Eccentric torque controllable spar stability test device

Abstract

The invention belongs to the technical field of airplane structure strength tests, and relates to a spar stability test device with a controllable eccentric torque. The device comprises a supporting bottom beam (1), a load applying system (5), a beam web loading clamping plate (6) and an eccentric torque controller (8), one end of the wing spar (2) is fixed on the supporting bottom beam (1), the other end of the wing spar (2) is clamped by a beam web loading clamping plate (6), the beam web loading clamping plate (6) is connected with a lateral adjustable loading joint (7) with an adjustable position, and the lateral adjustable loading joint (7) is connected with a load applying system (5). Two sets of eccentric torque controllers (8) are used for providing jacking force for the outer side faces of trapezoid loading clamping plates (11) of the beam web loading clamping plates (6), and force sensors (23) are arranged on the eccentric torque controllers (8). The loading force line can be close to the rigid center of the spar as much as possible, the adjustable dimension is increased, and the test stability is improved.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft structure strength testing, and in particular relates to a wing beam stability testing device with controllable eccentric torque. Background Art

[0002] The web-type spar is the most common longitudinal load-bearing member of the wing surface, usually composed of upper and lower ribs and a web. The upper and lower ribs bear bending moments in the form of tension or compression, and the web transmits shear force in the form of shear. In order to assess the load-bearing capacity of the spar and ensure the reliability of the wing structure design, it is necessary to apply shear force in the plane where the web is located to conduct a stability test.

[0003] The cross section of the wing spar is usually I-shaped or other forms, but its rigid center is mostly located outside the web plane. If the load is only applied within the web plane, the eccentric torque generated during the loading process will cause the web to twist and change the web's force mode. Therefore, in order to prevent the wing spar from twisting during loading, it is usually necessary to set an anti-twist device during web loading to avoid twisting when shear force is applied to the web.

[0004] The existing anti-twist device consists of a top wheel, a top rod and a fixed end, and the top rod connects the top wheel and the fixed end. During the test, several groups of top wheels are arranged on both sides of the web, and the top wheels directly press against the web to form a constraint to prevent the test piece from twisting. The shortcomings of this technology are as follows:

[0005] a) The top wheel and the web are in point contact, which leads to excessive local stress and affects the test results;

[0006] b) The compressive stability of the push rod is poor, and the push rod itself is prone to stability deformation, affecting the anti-twist effect;

[0007] c) The force between the push rod and the web cannot be monitored and controlled, and the point of action cannot be adjusted;

[0008] d) The force acting on the web surface through the push rod and the push wheel is a passive torque. In fact, there is still torque on the web itself.

[0009] In summary, the existing anti-twist device has a poor anti-twist effect, which affects the performance of the web itself. Summary of the invention

[0010] In order to solve at least one of the above-mentioned technical problems, the present application provides a wing beam stability test device with controllable eccentric torque, which avoids torsion when shear force is applied to the web through an eccentric torque controller, so as to achieve the purpose of effectively evaluating the bearing capacity of the beam web.

[0011] The wing beam stability test device with controllable eccentric torque provided in the present application mainly comprises a supporting bottom beam, a load application system, a beam web loading clamp and an eccentric torque controller;

[0012] Among them, one end of the wing beam is fixed on the supporting bottom beam, and the other end is clamped by the beam web loading clamp, the beam web loading clamp includes two trapezoidal loading clamps for clamping the front and rear plate surfaces of the web of the wing beam and a loading transition adapter clamp located on one side of the two trapezoidal loading clamps, the loading transition adapter clamp is connected to a lateral adjustable loading joint with adjustable relative position through a strip hole, the lateral adjustable loading joint is connected to a load application system, and the outer side of each trapezoidal loading clamp is provided with a tightening force by two sets of eccentric torque controllers, and a force sensor is arranged on the eccentric torque controller.

[0013] Preferably, the other sides of the two trapezoidal loading clamps are connected by a clamp connecting fixture.

[0014] Preferably, the two trapezoidal loading clamps and the spar located between the two trapezoidal loading clamps are penetrated by pins, and the pins are tightened to push the two trapezoidal loading clamps to clamp the spar.

[0015] Preferably, a cap pad is provided on the outer side of the bottom edge of the trapezoidal loading clamp for supporting the cap of the spar.

[0016] Preferably, the loading transition adapter clamp is provided with a plurality of lateral long holes perpendicular to the web plate surface of the wing beam, and / or the lateral adjustable loading joint is provided with lateral adjustable long holes in the same direction, and the position of the lateral adjustable loading joint relative to the loading transition adapter clamp is adjusted based on the lateral long holes and / or the lateral adjustable long holes.

[0017] Preferably, the load application system comprises a hydraulic jack connected to the supporting bottom beam via an jack base fixture.

[0018] Preferably, the force sensor of the eccentric torque controller is arranged on a push rod, a roller is provided at one end of the push rod, and a screw rod is connected to the other end, the roller abuts against the outer surface of the trapezoidal loading clamp, the screw rod passes through a threaded sleeve rod and is connected to a rotating handwheel, and the sleeve rod is fixed on the load-bearing column.

[0019] Preferably, the two sleeve rods located on one side of the trapezoidal loading clamp are connected to the load-bearing columns through an anti-torsion beam, and the anti-torsion beam is also connected to an anti-torsion frame, which extends toward the push rod and forms a pair of pressure rod anti-torsion joints complementary to the cross-sectional shape of the push rod at the end, and the pressure rod anti-torsion joints are sleeved on the push rod.

[0020] This application can make the loading force line as close as possible to the rigid center of the wing beam, increase the adjustable dimension, and improve the test stability. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a structural schematic diagram of a preferred embodiment of the wing beam stability test device with controllable eccentric torque of the present application.

[0022] Figure 2 Schematic diagram of the structure of the beam web eccentric torque control system.

[0023] Figure 3 Schematic diagram of the splint structure for loading the web of the beam.

[0024] Figure 4 Schematic diagram of the laterally adjustable loading joint structure.

[0025] Figure 5 Schematic diagram of the load application system structure.

[0026] Figure 6 Schematic diagram of the eccentric torque controller structure.

[0027] Figure 7 Schematic diagram of the anti-torsion frame structure.

[0028] Among them, 1-supporting bottom beam, 2-wing beam, 3-beam web eccentric torque control system, 4-load-bearing column, 5-load application system, 6-beam web loading splint, 7-lateral adjustable loading joint, 8-eccentric torque controller, 9-anti-twist frame, 10-anti-twist beam, 11-trapezoidal loading splint, 12-pin, 13-edge strip pad, 14-loading transition adapter clamp, 15-lateral long strip hole, 16-splint connection clamp, 17-lateral adjustable long strip hole, 18-loading ear, 19-hydraulic actuator, 20-actuator base fixer, 21-roller, 22-rod, 23-force sensor, 24-sleeve rod, 25-rotating handwheel, 26-pressure rod anti-twist joint. DETAILED DESCRIPTION

[0029] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the implementation of this application will be described in more detail in combination with the drawings in the implementation of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described implementation is a part of the implementation of this application, not all of the implementations. The implementation described below with reference to the drawings is exemplary and is intended to be used to explain this application, and cannot be understood as a limitation on this application. Based on the implementation in this application, all other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The implementation of this application is described in detail below in combination with the drawings.

[0030] The present application provides a wing beam stability test device with controllable eccentric torque, such as Figure 1-Figure 7 As shown, it mainly includes:

[0031] Supporting bottom beam 1, load application system 5, beam web loading clamp 6 and eccentric torque controller 8;

[0032] Among them, one end of the wing beam 2 is fixed on the supporting bottom beam 1, and the other end is clamped by the beam web loading clamp 6, the beam web loading clamp 6 includes two trapezoidal loading clamps 11 for clamping the front and rear plate surfaces of the web of the wing beam 2 and a loading transition adapter clamp 14 located on one side of the two trapezoidal loading clamps 11, the loading transition adapter clamp 14 is connected to the lateral adjustable loading joint 7 with adjustable relative position through a strip hole, the lateral adjustable loading joint 7 is connected to the load application system 5, and the outer side surface of each trapezoidal loading clamp 11 is provided with a tightening force by two sets of eccentric torque controllers 8, and a force sensor 23 is arranged on the eccentric torque controller 8.

[0033] like Figure 1 and Figure 2 As shown, the present application fixes one end of the wing beam 2 on the supporting bottom beam 1 so that the wing beam 2 is placed vertically, and then clamps the top end of the wing beam 2 through the beam web loading clamp 6, provides a tightening force to the beam web loading clamp 6 through the eccentric torque controller 8, and applies a specified shear load to the wing beam 2 through the load application system 5, wherein the beam web loading clamp 6 and the eccentric torque controller 8 together constitute Figure 1 The web eccentric torque control system 3 in the beam can adjust the position of the lateral adjustable loading joint 7 relative to the loading transition adapter 14 based on the feedback values ​​of the multiple force sensors 23 of the eccentric torque controller 8, that is, adjust the load application point of the load application system 5 on the wing beam 2, so as to adjust the loading force line so that the loading force line is as close to the rigid center of the wing beam 2 as possible until the torque is reduced to a minimum.

[0034] In some optional embodiments, the other sides of the two trapezoidal loading clamps 11 are connected by a clamp connection fixture 16. Figure 2 and Figure 3 In this embodiment, in addition to the two left and right trapezoidal loading clamps 11, the web loading clamp 6 also includes two front and rear connecting plates, one is a loading transition adapter clamp 14 located on the front side for connecting the load application system 5, and the other is a clamp connecting clamp 16 located on the rear side. The two trapezoidal loading clamps 11, the loading transition adapter clamp 14 and the clamp connecting clamp 16 together form a containing frame to accommodate and clamp the wing beam 2.

[0035] In some optional embodiments, the two trapezoidal loading clamps 11 and the wing beam 2 located between the two trapezoidal loading clamps 11 are penetrated by pins 12, and the pins 12 are tightened to push the two trapezoidal loading clamps 11 to clamp the wing beam 2.

[0036] In the present application, two trapezoidal loading clamps 11 complementary to the I-shaped or other shaped cross-sections are fixed to the two sides of the web loading position of the spar 2 by pins 12. The pins 12 penetrate the trapezoidal loading clamps 11 and the spar 2. The trapezoidal loading clamps 11 are connected to the web of the spar 2 in the form of surface contact, and the applied shear force is transmitted to the loading position of the web through the pins 12.

[0037] In some optional embodiments, a cap pad 13 is provided on the outer side of the bottom edge of the trapezoidal loading clamp 11 to support the cap of the spar 2 .

[0038] like Figure 3 As shown, the trapezoidal loading clamping plate 11 provides support for the spar's spar through the spar pads 13 on both sides, so that the trapezoidal loading clamping plate 11 and the spar web 2 are in a coordinated deformation state.

[0039] In some optional embodiments, the loading transition adapter clamp 14 is provided with a plurality of lateral long holes 15 perpendicular to the web plate surface of the wing beam 2, and / or the lateral adjustable loading joint 7 is provided with lateral adjustable long holes 17 with the same direction. Based on the lateral long holes 15 and / or the lateral adjustable long holes 17, the position of the lateral adjustable loading joint 7 relative to the loading transition adapter clamp 14 is adjusted.

[0040] like Figure 3 and Figure 4 As shown, at least one of the loading transition adapter clamp 14 and the laterally adjustable loading joint 7 is provided with a strip hole, so that the degree of deviation between the loading transition adapter clamp 14 and the laterally adjustable loading joint 7 in the connection direction can be adjusted. As mentioned above, the laterally adjustable loading joint 7 is moved along the laterally adjustable long strip hole 17 or the laterally adjustable long strip hole 15 according to the load feedback value of the force sensor 23, so that the loading force line is as close to the rigid center of the beam web 2 as possible.

[0041] In some optional embodiments, the load application system 5 includes a hydraulic jack 19, which is connected to the supporting bottom beam 1 via an jack base fixture 20. Figure 4 and Figure 5 A loading ear 18 is provided on the laterally adjustable loading joint 7. One end of the hydraulic actuator 19 in the load application system 5 is connected to the supporting bottom beam 1 through the actuator base fixture 20, and the other end is connected to the loading ear 18 on the laterally adjustable loading joint 7 so as to apply a load of a specified size.

[0042] In some optional embodiments, the force sensor 23 of the eccentric torque controller 8 is arranged on the top rod 22, a roller 21 is arranged at one end of the top rod 22, and a screw rod is connected to the other end, the roller 21 abuts against the outer surface of the trapezoidal loading clamp 11, and the screw rod passes through a threaded sleeve rod 24 and is connected to a rotating handwheel 25, and the sleeve rod 24 is fixed on the load-bearing column 4.

[0043] refer to Figure 6 In this embodiment, the outer plane of each trapezoidal loading clamp 11 contacts the rollers 21 in the two sets of eccentric torque controllers 8. The torsion condition of the web can be determined according to the load value fed back by the force sensor 23 connected to each push rod 22. The load acting on the push rod 22 is adjusted by rotating the hand wheel 25 until the load values ​​fed back by each force sensor 23 are equal, that is, after the loads applied by each push rod 22 to the trapezoidal loading clamp 11 are uniform, the web 2 of the beam and the trapezoidal loading clamp 11 are deformed in coordination, and the torque generated by the web is offset.

[0044] In some optional embodiments, two sleeve rods 24 located on one side of the trapezoidal loading clamp plate 11 are connected to the load-bearing column 4 through an anti-torsion beam 10, and the anti-torsion beam 10 is also connected to an anti-torsion frame 9, which extends toward the top rod 22 and forms a pair of pressure rod anti-torsion joints 26 at the end that are complementary to the cross-sectional shape of the top rod 22, and the pressure rod anti-torsion joints 26 are sleeved on the top rod 22.

[0045] refer to Figure 2 and Figure 7 In this embodiment, the anti-torsion frame 9 and the anti-torsion beam 10 are fixed on the load-bearing column 4. The top rod 22 of the eccentric torque controller 8 is connected to the anti-torsion beam 10 through the sleeve rod 24. The anti-torsion frame 9 extends a pair of pressure rod anti-torsion joints 26 with a complementary cross-sectional shape to the top rod 22 to prevent the top rod 22 from being deformed under pressure.

[0046] The material of the positioning bolts and positioning pins of the present application is 30CrMnSiA, and the material of the remaining devices can be Q235 steel. The web loading splints of the beams of corresponding specifications are designed according to the parameters of the wing beams and their webs, which can adapt to the shear tests of wing beams of various configurations and specifications and other components of similar configurations.

[0047] The present application converts the fixed end of the roller into a controllable handwheel control, which can actively offset the torsional moment generated during the web loading process, so that the web itself is not affected by the torque, and the stability effect is significantly improved; the direct point contact between the wing beam web and the roller is converted into a surface contact between the clamp and the wing beam web through the beam web loading splint design. This form of interaction will not cause force concentration at the local position of the wing beam web, thereby ensuring that the force on the wing beam web is accurate and effective; by preliminarily adjusting the position of the force line of the applied load on the laterally adjustable loading joint, the force line is made as close as possible to the rigid center of the wing beam, and the adjustable dimension is increased; at the same time, the beam web loading splint occupies a small area on the wing beam web, so it is not limited by the number of loading positions, the versatility is improved, and the number and specifications of the eccentric torque controllers are not limited by the wing beam configuration; the present application designs a sleeve rod and an anti-sway frame in the middle of the push rod to prevent the push rod from deforming.

[0048] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A wing spar stability test device with controllable eccentric torque, characterized in that: It comprises a supporting bottom beam (1), a load application system (5), a beam web loading clamp (6) and an eccentric torque controller (8); One end of the wing beam (2) is fixed on the supporting bottom beam (1), and the other end is clamped by a beam web loading clamp (6), the beam web loading clamp (6) comprises two trapezoidal loading clamps (11) for clamping the front and rear plate surfaces of the web of the wing beam (2) and a loading transition adapter clamp (14) located on one side of the two trapezoidal loading clamps (11), the loading transition adapter clamp (14) is connected to a lateral adjustable loading joint (7) whose relative position can be adjusted through a strip hole, the lateral adjustable loading joint (7) is connected to a load application system (5), and the outer side surface of each trapezoidal loading clamp (11) is provided with a tightening force by two sets of eccentric torque controllers (8), and a force sensor (23) is arranged on the eccentric torque controller (8).

2. The wing beam stability test device with controllable eccentric torque according to claim 1, characterized in that: The other sides of the two trapezoidal loading clamps (11) are connected via a clamp connection fixture (16).

3. The wing beam stability test device with controllable eccentric torque according to claim 1, characterized in that: The two trapezoidal loading clamps (11) and the wing beam (2) located between the two trapezoidal loading clamps (11) are penetrated by a pin (12), and the pin (12) is tightened to push the two trapezoidal loading clamps (11) to clamp the wing beam (2).

4. The wing beam stability test device with controllable eccentric torque according to claim 1, characterized in that: A cap strip pad (13) is arranged on the outer side of the bottom edge of the trapezoidal loading clamp (11) for supporting the cap strip of the wing beam (2).

5. The wing beam stability test device with controllable eccentric torque according to claim 1, characterized in that: The loading transition adapter clamp (14) is provided with a plurality of lateral long holes (15) perpendicular to the web plate surface of the wing beam (2), and / or the lateral adjustable loading joint (7) is provided with lateral adjustable long holes (17) with the same direction. Based on the lateral long holes (15) and / or the lateral adjustable long holes (17), the position of the lateral adjustable loading joint (7) relative to the loading transition adapter clamp (14) is adjusted.

6. The wing beam stability test device with controllable eccentric torque according to claim 1, characterized in that: The load application system (5) comprises a hydraulic actuator (19), which is connected to the supporting bottom beam (1) via an actuator base fixture (20).

7. The wing beam stability test device with controllable eccentric torque according to claim 1, characterized in that: The force sensor (23) of the eccentric torque controller (8) is arranged on a push rod (22); a roller (21) is arranged at one end of the push rod (22); and a screw rod is connected to the other end; the roller (21) abuts against the outer surface of the trapezoidal loading clamp (11); the screw rod passes through a sleeve rod (24) with a thread and is connected to a rotating hand wheel (25); and the sleeve rod (24) is fixed on a load-bearing column (4).

8. The wing beam stability test device with controllable eccentric torque according to claim 7, characterized in that: Two sleeve rods (24) located on one side of the trapezoidal loading clamp plate (11) are connected to the load-bearing column (4) through an anti-torsion beam (10). The anti-torsion beam (10) is also connected to an anti-torsion frame (9). The anti-torsion frame (9) extends toward the push rod (22) and forms a pair of pressure rod anti-torsion joints (26) at the end thereof, which are complementary to the cross-sectional shape of the push rod (22). The pressure rod anti-torsion joints (26) are sleeved on the push rod (22).

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