False part for verifying aircraft wing follow-up loading technology

Abstract

The invention belongs to the technical field of airplane wing strength tests, and particularly relates to a false part for airplane wing follow-up loading technology verification, which comprises a base, triangular false part units, compression springs, connecting rods and anti-sagging structures, the bottoms of the triangular false piece units are sequentially hinged and connected in series, and the tops are connected through compression springs; a loading joint is arranged at the bottom of each triangular false part unit; the bottom of the triangular false piece unit at the front end is hinged to the base; the connecting rod is hinged between the top of the triangular false piece unit at the front end and the base; the multiple anti-sagging structures are arranged between the bottoms of the adjacent triangular false piece units so as to prevent the triangular false piece units from sagging.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft wing strength test, and specifically relates to a dummy for verifying aircraft wing dynamic loading technology. Background Art

[0002] In the strength test of aircraft wings, force-controlled actuators are generally used for loading. The bottom end of the force-controlled actuator is connected to a fixed load-bearing device, such as a ground rail, a support, etc., and the top end is connected to a lever system on the wing surface to form a two-force rod system with hinged ends. The loading amplitude can be controlled by the loading control system and the force sensor installed on the force-controlled actuator, while the loading direction is determined by the installation position of the two ends of the force-controlled actuator. Obviously, when the wing is deformed by the test load, the posture of the force-controlled actuator will tilt accordingly, causing the actual test load to deviate from the designed vertical direction of the wing surface. This problem is particularly prominent in the strength test of large-deformation wings.

[0003] In order to ensure that the test load is always perpendicular to the wing chord plane during the aircraft wing strength test, an aircraft wing follow-up loading technology is designed. According to the estimated or measured wing deformation state, the position of the force-controlled actuator is adjusted in real time along the track by the position-controlled actuator, so that the axial direction of the force-controlled actuator is always perpendicular to the wing chord plane.

[0004] The actual performance and reliability of aircraft wing follow-up loading technology involve many aspects such as mechanical processing, equipment installation, and program design. Before it is officially put into use, sufficient test verification is required to avoid major losses and accidents. If a full-size real wing is used as the test verification loading object, the economic cost will be huge, the test risk will be extremely high, and implementation will be difficult. In view of this, this application is filed. Summary of the invention

[0005] The purpose of the present application is to provide a dummy for verifying the aircraft wing follow-up loading technology, so as to verify the actual performance and reliability of the aircraft wing follow-up loading technology in a low-cost, safe and efficient manner.

[0006] The technical solution of this application is:

[0007] A dummy for verifying the dynamic loading technology of an aircraft wing, comprising a base, a triangular dummy unit, a compression spring, a connecting rod, and an anti-droop structure;

[0008] There are multiple triangular dummy units, the bottoms of which are hinged in series and the tops are connected by compression springs;

[0009] A loading joint is provided at the bottom of each triangular dummy unit;

[0010] The bottom of the triangular dummy unit at the front end is hinged on the base;

[0011] The connecting rod is hinged between the top of the triangular dummy unit at the front end and the base;

[0012] There are a plurality of anti-drooping structures, which are arranged between the bottoms of adjacent triangular dummy units to prevent the triangular dummy units from sagging.

[0013] According to at least one embodiment of the present application, in the above-mentioned dummy for verifying the dynamic loading technology of the aircraft wing, the bottom of each dummy unit is hinged by a hinge;

[0014] The bottom of the triangular dummy unit at the front end is hinged to the base through a hinge;

[0015] The connecting rod is hinged to the top and base of the triangular dummy unit at the front end through a hinge.

[0016] According to at least one embodiment of the present application, in the above-mentioned aircraft wing follower loading technology verification dummy, the anti-droop structure includes a stop boss, a support boss, and a stop screw, wherein:

[0017] The stop boss is connected to the bottom of the front adjacent triangular dummy unit;

[0018] The supporting boss is connected to the bottom of the adjacent triangular dummy unit at the rear;

[0019] The stop screw is screwed on the supporting boss, and the top end is pressed against the stop boss.

[0020] According to at least one embodiment of the present application, in the above-mentioned dummy for verifying the dynamic loading technology of the aircraft wing, the stop boss is integrally formed with the bottom of the triangular dummy unit;

[0021] The supporting boss is integrally formed with the bottom of the triangular dummy unit.

[0022] According to at least one embodiment of the present application, in the above-mentioned dummy for verifying the aircraft wing follower loading technology, the compression spring at the front end has the largest stiffness, and the compression spring at the rear end has the smallest stiffness.

[0023] According to at least one embodiment of the present application, in the above-mentioned dummy for verifying the aircraft wing follow-up loading technology, a telescopic rod is arranged inside the compression spring, and connecting pieces are arranged at both ends of the telescopic rod to connect the two ends of the compression spring to form a spring assembly. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a schematic diagram of a dummy for verifying the aircraft wing follow-up loading technology provided in an embodiment of the present application;

[0025] Figure 2 This is a schematic diagram of an aircraft wing follow-up loading technology verification test before load loading provided by an embodiment of the present application;

[0026] Figure 3 It is a schematic diagram of the aircraft wing follow-up loading technology verification test after load loading provided by the embodiment of the present application;

[0027] in:

[0028] 1-base; 2-triangular dummy unit; 3-compression spring; 4-connecting rod; 5-anti-drooping structure; 6-stop boss; 7-support boss; 8-stop screw.

[0029] In order to better illustrate the present embodiment, some contents of the drawings may be omitted, enlarged or reduced, which is only used for illustrative purposes and should not be construed as limiting the present application. DETAILED DESCRIPTION

[0030] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design.

[0031] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should be the common meanings understood by those skilled in the art in the field to which this application belongs. The term "include" used in the description of this application means that the concepts appearing before the term include the concepts listed after the term and their equivalents, without excluding other related concepts.

[0032] In addition, the words indicating orientation used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the object being described changes, its relative positional relationship may also change accordingly. It should also be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" and other similar words used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0033] A dummy for verifying the dynamic loading technology of an aircraft wing, such as Figure 1 As shown, it includes a base 1, a triangular dummy unit 2, a compression spring 3, a connecting rod 4, and an anti-drooping structure 5.

[0034] The base 1 is used to be connected to a fixed load-bearing structure, for example, it can be connected to a load-bearing wall.

[0035] There are a plurality of triangular dummy units 2, the bottoms of which are hinged in series, and the tops are connected by compression springs 3. The bottoms of the dummy units 2 can be hinged by hinges.

[0036] A loading joint is provided at the bottom of each triangular dummy unit 2 for connecting to the top of the force-controlled actuating cylinder, and can be specifically hinged to the top of the force-controlled actuating cylinder through a single-ear and double-ear structure.

[0037] The bottom of the triangular dummy unit 2 at the front end is hinged to the base 1, and can be hinged by a hinge.

[0038] The connecting rod 4 is hinged between the top of the triangular dummy unit 2 at the front end and the base 1, and can be hinged by a hinge. The structure composed of the triangular dummy units 2 connected in series is in a horizontal state.

[0039] There are multiple anti-drooping structures 5, which are arranged between the bottoms of adjacent triangular dummy units 2 to prevent the triangular dummy units 2 from sagging. Specifically, the anti-drooping structure 5 can be designed to include a stop boss 6, a support boss 7, and a stop screw 8, wherein:

[0040] The stop boss 6 is connected to the bottom of the front adjacent triangular dummy unit 2, and can be integrally formed with the bottom of the triangular dummy unit 2;

[0041] The supporting boss 7 is connected to the bottom of the adjacent triangular dummy unit 2 at the rear, and can be formed integrally with the bottom of the triangular dummy unit 2;

[0042] The stop screw 8 is screwed onto the supporting boss 7 , and the top end thereof is pressed against the stop boss 6 .

[0043] The dummy for verifying the aircraft wing dynamic loading technology disclosed in the above embodiment can replace the real wing test to verify the aircraft wing dynamic loading technology. The specific use can be referred to as follows:

[0044] The top of the force control cylinder is hinged to a loading joint. The specific loading joint to which it is hinged is determined according to the specific test needs. The bottom of the force control cylinder is connected to the guide rail and connected to the position control cylinder, such as Figure 2 As shown;

[0045] The load control system controls the force control cylinder to apply the test load to the dummy. When the load is applied, each triangular dummy unit 2 in series will overcome the elasticity of the compression spring 3 and rotate relatively. The upward rotation of each triangular dummy unit 2 is superimposed, so that the dummy as a whole can curl upward, thereby simulating the vertical and angular deformation of the wing, such as Figure 3As shown, during this process, the loading control system will, as designed, use the position-controlled actuator to adjust the position of the force-controlled actuator along the guide rail in real time according to the estimated or measured deformation state of the dummy component, so that the axial direction of the force-controlled actuator remains perpendicular to the wing chord plane, thereby verifying the actual performance and reliability of the aircraft wing follow-up loading technology.

[0046] The dummy component for verifying the aircraft wing follow-up loading technology disclosed in the above-mentioned embodiment has a certain load-bearing capacity and overall stiffness, and can simulate the vertical and angular deformation of the wing after being subjected to load. It has a simple structure, low manufacturing cost, and small size. It can replace the real wing to effectively test and verify the aircraft wing follow-up loading technology, and can greatly reduce the test cost.

[0047] According to the actual distribution of wing stiffness, the compression spring 3 at the front end can be designed to have the largest stiffness, which gradually decreases toward the rear, and the compression spring 3 at the tail end has the smallest stiffness. In addition, in order to improve the bearing capacity of the dummy, a plurality of compression springs 3 can be designed to be arranged in parallel between adjacent triangular dummy units 2, and the overall stiffness distribution of the dummy can be adjusted through detailed design of the height of the triangular dummy unit 2 and the stiffness of the compression spring 3 so as to match the stiffness distribution of the real wing.

[0048] In order to ensure that the compression spring 3 is stably compressed and avoid excessive compression damage, a piston-type guide and limit device can be set on the compression spring 3. Specifically, a telescopic rod is set in the compression spring 3, and connecting plates are set at both ends of the telescopic rod to connect the two ends of the compression spring 3 to form a spring assembly, which is connected between the tops of adjacent triangular dummy units 2. Specifically, it can be connected by a pin shaft through a single-double-ear structure.

[0049] The dummy for verifying the aircraft wing follow-up loading technology disclosed in the above-mentioned embodiment can adjust the tightness of the top end of the stop screw 8 on the stop boss 6 by turning each stop screw 8, change the relative angle between adjacent triangular dummy units 2, and adjust the initial curvature distribution of the dummy as a whole, so as to simulate wings with different curvature distributions.

[0050] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. A dummy for verifying the dynamic loading technology of an aircraft wing, characterized in that: It comprises a base (1), a triangular dummy unit (2), a compression spring (3), a connecting rod (4), and an anti-drooping structure (5); There are a plurality of triangular dummy units (2), the bottoms of which are hinged in series and the tops are connected via compression springs (3); A loading joint is arranged at the bottom of each triangular dummy unit (2); The bottom of the triangular dummy unit (2) at the front end is hinged on the base (1); The connecting rod (4) is hinged between the top of the triangular dummy unit (2) at the front end and the base (1); There are a plurality of anti-drooping structures (5) which are arranged between the bottoms of adjacent triangular dummy units (2) to prevent the triangular dummy units (2) from sagging.

2. The dummy for verifying the aircraft wing dynamic loading technology according to claim 1 is characterized in that: The bottoms of the dummy units (2) are hinged via hinges; The bottom of the triangular dummy unit (2) at the front end is hinged to the base (1) via a hinge; The connecting rod (4) is hingedly connected to the top of the triangular dummy unit (2) at the front end and the base (1) via a hinge.

3. The dummy for verifying the aircraft wing dynamic loading technology according to claim 2 is characterized in that: The anti-drooping structure (5) comprises a stop boss (6), a support boss (7), and a stop screw (8), wherein: The stop boss (6) is connected to the bottom of the front adjacent triangular dummy unit (2); The supporting boss (7) is connected to the bottom of the adjacent triangular dummy unit (2) at the rear; The stop screw (8) is screwed onto the supporting boss (7), and the top end thereof is pressed against the stop boss (6).

4. The dummy for verifying the aircraft wing dynamic loading technology according to claim 3 is characterized in that: The stop boss (6) is integrally formed with the bottom of the triangular dummy unit (2); The supporting boss (7) is integrally formed with the bottom of the triangular dummy unit (2).

5. The dummy for verifying the aircraft wing dynamic loading technology according to claim 4 is characterized in that: The compression spring (3) at the front end has the largest rigidity, and the compression spring (3) at the rear end has the smallest rigidity.

6. The dummy for verifying the aircraft wing dynamic loading technology according to claim 5, characterized in that: A telescopic rod is arranged inside the compression spring (3), and connecting pieces are arranged at both ends of the telescopic rod to connect the two ends of the compression spring (3) to form a spring assembly.

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