An aeronautical hydraulic component hydraulic action test device

Abstract

This invention discloses a hydraulic actuation testing device for aviation hydraulic components, belonging to the field of hydraulic component testing technology. It includes a base with a protective cover above it, a hydraulic station inside the base, a fixture and a lateral loading assembly on the base surface, an actuator cylinder installed inside the fixture, and a main thrust actuator and a hydraulic testing assembly on both sides of the fixture. This invention constructs a multi-axis composite load simulation system by setting up a main thrust actuator, a vertical bending load actuator, a lateral force actuator, and a torque actuator. This system can accurately reproduce the complex spatial loads acting on the actuator cylinder when an aircraft lands on a sea-based platform. Simultaneously, an ultrasonic device integrated into the hydraulic testing assembly can actively generate cavitation bubbles in the oil circuit, simulating extreme fluid environments. This transforms the transient impact of a simulated aircraft landing on a sea-based platform into a cyclical continuous loading process, improving the data quality for fatigue damage research and life prediction testing of aviation hydraulic actuator cylinders.

Description

Technical Field

[0001] This invention relates to the field of hydraulic component testing technology, and in particular to a hydraulic action testing device for aviation hydraulic components. Background Technology

[0002] Aviation hydraulic actuators are core execution components of flight control systems. For aircraft landing on sea-based platforms, during the landing process, they need to undergo high-speed interception and forced deceleration. During this process, the entire airframe structure will generate impact loads of up to several gravitational accelerations. This causes the actuators mounted on the flaps to simultaneously bear huge axial inertial impacts, vertical loads generated by fuselage pitch ("nodding"), lateral forces caused by wing bending deformation, and possible torsional moments around the axis. Under such intense pressure fluctuations, the hydraulic oil system inside the actuator is prone to cavitation. When the bubbles formed collapse in the high-pressure area, they will generate micro-jet streams and shock waves, which may cause potential cavitation corrosion to the inner wall of the actuator and sealing components.

[0003] Due to the existence of cavitation, existing equipment generally uses drop hammer test benches or disposable impact devices to simulate impact loads. However, this loading process is transient and cannot be repeatedly controlled. It is impossible to expand the complex impact at the millisecond level in real working conditions into a continuous load spectrum that can be analyzed, making it difficult to collect complete dynamic response data.

[0004] In addition to the severe pressure fluctuations caused by the impact of landing, hydraulic systems also experience cavitation under extreme conditions such as high altitude and low pressure and high-speed oil flow. However, existing testing equipment generally lacks the ability to actively simulate and study this fluid cavitation effect and its damage mechanism to components under controlled, independent and quantifiable conditions.

[0005] To address these issues, a hydraulic actuation testing device for aviation hydraulic components is proposed. Summary of the Invention

[0006] The purpose of this invention is to solve the problems of limited testing methods, distorted load simulation, difficulty in fatigue testing, and inability to actively study the cavitation erosion mechanism in existing hydraulic component testing technologies, and to propose a hydraulic action testing device for aviation hydraulic components.

[0007] To achieve the above objectives, the present invention adopts the following technical solution:

[0008] A hydraulic actuation testing device for aviation hydraulic components includes a base, a protective cover above the base, a hydraulic station inside the base, a fixture on the surface of the base, an actuator cylinder installed inside the fixture, a main thrust actuator on one side of the fixture, a hydraulic testing assembly on the other side, a test slide bar on the platform of the base located between the fixture and the main thrust actuator, and a lateral loading assembly on the test slide bar.

[0009] The hydraulic testing assembly includes a hydraulic pipe connected to a hydraulic station, and the output end of the hydraulic pipe is provided with a test connector, and the outer wall of the test connector is provided with an ultrasonic transducer.

[0010] The lateral loading assembly includes two opposing mounting bases. Each mounting base has a mounting groove on the side facing the fixture. The mounting groove contains two lateral force actuators, one torque actuator, and two loading slide rods. The two lateral force actuators are arranged opposite each other. A load slider is slidably connected to the loading slide rod for loading the actuator cylinder.

[0011] Preferably, the fixture includes a platform, the surface of which is provided with fixing ears for fixing the actuator cylinder body, and a vertical bending load actuator is provided on the platform corresponding to the actuator cylinder body to simulate a vertical load.

[0012] Preferably, the vertical bending load actuator is vertically arranged, and the piston rod of the vertical bending load actuator is provided with a bearing block adapted to the outer contour of the actuator cylinder at its top end, and the bearing block is provided with a positioning hoop.

[0013] Preferably, the test connector is provided with an ultrasonic head, and the outer wall of the test connector is provided with a threaded sleeve for installing an ultrasonic device at the location corresponding to the ultrasonic head.

[0014] Preferably, the outer wall of the load slider is connected to two lateral force actuators, and the load slider is equipped with a torsion loading joint via a bearing.

[0015] Preferably, the end of the torsion loading joint is connected to the piston rod of the actuator cylinder, and a compensation joint is provided on the top of the outer wall of the torsion loading joint. The torsion loading joint is slidably connected to the torque actuator through the compensation joint.

[0016] Preferably, when the torque actuator is activated, it drives the torsion loading joint to rotate around the axis of the load slider, causing the piston rod of the actuating cylinder to rotate synchronously.

[0017] Preferably, the mounting base is provided with a rigid load isolation plate on the side facing the main thrust actuator, so that the thrust of the main thrust actuator will not act directly on the load slider, thus providing a prerequisite for the lateral loading test.

[0018] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0019] 1. This invention integrates an ultrasonic head into the test joint of a hydraulic test assembly, and uses the sound waves generated by the ultrasonic device to realize the simulation of active and controllable cavitation effect. It allows the active generation of microbubble flow of specific size and distribution in the hydraulic oil circuit by adjusting the ultrasonic parameters without conducting a physical impact test. It can simulate the cavitation phenomenon that may be caused by high-altitude low-pressure and severe impact in a laboratory environment and its potential erosion effect on the actuator cylinder seal and inner wall.

[0020] 2. This invention constructs a multi-axis composite load simulation system by setting up a main thrust actuator, a vertical bending load actuator, a lateral force actuator, and a torque actuator. When used in conjunction with a hydraulic testing component, this system can decompose a severe transient impact into a slow, continuous, and cyclically applied continuous load. During this process, all sensors can continuously acquire data, thereby obtaining complete performance response and degradation data and improving the data quality of fatigue damage research and life prediction testing. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the external structure of a hydraulic action testing device for aviation hydraulic components proposed in this invention;

[0022] Figure 2 This is a schematic diagram of the internal structure of a hydraulic actuation testing device for aviation hydraulic components proposed in this invention;

[0023] Figure 3 This is a structural assembly diagram of the fixture and actuator cylinder in a hydraulic actuation testing device for aviation hydraulic components proposed in this invention;

[0024] Figure 4 This is a structural assembly diagram of the bearing block and positioning hoop in a hydraulic action testing device for aviation hydraulic components proposed in this invention;

[0025] Figure 5 This is a structural assembly diagram of the test joint and ultrasonic device in a hydraulic action testing device for aviation hydraulic components proposed in this invention;

[0026] Figure 6 This is a cross-sectional view of the internal structure of a test joint in a hydraulic actuation testing device for aviation hydraulic components proposed in this invention;

[0027] Figure 7 This is a front structural diagram of the lateral loading component in a hydraulic action testing device for aviation hydraulic components proposed in this invention.

[0028] Figure 8This is a schematic diagram of the internal structure of the lateral loading component in a hydraulic action testing device for aviation hydraulic components proposed in this invention;

[0029] Figure 9 This is a schematic diagram of the rear structure of the lateral loading component in a hydraulic action testing device for aviation hydraulic components proposed in this invention;

[0030] Figure 10 This is a structural assembly diagram of the load slider and torsional loading joint in a hydraulic action testing device for aviation hydraulic components proposed in this invention.

[0031] In the diagram: 1. Base; 2. Protective cover; 3. Hydraulic station; 4. Actuating cylinder; 5. Main thrust actuator; 6. Test slide bar; 7. Hydraulic pipe; 8. Test connector; 801. Ultrasonic head; 802. Threaded sleeve; 9. Ultrasonic device; 10. Mounting base; 11. Lateral force actuator; 12. Torque actuator; 13. Loading slide bar; 14. Load slider; 15. Platform; 16. Fixing lug; 17. Vertical bending load actuator; 18. Bearing block; 19. Positioning clamp; 20. Torsional loading connector; 21. Load isolation plate. Detailed Implementation

[0032] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0033] In the description of this invention, it should be noted that the terms "upper," "lower," "inner," "outer," "top / bottom," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0034] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installed," "equipped with," "sleeved / connected," "connected," etc., should be interpreted broadly. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can be a connection within two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0035] Example, refer to Figures 1 to 10 A hydraulic actuation testing device for aviation hydraulic components includes a base 1, a protective cover 2 above the base 1, a hydraulic station 3 inside the base 1, a fixture on the surface of the base 1, an actuator 4 installed inside the fixture, a main thrust actuator 5 on one side of the fixture, and a hydraulic testing assembly on the other side. A test slide rod 6 is provided on the platform of the base 1 located between the fixture and the main thrust actuator 5, and a transverse loading assembly is provided on the test slide rod 6.

[0036] The hydraulic testing assembly includes a hydraulic pipe 7 connected to the hydraulic station 3. The output end of the hydraulic pipe 7 is provided with a test connector 8. An ultrasonic device 9 is provided on the outer wall of the test connector 8. The ultrasonic device 9 is existing technology and will not be described in detail here.

[0037] The lateral loading assembly includes two opposing mounting bases 10. The mounting base 10 has a mounting groove on the side facing the fixture. The mounting groove contains two lateral force actuators 11, one torque actuator 12, and two loading slide rods 13. The two lateral force actuators 11 are arranged opposite to each other. A load slider 14 is slidably connected to the loading slide rod 13 for performing loading on the actuator cylinder 4.

[0038] It should be noted that during loading, the lateral force actuator 11 on one side extends and the lateral force actuator 11 on the other side retracts, driving the load slider 14 to slide along the loading slider 13. This coordinated driving process will not be described in detail below.

[0039] Furthermore, the fixture includes a platform 15, the surface of which is provided with fixing lugs 16 for fixing the cylinder body of the actuator 4. A vertical bending load actuator 17 is provided on the platform 15 corresponding to the cylinder body of the actuator 4. The independently controlled vertical bending load actuator 17 can simulate the vertical inertial force and impact generated by the fuselage "nodding" motion, deck heave or airflow turbulence when the aircraft lands on the sea-based platform. This allows the actuator 4 to withstand the internal hydraulic pressure and axial test thrust while being subjected to the vertical bending stress, thus more realistically reproducing the composite stress state in actual working conditions.

[0040] Furthermore, the vertical bending load actuator 17 is vertically arranged, and the piston rod of the vertical bending load actuator 17 is provided with a bearing block 18 that is adapted to the outer contour of the actuator cylinder 4 to ensure the uniformity of load transmission. The bearing block 18 is provided with a positioning hoop 19.

[0041] Furthermore, the test connector 8 is equipped with an ultrasonic head 801, and the outer wall of the test connector 8 is equipped with a threaded sleeve 802 for installing the ultrasonic device 9 at the location corresponding to the ultrasonic head 801. During the process of the hydraulic station 3 supplying oil to the actuator cylinder 4 and recovering hydraulic oil, ultrasonic waves are used to cavitate the flowing hydraulic medium, so that the hydraulic oil that finally enters the actuator cylinder 4 contains air bubbles. This allows researchers to separately evaluate the impact of the air bubble flow on the dynamic response of the piston seal of the actuator cylinder 4, the potential cavitation erosion effect, and the system pressure stability, thereby improving the pertinence of fault mechanism research.

[0042] The further advantage of the above is that, by adjusting the power and frequency of the ultrasonic device 9, the cavitation phenomenon that hydraulic oil may produce under high-altitude low-pressure environment and severe impact can be simulated in the oil inlet circuit of the actuator 4 without conducting impact tests. Alternatively, cavitation can be deliberately introduced to test the dynamic response and potential erosion effect of the piston seal of the actuator 4 when air bubbles pass through, and the impact environment can be simulated slowly and continuously.

[0043] Furthermore, the outer wall of the load slider 14 is connected to two lateral force actuators 11, and the load slider 14 is equipped with a torsion loading joint 20 via a bearing;

[0044] Furthermore, the end of the torsion loading joint 20 is connected to the piston rod of the actuator 4. The top of the outer wall of the torsion loading joint 20 is provided with a compensation joint. The torsion loading joint 20 is slidably connected to the torque actuator 12 through the compensation joint. When the torque actuator 12 performs the traction action, it drives the torsion loading joint 20 to rotate around the axis of the load slider 14, and applies a torsion load to the piston rod of the actuator 4.

[0045] It should be noted that if the piston rod of the actuator 4 rotates during this process, the drive torsion loading joint 20 will rotate. At this time, the end of the piston rod of the torque actuator 12 will slide from bottom to top in the compensation joint to compensate for the movement distance.

[0046] The further advantage of the above is that the linear motion of the torque actuator 12 can be converted into the lever arm of the drive torsion loading joint 20 via the hinge point, generating a rotational torque about the axis, simulating the torsional torque acting on the piston rod of the actuator cylinder 4 when the wing torsional deformation or asymmetric aerodynamic force is transmitted to the flap during landing.

[0047] Furthermore, the mounting base 10 is provided with a rigid load isolation plate 21 on the side facing the main thrust actuator 5. The load isolation plate 21 and the mounting base 10 form an independent rigid force flow channel. When the main thrust actuator 5 applies force, the frame structure where the lateral force actuator 11 and the torque actuator 12 are located will not be disturbed, so that lateral force and torsional load can be applied independently during this period.

[0048] When using this invention, the cylinder body of the test actuator 4 is installed and fixed through the fixing lug 16 on the surface of the fixture platform 15. The piston rod end of the test actuator 4 is connected and locked to the torsion loading joint 20 in the transverse loading assembly. Then, the hydraulic oil port of the test actuator 4 is connected and sealed to the test joint 8 of the hydraulic test assembly to complete the test preparation. The central control system coordinates and controls each component to perform loading actions according to the load spectrum.

[0049] During the loading and execution phase, the device simultaneously performs the following actions:

[0050] 1. The main thrust actuator 5 starts to move, pushing the mounting base 10 to slide toward the actuator cylinder 4, causing the load slider 14 to push the piston rod of the actuator cylinder 4, simulating the huge axial inertial impact load brought about by the high-speed interception and forced deceleration process;

[0051] 2. When the vertical bending load actuator 17 starts to move, the vertical bending load actuator 17 extends and retracts, and the bearing block 18 and the positioning hoop 19 work together to uniformly apply the vertical dynamic load of the simulated fuselage "nodding" motion and deck heave to the cylinder of the test actuator 4.

[0052] 3. The lateral loading assembly starts to work. The two lateral force actuators 11 in the mounting slot work together to drive the load slider 14 to slide along the loading slide bar 13, applying a lateral load to the piston rod of the test actuator 4.

[0053] 4. The torque actuator 12 starts to work. The piston rod of the torque actuator 12 moves in a straight line and is converted into a lever arm through the compensating joint. This drives the torsion loading joint 20 to rotate around its axis and apply a controllable pure torque load to the piston rod of the test actuator cylinder 4.

[0054] During the loading process described above, the hydraulic test assembly continuously supplies oil to the tested aircraft hydraulic actuator 4. The ultrasonic device 9 integrated on the test connector 8 can be activated according to the test requirements. The sound waves generated by the ultrasonic device 9 are transmitted to the hydraulic oil through the ultrasonic head 801. By adjusting the power and frequency of the ultrasonic device 9, a controllable microbubble flow is actively generated in the hydraulic circuit. The cavitation phenomenon that may occur in the hydraulic oil under the high-altitude low-pressure environment and the violent impact during landing is simulated in the oil inlet of the actuator 4. A violent transient impact is decomposed into an analyzable and controllable process. Cavitation can also be deliberately introduced to test the dynamic response and potential erosion effect of the piston seal of the actuator 4 when bubbles pass through, allowing researchers to evaluate the impact of the bubble flow on the piston seal of the actuator 4 independently.

[0055] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A hydraulic actuation testing device for aviation hydraulic components, comprising a base (1), characterized in that, A protective cover (2) is provided above the base (1), a hydraulic station (3) is provided inside the base (1), a fixture is provided on the surface of the base (1), an actuator (4) is installed inside the fixture, a main thrust actuator (5) is provided on one side of the fixture, and a hydraulic test assembly is provided on the other side. A test slide rod (6) is provided on the platform of the base (1) between the fixture and the main thrust actuator (5), and a transverse loading assembly is provided on the test slide rod (6). The fixture includes a platform (15), the surface of which is provided with fixing ears (16) for fixing the cylinder body of the actuator (4), and a vertical bending load actuator (17) is provided on the platform (15) corresponding to the cylinder body of the actuator (4) to simulate the load in the vertical direction. The vertical bending load actuator (17) is vertically arranged, and the piston rod of the vertical bending load actuator (17) is provided with a bearing block (18) adapted to the outer contour of the cylinder body of the actuator (4) at the top end. The bearing block (18) is provided with a positioning hoop (19). The hydraulic testing assembly includes a hydraulic pipe (7) connected to the hydraulic station (3), the output end of the hydraulic pipe (7) is provided with a test connector (8), the outer wall of the test connector (8) is provided with an ultrasonic device (9) and a threaded sleeve (802) for installing the ultrasonic device (9), and the test connector (8) is provided with an ultrasonic head (801). The lateral loading assembly includes two oppositely arranged mounting seats (10). The mounting seats (10) have a mounting groove on the side facing the fixture. The mounting groove is provided with two lateral force actuators (11), one torque actuator (12), and two loading slide rods (13). The two lateral force actuators (11) are arranged opposite to each other. A load slider (14) is slidably connected to the loading slide rod (13) for performing loading on the actuator cylinder (4). The mounting base (10) is provided with a rigid load isolation plate (21) on the side facing the main thrust actuator (5), so that the thrust of the main thrust actuator (5) will not act directly on the load slider (14), providing a prerequisite for the lateral loading test. The outer wall of the load slider (14) is connected to two lateral force actuators (11). The load slider (14) is equipped with a torsion loading joint (20) through a bearing. The end of the torsion loading joint (20) is connected to the piston rod of the actuator (4). A compensation joint is provided on the top of the outer wall of the torsion loading joint (20). The torsion loading joint (20) is slidably connected to the torque actuator (12) through the compensation joint.

2. The hydraulic actuation testing equipment for aviation hydraulic components according to claim 1, characterized in that, When the torque actuator (12) is activated, it drives the torsion loading joint (20) to rotate around the axis of the load slider (14), causing the piston rod of the actuator cylinder (4) to rotate synchronously.

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