Airplane airfoil course exciting force loading and mounting tool
By designing a C-shaped mounting frame and ball head seat structure that can adapt to aircraft wing surfaces of different shapes and sizes, the problem of unstable excitation force loading in the existing technology is solved, and the accuracy and safety of aircraft wing surface heading modal testing are achieved.
Patent Information
- Application Number
- CN202423046494.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-10
- Publication Date
- 2025-10-28
- Estimated Expiration
- 2034-12-10
AI Technical Summary
In the existing technology, in the heading modal test of the aircraft wing surface, the excitation force loading is difficult to adapt to irregular angles, resulting in limited excitation force transmission, glue damage to the aircraft surface, and bakelite blocks falling off, affecting the test accuracy and safety.
A tool for loading the heading excitation force on an aircraft wing is designed, which includes a C-shaped mounting frame, a threaded hole, a ball head and a ball head seat structure. The tool can adapt to wing surfaces of different shapes and sizes, flexibly adjust the direction of the excitation force loading, and ensure a stable installation through rubber pads and limit blocks.
It achieves accurate, stable and safe loading of aircraft wing surfaces under large excitation forces, improves the accuracy and reliability of modal tests, and avoids glue damage and falling off problems.
Smart Images
Figure CN223479354U_ABST
Abstract
Description
Technical Field
[0001] This utility model belongs to the field of aircraft strength testing technology, and relates to a vibration force loading tool used in aircraft ground vibration testing, specifically a wing surface directional excitation force loading installation tool. Background Technology
[0002] Currently, in directional modal testing of aircraft wings, horizontal stabilizers, and vertical stabilizers, the unique shape of the wing surfaces—wider nose and pointed tail—and irregular angles between the upper and lower surfaces and the directional direction, makes the application of excitation force a challenge. Existing methods often involve attaching bakelite blocks to the wing surface to connect the exciter for excitation. However, this method has significant limitations: First, using glue to attach the bakelite blocks restricts the transmitted excitation force, potentially failing to reach the required test force, and the glue may damage the aircraft surface, especially after long-term or repeated testing. Second, during testing, vibrations and impacts can cause the bakelite blocks to detach from the wing surface, affecting test accuracy and potentially damaging the testing equipment and aircraft. Third, the bakelite block connection method makes it difficult to ensure that the direction of the excitation force is consistent with the test requirements, sometimes with significant deviations, leading to inaccurate test results and increasing the difficulty of the test. These problems have impacted the directional modal testing of aircraft wings, affecting both the accuracy and safety of the tests. Utility Model Content
[0003] To address the aforementioned issues, this invention provides an aircraft wing surface heading excitation force loading installation tool that can adapt to aircraft wings of different shapes and sizes, and can accommodate irregular angles between the upper and lower surfaces of the wing surface and the heading, flexibly adjusting the direction of the excitation force loading.
[0004] The technical solution of this utility model is as follows:
[0005] An installation tool for loading directional excitation force on an aircraft wing surface includes a C-shaped mounting bracket. The upper and lower plates of the C-shaped mounting bracket are provided with threaded holes. Two identical flat pressure structures are respectively connected to the threaded holes on the upper and lower plates of the C-shaped mounting bracket. The outer side of the back plate of the C-shaped mounting bracket is provided with a connecting structure for connecting a vibrator. One of the flat pressure structures consists of a threaded rod that is threadedly connected to a threaded hole. The bottom of the threaded rod is provided with an adjustable pressure foot whose angle can be changed, and the top of the threaded rod is provided with a handle.
[0006] Furthermore, the connection structure between the threaded rod and the adjusting foot is a ball head and ball head seat structure.
[0007] Furthermore, the threaded rod body is specifically an adjusting rod, the top of the adjusting rod has a handle mounting hole, the middle section of the adjusting rod is a threaded rod, the bottom of the adjusting rod is a spherical end embedded in a circular pressure foot, and a small-diameter transition rod is provided between the spherical end and the threaded rod.
[0008] Furthermore, the top of the adjusting foot has a ball-head structure, and the bottom of the adjusting foot has a circular base plate in the shape of a disc.
[0009] Furthermore, the ball head seat structure of the adjusting presser foot includes: a presser foot boss and a circular groove formed by the indentation in the center of the presser foot boss. The circular groove is a cylindrical groove, and the cylindrical surface of the circular groove matches the maximum circular cross-section of the ball head.
[0010] Furthermore, it also includes a limiting block; one end of the circular groove is a through groove with an opening, and a square groove is provided at the opening of the circular groove, with the limiting block matching the shape of the square groove.
[0011] Furthermore, it also includes a rubber pad, which is attached to the bottom of the adjusting foot.
[0012] The beneficial effects of this utility model are as follows:
[0013] 1. This utility model can be adapted to aircraft wings of different shapes and sizes, and can adapt to irregular angles between the upper and lower surfaces of the wing and the heading, and can flexibly adjust the direction of excitation force loading; at the same time, it has upper and lower clamping characteristics, which can maintain stability under large excitation force, ensuring that the excitation force can be accurately, stably and safely loaded on the heading of the aircraft wing, thereby improving the accuracy and reliability of modal testing.
[0014] 2. This utility model, through its flexible adjustment design, fully demonstrates its wide applicability to aircraft wings of different shapes and sizes. In particular, the adjustability of the relative position and axial angle between the adjusting rod and the circular groove of the adjusting foot allows this utility model to easily handle various irregular angles that may exist between the upper and lower surfaces of the wing and the heading. Furthermore, in actual use, the direction of the excitation force can be precisely controlled by adjusting the relative position and axial angle between the adjusting rod and the circular groove of the adjusting foot according to the specific shape and size of the wing. This flexibility not only improves work efficiency but also ensures that the excitation is accurately applied to the required position, resulting in more accurate and reliable test results. In addition, the design of the adjusting rod pressing down firmly ensures the stability of the installation, which is particularly important for high-intensity vibration in modal testing. A stable installation not only prevents accidental detachment or loosening during testing but also ensures that the excitation force is stably transmitted to the wing surface, resulting in more accurate test results. Attached Figure Description
[0015] Figure 1This is a schematic diagram illustrating the application of this utility model.
[0016] Figure 2 This is a schematic diagram of the structure of this utility model.
[0017] Figure 3 This is a schematic diagram of the structure of the adjusting rod of this utility model.
[0018] Figure 4 This is a schematic diagram of the structure of the adjusting pressure foot of this utility model.
[0019] Figure 5 This is a structural schematic diagram of the screw of this utility model.
[0020] Figure 6 This is a structural schematic diagram of the C-type mounting bracket of this utility model.
[0021] In the figure, 01 is the vibrator, 02 is the vibrator connecting rod, 03 is the force sensor, 04 is the aircraft wing surface heading excitation force loading and installation tool of this utility model, and 05 is a simplified diagram of the aircraft wing surface.
[0022] 1 is the handle, 2 is the adjusting rod, 3 is the adjusting foot, 4 is the rubber pad, 5 is the limit stop, 6 is the screw, and 7 is the C-type mounting bracket.
[0023] 201 is the square end, 202 is the handle mounting hole, 203 is the threaded rod, 204 is the transition rod, and 205 is the spherical end.
[0024] 301 is a round presser foot base plate, 302 is a presser foot boss, 303 is a round groove, and 304 is a square groove;
[0025] 601 is a threaded rod, and 602 is a slotted rod;
[0026] 701 is the clamping surface, 702 is the loading surface, 703 is the screw hole, and 704 is the threaded hole. Detailed Implementation
[0027] This section describes embodiments of the present invention, used to explain and illustrate the technical solutions of the present invention. Unless otherwise specified, the embodiments and features described herein can be combined with each other.
[0028] In the description of this utility model, it should be understood that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating directions or positional relationships, are based on the orientation or positional relationships in the accompanying drawings and are only for the convenience of describing this utility model and simplifying the description. They do not indicate or imply that the device or device referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as limiting this utility model. Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implying the number of indicated technical features. Thus, features defined with "first," "second," etc., may explicitly or implicitly include more than one of those features. In the description of this utility model, unless otherwise stated, "a plurality of" means two or more.
[0029] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integrated connection; they can refer to a mechanical connection or a point 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 utility model based on the specific circumstances.
[0030] Example 1:
[0031] An installation tool for loading directional excitation force on an aircraft wing surface includes a C-type mounting bracket 7. The upper and lower plates of the C-type mounting bracket 7 are provided with threaded holes. Two identical flat pressure structures are respectively connected to the threaded holes on the upper and lower plates of the C-type mounting bracket 7. The outer side of the back plate of the C-type mounting bracket 7 is provided with a connection structure for connecting a vibrator 01. One of the flat pressure structures is: a threaded rod body is threadedly connected to the threaded hole, the bottom of the threaded rod body is provided with an adjustable pressure foot 3 whose angle can be changed, and the top of the threaded rod body is provided with a handle 1.
[0032] The connection structure between the threaded rod and the adjusting foot 3 is a ball head and ball head seat structure.
[0033] The threaded rod body is specifically an adjusting rod 2. The top of the adjusting rod 2 has a handle mounting hole 202, the middle section of the adjusting rod 2 is a threaded rod 203, and the bottom of the adjusting rod 2 is a spherical end 205 embedded in a circular presser foot. A small-diameter transition rod 204 is provided between the spherical end 205 and the threaded rod 203.
[0034] The top of the adjusting foot 3 is a ball head structure, and the bottom of the adjusting foot 3 is a circular foot base plate 301 in the shape of a disc.
[0035] The ball head seat structure of the adjusting presser foot 3 includes: a presser foot boss 302 and a circular groove 303 formed by the indentation of the center of the presser foot boss 302. The circular groove 303 is a cylindrical groove, and the cylindrical surface of the circular groove 303 matches the maximum circular cross section of the ball head.
[0036] It also includes a limiting block 5; one end of the circular groove 303 is an open through groove, and a square groove 304 is provided at the opening of the circular groove 303, and the shape of the limiting block 5 matches that of the square groove 304.
[0037] It also includes a rubber pad 4, which is attached to the bottom of the adjusting foot 3.
[0038] Example 2:
[0039] An installation tool for loading directional excitation force onto an aircraft wing surface includes a handle 1, an adjusting rod 2, an adjusting foot 3, a rubber pad 4, a limit stop 5, a screw 6, and a C-type mounting bracket 7. Refer to the following for assembly: Figure 2 Insert the two handles 1 into the handle mounting holes of the two adjusting rods 2 respectively; then screw the two adjusting rods into the threaded holes on the clamping surface of the C-type mounting bracket 7 respectively; then glue the two rubber pads 4 to the bottom surface of the circular pressure foot base plate of the two adjusting pressure feet 3 respectively with structural adhesive; then slide the spherical ends of the two adjusting rods 2 into the circular grooves of the two adjusting pressure feet 3 respectively; then insert the two limit blocks 5 into the square grooves of the adjusting pressure feet 3 respectively, and glue them with structural adhesive; screw the screws 6 into the screw holes on the loading surface of the C-type mounting bracket 7; at this point, the aircraft wing surface heading excitation force loading mounting clamp is assembled.
[0040] When using this utility model, refer to Figure 1 Insert the pointed end of the aircraft wing surface between the two adjusting feet 3; then adjust the orientation of the loading surface of the C-mount bracket 7 to ensure that the loading direction is aligned with the heading of the aircraft wing surface; rotate the adjusting rods 2 at both ends, and flexibly adjust the relative position between the adjusting rods 2 and the circular grooves of the adjusting feet 3, as well as the angle between their axes, so that the rubber pads 4 at both ends are in contact with the wing surface; then tighten the adjusting rods 2 at both ends to ensure the installation is secure; then fasten the force sensor to the loading surface of the C-mount bracket 7 with screws 6; finally, tighten the vibrator connecting rod and the vibrator respectively. In this way, the present invention can adapt to aircraft wings of different shapes and sizes, accurately control the loading direction of the excitation force, and ensure the stability of the installation, thus meeting the requirements of large excitation force vibration in the heading.
[0041] The adjusting rod 2 includes a square head end 201, a handle mounting hole 202, a threaded rod 203, a transition rod 204, and a spherical end 205, as shown in the reference. Figure 3 The handle mounting hole 202 is adapted to the round rod of handle 1.
[0042] The adjusting foot 3 includes a circular foot base plate 301, a foot boss 302, a circular groove 303, and a square groove 304, as shown in the reference. Figure 4 The circular groove 303 is adapted to the spherical end 205 of the adjusting rod 2.
[0043] The screw 6 includes a threaded shank 601 and a slotted groove 602, as shown in the reference. Figure 5 The threaded rod 601 is adapted to the mounting threaded hole of the force sensor used in actual applications.
[0044] The C-type mounting bracket 7 includes a clamping surface 701, a loading surface 702, a screw hole 703, and a threaded hole 704, as shown in the reference. Figure 6 Screw hole 703 is adapted to screw 6, and threaded hole 704 is adapted to threaded rod 203 of adjusting rod 2.
[0045] Example 3:
[0046] like Figures 1 to 6 As shown, this utility model proposes an aircraft wing surface yaw excitation force loading mounting clip, including a handle 1, an adjusting rod 2, an adjusting foot 3, a rubber pad 4, a limiting block 5, a screw 6, and a C-type mounting bracket 7. The handle 1 is a cylindrical thin rod. The adjusting rod 2 is an overall screw structure, including a square head end 201, a handle mounting hole 202, a threaded rod 203, a transition rod 204, and a spherical end 205, as shown in the figure. Figure 3 The handle mounting hole 202 is adapted to the round rod of the handle 1. The adjusting foot 3 is a circular plate, including a circular foot base plate 301, a foot boss 302, a circular groove 303, and a square groove 304, as shown in the reference. Figure 4 The circular groove 303 is adapted to the spherical end 205 of the adjusting rod 2. The rubber pad 4 is a thin circular rubber pad, the shape of which is adapted to the circular pressure foot base plate 301 of the adjusting pressure foot 3. The limiting block 5 is a square plate, the shape of which is adapted to the square groove 304 of the adjusting pressure foot 3. The screw 6 is a fully threaded rod, including a threaded rod 601 and a slotted groove 602, as shown in the figure. Figure 5 The threaded rod 601 is adapted to the mounting threaded hole of the force sensor in actual use. The C-shaped mounting bracket 7 is an overall C-shaped frame, including a clamping surface 701, a loading surface 702, a screw hole 703, and a threaded hole 704, as shown in the reference. Figure 6 The screw hole 703 is adapted to the screw 6, and the threaded hole 704 is adapted to the threaded rod 203 of the adjusting rod 2.
[0047] Reference Figure 2Insert the two handles 1 into the handle mounting holes 202 of the two adjusting rods 2 respectively; then screw the two adjusting rods into the threaded holes 704 on the clamping surface of the C-type mounting bracket 7 respectively; then glue the two rubber pads 4 to the bottom surface of the circular pressure foot base plate 301 of the two adjusting pressure feet 3 respectively with structural adhesive; then slide the spherical ends 205 of the two adjusting rods 2 into the circular grooves 303 of the two adjusting pressure feet 3 respectively; then insert the two limit blocks 5 into the square grooves 304 of the adjusting pressure feet 3 respectively, and glue them with structural adhesive; then screw the screws 6 into the screw holes 703 on the loading surface 702 of the C-type mounting bracket 7; at this point, the aircraft wing surface heading excitation force loading mounting clamp is assembled.
[0048] When using this utility model, refer to Figure 1 Insert the pointed end of the aircraft wing surface 05 between the two adjusting feet 3; then adjust the orientation of the loading surface 702 of the C-type mounting bracket 7 to ensure that the loading direction is aligned with the heading of the aircraft wing surface; rotate the adjusting rods 2 at both ends, and flexibly adjust the relative position between the adjusting rods 2 and the circular grooves 303 of the adjusting feet 3 and the included angle between their axes to make the rubber pads 4 at both ends fit against the wing surface; then tighten the adjusting rods 2 at both ends to ensure that the present invention is securely installed; then fasten the force sensor 03 to the loading surface 702 of the C-type mounting bracket 7 with screws 6; then tighten the vibrator connecting rod 02 and the vibrator 01 respectively. In this way, by flexibly adjusting the relative position between the adjusting rods 2 and the circular grooves 303 of the adjusting feet 3 and the included angle between their axes, the present invention can adapt to aircraft wings of different shapes and sizes, and can accurately control the loading direction of the excitation force; and by tightening the upper and lower adjusting rods 2, the stability of the installation can be ensured to meet the requirements of large excitation force vibration in the heading.
[0049] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of this utility model, but the protection scope of this utility model is not limited thereto. Any person skilled in the art can easily conceive of various equivalent modifications or substitutions within the technical scope disclosed in this utility model, and these modifications or substitutions should be covered within the protection scope of this utility model.
Claims
1. A tool for loading and installing directional excitation force on an aircraft wing surface, characterized in that, Includes a C-type mounting bracket (7), with threaded holes on the upper and lower plates of the C-type mounting bracket (7), and two identical flat pressure structures connected to the threaded holes on the upper and lower plates of the C-type mounting bracket (7) respectively; the back plate of the C-type mounting bracket (7) has a connecting structure for connecting the vibrator (01) on its outer side; one of the flat pressure structures is: a threaded rod body is threadedly connected to the threaded hole, the bottom of the threaded rod body is provided with an adjustable pressure foot (3) whose angle can be changed, and the top of the threaded rod body is provided with a handle (1).
2. The aircraft wing surface heading excitation force loading and installation tool according to claim 1, characterized in that, The connection structure between the threaded rod and the adjusting foot (3) is a ball head and ball head seat structure.
3. The aircraft wing surface heading excitation force loading and installation tool according to claim 2, characterized in that, The threaded rod body is specifically an adjusting rod (2). The top of the adjusting rod (2) has a handle mounting hole (202), the middle section of the adjusting rod (2) is a threaded rod (203), and the bottom of the adjusting rod (2) is a spherical end (205) embedded in a circular presser foot. A small-diameter transition rod (204) is provided between the spherical end (205) and the threaded rod (203).
4. The aircraft wing surface heading excitation force loading and installation tool according to claim 2, characterized in that, The top of the adjusting foot (3) is a ball head seat structure, and the bottom of the adjusting foot (3) is a circular foot base plate (301) in the shape of a disc.
5. The aircraft wing surface heading excitation force loading and installation tool according to claim 4, characterized in that, The ball head seat structure of the adjusting foot (3) includes: a foot boss (302) and a circular groove (303) formed by the indentation of the center of the foot boss (302). The circular groove (303) is a cylindrical groove, and the cylindrical surface of the circular groove (303) matches the maximum circular cross section of the ball head.
6. The aircraft wing surface directional excitation force loading and installation tool according to claim 5, characterized in that, It also includes a limiting block (5); one end of the circular groove (303) is a through groove with an opening, and a square groove (304) is provided at the opening of the circular groove (303), and the shape of the limiting block (5) matches that of the square groove (304).
7. The aircraft wing surface heading excitation force loading and installation tool according to claim 1, characterized in that, It also includes a rubber pad (4), which is attached to the bottom of the adjusting foot (3).