Aleron test device for simulating wing deformation and simulation test method

Abstract

The invention relates to the technical field of aircraft structure design, and particularly discloses an aileron test device for simulating wing deformation and a simulation test method.The aileron test device for simulating wing deformation comprises a base, a plurality of connecting pieces and a plurality of driving assemblies. According to the aileron test device for simulating wing deformation, the driving assembly drives the connecting piece to move, so that the connecting piece drives the to-be-tested aileron joint to move, the control process is simple, and the test period of the whole aileron test machine can be effectively shortened; while an aileron ground bench test for simulating wing deformation is realized, the loading and measurement workload of an aileron test is reduced, the test complexity is simplified, the test cost is saved, and the whole-aircraft test period is shortened.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft structure design, and in particular to aileron test device for simulating wing deformation and simulation test method. BACKGROUND

[0002] The aileron of a large aircraft is connected with the wing box through multiple joints, and is a statically indeterminate structure. Generally, the most serious strain value on the aileron structure can reach 1000-2000 micro-strains, and the strain value of the aileron affected by the wing deformation is about 700 micro-strains, so from the order of magnitude of the strain value, the wing box deformation will inevitably affect the stress and strain distribution of the aileron surface. Therefore, when carrying out full-size aileron test, the influence of the wing box deformation on the aileron must be considered.

[0003] Generally, the size of the aileron is obviously much smaller than that of the wing box structure, but in order to consider the influence of the wing box deformation, the wing box must be matched to implement loading, which greatly increases the demand for test loading and corresponding measurement equipment, not only occupies the full aircraft test time, but also lengthens the full aircraft test cycle and the model development cycle. If a wing box is specially manufactured as an aileron test support section, the strength of the aileron can be checked, but the test cost will be greatly increased.

[0004] In the prior art, the deformation of the beam body drives the deformation of the slat test piece to carry out the slat test. However, the control process is relatively complicated and the test cost is too high. SUMMARY

[0005] The present application aims to provide an aileron test device for simulating wing deformation and simulation test method, to solve the problem of complicated control process and high cost in the prior art.

[0006] In one aspect, the present application provides an aileron test device for simulating wing deformation, which comprises: a base having a plurality of spaced apart accommodating grooves and being capable of being connected with a test site ground device; a plurality of connecting pieces, the connecting pieces being slidingly arranged in the accommodating grooves along a first direction and being limitedly matched with the accommodating grooves in a second direction, at least part of the connecting pieces being located outside the accommodating grooves and being capable of being connected with aileron joints to be tested, the first direction being perpendicular to the second direction, the plurality of connecting pieces and the plurality of accommodating grooves being arranged one-to-one; and a plurality of driving assemblies, the driving assemblies being arranged on the base, the driving assemblies and the connecting pieces being drivingly connected to drive the connecting pieces to move along the first direction, the plurality of driving assemblies and the plurality of connecting pieces being arranged one-to-one.

[0007] As an optional technical scheme of the aileron test device for simulating wing deformation, one of the connecting piece and the inner wall of the accommodating groove has a limiting protrusion, and the other has a limiting groove, the limiting protrusion and the limiting groove extend along the first direction, the limiting protrusion is located in the limiting groove, and the limiting protrusion and the limiting groove are limited in the second direction.

[0008] As an optional technical scheme of the aileron test device for simulating wing deformation, the connecting piece includes a limiting block and a connecting block connected with each other, the limiting block is located in the accommodating groove and is limited in the second direction with the accommodating groove, and the connecting block is located outside the accommodating groove and can be connected with the aileron joint to be tested.

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

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

[0011] As an optional technical scheme of the aileron test device for simulating wing deformation, the driving assembly includes a driving motor, a sensor and a transmission piece, the output end of the driving motor is connected with the input end of the sensor, the output end of the sensor is connected with the transmission piece, the transmission piece is sleeved on the connecting piece, the transmission piece is located in the accommodating groove, the driving motor drives the transmission piece to rotate, the transmission piece drives the connecting piece to move along the first direction, and the sensor is used for detecting the moving distance of the connecting piece.

[0012] As an optional technical scheme of the aileron test device for simulating wing deformation, the transmission piece is a lead screw, the connecting piece has a threaded hole, the lead screw penetrates the threaded hole and is screwed with the threaded hole, the driving motor drives the lead screw to rotate, and the lead screw drives the connecting piece to move along the first direction.

[0013] As an optional technical scheme of the aileron test device for simulating wing deformation, the driving assembly further includes a first baffle and a second baffle, the first baffle and the second baffle are respectively rotationally connected with two ends of the transmission piece, the first baffle is located between the connecting piece and the sensor, the first baffle abuts against the base, and the first baffle and the second baffle can be stopped by the connecting piece.

[0014] As an optional technical solution of the aileron test device simulating wing deformation, the aileron test device simulating wing deformation further comprises a plurality of first supporting rods and a plurality of second supporting rods, one end of the first supporting rod is connected with the connecting piece, the other end of the first supporting rod is connected with the aileron joint to be tested, one end of the second supporting rod is connected with the connecting piece, the other end of the second supporting rod is hingedly connected with the aileron joint to be tested, the plurality of first supporting rods and the plurality of connecting pieces are one-to-one correspondingly arranged, and the plurality of second supporting rods and the plurality of connecting pieces are one-to-one correspondingly arranged.

[0015] In another aspect, the present application provides a simulation test method applied to the aileron test device simulating wing deformation in any of the above-mentioned solutions, and the simulation test method comprises:

[0016] S1: fixing the base on the ground device of the test site;

[0017] S2: connecting the driving assembly and the connecting piece, and installing a plurality of connected driving assemblies and connecting pieces in the corresponding accommodating grooves;

[0018] S3: connecting the plurality of connecting pieces with the aileron joint to be tested through the first supporting rod and the second supporting rod in the aileron test device simulating wing deformation;

[0019] S4: moving the corresponding connecting piece to the preset position through each driving assembly, so that the aileron to be tested is deformed to reach the preset load, and the influence of the wing deformation on the aileron to be tested is realized.

[0020] The present application has the following advantages:

[0021] The present application provides an aileron test device simulating wing deformation, which comprises a base, a plurality of connecting pieces and a plurality of driving assemblies. By arranging the driving assembly, the connecting piece arranged in the accommodating groove can be moved in the first direction, and since the plurality of connecting pieces are connected with the aileron joint to be tested, the aileron to be tested can be moved to the specified position in the first direction according to the preset position of each connecting piece, so that the aileron to be tested is deformed, and the influence of the wing deformation on the aileron to be tested is realized. By using the aileron test device simulating wing deformation of the present application, the connecting piece is moved by the driving assembly, and then the aileron to be tested is moved by the connecting piece, so that the control process is simple, the whole machine test cycle of the aileron test can be effectively shortened, the aileron ground bench test simulating wing deformation is realized, the workload of aileron test loading and measurement is reduced, the test complexity is simplified, the test cost is saved, and the whole machine test cycle is shortened. BRIEF DESCRIPTION OF DRAWINGS

[0022] Figure 1 It is a structural schematic view of the aileron test device simulating wing deformation in the embodiment of the present application.

[0023] Figure 2 Fig. 1 is a structural schematic diagram of a driving assembly in an embodiment of the present application;

[0024] Figure 3 Fig. 2 is a structural schematic diagram of a connecting piece in an embodiment of the present application;

[0025] Figure 4 Fig. 3 is a structural schematic diagram of a base in an embodiment of the present application;

[0026] Figure 5 Fig. 4 is a structural schematic diagram of a flap test device on which a flap to be tested is installed in an embodiment of the present application.

[0027] In the drawings:

[0028] 1, base; 11, accommodating groove; 111, limiting protrusion; 12, fixing hole;

[0029] 2, connecting piece; 21, limiting groove; 22, limiting block; 23, connecting block; 231, avoiding slot; 232, fastening hole; 24, threaded hole;

[0030] 3, driving assembly; 31, driving motor; 32, sensor; 33, transmission piece; 34, first baffle; 35, second baffle;

[0031] 4, first supporting rod;

[0032] 5, second supporting rod;

[0033] 6, flap to be tested. DETAILED DESCRIPTION

[0034] The technical solutions of the present application will be described clearly and completely below in conjunction with the drawings. Obviously, the described embodiments are part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all the other embodiments obtained by those skilled in the art without creative labor fall within the protection scope of the present application.

[0035] In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate the orientation or positional relationship shown in the drawings based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application. In addition, the terms "first", "second", are only for the purpose of description, and cannot be understood as indicating or implying relative importance. Among them, the terms "first position" and "second position" are two different positions, and moreover, the "above", "over" and "on" of the first feature to the second feature include the first feature above and obliquely above the second feature, or only indicate that the first feature is higher than the second feature in horizontal height. The "below", "under" and "under" of the first feature to the second feature include the first feature below and obliquely below the second feature, or only indicate that the first feature is lower than the second feature in horizontal height.

[0036] In the description of the present application, it should be noted that unless otherwise explicitly specified and limited, the terms "mounting", "connecting", "connecting" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium; it can be the communication inside two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0037] The embodiments of the present application are described in detail below, examples of which are shown in the drawings, wherein the same or similar reference numerals represent the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by referring to the drawings are exemplary and are only used to explain the present application, and cannot be understood as a limitation on the present application.

[0038] As Figures 1 to 5As shown, the embodiment provides aileron test device for simulating wing deformation, which comprises a base 1, a plurality of connecting pieces 2 and a plurality of driving assemblies 3. The connecting piece 2 is arranged in the accommodating groove 11 in the first direction and can be limitedly matched with the accommodating groove 11 in the second direction. The connecting piece 2 can be connected with the aileron 6 to be tested, and is driven by the driving assembly 3 and the connecting piece 2, so as to drive the connecting piece 2 to move in the first direction, thereby realizing the movement of the aileron 6 to be tested in the first direction to produce deformation. The accommodating groove 11, the connecting piece 2 and the driving assembly 3 in the embodiment are all in plurality, the plurality of connecting pieces 2 and the plurality of accommodating grooves 11 are arranged one by one, and the plurality of driving assemblies 3 and the plurality of connecting pieces 2 are arranged one by one. Thus, the aileron 6 to be tested can be driven to the specified position in the first direction according to the preset position of each connecting piece 2, so as to deform the aileron 6 to be tested and achieve the influence of the simulated wing deformation on the aileron 6 to be tested. The first direction is perpendicular to the second direction, so that the connecting piece 2 can always move in the first direction, and the aileron 6 to be tested is perpendicular to the base 1.

[0039] The aileron test device for simulating wing deformation of the embodiment drives the connecting piece 2 to move through the driving assembly 3, so that the connecting piece drives the aileron 6 to be tested to move, which has a simple control process and can effectively shorten the aileron test whole machine test cycle. While realizing the aileron ground bench test for simulating wing deformation, the aileron test loading and measuring workload is reduced, the test complexity is simplified, the test cost is saved, and the whole machine test cycle is shortened.

[0040] In the embodiment, the inner wall of the accommodating groove 11 is provided with a limiting protrusion 111, and the connecting piece 2 is provided with a limiting groove 21. The limiting protrusion 111 and the limiting groove 21 extend in the first direction. During installation, the limiting protrusion 111 is arranged in the limiting groove 21, and the limiting protrusion 111 and the limiting groove 21 are limitedly matched in the second direction, so as to realize the limiting matching of the connecting piece 2 and the base 1 in the second direction.

[0041] Alternatively, the connecting piece 2 is provided with a limiting protrusion 111, and the inner wall of the accommodating groove 11 is provided with a limiting groove 21. In this way, the limiting matching of the connecting piece 2 and the base 1 in the second direction can also be realized.

[0042] Specifically, the connecting piece 2 comprises a limiting block 22 and a connecting block 23 connected with each other. The limiting block 22 is arranged in the accommodating groove 11 and can be limitedly matched with the accommodating groove 11 in the second direction. Meanwhile, the connecting block 23 is located outside the accommodating groove 11 and is convenient for being connected with the aileron 6 to be tested. The driving assembly 3 can be drivenly connected with the limiting block 22, and the limiting block 22 can be driven to move in the first direction by the driving assembly 3.

[0043] The driving assembly 3 includes, but is not limited to, a telescopic cylinder or other device with telescopic function.

[0044] Further, 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. In this way, the connecting block 23 and the aileron 6 to be tested are connected through the first fastener, which facilitates installation and disassembly. The first fastener is a bolt.

[0045] The connecting block 23 has an avoiding groove 231 and a fastening hole 232. The avoiding groove 231 extends in the first direction, so that the first fastener can enter the avoiding groove 231 after passing through the aileron 6 to be tested and the fastening hole 232 in sequence, facilitating the operation of the operator. Moreover, the fastening hole 232 penetrates the avoiding groove 231 in the second direction, so that the aileron 6 to be tested can be perpendicular to the base 1 after installation.

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

[0047] Further, in this embodiment, the transmission member 33 can be a lead screw, and the connecting member 2 has a threaded hole 24. The lead screw passes through the threaded hole 24 and is screwed with the threaded hole 24, so that the driving motor 31 can drive the lead screw to rotate, thereby realizing the purpose of driving the connecting member 2 to move in the first direction.

[0048] Specifically, the driving assembly 3 further includes a first baffle 34 and a second baffle 35. The first baffle 34 and the second baffle 35 are respectively rotatably connected to the two ends of the transmission member 33. The first baffle 34 is located between the connecting member 2 and the sensor 32, and abuts against the base 1 to ensure the stability of the driving assembly 3 during operation. The first baffle 34 and the second baffle 35 can be stopped by the connecting member 2, so as to limit the movement range of the connecting member 2 and prevent the connecting member 2 from exceeding the movement range.

[0049] Specifically, the aileron test device for simulating wing deformation further comprises a plurality of first support rods 4 and a plurality of second support rods 5. One end of the first support rod 4 is connected with the connecting piece 2, and the other end of the first support rod 4 is connected with the aileron 6 to be tested. Meanwhile, one end of the second support rod 5 is connected with the connecting piece 2, and the other end of the second support rod 5 is hingedly connected with the aileron 6 to be tested. The plurality of first support rods 4 and the plurality of connecting pieces 2 are one-to-one correspondingly arranged, and the plurality of second support rods 5 and the plurality of connecting pieces 2 are one-to-one correspondingly arranged. In this way, the aileron 6 to be tested can also rotate, the aileron angle can be changed, and the loading test under different angles can be met.

[0050] Optionally, the aileron test device for simulating wing deformation further comprises a second fastener, the fixing hole 12 penetrates through the base 1 along the second direction, and the second fastener penetrates through the fixing hole 12 to connect the base 1 and the test site ground device.

[0051] The 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 comprises the following steps: S1: fixing the base 1 on the test site ground device; S2: connecting the driving assembly 3 and the connecting piece 2, and installing the plurality of connected driving assemblies 3 and connecting pieces 2 in the corresponding accommodating grooves 11; S3: connecting the plurality of connecting pieces 2 and 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: driving the corresponding connecting piece 2 to move to a preset position through each driving assembly 3, so that the aileron 6 to be tested is deformed to reach a preset load, and the influence of the wing deformation on the aileron 6 to be tested is simulated.

[0052] First, the fixing hole 12 on the base 1 is fixed with the test site ground device, so that the base 1 as a whole is in a fixed state with zero degree of freedom;

[0053] Then, the driving assembly 3 and the connecting piece 2 are installed on the base 1. The connecting piece 2 has a matched movement track with the base 1. Under such a track setting, the driving assembly 3 is powered by the driving motor 31, and the connecting piece 2 can move in the base 1 along the axial direction parallel to the driving assembly 3 through the lead screw;

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

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

[0056] According to the wing structure load department provides the load internal force solution F of wing in each flight condition, the load F of the actuator joint and hinge joint connected with the wing and the test aileron in each flight condition can be obtained.

[0057] The connecting piece 2 is driven by the driving assembly 3 to move along the axial direction parallel to the driving assembly 3, so as to drive the first support rod 4 and the second support rod 5 to move, and then the movement of the actuator joint and hinge joint on the test aileron in the vertical aileron span direction is realized, the deformation caused by the movement brings corresponding load influence to the test aileron, that is, the influence of the wing deformation to the test aileron is realized.

[0058] Since the aircraft wing structure will be deformed under the load action in the flight condition, the joint position on the wing will also be deformed, and then according to the deformation compatibility equation, the test aileron joint will also be deformed due to the hinge with the wing joint, and the value of the deformation can be simulated by applying a load force to the test aileron joint, and the load force value is determined by the load in the flight condition.

[0059] The deformation compatibility equation is not a geometric equation, but a condition that ensures the continuity and continuity of the continuous solid after deformation. These conditions can be expressed by six second-order partial differential equations satisfied by the six strain components (i.e. three extensional strains and three shear strains in the Cartesian rectangular coordinate system) of each point in the solid. In the field of elastic mechanics, these equations describe the relationship between strain components, ensuring that the deformed object neither breaks between adjacent parts nor overlaps, thereby maintaining the continuity and integrity of the object.

[0060] In summary, in order to realize the simulation of the wing deformation between the wing and the test aileron, and to support the test aileron in the deformed state, the key is to realize the load F influence on the actuator joint and hinge joint connected between the two in each flight condition, so the core of the present application is to move the actuator joint and hinge joint in the vertical aileron span direction, and the displacement value of the movement is obtained by the stress value σ of the wing load F, and then the strain ε, that is, the displacement value.

[0061] Obviously, the above embodiments of the present application are only examples for clearly illustrating the present application, and are not intended to limit the embodiments of the present application. For ordinary skilled in the art, other different forms of changes or variations can be made on the basis of the above description. Here, all the embodiments are not required to be exhausted. Any modification, equivalent replacement and improvement made within the spirit and principle of the present application shall be included in the protection scope of the claims of the present application.

Claims

1. An aileron test device for simulating wing deformation, characterized in that: include: A base (1) has a plurality of spaced-apart receiving slots (11) and is capable of being connected to a ground device at a test site; A plurality of connecting members (2), wherein the connecting members (2) are slidably arranged in the receiving groove (11) along a first direction and are engaged with the receiving groove (11) in an upper limit position in a second direction, at least a portion of the connecting member (2) is located outside the receiving groove (11) and is capable of being connected to a joint of an aileron (6) to be tested, the first direction and the second direction are perpendicular, and the plurality of connecting members (2) and the plurality of receiving grooves (11) are arranged in a one-to-one correspondence; A plurality of drive assemblies (3), wherein the drive assemblies (3) are arranged on the base (1), and the drive assemblies (3) and the connecting member (2) are drivingly connected to drive the connecting member (2) to move along the first direction, and the plurality of drive assemblies (3) and the plurality of connecting members (2) are arranged in a one-to-one correspondence.

2. The aileron test device for simulating wing deformation according to claim 1, characterized in that: One of the inner walls of the connecting member (2) and the accommodating groove (11) has a limiting protrusion (111), and the other has a limiting groove (21). Both the limiting protrusion (111) and the limiting groove (21) 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) cooperate in limiting position in the second direction.

3. The aileron test device for simulating wing deformation according to claim 1, characterized in that: The connecting member (2) includes a limit block (22) and a connecting block (23) connected to each other, the limit block (22) is located in the accommodating groove (11) and cooperates with the accommodating groove (11) to limit the position in the second direction, the connecting block (23) is located outside the accommodating groove (11) and can be connected to the joint of the aileron to be tested (6), and the driving component (3) and the limit block (22) are drivingly connected to drive the limit block (22) to move along the first direction.

4. The aileron test device for simulating wing deformation according to claim 3, characterized in that: The aileron test device for simulating wing deformation comprises a first fastener, and the connecting block (23) is connected to the joint of the aileron to be tested (6) via the first fastener.

5. The aileron test device for simulating wing deformation according to claim 4, characterized in that: The connecting block (23) has an avoidance groove (231) and a fastening hole (232), wherein the avoidance groove (231) extends along the first direction, and the fastening hole (232) penetrates the avoidance groove (231) along the second direction, and the first fastener sequentially passes through the joint of the aileron (6) to be tested, the fastening hole (232) and the avoidance groove (231), so as to connect the joint of the aileron (6) to be tested and the connecting block (23).

6. The aileron test device for simulating wing deformation according to claim 1, characterized in that: The driving assembly (3) comprises a driving motor (31), a sensor (32) and a transmission member (33); the output end of the driving motor (31) is connected to the input end of the sensor (32); the output end of the sensor (32) is connected to the transmission member (33); the transmission member (33) and the connecting member (2) are sleeved on the transmission member (33); the transmission member (33) is located in the accommodating groove (11); the driving motor (31) drives the transmission member (33) to rotate; the transmission member (33) drives the connecting member (2) to move along the first direction; and the sensor (32) is used to detect the moving distance of the connecting member (2).

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

8. The aileron test device for simulating wing deformation according to claim 6, characterized in that: The driving assembly (3) further comprises a first baffle (34) and a second baffle (35), wherein the first baffle (34) and the second baffle (35) are respectively rotatably connected to two ends of the transmission member (33), the first baffle (34) is located between the connecting member (2) and the sensor (32), the first baffle (34) abuts against the base (1), and the first baffle (34) and the second baffle (35) are both capable of engaging with the connecting member (2) as a stop.

9. The aileron test device for simulating wing deformation according to claim 1, characterized in that: The aileron test device for simulating wing deformation also includes a plurality of first support rods (4) and a plurality of second support rods (5), one end of the first support rod (4) is connected to the connecting member (2), the other end of the first support rod (4) is connected to the joint of the aileron to be tested (6), one end of the second support rod (5) is connected to the connecting member (2), the other end of the second support rod (5) is hinged to the joint of the aileron to be tested (6), the plurality of first support rods (4) and the plurality of connecting members (2) are arranged in a one-to-one correspondence, and the plurality of second support rods (5) and the plurality of connecting members (2) are arranged in a one-to-one correspondence.

10. A simulation test method, characterized in that: The aileron test device for simulating wing deformation according to any one of claims 1 to 9, wherein the simulation test method comprises: S1: Fixing the base (1) on the ground of the test site; S2: connecting the driving assembly (3) and the connecting member (2), and installing a plurality of connected driving assemblies (3) and connecting members (2) in corresponding receiving grooves (11); S3: connecting the plurality of connecting members (2) to the joint of the aileron to be tested (6) via a first support rod (4) and a second support rod (5) in the aileron test device simulating wing deformation; S4: Each of the driving components (3) drives the corresponding connecting member (2) to move to a preset position, causing the aileron (6) to be tested to deform to reach a preset load, thereby simulating the effect of wing deformation on the aileron (6) to be tested.

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