Spaceflight launching equipment structure crack detection device

Abstract

The utility model discloses a spaceflight launching equipment structure crack detection device which comprises a hydraulic lifting system, a control unit, an ultrasonic flaw detection probe, a conductive slip ring, a cable, a data acquisition assembly and a digital twin system. The data acquisition assembly is used for acquiring images of the surface of the structure, the control unit is used for transmitting information detected by the ultrasonic flaw detection probe and acquired by the data acquisition assembly to the digital twin system, and when crack loss exists in the structure, the position and degree can be visually displayed, positioning is facilitated, timely processing is facilitated, and the working efficiency is improved. And during detection, automatic control is facilitated, and use is convenient.

Description

Technical Field

[0001] The utility model relates to the technical field of aerospace launch equipment detection, in particular to a device for detecting structural cracks of aerospace launch equipment. Background Art

[0002] Large-scale space launch equipment is a critical facility that supports and carries carrier rockets through a series of activities, including hoisting, transport, testing, and launch. It is generally composed of subsystems such as the travel mechanism, support and adjustment mechanism, control system, hydraulic system, and mechanical structure. Considering its mechanical structure as the primary load-bearing component, regular inspection is required to ensure its reliability and safety to avoid safety hazards caused by cracks. Digital twins fully utilize data from physical models, sensor updates, and operational history, integrating multidisciplinary, multi-physical, multi-scale, and multi-probability simulation processes to complete mapping in virtual space, thereby reflecting the entire life cycle of the corresponding physical equipment.

[0003] Existing crack detection technology for space launch equipment generally requires the equipment to be disassembled and decomposed, making it impossible to carry out detection work during the execution of space launch activities, and it is even impossible to intuitively display the location and extent of the cracks, making it inconvenient to locate them. This restricts the implementation of current high-density space launch activities. Therefore, a structural crack detection device for space launch equipment is needed to meet the needs. Utility Model Content

[0004] The purpose of the present utility model is to provide a device for detecting cracks in a structure of aerospace launch equipment, so as to solve the problems raised in the above-mentioned background technology.

[0005] To achieve the above-mentioned object, the present utility model provides the following technical solutions: a device for detecting structural cracks in aerospace launch equipment, comprising a hydraulic lifting system, a control unit, an ultrasonic flaw detection probe, a conductive slip ring, a cable, a data acquisition component, and a digital twin system;

[0006] The hydraulic lifting system can carry the ultrasonic flaw detection probe and achieve lifting within a range of - meters;

[0007] The ultrasonic flaw detection probe is installed on the top of the hydraulic lifting system arm;

[0008] The conductive slip ring is sleeved on the top of the hydraulic lifting system arm;

[0009] The cables are distributed in a circular array around the conductive slip ring;

[0010] The data acquisition components are arranged on each cable, the output end of which is connected to the control unit, and the data acquisition components are evenly arranged in an array on the cable;

[0011] The control unit is connected to the digital twin system signal.

[0012] Preferably, the input end of the ultrasonic flaw detection probe is connected to a conductive slip ring via a connecting wire.

[0013] Preferably, a fixed stopper is installed at the top end of the support arm of the hydraulic lifting system, and the diameter of the fixed stopper is larger than the diameter of the conductive slip ring.

[0014] Preferably, a mounting plate is fixedly mounted on the lower end of the hydraulic lifting system support arm, and the ultrasonic flaw detection probe is fixedly mounted on the mounting plate and protected by a protective shell.

[0015] Preferably, the data acquisition component includes a fixed shell and a collection probe, the fixed shell is installed on the cable, the collection probe is installed in the fixed shell, mounting ears are installed on both sides of the fixed shell, and the fixed shell is installed on the cable through the mounting ears on both sides.

[0016] Preferably, a sealing gasket is provided on the inner side of the fixed shell around the collection probe, and the fixed shell is pressed against the collection probe through the sealing gasket.

[0017] Preferably, the control unit includes a control board and a communication module, an information storage module and a delay control module connected to the control board signal, and the delay control module is connected to the ultrasonic flaw detection probe signal; the data acquisition component end is respectively connected to the delay control module and the control unit signal through the communication module; the information storage module and the delay control module are signal-connected to the communication module, and the communication module is signal-connected to the digital twin system.

[0018] The beneficial effects of the utility model are:

[0019] In the utility model, an ultrasonic flaw detection probe is used to detect cracks in a mechanical structure, and an image of the surface of the structure is collected by a data acquisition component. The information detected by the ultrasonic flaw detection probe and collected by the data acquisition component is transmitted to the digital twin system through a control unit. When there is crack loss in the structure, the position and degree can be displayed intuitively, which is convenient for positioning so as to carry out timely processing. Moreover, during the detection, it is convenient for automatic control and easy to use. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 This is a schematic structural diagram of a space launch equipment structural crack detection device proposed by the present invention;

[0021] Figure 2 This is a schematic diagram of the connection structure between an ultrasonic flaw detection probe and a conductor slip ring of a space launch equipment structural crack detection device proposed by the present invention;

[0022] Figure 3 This is a schematic diagram of the connection structure of the conductive slip ring and cable of a structural crack detection device for aerospace launch equipment proposed by the present invention;

[0023] Figure 4 This is a schematic diagram of the data acquisition component structure of a space launch equipment structural crack detection device proposed by the utility model;

[0024] Figure 5 This is a schematic diagram of a control unit of a structural crack detection device for aerospace launch equipment proposed in the present invention.

[0025] In the figure: 1. Hydraulic lifting system; 2. Control unit; 3. Ultrasonic flaw detection probe; 4. Conductive slip ring; 5. Cable; 6. Data acquisition component; 61. Fixed shell; 62. Acquisition probe; 63. Mounting ear; 64. Sealing gasket; 7. Connecting wire; 8. Fixed stopper; 9. Mounting plate; 10. Protective shell. DETAILED DESCRIPTION

[0026] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0027] Reference Figure 1-5 , a structural crack detection device for aerospace launch equipment, comprising a hydraulic lifting system 1, a control unit 2, an ultrasonic flaw detection probe 3, a conductive slip ring 4, a cable 5, a data acquisition component 6 and a digital twin system;

[0028] The hydraulic lifting system 1 can carry the ultrasonic flaw detection probe 3 to achieve lifting within the range of 1-10 meters;

[0029] The ultrasonic flaw detection probe 3 is installed on the top of the support arm of the hydraulic lifting system 1;

[0030] The conductive slip ring 4 is sleeved on the top of the support arm of the hydraulic lifting system 1;

[0031] The cables 5 are distributed in a circular array around the conductive slip ring 4;

[0032] The data acquisition components 6 are arranged on each cable 5, and the output end is connected to the control unit 2. The data acquisition components 6 are evenly arranged in an array on the cables 5;

[0033] The control unit 2 is connected to the digital twin system signal.

[0034] By using an ultrasonic flaw detection probe 3 to detect cracks in the mechanical structure and using a data acquisition component 6 to capture images of the surface of the structure, the information detected by the ultrasonic flaw detection probe 3 and collected by the data acquisition component 6 is transmitted to the digital twin system through the control unit 2. When there is crack loss in the structure, the position and degree can be displayed intuitively, which is convenient for positioning so that timely processing can be carried out. In addition, during detection, it is convenient for automatic control and easy to use.

[0035] Specifically, in this embodiment, the input end of the ultrasonic flaw detection probe 3 is connected to the conductive slip ring 4 via a connecting line 7 , which provides power supply and data transmission connection for the ultrasonic flaw detection probe 3 .

[0036] Specifically, in this embodiment, a fixed stopper 8 is installed at the top of the support arm of the hydraulic lifting system 1. The diameter of the fixed stopper 8 is larger than the diameter of the conductive slip ring 4 to prevent the conductive slip ring 4 from slipping out. It can be fixed by appropriate methods such as adhesion, adsorption, and welding.

[0037] Specifically, in this embodiment, a mounting plate 9 is fixedly installed at the lower end of the arm of the hydraulic lifting system 1, and the ultrasonic flaw detection probe 3 is fixedly installed on the mounting plate 9 and protected by a protective shell 10 to prevent the ultrasonic flaw detection probe 3 from being exposed to wind and sun outside, which may shorten its service life.

[0038] Specifically, in this embodiment, the data acquisition component 6 includes a fixed shell 61 and a collection probe 62. The fixed shell 61 is installed on the cable 5, and the collection probe 62 is installed in the fixed shell 61. Mounting ears 63 are installed on both sides of the fixed shell 61. The fixed shell 61 is installed on the cable 5 through the mounting ears 63 on both sides. During installation, the ear holes of the mounting ears 63 are fixed with screws.

[0039] Specifically, in this embodiment, a sealing gasket 64 is provided on the inner side of the fixed shell 61 around the acquisition probe 62. The fixed shell 61 is pressed against the acquisition probe 62 by the sealing gasket 64. The acquisition probe 62 is protected by the sealing gasket 64. After the installation is completed, it is convenient to collect images of cracks and hidden damages in the mechanical structure.

[0040] Specifically, in this embodiment, the control unit 2 includes a control board and a communication module, an information storage module and a delay control module connected to the control board signal. The delay control module is connected to the ultrasonic flaw detection probe 3 signal; the data acquisition component 6 end is respectively connected to the delay control module and the control unit 2 signal through the communication module; the information storage module and the delay control module are connected to the communication module signal, and the communication module is connected to the digital twin system signal.

[0041] The information storage module temporarily stores the information collected by the acquisition terminal and the data acquisition component 6; when in use, the communication module connects the signal with the external digital twin system to realize signal transmission. The information storage module temporarily stores the detected information and sends it to the external digital twin system for analysis after preliminary sorting; the crack detection device is timed to start through the delay control module, and periodic inspections are carried out to improve the degree of automation. When performing flaw detection, the ultrasonic flaw detection probe 3 uses the data acquisition component 6 to detect cracks or hidden damage in the mechanical structure, and determines whether there is a crack by analyzing the reflected wave; when performing detection, the ultrasonic flaw detection probe 3 transmits the detected signal to the control unit 2, and the control unit 2 sends the detected signal to the external digital twin system, and displays whether there is a hidden damage or crack on the digital twin system visualization page. When there is a hidden damage or crack, the location of the fault is further displayed on the digital twin visualization page, which is convenient for online detection, quick positioning of the crack location, and maintenance and rapid processing.

[0042] The above are only preferred specific implementation methods of the present invention, but the protection scope of the present invention is not limited to them. Any technician familiar with the technical field can make equivalent replacements or changes based on the technical solution and utility model concept of the present invention within the technical scope disclosed by the present invention, and they should be covered by the protection scope of the present invention.

Claims

1. A structural crack detection device for aerospace launch equipment, comprising a hydraulic lifting system (1), a control unit (2), an ultrasonic flaw detection probe (3), a conductive slip ring (4), a cable (5), a data acquisition component (6), and a digital twin system, characterized in that: The hydraulic lifting system (1) can carry the ultrasonic flaw detection probe (3) to achieve lifting within a range of 1-10 meters; The ultrasonic flaw detection probe (3) is installed at the top end of the support arm of the hydraulic lifting system (1); The conductive slip ring (4) is sleeved on the top end of the support arm of the hydraulic lifting system (1); The cables (5) are distributed in a circular array around the conductive slip ring (4); The data acquisition components (6) are arranged on each cable (5), and the output end is connected to the control unit (2). The data acquisition components (6) are evenly arranged in an array on the cable (5); The control unit (2) is connected to the digital twin system signal.

2. The device for detecting cracks in a structure of a space launch equipment according to claim 1, characterized in that: The input end of the ultrasonic flaw detection probe (3) is connected to the conductive slip ring (4) via a connecting line (7).

3. The device for detecting structural cracks in aerospace launch equipment according to claim 1, wherein: A fixed stopper (8) is installed at the top end of the support arm of the hydraulic lifting system (1); the diameter of the fixed stopper (8) is larger than the diameter of the conductive slip ring (4).

4. The device for detecting cracks in a structure of a space launch equipment according to claim 1, wherein: A mounting plate (9) is fixedly mounted on the lower end of the support arm of the hydraulic lifting system (1), and an ultrasonic flaw detection probe (3) is fixedly mounted on the mounting plate (9) and protected by a protective shell (10).

5. The device for detecting structural cracks in aerospace launch equipment according to claim 1, wherein: The data acquisition component (6) comprises a fixed shell (61) and a collection probe (62); the fixed shell (61) is mounted on the cable (5); the collection probe (62) is mounted in the fixed shell (61); mounting ears (63) are mounted on both sides of the fixed shell (61); and the fixed shell (61) is mounted on the cable (5) via the mounting ears (63) on both sides.

6. The device for detecting cracks in a structure of a space launch equipment according to claim 5, characterized in that: A sealing gasket (64) is provided on the inner side of the fixed shell (61) around the collecting probe (62), and the fixed shell (61) is pressed tightly against the collecting probe (62) via the sealing gasket (64).

7. The device for detecting structural cracks in aerospace launch equipment according to claim 1, characterized in that: The control unit (2) includes a control panel and a communication module, an information storage module, and a delay control module connected to the control panel by signal; the delay control module is connected to the ultrasonic flaw detection probe (3) by signal; the data acquisition component (6) is connected to the delay control module and the control unit (2) by signal through the communication module; the information storage module and the delay control module are connected to the communication module by signal, and the communication module is connected to the digital twin system by signal.

Images