Rigidity detection device for aircraft wing

Abstract

The utility model provides a rigidity detection device of an aviation aircraft wing. The rigidity detection device comprises a bottom frame. The utility model relates to a rigidity detection device for wings of an aviation aircraft, which is characterized in that the wings are firstly placed in two limiting sleeve blocks to be clamped, then two rotating rods are respectively rotated, so that the wings are stably limited in the two limiting sleeve blocks, two air cylinders are used for pressing an extrusion plate during detection, and the wings are clamped in the two limiting sleeve blocks; the two pressure sensors transmit pressure values in the extrusion process to a computer end to complete detection data collection, and the two hooks and the two pull ropes can be combined for use in the process, so that data collection of the pull compression resistance value of the wing can be realized; when extrusion detection needs to be carried out on different positions of the wing, a rotary knob is rotated to enable a threaded column to rotate, a threaded sliding block slides outside the threaded column along a sliding groove, position adjustment of the whole sliding frame is achieved, and the extrusion plate extrudes the different positions of the wing.

Description

Technical Field

[0001] The utility model belongs to the technical field of wing stiffness detection, in particular to a stiffness detection device for an aircraft wing. Background Art

[0002] One of the contents of structural testing is to observe and study the strength, stiffness, stress and deformation distribution of aircraft structures or components under static loads. It is an important means to verify the structural strength of aircraft and the correctness of static analysis. The loading system of full-scale structural static testing is relatively complex. The static test devices for aircraft wing strength currently on the market are generally inconvenient to install. There is no unified support frame at the installation site. Generally, each detection point is fixed separately. The installation site requires measurement and drilling operations. This method is suitable for a small range of aircraft models, which is not conducive to static testing of the wing strength of aircraft of different models. The position of the detection point cannot be adjusted quickly and conveniently. Most of them cannot ensure that the detection points are on the same horizontal line, resulting in deviations in the detection, which is not conducive to the accuracy of the detection.

[0003] The existing authorized public number is CN218156829U, which discloses a wing strength detection device for UAV manufacturing, including: a horizontal plate, the upper end surface of the horizontal plate is symmetrically fixedly connected to two support plates, the upper end surfaces of the two support plates are commonly fixedly connected to a top plate, the lower end surface of the top plate is symmetrically fixedly connected to two hydraulic telescopic rods, and the telescopic end of each hydraulic telescopic rod is fixedly connected to a connecting plate. The utility model can drive the rotating rod to rotate through the coordinated setting of the reduction motor, the worm and the worm gear, and the rotating rod can drive the bidirectional threaded rod to rotate through the coordinated setting of the first gear and the second gear. The bidirectional threaded rod can drive the two clamps to move relative to each other and clamp the UAV wing to limit the position through the coordinated setting of the threaded sleeve, the pull rod and the electric telescopic rod, and the two clamps can be fine-tuned to make the clamping more stable, prevent the UAV wing from shaking, and thus improve the clamping effect. However, the wing strength testing device for UAV manufacturing is not convenient for adjusting the clamping mechanism during the testing process, so that the stiffness testing of the wing at different extrusion angles cannot be performed. Therefore, it is necessary to provide a stiffness testing device for aircraft wings to solve the above problem. Utility Model Content

[0004] The technical content of the utility model is to provide a rigidity detection device for the wing of an aviation aircraft.

[0005] In order to solve the above problems, the utility model provides a stiffness detection device for the wing of an aircraft, comprising: a bottom frame, the top of the bottom frame is fixedly connected to a fixing frame, the top of the fixing frame is internally fixedly connected to two cylinders, the bottoms of the two cylinders are fixedly connected to pressure sensors, the bottoms of the two pressure sensors are commonly fixedly connected to an extrusion plate, and the top of the bottom frame is slidably connected to a sliding frame; an adjusting component, the adjusting component comprises a threaded column, and the threaded column is rotatably connected to the inside of the bottom frame; a rotation limiting component, the rotation limiting component comprises two threaded rods, and the two threaded rods are oppositely fixedly connected to the inside of the sliding frame, firstly, the wing is placed inside the two limiting sleeves for clamping, and then the two rotating rods are respectively rotated so that the wing is firmly limited inside the two limiting sleeves, and during detection, the extrusion plate is pressed by the two cylinders so that the extrusion plate squeezes the wing, and at the same time, the two pressure sensors are pressed. The sensor transmits the pressure value during the extrusion process to the computer to complete the data collection of the detection. During the process, two hooks and two pull ropes can be used in combination to realize the data collection of the wing pulling pressure resistance value. When it is necessary to perform extrusion detection on different positions of the wing, the threaded column is rotated by turning the knob. When the threaded column rotates, the threaded slider slides along the slide groove on the outside of the threaded column to adjust the position of the entire sliding frame, so that the extrusion plate squeezes different positions of the wing. When it is necessary to perform side extrusion rigidity detection on the entire wing rotation, the wing after limiting can be rotated by combining the universal sleeve and the universal ball. When it is rotated to the appropriate position, the threaded sleeve is rotated along the outside of the threaded rod to approach the universal sleeve, so that the universal sleeve shrinks and wraps the universal ball to tighten and limit the position, thereby completing the position locking of the wing after rotation and completing the purpose of side rigidity detection of wing rotation.

[0006] As a further solution of the present invention, the adjustment assembly also includes a threaded slider, which is sleeved on the outside of the threaded column and fixedly connected to the bottom of the sliding frame. When the threaded column rotates, the threaded slider will move along the outside of the threaded column, thereby synchronously completing the longitudinal displacement of the entire sliding frame.

[0007] As a further solution of the present invention, a knob is fixedly connected to the end of the threaded column, and the knob extends out of the bottom frame. A slide groove is provided on the top of the bottom frame, and the threaded slider extends out of the bottom frame through the slide groove. The slide groove can limit the sliding trajectory of the entire threaded slider. The knob is convenient for the user to rotate and synchronously control the rotation of the threaded column to complete the longitudinal position adjustment of the entire sliding frame, and further complete the collection of rigidity detection experimental data at different longitudinal positions of the wing.

[0008] As a further solution of the utility model, two pull ropes are fixedly connected to the bottom of the extrusion plate, and hooks are fixedly connected to the bottom of the two pull ropes. The two pull ropes and the two hooks are used in combination to lock the middle position of the wing, and then perform a rigidity test on the wing by waist stretching.

[0009] As a further solution of the present invention, the rotation limit assembly also includes two universal sleeves, which are respectively fixedly connected to the ends of the two threaded rods, and the interiors of the two universal sleeves are each provided with a universal ball, and the exterior of the universal ball is fixedly connected to a limit sleeve block. The universal ball and the universal sleeve are used in combination to rotate the clamped wing to facilitate rigidity detection at different side positions.

[0010] As a further solution of the utility model, the outside of the two threaded rods are rotatably connected to a threaded sleeve, and the outside of the threaded sleeve is fixedly connected to a hemispherical sleeve. When the threaded sleeve rotates, it can approach the universal sleeve along the outside of the threaded rod. At the same time, the hemispherical sleeve squeezes the universal sleeve, synchronously causing the universal sleeve to shrink and wrap the universal ball to complete position locking.

[0011] As a further solution of the present invention, the two limit sleeves are rotatably connected to the inside with a rotating rod, and the bottom of the rotating rod is fixedly connected to a rubber block. The rotating rod can be rotated to further limit and lock the wing stuck inside the limit sleeve to improve stability.

[0012] In summary, the utility model includes at least the following beneficial technical effects:

[0013] First, the utility model records a stiffness detection device for the wings of aircraft, which records that the wing is first placed inside two limit sleeves for clamping, and then the two rotating rods are rotated respectively so that the wing is firmly limited inside the two limit sleeves. During the detection, the extrusion plate is pressed by two cylinders so that the extrusion plate squeezes the wing. At the same time, two pressure sensors transmit the pressure values ​​during the extrusion process to the computer to complete the data collection of the detection. During the process, two hooks and two pull ropes can also be used in combination to realize the data collection of the pulling pressure resistance value of the wing. When it is necessary to perform extrusion detection on different positions of the wing, the threaded column is rotated by turning the knob. When the threaded column rotates, the threaded slider slides along the slide groove on the outside of the threaded column to realize the position adjustment of the entire sliding frame, so that the extrusion plate squeezes different positions of the wing.

[0014] Second, the utility model records a stiffness detection device for an aircraft wing. When it is necessary to perform a side extrusion rigidity detection on the rotation of the entire wing, the wing can be rotated after being limited by using a combination of a universal sleeve and a universal ball. When it is rotated to a suitable position, the threaded sleeve is rotated along the outside of the threaded rod to approach the universal sleeve, so that the universal sleeve contracts and wraps the universal ball to tighten and limit the position, thereby locking the position of the wing after rotation and achieving the purpose of side rigidity detection of the wing rotation. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to facilitate understanding by those skilled in the art, the present invention is further described below in conjunction with the accompanying drawings.

[0016] Figure 1 It is a schematic diagram of the external three-dimensional structure of the stiffness detection device of the wing of an aircraft of the utility model;

[0017] Figure 2 It is a schematic diagram of the cross-section internal structure of the stiffness detection device for the wing of an aircraft of the utility model;

[0018] Figure 3 This is a schematic diagram of the internal structure of the bottom frame of the rigidity detection device for the wing of an aircraft according to the utility model;

[0019] Figure 4 The utility model is a schematic diagram of the structure of a universal ball and a universal sleeve of a rigidity detection device for an aircraft wing.

[0020] Figure numerals: 1. bottom frame; 2. fixing frame; 3. cylinder; 4. pressure sensor; 5. extrusion plate; 6. sliding frame; 7. pull rope; 8. hook; 9. slide groove; 10. threaded rod; 11. threaded sleeve; 12. universal sleeve; 13. universal ball; 14. limit sleeve block; 15. rotating rod; 16. threaded column; 17. threaded slider; 18. knob. DETAILED DESCRIPTION

[0021] Please refer to Figure 1 , Figure 2 , Figure 3 , Figure 4. A stiffness detection device for an aircraft wing comprises: a bottom frame 1, a fixing frame 2 is fixedly connected to the top of the bottom frame 1, two cylinders 3 are fixedly connected to the top of the fixing frame 2, pressure sensors 4 are fixedly connected to the bottoms of the two cylinders 3, an extrusion plate 5 is fixedly connected to the bottoms of the two pressure sensors 4, and a sliding frame 6 is slidably connected to the top of the bottom frame 1; an adjusting component, the adjusting component comprises a threaded column 16, the threaded column 16 is rotatably connected to the inside of the bottom frame 1; a rotation limiting component, the rotation limiting component comprises two threaded rods 10, the two threaded rods 10 are oppositely fixedly connected to the inside of the sliding frame 6, firstly, the wing is placed inside the two limiting sleeves 14 for clamping, and then the two rotating rods 15 are rotated respectively so that the wing is firmly limited inside the two limiting sleeves 14, and during detection, the extrusion plate 5 is pressed by the two cylinders 3 so that the extrusion plate 5 squeezes the wing, and at the same time, the two pressure sensors 4 transmit the pressure values ​​during the extrusion process. The data is input to the computer to complete the detection data collection. During the process, the two hooks 8 and the two pull ropes 7 can also be used in combination to realize the data collection of the wing pulling compression resistance value. When it is necessary to perform extrusion detection on different positions of the wing, the threaded column 16 is rotated by turning the knob 18. When the threaded column 16 rotates, the threaded slider 17 slides along the slide groove 9 on the outside of the threaded column 16 to adjust the position of the entire sliding frame 6, so that the extrusion plate 5 can squeeze different positions of the wing. When it is necessary to perform side extrusion rigidity detection on the entire wing rotation, the universal sleeve 12 and the universal ball 13 are used in combination to rotate the wing after limiting. When it is rotated to the appropriate position, the threaded sleeve 11 is rotated along the outside of the threaded rod 10 to approach the universal sleeve 12, so that the universal sleeve 12 shrinks and wraps the universal ball 13 to tighten and limit the position, thereby completing the position locking of the wing after rotation and completing the purpose of side rigidity detection of the wing rotation.

[0022] The adjustment assembly further includes a threaded slider 17, which is sleeved on the outside of the threaded column 16. The threaded slider 17 is fixedly connected to the bottom of the sliding frame 6. When the threaded column 16 rotates, the threaded slider 17 will move along the outside of the threaded column 16, and synchronously complete the longitudinal displacement of the entire sliding frame 6.

[0023] The end of the threaded column 16 is fixedly connected with a knob 18, and the knob 18 extends out of the bottom frame 1. A slide groove 9 is provided on the top of the bottom frame 1. The threaded slider 17 extends out of the bottom frame 1 through the slide groove 9. The slide groove 9 can limit the sliding track of the entire threaded slider 17. The knob 18 is convenient for the user to rotate, and synchronously controls the rotation of the threaded column 16 to complete the longitudinal position adjustment of the entire sliding frame 6, and further completes the rigidity detection experimental data collection at different longitudinal positions of the wing;

[0024] Two pull ropes 7 are fixedly connected to the bottom of the extrusion plate 5, and hooks 8 are fixedly connected to the bottom of the two pull ropes 7. The two pull ropes 7 and the two hooks 8 are used in combination to lock the middle position of the wing, and then perform a rigidity test on the wing by waist stretching.

[0025] It should be noted that the utility model first places the wing inside the two limit sleeves 14 for clamping, and then rotates the two rotating rods 15 respectively, so that the wing is firmly limited inside the two limit sleeves 14. During detection, the two cylinders 3 press the extrusion plate 5 so that the extrusion plate 5 squeezes the wing. At the same time, the two pressure sensors 4 transmit the pressure values ​​during the extrusion process to the computer to complete the data collection of the detection. During the process, the two hooks 8 and the two pull ropes 7 can also be used in combination to realize the data collection of the wing pulling pressure resistance value. When it is necessary to perform extrusion detection on different positions of the wing, the threaded column 16 is rotated by rotating the knob 18. When the threaded column 16 rotates, the threaded slider 17 slides along the slide groove 9 on the outside of the threaded column 16 to realize the position adjustment of the entire sliding frame 6, so that the extrusion plate 5 squeezes different positions of the wing.

[0026] Please refer to Figure 1 , Figure 2 , Figure 3 , Figure 4 The rigidity detection device of the wing of an aircraft, preferably, the rotation limit assembly also includes two universal sleeves 12, the two universal sleeves 12 are respectively fixedly connected to the ends of the two threaded rods 10, the interiors of the two universal sleeves 12 are sleeved with universal balls 13, the exteriors of the universal balls 13 are fixedly connected with the limit sleeve blocks 14, the universal balls 13 and the universal sleeves 12 are used in combination, and the clamped wing can be rotated to facilitate the rigidity detection of different side positions;

[0027] The two limiting sleeves 14 are both rotatably connected with a rotating rod 15, and the bottom of the rotating rod 15 is fixedly connected with a rubber block. The rotating rod 15 can further limit and lock the wing stuck inside the limiting sleeve 14 to improve stability by rotating.

[0028] It should be noted that, according to the utility model, when it is necessary to perform side extrusion rigidity detection on the entire wing rotation, the wing after limiting can be rotated by using the universal sleeve 12 and the universal ball 13 in combination. When rotated to the appropriate position, the threaded sleeve 11 is rotated along the outside of the threaded rod 10 to approach the universal sleeve 12, so that the universal sleeve 12 contracts and wraps the universal ball 13 to tighten and limit the position, thereby locking the position of the wing after rotation and achieving the purpose of side rigidity detection of the wing rotation.

[0029] Although the embodiments of the present invention have been shown and described, it is understood by those skilled in the art that various changes, modifications, substitutions and variations or direct or indirect applications may be made to these embodiments without departing from the principles and spirit of the present invention. In other related technical fields, the scope of the present invention is defined by the attached claims and their equivalents, which are equally included in the scope of patent protection of the present invention.

Claims

1. A device for detecting the stiffness of an aircraft wing, characterized in that: include: A bottom frame (1), wherein the top of the bottom frame (1) is fixedly connected to a fixing frame (2), the top of the fixing frame (2) is internally fixedly connected to two cylinders (3), the bottoms of the two cylinders (3) are both fixedly connected to pressure sensors (4), the bottoms of the two pressure sensors (4) are commonly fixedly connected to an extrusion plate (5), and the top of the bottom frame (1) is slidably connected to a sliding frame (6); An adjustment component, the adjustment component comprising a threaded column (16), the threaded column (16) being rotatably connected to the interior of the bottom frame (1); A rotation limiting assembly, the rotation limiting assembly comprising two threaded rods (10), the two threaded rods (10) being oppositely fixedly connected to the inside of a sliding frame (6).

2. The device for detecting the stiffness of an aircraft wing according to claim 1, characterized in that: The adjustment assembly further comprises a threaded slider (17), wherein the threaded slider (17) is sleeved on the outside of the threaded column (16), and the threaded slider (17) is fixedly connected to the bottom of the sliding frame (6).

3. The device for detecting the stiffness of an aircraft wing according to claim 2, characterized in that: The end of the threaded column (16) is fixedly connected to a knob (18), and the knob (18) extends out of the bottom frame (1). A slide groove (9) is provided on the top of the bottom frame (1), and the threaded slider (17) extends out of the bottom frame (1) through the slide groove (9).

4. The device for detecting the stiffness of an aircraft wing according to claim 1, characterized in that: Two drawstrings (7) are fixedly connected to the bottom of the extrusion plate (5), and hooks (8) are fixedly connected to the bottoms of the two drawstrings (7).

5. The device for detecting the stiffness of an aircraft wing according to claim 1, characterized in that: The rotation limiting assembly further comprises two universal sleeves (12), the two universal sleeves (12) being fixedly connected to the ends of the two threaded rods (10) respectively, the interiors of the two universal sleeves (12) being sleeved with universal balls (13), the exteriors of the universal balls (13) being fixedly connected to the limiting sleeve blocks (14).

6. The device for detecting the stiffness of an aircraft wing according to claim 1, characterized in that: The outsides of the two threaded rods (10) are rotatably connected to threaded sleeves (11), and the outsides of the threaded sleeves (11) are fixedly connected to a hemispherical sleeve.

7. The device for detecting the stiffness of an aircraft wing according to claim 5, characterized in that: The interiors of the two limiting sleeve blocks (14) are both rotatably connected to a rotating rod (15), and the bottoms of the rotating rods (15) are fixedly connected to a rubber block.

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