Aviation cylinder clamping detection equipment

Abstract

The invention discloses aviation cylinder clamping detection equipment which comprises a foundation base. The self-adaptive supporting units are divided into a left group and a right group and are symmetrically and fixedly mounted on the upper surface of the foundation base; the axial positioning unit is fixedly mounted at one end of the upper surface of the foundation base; the integrated detection unit is mounted above the foundation base; wherein each group of self-adaptive supporting units comprises at least four independent units which are arranged along the length direction of the foundation base; each independent unit comprises a contact end, a two-dimensional swing mechanism, a six-dimensional force sensor and a radial sliding table which are sequentially arranged from top to bottom, the lower surface of each contact end is fixedly connected with the upper surface of the corresponding two-dimensional swing mechanism, and active control of the corresponding six-dimensional force sensor is combined with two-dimensional swing passive adaptation. The supporting force is uniform, the direction is pure radial, cylinder deformation caused by traditional rigid clamping is fundamentally avoided, a workpiece is protected, and a premise is provided for real measurement.

Description

Technical Field

[0001] This invention relates to the fields of aerospace manufacturing and precision measurement technology, and more specifically, to an aircraft cylinder clamping and testing device. Background Technology

[0002] Large, thin-walled aerospace cylindrical components, such as rocket fuel tank sections and aircraft fuselage sections, are characterized by their large size, thin walls, low rigidity, and susceptibility to deformation. Two core challenges arise during their manufacturing and assembly:

[0003] Firstly, traditional clamping methods often use rigid clamps or multi-point rigid supports, which are prone to generating "assembly stress" or "clamping deformation" inside the cylinder due to over-positioning or uneven distribution of clamping force. This deformation will directly affect the accuracy of subsequent processing or mask the true shape error of the workpiece itself.

[0004] Secondly, geometric accuracy testing typically requires hoisting the cylinder from the tooling to offline testing equipment such as a coordinate measuring machine. This process is inefficient, and hoisting may introduce secondary deformation or collision risks. If manual handheld measuring equipment is used for on-site testing, it presents problems such as complex operation, long cycle time, accuracy dependence on personnel skill, and data dispersion. Summary of the Invention

[0005] The purpose of this invention is to provide an aircraft cylinder clamping and testing device to solve the problems in the prior art.

[0006] The above-mentioned technical objective of the present invention is achieved through the following technical solution: an aircraft cylinder clamping and testing device, comprising: a base base; adaptive support units divided into two groups, symmetrically fixedly installed on the upper surface of the base base; an axial positioning unit fixedly installed at one end of the upper surface of the base base; and an integrated testing unit installed above the base base; wherein each group of adaptive support units comprises at least four independent units arranged along the length direction of the base base;

[0007] Each independent unit includes, from top to bottom, a contact end, a two-dimensional swing mechanism, a six-dimensional force sensor, and a radial slide. The lower surface of the contact end is fixedly connected to the upper surface of the two-dimensional swing mechanism, the lower surface of the two-dimensional swing mechanism is fixedly connected to the upper surface of the six-dimensional force sensor, and the lower surface of the six-dimensional force sensor is fixedly connected to the upper surface of the slider of the radial slide. The lower surface of the base of the radial slide is fixedly connected to the upper surface of the base. The working surfaces of the left and right sets of contact ends are arranged facing each other.

[0008] The invention is further configured such that: the contact end is made of non-metallic material, and its working surface facing the cylinder is a V-groove or a large-radius arc surface.

[0009] The present invention is further configured such that: the two-dimensional swing mechanism includes a U-shaped base, a cross shaft, and a U-shaped swing frame; the upper surface of the U-shaped swing frame is fixedly connected to the lower surface of the contact end; the lower surface of the U-shaped base is fixedly connected to the upper surface of the six-dimensional force sensor; the cross shaft has a first journal and a second journal that are perpendicular to each other; the two ends of the first journal are rotatably connected to the two side plates of the U-shaped base through bearings; and the two ends of the second journal are rotatably connected to the two side plates of the U-shaped swing frame through bearings.

[0010] The present invention is further configured such that: the radial slide is a precision linear module, and the sliding block is set horizontally and perpendicular to the axial direction of the aircraft cylinder.

[0011] The present invention is further configured such that: the axial positioning unit includes a mounting support, a transverse adjustment slide, and an end cover plate; the lower surface of the mounting support is fixedly connected to the upper surface of the base; the base of the transverse adjustment slide is fixedly connected to the mounting support; the back of the end cover plate is fixedly connected to the front of the slider of the transverse adjustment slide; and the front of the end cover plate is provided with a plurality of positioning pins that can extend and retract along the axis of the cylinder.

[0012] The present invention is further configured such that: the integrated detection unit includes columns, a circular track, a moving platform, a vertical lifting slide, a sensor mounting plate, and a measuring sensor; the lower ends of the two columns are fixedly connected to the upper surface of the base, and are respectively located on the outer sides of the left and right sets of adaptive support units; the two ends of the circular track are respectively fixedly connected to the upper ends of the two columns; the moving platform is slidably connected to the circular track; the back of the base of the vertical lifting slide is fixedly connected to the front of the moving platform; the back of the sensor mounting plate is fixedly connected to the front of the slider of the vertical lifting slide; and the measuring sensor is fixedly mounted on the front of the sensor mounting plate.

[0013] The present invention is further configured such that the measurement sensor includes a laser displacement sensor and a vision camera.

[0014] A clamping and inspection method for an aircraft cylinder clamping and inspection device includes the following steps: S1: hoisting the aircraft cylinder between two sets of adaptive support units on the left and right sides;

[0015] S2: The positioning pin of the drive axial positioning unit extends until it contacts the end face of the cylinder, thus completing the axial positioning;

[0016] S3: Drives the sliders of all radial slides to move synchronously towards the cylinder, pushing the contact end to contact the cylinder surface;

[0017] S4: Based on the real-time feedback of the six-dimensional force sensor, each radial slide is independently controlled by closed-loop force until the radial force at each contact point reaches the set value and the lateral force and torque approach zero. During this process, the two-dimensional swing mechanism passively adapts to the shape of the cylinder surface.

[0018] S5: Control the moving platform of the integrated detection unit to move along the circular track, and at the same time control the slider of the vertical lifting slide to move up and down, so as to drive the measuring sensor to scan and measure the surface of the cylinder.

[0019] S6: Process measurement data and generate a report on the form and position tolerances of the cylinder.

[0020] 9. The aircraft cylinder clamping and testing device according to claim 8, characterized in that, after step S6, it further includes:

[0021] S7: Calculate the shape deviation based on the aforementioned geometric tolerance report;

[0022] S8: Based on the shape deviation, generate an adjustment command to drive the specified radial slide to perform fine-tuning of the position, so as to actively correct the shape of the cylinder.

[0023] The present invention is further configured such that, in step S5, the movement of the mobile platform is linked to the lifting motion of the vertical lifting slide, so that the scanning path of the measuring sensor is a spiral line covering the measured area of ​​the cylinder.

[0024] The present invention is further configured as follows:

[0025] pass.

[0026] In summary, the present invention has the following beneficial effects: by combining active control by a six-dimensional force sensor with passive adaptation by two-dimensional swing, the supporting force is uniform and the direction is purely radial, which fundamentally avoids the deformation of the cylinder caused by traditional rigid clamping, protects the workpiece, and provides a premise for real measurement.

[0027] After clamping, there is no need to move the workpiece. Through the automated composite motion of the integrated detection unit, a large-scale, high-density scanning detection of the cylinder surface can be completed, which greatly improves efficiency compared to offline detection and provides better data consistency.

[0028] Integrating clamping status monitoring, geometric quantity detection, and shape fine-tuning functions, it can proactively optimize the clamping status based on the detection results, providing an end-to-end solution for digital and intelligent precision manufacturing and assembly.

[0029] Adaptive design enables the equipment to be compatible with cylinders of varying sizes and shapes with different precision requirements, reducing tooling customization costs and improving equipment utilization. The passive swing mechanism has no additional drive components, is structurally reliable, and is easy to maintain. Attached Figure Description

[0030] Figure 1 This is a perspective view of an embodiment of the present invention;

[0031] Figure 2 This is a cross-sectional view in an embodiment of the present invention.

[0032] In the picture:

[0033] 1. Basic base; 2. Cross frame; 3. Six-dimensional force sensor; 4. U-shaped base; 5. U-shaped swing frame; 6. Contact head; 7. V-groove. Detailed Implementation

[0034] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The components of the embodiments of the present invention described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0035] Therefore, the following detailed description of the embodiments of the invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the invention without inventive effort are within the scope of protection of the invention.

[0036] It should be noted that, unless otherwise specified, the embodiments and features described in this invention can be combined with each other.

[0037] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0038] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product of this invention is in use, or the orientation or positional relationship commonly understood by those skilled in the art. They are only used for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention. In addition, the terms "first," "second," etc., are only used to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0039] In the description of this invention, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical 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 invention based on the specific circumstances.

[0040] The following is in conjunction with the appendix Figure 1-2 The present invention will be described in further detail below, but the scope of protection of the present invention is not limited to the following description.

[0041] Example 1

[0042] This embodiment provides an aircraft cylinder clamping and testing device, including: a horizontally arranged rectangular base, which serves as the installation foundation for the entire device, and is composed of a rigid welded frame with a finely machined upper surface.

[0043] Two sets of adaptive support units are symmetrically fixed on the upper surface of the base.

[0044] Each set of adaptive support units contains at least four independent support units, which are arranged along the length of the base.

[0045] An axial positioning unit is fixedly installed at one end of the upper surface of the base.

[0046] An integrated detection unit is installed above the base.

[0047] Each adaptive support unit has a defined structural hierarchy.

[0048] Its topmost part is the contact end, which is made of nylon material, and its working surface facing the inside of the cylinder is specifically machined into a 110-degree V-groove.

[0049] The lower surface of the contact end is fixedly connected to the upper surface of a two-dimensional swing mechanism by bolts.

[0050] This two-dimensional oscillating mechanism is the core of achieving passive compliance, and its specific structure is as follows:

[0051] The upper surface of a U-shaped swing arm is connected to the contact end;

[0052] The lower surface of a U-shaped base is used for downward connection;

[0053] The cross axis configuration allows the U-shaped pendulum to swing with two degrees of freedom relative to the U-shaped base. Specifically, the cross axis has a first journal and a second journal that are perpendicular to each other.

[0054] The two ends of the first journal are rotatably connected to the bearing seats on the side plates of the U-shaped base via needle roller bearings, forming the first oscillating pair. Similarly, the two ends of the second journal are rotatably connected to the bearing seats on the side plates of the U-shaped swing frame via needle roller bearings, forming the second oscillating pair. The lower surface of the two-dimensional oscillating mechanism, i.e., the base plate of the U-shaped base, is fixedly connected to the upper surface of a six-dimensional force sensor.

[0055] The six-dimensional force sensor has a standard flange structure, and its lower surface is fixedly connected to the upper surface of the slider of a radial slide.

[0056] The radial slide uses a precision electric linear module, whose base is vertically mounted on the foundation base by bolts. The movement direction of its slider is precisely adjusted to be horizontal and perpendicular to the theoretical axis of the cylinder. The contact ends of the left and right sets of adaptive support units have V-groove openings facing each other, which together are used to clamp the cylinder.

[0057] The axial positioning unit specifically includes a mounting bracket, a transverse adjustment slide, and an end cover plate. The lower surface of the mounting bracket is fixedly connected to the foundation base. The base of the transverse adjustment slide is fixedly connected to the mounting bracket, and its slide can be finely adjusted perpendicular to the cylinder axis. The back of the end cover plate is fixedly connected to the slide of the transverse adjustment slide, and its front is equipped with multiple electric or pneumatic positioning pins that can extend and retract along the cylinder axis.

[0058] The integrated detection unit has the following structure: The lower ends of two columns are fixed to the upper surface of the base, corresponding to the outer positions of the two sets of support units. A rigid annular track is fixedly connected to the upper ends of the two columns at both ends, with its axis coaxial with the ideal axis of the cylinder. A moving platform is slidably connected to the annular track via a slider at its bottom and can move circumferentially along the track. The back of the base of a vertical lifting slide is fixedly connected to the front of the moving platform. The back of a sensor mounting plate is fixedly connected to the front of the slider of the vertical lifting slide. Measurement sensors, including a laser displacement sensor and a vision camera, are directly fixedly mounted on the front of the sensor mounting plate.

[0059] Example 2

[0060] A clamping and inspection method for an aircraft cylinder clamping and inspection device:

[0061] The method for adaptive clamping and inspection using this device is as follows:

[0062] S1, hoist the aircraft cylinder into the space between the left and right sets of adaptive support units.

[0063] S2, all the positioning pins on the end cover of the drive axial positioning unit extend synchronously until they all contact the end face of the cylinder and apply a slight preload, thereby completing the positioning of the cylinder in the axial direction.

[0064] S3 simultaneously drives the radial slides in all support units, causing their sliders to move toward the center of the cylinder, thereby pushing the contact end to contact the outer wall of the cylinder.

[0065] S4, this step is the core adaptive clamping process. The system reads the real-time force and torque data from each six-dimensional force sensor. Based on the set target radial support force, the control system independently and in a closed loop adjusts the position of each radial slide. Through continuous fine-tuning, the radial force at each contact point is precisely adjusted to the set value, while minimizing lateral force and torque. Throughout the force control adjustment process, the two-dimensional oscillating mechanism passively oscillates slightly, allowing the contact end to automatically adapt to the actual shape of the cylinder surface, achieving a proper fit.

[0066] S5. After the clamping is stable, the integrated detection unit is activated. The control system coordinates the circular motion of the moving platform along the ring track with the lifting motion of the vertical lifting slide, making the two work together. This drives the laser displacement sensor and vision camera on the mounting plate to move along a spiral path covering the measured area of ​​the cylinder, and simultaneously acquires measurement data and images during the process.

[0067] S6 processes the collected measurement data, calculates the geometric tolerances such as roundness, overall cylindricity, and generatrix straightness of key sections of the cylinder, and generates an inspection report.

[0068] S7, as an optional advanced function, analyzes shape deviations based on the generated geometric tolerance report after step six. Based on the analysis results, the system calculates the required adjustment amount and generates instructions to drive the radial slide at a specific location to perform extremely small position compensation, thereby actively correcting the shape of the cylinder. This forms a closed loop of "detection-feedback-shape adjustment." In step eight, specifically during the scanning process of step five, the circular motion of the moving platform and the lifting motion of the vertical lifting slide are always coordinated to ensure that the scanning trajectory of the measuring sensor is a continuous and uniform spiral.

[0069] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. An aircraft cylinder clamping and testing device, characterized in that... ,include: Basic base; The adaptive support unit is divided into two symmetrical groups, left and right, and is fixedly installed on the upper surface of the base. An axial positioning unit is fixedly installed at one end of the upper surface of the base; An integrated detection unit is installed above the base. Each group of adaptive support units includes at least four independent units arranged along the length of the base base; Each independent unit includes, from top to bottom, a contact end, a two-dimensional swing mechanism, a six-dimensional force sensor, and a radial slide. The lower surface of the contact end is fixedly connected to the upper surface of the two-dimensional swing mechanism, the lower surface of the two-dimensional swing mechanism is fixedly connected to the upper surface of the six-dimensional force sensor, and the lower surface of the six-dimensional force sensor is fixedly connected to the upper surface of the slider of the radial slide. The lower surface of the base of the radial slide is fixedly connected to the upper surface of the base. The working surfaces of the left and right sets of contact ends are arranged facing each other.

2. The aircraft cylinder clamping and testing equipment according to claim 1, characterized in that: The contact end is made of non-metallic material, and its working surface facing the cylinder is a V-groove or a large-radius arc surface.

3. The aircraft cylinder clamping and testing equipment according to claim 1, characterized in that: The two-dimensional swing mechanism includes a U-shaped base, a cross shaft, and a U-shaped swing frame. The upper surface of the U-shaped swing frame is fixedly connected to the lower surface of the contact end. The lower surface of the U-shaped base is fixedly connected to the upper surface of the six-dimensional force sensor. The cross shaft has a first journal and a second journal that are perpendicular to each other. The two ends of the first journal are rotatably connected to the two side plates of the U-shaped base through bearings. The two ends of the second journal are rotatably connected to the two side plates of the U-shaped swing frame through bearings.

4. The aircraft cylinder clamping and testing equipment according to claim 3, characterized in that: The radial slide is a precision linear module, and the sliding block moves horizontally and perpendicular to the axis of the aircraft cylinder.

5. The aircraft cylinder clamping and testing equipment according to claim 1, characterized in that: The axial positioning unit includes a mounting bracket, a transverse adjustment slide, and an end cover plate. The lower surface of the mounting bracket is fixedly connected to the upper surface of the base. The base of the transverse adjustment slide is fixedly connected to the mounting bracket. The back of the end cover plate is fixedly connected to the front of the slider of the transverse adjustment slide. The front of the end cover plate is provided with multiple positioning pins that can extend and retract along the axis of the cylinder.

6. The aircraft cylinder clamping and testing equipment according to claim 1, characterized in that: The integrated detection unit includes columns, a circular track, a moving platform, a vertical lifting slide, a sensor mounting plate, and a measuring sensor. The lower ends of the two columns are fixedly connected to the upper surface of the base and are located on the outside of the left and right sets of adaptive support units, respectively. The two ends of the circular track are fixedly connected to the upper ends of the two columns, respectively. The moving platform is slidably connected to the circular track. The back of the base of the vertical lifting slide is fixedly connected to the front of the moving platform. The back of the sensor mounting plate is fixedly connected to the front of the slider of the vertical lifting slide. The measuring sensor is fixedly mounted on the front of the sensor mounting plate.

7. The aircraft cylinder clamping and testing equipment according to claim 6, characterized in that: The measurement sensors include a laser displacement sensor and a vision camera.

8. A clamping and inspection method for an aircraft cylinder clamping and inspection device as described in any one of 1-7, characterized in that, Includes the following steps: S1: Hoist the aircraft cylinder between the left and right sets of adaptive support units; S2: The positioning pin of the drive axial positioning unit extends until it contacts the end face of the cylinder, thus completing the axial positioning; S3: Drives the sliders of all radial slides to move synchronously towards the cylinder, pushing the contact end to contact the cylinder surface; S4: Based on the real-time feedback of the six-dimensional force sensor, each radial slide is independently controlled by closed-loop force until the radial force at each contact point reaches the set value and the lateral force and torque approach zero. During this process, the two-dimensional swing mechanism passively adapts to the shape of the cylinder surface. S5: Control the moving platform of the integrated detection unit to move along the circular track, and at the same time control the slider of the vertical lifting slide to move up and down, so as to drive the measuring sensor to scan and measure the surface of the cylinder. S6: Process measurement data and generate a report on the form and position tolerances of the cylinder.

9. The clamping and inspection method of an aircraft cylinder clamping and inspection device according to claim 8, characterized in that, Step S6 is followed by: S7: Calculate the shape deviation based on the aforementioned geometric tolerance report; S8: Based on the shape deviation, generate an adjustment command to drive the specified radial slide to perform fine-tuning of the position, so as to actively correct the shape of the cylinder.

10. The clamping and inspection method of an aircraft cylinder clamping and inspection device according to claim 9, characterized in that: In step S5, the movement of the mobile platform is linked to the lifting and lowering motion of the vertical lifting slide, so that the scanning path of the measuring sensor is a spiral line covering the measured area of ​​the cylinder.

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