Automatic shape righting system for aerospace cabin structural component

Abstract

The invention discloses an automatic shape righting system for a cabin structural part for spaceflight. The system comprises a clamping and positioning subsystem, a motion control subsystem, a shape righting execution subsystem and a deformation detection subsystem. Performing three-dimensional scanning on the structural part through a laser three-dimensional scanning device, and comparing the structural part with a standard model to position a deformation area; the motion control system is used for driving the hydraulic device to accurately position, and accurate and controllable orthopedic force is applied through the pressure-bearing roller to achieve deformation correction. According to the method, the problems that in traditional manual shape correction, operation depends on experience, repeatability is poor, and products are prone to being scrapped are solved, automation, precision and standardization of shape correction work of the spaceflight cabin structural parts are achieved, and the product percent of pass and work efficiency are remarkably improved.

Description

Technical Field

[0001] This invention relates to the field of machining technology, and more specifically to an automated straightening system for aerospace cabin structural components. Background Technology

[0002] Spacecraft cabin structural components are essential parts of spacecraft, playing a crucial role in protecting, supporting, and connecting internal components. Their dimensional accuracy directly affects the stability, aerodynamic characteristics, and overall performance of the spacecraft during launch and flight. Currently, these components are typically made of lightweight alloy materials such as magnesium alloys and aluminum alloys, and formed through casting processes. The specific process includes mold design → sand mold preparation → sand mold assembly → casting → mold opening → gating cutting → heat treatment → flaw detection → machining → delivery.

[0003] In this production process, the unpacking, heat treatment, and machining processes can easily lead to deformation of the cabin structural components. The main reasons include uneven distribution of residual stress in the castings, lattice distortion during heat treatment, and cutting stress generated during machining. Such deformation often results in dimensional deviations of the workpieces, leading to a high scrap rate, a significant increase in production costs, and difficulty in meeting the ever-increasing demand for low-cost manufacturing in the aerospace field.

[0004] For deformable cabin structural components, the traditional manufacturing process generally adopts manual straightening, that is, using a wooden mallet as a straightening tool, with operators using their experience to tap the deformed area to change the local shape and achieve the straightening purpose. This method has the following obvious defects: (1) manual operation depends on experience and requires operators with rich experience; (2) poor repeatability. Even with experienced operators, it is still impossible to ensure that every structural component is straightened to the required standard; (3) easy to produce scrapped products. The amount of force applied during the operation determines the straightening quality of the cabin. When the force is too great, the cabin structural component will crack and become scrapped.

[0005] In the prior art, for example, Chinese utility model patent CN208662205U discloses a straightening device that uses the principle of reverse deformation to correct welding deformation of automotive aluminum alloy extruded crossbeams. This device includes a base, a jack mounted on the base, and a fixed measuring scale. The extension length of the jack's rod is adjusted to correct different degrees of deformation. Although this device has a certain degree of adjustment accuracy, it is mainly designed for regular welding deformation and is suitable for relatively simple automotive parts. It is difficult to handle the complex, multi-dimensional deformations generated during casting, heat treatment, and machining of aerospace cabin structural components, and it cannot achieve automated, repeatable, high-precision straightening operations.

[0006] In summary, existing orthopedic techniques still suffer from problems such as low automation, insufficient precision control, and limited applicability. There is an urgent need for an automated device that can adapt to the characteristics of aerospace cabin structural components and achieve precise and controllable orthopedic correction. Summary of the Invention

[0007] The purpose of this invention is to provide an automated correction system for aerospace cabin structural components, which solves problems such as repeatability and easy product scrapping during manual operation.

[0008] The technical solution of this invention: An automated correction system for aerospace cabin structural components, comprising... Clamping and positioning subsystem: It consists of a pair of symmetrically arranged supports and three-jaw chucks respectively mounted on them, used to coaxially clamp the cabin structure components; Motion control subsystem: includes a three-jaw chuck motion control screw located below the support, which controls the movement of the support along the X and Y axes, and is used to adjust the position of the clamping and positioning subsystem; The orthopedic actuation subsystem includes a hydraulic oil tank with a pair of pressure rollers connected to it, which are driven by the hydraulic oil tank and slide horizontally along the Y-axis to apply precise orthopedic force to the deformed area of ​​the cabin. The deformation detection subsystem includes a laser 3D scanning device, which is used to acquire 3D topographic data of the cabin under clamping conditions to identify the deformation area and deformation amount.

[0009] Furthermore, the clamping and positioning subsystem is mounted on a flat plate, which is positioned above the base and forms a displacement space with the base, enabling the clamping and positioning subsystem to be adjusted relative to the base in the XY plane; the base is provided with multiple lead screw mounting seats for mounting the motion control subsystem around its periphery.

[0010] Furthermore, the motion control subsystem includes a first lead screw and a second lead screw arranged perpendicularly to each other; the two ends of the first lead screw are mounted on a pair of opposing lead screw mounting seats for driving the plate to move along the X-axis; the two ends of the second lead screw are mounted on another pair of opposing lead screw mounting seats for driving the plate to move along the Y-axis.

[0011] Furthermore, the support integrates a rotary motor, which is connected to the three-jaw chuck for driving the three-jaw chuck to rotate continuously 360° around its axis.

[0012] Furthermore, the orthopedic actuation subsystem is an independently configured hydraulic actuator, which includes a vertically configured hydraulic oil tank, a pair of horizontally symmetrically configured hydraulic rod mounting supports, a hydraulic rod, and a pressure roller; the hydraulic rod mounting supports are fixedly installed on the hydraulic oil tank, the cylinder end of the hydraulic rod is installed on the hydraulic rod mounting support, and the piston rod end is equipped with a pressure roller; Two hydraulic rods are horizontally opposed to each other and move toward or away from each other via hydraulic drive, thereby driving the pressure rollers to apply a corrective force to the cabin structure.

[0013] Furthermore, the pair of hydraulic rod mounting supports are spaced apart vertically on the hydraulic oil tank, and the space formed between them covers the movement range of the cabin structure during the straightening process.

[0014] Furthermore, the orthopedic execution subsystem is an independently executed scanning mechanism, including a robotic arm. One end of the robotic arm is mounted on a robotic arm support, and the other end is rotatably mounted with a laser three-dimensional scanning device.

[0015] Furthermore, the laser three-dimensional scanning device is configured to perform three-dimensional scanning of the shape of the cabin structure and compare the scanning data with a preset part model to identify the deformation area and measure the deformation amount.

[0016] Furthermore, the robotic arm has a multi-joint structure, enabling multi-degree-of-freedom spatial movement and driving a laser 3D scanning device to complete an all-round scan of the cabin structure.

[0017] The beneficial effects of this invention are as follows: This invention uses a laser 3D scanning device to perform precise 3D scanning of the structural component's shape and automatically compares it with a standard part model, achieving precise positioning of out-of-tolerance areas and accurate acquisition of deformation dimensions. Furthermore, a motion control system controls the precise positioning of the hydraulic device, and a straightening execution subsystem applies precise and controllable force to the deformed area, completing the automated straightening operation. This technical solution effectively solves the problems of poor repeatability and easy product scrapping in traditional manual straightening processes, while also possessing good product versatility and process stability. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the specific embodiments of the present invention, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0019] Figure 1 This is a front view of the automated correction device for aerospace cabin structural components according to the present invention; Figure 2 This is a top view of the automated correction device for aerospace cabin structural components according to the present invention; Figure 3 This is a schematic diagram of the control principle of the system of the present invention; Reference numerals in the attached figures: 1-Three-jaw chuck; 2-Three-jaw chuck support; 3-Screw mounting support; 4-Three-jaw chuck motion control screw; 5-Robotic arm; 6-Laser 3D scanning device; 7-Pressure roller; 8-Hydraulic rod; 9-Robotic arm support; 10-Hydraulic rod mounting support; 11-Hydraulic oil tank; 41-First screw; 42-Second screw. Detailed Implementation

[0020] The present invention will be further described below with reference to the accompanying drawings and specific embodiments. However, it should not be construed that the scope of the subject matter of the present invention is limited to the following embodiments. All modifications, substitutions and alterations made based on ordinary technical knowledge and common practices in the art without departing from the above-described technical concept of the present invention are included within the scope of the present invention.

[0021] This invention discloses an automated correction system for aerospace cabin structural components. Through integrated and automated design, this system achieves high-precision and repeatable correction of deformations in aerospace cabin structural components. (Refer to...) Figure 1 and Figure 2 This system mainly consists of four functional subsystems, including: The clamping and positioning subsystem consists of a pair of symmetrically arranged three-jaw chuck supports 2 and three-jaw chucks 1 mounted on them, used for coaxially opposing clamping of cabin structural components. The three-jaw chuck supports 2 integrate a rotary motor, which can drive the three-jaw chucks 1 to rotate continuously 360° around its axis, facilitating straightening operations at different circumferential positions of the cabin. The three-jaw chucks 1 are mainly used for clamping cabin structural components of different diameters.

[0022] The motion control subsystem includes a three-jaw chuck motion control screw 4 located below the three-jaw chuck support 2, and a first screw 41 and a second screw 42 arranged perpendicularly to each other. The clamping and positioning subsystem is mounted on a flat plate, which is positioned above the base and forms a displacement space with the base. The first screw 41 drives the flat plate to move along the X-axis, and the second screw 42 drives the flat plate to move along the Y-axis, achieving precise displacement adjustment of the clamping and positioning subsystem in the XY plane. Multiple screw mounting seats 3 are arranged around the base to fix and support the screw mechanism. The first lead screw 41 is also configured to be directly connected to the three-jaw chuck support 2, controlling the three-jaw chuck support 2 to move towards and away from each other on the flat plate, so as to achieve the clamping of cabin structural components of different lengths. The second lead screw 42 is used to control the cabin structural components to move away from or towards the orthopedic actuation subsystem.

[0023] The orthopedic actuation subsystem is an independently configured hydraulic actuator, comprising a vertically positioned hydraulic oil tank 11, a pair of horizontally symmetrical hydraulic rod mounting supports 10, hydraulic rods 8, and pressure rollers 7. The hydraulic rod mounting supports 10 are spaced vertically on the hydraulic oil tank 11, forming a space that covers the movement range of the cabin structure during the orthopedic process. The cylinder end of the hydraulic rod 8 is mounted on the hydraulic rod mounting support 10, and the piston rod end is fitted with the pressure roller 7. The two hydraulic rods 8 are horizontally opposed and hydraulically driven to move towards or away from each other, thereby driving the pressure rollers 7 to apply precise radial orthopedic force to the cabin structure.

[0024] The deformation detection subsystem includes a robotic arm 5 and a laser 3D scanning device 6. The robotic arm 5 is a multi-jointed structure capable of multi-degree-of-freedom spatial movement. One end is mounted on a robotic arm support 9, and the other end is rotatably equipped with the laser 3D scanning device 6. This scanning device is configured to perform 3D scanning of the cabin structural components and compare the scanned data with a preset part model to achieve precise positioning of the deformable area and accurate measurement of the deformation.

[0025] The system's workflow is as follows: Stable clamping of cabin structural components of different diameters and lengths is achieved through the diameter adjustment of the three-jaw chuck 1 and the opposing / dispersing motion of the three-jaw chuck motion control screw 4. The robotic arm 5 drives the laser 3D scanning device 6, combined with the circumferential rotation of the three-jaw chuck 1, to perform a comprehensive 3D scan of the cabin surface, acquiring complete shape data. The scanned data is compared with a preset 3D model of the part, automatically identifying areas with excessive deformation and accurately calculating the deformation amount and the force required for correction. The motion control subsystem precisely positions the correction execution subsystem to the deformation area, ensuring that the pressure roller 7 accurately acts on the deformed part. Based on the deformation amount, the hydraulic rod 8 applies a progressive correction force, and the pressure roller 7 precisely loads force onto the deformation area, achieving material plastic deformation correction. After correction, the cabin is scanned again by the laser 3D scanning device 6 to verify the correction effect, forming a complete quality closed loop.

[0026] This system effectively solves the key technical problems of traditional manual straightening methods. Through laser 3D scanning and automated control, it replaces the traditional hammering straightening method that relies on operator experience, achieving standardized operations based on precise measurements. By working collaboratively through multiple subsystems, this system establishes a complete technical system for the straightening of aerospace cabin structural components, providing the aerospace manufacturing field with an efficient, reliable, and repeatable automated straightening solution.

[0027] Example 2: This invention provides an automated straightening device for aerospace cabin structural components. This device includes a laser 3D scanning subsystem, a hydraulic subsystem, a clamping subsystem, and a motion control subsystem. It solves the problems of reliance on manual labor and poor repeatability in traditional straightening / correction processes, achieving automated and repeatable cabin straightening / correction operations, and improving product qualification rates. The operation method and principle are as follows: The specific operating procedure is as follows: First, adjust the diameter using a three-jaw chuck and... Figure 1 The three-jaw chuck motion control screw 4 performs opposite or opposite movements to achieve clamping of hulls of different diameters or lengths; after clamping, it uses... Figure 1 The robotic arm 5 controls a laser 3D scanning device 6, which, in conjunction with the circumferential motion of a rotation control motor built into the three-jaw chuck support 2, achieves 3D scanning of different cabin areas. By comparing the data with the cabin part model, the location of areas with excessive deformation and the measurement of deformation are achieved. After locating the deformed area and measuring the deformation, the position is adjusted by the three-jaw chuck motion control screw 4, moving the pressure roller 7 controlled by the hydraulic rod 8 to the deformed area. Then, by controlling the hydraulic rod 8 and applying a certain force (gradually increasing) according to the deformation, the deformation in that area is corrected. After correction, the three-jaw chuck motion control screw 4 or the motor built into the three-jaw chuck support 2 is used to achieve correction at different positions. After correction, the 3D scanning results of the cabin structure are re-measured by the laser 3D scanning device 6 to verify the correction results.

[0028] The control principle is as follows: (Refer to...) Figure 3 , Scan command initiation and execution: The control system sends a three-dimensional scanning command for the aerospace cabin structural components to the laser three-dimensional scanning system; the laser three-dimensional scanning system sends a "scan command to drive execution" to the motion control system, which then performs deformation measurement / positioning work on the aerospace cabin structural components.

[0029] Data processing and feedback: The motion control system transmits deformation measurement data to the structural data analysis module; the structural data analysis module feeds back the deformation data to the control system and sends dynamic adjustment and correction commands to the correction device; at the same time, the control system also sends dynamic adjustment and correction commands directly to the correction device.

[0030] Calibration and closed-loop control: After receiving the command, the calibration device performs dynamic calibration operation and feeds back the calibration data to the sensor; the sensor transmits the calibration data information back to the control system, thus forming a complete scan-analysis-calibration-feedback closed-loop control process to achieve accurate monitoring and dynamic calibration of aerospace cabin structural components.

[0031] The automated correction system for aerospace cabin structural components provided by this invention has been described in detail above. Specific examples have been used to illustrate the structure and working principle of this invention. The descriptions of the embodiments above are only for the purpose of helping to understand the method and core ideas of this invention. It should be noted that those skilled in the art can make various improvements and modifications to this invention without departing from its principles, and these improvements and modifications also fall within the scope of protection of the claims of this invention.

Claims

1. An automated correction system for aerospace cabin structural components, characterized in that: include Clamping and positioning subsystem: It consists of a pair of symmetrically arranged supports (2) and three-jaw chucks (1) respectively installed on them, for coaxially opposing clamping of cabin structural components; Motion control subsystem: includes a three-jaw chuck motion control screw (4) located below the support (2) and controlling the movement of the support (2) along the X and Y axes, used to adjust the position of the clamping and positioning subsystem; The orthopedic execution subsystem includes a hydraulic oil tank (11) with a pair of pressure rollers (7) connected to it and driven by it to slide horizontally along the Y-axis, for applying precise orthopedic force to the deformable area of ​​the cabin. The deformation detection subsystem includes a laser three-dimensional scanning device (6) for acquiring three-dimensional topographic data of the cabin under clamping conditions to identify the deformation area and deformation amount.

2. The automated correction system for aerospace cabin structural components according to claim 1, characterized in that: The clamping and positioning subsystem is mounted on a flat plate, which is positioned above the base and forms a displacement space with the base, enabling the clamping and positioning subsystem to be adjusted relative to the base in the XY plane; the base is provided with multiple lead screw mounting seats (3) for mounting the motion control subsystem.

3. The automated correction system for aerospace cabin structural components according to claim 2, characterized in that: The motion control subsystem includes a first lead screw (41) and a second lead screw (42) arranged perpendicularly to each other; the two ends of the first lead screw (41) are mounted on a pair of opposing lead screw mounting seats (3) for driving the plate to move along the X-axis direction; the two ends of the second lead screw (42) are mounted on another pair of opposing lead screw mounting seats (3) for driving the plate to move along the Y-axis direction.

4. The automated correction system for aerospace cabin structural components according to claim 1, characterized in that: The support (2) has an integrated rotating motor inside, which is connected to the three-jaw chuck (1) for driving the three-jaw chuck (1) to rotate continuously around its axis by 360°.

5. The automated correction system for aerospace cabin structural components according to claim 1, characterized in that: The orthopedic actuation subsystem is an independently set hydraulic actuator, which includes a vertically set hydraulic oil tank (11), a pair of horizontally symmetrically set hydraulic rod mounting supports (10), a hydraulic rod (8) and a pressure roller (7); the hydraulic rod mounting supports (10) are fixedly installed on the hydraulic oil tank (11), the cylinder end of the hydraulic rod (8) is installed on the hydraulic rod mounting supports (10), and the piston rod end is equipped with a pressure roller (7). Two hydraulic rods (8) are horizontally opposite each other and move towards or away from each other through hydraulic drive, so as to drive the pressure roller (7) to apply a corrective force to the cabin structure.

6. The automated correction system for aerospace cabin structural components according to claim 5, characterized in that: The pair of hydraulic rod mounting supports (10) are arranged vertically at intervals on the hydraulic oil tank (11), and the space formed between them covers the movement range of the cabin structure during the straightening process.

7. The automated correction system for aerospace cabin structural components according to claim 1, characterized in that: The orthopedic execution subsystem is an independently executed scanning mechanism, including a robotic arm (5). One end of the robotic arm (5) is mounted on a robotic arm support (9), and the other end is rotatably mounted with a laser three-dimensional scanning device (6).

8. The automated correction system for aerospace cabin structural components according to claim 7, characterized in that: The laser three-dimensional scanning device (6) is configured to perform three-dimensional scanning on the shape of the cabin structure and compare the scanning data with the preset part model to identify the deformation area and measure the deformation amount.

9. The automated correction system for aerospace cabin structural components according to claim 7, characterized in that: The robotic arm (5) is a multi-joint structure, which can realize multi-degree-of-freedom spatial movement and drive the laser three-dimensional scanning device (6) to complete the all-round scanning of the cabin structure.

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