A Ground Drive Test Device for Integrated Hydraulic Modules of Civil Rotorcraft

Abstract

This invention belongs to the field of aviation technology, and particularly relates to a ground drive test device for an integrated hydraulic module of a civil rotorcraft. The device includes: a frequency converter, an electric motor, a torque sensor, a fixed displacement pump, a pressure oil circuit temperature sensor, an output oil circuit temperature sensor, a return oil temperature sensor, a pressure oil circuit flow sensor, an output oil circuit flow sensor, a return oil flow sensor, a pressure oil circuit pressure sensor, an output oil circuit pressure sensor, a return oil pressure sensor, a two-position three-way solenoid valve, an integrated hydraulic module for the rotorcraft, a tail servo booster, a left front servo booster, a left rear servo booster, a right front servo booster, a hydraulic oil tank with a contaminant discharge port, an online oil contamination detection device, an oil temperature control device, and a proportional relief valve assembly. The device verifies the integrity, safety, and functionality of the integrated hydraulic module for the rotorcraft.

Description

Technical Field

[0001] This invention belongs to the field of aviation technology, and in particular relates to a ground drive test device for an integrated hydraulic module of a civil rotorcraft. Background Technology

[0002] In existing civil rotorcraft, hydraulic components and piping systems are complex and numerous. Installing hydraulic systems within the limited space of a civil rotorcraft is labor-intensive, heavy, and bulky. To address this issue, current rotorcraft hydraulic systems generally adopt integrated modular design technology, integrating pressurized oil tanks, filters, overflow valves, sensors, alarm signal devices, etc. However, due to the complex structure and multiple functions of integrated hydraulic modules, the interaction between components may lead to increased internal leakage, increased pressure loss, increased temperature, and increased oil contamination levels. To verify whether the performance indicators of integrated hydraulic modules meet the requirements of the control system and to discover potential faults and defects in the hydraulic system, test devices should be designed to conduct tests. Summary of the Invention

[0003] This invention provides a ground-based test device for integrated hydraulic modules of civil rotorcraft, which accurately and effectively solves the problem of simulating the state of integrated hydraulic modules of rotorcraft under all operating conditions, such as load changes, control rate changes, contamination changes, and oil temperature changes; accurately and effectively solves the problem of simulating fault states of integrated hydraulic modules of rotorcraft, such as abnormal torque changes, abnormal speed changes, and abnormal load changes; accurately and effectively solves the problem of state evaluation of integrated hydraulic modules of rotorcraft; and effectively verifies the contents involved in airworthiness clauses, mainly including CCAR27.1301, CCAR27.1435, CCAR29.1301, and CCAR29.1435.

[0004] The technical solution of the present invention:

[0005] A ground drive test device for an integrated hydraulic module of a civil rotorcraft, the device comprising: a frequency converter 1, an electric motor 2, a torque sensor 3, a fixed displacement pump 4, a pressure oil circuit temperature sensor 5a, an output oil circuit temperature sensor 5b, a return oil temperature sensor 5c, a pressure oil circuit flow sensor 6a, an output oil circuit flow sensor 6b, a return oil flow sensor 6c, a pressure oil circuit pressure sensor 7a, an output oil circuit pressure sensor 7b, a return oil pressure sensor 7c, a two-position three-way solenoid valve 8, an integrated hydraulic module for rotorcraft 9, a tail servo booster 10, a left front servo booster 11a, a left rear servo booster 11b, a right front servo booster 11c, a hydraulic oil tank with a contaminant discharge port 12, an online oil contamination detection device 13, an oil temperature control device 14, and a proportional relief valve assembly 15.

[0006] Define the return oil interface of the integrated hydraulic module and hydraulic pump housing of the rotorcraft as port A, the suction oil interface of the integrated hydraulic module and hydraulic pump of the rotorcraft as port B, the return oil interface of the integrated hydraulic module and booster of the rotorcraft as port C, the oil supply interface of the integrated hydraulic module and booster of the rotorcraft as port D, and the oil supply interface of the integrated hydraulic module and hydraulic pump of the rotorcraft as port E.

[0007] The output shaft of motor 2 is mechanically connected to the drive shaft of fixed displacement pump 4, and a torque sensor 3 is installed between the two shafts. Frequency converter 1 is electrically connected to motor 2 to control its speed. The suction port a of fixed displacement pump 4 is connected to port c of two-position three-way solenoid valve 8. Port b of two-position three-way solenoid valve 8 is connected to the supply port of hydraulic oil tank 12 with contaminant discharge port. Port a of two-position three-way solenoid valve 8 is connected to one end of return oil flow sensor 6c. The other end of return oil flow sensor 6c is connected to one end of return oil temperature sensor 5c, one end of return oil pressure sensor 7c, and port B of rotorcraft integrated hydraulic module. The outlet port b of fixed displacement pump 4 is connected to one end of online oil contamination detection device 13. The housing port c of fixed displacement pump 4 is connected to port A of rotorcraft integrated hydraulic module. The other end of online oil contamination detection device 13 is connected to the inlet of proportional relief valve assembly 15, one end of pressure oil circuit temperature sensor 5a, and one end of pressure oil circuit flow sensor 6a. The proportional relief valve assembly 15... The section of the pressure oil circuit connected to the pressure oil circuit flow sensor 6a must pass through the oil temperature control device 14. The outlet of the proportional relief valve assembly 15 is connected to the return port of the hydraulic oil tank 12 with a contaminant discharge port. The other end of the pressure oil circuit flow sensor 6a is connected to the pressure oil circuit pressure sensor 7a and the E port of the rotorcraft integrated hydraulic module. The D port of the rotorcraft integrated hydraulic module is connected to the output oil circuit pressure sensor 7b, the output oil circuit temperature sensor 5b, and the output oil circuit flow sensor 7a. One end of the flow sensor 6b is connected to the oil inlet of the left front servo booster 11a, the oil inlet of the left rear servo booster 11b, the oil inlet of the right front servo booster 11c, and the oil inlet of the tail servo booster 10, respectively. The return ports of the left front servo booster 11a, the left rear servo booster 11b, the right front servo booster 11c, and the tail servo booster 10 are respectively connected to the C port of the integrated hydraulic module of the rotorcraft.

[0008] Furthermore, the frequency converter 1 is used to adjust the speed of the motor 2, thereby simulating the fault state of the pressure supply of the integrated hydraulic module of the rotorcraft, as well as the working performance of the integrated hydraulic module of the rotorcraft under different flow conditions.

[0009] Furthermore, the proportional relief valve assembly 15 is used to regulate pressure, thereby assessing the performance of the integrated hydraulic module of the rotorcraft under different pressure conditions.

[0010] Furthermore, the oil temperature control device 14 is used to adjust the oil temperature input to the integrated hydraulic module of the rotorcraft, thereby evaluating the working performance of the integrated hydraulic module of the rotorcraft under different oil temperature conditions.

[0011] Furthermore, the hydraulic oil tank 12 with the contaminant discharge port is used in conjunction with the online oil contamination detection device 13 to assess the working performance of the integrated hydraulic module of the rotorcraft under different oil contamination conditions.

[0012] Furthermore, the two-position three-way solenoid valve 8 is used to switch the hydraulic oil tank 12 with the pollutant release port and the return oil port of the rotorcraft integrated hydraulic module 9.

[0013] Furthermore, pressure oil circuit temperature sensor 5a, output oil circuit temperature sensor 5b, return oil temperature sensor 5c, pressure oil circuit flow sensor 6a, output oil circuit flow sensor 6b, return oil flow sensor 6c, pressure oil circuit pressure sensor 7a, output oil circuit pressure sensor 7b, and return oil pressure sensor 7c are used at different test points to monitor the working status of the integrated hydraulic module of the rotorcraft.

[0014] Furthermore, the metering pump 4 is a gear pump.

[0015] Benefits and effects of the technical solution of this invention:

[0016] (1) A speed regulation method combining permanent magnet synchronous motor and frequency converter is adopted. The permanent magnet synchronous motor has high power density and good control performance, and can achieve speed regulation from 0 to 8000 rpm. By adjusting the speed of the permanent magnet synchronous motor, the flow rate change of the integrated hydraulic module of the rotorcraft can be accurately simulated.

[0017] (2) A hydraulic oil tank with a contaminant discharge port is adopted. This component is used in conjunction with an online oil contamination detection device. Based on the test results of the online oil contamination detection device, the quantity and type of contaminants added to or reduced in the hydraulic oil tank with the contaminant discharge port can accurately simulate the working state of the integrated hydraulic module of the rotorcraft under different contamination levels (NAS1638-6 to NAS1638-9), thereby accurately assessing the working condition of the integrated hydraulic module of the rotorcraft under different contamination levels.

[0018] (3) An oil temperature control device is applied to the input port of the integrated hydraulic module of the rotorcraft instead of the oil tank. This position is the closest to the integrated hydraulic module of the rotorcraft. This can avoid the oil temperature being affected by the heat emitted by the metering pump during operation, as well as by other environmental factors. Installing the oil temperature control device at the input port of the integrated hydraulic module of the rotorcraft can accurately assess the working status of the integrated hydraulic module of the rotorcraft at different oil temperatures (-55℃ to 135℃).

[0019] (4) A proportional overflow valve assembly with a filter is adopted to ensure that pollutants will not enter the test system when conducting pollution level capability tests. Installing a proportional overflow valve assembly with a filter not only avoids affecting the lifespan of the proportional overflow valve assembly when conducting pollution level status assessments of the integrated hydraulic module of the rotorcraft, but also accurately simulates the working state of the integrated hydraulic module of the rotorcraft under different pressures.

[0020] (5) The detection points for temperature, pressure and flow rate are reasonably set, which can meet the working needs and avoid too many test points, thus increasing the cost of the device. The pressure sensor is set on the pipeline closest to the interface of the rotorcraft integrated hydraulic module, and there are no other devices between the pressure sensor and the interface of the rotorcraft integrated hydraulic module. The pressure gauge is set at 2 to 4 times the inner diameter of the pipeline from the input or output port of the rotorcraft integrated hydraulic module.

[0021] (6) In order to meet the testing function of the integrated hydraulic module of rotorcraft under different pollution conditions, a gear pump with strong anti-pollution capability was adopted instead of a plunger pump, which not only met the testing requirements, reduced costs, but also improved the life of the device. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the structure of a ground drive test device for an integrated hydraulic module of a civil rotorcraft, provided in an embodiment of the present invention.

[0023] The components include: frequency converter 1, electric motor 2, torque sensor 3, fixed displacement pump 4, pressure oil circuit temperature sensor 5a, output oil circuit temperature sensor 5b, return oil temperature sensor 5c, pressure oil circuit flow sensor 6a, output oil circuit flow sensor 6b, return oil flow sensor 6c, pressure oil circuit pressure sensor 7a, output oil circuit pressure sensor 7b, return oil pressure sensor 7c, two-position three-way solenoid valve 8, rotorcraft integrated hydraulic module 9, tail servo booster 10, left front servo booster 11a, left rear servo booster 11b, right front servo booster 11c, hydraulic oil tank with contaminant discharge port 12, online oil contamination detection device 13, oil temperature control device 14, and proportional relief valve assembly 15. Detailed Implementation

[0024] The technical solution of the present invention will now be described in detail with reference to the accompanying drawings.

[0025] This invention provides a ground-drive test device for an integrated hydraulic module of a civil rotorcraft, which has the following functions:

[0026] (1) Verify that the integrated hydraulic module can ensure that the civil rotorcraft can complete all normal flight tasks, including start-up, climb, cruise, maneuver, return, and landing. The specific content mainly includes the matching with the control system, namely the left front servo booster, left rear servo booster, right front servo booster, and tail servo booster, under the specified flight envelope and changing load conditions, including speed, output force, and response speed.

[0027] (2) Simulate the most unfavorable state (flight attitude, altitude and speed) of civil rotorcraft to verify the function of the integrated hydraulic module. This mainly includes the matching of the control system with the left front servo booster, left rear servo booster, right front servo booster and tail servo booster under the load conditions, environmental conditions, pollution conditions, and oil temperature under extreme conditions. This includes speed, output force and response speed, as well as hydraulic system pressure and flow, alarm, signal and conversion functions.

[0028] (3) Evaluate the fault resistance of the integrated hydraulic module, mainly including the fault state of the hydraulic system itself, such as the matching of the control system, namely the left front servo booster, left rear servo booster, right front servo booster and tail servo booster under working conditions such as reduced flow and reduced pressure, including speed, output force and response speed.

[0029] (4) It is able to effectively verify the provisions concerning the hydraulic systems and components of civil rotorcraft and meet the airworthiness requirements.

[0030] This invention provides a ground-based test device for an integrated hydraulic module of a civil rotorcraft, such as... Figure 1 As shown, it includes: frequency converter 1, electric motor 2, torque sensor 3, fixed displacement pump 4, pressure oil circuit temperature sensor 5a, output oil circuit temperature sensor 5b, return oil temperature sensor 5c, pressure oil circuit flow sensor 6a, output oil circuit flow sensor 6b, return oil flow sensor 6c, pressure oil circuit pressure sensor 7a, output oil circuit pressure sensor 7b, return oil pressure sensor 7c, two-position three-way solenoid valve 8, rotorcraft integrated hydraulic module 9, tail servo booster 10, left front servo booster 11a, left rear servo booster 11b, right front servo booster 11c, hydraulic oil tank with contaminant discharge port 12, online oil contamination detection device 13, oil temperature control device 14, and proportional relief valve assembly 15.

[0031] The output shaft of motor 2 is mechanically connected to the drive shaft of fixed displacement pump 4, and a torque sensor 3 is installed between the two shafts. Frequency converter 1 is electrically connected to motor 2 to control its speed. The suction port a of fixed displacement pump 4 is connected to port c of two-position three-way solenoid valve 8. Port b of two-position three-way solenoid valve 8 is connected to the supply port of hydraulic oil tank 12 with contaminant discharge port. Port a of two-position three-way solenoid valve 8 is connected to one end of return flow sensor 6c. The other end of return flow sensor 6c is connected to one end of return temperature sensor 5c, one end of return pressure sensor 7c, and port B of rotorcraft integrated hydraulic module. The outlet port b of fixed displacement pump 4 is connected to one end of online oil contamination detection device 13. The housing port c of fixed displacement pump 4 is connected to port A of rotorcraft integrated hydraulic module. The other end of online oil contamination detection device 13 is connected to the inlet of proportional relief valve assembly 15, one end of pressure oil circuit temperature sensor 5a, and one end of pressure oil circuit flow sensor 6a. Proportional relief valve assembly 15... The section of the pressure oil circuit connected to the inlet of the oil inlet and the pressure oil circuit flow sensor 6a must pass through the oil temperature control device 14. The outlet of the proportional relief valve assembly 15 is connected to the return port of the hydraulic oil tank 12 with a contaminant discharge port. The other end of the pressure oil circuit flow sensor 6a is connected to the pressure oil circuit pressure sensor 7a and the E port of the rotorcraft integrated hydraulic module, respectively. The D port of the rotorcraft integrated hydraulic module is connected to the output oil circuit pressure sensor 7b, the output oil circuit temperature sensor 5b, and the output oil circuit flow sensor 7a, respectively. One end of the flow sensor 6b is connected to the oil inlet of the left front servo booster 11a, the oil inlet of the left rear servo booster 11b, the oil inlet of the right front servo booster 11c, and the oil inlet of the tail servo booster 10, respectively. The return ports of the left front servo booster 11a, the left rear servo booster 11b, the right front servo booster 11c, and the tail servo booster 10 are respectively connected to the C port of the integrated hydraulic module of the rotorcraft.

[0032] This invention employs a combination of electromechanical and hydraulic methods, utilizing mechanical, hydraulic, and electronic control technologies, as well as sensing and detection technologies. The specific technical solution is as follows:

[0033] A schematic diagram of the working scheme of the ground drive test device for integrated hydraulic modules of rotorcraft is shown below. Figure 1As shown. The hydraulic power source of the ground drive test device for the integrated hydraulic module of the rotorcraft comes from the fixed displacement pump 4. The electric motor 2 drives the fixed displacement pump 4. A torque sensor 3 is installed between the output shaft of the electric motor 2 and the input shaft of the fixed displacement pump 4 to test the output torque of the electric motor 2. To simulate the pressure supply failure state of the integrated hydraulic module of the rotorcraft, this device uses a frequency converter 1 to adjust the speed of the electric motor 2 to evaluate the working performance of the integrated hydraulic module of the rotorcraft under different flow conditions. This device uses a proportional relief valve assembly 15 with a filter to adjust the system pressure to evaluate the working performance of the integrated hydraulic module of the rotorcraft under different pressure conditions. This device uses an oil temperature control device 14 to adjust the input oil temperature of the rotorcraft. The device measures the oil temperature of the integrated hydraulic module to assess its performance under different oil temperature conditions. It employs a hydraulic oil tank 12 with a contaminant discharge port, which works in conjunction with an online oil contamination detection device 13 to evaluate the integrated hydraulic module's performance under different oil contamination conditions. A two-position three-way solenoid valve 8 is used to switch between the hydraulic oil tank 12 with the contaminant discharge port and the return port B of the integrated hydraulic module 9. Temperature sensors 5a, 5b, and 5c, flow sensors 6a, 6b, and 6c, and pressure sensors 7a, 7b, and 7c are used at different test points to monitor the operating status of the integrated hydraulic module.

[0034] Benefits and effects of the technical solution of this invention:

[0035] (1) A speed regulation method combining permanent magnet synchronous motor and frequency converter is adopted. The permanent magnet synchronous motor has high power density and good control performance, and can achieve speed regulation from 0 to 8000 rpm. By adjusting the speed of the permanent magnet synchronous motor, the flow rate change of the integrated hydraulic module of the rotorcraft can be accurately simulated.

[0036] (2) A hydraulic oil tank with a contaminant discharge port is adopted. This component is used in conjunction with an online oil contamination detection device. Based on the test results of the online oil contamination detection device, the quantity and type of contaminants added to or reduced in the hydraulic oil tank with the contaminant discharge port can accurately simulate the working state of the integrated hydraulic module of the rotorcraft under different contamination levels (NAS1638-6 to NAS1638-9), thereby accurately assessing the working condition of the integrated hydraulic module of the rotorcraft under different contamination levels.

[0037] (3) An oil temperature control device is applied to the input port of the integrated hydraulic module of the rotorcraft instead of the oil tank. This position is the closest to the integrated hydraulic module of the rotorcraft. This can avoid the oil temperature being affected by the heat emitted by the metering pump during operation, as well as by other environmental factors. Installing the oil temperature control device at the input port of the integrated hydraulic module of the rotorcraft can accurately assess the working status of the integrated hydraulic module of the rotorcraft at different oil temperatures (-55℃ to 135℃).

[0038] (4) A proportional overflow valve assembly with a filter is adopted to ensure that pollutants will not enter the test system when conducting pollution level capability tests. Installing a proportional overflow valve assembly with a filter not only avoids affecting the lifespan of the proportional overflow valve assembly when conducting pollution level status assessments of the integrated hydraulic module of the rotorcraft, but also accurately simulates the working state of the integrated hydraulic module of the rotorcraft under different pressures.

[0039] (5) The detection points for temperature, pressure and flow rate are reasonably set, which can meet the working needs and avoid too many test points, thus increasing the cost of the device. The pressure sensor is set on the pipeline closest to the interface of the rotorcraft integrated hydraulic module, and there are no other devices between the pressure sensor and the interface of the rotorcraft integrated hydraulic module. The pressure gauge is set at 2 to 4 times the inner diameter of the pipeline from the input or output port of the rotorcraft integrated hydraulic module.

[0040] (6) In order to meet the testing function of the integrated hydraulic module of rotorcraft under different pollution conditions, a gear pump with strong anti-pollution capability was adopted instead of a plunger pump, which not only met the testing requirements, reduced costs, but also improved the life of the device.

Claims

1. A ground-drive test device for an integrated hydraulic module of a civil rotorcraft, characterized in that, The device includes: a frequency converter (1), a motor (2), a torque sensor (3), a fixed displacement pump (4), a pressure oil circuit temperature sensor (5a), an output oil circuit temperature sensor (5b), a return oil temperature sensor (5c), a pressure oil circuit flow sensor (6a), an output oil circuit flow sensor (6b), a return oil flow sensor (6c), a pressure oil circuit pressure sensor (7a), an output oil circuit pressure sensor (7b), a return oil pressure sensor (7c), a two-position three-way solenoid valve (8), a rotorcraft integrated hydraulic module (9), a tail servo booster (10), a left front servo booster (11a), a left rear servo booster (11b), a right front servo booster (11c), a hydraulic oil tank with a contaminant discharge port (12), an online oil contamination detection device (13), an oil temperature control device (14), and a proportional relief valve assembly (15). Define the return oil interface of the integrated hydraulic module and hydraulic pump housing of the rotorcraft as port A, the suction oil interface of the integrated hydraulic module and hydraulic pump of the rotorcraft as port B, the return oil interface of the integrated hydraulic module and booster of the rotorcraft as port C, the oil supply interface of the integrated hydraulic module and booster of the rotorcraft as port D, and the oil supply interface of the integrated hydraulic module and hydraulic pump of the rotorcraft as port E. The output shaft of the electric motor (2) is mechanically connected to the drive shaft of the metering pump (4), and a torque sensor (3) is installed between the two shafts. The frequency converter (1) is electrically connected to the electric motor (2) to control the speed of the electric motor (2). The suction port a of the metering pump (4) is connected to the c port of the two-position three-way solenoid valve (8). The b port of the two-position three-way solenoid valve (8) is connected to the oil supply port of the hydraulic oil tank (12) with a contaminant discharge port. The a port of the two-position three-way solenoid valve (8) is connected to one end of the return oil flow sensor (6c), and the other end of the return oil flow sensor (6c) is connected to... One end of the return oil temperature sensor (5c), one end of the return oil pressure sensor (7c), and port B of the rotorcraft integrated hydraulic module are connected. The oil outlet b of the metering pump (4) is connected to one end of the online oil contamination detection device (13). The oil port c of the casing of the metering pump (4) is connected to port A of the rotorcraft integrated hydraulic module. The other end of the online oil contamination detection device (13) is connected to the oil inlet of the proportional relief valve assembly (15), one end of the pressure oil circuit temperature sensor (5a), and one end of the pressure oil circuit flow sensor (6a). The section of the pressure oil circuit connected to the inlet of (15) and the pressure oil circuit flow sensor (6a) must pass through the oil temperature control device (14). The outlet of the proportional relief valve assembly (15) is connected to the return port of the hydraulic oil tank (12) with a contaminant discharge port. The other end of the pressure oil circuit flow sensor (6a) is connected to the pressure oil circuit pressure sensor (7a) and the E port of the rotorcraft integrated hydraulic module, respectively. The D port of the rotorcraft integrated hydraulic module is connected to the output oil circuit pressure sensor (7b), the output oil circuit temperature sensor (5b), and the output oil circuit flow sensor (6a). One end of the flow sensor (6b) is connected to the oil inlet of the left front servo booster (11a), the oil inlet of the left rear servo booster (11b), the oil inlet of the right front servo booster (11c), and the oil inlet of the tail servo booster (10), respectively. The return ports of the left front servo booster (11a), the left rear servo booster (11b), the right front servo booster (11c), and the tail servo booster (10) are respectively connected to the C port of the integrated hydraulic module of the rotorcraft.

2. The integrated hydraulic module ground drive test device for civil rotorcraft according to claim 1, characterized in that, The frequency converter (1) is used to adjust the speed of the motor (2) to simulate the fault state of the pressure supply of the integrated hydraulic module of the rotorcraft, as well as the working performance of the integrated hydraulic module of the rotorcraft under different flow conditions.

3. The integrated hydraulic module ground drive test device for civil rotorcraft according to claim 1, characterized in that, The proportional relief valve assembly (15) is used to regulate pressure, thereby assessing the performance of the integrated hydraulic module of the rotorcraft under different pressure conditions.

4. The integrated hydraulic module ground drive test device for civil rotorcraft according to claim 1, characterized in that, The oil temperature control device (14) is used to adjust the oil temperature of the integrated hydraulic module of the rotorcraft, thereby evaluating the working performance of the integrated hydraulic module of the rotorcraft under different oil temperature conditions.

5. The integrated hydraulic module ground drive test device for civil rotorcraft according to claim 1, characterized in that, The hydraulic oil tank (12) with the pollutant discharge port is used in conjunction with the online oil contamination detection device (13) to evaluate the working performance of the integrated hydraulic module of the rotorcraft under different oil contamination conditions.

6. The integrated hydraulic module ground drive test device for civil rotorcraft according to claim 1, characterized in that, The two-position three-way solenoid valve (8) is used to switch the return oil port of the hydraulic oil tank (12) with the pollutant release port and the integrated hydraulic module (9) of the rotorcraft.

7. The integrated hydraulic module ground drive test device for civil rotorcraft according to claim 1, characterized in that, At different test points, pressure oil circuit temperature sensor (5a), output oil circuit temperature sensor (5b), return oil temperature sensor (5c), pressure oil circuit flow sensor (6a), output oil circuit flow sensor (6b), return oil flow sensor (6c), pressure oil circuit pressure sensor (7a), output oil circuit pressure sensor (7b), and return oil pressure sensor (7c) are used to monitor the working status of the integrated hydraulic module of the rotorcraft.

8. The ground drive test device for an integrated hydraulic module of a civil rotorcraft according to claim 1, characterized in that, The metering pump (4) is a gear pump.

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