Aircraft EWIS cable rapid locking device and use method thereof

Abstract

The invention relates to the technical field of airplane electrical circuit interconnection system safety, in particular to an airplane EWIS cable rapid locking device and a using method thereof.The airplane EWIS cable rapid locking device comprises a shell, a pull rod, a clamping sleeve, a nut, a button, a spring, a gasket and a ball, the pull rod is provided with a spiral groove and a pit, and the ball and a conical hole are arranged in the clamping sleeve. By pressing and rotating the button, the pull rod is driven to move to enable the ball to be clamped into the pit along the spiral groove, and a composite anti-loosening structure is formed by combining pre-tightening of the spring. The cable support solves the problems that a traditional cable support is prone to loosening during vibration and inconvenient to install and maintain, has the advantages of being reliable in locking, convenient and fast to operate, rapid to disassemble and assemble and controllable in clamping force, is friendly to a composite material structure, can accurately meet different clamping requirements, and is particularly suitable for installation and fixation of an airplane EWIS cable in severe environments such as vibration and impact.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft electrical wiring interconnection system safety, in particular to an aircraft EWIS cable quick locking device and a method thereof. BACKGROUND

[0002] As the "nerve system" of the aircraft, the electrical wiring interconnection system (EWIS) is responsible for transmitting power and signals, and its reliability is directly related to flight safety. According to statistics, EWIS failures account for 49% of all aircraft failures. There have been many air disasters caused by wiring problems in history, such as the TWA 800 flight explosion caused by a short circuit in the electrical wiring, and the F-35B fighter fire caused by loose cable support, highlighting the key role of EWIS fixing components.

[0003] The existing cable fixing method mainly uses metal supports combined with rivets or bolts for installation, and then uses a clamp to fix the wiring harness. This method has obvious defects: first, it is inconvenient to install and maintain, and special tools are needed for operation in the narrow cabin of the aircraft, which is low in efficiency and easy to introduce human errors; second, the anti-loose capability is insufficient, and the traditional structure relying on the friction force of the threaded pair is prone to loosening under high-frequency vibration, which is hidden and fatal.

[0004] Especially during the test flight stage of the aircraft, the EWIS needs to frequently adjust the position of the wiring harness and support, and the traditional device cannot meet the requirement of quick disassembly and assembly. These problems have become a key bottleneck restricting flight safety and debugging efficiency, and therefore there is an urgent need to develop a new type of EWIS cable locking device that is suitable for harsh environments, easy to operate, and reliable in anti-loose. SUMMARY

[0005] In view of the deficiencies of the prior art, the present application provides an aircraft EWIS cable quick locking device and a method thereof, aiming to solve at least one of the problems in the background art.

[0006] In a first aspect, the present application provides an aircraft EWIS cable quick locking device, comprising: an outer shell, which is a bottomed cylindrical structure with a circular opening at the bottom, and an opening is provided at the top of the side wall of the outer shell; a pull rod, which is a variable cross-section cylindrical structure, the top cylindrical cross-section of the pull rod is larger than the bottom cylindrical cross-section, the outer diameter of the short cross-section of the pull rod is smaller than the inner diameter of the bottom opening of the outer shell, the outer diameter of the large cross-section of the pull rod is larger than the inner diameter of the bottom opening of the outer shell and smaller than the inner diameter of the outer shell, a threaded hole is provided at the top of the pull rod, a spiral groove is provided at the bottom of the pull rod, the cross-section of the spiral groove is circular, and the center of the spiral groove is located outside the bottom of the pull rod, a circular pit is provided at the top end of the spiral groove, the distance between the edge of the pit and the bottom end of the pull rod is 0.1-0.5mm smaller than the distance between the turning point of the spiral groove and the pit and the bottom end of the pull rod, and the pull rod is arranged inside the outer shell; The sleeve is a variable cross-section cylinder with a top cross-section smaller than the bottom cross-section. The bottom of the sleeve is provided with a threaded hole, the top of the sleeve is provided with an axial opening, the outer side wall of the top of the sleeve is provided with an external thread, and the side wall of the top of the sleeve is provided with a tapered hole facing the axis. The bottom of the pull rod extends into the opening at the top of the sleeve. A nut, the internal thread of which matches the external thread of the ferrule, and the nut is threadedly connected to the top of the ferrule; The button includes a metal stud and a ball handle, wherein the metal stud and the ball handle are integrally formed, the metal stud matches the threaded hole at the top of the pull rod, and the metal stud is threadedly connected to the threaded hole at the top of the pull rod; The spring is a helical spring, with an inner diameter larger than the outer diameter of the bottom of the pull rod and smaller than the outer diameter of the top of the pull rod. The spring is disposed inside the housing and sleeved on the outside of the pull rod. The washer has an inner diameter larger than the outer diameter of the bottom of the pull rod, and the outer diameter of the washer is smaller than the inner diameter of the outer shell; The ball is spherical, and its outer diameter matches the inner diameter of the spiral groove. The ball and the spiral groove are in a rolling connection.

[0007] In some embodiments, the housing material is aluminum alloy or polymer material, and the opening at the top of the housing is circular, elliptical, waist-shaped or rectangular, with the inner diameter of the opening at the top of the housing being larger than the outer diameter of the metal stud.

[0008] In some embodiments, the tie rod is made of alloy steel or titanium alloy.

[0009] In some embodiments, the bottom diameter of the pull rod is 6.35 mm or 4.3 mm.

[0010] In some embodiments, the spiral grooves at the bottom of the pull rod are arranged symmetrically along the axial direction, and the number of them is three.

[0011] In some embodiments, the axial opening at the top of the sleeve matches the bottom of the pull rod, the bottom diameter of the tapered hole at the top of the sleeve is smaller than the outer diameter of the ball, the top diameter of the tapered hole at the top of the sleeve is larger than the diameter of the ball, and the axial arrangement of the tapered holes is the same as the spiral groove of the pull rod.

[0012] In some embodiments, the threaded hole at the bottom of the sleeve is a fine-pitch threaded hole with a specification of M4×0.5 or M5×0.5.

[0013] In some embodiments, the number of buttons is two, arranged symmetrically along the axis of the pull rod.

[0014] In some embodiments, the locking force of the aircraft EWIS cable quick-locking device is determined based on the thickness of the clamped object, the elasticity and original length of the spring, and the relevant dimensions of the housing, pull rod, ferrule, and washer. The specific calculation method is as follows: In the formula, F is the locking force, and the unit is N; is the spring constant, expressed in N / mm; E is the minimum distance between the bottom of the tapered hole of the ferrule (near the ferrule axis) and the end of the ferrule, in mm; The thickness of the clamped structure is in mm. This refers to the thickness of the bottom of the outer casing, in mm. The thickness of the washer is in mm; D is the minimum distance between the edge of the recess in the tie rod and the cylindrical section with a larger cross-section, in mm.

[0015] In addition, the distance between the edge of the opening on the side of the outer shell and the bottom surface of the cylinder, the distance between the thread on the side of the pull rod and the bottom surface of the larger cylinder, the thickness of the clamped structure, and dimension D must satisfy the following relationships: .

[0016] Secondly, the present invention provides a method for using an aircraft EWIS cable quick-locking device, comprising the following steps: Based on the thickness, aperture, and clamping force requirements of the structure being clamped, select a matching quick-locking device and determine the spring specifications and washer thickness. Install the washer, spring, and pull rod into the housing in sequence, and screw the button into the pull rod to form assembly 1; Place the ball into the conical hole of the ferrule and screw in the nut, ensuring that the nut covers the ball, to form assembly 2; Place assembly 1 and assembly 2 on both sides of the clamped structure, align them with the holes on the clamped structure, and press the button to extend the pull rod. Rotate the assembly 1 so that the ball screws in along the spiral groove at the end of the pull rod and falls into the recess at the end of the spiral groove of the pull rod, thereby locking it in place; The cable is secured to the clamp, the clamp is installed on the end face of the clamp, and tightened with screws; When it is necessary to remove, press the button firmly and rotate the assembly 1 in the opposite direction so that the ball rolls out of the recess at the end of the pull rod spiral groove, and the assembly 1 and assembly 2 will separate.

[0017] Compared with existing technologies, the advantages of this invention are as follows: Reliable locking and excellent anti-loosening performance. Through the mechanical self-locking structure of the ball and the spiral groove of the pull rod, combined with the continuous preload provided by the spring, a composite anti-loosening mechanism is formed. This effectively resists high-frequency vibrations and impacts during aircraft flight, fundamentally preventing safety hazards caused by "vibration loosening" and ensuring the stability of cable fixation. Convenient and efficient operation. The "press-rotate" locking method requires no special tools and can be completed with one hand in the confined space of an aircraft, significantly reducing operational difficulty and improving the efficiency of EWIS harness installation, debugging, and maintenance, especially suitable for the frequent adjustments required during flight testing. Controllable and scientifically designed clamping force. A clear formula for calculating the clamping force is provided, allowing for precise selection of spring specifications and washer thickness based on actual conditions such as the thickness of the clamped object. This enables predictable and adjustable clamping force, adapting to different working conditions.

[0018] The above general description and the following detailed description are exemplary and explanatory only, and are not intended to limit this disclosure.

[0019] Other features and aspects of this disclosure will become clearer from the following detailed description of exemplary embodiments with reference to the accompanying drawings. Attached Figure Description

[0020] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0021] Figure 1 This is a front view of the aircraft EWIS cable quick-locking device provided in an embodiment of the present invention; Figure 2 This is a front structural cross-sectional view of the aircraft EWIS cable quick-locking device provided in an embodiment of the present invention; Figure 3 This is a front structural cross-sectional view of the aircraft EWIS cable quick-locking device provided in an embodiment of the present invention; Figure 4 This is a front structural cross-sectional view of the aircraft EWIS cable quick-locking device provided in an embodiment of the present invention; Figure 5 This is a front structural cross-sectional view of the aircraft EWIS cable quick-locking device provided in an embodiment of the present invention; Figure 6 This is a front structural cross-sectional view of the aircraft EWIS cable quick-locking device provided in an embodiment of the present invention.

[0022] The components are: 1. outer shell; 2. pull rod; 3. ferrule; 4. nut; 5. button; 6. spring; 7. washer; 8. ball. Detailed Implementation

[0023] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of the embodiments. Based on the embodiments of this application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of this application.

[0024] In the description of this application, it should be understood that the terms "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application 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. Therefore, they should not be construed as limitations on this application.

[0025] The terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this application, unless otherwise stated, "a plurality of" means two or more.

[0026] In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "linking" 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 between two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0027] See Figures 1-6 As shown in the first embodiment, a quick-locking device for aircraft EWIS cables according to an embodiment of this application includes: The outer shell 1 is a cylindrical structure with a bottom and a circular opening at the bottom. An opening is provided at the top of the side wall of the outer shell 1. The pull rod 2 is a variable cross-section cylindrical structure. The top cylindrical cross-section of the pull rod 2 is larger than that of the bottom cylindrical cross-section. The outer diameter of the short cross-section cylinder of the pull rod 2 is smaller than the inner diameter of the bottom opening of the outer shell 1. The outer diameter of the large cross-section cylinder of the pull rod 2 is larger than the inner diameter of the bottom opening of the outer shell 1, but smaller than the inner diameter of the outer shell 1. The top of the pull rod 2 is provided with a threaded hole, and the bottom of the pull rod 2 is provided with a spiral groove. The cross-section of the spiral groove is circular, and the center of the spiral groove is located outside the bottom of the pull rod 2. The top of the spiral groove is provided with a circular recess. The distance between the edge of the recess and the bottom of the pull rod is 0.1~0.5mm smaller than the distance between the turning point of the spiral groove and the recess and the bottom of the pull rod. The pull rod 2 is disposed inside the outer shell 1. The sleeve 3 is a variable cross-section cylinder with a top cross-section smaller than the bottom cross-section. The bottom of the sleeve 3 is provided with a threaded hole, the top of the sleeve 3 is provided with an axial opening, the outer side wall of the top of the sleeve 3 is provided with an external thread, and the side wall of the top of the sleeve 3 is provided with a tapered hole facing the axis. The bottom of the pull rod 2 extends into the opening at the top of the sleeve 3. Nut 4, whose internal thread matches the external thread of the ferrule 3, and the nut 4 is threadedly connected to the top of the ferrule 3; Button 5 includes a metal stud and a ball handle. The metal stud and the ball handle are integrally formed. The metal stud matches the threaded hole at the top of the pull rod 2 and is threadedly connected to the threaded hole at the top of the pull rod 2. Spring 6 is a helical spring, whose inner diameter is larger than the outer diameter of the bottom of the pull rod 2 and smaller than the outer diameter of the top of the pull rod 2. Spring 6 is disposed inside the outer shell 1 and sleeved on the outer side of the pull rod 2. Washer 7 has an inner diameter larger than the outer diameter of the bottom of the pull rod 2, and the outer diameter of the washer 7 is smaller than the inner diameter of the outer shell 1; The ball 8 is spherical, and its outer diameter matches the inner diameter of the spiral groove. The ball 8 is in a rolling connection with the spiral groove.

[0028] In some specific embodiments, the outer shell 1 is made of aluminum alloy or polymer material, and the opening at the top of the outer shell 1 is circular, elliptical, waist-shaped or rectangular, and the inner diameter of the opening at the top of the outer shell 1 is larger than the outer diameter of the metal stud.

[0029] In some specific embodiments, the tie rod 2 is made of alloy steel or titanium alloy.

[0030] In some specific embodiments, the bottom diameter of the pull rod 2 is 6.35 mm or 4.3 mm.

[0031] In some specific embodiments, the spiral grooves at the bottom of the pull rod 2 are arranged symmetrically along the axial direction, and the number is three.

[0032] In some specific embodiments, the axial opening at the top of the sleeve 3 matches the bottom of the pull rod 2, the bottom diameter of the tapered hole at the top of the sleeve 3 is smaller than the outer diameter of the ball 8, the top diameter of the tapered hole at the top of the sleeve 3 is larger than the diameter of the ball 8, and the axial arrangement of the tapered holes is the same as the spiral groove of the pull rod.

[0033] In some specific embodiments, the threaded hole at the bottom of the sleeve 3 is a fine threaded hole with a specification of M4×0.5 or M5×0.5.

[0034] In some specific embodiments, there are two buttons 5, which are arranged symmetrically along the axis of the pull rod 2.

[0035] In some specific embodiments, the locking force of the aircraft EWIS cable quick-locking device is determined based on the thickness of the clamped object, the elasticity and original length of the spring 6, and the relevant dimensions of the housing 1, pull rod 2, ferrule 3, and washer. The specific calculation method is as follows: In the formula, F is the locking force, and the unit is N; is the spring constant, expressed in N / mm; E is the minimum distance between the bottom of the tapered hole of the ferrule (near the ferrule axis) and the end of the ferrule, in mm; The thickness of the clamped structure is in mm. This refers to the thickness of the bottom of the outer casing, in mm. The thickness of the washer is in mm; D is the minimum distance between the edge of the recess in the tie rod and the cylindrical section with a larger cross-section, in mm.

[0036] In addition, the distance between the edge of the opening on the side of the outer shell and the bottom surface of the cylinder, the distance between the thread on the side of the pull rod and the bottom surface of the larger cylinder, the thickness of the clamped structure, and dimension D must satisfy the following relationships: .

[0037] A second embodiment of the method of using an aircraft EWIS cable quick-locking device according to an embodiment of this application includes the following steps: S100. Based on the thickness, aperture, and clamping force requirements of the structure being clamped, select a matching quick-locking device and determine the spring specifications and washer thickness. S200. Install the washer, spring and pull rod into the housing in sequence, and screw the button into the pull rod to form assembly 1. S300. Place the ball into the conical hole of the sleeve and screw in the nut, ensuring that the nut covers the ball, to form assembly 2. S400. Place assembly 1 and assembly 2 on both sides of the clamped structure, align them with the holes on the clamped structure, and press the button to extend the pull rod. S500, rotating assembly 1, causes the ball to rotate along the spiral groove at the end of the pull rod and fall into the recess at the end of the spiral groove of the pull rod, thereby locking it; S600. Secure the cable to the clamp, install the clamp on the end face of the sleeve, and tighten it with screws; S700: When it is necessary to remove it, press the button firmly and rotate the assembly 1 in the opposite direction so that the ball rolls out of the recess at the end of the pull rod spiral groove, and the assembly 1 and assembly 2 will be separated.

[0038] It should be understood that by clarifying the structural parameters and assembly relationships of eight core components, including the outer shell 1, pull rod 2, and clamp 3, a basic system of "power transmission-guidance-locking-pre-tightening" is constructed. The outer shell 1 provides the mounting base for the whole, with an opening at the bottom for the pull rod 2 to extend out, and an opening on the top side to reserve operating space for the button 5; the variable cross-section design of the pull rod 2 restricts its own axial displacement, the spiral groove guides the movement of the ball 8, and the recess achieves the positioning and locking of the ball 8; the tapered hole of the clamp 3 provides a channel for receiving and guiding the ball 8, and the external thread cooperates with the nut 4 to prevent the ball 8 from falling out; the button 5 is connected to the pull rod 2 through the thread, transmitting "press-rotate" power; the spring 6 provides continuous pre-tightening force, and the washer 7 buffers the force; the ball 8, as the locking medium, switches between the spiral groove and the recess to complete the core actions of locking and unlocking, and the cooperation of each component ensures the realization of the basic functions of the device.

[0039] Using aluminum alloy or polymer materials, it balances lightweight and structural strength, meeting the aircraft's weight reduction goals and compatibility with composite material fuselages; the top opening is designed in various shapes such as round and elliptical, and its size is larger than the outer diameter of the metal stud of button 5. This ensures that the metal stud of button 5 can be smoothly inserted and threadedly connected to the pull rod 2, while not restricting the pressing stroke and rotation angle of button 5, avoiding operational interference, and providing structural support for convenient operation.

[0040] By utilizing the material properties and heat treatment processes of alloy steel or titanium alloy, the mechanical requirements of the pull rod 2 are met. Under the high-frequency vibration and impact environment of aircraft, the pull rod 2 needs to withstand the rolling friction of the ball 8, the preload of the spring 6, and the clamping force after locking. High-strength materials can prevent deformation of the pull rod 2, while wear resistance ensures the long-term structural accuracy of the spiral groove and the recess, maintains the reliable fit between the ball 8 and the groove / recess, and ensures the stability and service life of the locking function.

[0041] The standardized bottom diameter of the pull rod 2 (6.35mm or 4.3mm) accommodates the bore requirements of different installation positions on the aircraft. This diameter forms a clearance fit with the bottom opening of the housing 1 and the axial opening of the sleeve 3, ensuring smooth extension of the pull rod 2 when pressed and no jamming during rotation, while avoiding assembly difficulties due to an excessively large diameter or uneven force due to an excessively small diameter, thus ensuring smooth power transmission and structural fit accuracy.

[0042] The design employs three axially symmetrical spiral grooves to achieve uniform force distribution and stable locking of the ball 8. Each of the three spiral grooves corresponds one-to-one with the tapered hole of the sleeve 3. When the pull rod 2 is rotated, the three balls 8 roll synchronously along the symmetrical spiral grooves, locking into the recesses to form a three-point uniform locking mechanism. This prevents the pull rod 2 from shifting or the locking mechanism from loosening due to unilateral force distribution, enhancing the mechanical self-locking mechanism's ability to resist asymmetric loads caused by aircraft vibrations.

[0043] The precise connection of the locking action is ensured through the matching design of the sleeve 3 and the pull rod 2, as well as the optimization of the tapered hole size. The axial opening of the sleeve 3 and the bottom clearance of the pull rod 2 are matched to eliminate motion interference caused by assembly errors. The design of the tapered hole with "bottom diameter < diameter of ball 8 < top diameter" not only restricts the ball 8 from falling out of the sleeve 3, but also guides the ball 8 to gather towards the axis and accurately engage with the recess of the pull rod 2. The corresponding relationship between the tapered hole and the spiral groove ensures that the movement trajectory of the ball 8 is completely matched with the spiral groove, achieving a seamless connection of "guidance-positioning-locking".

[0044] Selecting fine-pitch threads (M40.5 or M50.5) improves the reliability of clamp installation against loosening. Fine-pitch threads have higher engagement accuracy and anti-loosening ability. When used to install clamps for fixing cables, it can reduce the risk of screws loosening in aircraft vibration environments, ensure a reliable connection between the clamp and the sleeve 3, and thus ensure that the cable is stably constrained, avoiding cable displacement and wear caused by loose threads.

[0045] The two axially symmetrically arranged buttons 5 are designed to suit the confined space of an aircraft cabin. The symmetrical arrangement of the buttons 5 allows operators to perform pressing and rotating actions with one hand from different angles, eliminating the need to adjust body position. This reduces operational difficulty in confined spaces and obstructed visibility environments, improves installation and disassembly efficiency, and is particularly suitable for the frequent adjustments required during flight testing.

[0046] By quantifying parameters and dimensional constraints, the locking force is ensured to be controllable and the locking is effective. The locking force calculation formula achieves precise calculation of the clamping force through the elastic coefficient of spring 6, free length, and dimensions of each component. The specifications of spring 6 and the thickness of washer 7 can be adjusted according to the thickness of the clamped object to ensure that the locking force is sufficient to resist vibration and prevent loosening without damaging the clamped structure. The dimensional relationship "A < E + C + D + t plate" ensures that the extension length of pull rod 2 and the matching stroke of ferrule 3 meet the necessary conditions for ball 8 to engage in the recess, avoiding locking failure due to dimensional mismatch, and ensuring locking reliability from the design level.

[0047] Following a logical flow of "selection-assembly-connection-locking-cable fixing-disassembly," the device achieves efficient application. In the selection phase, device components are matched based on the parameters of the clamped structure and the clamping force requirements to ensure compatibility. In the assembly phase, components are combined into two assemblies, simplifying the installation process. In the locking phase, a coordinated action of "pressing (extending lever 2) - rotating (ball 8 engages in the recess)" quickly completes mechanical self-locking and spring pre-tensioning. In the disassembly phase, the reverse operation disengages ball 8 from the recess, achieving rapid separation. No special tools are required throughout the process, making it suitable for operation in confined spaces and frequent adjustments. Simultaneously, cable fixing via clamps forms a complete closed loop of "device locking - cable fixing."

[0048] The core working principle is based on a composite anti-loosening mechanism of "mechanical self-locking + spring pre-tensioning," combined with a modular assembly and convenient operation design, enabling rapid and reliable locking and unlocking of aircraft EWIS cables under harsh environments such as vibration and impact. The specific process is as follows: First, assembly preparation is performed. Washer 7, spring 6, pull rod 2, and button 5 are combined to form assembly 1 (power and pre-tensioning unit). Ball 8, sleeve 3, and nut 4 are combined to form assembly 2 (locking and cable fixing unit). The modular design adapts to the installation requirements of the confined space inside the aircraft cabin. Next, docking and positioning are performed. Assembly 1 and assembly 2 are placed on both sides of the clamped structure. After aligning the openings, button 5 is pressed, driving pull rod 2 to pass through the opening in the clamped structure and the axial opening of sleeve 3 in assembly 2, completing the initial docking of the two assemblies. Then, the locking action is executed. Rotating button 5 drives pull rod 2 to rotate, and ball 8 in the conical hole of sleeve 3 rolls along the spiral groove of pull rod 2 (spiral groove guide rail). The ball 8, with its conical hole restricting radial displacement, finally engages with the recess at the end of the pull rod 2, forming a mechanical self-lock. Simultaneously, the spring 6 is compressed, generating a continuous pre-tension force that tightly seals the outer shell 1, the clamped structure, and the sleeve 3, preventing the ball 8 from dislodging during vibration. This achieves a dual anti-loosening mechanism of "self-locking + pre-tension." Next, the cable is secured to the clamp, and the clamp is fixed with screws through the fine-threaded hole at the bottom of the sleeve 3, ensuring a reliable connection between the cable and the device. Finally, for unlocking and disassembly, press button 5 firmly (overcoming the pre-tension force of spring 6, creating a gap between the ball 8 and the recess), and rotate button 5 in the opposite direction to rotate the pull rod 2. The ball 8 rolls out of the recess along the spiral groove, separating assembly 1 from assembly 2 for quick disassembly. The entire process requires no special tools, is easy to operate, has controllable clamping force, and is compatible with composite material bodies, effectively solving the pain points of traditional brackets that vibrate and loosen, and are cumbersome to operate.

[0049] Obviously, those skilled in the art can make various modifications and variations to this invention without departing from its spirit and scope. Therefore, if these modifications and variations fall within the scope of the claims of this invention and their equivalents, this invention also intends to include these modifications and variations.

Claims

1. A quick-locking device for aircraft EWIS cables, characterized in that, include: The outer shell is a cylindrical structure with a bottom, and a circular opening at the bottom. An opening is provided at the top of the side wall of the outer shell. The pull rod is a variable cross-section cylindrical structure. The top cylindrical cross-section of the pull rod is larger than the bottom cylindrical cross-section. The outer diameter of the short cross-section cylinder of the pull rod is smaller than the inner diameter of the bottom opening of the outer shell. The outer diameter of the large cross-section cylinder of the pull rod is larger than the inner diameter of the bottom opening of the outer shell, but smaller than the inner diameter of the outer shell. The top of the pull rod is provided with a threaded hole, and the bottom of the pull rod is provided with a spiral groove. The cross-section of the spiral groove is circular, and the center of the spiral groove is located outside the bottom of the pull rod. The top of the spiral groove is provided with a circular recess. The distance between the edge of the recess and the bottom of the pull rod is 0.1~0.5mm smaller than the distance between the turning point of the spiral groove and the recess and the bottom of the pull rod. The pull rod is disposed inside the outer shell. The sleeve is a variable cross-section cylinder with a top cross-section smaller than the bottom cross-section. The bottom of the sleeve is provided with a threaded hole, the top of the sleeve is provided with an axial opening, the outer side wall of the top of the sleeve is provided with an external thread, and the side wall of the top of the sleeve is provided with a tapered hole facing the axis. The bottom of the pull rod extends into the opening at the top of the sleeve. A nut, the internal thread of which matches the external thread of the ferrule, and the nut is threadedly connected to the top of the ferrule; The button includes a metal stud and a ball handle, wherein the metal stud and the ball handle are integrally formed, the metal stud matches the threaded hole at the top of the pull rod, and the metal stud is threadedly connected to the threaded hole at the top of the pull rod; The spring is a helical spring, with an inner diameter larger than the outer diameter of the bottom of the pull rod and smaller than the outer diameter of the top of the pull rod. The spring is disposed inside the housing and sleeved on the outside of the pull rod. The washer has an inner diameter larger than the outer diameter of the bottom of the pull rod, and the outer diameter of the washer is smaller than the inner diameter of the outer shell; The ball is spherical, and its outer diameter matches the inner diameter of the spiral groove. The ball and the spiral groove are in a rolling connection.

2. The quick-locking device for aircraft EWIS cables according to claim 1, characterized in that, The outer shell material is aluminum alloy or polymer material, and the opening at the top of the outer shell is circular, elliptical, waist-shaped or rectangular, with the inner diameter of the opening at the top of the outer shell being larger than the outer diameter of the metal stud.

3. The aircraft EWIS cable quick-locking device according to claim 2, characterized in that, The tie rod is made of alloy steel or titanium alloy.

4. The aircraft EWIS cable quick-locking device according to claim 3, characterized in that, The bottom diameter of the pull rod is 6.35mm or 4.3mm.

5. The aircraft EWIS cable quick-locking device according to claim 4, characterized in that, The spiral grooves at the bottom of the pull rod are arranged symmetrically along the axial direction, and there are 3 of them.

6. The aircraft EWIS cable quick-locking device according to claim 5, characterized in that, The axial opening at the top of the sleeve matches the bottom of the pull rod. The bottom diameter of the tapered hole at the top of the sleeve is smaller than the outer diameter of the ball, and the top diameter of the tapered hole at the top of the sleeve is larger than the diameter of the ball. The axial arrangement of the tapered holes is the same as that of the spiral groove of the pull rod.

7. A quick-locking device for aircraft EWIS cables according to claim 6, characterized in that, The threaded hole at the bottom of the ferrule is a fine threaded hole, with a specification of M4×0.5 or M5×0.

5.

8. A quick-locking device for aircraft EWIS cables according to claim 7, characterized in that, The number of buttons is two, and they are arranged symmetrically along the axis of the pull rod.

9. A quick-locking device for aircraft EWIS cables according to claim 8, characterized in that, The locking force of the aircraft EWIS cable quick-locking device is determined based on the thickness of the clamped object, the elasticity and original length of the spring, and the relevant dimensions of the housing, pull rod, ferrule, and washer. The specific calculation method is as follows: In the formula, F is the locking force, and the unit is N; is the spring constant, expressed in N / mm; E is the minimum distance between the bottom of the tapered hole of the ferrule (near the ferrule axis) and the end of the ferrule, in mm; The thickness of the clamped structure is expressed in mm. This refers to the thickness of the bottom of the outer casing, in mm. The thickness of the washer is in mm; D is the minimum distance between the edge of the recess in the tie rod and the cylindrical section with a larger cross-section, in mm. In addition, the distance between the edge of the opening on the side of the outer shell and the bottom surface of the cylinder, the distance between the thread on the side of the pull rod and the bottom surface of the larger cylinder, the thickness of the clamped structure, and dimension D must satisfy the following relationships: 。 10. A method of using a quick-locking device for aircraft EWIS cables, characterized in that, The quick-locking device for an aircraft EWIS cable as described in any one of claims 1 to 9 comprises the following steps: Based on the thickness, aperture, and clamping force requirements of the structure being clamped, select a matching quick-locking device and determine the spring specifications and washer thickness. Install the washer, spring, and pull rod into the housing in sequence, and screw the button into the pull rod to form assembly 1; Place the ball into the conical hole of the ferrule and screw in the nut, ensuring that the nut covers the ball, to form assembly 2; Place assembly 1 and assembly 2 on both sides of the clamped structure, align them with the holes on the clamped structure, and press the button to extend the pull rod. Rotate the assembly 1 so that the ball screws in along the spiral groove at the end of the pull rod and falls into the recess at the end of the spiral groove of the pull rod, thereby locking it in place; The cable is secured to the clamp, the clamp is installed on the end face of the clamp, and tightened with screws; When it is necessary to remove, press the button firmly and rotate the assembly 1 in the opposite direction so that the ball rolls out of the recess at the end of the pull rod spiral groove, and the assembly 1 and assembly 2 will separate.

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