Civil aircraft multi-subsystem pump source integrated test system

Abstract

The invention discloses a civil aircraft multi-subsystem pump source integrated test system, an engine driving pump driving module comprises a variable frequency motor and an engine driving pump driven by the variable frequency motor, and an electric pump driving module comprises a direct current motor and an electric pump driven by the direct current motor; the engine driving pump driving module and the electric pump driving module are respectively connected with the input end of the power conversion device through the power conversion device connecting module under the control of the driving parallel module, and the driving end of the power conversion device is an engine driving pump and / or an electric pump; the energy recovery module is respectively connected with the engine driving pump and the electric pump; the driving distribution module is connected with the driving parallel module and used for intelligently distributing driving end power according to actual requirements and controlling the driving parallel module to execute a corresponding control mode. According to the invention, the test requirements of different types of pump sources can be met, the integrated test is realized, the test process is simplified, and the test efficiency is improved.

Description

Technical Field

[0001] The invention relates to the technical field of hydraulic pressure testing of civil aircraft, and in particular to a multi-subsystem pump source integrated testing system for civil aircraft. Background Art

[0002] The hydraulic system of civil aircraft is a key factor in ensuring flight safety and improving operational performance. It is responsible for providing the necessary power for various operations of the aircraft. These systems include but are not limited to flight control systems, landing gear retraction and extension, flap adjustment, brake systems, etc., and the realization of all these functions depends on a stable and efficient pump source. In the existing civil aircraft design, the pump source mainly includes an engine-driven pump, an electric pump, and a power conversion device, each of which is responsible for providing hydraulic power for the aircraft. However, there are significant differences in the design and operation of these pump sources. The engine-driven pump is usually directly connected to the aircraft engine, and its speed and flow are affected by the working state of the engine; the electric pump is driven by an electric motor and has better controllability and stability; the power conversion device is responsible for converting and distributing energy between different pump sources. The huge differences in the driving source, working load, and life cycle load spectrum of these pump sources make it difficult to conduct a comprehensive performance evaluation in a unified test environment. For example, the engine-driven pump may work at a high speed, while the electric pump may need to operate stably at a variety of different speeds and loads. This complexity has led to the inability of traditional hydraulic pump comprehensive performance test benches to meet the test requirements, thus becoming a long-standing technical problem in the aviation industry. In addition, the pump power of the aircraft hydraulic system has a wide range, from low-power auxiliary systems to high-power main actuators, which puts higher requirements on the design of the test system. If a test system driven by a high-power motor is used, although it can cover a wide range of test needs, it will lead to a significant increase in costs. At the same time, during the test process, especially under conditions where the pump power varies greatly, there is a large energy waste problem. This energy waste not only increases the test cost, but is also not conducive to environmental protection and sustainable development. Summary of the invention

[0003] In order to solve the problem of pump source testing for multiple subsystems of civil aircraft, the present invention proposes an integrated test system for pump sources for multiple subsystems of civil aircraft. The system can simulate the working conditions of different pump sources and realize the comprehensive performance evaluation of engine-driven pumps, electric pumps and power conversion devices. This requires the system to have high flexibility and adaptability and to be able to accurately control and test according to the characteristics of different pump sources. At the same time, the system also needs to integrate advanced energy recovery technology to reduce energy loss during the test process, improve energy efficiency and reduce operating costs.

[0004] The specific technical solutions are as follows:

[0005] A multi-subsystem pump source integrated test system for a civil aircraft, comprising: 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 comprises a variable frequency motor and an engine driven pump driven thereby, the electric pump drive module comprises a DC motor and an electric pump driven thereby, and the drive end comprises the engine driven pump and the electric pump;

[0006] The engine driven pump driving module and the electric pump driving 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, and the driving end of the power conversion device is the engine driven pump and / or the electric pump; the energy recovery module is respectively connected to the engine driven pump and the electric pump, 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 distribution module intelligently distributes the drive end power in the following five distribution modes:

[0008] Distribution mode 1 is used to test the engine driven pump. Under this distribution mode, under the action of the drive parallel module, the variable frequency motor drives the engine driven pump to operate and load the load, and the excess power is recovered through the energy recovery module;

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

[0010] Distribution mode 3 is used to test the power conversion device. Under this distribution mode, under the action of the driving 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 to realize the electric pump driving the power conversion device; the variable frequency motor is connected to the first input end of the engine driven pump, and the output end of the power conversion device is connected to the second input end of the engine driven pump, so that the electric pump and the variable frequency motor jointly drive the engine driven pump to operate;

[0011] Distribution mode 4 is used to test the power conversion device. Under this distribution mode, under the action of the driving parallel module, the variable frequency motor drives the engine driven pump to operate and load the load. 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, so that the engine driven 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 driven pump and the DC motor jointly drive the electric pump to operate;

[0012] Distribution mode 5 is used to test a high-power pump source. Under this distribution mode, under the action of the drive parallel module, the variable frequency motor drives the engine driven pump, 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, 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, and 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 distributed according to the drive distribution module; and the excess power is recovered through the energy recovery module.

[0013] Furthermore, the power conversion device connection module includes a dual-stage clutch and a connecting pipeline; the dual-stage clutch includes a primary clutch and a secondary clutch, the primary clutch is used to preliminarily connect the power source and the transmission system, and is started when testing the power conversion device to achieve smooth power transmission and reduce impact; the secondary clutch is started when testing a high-power pump source, and is used 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 dual-stage clutch and a differential gearbox; the differential gearbox is used to allow differential rotation of two input ends, namely the engine-driven pump and the electric pump; the dual-stage clutch includes a primary clutch and a secondary clutch, the primary clutch is used to preliminarily connect the power source and the transmission system, and is started when testing the power conversion device to achieve smooth power transmission; the secondary clutch is started when testing the high-power pump source, and 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, and the high-power pump source is jointly driven, and the excess power is recovered through the energy recovery module.

[0016] Furthermore, the drive distribution module calculates the actual required drive power according to the actual test requirements of the pump source, distributes the total power of the engine-driven pump drive module and the electric pump drive module, and realizes intelligent matching of the output power of the drive end.

[0017] Furthermore, it also includes a control end, 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 them into the test control unit;

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

[0020] The network connection unit is used to provide a 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 process through the network connection unit, analyzes, stores and manages the data, and feeds them 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-end control instructions, simulate load characteristics, and input them into the test system; the test process data collected and analyzed by the data analysis storage unit is processed by the test control unit to determine whether the test system is safely operating according to the working conditions set by the load simulation unit. If not, it is fed back to the load simulation unit for parameter adjustment.

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

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

[0025] The beneficial effects of the present invention are:

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

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

[0028] (3) The intelligent allocation function of the drive allocation module designed in the present invention can dynamically match the power demand of the pump source to be tested according to the real-time test requirements, thereby enabling the testing of high-power pump sources and improving the test limit of the test system.

[0029] (4) The application of the energy recovery module in the present invention significantly reduces the energy waste during the test process. By recovering and reusing the energy generated by the hydraulic system, the dependence on external energy is reduced, thereby reducing the test cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 It is a schematic diagram of the framework of a civil aircraft multi-subsystem pump source integration test system in an embodiment of the present invention.

[0031] Figure 2 It is a schematic framework diagram of the distribution method 1 of the civil aircraft multi-subsystem pump source integrated test system in the embodiment of the present invention.

[0032] Figure 3 It is a schematic framework diagram of the distribution method 2 of the civil aircraft multi-subsystem pump source integrated test system in the embodiment of the present invention.

[0033] Figure 4 It is a schematic framework diagram of the distribution mode 3 of the civil aircraft multi-subsystem pump source integrated test system in the embodiment of the present invention.

[0034] Figure 5 It is a schematic framework diagram of the distribution mode 4 of the civil aircraft multi-subsystem pump source integrated test system in the embodiment of the present invention.

[0035] Figure 6 It is a schematic framework diagram of the distribution method 5 of the civil aircraft multi-subsystem pump source integrated test system in the embodiment of the present invention.

[0036] Figure 7 It is a schematic diagram of the framework of the civil aircraft multi-subsystem pump source integrated test system during the test in the embodiment of the present invention. DETAILED DESCRIPTION

[0037] The present invention will be described in detail below according to the accompanying drawings and preferred embodiments, and the purpose and effect of the present invention will become more clear. The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0038] like Figure 1As shown, a civil aircraft multi-subsystem pump source integrated test system includes: an engine-driven pump drive module, an electric pump drive module, a power transfer unit (hereinafter referred to as 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 frame and an engine-driven pump (hereinafter referred to as EDP); the variable frequency motor is used to drive the EDP. The electric pump drive module includes: a DC motor, a second mounting frame and an electric pump (hereinafter referred to as EMP); the DC motor is used to drive the EMP. EDP and EMP are collectively referred to as the drive end. The power conversion device connection module includes: a dual-stage clutch, a connecting pipeline, and a third mounting frame. Among them, the first mounting frame, the second mounting frame, and the third mounting frame respectively play the role of supporting the corresponding modules. The connecting pipeline is used to transmit power or control signals from one module to another. It is a transmission medium for power and control and is used to ensure system stability. A bipolar clutch is a clutch structure used in mechanical transmission systems to perform specific power engagement and separation. The primary clutch is mainly responsible for the initial connection between the power source and the transmission system. It is activated when testing the power conversion device. Its function is to achieve smooth power transmission at lower power output or lower load and reduce impact (corresponding to distribution modes 3 and 4 below). The secondary 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 the drive parallel module respectively, and connected to the input end of the PTU through the PTU connection module, so as to realize the energy transfer of EDP and EMP through the PTU respectively; the drive end of the PTU can be EDP or EMP. The energy recovery module is connected to the EDP and EMP respectively; the drive distribution module is connected to the drive parallel module, which is used to intelligently distribute the power of the drive end and control the drive parallel module to execute the corresponding control mode.

[0040] The energy recovery module is used to recover the unused power in the hydraulic system of the civil aircraft multi-subsystem pump source integrated test system, convert it into electrical energy, and recycle 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 dual-stage clutch and a differential gearbox; the differential gearbox is used to allow the two input ends (ie, EDP and EMP) to rotate differentially, and the structure and function of the double-click clutch are the same as above. When it is necessary to test the high-power pump source, the secondary clutch is engaged, the differential gearbox is activated, the output end of the EDP is connected to the input end of the PTU connection module, and the output end of the EMP is connected to the input end of the PTU connection module, and the high-power pump source is driven together, and the excess power is recovered through the energy recovery module. When testing the PTU, the primary clutch is engaged and the differential box is activated.

[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 realizing intelligent matching of the drive end output power to meet the actual test 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 to test EDP. In this allocation mode, the engine-driven pump drive module and the energy recovery module are started. The variable frequency motor drives the EDP to operate and load the load. The excess power is recovered by 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 to test EMP. In this allocation mode, the electric pump drive module and the energy recovery module are started. The DC motor drives the EMP to operate and load the load. The excess power is recovered by 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 to test PTU. In this allocation mode, the following are started: engine driven pump drive module, electric pump drive module, power conversion device connection module, and PTU. The DC motor drives the EMP to operate and load the load. At the same time, the output end of the EMP is connected to the input end of the PTU through the power conversion device connection module, and the EMP drives the PTU; the output end of the PTU is connected to the input end of the EDP, and the power of the EMP is transmitted through the PTU, and drives the EDP to operate together with the variable frequency motor, thereby ensuring the normal operation of the load.

[0046] like Figure 5As shown, allocation mode 4 is used to test PTU. In this allocation mode, the following are started: engine driven pump drive module, electric pump drive module, power conversion device connection module, and PTU. The variable frequency motor drives the EDP to operate and load the load. At the same time, the output end of the EDP is connected to the input end of the PTU through the power conversion device connection module, and the EDP drives the PTU; the output end of the PTU is connected to the input end of the EMP, and the power of the EDP is transmitted through the PTU, and drives the EMP to operate together with the DC motor, thereby ensuring the normal operation of the load.

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

[0048] like Figure 7 As shown, when the civil aircraft multi-subsystem pump source integrated test system is tested, its external control end 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 the load characteristics under actual working conditions and inputting them into the test control unit. The load characteristics include load change, load torque, load pressure, etc. Through accurate load simulation, a test environment close to the actual working conditions is provided for the test system (mainly controlling the load end, i.e. controlling the controlled object) to ensure the accuracy and reliability of the test.

[0050] The test control unit is responsible for the automated control of the entire test process of the test system, including: starting or stopping the test process, the action of the drive distribution module, the parameter setting of the drive end and the load end, and the test system status monitoring, etc. It ensures that the test is carried out according to the predetermined procedures and parameters, and realizes the automated and intelligent control of the test process.

[0051] The network connection unit provides the connection function between the test system and the external network, realizes the remote access, transmission and sharing of data, facilitates the remote monitoring, analysis and report distribution of test data, and supports remote fault diagnosis and technical support.

[0052] The data analysis and storage unit collects various types of data generated by the test system during the test process through the network connection unit, including pressure, flow, temperature, time, etc., and analyzes, stores and manages these data, and feeds them back to the test control unit to provide original data support for subsequent data analysis, report generation and test result evaluation, ensuring data integrity and traceability.

[0053] The test control unit converts the working conditions input by the load simulation unit into load-side control instructions, simulates load characteristics, and inputs them into the test system. The test process data collected and analyzed by the data analysis 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, it is fed back to the load simulation unit for parameter adjustment.

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

[0055] Those skilled in the art can understand that the above are only preferred examples of the invention and are not intended to limit the invention. Although the invention is described in detail with reference to the above examples, those skilled in the art can still modify the technical solutions recorded in the above examples or replace some of the technical features therein with equivalents. Any modification, equivalent replacement, etc. made within the spirit and principle of the invention shall be included in the protection scope of the invention.

Claims

1. A civil aircraft multi-subsystem pump source integrated test system, characterized in that: include: An engine driven pump driving module, an electric pump driving 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 driving module includes a variable frequency motor and an engine driven pump driven thereby, the electric pump driving module includes a DC motor and an electric pump driven thereby, and the driving end includes the engine driven pump and the electric pump; The engine driven pump driving module and the electric pump driving 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, and the driving end of the power conversion device is the engine driven pump and / or the electric pump; the energy recovery module is respectively connected to the engine driven pump and the electric pump, 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 civil aircraft multi-subsystem pump source integrated test system according to claim 1 is characterized in that: The drive distribution module intelligently distributes the drive end power in the following five distribution modes: Distribution mode 1 is used to test the engine driven pump. Under this distribution mode, under the action of the drive parallel module, the variable frequency motor drives the engine driven pump to operate and load the load, and the excess power is recovered through the energy recovery module; Distribution mode 2 is used to test the electric pump. Under this distribution mode, under the action of the parallel driving module, the DC motor drives the electric pump to operate and load the load, and the excess power is recovered through the energy recovery module; Distribution mode 3 is used to test the power conversion device. Under this distribution mode, under the action of the driving 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 to realize the electric pump driving the power conversion device; the variable frequency motor is connected to the first input end of the engine driven pump, and the output end of the power conversion device is connected to the second input end of the engine driven pump, so that the electric pump and the variable frequency motor jointly drive the engine driven pump to operate; Distribution mode 4 is used to test the power conversion device. Under this distribution mode, under the action of the driving parallel module, the variable frequency motor drives the engine driven pump to operate and load the load. 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, so that the engine driven 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 driven pump and the DC motor jointly drive the electric pump to operate; Distribution mode 5 is used to test a high-power pump source. Under this distribution mode, under the action of the drive parallel module, the variable frequency motor drives the engine driven pump, 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, 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, and 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 distributed according to the drive distribution module; and the excess power is recovered through the energy recovery module.

3. The civil aircraft multi-subsystem pump source integrated test system according to claim 1, characterized in that: The power conversion device connection module includes a dual-stage clutch and a connecting pipeline; the dual-stage clutch includes a primary clutch and a secondary clutch, the primary clutch is used to preliminarily connect the power source and the transmission system, and is started when testing the power conversion device to achieve smooth power transmission and reduce impact; the secondary clutch is started when testing a high-power pump source and is used to transmit greater torque to the output end; the connecting pipeline is used to transmit power or control signals from one module to another.

4. The civil aircraft multi-subsystem pump source integrated test system 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 civil aircraft multi-subsystem pump source integrated test system according to claim 1, characterized in that: The drive parallel module includes a dual-stage clutch and a differential gearbox; the differential gearbox is used to allow two input ends, namely the engine-driven pump and the electric pump, to rotate differentially; the dual-stage clutch includes a primary clutch and a secondary clutch, the primary clutch is used to preliminarily connect the power source and the transmission system, and is started when testing the power conversion device to achieve smooth power transmission; the secondary clutch is started when testing the high-power pump source, and 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, and the high-power pump source is driven together, and the excess power is recovered through the energy recovery module.

6. The civil aircraft multi-subsystem pump source integrated test system according to claim 1, characterized in that: The drive distribution module calculates the actual required drive power according to the actual test requirements of the pump source, distributes the total power of the engine-driven pump drive module and the electric pump drive module, and realizes intelligent matching of the output power of the drive end.

7. The civil aircraft multi-subsystem pump source integrated test system according to claim 1, characterized in that: Also includes a control terminal, the control terminal 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 them into the test control unit; The test control unit is used to automatically control the entire test process of the test system to ensure that the test is carried out according to the predetermined procedures and parameters; the control content includes: starting or stopping the test process, the control mode of the drive distribution module, the parameter setting of the drive end and the load end, and the test system status monitoring; The network connection unit is used to provide a 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 process through the network connection unit, analyzes, stores and manages the data, and feeds them 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-end control instructions, simulate load characteristics, and input them into the test system; the test process data collected and analyzed by the data analysis storage unit is processed by the test control unit to determine whether the test system is safely operating according to the working conditions set by the load simulation unit. If not, it is fed back to the load simulation unit for parameter adjustment.

8. The civil aircraft multi-subsystem pump source integrated test system according to claim 7, characterized in that: The load characteristics include: load change, load torque and load pressure.

9. The civil aircraft multi-subsystem pump source integrated test system according to claim 7, characterized in that: The various types of data generated by the test system during the test process include: pressure, flow, temperature, and time.

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