assembly 2 body temperature and faults, pump assembly 2 target liquid supply pressure, etc. Other signal transmission processes refer to pump assembly 1. The control process of pump assembly 2 refers to pump assembly 1, and only the related components are different.

[0103] In the scheme of the present invention, IMA can realize automatic, independent and dynamic control of multiple pump assemblies, and monitor the status of temperature, faults, etc., so as to improve the intelligent and automatic control of the pump assembly system, and ensure the accuracy of the liquid supply pressure. In addition, the pump assembly has the functions of one pump for backup and one for use, and the cross-control of the controller, which greatly improves the reliability of the system operation. In specific applications, the operating effects under different refrigeration conditions and system operating conditions should be tested in detail, and the specific parameters in the control logic should be adjusted to ensure that the system can operate efficiently and stably under different working conditions. In addition, the relevant measuring elements and monitoring elements can be adjusted to realize the automatic control of other components (such as bypass valves, multi-flow path heat dissipation), realize the full automatic control of the pump assembly of the aircraft auxiliary cooling system, and meet the requirements of aviation generalization and reliability design. It has the functions of liquid pressurization, safety pressure relief, refrigerant filtration, filter bypass, voltage stabilization, pump motor overheat protection, controller overheat protection, pump outlet overpressure protection, pump outlet low pressure protection, automatic control of liquid supply pressure, fault monitoring, fault storage data, controller cross control, etc.

[0104] It should be noted that, although the scheme of the present invention has been described above with reference to various embodiments, it should be understood that the system and the device are only examples, and various processes and components can be appropriately omitted, replaced or added in each device. For example, the system can be arranged with three or more pump components. In addition, the proportional coefficient and the integral coefficient in the PI regulation should be adjusted according to the detailed test conditions, and the relevant temperature measuring elements, pressure measuring elements and other components can be adjusted to monitor the system status.

[0105] In some embodiments, each of the controlled components includes any one of a pump assembly, a heating unit, a radiator, and a bypass valve.

[0106] exist Figure 2 and Figure 4 In the example shown, the pump assembly can also be replaced by a heating unit, bypass valve and other related controlled components, and the control logic and measuring elements need to be adjusted accordingly. The pump assembly can be replaced by a heating unit and other aircraft auxiliary cooling system related controlled components to meet the aviation universal design requirements. It can be used by replacing related controlled components and control logic, and reliability can be improved. Figure 3 This is a control flow diagram of a multi-heating unit control system. Figure 3 As shown, heating unit 1, heating unit 2 and heating unit 3 are provided. For heating unit 1 (including controller), the related controlled components are inlet temperature measuring element PTin1, outlet temperature measuring element PTout1, flow monitoring unit F1, switching unit 1, heater top temperature measuring elements PT1 and PT2, and the related data include heating unit 1 body temperature and fault, heating unit 1 control instructions, etc., and its signal transmission process refers to pump assembly 1. The related controlled components of heating unit 2 and heating unit 3 refer to the related controlled components of heating unit 1.

[0107] A liquid supply pressure control scheme applicable to multiple pump assemblies is proposed in the scheme of the present invention, and a pressure measuring element (replaceable controlled component), a flow monitoring unit (replaceable controlled component), a detection unit, a communication unit, a switching unit, a pump assembly (replaceable controlled component) and an IMA are set. Taking the pressure measuring element, the flow monitoring unit and the pump assembly as an example, the actual liquid supply pressure is calculated according to the feedback results of the pressure measuring element and the flow monitoring unit, and the pump motor frequency is dynamically adjusted by PI according to the target liquid supply pressure set by IMA, so as to achieve the purpose of simultaneous, independent and automatic accurate control of multiple pump assemblies; the problem that the target liquid supply pressure does not match the actual liquid supply pressure, resulting in a large error in the liquid pressurization amount and the inability to ensure the accuracy of the relevant data can be solved. At the same time, the IMA can also realize the monitoring of the temperature, fault and other states of the pump assembly, and the controller of the pump assembly has a cross-control function, which greatly improves the reliability of the operation of the aircraft auxiliary cooling system.

[0108] There is no related solution that has a multi-controlled component control device and method suitable for an aircraft auxiliary cooling system. The solution of the present invention can realize full-automatic control and status monitoring of multiple controlled components that meet aviation standards, and realize information interaction with the whole machine, so as to handle different situations according to different flight states. In addition, the control device adopts a universal design (aerospace design requirements), and the control of different controlled components only needs to adjust the relevant control logic.

[0109] By adopting the technical solution of the present invention, a general control device mainly composed of a detection unit and a communication unit is set for multiple components that need to be controlled in the aircraft auxiliary cooling system (such as multiple pump assemblies, multiple heating units, etc.), the detection unit is used to receive the detection data sampled by the measuring element and the monitoring unit at each component in the multiple components and then upload it to the communication unit, the communication unit is used to receive the control instruction of the IMA and transmit it together with the corresponding detection data to the controller of the corresponding component through the corresponding adapter unit to realize the control of the multiple components; for the pump assembly in the multiple components, redundant control can be realized for the two pumps inside the pump assembly, and for different pump assemblies, when the controller of one pump assembly fails, cross control can be realized through the controllers of other pump assemblies; thus, by utilizing the general control device composed of the communication unit and the IMA control unit, when the controller of one pump assembly fails, cross control can be realized through the controllers of other pump assemblies, so as to prevent the failure of the controller of the pump assembly on one side from affecting the cooling function of that side, and improve the reliability of the operation of the aircraft auxiliary cooling system.

[0110] According to an embodiment of the present invention, an aircraft auxiliary cooling system corresponding to the control device of the aircraft auxiliary cooling system is also provided. The aircraft auxiliary cooling system may include: the control device of the aircraft auxiliary cooling system described above.

[0111] Since the processing and functions implemented by the aircraft auxiliary cooling system of this embodiment basically correspond to the embodiments, principles and examples of the control device, for the details not fully described in this embodiment, please refer to the relevant descriptions in the aforementioned embodiments and will not be repeated here.

[0112] According to an embodiment of the present invention, a control method for an aircraft auxiliary cooling system corresponding to the aircraft auxiliary cooling system is also provided, such as Figure 5 The flowchart of an embodiment of the method of the present invention is shown in FIG. The control method of the aircraft auxiliary cooling system may include: steps S110 to S150.

[0113] In step S110, the sampling unit of each controlled component samples the data at the location of the sampling unit of each controlled component as the detection data of each controlled component; thereby, the detection data of all the controlled components among more than two controlled components are obtained.

[0114] At step S120, the IMA control unit generates a target control instruction for each controlled component according to the detection data of each controlled component, and sends the target control instruction of each controlled component to the switching unit of each controlled component through the communication unit, so as to be transmitted to the controller of each controlled component via the switching unit of each controlled component to realize control of the operation process of each controlled component.

[0115] In step S130, the state data of the controller of each controlled component is obtained from the controller of each controlled component through the switching unit of each controlled component and transmitted to the communication unit.

[0116] At step S140, the status data of the controller of each of the controlled components is obtained from the communication unit through the IMA control unit, and whether the controller of each of the controlled components is faulty is determined based on the status data of the controller of each of the controlled components; and if it is determined that the controller of each of the controlled components is faulty, it is recorded as a controller failure of the first controlled component, and the target control instruction of the first controlled component is sent to the switching unit of the second controlled component among the two or more controlled components through the communication unit; the second controlled component is one of the other controlled components among the two or more controlled components except the first controlled component.

[0117] At step S150, the target control instruction of the first controlled component is obtained from the communication unit through the switching unit of the second controlled component and transmitted to the controller of the second controlled component, so that the controller of the second controlled component can realize cross-control of the operation process of the first controlled component, thereby preventing the failure of the controller of the first controlled component from affecting the cooling function of the first controlled component, and improving the reliability of the operation of the aircraft auxiliary cooling system.

[0118] The solution of the present invention is to set a universal control device consisting of a communication unit and an IMA control unit for multiple controlled components of the aircraft auxiliary refrigeration system, such as pump assemblies. When the controller of one pump assembly fails, cross-control can be achieved through the controllers of other pump assemblies for different pump assemblies, thereby preventing the failure of the controller of one pump assembly from affecting the cooling function of that side, thereby improving the reliability of the operation of the aircraft auxiliary cooling system.

[0119] like Figure 4 As shown, the control process of the pump assembly 1 also includes: f. The controllers of the pump assemblies on both sides regularly transmit status signals to IMA through the adapter unit 1 and the communication unit. If the controller of the pump assembly on one side fails, IMA immediately transmits the pressure and flow signals on that side to the controller of the pump assembly on the other side. The controller on the other side will dynamically control the two pump assemblies at the same time according to the feedback results of the relevant measuring elements.

[0120] In the scheme of the present invention, the controller of the pump assembly has a cross-control function. When the controller of the pump assembly on one side fails, the controller of the pump assembly on the other side can simultaneously control the operation of the pump assemblies on both sides and perform status monitoring. Each pump assembly has two refrigerant pumps. When one of the pumps is damaged, the other pump will provide a pressurization function, thereby realizing synchronous automatic control and fault status monitoring of multiple pump assemblies, greatly improving the intelligence and automation of the pumps, and greatly improving the operational reliability of the aircraft auxiliary cooling system.

[0121] In some embodiments, the control method of the aircraft auxiliary cooling system described in the solution of the present invention also includes: a process of performing general processing on the detection data.

[0122] Combine the following Figure 6 The flowchart of an embodiment of the method of the present invention for general processing of detection data further illustrates the specific process of general processing of detection data, including: step S210 to step S240.

[0123] Step S210: receiving the detection data of all the controlled components through the detection unit and uploading the data to the communication unit, so as to transmit the detection data of all the controlled components to the IMA control unit through the communication unit.

[0124] Step S220, through the IMA control unit, extract the detection data of each controlled component from the detection data of all the controlled components at the communication unit, generate a target control instruction for each controlled component according to the detection data of each controlled component, and send the target control instruction of each controlled component to the switching unit of each controlled component through the communication unit, so as to transmit the target control instruction of each controlled component to the switching unit of each controlled component through the communication unit, so as to transmit it to the controller of each controlled component via the switching unit of each controlled component to realize control of the operation process of each controlled component.

[0125] Step S230, obtaining the detection data of each controlled component and the target control instruction of each controlled component from the communication unit through the switching unit of each controlled component; performing switching processing on the detection data of each controlled component to obtain the switching processing data of each controlled component; and transmitting the switching processing data of each controlled component and the target control instruction of each controlled component to the controller of each controlled component.

[0126] Step S240, through the controller of each controlled component, obtain the transfer processing data of each controlled component and the target control instruction of each controlled component from the transfer unit of each controlled component; and control the operation process of each controlled component in combination with the transfer processing data of each controlled component and the target control instruction of each controlled component.

[0127] In the scheme of the present invention, a universal control device consisting of a detection unit, a communication unit and an IMA control unit is provided for multiple controlled components of the aircraft auxiliary refrigeration system, such as pump assemblies. When a controller of one pump assembly fails, cross-control can be achieved through the controllers of other pump assemblies for different pump assemblies, thereby preventing the failure of the controller of the pump assembly on one side from affecting the cooling function of that side, thereby improving the reliability of the operation of the aircraft auxiliary cooling system.

[0128] In some embodiments, each of the controlled components includes a pump assembly; in the case where each of the controlled components includes a pump assembly, the sampling unit of each of the pump assemblies includes at least one of: an inlet pressure measuring element, an outlet pressure measuring element, and a flow monitoring unit; the detection data of each of the pump assemblies includes: at least one of the inlet pressure, outlet pressure, and flow rate.

[0129] In step S230, the detection data of each controlled component is transferred and processed by the transfer unit of each controlled component to obtain the transferred processing data of each controlled component, including: when each controlled component includes a pump assembly, the difference between the outlet pressure and the inlet pressure of each pump assembly is determined as the current actual liquid supply pressure of each pump assembly.

[0130] Step S240 controls the operation of each controlled component through the controller of each controlled component, in combination with the transfer processing data of each controlled component and the target control instruction of each controlled component. Please refer to the following exemplary description for the specific process.

[0131] Combine the following Figure 7 The flowchart of an embodiment of the method of the present invention for controlling the operation process of each of the controlled components further illustrates the specific process of controlling the operation process of each of the controlled components in step S240, including: step S310 to step S320.

[0132] Step S310, when each of the controlled components includes a pump assembly, determines the target fluid supply pressure of each pump assembly carried by the target control instruction of each pump assembly; and determines the fluid supply pressure difference between the target fluid supply pressure of each pump assembly and the current actual fluid supply pressure of each pump assembly to obtain the fluid supply pressure difference of each pump assembly.

[0133] Step S320: When each of the controlled components includes a pump assembly, PI adjustment is performed on the pump frequency of each of the pump assemblies according to the difference in the liquid supply pressure of each of the pump assemblies.

[0134] Figure 2 FIG. 1 is a control flow diagram of a multi-pump assembly control system. The solution of the present invention is described in detail by taking two sets of pump assemblies as an example. Figure 2 As shown. Figure 2 As shown, the controlled components related to pump assembly 1 and the controlled components related to pump assembly 2 are set. For pump assembly 1, the detection unit monitors the data of its inlet pressure measuring element Pin1, outlet pressure measuring element Pout1, and flow monitoring unit F1 to obtain detection data, and uploads the detection data to the communication unit; the communication unit can transmit the detection data to the adapter unit 1 associated with the pump assembly 1 (including the controller).

[0135] Figure 4 FIG. 1 is a flow chart of a multi-pump component control method. Figure 4 As shown, the control process of the pump assembly 1 includes:

[0136] Step 1, data monitoring: Pump assembly 1 inlet pressure measuring element Pin1 monitors pressure P in1 , outlet pressure measuring element Pout1 monitors pressure P out1 , flow monitoring unit F1 monitors flow m q1 , the obtained detection data is uploaded to the detection unit, and the detection unit transmits the detection data to the switching unit 1 and IMA respectively via the communication unit.

[0137] Step 2: Target setting: IMA is based on the current monitoring flow m q1 Set the target liquid supply pressure P1 and give the target instruction; the target instruction is transmitted to the adapter unit 1 through the communication unit, and the adapter unit 1 then transmits the target instruction to the pump assembly 1. Among them, IMA combines the current flight status, coolant temperature, and current monitoring flow to set a given value as the target liquid supply pressure P1. The given value is obtained from the results of previous experimental tests and then integrated into the IMA program; different flight states and monitoring flows will correspond to a certain target liquid supply pressure value. For example: the aircraft is in the cruising stage, the altitude is 40,000ft, and the coolant temperature is -9°C. At this time, IMA will combine the above three and find the corresponding target liquid supply pressure value in the program as the target liquid supply pressure P1. The adapter unit 1 calculates the current actual liquid supply pressure P through detection data. ac1 , as shown in formula (1):

[0138] P ac1 =P out1 -P in1 (1).

[0139] Where P ac1 is the current actual liquid supply pressure, in Pa; P out1 is the outlet pressure of pump assembly 1, in Pa; P in1 It is the inlet pressure of pump component 1, in Pa.

[0140] In the solution of the present invention, through IMA (resident application software) and other related control components, multiple pump components are dynamically adjusted and fault status monitored at the same time according to target instructions, so as to realize full automatic control and status monitoring of aviation products, and the aircraft auxiliary cooling system IMA can exchange information with the aircraft IMA and perform corresponding processing to realize reliable operation of the whole aircraft.

[0141] Step 3, PI adjustment: The adapter unit 1 adjusts the current actual liquid supply pressure P ac1 The pressure is transmitted to the pump assembly 1, and the controller of the pump assembly 1 compares the target liquid supply pressure P1 with the current actual liquid supply pressure P ac1 , the pump frequency H1 of the pump assembly 1 is PI-regulated.

[0142] Among them, after receiving the above detection data, the adapter unit 1 automatically processes and calculates the actual liquid pressurization of the pump component 1, and then transmits the detection data to the pump component 1. The adapter unit also transmits the target pressurization (such as the target liquid supply pressure of the pump component 1) instruction sent by IMA through the communication unit to the pump component 1; the pump component 1 compares the difference between the actual liquid pressurization and the target liquid pressurization, and performs PI dynamic adjustment on the pump motor frequency, thereby achieving precise control of the liquid heating amount. IMA can also monitor the status of each pump component. If the controller of the pump component on one side fails, the controller of the pump component on the other side can dynamically control the pump motor frequency according to the feedback results of the pressure measurement element and flow monitoring unit on that side, thereby realizing the cross-control function of the pump component. Among them, the pump assembly 1 integrates the pump assembly controller, which regularly feeds back the operation status information with the adapter unit 1. If the adapter unit 1 does not receive the normal operation information fed back by the pump assembly 1 controller or receives the control abnormality information fed back for several consecutive cycles (such as three consecutive cycles), it indicates that the pump assembly 1 control fails, and the adapter unit 1 sends the failure information and the calculated actual liquid supply pressure Pac1 of the pump assembly 1 to the IMA through the communication unit. After receiving the control failure information of the pump assembly 1, the IMA notifies the pump assembly 2 of the information and the actual liquid supply pressure P1 of the pump assembly 1 through the communication unit and the adapter unit 2. The pump assembly 2 compares the liquid target supply pressure P1 and the current actual liquid supply pressure Pac1, calculates the PI adjustment change value, and transmits the value to the pump assembly 1 through the referral unit 2, the communication unit, and the adapter unit 1 for control. In general, there are two flow paths in the aircraft auxiliary cooling system. If the controller of the pump assembly on one side of the flow path fails, the controller on the other side can control the pump assemblies on both sides at the same time to prevent the cooling function of one side from being affected by the failure of the controller, thereby greatly improving the operational reliability of the aircraft auxiliary cooling system.

[0143] In some embodiments, when each of the controlled components includes a pump assembly, in step S320, the controller of each of the controlled components performs PI regulation on the pump frequency of each of the pump assemblies according to the difference in the liquid supply pressure of each of the pump assemblies, including: determining the change in the pump frequency of the pump assembly according to the following formula, and controlling the pump frequency of the pump assembly to change according to the change in the pump frequency of the pump assembly:

[0144]

[0145] Wherein, ΔFp(n) is the change in the pump frequency of each pump assembly, T1 is the reading cycle, T2 is the calculation cycle, Δe is the difference between the current actual fluid supply pressure and the target fluid supply pressure in each calculation cycle, e i It is the difference between the current actual supply pressure and the target supply pressure for each reading cycle, A is the proportional coefficient, and B is the integral coefficient.

[0146] like Figure 4 As shown, the control process of the pump assembly 1 also includes: in step 3, the calculation method of the change amount ΔFp(n) of the pump frequency of the pump assembly 1 is as shown in formula (2):

[0147]

[0148] Wherein, Δe=e(n)-e(n-1); e represents the difference between the actual liquid supply pressure and the target liquid supply pressure in each calculation cycle T2, in Pa, e=P ac1 -P1, current actual liquid supply pressure P ac1 , set the target liquid supply pressure P1; A is the proportional coefficient, B is the integral coefficient; e(n) represents the e calculated in the current calculation cycle T2, and e(n-1) represents the e calculated in the previous calculation cycle T2.

[0149] The liquid supply pressure deviation e is read once every 1 second (reading cycle T1) and calculated once every 10 seconds (calculation cycle T2). During normal operation, after the integral gain term is discretized, the change ΔFp(n) of the pump frequency of the pump assembly 1 is calculated as shown in formula (3):

[0150]

[0151] In the formula, e i The liquid supply pressure difference of each reading cycle T1 (i.e., the difference between the current actual liquid supply pressure and the target liquid supply pressure), in Pa. Δe represents the liquid supply pressure difference of each calculation cycle T2 (i.e., the difference between the current actual liquid supply pressure and the target liquid supply pressure). Here, the proportional coefficient can be A=-0.5, and the integral coefficient B=-1 (for illustration only).

[0152] In the solution of the present invention, the pump frequency is dynamically adjusted by PI according to the actual liquid pressurization amount and the target liquid pressurization amount, so as to improve the accuracy and adaptability of the liquid pressurization of the pump component and solve the problem of large deviation in the pressurization amount.

[0153] In some embodiments, each of the controlled components comprises a pump assembly.

[0154] In the case where each of the controlled components includes a pump assembly, in step S240, the operation process of each of the controlled components is controlled by the controller of each of the controlled components, in combination with the transfer processing data of each of the controlled components and the target control instructions of each of the controlled components, and also includes: the process of controlling the pump frequency of each of the pump assemblies.

[0155] Combine the following Figure 8The flowchart of an embodiment of controlling the pump frequency of each pump component in the method of the present invention further illustrates the specific process of controlling the pump frequency of each pump component in step S240, including: step S410 to step S420.

[0156] Step S410, when each of the controlled components includes a pump assembly, the initial value of the pump frequency of each of the pump assemblies is set to a set frequency (eg, 20 Hz).

[0157] Step S420, during the operation of each pump component after it is started with the initial value of the pump frequency of each pump component, when the target liquid supply pressure carried by the target control instruction of each pump component is 0: if the pump frequency of each pump component is 0, maintain the current state of each pump component; if the pump frequency of each pump component is not 0, then when the pump frequency of each pump component is less than or equal to the set frequency, control each pump component to shut down; when the pump frequency of each pump component is greater than the set frequency, control the pump frequency of each pump component to decrease from the set value to the set frequency, and then control each pump component to shut down.

[0158] like Figure 4 As shown, the control process of the pump assembly 1 also includes:

[0159] a. The initial value of the pump component frequency output is set to 20Hz.

[0160] b. When the IMA instruction sets the target liquid supply pressure to 0: if the pump frequency of pump assembly 1 is 0, it remains unchanged; if pump assembly 1 is running, the controller of pump assembly 1 must first determine the current pump operating frequency. If the current pump operating frequency of pump assembly 1 is ≤20Hz, it will be shut down directly. If the current pump operating frequency of pump assembly 1 is >20Hz, the pump frequency of pump assembly 1 is controlled to decrease by 2Hz to 20Hz, and then shut down.

[0161] In the scheme of the present invention, by controlling the state of each pump component in different ways according to the pump frequency range of each pump component (such as the range of 0HZ, the range of 0-20HZ, and the range above 20HZ) when the target liquid supply pressure carried by the target control instruction of each pump component is 0, on the one hand, it can avoid the pump frequency adjustment span of each pump component being too large, and on the other hand, it is conducive to slowly changing the environmental state to improve the user experience and protect the pump motor from being damaged due to excessive frequency changes.

[0162] In some embodiments, each of the controlled components includes a pump assembly; in the case where each of the controlled components includes a pump assembly, an auxiliary measurement unit is also provided at each of the pump assemblies; the auxiliary measurement unit includes at least one of the following: a pump motor temperature measuring element, a filter signal measuring element, and a hydraulic valve signal measuring element; the auxiliary measurement unit of each of the pump assemblies is used to obtain an auxiliary measurement signal of each of the pump assemblies; the auxiliary measurement signal of each of the pump assemblies includes: at least one of the pump motor temperature, the filter signal, and the hydraulic valve signal of each of the pump assemblies.

[0163] Among them, the control method of the aircraft auxiliary cooling system also includes: through the controller of each of the pump components, when the pump motor temperature of each of the pump components is greater than or equal to the first set temperature, controlling the pump frequency of each of the pump components to decrease from a set value to a set frequency; until the pump motor temperature of each of the pump components drops to less than or equal to the second set temperature, restoring the preset control (i.e., normal control) of the pump frequency of each of the pump components; wherein the first set temperature is such as 80°C and the second set temperature is such as 60°C.

[0164] like Figure 4 As shown, the control process of the pump component 1 also includes: c. The pump component 1 monitors the temperature signal of the pump motor in real time. When the temperature is ≥80°C, the pump frequency decreases from 2Hz to 20Hz, and when the temperature is ≤60°C, normal control is restored.

[0165] In the scheme of the present invention, by controlling the pump frequency of each pump component according to the pump motor temperature of each pump component, the pump frequency can be matched with the pump motor temperature, which is beneficial to protecting each pump component to extend the service life of each pump component.

[0166] The control method of the aircraft auxiliary cooling system also includes: a process of monitoring the auxiliary measurement signal.

[0167] Combine the following Fig. 9 The flowchart of an embodiment of monitoring the auxiliary measurement signal in the method of the present invention further illustrates the specific process of monitoring the auxiliary measurement signal, including: step S510 to step S520.

[0168] Step S510: Upload the auxiliary measurement signal of each pump component to the communication unit through the adapter unit of each pump component, so as to be transmitted to the IMA control unit through the communication unit.

[0169] Step S520: Obtain the auxiliary measurement signal of each pump component from the communication unit through the IMA control unit, and monitor the auxiliary measurement signal of each pump component.

[0170] For example: the IMA control unit is also used to determine whether the temperature of each pump component is normal according to the temperature signal of each pump component, determine whether the filter of each pump component is normal according to the filter signal of each pump component, and determine whether the hydraulic valve of each pump component is normal according to the hydraulic valve signal of each pump component, so as to obtain the fault data of each pump component; and upload the fault data of each pump component to the communication unit.

[0171] The communication unit is also used to transmit the fault data of each pump component to the IMA control unit.

[0172] The IMA control unit is also used to obtain fault data of each pump component from the communication unit, generate a fault control instruction for each pump component according to the fault data of each pump component, and transmit the fault control instruction of each pump component to the communication unit; wherein, in the case where each of the controlled components includes a pump component, in the case where the controller of one of the two pump components fails, the IMA control unit generates a fault control instruction for controlling the operation process of one pump component by using the controller of the other of the two pump components based on the data of the failure of the controller of one of the pump components in the fault data of the pump component.

[0173] The communication unit is also used to transmit a fault control instruction for controlling the operation process of one of the two pump assemblies to the switching unit of the other of the two pump assemblies.

[0174] The adapter unit of the other pump assembly of the two pump assemblies is also used to obtain a fault control instruction for controlling the operation process of one pump assembly from the communication unit, and transmit it to the controller of the other pump assembly; thereby, the operation process of one pump assembly is controlled through the adapter unit of the other pump assembly, the communication unit, the adapter unit of one pump assembly, and the pump assembly.

[0175] like Figure 4 As shown, the control process of the pump component 1 also includes: d. The pump component 1 transmits the signals or fault feedback of the pump motor temperature, filter, pressure relief valve, etc. to the communication unit through the adapter unit 1, and then transmits it to the IMA, so as to realize the aircraft auxiliary cooling system pump component fully automatic safety pressure relief, coolant filtration, pressure stabilization, filter bypass, pump motor overheat protection, pump outlet overpressure protection, pump outlet low pressure protection, fault monitoring, fault storage data and other functions.

[0176] like Figure 2As shown, the pump group 1 monitors the operating status of the pump motor, filter 1, pressure relief valve 1, etc. in real time (such as monitoring the pump motor temperature measuring element PT1, filter 1, and pressure relief valve 1 signal), and transmits it to the adapter unit 1. The adapter unit 1 feeds back the data and faults (such as the pump component 1 body temperature, faults, etc.) to the IMA through the communication unit, so as to realize the aircraft auxiliary cooling system pump component fully automatic safety pressure relief, coolant filtration, pressure stabilization, filter bypass, pump motor overheat protection, pump outlet overpressure protection, pump outlet low pressure protection, fault monitoring, fault storage data and other functions, not only to realize the aircraft auxiliary cooling system The controlled components (such as the pump component described here) are fully automatically controlled and monitored, and related processing is performed according to the status, and information exchange can be realized with the aircraft IMA through the aircraft auxiliary cooling system IMA, thereby improving the reliability of the entire aircraft operation. For example: if the pump outlet pressure exceeds a given safety value, the pump group controls the pressure relief valve to open to realize automatic safety pressure relief function and outlet overpressure protection; if the filter realizes refrigerant filtration, the filter bypass valve is controlled to realize the filtration bypass function; if the pump motor is overheated, the pump component controls the pump frequency to be reduced to 20Hz, and when the motor temperature drops to the normal value, the pump frequency is restored and PI control is performed; if the pump outlet pressure is too low, the pump frequency is gradually increased; the fault information monitored by the pump component controller will be fed back to the IMA storage.

[0177] In the control method of the aircraft auxiliary cooling system described in the solution of the present invention, in step S120, the operation process of each controlled component is controlled by the controller of each controlled component, including: when each controlled component includes a pump assembly, each pump assembly includes a first pump and a second pump; when controlling the operation of the first pump, if the first pump fails, switch to controlling the operation of the second pump: start the second pump, make the pump frequency of the second pump run at a set frequency for a set time, then restore the pump frequency of the second pump to the pump frequency of each pump assembly before the failure of the first pump, and then perform PI adjustment on the pump frequency of the second pump.

[0178] like Figure 4 As shown, the control process of the pump component 1 also includes: e. The pump component includes two pumps, one for backup and one for use (that is, during operation, pump 1 is started and pump 2 is on backup), and the controller monitors the pump operation status or fault signal in turn and regularly (such as every 20 minutes); if pump 1 is damaged during operation, the controller will immediately start pump 2 and first control it to run at 20Hz for 30s, then restore to the frequency before pump 1 was damaged, and finally PI dynamically adjusts the frequency.

[0179] In the scheme of the present invention, by providing a universal control device consisting of a detection unit, a communication unit and an IMA control unit for multiple controlled components of the aircraft auxiliary refrigeration system, such as a pump assembly, redundant control can be achieved for the two pumps inside the pump assembly, thereby improving the reliability of the operation of the aircraft auxiliary cooling system.

[0180] In the scheme of the present invention, the multi-pump assembly control system is composed of a pressure measuring element, a flow monitoring unit, a detection unit, a communication unit, a switching unit, a pump assembly and an IMA, which can realize automatic and independent dynamic adjustment and fault status monitoring of the multi-pump assembly (which can be replaced by a bypass valve, a radiator, a heating unit, etc.), greatly improving the intelligence and automation of the system, and at the same time ensuring the high accuracy of relevant data. In addition, for a single set of pump assemblies (two pumps, one for backup and one for use), if pump 1 fails, pump 2 can be started to provide a pressurization function; when the controller of a pump assembly on one side is damaged, the pump assembly on the other side can control and monitor the status of the pump assembly on that side, greatly improving the reliability of system operation.

[0181] Since the processing and functions implemented by the method of this embodiment basically correspond to the embodiments, principles and examples of the aforementioned aircraft auxiliary cooling system, for the details not fully described in this embodiment, please refer to the relevant descriptions in the aforementioned embodiments, and no further elaboration will be made here.

[0182] In summary, it is easy for those skilled in the art to understand that, under the premise of no conflict, the above-mentioned advantageous methods can be freely combined and superimposed.

[0183] 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 device for an aircraft auxiliary cooling system, characterized in that: The aircraft auxiliary cooling system has controlled components, and the number of the controlled components is more than two; for each of the more than two controlled components, a sampling unit, a switching unit and a controller are provided; The control device of the aircraft auxiliary cooling system comprises: a communication unit and an IMA control unit; wherein, The sampling unit of each of the controlled components is used to sample data at a location of the sampling unit of each of the controlled components as detection data of each of the controlled components; The IMA control unit is used to generate a target control instruction for each of the controlled components according to the detection data of each of the controlled components, and send the target control instruction of each of the controlled components to the switching unit of each of the controlled components through the communication unit, so as to be transmitted to the controller of each of the controlled components via the switching unit of each of the controlled components to realize the control of the operation process of each of the controlled components; The switching unit of each of the controlled components is used to obtain the status data of the controller of each of the controlled components from the controller of each of the controlled components and transmit the status data to the communication unit; The IMA control unit is further used to obtain the status data of the controller of each of the controlled components from the communication unit, and determine whether the controller of each of the controlled components is faulty according to the status data of the controller of each of the controlled components; and if it is determined that the controller of each of the controlled components is faulty, it is recorded as a controller fault of the first controlled component, and the target control instruction of the first controlled component is sent to the switching unit of the second controlled component among the two or more controlled components through the communication unit; The switching unit of the second controlled component is used to obtain the target control instruction of the first controlled component from the communication unit and transmit it to the controller of the second controlled component, so that the controller of the second controlled component can realize cross-control of the operation process of the first controlled component.

2. The control device for an aircraft auxiliary cooling system according to claim 1, characterized in that: The control device of the aircraft auxiliary cooling system further includes: a detection unit; wherein, The detection unit is used to receive the detection data of all the controlled components and upload them to the communication unit; The IMA control unit is further used to extract detection data of each controlled component from detection data of all the controlled components at the communication unit, generate a target control instruction of each controlled component according to the detection data of each controlled component, and send the target control instruction of each controlled component to the switching unit of each controlled component through the communication unit, so as to be transmitted to the controller of each controlled component via the switching unit of each controlled component to realize control of the operation process of each controlled component; The switching unit of each controlled component is used to obtain the detection data of each controlled component and the target control instruction of each controlled component from the communication unit; perform switching processing on the detection data of each controlled component to obtain the switching processing data of each controlled component; and transmit the switching processing data of each controlled component and the target control instruction of each controlled component to the controller of each controlled component; The controller of each controlled component is used to obtain the transfer processing data of each controlled component and the target control instructions of each controlled component from the transfer unit of each controlled component; and control the operation process of each controlled component in combination with the transfer processing data of each controlled component and the target control instructions of each controlled component.

3. The control device of the aircraft auxiliary cooling system according to claim 1 or 2, characterized in that: Each of the controlled components includes any one of a pump assembly, a heating unit, a radiator, and a bypass valve.

4. An aircraft auxiliary cooling system, characterized in that: include: A control device for an aircraft auxiliary cooling system according to any one of claims 1 to 3.

5. A control method for an aircraft auxiliary cooling system as claimed in claim 4, characterized in that: include: By using the sampling unit of each of the controlled components, sampling the data at the position where the sampling unit of each of the controlled components is located, as the detection data of each of the controlled components; Generate a target control instruction for each of the controlled components according to the detection data of each of the controlled components, and send the target control instruction for each of the controlled components to the switching unit of each of the controlled components through the communication unit, so as to be transmitted to the controller of each of the controlled components via the switching unit of each of the controlled components to realize control of the operation process of each of the controlled components; Acquire the state data of the controller of each controlled component from the controller of each controlled component through the switching unit of each controlled component and transmit the state data to the communication unit; Obtaining, by the IMA control unit, status data of the controller of each of the controlled components from the communication unit, and determining whether the controller of each of the controlled components is faulty according to the status data of the controller of each of the controlled components; And, if it is determined that the controller of each of the controlled components fails, it is recorded as a controller failure of the first controlled component, and the target control instruction of the first controlled component is sent to the switching unit of the second controlled component among the two or more controlled components through the communication unit; Through the switching unit of the second controlled component, the target control instruction of the first controlled component is obtained from the communication unit and transmitted to the controller of the second controlled component, so that the controller of the second controlled component can realize cross-control of the operation process of the first controlled component.

6. The control method of the aircraft auxiliary cooling system according to claim 5, characterized in that: Also includes: Receiving detection data of all the controlled components through the detection unit and uploading the data to the communication unit; By means of the IMA control unit, the detection data of each of the controlled components is extracted from the detection data of all the controlled components at the communication unit, a target control instruction of each of the controlled components is generated according to the detection data of each of the controlled components, and the target control instruction of each of the controlled components is sent to the switching unit of each of the controlled components through the communication unit, so as to be transmitted to the controller of each of the controlled components via the switching unit of each of the controlled components to realize the control of the operation process of each of the controlled components; Obtaining detection data of each of the controlled components and target control instructions of each of the controlled components from the communication unit through the switching unit of each of the controlled components; Performing transfer processing on the detection data of each of the controlled components to obtain transfer processing data of each of the controlled components; and transmitting the transfer processing data of each of the controlled components and the target control instruction of each of the controlled components to the controller of each of the controlled components; Obtaining, through the controller of each of the controlled components, the switching processing data of each of the controlled components and the target control instruction of each of the controlled components from the switching unit of each of the controlled components; The operation process of each controlled component is controlled by combining the transfer processing data of each controlled component and the target control instruction of each controlled component.

7. The control method of the aircraft auxiliary cooling system according to claim 6, characterized in that: Each of the controlled components includes a pump assembly; the sampling unit of each of the pump assemblies includes at least one of the following: an inlet pressure measuring element, an outlet pressure measuring element, and a flow monitoring unit; The detection data of each pump assembly includes at least one of inlet pressure, outlet pressure and flow rate; The detection data of each controlled component is transferred and processed by the transfer unit of each controlled component to obtain the transferred and processed data of each controlled component, including: Determine the difference between the outlet pressure and the inlet pressure of each pump assembly as the current actual liquid supply pressure of each pump assembly; The operation process of each controlled component is controlled by the controller of each controlled component in combination with the transfer processing data of each controlled component and the target control instruction of each controlled component, including: Determine the target fluid supply pressure of each pump component carried by the target control instruction of each pump component; and determine the fluid supply pressure difference between the target fluid supply pressure of each pump component and the current actual fluid supply pressure of each pump component to obtain the fluid supply pressure difference of each pump component; According to the difference in the liquid supply pressure of each pump assembly, the pump frequency of each pump assembly is PI-regulated.

8. The control method of the aircraft auxiliary cooling system according to claim 7, characterized in that: In the case where each of the controlled components includes a pump assembly, the pump frequency of each of the pump assemblies is PI-regulated according to the difference in the liquid supply pressure of each of the pump assemblies by the controller of each of the controlled components, including: The change amount of the pump frequency of the pump assembly is determined according to the following formula, and the pump frequency of the pump assembly is controlled to change according to the change amount of the pump frequency of the pump assembly: Wherein, ΔFp(n) is the change in the pump frequency of each pump assembly, T1 is the reading cycle, T2 is the calculation cycle, Δe is the difference between the current actual fluid supply pressure and the target fluid supply pressure in each calculation cycle, e i It is the difference between the current actual supply pressure and the target supply pressure for each reading cycle, A is the proportional coefficient, and B is the integral coefficient.

9. The control method of an aircraft auxiliary cooling system according to any one of claims 6 to 8, characterized in that: Each of the controlled components includes a pump assembly; By means of the controller of each of the controlled components, combined with the transfer processing data of each of the controlled components and the target control instruction of each of the controlled components, the operation process of each of the controlled components is controlled, and the method further includes: Setting the initial value of the pump frequency of each of the pump assemblies to a set frequency; During the operation of each pump assembly after it is started at the initial value of the pump frequency of each pump assembly, when the target liquid supply pressure carried by the target control instruction of each pump assembly is 0: If the pump frequency of each pump component is 0, the current state of each pump component is maintained; if the pump frequency of each pump component is not 0, then when the pump frequency of each pump component is less than or equal to the set frequency, each pump component is controlled to shut down; when the pump frequency of each pump component is greater than the set frequency, the pump frequency of each pump component is controlled to decrease from the set value to the set frequency, and then each pump component is controlled to shut down.

10. The control method of an aircraft auxiliary cooling system according to any one of claims 5 to 9, characterized in that: Each of the controlled components includes a pump assembly, and an auxiliary measurement unit is also provided at each of the pump assemblies; the auxiliary measurement unit includes at least one of the following: a pump motor temperature measurement element, a filter signal measurement element, and a hydraulic valve signal measurement element; the auxiliary measurement unit of each of the pump assemblies is used to obtain an auxiliary measurement signal of each of the pump assemblies; the auxiliary measurement signal of each of the pump assemblies includes: at least one of the pump motor temperature, the filter signal, and the hydraulic valve signal of each of the pump assemblies; in, The control method of the aircraft auxiliary cooling system further includes: By means of the controller of each of the pump assemblies, when the temperature of the pump motor of each of the pump assemblies is greater than or equal to the first set temperature, the pump frequency of each of the pump assemblies is controlled to decrease to the set frequency by the set value; until the temperature of the pump motor of each of the pump assemblies decreases to less than or equal to the second set temperature, the preset control of the pump frequency of each of the pump assemblies is restored; and / or, The control method of the aircraft auxiliary cooling system further includes: Uploading the auxiliary measurement signal of each pump component to the communication unit through the adapter unit of each pump component, so as to be transmitted to the IMA control unit through the communication unit; Obtaining, by means of the IMA control unit, an auxiliary measurement signal of each pump component from the communication unit, and monitoring the auxiliary measurement signal of each pump component; and / or, The control of the operation process of each of the controlled components is realized by the controller of each of the controlled components, including: In the case where each of the controlled components includes a pump assembly, each of the pump assemblies includes a first pump and a second pump; when controlling the operation of the first pump, if the first pump fails, switch to controlling the operation of the second pump: start the second pump, make the pump frequency of the second pump run at a set frequency for a set time, then restore the pump frequency of the second pump to the pump frequency of each of the pump assemblies before the failure of the first pump, and then perform PI adjustment on the pump frequency of the second pump.

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