A cracked control surface fatigue and functional reliability testing system

Abstract

This invention provides a cracked control surface fatigue and functional reliability testing system, belonging to the technical field of cracked control surface testing. The system includes a test support frame, a deformation support device, a gravity-eliminating follow-up loading device, and a test control device located outside the test support frame for test control. Multiple sets of gravity-eliminating follow-up loading devices are provided, with one or more sets on both the upper and lower control surfaces. This system employs dual follow-up loading devices to solve the problem of dual-control surface follow-up loading, meeting the requirements of tensile and compressive bidirectional loading and large-range motion following. Furthermore, the follow-up loading device is capable of eliminating the non-axial component of gravity, eliminating additional accessory loads, improving test loading accuracy, and achieving accurate simulation of aerodynamic loads on the control surface.

Description

Technical Field

[0001] This invention belongs to the field of aircraft control surface testing technology, specifically relating to a cracked control surface fatigue and functional reliability testing system. Background Technology

[0002] Split control surfaces are a new type of control surface that integrates the functions of conventional control surfaces such as flaps, ailerons, rudders, and elevators, while also increasing the aircraft's stealth characteristics and reducing the complexity of control surfaces.

[0003] Due to the novel configuration of the split control surface, functional reliability verification is a significant challenge during its development, necessitating the development of a testing device that includes test piece support and loading mechanisms. Current fatigue and functional reliability tests primarily target single control surfaces, typically conducted under normal conditions. This involves supporting the control surface test piece on a real wing structure, wing dummy, or mounting joint structure; a follow-up loading device is designed on the upper or lower side of the control surface test piece to simulate the aerodynamic loads on the support boundary and surface of the control surface. This approach has the following drawbacks: 1) It can only simulate the aerodynamic loads on a single control surface, failing to simulate the aerodynamic loads on a split dual control surface; 2) Control surface support and manipulation cannot simulate high / low temperature, humidity, and other environmental requirements, making it impossible to assess the impact of the environment on the control surface drive transmission system; 3) Existing follow-up loading methods and devices can only deduct the gravitational component along the actuator axis, failing to eliminate the non-axial component of the actuator's gravity, resulting in additional loads and inaccurate loading; 4) Existing test loading methods rely on emergency disconnection of the control system to stop the test loading in dangerous situations, lacking physical isolation protection.

[0004] Therefore, a new fatigue and performance reliability testing system is needed to meet the testing requirements of cracked control surfaces. Summary of the Invention

[0005] The purpose of this invention is to provide a fatigue and functional reliability testing system for cracked dual control surfaces.

[0006] To achieve the above objectives, the present invention provides the following technical solution: a cracked control surface fatigue and functional reliability testing system, used for conducting fatigue and functional reliability tests on cracked control surface test pieces. The cracked control surface includes an upper control surface and a lower control surface. The device includes a test support frame, a deformation support device, a follow-up loading device to eliminate the influence of gravity, and a test control device disposed outside the test support frame for test control.

[0007] The follow-up loading device for eliminating the influence of gravity includes multiple sets, with one or more sets of follow-up loading devices for eliminating the influence of gravity provided on both the upper and lower control surfaces.

[0008] The cracked control surface fatigue and functional reliability testing system provided by this invention also has the following technical features: the deformation support device includes a deformation boundary simulation chamber structure for simulating support stiffness and supporting deformation; a cracked control surface mounting joint installed on one side of the deformation boundary simulation chamber structure and connected and fixed to the cracked control surface test piece; multiple deformation loading actuators installed below the deformation boundary simulation chamber structure for loading the deformation boundary simulation chamber structure; and a low-temperature environment device and a humid heat environment device for providing the test gaseous medium.

[0009] The other side of the deformation boundary simulation chamber structure is installed on the inner wall of the overall test support frame. The low temperature environment device and the humid heat environment device are placed outside the overall test support frame and are introduced into the deformation boundary simulation chamber structure through pipelines to test gaseous media of different temperatures.

[0010] The cracked control surface fatigue and functional reliability testing system provided by this invention also has the following technical feature: openings are provided on one side of the deformation boundary simulation closed chamber structure where the cracked control surface test piece is installed, on the side of the installation mating surface of the overall test support frame, and on its internal partition structure.

[0011] The opening is used to uniformly transport the gaseous medium at a specific temperature generated by the low-temperature environment device and the hot and humid environment device to the cracked control surface test piece, and multiple sensors are distributed on the mounting side of the cracked control surface test piece.

[0012] The cracked control surface fatigue and functional reliability testing system provided by the present invention also has the following technical feature: the cracked control surface mounting joint is identical to the cracked control surface and its drive transmission structure.

[0013] The cracked control surface fatigue and functional reliability testing system provided by the present invention also has the following technical features: the low temperature environment device is used to generate a low temperature dry gaseous medium below 20°C, the humid heat environment device is used to generate a gaseous medium above 20°C and with 0-95% humidity, and the pipeline is equipped with an automatically controlled proportional switching valve.

[0014] The cracked control surface fatigue and functional reliability testing system provided by this invention also has the following technical feature: the follow-up loading device for eliminating the influence of gravity includes: a posture loading component, a gravity elimination component, and a loading actuator; the posture loading component and the gravity elimination component are installed on the inner wall of the overall test support frame.

[0015] The loading end of the loading actuator is mounted on the cracked maneuvering surface test piece via a hinged joint, with its end hinged to the posture loading assembly and its exterior hinged to the gravity elimination assembly.

[0016] The cracked control surface fatigue and functional reliability testing system provided by this invention also has the following technical features: the posture loading assembly includes a loading posture servo controller and a loading posture servo control screw bearing mounted on the inner wall of the test support frame, a movable mounting base for the loading actuator connected to the end of the loading actuator, and a loading posture servo control screw driven by the loading posture servo controller. The movable mounting base for the loading actuator is sleeved on the loading position servo control screw.

[0017] The loading posture servo controller drives the loading posture servo control screw to rotate, thereby pushing the loading actuator movable mounting base to move.

[0018] The cracked operating surface fatigue and functional reliability testing system provided by this invention also has the following technical features: the gravity elimination assembly includes a gravity elimination servo controller and a gravity elimination servo control screw bearing mounted on the inner wall of the test support frame, a gravity elimination connector connected to the outside of the loading actuator, and a gravity elimination servo control screw driven by the gravity elimination servo controller. The gravity elimination connector is sleeved on the gravity elimination servo control screw.

[0019] The gravity elimination servo controller drives the gravity elimination servo control screw to rotate, thereby driving the gravity elimination connector to move.

[0020] The cracked control surface fatigue and functional reliability testing system provided by the present invention also has the following technical feature: the front end of the loading actuator is provided with an emergency release pin.

[0021] The cracked control surface fatigue and functional reliability testing system provided by this invention also has the following technical feature: the test control device is connected and communicates with the deformation support device, the cracked control surface test piece, and the follow-up loading device to eliminate the influence of gravity via cables.

[0022] The experiment supports the installation of observation and detection components on the overall framework.

[0023] Beneficial effects:

[0024] The device provided in this application uses a dual follow-up loading device to solve the problem of follow-up loading on dual control surfaces, meeting the requirements of bidirectional tension and compression loading and large-range motion following; and the follow-up loading device is a follow-up loading device that can eliminate the non-axial component of gravity, eliminating additional accessory loads, improving the accuracy of test loading, and realizing accurate simulation of aerodynamic loads on control surfaces.

[0025] The device provided in this application adds two different environmental devices, enabling boundary support and follow-up loading for high and low temperature and humidity environment simulation without using an environmental chamber, thereby improving the accuracy of environmental simulation and reducing the impact on the test equipment. Attached Figure Description

[0026] To more clearly illustrate the technical solutions of the embodiments of this disclosure, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this disclosure. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0027] Figure 1 This is a schematic diagram of the system provided in the embodiments of the present invention;

[0028] Figure 2 This is a schematic diagram of the deformation support device provided in an embodiment of the present invention;

[0029] Figure 3 This is a schematic diagram of the structure of the follow-up loading device for eliminating the influence of gravity provided in the embodiment of the present invention;

[0030] Figure 4 This is a schematic diagram of the test loading of the system provided in the embodiment of the present invention under the fully closed state of the cracked control surface;

[0031] Figure 5 This is a schematic diagram of the test loading of the system provided in the embodiment of the present invention under the fully open state of the cracked control surface;

[0032] Figure 6 This is a schematic diagram of the test loading of the system provided in the embodiment of the present invention under the same deflection state of the cracked control surface.

[0033] Among them, 1: test control device; 2: test support frame; 3: deformation support device; 4: cracked control surface test piece; 5: follow-up loading to eliminate the influence of gravity; 6: observation and testing platform; 7: safety ladder; 8: cracked control surface mounting joint; 9: deformation boundary simulation closed chamber structure; 10: deformation loading actuator; 11: low temperature environment device; 12: humid heat environment device; 13: loading posture servo controller; 14: loading posture servo control screw; 15: gravity elimination servo controller; 16: gravity elimination servo control screw; 17: loading actuator movable mounting base; 18: gravity elimination connector; 19: loading actuator; 20: loading posture servo control screw bearing; 21: gravity elimination servo control screw bearing. Detailed Implementation

[0034] The present invention will be further described in detail below with reference to the accompanying drawings and embodiments. However, it should be noted that these embodiments are not intended to limit the present invention. Equivalent changes or substitutions in function, method, or structure made by those skilled in the art based on these embodiments are all within the protection scope of the present invention.

[0035] In the description of the embodiments of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the invention and 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 limiting the invention.

[0036] Furthermore, the terms "first," "second," "third," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined with "first," "second," etc., may explicitly or implicitly include one or more of that feature. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0037] The terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections or electrical connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to the internal connection between two components. Those skilled in the art will understand the specific meaning of these terms in this invention based on the specific circumstances.

[0038] like Figure 1-6 As shown, this embodiment of the invention provides a fatigue and functional reliability testing system for a cracked control surface, used to conduct fatigue and functional reliability tests on a cracked control surface test piece 4. The cracked control surface includes an upper control surface and a lower control surface. The system includes a test support frame 2, a deformation support device 3, a follow-up loading device 5 to eliminate the influence of gravity, and a test control device 1 set outside the test support frame 2 for test control. The follow-up loading device 5 to eliminate the influence of gravity includes multiple sets, with one or more sets of follow-up loading devices 5 to eliminate the influence of gravity provided on both the upper and lower control surfaces.

[0039] In some embodiments, two sets of follow-up loading devices 5 to eliminate the influence of gravity are provided. One set of follow-up loading devices 5 to eliminate the influence of gravity is installed in the upper space within the overall test support frame 2 and is connected to the upper control surface through a rigid loading connection method such as tension pads or connecting joints, for loading the upper control surface; the other set is installed in the lower space within the overall test support frame 2 and is connected to the lower control surface through a rigid loading connection method such as tension pads or connecting joints, for loading the lower control surface.

[0040] In some embodiments, the deformation support device 3 includes a deformation boundary simulation chamber structure 9 for simulating support stiffness and support deformation, a cracked maneuvering surface mounting joint 8 installed on one side of the deformation boundary simulation chamber structure 9 and connected and fixed to the cracked maneuvering surface test piece 4, multiple deformation loading actuators 10 installed below the deformation boundary simulation chamber structure 9 for loading the deformation boundary simulation chamber structure 9, and a low-temperature environment device 11 and a humid heat environment device 12 for providing test gaseous media. The other side of the deformation boundary simulation chamber structure 9 is installed on the inner wall of the test support overall frame 2. The low-temperature environment device 11 and the humid heat environment device 12 are placed outside the test support overall frame 2 and test gaseous media of different temperatures are introduced into the deformation boundary simulation chamber structure 9 through pipelines.

[0041] In the above embodiments, the deformable boundary simulation chamber structure 9, in addition to simulating support stiffness and deformation, also serves as the receiver for simulating the cold / humid / hot environment of the boundary and control mechanism. The deformable support device 3 is used to simultaneously simulate the deformation boundary support conditions of the aircraft fuselage structure on the cracked control surface, as well as high and low temperature / humid / hot environments. The deformable boundary simulation chamber structure 9 adopts a stiffness approximation method to simplify its design, making its stiffness and deformation the same as / similar to the stiffness and deformation of the support boundary of the actual cracked control surface. Multiple deformation loading actuators 10 are connected to the test control device 1 to load the deformable boundary simulation chamber structure 9, causing deformation identical to that of the actual cracked control surface support structure. The loading loads of all deformation loading actuators 10 are calculated during the test design phase, satisfying the stiffness and deformation history of the entire aircraft's use / service process, compiling a load spectrum, and inputting it into the test control device 1.

[0042] In some embodiments, openings are provided on the side of the deformation boundary simulation closed chamber structure 9 where the cracked maneuvering surface test piece 4 is mounted, on the side of the test support integral frame 2 where it is mounted, and on its internal partition structure. These openings are locally reinforced. The openings are used to uniformly transport the gaseous medium at a specific temperature generated by the low-temperature environment device 11 and the humid-heat environment device 12 to the cracked maneuvering surface test piece 4. Multiple sensors are distributed on the mounting side of the cracked maneuvering surface test piece 4. These sensors include, but are not limited to, displacement sensors, humidity sensors, and temperature sensors, used to detect temperature and humidity in real time and feed them back to the test control device 1 for accurate control of the test temperature, humidity, and deformation support loading.

[0043] In some embodiments, the split-type control surface mounting joint 8 is identical to the split-type control surface and its drive transmission structure.

[0044] In some embodiments, the low-temperature environment device 11 is used to generate a low-temperature dry gaseous medium below 20°C, and the humid heat environment device 12 is used to generate a gaseous medium above 20°C with 0-95% humidity. An automatically controlled proportional switching valve is installed on the pipeline. The proportional switching valve is connected to the test control device to accurately simulate the high / low temperature / humidity environment during the service / use of the crack-type control surface.

[0045] In some embodiments, the follow-up loading device 5 for eliminating the influence of gravity includes: a posture loading component, a gravity elimination component, and a loading actuator 19. The posture loading component and the gravity elimination component are installed on the inner wall of the test support frame 2. The loading end of the loading actuator is installed on the cracked maneuvering surface test piece 4 through a hinge joint, with its end hinged to the posture loading component and its exterior hinged to the gravity elimination component.

[0046] In the above embodiment, the follow-up loading device 5 is used to accurately apply simulated aerodynamic loads to the upper and lower control surfaces of the cracked control surface, and introduces the gravity of the loading actuator 19 during the loading process.

[0047] In some embodiments, the pose loading assembly includes a loading pose servo controller 13 and a loading pose servo control screw bearing 20 mounted on the inner wall of the test support frame 2, a loading actuator movable mounting base 17 connected to the end of the loading actuator 19, and a loading pose servo control screw 14 driven by the loading pose servo controller 13. The loading actuator movable mounting base 17 is sleeved on the loading position servo control screw 14.

[0048] The loading posture servo controller 13 drives the loading posture servo control screw 14 to rotate, thereby pushing the loading actuator movable mounting base 17 to move.

[0049] In some embodiments, the gravity elimination assembly includes a gravity elimination servo controller 15 and a gravity elimination servo control screw bearing 21 mounted on the inner wall of the test support frame 2, a gravity elimination connector 18 connected to the outside of the loading actuator, and a gravity elimination servo control screw 16 driven by the gravity elimination servo controller 15, wherein the gravity elimination connector 18 is sleeved on the gravity elimination servo control screw 16.

[0050] The gravity elimination servo controller 15 drives the gravity elimination servo control screw 16 to rotate, thereby pushing the gravity elimination connector 18 to move.

[0051] In some embodiments, the loading actuator 19 is provided with an emergency release pin at its front end. When a dangerous situation occurs during the test, the emergency release pin disengages and terminates the loading process to protect the test specimen and the testing apparatus.

[0052] In some embodiments, the loading pose servo controller 13, the gravity elimination servo controller 15, and the loading actuator 19 are all connected to the test control device 1. The motion of the loading actuator movable mounting base 17 and the gravity elimination connector 18, as well as the loading amount of the loading actuator 19, are calculated during the test design phase and compiled into one of the test control spectra. The combined motion of the loading actuator movable mounting base 17 and the gravity elimination connector 18 follows the deflection motion of the split-type control surface on the one hand, and on the other hand, balances and eliminates the component of gravity of the loading actuator 19 on its non-axial direction with the gravity elimination connector 18, thereby achieving the purpose of eliminating the additional gravity component of the loading actuator 19.

[0053] In some embodiments, the test control device 1 is connected and communicates with the deformation support device 3, the drive PDU of the cracked manipulator surface test piece 4 and the follow-up loading device 5 to eliminate the influence of gravity via cables, and the observation and detection components are installed on the test support overall frame 2.

[0054] In the above embodiments, the test control device 1 controls the test device based on the pre-programmed test load / environment spectrum to achieve crack-type operating surface fatigue, functional, and reliability tests under high / low temperature / humidity environments. The observation and inspection components are installed on suitable locations for test inspection and testing on the overall test support frame 2, including but not limited to the observation and inspection platform 6, for test inspection and testing during long-term testing, and can also be used to house some test measurement, imaging, and data acquisition equipment. A safety ladder with guardrails is designed and installed near the observation and inspection platform 6 to provide conditions for test personnel to install, inspect, and observe.

[0055] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention. The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of the present invention, and these improvements and modifications should also be considered within the protection scope of the present invention.

Claims

1. A fatigue and functional reliability testing system for a cracked control surface, used for conducting fatigue and functional reliability tests on a cracked control surface test piece (4), wherein the cracked control surface includes an upper control surface and a lower control surface, characterized in that, The system includes an overall test support frame (2), a deformation support device (3), a follow-up loading device (5) to eliminate the influence of gravity, and a test control device (1) set outside the overall test support frame (2) for test control. The deformation support device (3) includes a deformation boundary simulation chamber structure (9) for simulating support stiffness and supporting deformation, a cracked maneuvering surface mounting joint (8) installed on one side of the deformation boundary simulation chamber structure (9) and connected and fixed to the cracked maneuvering surface test piece (4), multiple deformation loading actuators (10) installed below the deformation boundary simulation chamber structure (9) for loading the deformation boundary simulation chamber structure, and a low temperature environment device (11) and a humid heat environment device (12) for providing the test gaseous medium. The deformation boundary simulation chamber structure (9) is installed on the inner wall of the test support frame (2) on the other side. The low temperature environment device (11) and the humid heat environment device (12) are placed outside the test support frame (2) and are introduced into the deformation boundary simulation chamber structure (9) through pipelines to test gaseous media of different temperatures. The following loading device (5) for eliminating the influence of gravity includes multiple sets, with one or more sets of following loading devices (5) for eliminating the influence of gravity provided on both the upper and lower control surfaces. The follow-up loading device (5) for eliminating the influence of gravity includes: a pose loading component, a gravity elimination component, and a loading actuator (19). The pose loading component and the gravity elimination component are installed on the inner wall of the test support frame (2). The loading end of the loading actuator (19) is mounted on the cracked maneuvering surface test piece via a hinge joint, with the end hinged to the posture loading assembly and the outside hinged to the gravity elimination assembly.

2. The cracked control surface fatigue and functional reliability testing system according to claim 1, characterized in that, The deformable boundary simulation closed chamber structure (9) has openings on one side of the cracked maneuvering surface test piece (4), one side of the test support frame (2) installation mating surface, and its internal partition structure. The opening is used to uniformly transport the gaseous medium at a specific temperature generated by the low temperature environment device (11) and the hot and humid environment device (12) to the cracked maneuvering surface test piece (4), and multiple sensors are distributed on the mounting side of the cracked maneuvering surface test piece (4).

3. The cracked control surface fatigue and functional reliability testing system according to claim 1, characterized in that, The split-type control surface mounting joint (8) is identical to the split-type control surface and its drive transmission structure.

4. The cracked control surface fatigue and functional reliability testing system according to claim 1, characterized in that, The low-temperature environment device (11) is used to generate a low-temperature dry gaseous medium below 20°C, and the humid heat environment device (12) is used to generate a gaseous medium above 20°C with 0-95% humidity. The pipeline is equipped with an automatically controlled proportional switch valve.

5. The cracked control surface fatigue and functional reliability testing system according to claim 1, characterized in that, The pose loading assembly includes a loading pose servo controller (13) and a loading pose servo control screw bearing (20) mounted on the inner wall of the test support frame (2), a loading actuator movable mounting base (17) connected to the end of the loading actuator (19), and a loading pose servo control screw (14) driven by the loading pose servo controller (13). The loading actuator movable mounting base (17) is sleeved on the loading position servo control screw (14). The loading posture servo controller (13) drives the loading posture servo control screw (14) to rotate, thereby pushing the loading actuator movable mounting base (17) to move.

6. The cracked control surface fatigue and functional reliability testing system according to claim 1, characterized in that, The gravity elimination assembly includes a gravity elimination servo controller (15) and a gravity elimination servo control screw bearing (21) mounted on the inner wall of the test support frame (2), a gravity elimination connector (18) connected to the outside of the loading actuator (19), and a gravity elimination servo control screw (16) driven by the gravity elimination servo controller (15). The gravity elimination connector (18) is sleeved on the gravity elimination servo control screw (16). The gravity elimination servo controller (15) drives the gravity elimination servo control screw (16) to rotate, thereby pushing the gravity elimination connector (18) to move.

7. The cracked control surface fatigue and functional reliability testing system according to claim 1, characterized in that, The loading actuator (19) is equipped with an emergency release pin at its front end.

8. The cracked control surface fatigue and functional reliability testing system according to claim 1, characterized in that, The test control device (1) is connected and communicates with the deformation support device (3), the cracked manipulator test piece (4), and the follow-up loading device (5) to eliminate the influence of gravity via cables. The experiment supports the installation of observation and detection components on the overall frame (2).

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