An integrated test system for pump sources in multiple subsystems of civil aircraft

Abstract

This invention discloses an integrated pump source test system for multiple subsystems of civil aircraft. The engine-driven pump drive module includes a variable frequency motor and an engine-driven pump driven by it, while the electric pump drive module includes a DC motor and an electric pump driven by it. The engine-driven pump drive module and the electric pump drive module are respectively connected to the input end of a power conversion device via a power conversion device connection module under the control of a parallel drive module. The drive end of the power conversion device is the engine-driven pump and / or the electric pump. An energy recovery module is connected to both the engine-driven pump and the electric pump. A drive distribution module is connected to the parallel drive module and is used to intelligently distribute the power to the drive end according to actual needs and control the parallel drive module to execute the corresponding control mode. This invention can adapt to the testing requirements of different types of pump sources, achieve integrated testing, simplify the testing process, and improve testing efficiency.

Description

Technical Field

[0001] This invention relates to the field of hydraulic testing technology for civil aircraft, and in particular to an integrated testing system for pump sources of multiple subsystems in civil aircraft. Background Technology

[0002] The hydraulic system of civil aircraft is a key factor in ensuring flight safety and improving operational performance, providing the necessary power for various aircraft operations. These systems include, but are not limited to, flight control systems, landing gear retraction and extension, flap adjustment, and braking systems, all of which rely on a stable and efficient pump source. In existing civil aircraft designs, pump sources mainly include engine-driven pumps, electric pumps, and power conversion devices, each responsible for providing hydraulic power to the aircraft. However, these pump sources differ significantly in design and operation. Engine-driven pumps are typically directly connected to the aircraft engine, and their speed and flow rate are affected by the engine's operating conditions; electric pumps are driven by electric motors, offering better controllability and stability; and power conversion devices are responsible for converting and distributing energy between different pump sources. The vast differences in the driving source, operating load, and full life-cycle load spectrum of these pump sources make it difficult to conduct comprehensive performance evaluations in a unified testing environment. For example, engine-driven pumps may operate at high speeds, while electric pumps may need to operate stably under various speeds and loads. This complexity means that traditional hydraulic pump comprehensive performance test benches cannot meet testing requirements, thus becoming a long-standing technical challenge in the aviation industry. Furthermore, the pump power range of aircraft hydraulic systems is extremely wide, from low-power auxiliary systems to high-power main actuators, which places higher demands on the design of test systems. While using high-power motor-driven test systems can cover a broad range of testing needs, it leads to a significant increase in cost. At the same time, during testing, especially under conditions of large fluctuations in pump power, there is significant energy waste. This energy waste not only increases testing costs but also hinders environmental protection and sustainable development. Summary of the Invention

[0003] To address the challenges of testing pump sources in multiple subsystems of civil aircraft, this invention proposes an integrated testing system for pump sources in civil aircraft. This system can simulate the operating conditions of different pump sources, enabling comprehensive performance evaluation of engine-driven pumps, electric pumps, and power conversion devices. This requires the system to possess high flexibility and adaptability, capable of precise control and testing based on the characteristics of different pump sources. Simultaneously, the system also needs to integrate advanced energy recovery technology to reduce energy loss during testing, improve energy efficiency, and lower operating costs.

[0004] The specific technical solution is as follows:

[0005] An integrated pump source test system for multiple subsystems of a civil aircraft includes: an engine-driven pump drive module, an electric pump drive module, a variable frequency motor, an engine-driven pump, a DC motor, an electric pump, a power conversion device, a power conversion device connection module, an energy recovery module, a drive parallel module, and a drive distribution module; the engine-driven pump drive module includes a variable frequency motor and an engine-driven pump driven by it, the electric pump drive module includes a DC motor and an electric pump driven by it, and the drive end includes the engine-driven pump and the electric pump;

[0006] The engine-driven pump drive module and the electric pump drive module are respectively connected to the input end of the power conversion device through the power conversion device connection module under the control of the drive parallel module. The drive end of the power conversion device is the engine-driven pump and / or the electric pump. The energy recovery module is connected to the engine-driven pump and the electric pump respectively, and is used to recover the unused power of the test system and convert it into electrical energy. The drive distribution module is connected to the drive parallel module and is used to intelligently distribute the drive end power according to actual needs and control the drive parallel module to execute the corresponding control mode.

[0007] Furthermore, the drive allocation module intelligently allocates power to the drive end using the following five allocation methods:

[0008] Allocation method 1 is used to test the engine-driven pump. In this allocation method, under the action of the drive parallel module, the variable frequency motor drives the engine-driven pump to operate and load the load. Excess power is recovered through the energy recovery module.

[0009] Distribution method 2 is used to test the electric pump. In this distribution method, the DC motor drives the electric pump to operate under the action of the drive parallel module to load the load, and the excess power is recovered through the energy recovery module.

[0010] Allocation method 3 is used to test the power conversion device. In this allocation method, under the action of the drive parallel module, the DC motor drives the electric pump to operate and load the load. The output end of the electric pump is connected to the input end of the power conversion device through the power conversion device connection module, so that the electric pump drives the power conversion device. The variable frequency motor is connected to the first input end of the engine drive pump, and the output end of the power conversion device is connected to the second input end of the engine drive pump, so that the electric pump and the variable frequency motor jointly drive the engine drive pump to operate.

[0011] Allocation method 4 is used to test the power conversion device. In this allocation method, under the action of the drive parallel module, the variable frequency motor drives the engine drive pump to operate and load the load. The output end of the engine drive pump is connected to the input end of the power conversion device through the power conversion device connection module, so that the engine drive pump drives the power conversion device. The DC motor is connected to the first input end of the electric pump, and the output end of the power conversion device is connected to the second input end of the electric pump, so that the engine drive pump and the DC motor jointly drive the electric pump to operate.

[0012] Allocation method 5 is used to test high-power pump sources. In this allocation method, under the action of the drive parallel module, the variable frequency motor drives the engine-driven pump, and the DC motor drives the electric pump. The output end of the engine-driven pump is connected to the input end of the power conversion device through the power conversion device connection module, and the output end of the electric pump is connected to the input end of the power conversion device through the power conversion device connection module. The output end of the power conversion device is connected to the high-power pump source. The engine-driven pump and the electric pump jointly drive the high-power pump source. The power of the engine-driven pump and the electric pump is allocated according to the drive allocation module. Excess power is recovered through the energy recovery module.

[0013] Furthermore, the power conversion device connection module includes a two-stage clutch and a connecting pipeline; the two-stage clutch includes a primary clutch and a secondary clutch, the primary clutch is used to initially connect the power source and the transmission system, and is activated when testing the power conversion device to achieve smooth power transmission and reduce impact; the secondary clutch is activated when testing a high-power pump source to transmit greater torque to the output end; the connecting pipeline is used to transmit power or control signals from one module to another.

[0014] Furthermore, the energy recovery module includes a hydraulic motor, a generator, and an energy storage unit; the hydraulic motor is used to convert excess hydraulic energy of the test system into mechanical energy, the generator is used to convert mechanical energy into electrical energy, and the energy storage unit is used to store the converted electrical energy.

[0015] Furthermore, the drive parallel module includes a two-stage clutch and a differential gearbox; the differential gearbox allows the two input ends, namely the engine-driven pump and the electric pump, to rotate differentially; the two-stage clutch includes a primary clutch and a secondary clutch, the primary clutch is used to initially connect the power source and the transmission system, and is activated when testing the power conversion device to achieve smooth power transmission; the secondary clutch is activated when testing the high-power pump source, connecting the output end of the engine-driven pump to the input end of the power conversion device through the power conversion device connection module, and connecting the output end of the electric pump to the input end of the power conversion device through the power conversion device connection module, jointly driving the high-power pump source, and recovering excess power through the energy recovery module.

[0016] Furthermore, the drive allocation module calculates the actual required drive power based on the actual test requirements of the pump source, and allocates the total power of the engine drive pump drive module and the electric pump drive module to achieve intelligent matching of the output power of the drive end.

[0017] Furthermore, it also includes a control terminal, which includes: a load simulation unit, a test control unit, a data analysis and storage unit, and a network connection unit;

[0018] The load simulation unit is used to simulate the load characteristics under actual working conditions and input the data into the test control unit;

[0019] The test control unit is used to automatically control the entire test process of the test system, ensuring that the test is carried out according to the predetermined program and parameters; the control content includes: starting or stopping the test process, controlling the control mode of the drive distribution module, setting the parameters of the drive end and the load end, and monitoring the status of the test system;

[0020] The network connection unit is used to provide the connection function between the test system and the external network, realize remote access, transmission and sharing of data, facilitate remote monitoring, analysis and report distribution of test data, and support remote fault diagnosis and technical support.

[0021] The data analysis and storage unit collects various types of data generated by the test system during the test through the network connection unit, analyzes, stores and manages this data, and feeds it back to the test control unit;

[0022] The test control unit is used to convert the working conditions input by the load simulation unit into load-side control commands, simulate load characteristics, and input them into the test system. The test process data collected and analyzed by the data analysis and storage unit is processed by the test control unit to determine whether the test system is operating safely according to the working conditions set by the load simulation unit. If not, the data is fed back to the load simulation unit for parameter adjustment.

[0023] Furthermore, the load characteristics include: load variation, load torque, and load pressure.

[0024] Furthermore, the various data generated by the test system during the test include: pressure, flow rate, temperature, and time.

[0025] The beneficial effects of this invention are:

[0026] (1) The test system of the present invention can adapt to the test requirements of different types of pump sources, including engine-driven pumps, electric pumps, power conversion devices and high-power pump sources, and solves the problem that traditional test benches cannot fully evaluate these pump sources.

[0027] (2) By connecting the engine drive pump, electric pump and power conversion device in parallel, the present invention realizes integrated testing, simplifies the testing process and improves testing efficiency.

[0028] (3) The intelligent allocation function of the drive allocation module designed in this invention can dynamically match the power requirements of the pump source under test according to real-time test requirements, which can realize the test of high-power pump sources and improve the test limit of the test system.

[0029] (4) The application of the energy recovery module in this invention significantly reduces energy waste during the testing process. By recovering and reusing the energy generated by the hydraulic system, the dependence on external energy is reduced and the testing cost is lowered. Attached Figure Description

[0030] Figure 1 This is a schematic diagram of the framework of the integrated pump source test system for multiple subsystems of civil aircraft in an embodiment of the present invention.

[0031] Figure 2 This is a schematic diagram of the allocation method 1 of the integrated pump source test system for multi-subsystem civil aircraft in this embodiment of the invention.

[0032] Figure 3 This is a schematic diagram of the allocation method 2 of the integrated pump source test system for multi-subsystem civil aircraft in this embodiment of the invention.

[0033] Figure 4 This is a schematic diagram of the allocation method 3 of the integrated pump source test system for multi-subsystem civil aircraft in this embodiment of the invention.

[0034] Figure 5 This is a schematic diagram of the allocation method 4 of the integrated pump source test system for multi-subsystem civil aircraft in this embodiment of the invention.

[0035] Figure 6 This is a schematic diagram of the allocation method 5 of the integrated pump source test system for multi-subsystem civil aircraft in this embodiment of the invention.

[0036] Figure 7 This is a schematic diagram of the framework of the integrated pump source test system for multiple subsystems of civil aircraft during testing, as described in this embodiment of the invention. Detailed Implementation

[0037] The present invention will be described in detail below with reference to the accompanying drawings and preferred embodiments. The objectives and effects of the present invention will become clearer as a result. The present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

[0038] like Figure 1As shown, a multi-subsystem pump-source integrated test system for civil aircraft includes: an engine-driven pump drive module, an electric pump drive module, a power transfer unit (PTU), a power transfer unit connection module, an energy recovery module, a drive parallel module, and a drive distribution module. The engine-driven pump drive module includes: a variable frequency motor, a first mounting bracket, and an engine-driven pump (EDP); the variable frequency motor drives the EDP. The electric pump drive module includes: a DC motor, a second mounting bracket, and an electric motor pump (EMP); the DC motor drives the EMP. The EDP and EMP are collectively referred to as the drive end. The power transfer unit connection module includes: a two-stage clutch, connecting pipes, and a third mounting bracket. The first, second, and third mounting brackets respectively support the corresponding modules. The connecting pipes are used to transmit power or control signals from one module to another, serving as the transmission medium for power and control, and ensuring system stability. A dual-stage clutch is a clutch structure used in mechanical transmission systems to perform specific power engagement and disengagement. The first-stage clutch is mainly responsible for initially connecting the power source and the transmission system. It is activated when testing power conversion devices and its function is to achieve smooth power transmission and reduce shock under low power output or low load (corresponding to distribution modes 3 and 4 below). The second-stage clutch is activated when the system requires higher power output or enters a high-load working state (corresponding to distribution mode 5 below) and is mainly responsible for transmitting greater torque to the output end.

[0039] The engine-driven pump drive module and the electric pump drive module are controlled by a parallel drive module and connected to the input terminal of the PTU via a PTU connection module, thereby enabling energy transfer from the EDP and EMP through the PTU. The drive terminal of the PTU can be either the EDP or the EMP. The energy recovery module is connected to both the EDP and EMP. The drive distribution module is connected to the parallel drive module and is used to intelligently distribute power to the drive terminals and control the parallel drive module to execute the corresponding control mode.

[0040] The energy recovery module is used to recover unused power from the hydraulic system of the integrated pump-source test system for multi-subsystems of civil aircraft, convert it into electrical energy, and reuse it. The energy recovery module includes: a hydraulic motor, a generator, and an energy storage unit; the hydraulic motor is used to convert hydraulic energy into mechanical energy, the generator is used to convert the mechanical energy of the hydraulic motor into electrical energy, and the recovered electrical energy is stored in the energy storage unit.

[0041] The drive parallel module includes a two-stage clutch and a differential gearbox; the differential gearbox allows differential rotation of the two input terminals (EDP and EMP), and the structure and function of the two-stage clutch are the same as described above. When testing a high-power pump source, the two-stage clutch engages, the differential gearbox actuates, connecting the output of the EDP to the input of the PTU connection module, and the output of the EMP to the input of the PTU connection module, jointly driving the high-power pump source. Excess power is recovered through the energy recovery module. When testing the PTU, the first-stage clutch engages, and the differential gearbox actuates.

[0042] The drive allocation module calculates the actual required drive power and allocates it to the engine drive pump drive module and the electric pump drive module, thereby achieving intelligent matching of the output power at the drive end and meeting the actual testing requirements of the pump source. In this embodiment, the test system has the following five allocation methods to test different objects:

[0043] like Figure 2 As shown, allocation mode 1 is used for testing the EDP. In this allocation mode, the engine-driven pump drive module and the energy recovery module are activated. The variable frequency motor drives the EDP to operate and load the load. Excess power is recovered through the energy recovery module; the electricity stored in the energy recovery module can also be used for EDP operation.

[0044] like Figure 3 As shown, allocation mode 2 is used for testing the EMP. In this allocation mode, the electric pump drive module and the energy recovery module are activated. The DC motor drives the EMP to operate and load the load. Excess power is recovered through the energy recovery module; the electricity stored in the energy recovery module can also be used for EMP operation.

[0045] like Figure 4 As shown, allocation mode 3 is used for testing the PTU. In this allocation mode, the following are activated: the engine-driven pump drive module, the electric pump drive module, the power conversion device connection module, and the PTU. The DC motor drives the EMP to operate and load the load. Simultaneously, the output of the EMP is connected to the input of the PTU through the power conversion device connection module, allowing the EMP to drive the PTU. The output of the PTU is connected to the input of the EDP, and the power from the EMP is transmitted through the PTU, working together with the variable frequency motor to drive the EDP, thus ensuring the normal operation of the load.

[0046] like Figure 5As shown, allocation mode 4 is used for testing the PTU. In this allocation mode, the following are activated: the engine-driven pump drive module, the electric pump drive module, the power conversion device connection module, and the PTU. The variable frequency motor drives the EDP to operate and load the load. Simultaneously, the output terminal of the EDP is connected to the input terminal of the PTU through the power conversion device connection module, allowing the EDP to drive the PTU. The output terminal of the PTU is connected to the input terminal of the EMP. The power from the EDP is transmitted through the PTU, working together with the DC motor to drive the EMP, thus ensuring the normal operation of the load.

[0047] like Figure 6 As shown, allocation mode 5 is used to test the high-power pump source. In this allocation mode, the following modules are activated: engine-driven pump drive module, electric pump drive module, PTU, power conversion device connection module, and energy recovery module. The variable frequency motor drives the EDP, and the DC motor drives the EMP. The output of the EDP is connected to the input of the PTU via the power conversion device connection module, and the output of the EMP is connected to the input of the PTU via the same module. The output of the PTU is connected to the high-power pump source. The EDP and EMP jointly drive the high-power pump source, and the power of the EDP and EMP is allocated according to the drive allocation module. Excess power is recovered through the energy recovery module.

[0048] like Figure 7 As shown, when the integrated pump source test system for multiple subsystems of civil aircraft is tested, its external control terminal includes: a load simulation unit, a test control unit, a data analysis and storage unit, and a network connection unit.

[0049] The load simulation unit is responsible for simulating load characteristics under actual working conditions and inputting the data into the test control unit. Load characteristics include load variation, load torque, and load pressure. Through accurate load simulation, it provides a test environment close to actual working conditions for the test system (primarily controlling the load end, i.e., controlling the controlled object), ensuring the accuracy and reliability of the test.

[0050] The test control unit is responsible for the automated control of the entire test process, including: starting or stopping the test procedure, operating the drive distribution module, setting parameters for the drive and load ends, and monitoring the test system status. It ensures that the test proceeds according to the predetermined program and parameters, achieving automated and intelligent control of the test process.

[0051] The network connection unit provides connectivity between the test system and external networks, enabling remote access, transmission, and sharing of data. This facilitates remote monitoring, analysis, and report distribution of test data, while also supporting remote fault diagnosis and technical support.

[0052] The data analysis and storage unit collects various data generated by the test system during the test through the network connection unit, including pressure, flow rate, temperature, time, etc.; analyzes, stores and manages this data, and feeds it back to the test control unit, providing raw data support for subsequent data analysis, report generation and test result evaluation, and ensuring the integrity and traceability of the data.

[0053] The test control unit converts the operating conditions input by the load simulation unit into load-side control commands, simulates load characteristics, and inputs them into the test system. The data analysis and storage unit collects and analyzes the test process data, which is then processed by the test control unit to determine whether the test system is operating safely according to the operating conditions set by the load simulation unit. If not, the data is fed back to the load simulation unit for parameter adjustment.

[0054] The integrated test system for pump sources of multi-subsystems in civil aircraft of the present invention has the advantages of high testing efficiency, high energy utilization rate and low testing cost. It can effectively conduct comprehensive performance evaluation and testing of hydraulic pump sources of civil aircraft, while reducing energy consumption and testing costs. It has important practical value and market application prospects.

[0055] It will be understood by those skilled in the art that the above descriptions are merely preferred examples of the invention and are not intended to limit the invention. Although the invention has been described in detail with reference to the foregoing examples, those skilled in the art can still modify the technical solutions described in the foregoing examples or make equivalent substitutions for some of the technical features. All modifications and equivalent substitutions made within the spirit and principles of the invention should be included within the scope of protection of the invention.

Claims

1. An integrated pump source test system for multiple subsystems of civil aircraft, characterized in that, include: The system includes an engine-driven pump drive module, an electric pump drive module, a variable frequency motor, an engine-driven pump, a DC motor, an electric pump, a power conversion device, a power conversion device connection module, an energy recovery module, a drive parallel module, and a drive distribution module. The engine-driven pump drive module includes a variable frequency motor and an engine-driven pump driven by it, and the electric pump drive module includes a DC motor and an electric pump driven by it. The drive end includes the engine-driven pump and the electric pump. The engine-driven pump drive module and the electric pump drive module are respectively connected to the input end of the power conversion device through the power conversion device connection module under the control of the drive parallel module. The drive end of the power conversion device is the engine-driven pump and / or the electric pump. The energy recovery module is connected to the engine-driven pump and the electric pump respectively, and is used to recover the unused power of the test system and convert it into electrical energy. The drive distribution module is connected to the drive parallel module and is used to intelligently distribute the drive end power according to actual needs and control the drive parallel module to execute the corresponding control mode.

2. The integrated pump source test system for multiple subsystems of civil aircraft according to claim 1, characterized in that, The drive distribution module intelligently distributes power to the drive end in the following five ways: Allocation method 1 is used to test the engine-driven pump. In this allocation method, under the action of the drive parallel module, the variable frequency motor drives the engine-driven pump to operate and load the load. Excess power is recovered through the energy recovery module. Distribution method 2 is used to test the electric pump. In this distribution method, the DC motor drives the electric pump to operate under the action of the drive parallel module to load the load, and the excess power is recovered through the energy recovery module. Allocation method 3 is used to test the power conversion device. In this allocation method, under the action of the drive parallel module, the DC motor drives the electric pump to operate and load the load. The output end of the electric pump is connected to the input end of the power conversion device through the power conversion device connection module, so that the electric pump drives the power conversion device. The variable frequency motor is connected to the first input end of the engine drive pump, and the output end of the power conversion device is connected to the second input end of the engine drive pump, so that the electric pump and the variable frequency motor jointly drive the engine drive pump to operate. Allocation method 4 is used to test the power conversion device. In this allocation method, under the action of the drive parallel module, the variable frequency motor drives the engine drive pump to operate and load the load. The output end of the engine drive pump is connected to the input end of the power conversion device through the power conversion device connection module, so that the engine drive pump drives the power conversion device. The DC motor is connected to the first input end of the electric pump, and the output end of the power conversion device is connected to the second input end of the electric pump, so that the engine drive pump and the DC motor jointly drive the electric pump to operate. Allocation method 5 is used to test high-power pump sources. In this allocation method, under the action of the drive parallel module, the variable frequency motor drives the engine-driven pump, and the DC motor drives the electric pump. The output end of the engine-driven pump is connected to the input end of the power conversion device through the power conversion device connection module, and the output end of the electric pump is connected to the input end of the power conversion device through the power conversion device connection module. The output end of the power conversion device is connected to the high-power pump source. The engine-driven pump and the electric pump jointly drive the high-power pump source. The power of the engine-driven pump and the electric pump is allocated according to the drive allocation module. Excess power is recovered through the energy recovery module.

3. The integrated pump source test system for multiple subsystems of civil aircraft according to claim 1, characterized in that, The power conversion device connection module includes a two-stage clutch and connecting pipelines; the two-stage clutch includes a primary clutch and a secondary clutch. The primary clutch is used to initially connect the power source and the transmission system, and is activated when testing the power conversion device to achieve smooth power transmission and reduce impact; the secondary clutch is activated when testing a high-power pump source to transmit greater torque to the output end; the connecting pipelines are used to transmit power or control signals from one module to another.

4. The integrated pump source test system for multiple subsystems of civil aircraft according to claim 1, characterized in that, The energy recovery module includes a hydraulic motor, a generator, and an energy storage unit; the hydraulic motor is used to convert excess hydraulic energy of the test system into mechanical energy, the generator is used to convert mechanical energy into electrical energy, and the energy storage unit is used to store the converted electrical energy.

5. The integrated pump source test system for multiple subsystems of civil aircraft according to claim 1, characterized in that, The drive parallel module includes a two-stage clutch and a differential gearbox. The differential gearbox allows the two input ends, namely the engine-driven pump and the electric pump, to rotate at different speeds. The two-stage clutch includes a primary clutch and a secondary clutch. The primary clutch is used to initially connect the power source and the transmission system, and is activated when testing the power conversion device to achieve smooth power transmission. The secondary clutch is activated when testing the high-power pump source, connecting the output end of the engine-driven pump to the input end of the power conversion device through the power conversion device connection module, and connecting the output end of the electric pump to the input end of the power conversion device through the power conversion device connection module, so as to jointly drive the high-power pump source. Excess power is recovered through the energy recovery module.

6. The integrated pump source test system for multiple subsystems of civil aircraft according to claim 1, characterized in that, The drive distribution module calculates the actual required drive power based on the actual test requirements of the pump source, and distributes the total power of the engine drive pump drive module and the electric pump drive module to achieve intelligent matching of the output power of the drive end.

7. The integrated pump source test system for multiple subsystems of civil aircraft according to claim 1, characterized in that, It also includes a control terminal, which includes: Load simulation unit, test control unit, data analysis and storage unit, network connection unit; The load simulation unit is used to simulate the load characteristics under actual working conditions and input the data into the test control unit; The test control unit is used to automatically control the entire test process of the test system, ensuring that the test is carried out according to the predetermined program and parameters; the control content includes: starting or stopping the test process, controlling the control mode of the drive distribution module, setting the parameters of the drive end and the load end, and monitoring the status of the test system; The network connection unit is used to provide the connection function between the test system and the external network, realize remote access, transmission and sharing of data, facilitate remote monitoring, analysis and report distribution of test data, and support remote fault diagnosis and technical support. The data analysis and storage unit collects various types of data generated by the test system during the test through the network connection unit, analyzes, stores and manages this data, and feeds it back to the test control unit; The test control unit is used to convert the working conditions input by the load simulation unit into load-side control commands, simulate load characteristics, and input them into the test system. The test process data collected and analyzed by the data analysis and storage unit is processed by the test control unit to determine whether the test system is operating safely according to the working conditions set by the load simulation unit. If not, the data is fed back to the load simulation unit for parameter adjustment.

8. The integrated pump source test system for multiple subsystems of civil aircraft according to claim 7, characterized in that, The load characteristics include: load variation, load torque, and load pressure.

9. The integrated pump source test system for multiple subsystems of civil aircraft according to claim 7, characterized in that, The test system generates various data during the test, including pressure, flow rate, temperature, and time.

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