An aileron testing device and simulation method for simulating wing deformation

Abstract

This invention relates to the field of aircraft structural design technology, specifically disclosing an aileron testing device and method for simulating wing deformation. The aileron testing device includes a base, multiple connectors, and multiple drive components. Utilizing this aileron testing device, the drive components move the connectors, which in turn move the aileron joint under test. This simple control process effectively shortens the overall aircraft testing cycle for ailerons. While achieving ground-based bench testing of aileron deformation, it reduces the workload of aileron loading and measurement, simplifies testing complexity, saves testing costs, and shortens the overall aircraft testing cycle.

Description

Technical Field

[0001] This invention relates to the field of aircraft structural design technology, and in particular to an aileron testing device and simulation testing method for simulating wing deformation. Background Technology

[0002] The ailerons of large aircraft are connected to the wing box via multiple joints, making them statically indeterminate structures. Generally, the most severe strain values ​​occurring on the aileron structure can reach 1000-2000 microstrains, while the strain value brought to the aileron by wing deformation is around 700 microstrains. Therefore, considering the order of magnitude of strain values, wing box deformation inevitably affects the stress and strain distribution on the aileron surface. Thus, when conducting full-scale aileron tests, the impact of wing box deformation on the aileron must be considered.

[0003] Typically, the aileron is significantly smaller than the wing box structure. However, to account for the effects of wing box deformation, a wing box must be used for loading, greatly increasing the demand for test loading and related measurement equipment. This not only occupies the entire aircraft testing time but also extends the overall testing cycle and model development cycle. While manufacturing a dedicated wing box as a support section for aileron bench testing could achieve aileron strength assessment, the testing cost would increase dramatically.

[0004] In existing technologies, slat tests are conducted by deforming the slat test specimen through the overall deformation of the beam body. However, this control process is cumbersome and the testing cost is too high. Summary of the Invention

[0005] The purpose of this invention is to provide an aileron testing device and simulation testing method for simulating wing deformation, so as to solve the problems of cumbersome control process and high cost in the prior art when testing ailerons.

[0006] On one hand, the present invention provides an aileron testing device for simulating wing deformation. The aileron testing device for simulating wing deformation includes: a base having a plurality of spaced-apart receiving slots and capable of being connected to a test site ground device; a plurality of connectors, the connectors being slidably disposed in the receiving slots along a first direction and engaging with the receiving slots at an upper limit in a second direction, at least a portion of the connectors being located outside the receiving slots and capable of being connected to the aileron connector to be tested, the first direction and the second direction being perpendicular, the plurality of connectors and the plurality of receiving slots being arranged one-to-one; and a plurality of driving components, the driving components being disposed on the base and drivingly connected to the connectors to drive the connectors to move along the first direction, the plurality of driving components and the plurality of connectors being arranged one-to-one.

[0007] As an optional technical solution for an aileron test device simulating wing deformation, one of the connecting parts and the inner wall of the receiving groove has a limiting protrusion and the other has a limiting groove. Both the limiting protrusion and the limiting groove extend along a first direction, with the limiting protrusion located in the limiting groove. The limiting protrusion and the limiting groove are engaged in a limiting fit in a second direction.

[0008] As an optional technical solution for an aileron test device simulating wing deformation, the connecting component includes a limiting block and a connecting block that are connected to each other. The limiting block is located in the receiving groove and is in upper limit engagement with the receiving groove in the second direction. The connecting block is located outside the receiving groove and can be connected to the aileron connector to be tested. The driving component and the limiting block are driven to drive the limiting block to move along the first direction.

[0009] As an optional technical solution for an aileron test device to simulate wing deformation, the aileron test device to simulate wing deformation includes a first fastener, and the connecting block is connected to the aileron joint to be tested through the first fastener.

[0010] As an optional technical solution for an aileron test device to simulate wing deformation, the connecting block has a clearance groove and a fastening hole. The clearance groove extends along a first direction, and the fastening hole extends through the clearance groove along a second direction. The first fastener passes through the aileron joint to be tested, the fastening hole and the clearance groove in sequence to connect the aileron joint to be tested and the connecting block.

[0011] As an optional technical solution for an aileron test device simulating wing deformation, the drive assembly includes a drive motor, a sensor, and a transmission component. The output end of the drive motor is connected to the input end of the sensor, and the output end of the sensor is connected to the transmission component. The transmission component and the connecting component are sleeved on the transmission component, which is located in a receiving groove. The drive motor drives the transmission component to rotate, and the transmission component drives the connecting component to move along a first direction. The sensor is used to detect the moving distance of the connecting component.

[0012] As an optional technical solution for an aileron test device simulating wing deformation, the transmission component is a lead screw, and the connecting component has a threaded hole. The lead screw passes through the threaded hole and is threadedly engaged with the threaded hole. The drive motor drives the lead screw to rotate, and the lead screw drives the connecting component to move along the first direction.

[0013] As an optional technical solution for the aileron test device for simulating wing deformation, the drive assembly also includes a first baffle and a second baffle. The first baffle and the second baffle are rotatably connected to both ends of the transmission component, respectively. The first baffle is located between the connector and the sensor. The first baffle abuts against the base. Both the first baffle and the second baffle can cooperate with the connector for stopping.

[0014] As an optional technical solution for an aileron test device simulating wing deformation, the aileron test device simulating wing deformation also includes multiple first support rods and multiple second support rods. One end of the first support rod is connected to a connector, and the other end of the first support rod is connected to the aileron connector to be tested. One end of the second support rod is connected to a connector, and the other end of the second support rod is hinged to the aileron connector to be tested. Multiple first support rods and multiple connectors are set in a one-to-one correspondence, and multiple second support rods and multiple connectors are set in a one-to-one correspondence.

[0015] On the other hand, the present invention provides a simulation test method, applied to the aileron test device for simulating wing deformation in any of the above-mentioned schemes, the simulation test method comprising:

[0016] S1: Fix the base to the ground of the test site;

[0017] S2: Connect the drive components and connectors, and install multiple connected drive components and connectors into the corresponding receiving slots;

[0018] S3: Multiple connectors are connected to the aileron joint to be tested via the first and second support rods in the aileron test device that simulates wing deformation.

[0019] S4: By driving the corresponding connecting parts to move to the preset position through each driving component, the aileron under test is deformed to achieve the preset load, thereby simulating the effect of wing deformation on the aileron under test.

[0020] The beneficial effects of this invention are as follows:

[0021] This invention provides an aileron testing device for simulating wing deformation. The device includes a base, multiple connectors, and multiple drive components. By using the drive components, the connectors, positioned within a receiving groove, can be moved along a first direction. Since each connector can connect to the aileron under test, the aileron can be moved to a designated position along the first direction according to the preset position of each connector, causing deformation and simulating the effects of wing deformation on the aileron. The aileron testing device of this invention, which uses drive components to move the connectors, thereby moving the aileron under test, simplifies the control process and effectively shortens the overall aircraft testing cycle for ailerons. While simulating aileron deformation on a ground bench, it reduces the workload of loading and measurement, simplifies the testing process, saves testing costs, and shortens the overall aircraft testing cycle. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the aileron test device for simulating wing deformation in an embodiment of the present invention;

[0023] Figure 2 This is a schematic diagram of the structure of the driving component in an embodiment of the present invention;

[0024] Figure 3 This is a schematic diagram of the connector structure in an embodiment of the present invention;

[0025] Figure 4 This is a schematic diagram of the base structure in an embodiment of the present invention;

[0026] Figure 5 This is a schematic diagram of the structure of the aileron to be tested mounted on the aileron test device for simulating wing deformation in an embodiment of the present invention.

[0027] In the picture:

[0028] 1. Base; 11. Receiving groove; 111. Limiting protrusion; 12. Fixing hole;

[0029] 2. Connecting component; 21. Limiting groove; 22. Limiting block; 23. Connecting block; 231. Clearance groove; 232. Fastening hole; 24. Threaded hole;

[0030] 3. Drive assembly; 31. Drive motor; 32. Sensor; 33. Transmission component; 34. First baffle; 35. Second baffle;

[0031] 4. First support rod;

[0032] 5. Second support rod;

[0033] 6. Aileron to be tested. Detailed Implementation

[0034] The technical solution of the present invention will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0035] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," 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. The terms "first position" and "second position" refer to two different positions. Furthermore, "above," "on top of," and "over" the first feature in relation to the second feature includes the first feature directly above and diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "under," and "below" the first feature in relation to the second feature includes the first feature directly below and diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0036] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0037] Embodiments of the present invention are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0038] like Figures 1 to 5As shown, this embodiment provides an aileron testing device for simulating wing deformation. The device includes a base 1, multiple connectors 2, and multiple drive components 3. Connectors 2 are slidably disposed in a receiving groove 11 along a first direction and can engage with the receiving groove 11 at its upper limit in a second direction. Connectors 2 can connect to the aileron 6 to be tested. Simultaneously, the drive components 3 drive the connectors 2, thereby moving them along the first direction, thus causing the aileron 6 to move along the first direction and deform. In this invention, there are multiple receiving grooves 11, connectors 2, and drive components 3. Multiple connectors 2 and multiple receiving grooves 11 are arranged in a one-to-one correspondence, and multiple drive components 3 and multiple connectors 2 are arranged in a one-to-one correspondence. This allows the aileron 6 to be tested to be moved to a designated position along the first direction according to the initially preset position of each connector 2, causing the aileron 6 to deform and simulating the effect of wing deformation on the aileron 6. The first direction and the second direction are perpendicular, which allows the connector 2 to always move along the first direction, and the aileron 6 connector and the base 1 are perpendicular to each other.

[0039] The aileron testing device for simulating wing deformation of the present invention uses a drive component 3 to drive the connecting member 2 to move, thereby driving the aileron 6 joint under test to move. The control process is simple and can effectively shorten the overall test cycle of the aileron. While realizing the ground bench test of the aileron to simulate wing deformation, it reduces the workload of aileron test loading and measurement, simplifies the test complexity, saves test costs, and shortens the overall test cycle of the aircraft.

[0040] In this embodiment, the inner wall of the receiving groove 11 has a limiting protrusion 111, and the connector 2 has a limiting groove 21. Both the limiting protrusion 111 and the limiting groove 21 extend along the first direction. During installation, the limiting protrusion 111 is placed in the limiting groove 21, and the limiting protrusion 111 and the limiting groove 21 are engaged in a limiting fit in the second direction, thereby achieving the purpose of the connector 2 and the base 1 being engaged in a limiting fit in the second direction.

[0041] Alternatively, the connector 2 has a limiting protrusion 111 and the inner wall of the receiving groove 11 has a limiting groove 21. With this configuration, the connector 2 and the base 1 can also achieve the purpose of limiting the fit in the second direction.

[0042] Specifically, the connector 2 includes a limiting block 22 and a connecting block 23 that are connected to each other. The limiting block 22 is set in the receiving groove 11 and can be engaged with the receiving groove 11 in the second direction. At the same time, the connecting block 23 is located outside the receiving groove 11, which is convenient to connect with the connector of the aileron 6 to be tested. The driving component 3 and the limiting block 22 can be driven to connect, and the limiting block 22 can be driven to move along the first direction by the driving component 3.

[0043] Among them, the drive component 3 includes, but is not limited to, devices with telescopic functions such as telescopic cylinders.

[0044] Furthermore, the aileron testing device for simulating wing deformation includes a first fastener, and the connecting block 23 is connected to the aileron 6 connector to be tested via the first fastener. This configuration, where the connecting block 23 and the aileron 6 connector are connected via the first fastener, facilitates installation and disassembly. The first fastener is a bolt.

[0045] The connecting block 23 has a clearance groove 231 and a fastening hole 232. The clearance groove 231 extends along a first direction, so that after the first fastener passes through the aileron 6 connector to be tested and the fastening hole 232 in sequence, it can enter the clearance groove 231, which facilitates the operation by the operator. Furthermore, the fastening hole 232 extends through the clearance groove 231 along a second direction, so that the aileron 6 connector to be tested after installation can be perpendicular to the base 1.

[0046] In this embodiment, the drive assembly 3 includes a drive motor 31, a sensor 32, and a transmission component 33. The output end of the drive motor 31 is connected to the input end of the sensor 32, and the output end of the sensor 32 is connected to the transmission component 33. The transmission component 33 and the connecting member 2 are sleeved on the transmission component 33. The transmission component 33 is located in the receiving groove 11. When moving, the drive motor 31 drives the transmission component 33 to rotate, thereby achieving the purpose of the transmission component 33 driving the connecting member 2 to move along the first direction. The sensor 32 is an angle sensor, which can detect the moving distance of the connecting member 2 by detecting the number of rotations of the transmission component 33.

[0047] Furthermore, in this embodiment, the transmission component 33 can be configured as a lead screw, and the connecting component 2 has a threaded hole 24. The lead screw passes through the threaded hole 24 and is threaded into the threaded hole 24, so that the drive motor 31 can drive the lead screw to rotate, thereby achieving the purpose of the lead screw driving the connecting component 2 to move along the first direction.

[0048] Specifically, the drive assembly 3 also includes a first baffle 34 and a second baffle 35. The first baffle 34 and the second baffle 35 are rotatably connected to both ends of the transmission member 33, respectively. The first baffle 34 is located between the connector 2 and the sensor 32, and abuts against the base 1 to ensure the stability of the drive assembly 3 during operation. At the same time, both the first baffle 34 and the second baffle 35 can cooperate with the connector 2 to stop, which can limit the movement range of the connector 2 and prevent the connector 2 from exceeding the movement range.

[0049] Specifically, the aileron testing device for simulating wing deformation also includes multiple first support rods 4 and multiple second support rods 5. One end of the first support rod 4 is connected to the connector 2, and the other end of the first support rod 4 is connected to the aileron 6 joint to be tested. Simultaneously, one end of the second support rod 5 is connected to the connector 2, and the other end of the second support rod 5 is hinged to the aileron 6 joint to be tested. The multiple first support rods 4 and multiple connectors 2 are arranged in a one-to-one correspondence, and the multiple second support rods 5 and multiple connectors 2 are also arranged in a one-to-one correspondence. With this configuration, the aileron 6 joint to be tested can also rotate, realizing the change of aileron angle and meeting the loading test requirements at different angles.

[0050] Optionally, the aileron test device for simulating wing deformation also includes a second fastener, with a fixing hole 12 penetrating the base 1 along the second direction, and the second fastener passing through the fixing hole 12 to connect the base 1 and the test site ground device.

[0051] This embodiment also provides a simulation test method applied to the aileron test device for simulating wing deformation in the above scheme. The simulation test method includes: S1: fixing the base 1 to the ground device of the test site; S2: connecting the drive component 3 and the connector 2, and installing multiple connected drive components 3 and connectors 2 in the corresponding receiving slots 11; S3: connecting multiple connectors 2 to the aileron 6 to be tested through the first support rod 4 and the second support rod 5 in the aileron test device for simulating wing deformation; S4: moving the corresponding connectors 2 to the preset position through each drive component 3, so that the aileron 6 to be tested deforms to achieve the preset load, thereby realizing the effect of wing deformation on the aileron 6 to be tested.

[0052] First, fix the fixing hole 12 on the base 1 to the ground device of the test site to ensure that the base 1 is in a fixed state with zero degrees of freedom;

[0053] The drive assembly 3 and connector 2 are then installed onto the base 1. Connector 2 and base 1 have a matching motion track. Under this track setting, the drive assembly 3 is powered by the drive motor 31, and the connector 2 can move within the base 1 along an axial direction parallel to the drive assembly 3 via a lead screw.

[0054] The first support rod 4 and the second support rod 5 are fixed to the connector 2 with bolts, so that the first support rod 4 and the second support rod 5 can move along the direction parallel to the drive assembly 3 with the connector 2;

[0055] The aileron to be tested is connected to the first support rod 4 and the second support rod 5 through the actuator joint and the hinge joint. Thus, the simulated connection between the wing and the aileron to be tested is realized.

[0056] Based on the load internal force solutions F of the wing structure under various flight conditions provided by the load department, the loads F of the actuator joint and hinge joint connecting the wing and the aileron under test under various flight conditions can be obtained.

[0057] The drive assembly 3 drives the connector 2 to move along the axial direction parallel to the drive assembly 3, thereby driving the first support rod 4 and the second support rod 5 to move, thereby realizing the movement of the actuator joint and hinge joint on the aileron under test in the direction perpendicular to the span of the aileron. The deformation generated by the movement will bring corresponding load effects to the aileron under test, that is, realize the effect of wing deformation on the aileron under test.

[0058] Because the aircraft wing structure will deform under the load of flight conditions, the joint position on the wing will also deform accordingly. According to the deformation compatibility equation, the aileron joint to be tested will also deform due to its hinge with the wing joint. The value of this deformation can be simulated by applying a load force to the aileron joint to be tested, and the load force value is determined by the load under flight conditions.

[0059] The deformation compatibility equations are not geometric equations, but rather conditions that ensure the integrity and continuity of a continuous solid after deformation. These conditions can be expressed by six second-order partial differential equations satisfied by the six strain components at each point within the solid (i.e., three stretching strains and three shear strains in a Cartesian coordinate system). In elasticity, these equations describe the relationships between the strain components, ensuring that the deformed object neither breaks apart between adjacent parts nor overlaps, thus maintaining the continuity and integrity of the object.

[0060] In summary, to simulate wing deformation between the wing and the aileron under test, and to support the aileron under deformation, the key lies in understanding the load F on the actuator joint and hinge joint connecting the two under various flight conditions. Therefore, the core of this invention is to move the actuator joint and hinge joint in the direction perpendicular to the aileron spanwise. The displacement value is obtained by obtaining the stress value σ from the wing load F, and then obtaining the strain ε, i.e., the displacement value.

[0061] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the implementation of the present invention. Those skilled in the art can make other variations or modifications based on the above description. It is neither necessary nor possible to exhaustively describe all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the scope of protection of the claims of the present invention.

Claims

1. Aileron test apparatus to simulate deformation of an airfoil, characterized by, include: The base (1) has multiple spaced-apart receiving slots (11) and can be connected to the test site ground device; Multiple connectors (2) are slidably disposed in the receiving groove (11) along the first direction and are engaged with the receiving groove (11) in the second direction. At least a portion of the connector (2) is located outside the receiving groove (11) and can be connected to the connector of the aileron (6) to be tested. The first direction and the second direction are perpendicular. Multiple connectors (2) and multiple receiving grooves (11) are arranged in a one-to-one correspondence. Multiple drive components (3) are disposed on the base (1). The drive components (3) and the connectors (2) are driven to be connected to drive the connectors (2) to move along the first direction. The multiple drive components (3) and the multiple connectors (2) are arranged one-to-one. The aileron test device for simulating wing deformation also includes multiple first support rods (4) and multiple second support rods (5). One end of the first support rod (4) is connected to the connector (2), and the other end of the first support rod (4) is connected to the joint of the aileron (6) to be tested. One end of the second support rod (5) is connected to the connector (2), and the other end of the second support rod (5) is hinged to the joint of the aileron (6) to be tested. The multiple first support rods (4) and the multiple connectors (2) are arranged in a one-to-one correspondence, and the multiple second support rods (5) and the multiple connectors (2) are arranged in a one-to-one correspondence.

2. The aileron test apparatus that simulates deformation of a wing according to claim 1, characterized by The inner wall of the connector (2) and the receiving groove (11) has a limiting protrusion (111) and a limiting groove (21), respectively. The limiting protrusion (111) and the limiting groove (21) both extend along the first direction. The limiting protrusion (111) is located in the limiting groove (21). The limiting protrusion (111) and the limiting groove (21) are engaged in a limiting fit in the second direction.

3. The aileron test apparatus that simulates deformation of a wing according to Claim 1, characterized by The connector (2) includes a limiting block (22) and a connecting block (23) connected to each other. The limiting block (22) is located in the receiving groove (11) and is in upper limit engagement with the receiving groove (11) in the second direction. The connecting block (23) is located outside the receiving groove (11) and can be connected to the connector of the aileron (6) to be tested. The driving assembly (3) and the limiting block (22) are driven to drive the limiting block (22) to move along the first direction.

4. The aileron test apparatus of claim 3, wherein, The aileron test device for simulating wing deformation includes a first fastener, and the connecting block (23) is connected to the aileron (6) to be tested through the first fastener.

5. The aileron testing apparatus for simulating wing deformation according to claim 4, characterized in that, The connecting block (23) has a clearance groove (231) and a fastening hole (232). The clearance groove (231) extends along the first direction, and the fastening hole (232) extends through the clearance groove (231) along the second direction. The first fastener passes through the aileron (6) joint to be tested, the fastening hole (232) and the clearance groove (231) in sequence to connect the aileron (6) joint to be tested and the connecting block (23).

6. The aileron testing apparatus for simulating wing deformation according to claim 1, characterized in that, The drive assembly (3) includes a drive motor (31), a sensor (32), and a transmission component (33). The output end of the drive motor (31) is connected to the input end of the sensor (32), and the output end of the sensor (32) is connected to the transmission component (33). The transmission component (33) and the connector (2) are sleeved on the transmission component (33). The transmission component (33) is located in the receiving groove (11). The drive motor (31) drives the transmission component (33) to rotate. The transmission component (33) drives the connector (2) to move along the first direction. The sensor (32) is used to detect the moving distance of the connector (2).

7. The aileron testing apparatus for simulating wing deformation according to claim 6, characterized in that, The transmission component (33) is a lead screw, and the connecting component (2) has a threaded hole (24). The lead screw passes through the threaded hole (24) and is threadedly engaged with the threaded hole (24). The drive motor (31) drives the lead screw to rotate, and the lead screw drives the connecting component (2) to move along the first direction.

8. The aileron testing apparatus for simulating wing deformation according to claim 6, characterized in that, The drive assembly (3) further includes a first baffle (34) and a second baffle (35). The first baffle (34) and the second baffle (35) are rotatably connected to both ends of the transmission member (33). The first baffle (34) is located between the connector (2) and the sensor (32). The first baffle (34) abuts against the base (1). Both the first baffle (34) and the second baffle (35) can stop and cooperate with the connector (2).

9. A simulation test method, characterized in that, The aileron testing apparatus for simulating wing deformation as described in any one of claims 1-8, wherein the simulation testing method comprises: S1: Fix the base (1) to the test site ground device; S2: Connect the drive assembly (3) and the connector (2), and install the multiple connected drive assemblies (3) and connectors (2) into the corresponding receiving slots (11); S3: The multiple connecting pieces (2) are connected to the joint of the aileron (6) to be tested through the first support rod (4) and the second support rod (5) in the aileron test device for simulating wing deformation; S4: The driving components (3) drive the corresponding connecting parts (2) to move to the preset position, so that the aileron (6) to be tested deforms to achieve the preset load, thereby simulating the effect of wing deformation on the aileron (6) to be tested.

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