Aircraft ground hydraulic source test tooling

Abstract

The utility model provides an aircraft ground hydraulic source test fixture, including an aircraft oil pump truck hydraulic source system to be tested, the outlet of the aircraft oil pump truck hydraulic source system is connected to a power unit for converting hydraulic energy into mechanical energy, the output end of the power unit is connected to a deceleration ratio unit, the deceleration ratio unit is used to load the converted mechanical energy to a load unit according to a wide range of deceleration; the load unit is invertedly installed on a test frame; the load unit is simultaneously connected to a load adjustment unit for adjusting the stroke and resetting; the return oil end of the power unit is connected to a buffer return oil unit. This fixture and method can be used to simulate the load of an oil pump truck and a hydraulic source, complete the pressure supply, flow supply, sealing, heat dissipation and transient response and other functional tests of the aircraft oil pump truck and the hydraulic source, store and analyze the test data, and test the comprehensive performance of the hydraulic system of the aircraft oil pump truck and the hydraulic source, and at the same time have the load performance test function of a single hydraulic oil pump.

Description

Technical Field

[0001] The utility model belongs to the field of aviation support equipment manufacturing, and in particular relates to an aircraft ground hydraulic source test tool. Background Art

[0002] Aircraft oil pump trucks are mainly used to provide hydraulic sources for different hydraulic power mechanisms on the aircraft during aircraft maintenance to drive their corresponding actions, including aircraft landing gear retraction and extension, front wheel turning, flap retraction, speed brake retraction, air inlet adjustment and other hydraulic power mechanisms. These different hydraulic power mechanisms require different hydraulic pressures and flows during operation. This requires that the aircraft oil pump truck must undergo performance loading simulation tests before leaving the factory to determine whether it can meet the use requirements. The main test content includes completing the aircraft oil pump truck, hydraulic source pressure supply, flow supply, sealing, heat dissipation and transient response and other functional tests. At present, there is no dedicated test fixture, so it is necessary to design corresponding test fixtures to test the aircraft oil pump truck. Utility Model Content

[0003] The purpose of the utility model is to provide an aircraft ground hydraulic source test tool, which can be used to simulate the load of an oil pump truck and a hydraulic source, complete functional tests such as pressure supply, flow supply, sealing, heat dissipation and transient response of the aircraft oil pump truck and the hydraulic source, store and analyze the test data, and inspect the comprehensive performance of the hydraulic system of the aircraft oil pump truck and the hydraulic source, and at the same time have the load performance test function of a single hydraulic oil pump.

[0004] In order to realize the above-mentioned technical features, the purpose of the utility model is realized as follows: an aircraft ground hydraulic source test tooling comprises an aircraft oil pump truck hydraulic source system to be tested, the outlet of the aircraft oil pump truck hydraulic source system is connected to a power unit for converting hydraulic energy into mechanical energy, the output end of the power unit is connected to a reduction ratio unit, and the reduction ratio unit is used to load the converted mechanical energy to a load unit according to a wide range of reduction; the load unit is invertedly mounted on a test frame; the load unit is also connected to a load adjustment unit for adjusting the stroke and resetting.

[0005] The aircraft oil pump truck hydraulic source system includes an oil pump truck pump group for providing hydraulic power, a pressure gauge and a flow meter are installed at the hydraulic output end of the oil pump truck pump group, the oil inlet of the oil pump truck pump group is connected to a test oil tank, the test oil tank is fixedly installed on the top of the oil tank mounting frame, and a ladder is provided on the oil tank mounting frame.

[0006] The power unit comprises a hydraulic motor, the hydraulic motor is connected to the oil outlet of the hydraulic source system of the aircraft oil pump truck, the output shaft of the hydraulic motor is connected to the input shaft of the reducer; the reducer is fixedly installed on the top of the reducer storage rack.

[0007] The speed reduction ratio unit includes a driving gear installed on the output shaft of the speed reducer, the driving gear meshes with the lifting rack for transmission, the lifting rack is slidably installed inside the rack mounting sleeve, and the top end of the lifting rack is connected to the input end of the load unit.

[0008] The test frame comprises a plurality of columns, the bottom ends of the columns are fixedly connected to the installation foundation through column pads, the tops of the columns are fixed with upper frames, and the bottom center of the upper frame is fixed with a cylinder installation flange.

[0009] The load unit includes a test cylinder, which is a double-acting hydraulic cylinder, including a cylinder outer tube, a mounting flange is provided at the top of the cylinder body of the cylinder outer tube, and the mounting flange is fixedly connected to the bottom end of the cylinder mounting flange of the test frame; a piston rod is installed inside the cylinder outer tube, and a buffer zone is provided at the inner bottom end of the cylinder outer tube.

[0010] The load adjustment unit includes an installation shell, a motor pump group is installed inside the installation shell, the oil inlet of the motor pump group is connected to the oil tank, and the oil outlet of the motor pump group is connected to the load unit through a safety valve and a reversing valve group; it also includes an electric proportional overflow valve installed on the return oil pipe.

[0011] The oil return end of the power unit is connected with a buffer oil return unit.

[0012] The buffer oil return unit comprises an oil return buffer, and an outlet of the oil return buffer is connected to the test oil tank through an electromagnetic oil return valve.

[0013] Also included is a test console, which includes a housing, a touch control screen, and an operating switch for controlling, monitoring, and adjusting a system load and a loading stroke;

[0014] It also includes an electric control cabinet and a test interface assembly. The test interface assembly is equipped with various types of aircraft ground hydraulic source connection joints to meet the testing of different types of aircraft ground hydraulic sources and oil pump trucks.

[0015] The utility model has the following beneficial effects:

[0016] 1. The tooling and method of the utility model can be used to simulate the load of oil pump trucks and hydraulic sources, complete functional tests such as pressure supply, flow supply, sealing, heat dissipation and transient response of aircraft oil pump trucks and hydraulic sources, store and analyze test data, and test the comprehensive performance of the hydraulic system of aircraft oil pump trucks and hydraulic sources. At the same time, it has the load performance test function of a single hydraulic oil pump.

[0017] 2. The above-mentioned power unit uses a hydraulic motor as an energy conversion mechanism to stably convert the variable energy output by the ground hydraulic source into mechanical energy. During the working process, the hydraulic motor is driven by the hydraulic source system of the aircraft oil pump truck, and the reducer is driven by the hydraulic motor.

[0018] 3. The above-mentioned speed reduction ratio unit can be used to load the mechanical energy converted by the hydraulic motor to the load unit according to a wide range of speed reduction.

[0019] 4. The load unit can be fixed and installed through the above-mentioned test frame.

[0020] 5. The above-mentioned load adjustment unit mainly simulates the loads of aircraft retracting and extending landing gear, front wheel turning, retracting flaps, retracting speed brakes, inlet duct adjustment, etc. through the continuously adjustable back pressure load of the rodless chamber of the hydraulic cylinder. The main working principle is to establish the corresponding simulated load through the linear opening of the electric proportional relief valve at the oil outlet of the rodless chamber of the cylinder.

[0021] 6. The buffer oil return unit is mainly used to receive the hydraulic oil source after the hydraulic motor is worked on. The high-flow oil source is decelerated through the buffer and then recovered to the hydraulic source tank on the test ground or the closed simulation tank provided by the tooling. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] The utility model is further described below in conjunction with the accompanying drawings and embodiments.

[0023] Figure 1 This is the principle diagram of the utility model system.

[0024] Figure 2 This is a three-dimensional diagram of the test tooling of the utility model from the first perspective.

[0025] Figure 3 This is a three-dimensional diagram of the test tooling of the utility model from the second perspective.

[0026] Figure 4 This is a three-dimensional diagram of the test tooling of the utility model from the third perspective.

[0027] Figure 5 This is a three-dimensional diagram of the fourth viewing angle of the test tooling of the utility model.

[0028] Figure 6 This is the front view of the test cylinder of the utility model.

[0029] Figure 7 For this utility model Figure 6 Medium AA view.

[0030] In the figure: aircraft oil pump truck hydraulic source system 1, power unit 2, speed reduction ratio unit 3, load adjustment unit 4, buffer oil return unit 5, test frame 6, load unit 7;

[0031] Test oil tank 101, oil pump truck pump unit 102, pressure gauge 103, flow meter 104;

[0032] Hydraulic motor 201, reducer 202, reducer storage rack 203;

[0033] Driving gear 301, lifting rack 302, rack mounting sleeve 303;

[0034] Motor pump group 401, oil tank 402, safety valve 403, reversing valve group 404, electric proportional relief valve 405, installation housing 406;

[0035] Oil return buffer 501, electromagnetic oil return valve 502;

[0036] Column 601, upper frame 602, cylinder mounting flange 603, column pad 604;

[0037] Install flange 701, cylinder outer tube 702, piston rod 703, and buffer zone 704. DETAILED DESCRIPTION

[0038] The embodiments of the present utility model are further described below in conjunction with the accompanying drawings.

[0039] Embodiment 1:

[0040] See also Figure 1-7 , an aircraft ground hydraulic source test fixture, comprising an aircraft oil pump truck hydraulic source system 1 to be tested, the outlet of the aircraft oil pump truck hydraulic source system 1 is connected to a power unit 2 for converting hydraulic energy into mechanical energy, the output end of the power unit 2 is connected to a deceleration ratio unit 3, the deceleration ratio unit 3 is used to load the converted mechanical energy to a load unit 7 according to a wide range of deceleration; the load unit 7 is invertedly installed on a test frame 6; the load unit 7 is also connected to a load adjustment unit 4 for adjusting the stroke and resetting; the return oil end of the power unit 2 is connected to a buffer return oil unit 5. This fixture and method can be used to simulate the load of an oil pump truck and a hydraulic source, complete the pressure supply, flow supply, sealing, heat dissipation and transient response and other functional tests of the aircraft oil pump truck and the hydraulic source, store and analyze the test data, and test the comprehensive performance of the hydraulic system of the aircraft oil pump truck and the hydraulic source, and at the same time have the load performance test function of a single hydraulic oil pump. By adopting the above-mentioned hydraulic source test fixture, the power unit 2 converts the hydraulic energy loaded by the test ground hydraulic source into mechanical energy, and loads the converted mechanical energy to the load unit 7 through the speed reduction ratio unit 3. The load unit is adjusted by the load adjustment unit 4 to realize the comprehensive performance detection of the hydraulic system of the test ground hydraulic source. The buffer return oil unit 5 is mainly used to recover the test hydraulic oil, and flows into the test source through different switching branches to realize the recycling of oil.

[0041] Furthermore, the aircraft oil pump truck hydraulic source system 1 includes an oil pump truck pump group 102 for providing hydraulic power, a pressure gauge 103 and a flow meter 104 are installed at the hydraulic output end of the oil pump truck pump group 102, an oil inlet of the oil pump truck pump group 102 is connected to a test oil tank 101, and the test oil tank 101 is fixedly installed on the top of the oil tank mounting frame 8, and a ladder is provided on the oil tank mounting frame 8. The aircraft oil pump truck hydraulic source system 1 is mainly an aircraft oil pump truck or other hydraulic power source.

[0042] Furthermore, the power unit 2 includes a hydraulic motor 201, which is connected to the oil outlet of the hydraulic source system 1 of the aircraft oil pump truck, and the output shaft of the hydraulic motor 201 is connected to the input shaft of the reducer 202; the reducer 202 is fixedly installed on the top of the reducer storage rack 203. The power unit 2 uses the hydraulic motor 201 as an energy conversion mechanism to stably convert the variable energy output by the ground hydraulic source into mechanical energy. During operation, the hydraulic motor 201 is driven by the hydraulic source system 1 of the aircraft oil pump truck, and the reducer 202 is driven by the hydraulic motor 201.

[0043] Furthermore, the reduction ratio unit 3 includes a driving gear 301 installed on the output shaft of the reducer 202, the driving gear 301 is meshed with the lifting rack 302 for transmission, the lifting rack 302 is slidably installed inside the rack mounting sleeve 303, and the top of the lifting rack 302 is connected to the input end of the load unit 7. The above-mentioned reduction ratio unit 3 can be used to load the mechanical energy converted by the hydraulic motor 201 to the load unit according to a wide range of deceleration. During the working process, the driving gear 301 is driven by the reducer 202, the lifting rack 302 is driven by the driving gear 301, and the load unit 7 is driven by the lifting rack 302, thereby achieving loading.

[0044] Furthermore, the test frame 6 includes a plurality of columns 601, the bottom ends of the columns 601 are fixedly connected to the installation base through column pads 604, an upper frame 602 is fixed to the top of the columns 601, and a cylinder mounting flange 603 is fixed to the bottom center of the upper frame 602. The load unit 7 can be fixed and installed through the above test frame 6.

[0045] Furthermore, the load unit 7 includes a test cylinder, which is a double-acting hydraulic cylinder, including a cylinder outer tube 702, a mounting flange 701 is provided at the top of the cylinder body of the cylinder outer tube 702, and the mounting flange 701 is fixedly connected to the bottom end of the cylinder mounting flange 603 of the test frame 6; a piston rod 703 is installed inside the cylinder outer tube 702, and a buffer zone 704 is provided at the inner bottom end of the cylinder outer tube 702.

[0046] Furthermore, the load regulating unit 4 includes a mounting shell 406, in which a motor pump group 401 is installed, the oil inlet of the motor pump group 401 is connected to the oil tank 402, and the oil outlet of the motor pump group 401 is connected to the load unit 7 through a safety valve 403 and a reversing valve group 404; and also includes an electric proportional relief valve 405 installed on the return oil pipe. The above-mentioned load regulating unit 4 mainly simulates the loads such as aircraft retracting and extending landing gear, front wheel turning, retracting flaps, retracting speed brakes, and air inlet adjustment through the continuously adjustable back pressure load of the rodless cavity of the hydraulic cylinder. The main working principle is to establish the corresponding simulated load through the linear opening of the electric proportional relief valve at the oil outlet of the rodless cavity of the cylinder. The load unit cylinder adopts a double-acting cylinder, equipped with an independent hydraulic motor pump group, to achieve the reset and stroke adjustment of the cylinder.

[0047] Furthermore, the buffer oil return unit 5 includes an oil return buffer 501, and the outlet of the oil return buffer 501 is connected to the test oil tank 101 through an electromagnetic oil return valve 502. The buffer oil return unit 5 is mainly used to receive the hydraulic oil source after the hydraulic motor is operated, and the high flow rate oil source is decelerated by the buffer and then recovered to the test ground hydraulic source tank or the closed simulation tank provided by the tooling.

[0048] Furthermore, it also includes a test console 9, which includes a shell, a touch control screen and an operating switch for controlling, monitoring and adjusting the system load and loading stroke.

[0049] Furthermore, it also includes an electric control cabinet 11 and a test interface assembly 10. The test interface assembly is equipped with various types of aircraft ground hydraulic source connection joints to meet the testing of different types of aircraft ground hydraulic sources and oil pump trucks.

[0050] Embodiment 2:

[0051] The overall structural layout of the utility model aircraft ground hydraulic source simulation test tooling is mainly open-type, and the test tooling is mainly divided into an operation area and a test area. The operation area is mainly equipped with a test console and a test interface component, which is convenient for the staff to operate the test. The test area is mainly equipped with a test frame, a hydraulic load unit, a hydraulic motor power unit, a pump station unit and a test oil tank. Each system unit component is directly installed on the ground in an open layout, which is convenient for system inspection and maintenance. The overall space size is 2900mm*3000mm*3235mm, covering an area of ​​8.7m2.

[0052] The test frame 6 is mainly used to carry the test cylinder to establish the test load. The main component profile is welded from square tubes. A cylinder mounting flange is welded on the top of the frame, and the cylinder assembly can be disassembled and installed as a whole. The four columns of the frame and the ground mounting position are welded with mounting flanges, which can be connected to the foundation assembly through expansion bolts.

[0053] The test cylinder is designed as a double-acting hydraulic cylinder, mainly composed of a piston rod, a cylinder outer tube, a mounting flange, a jacket nut, etc. The cylinder can be lifted up and down and its position can be set by resetting the valve group of the pump station to meet the adjustment of different load strokes. The full stroke of the piston rod is 930mm.

[0054] The hydraulic motor reduction mechanism is mainly composed of a variable hydraulic motor, a reducer, a lifting rack mechanism, a mechanical lifting device, etc. The main function is to convert the hydraulic energy output by the aircraft ground hydraulic source into mechanical energy through the hydraulic motor. After the reducer reduces the speed through the ratio, the mechanical energy is loaded to the mechanical lifting device through the gear rack. The mechanical lifting device achieves simulated load by lifting the hydraulic piston rod.

[0055] The buffer oil return unit 5 is composed of a motor pump group, a reversing valve group, a filter assembly, an oil tank, a protective shell, etc. Its main function is to provide hydraulic energy for the stroke adjustment and resetting of the test cylinder.

[0056] The test oil tank is mainly used to simulate the aircraft oil tank for closed working mode test of ground hydraulic source and oil recovery of hydraulic motor. The test oil tank is assembled by a simple working ladder to facilitate the maintenance of the test oil tank. The height of the test oil tank from the ground is about 1.8m, which is similar to the height of the aircraft oil tank, simulating the oil return back pressure of the aircraft oil tank to the greatest extent.

[0057] Embodiment 3:

[0058] Main technical indicators:

[0059] (1) Equipment power supply: AC380V / 50Hz;

[0060] (2) Number of systems: 1;

[0061] (3) Load test pressure: (4-40) MPa;

[0062] (4) Load test flow rate: (10-150) L / min;

[0063] (5) Load test temperature: (-20~+110)℃

[0064] (6) Working medium: No. 15 aviation hydraulic oil;

[0065] (7) Effective capacity of fuel tank: ≮100L;

[0066] (8) It has the function of performance test of ground hydraulic source open pressure supply working mode;

[0067] (9) It has the function of testing the performance of the closed pressure supply working mode of the ground hydraulic source;

[0068] (10) It has the function of testing the high-pressure sealing performance of the ground hydraulic source;

[0069] (11) It has the function of testing the heat dissipation performance of the ground hydraulic source system;

[0070] (12) It has the function of testing the transient response performance of the ground hydraulic source;

[0071] (13) Equipped with hydraulic oil pump load performance test function;

[0072] (14) Space dimensions: 2900mm*3000mm*3235mm, floor area 8.7m2.

[0073] Embodiment 4:

[0074] A test method for an aircraft ground hydraulic source, the test method being implemented using a test fixture, comprising the following steps:

[0075] The output end of the hydraulic source system 1 of the aircraft oil pump truck to be tested is connected to the power unit 2, and the hydraulic energy loaded by the test ground hydraulic source is converted into mechanical energy through the power unit 2 and transmitted to the speed reduction ratio unit 3, and the mechanical energy is loaded to the load unit 7 according to a wide range of speed reduction through the speed reduction ratio unit 3;

[0076] The load adjustment unit 4 simulates the aircraft retracting and extending the landing gear, front wheel turning, retracting the flaps, retracting the speed brakes, and adjusting the load of the air inlet through the continuously adjustable back pressure load of the rodless chamber of the test oil cylinder of the load unit 7, and establishes the corresponding simulated load through the linear opening of the electric proportional relief valve at the oil outlet of the rodless chamber of the test oil cylinder, and realizes the reset and stroke adjustment of the test oil cylinder through an independent motor pump group;

[0077] The test hydraulic oil is recovered through the buffer oil return unit 5 and flows into the test source through different switching branches to realize oil circulation.

Claims

1. Aircraft ground hydraulic source test tool, characterized in that: The invention comprises an aircraft oil pump truck hydraulic source system (1) to be tested, wherein the outlet of the aircraft oil pump truck hydraulic source system (1) is connected to a power unit (2) for converting hydraulic energy into mechanical energy, the output end of the power unit (2) is connected to a speed reduction ratio unit (3), and the speed reduction ratio unit (3) is used to load the converted mechanical energy to a load unit (7) according to a wide range of speed reduction; the load unit (7) is invertedly mounted on a test frame (6); and the load unit (7) is also connected to a load adjustment unit (4) for adjusting the stroke and resetting.

2. The aircraft ground hydraulic source test tool according to claim 1, characterized in that: The aircraft oil pump truck hydraulic source system (1) comprises an oil pump truck pump group (102) for providing hydraulic power, a pressure gauge (103) and a flow meter (104) are installed at the hydraulic output end of the oil pump truck pump group (102), an oil inlet of the oil pump truck pump group (102) is connected to a test oil tank (101), the test oil tank (101) is fixedly installed on the top of an oil tank mounting frame (8), and a ladder is provided on the oil tank mounting frame (8).

3. The aircraft ground hydraulic source test tool according to claim 1, characterized in that: The power unit (2) comprises a hydraulic motor (201), the hydraulic motor (201) being connected to the oil outlet of the hydraulic source system (1) of the aircraft oil pump truck, and the output shaft of the hydraulic motor (201) being connected to the input shaft of a reducer (202); the reducer (202) being fixedly mounted on the top of a reducer storage rack (203).

4. The aircraft ground hydraulic source test tool according to claim 3, characterized in that: The speed reduction ratio unit (3) comprises a driving gear (301) mounted on the output shaft of the speed reducer (202), the driving gear (301) meshing with a lifting rack (302) for transmission, the lifting rack (302) being slidably mounted inside a rack mounting sleeve (303), and the top end of the lifting rack (302) being connected to the input end of the load unit (7).

5. The aircraft ground hydraulic source test tool according to claim 3, characterized in that: The test frame (6) comprises a plurality of columns (601), the bottom ends of the columns (601) being fixedly connected to the installation base via column pads (604), the tops of the columns (601) being fixed with an upper frame (602), and the bottom center of the upper frame (602) being fixed with an oil cylinder installation flange (603).

6. The aircraft ground hydraulic source test tool according to claim 5, characterized in that: The load unit (7) comprises a test cylinder, which is a double-acting hydraulic cylinder and comprises a cylinder outer tube (702). A mounting flange (701) is provided at the top of the cylinder body of the cylinder outer tube (702), and the mounting flange (701) is fixedly connected to the bottom end of the cylinder mounting flange (603) of the test frame (6); a piston rod (703) is mounted inside the cylinder outer tube (702), and a buffer zone (704) is provided at the inner bottom end of the cylinder outer tube (702).

7. The aircraft ground hydraulic source test tool according to claim 6, characterized in that: The load regulating unit (4) comprises a mounting housing (406), a motor pump group (401) being mounted inside the mounting housing (406), an oil inlet of the motor pump group (401) being connected to an oil tank (402), and an oil outlet of the motor pump group (401) being connected to a load unit (7) via a safety valve (403) and a reversing valve group (404); and also comprises an electric proportional overflow valve (405) mounted on an oil return pipe.

8. The aircraft ground hydraulic source test tool according to claim 6, characterized in that: The oil return end of the power unit (2) is connected to a buffer oil return unit (5).

9. The aircraft ground hydraulic source test tool according to claim 8, characterized in that: The buffer oil return unit (5) comprises an oil return buffer (501), and an outlet of the oil return buffer (501) is connected to the test oil tank (101) via an electromagnetic oil return valve (502).

10. The aircraft ground hydraulic source test tool according to claim 5, characterized in that: It also includes a test console (9), which includes a housing, a touch control screen and an operating switch, and is used to control, monitor and adjust the system load and loading stroke; It also includes an electric control cabinet (11) and a test interface assembly (10), wherein the test interface assembly is provided with multiple types of aircraft ground hydraulic source connection joints, and can meet the needs of testing different types of aircraft ground hydraulic sources and oil pump trucks.

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