Low-damage secondary energy-gathered jet cutting device for fiber composite material

Abstract

The invention relates to a low-damage secondary energy-gathered jet cutting device for a fiber composite material. Comprising a buffer protection cover, a linear cutter module, a shaped charge module and an explosive-proof body arranged between the linear cutter module and the shaped charge module. The shaped charge module consists of a plurality of micro shaped charge units which are linearly arranged, and is used for pre-puncturing a row of pre-guide holes to form a continuous stress concentration line and a crack propagation prefabricated path; and the linear cutter module is detonated in a delayed mode, and final cutting is completed along the prefabricated path. According to the method, the problems of material tearing, layering, rough cutting boundary and the like are solved through a pre-guiding-post-cutting cooperation mechanism by means of guiding of prefabricated stress concentration points and sequential control of subsequent cutting, the smoothness and quality of a cutting surface are improved, the fiber damage problem is reduced, and the production efficiency is improved. And the method has a wide application prospect in precise cutting of high-performance composite materials such as carbon fibers and Kevlar used in the fields of aerospace, rail transit, high-performance ships and the like.

Description

Technical Field

[0001] This invention belongs to the field of composite material processing technology, specifically relating to a low-damage two-stage focused jet cutting device for fiber composite materials. Background Technology

[0002] Fiber-reinforced composites, especially carbon fiber composites and basalt fiber composites, have become key material systems for weight reduction and efficiency improvement in modern high-end industrial equipment due to their high specific strength, high specific modulus, excellent fatigue resistance, and designability. Their applications have expanded from aerospace to areas with stringent requirements for lightweighting and performance, such as new energy vehicle bodies, rail transit carriages, high-performance ship hulls, and precision sealed pressure vessels. However, with the deepening of applications, their anisotropy, non-uniformity, and relatively weak interlaminar strength pose serious challenges to machining, especially cutting and separation processes. Traditional mechanical cutting (such as tool cutting and mechanical drilling) or non-traditional cutting (such as water jetting and laser cutting) easily induces a series of damage defects when processing these materials, such as fiber tearing, delamination, and burrs. The quality of the cutting boundary is difficult to control, directly affecting the performance and reliability of the components.

[0003] To address these challenges, the industry has explored various cutting technologies. Linear shaped charge cutters, as a highly efficient separation device, utilize explosive detonation to drive a shaped charge liner, forming a high-speed metal jet to penetrate and cut the target material. They offer advantages such as concentrated energy, extremely short action time, and non-contact operation. However, when cutting composite materials, the cutting effect of traditional linear shaped charge cutters is extremely sensitive to the detonation height and charge parameters. If these parameters are not properly matched, the resulting jet may penetrate insufficiently or excessively, leading to rough cuts, edge tearing, or even large-area interlaminar delamination due to stress wave reflection. Their mechanism is more focused on "penetration-tearing," making it difficult to achieve controllable separation of sensitive structures in composite materials.

[0004] In summary, existing technologies struggle to achieve a good balance between high efficiency, low damage, and strong adaptability when cutting fiber-reinforced composite materials. While linear energy-concentrating cutters are highly efficient, the quality of the cut boundary is difficult to control, easily causing tearing and other damage to the composite material. Conversely, some precision cutting methods may have limitations in efficiency or applicable scenarios. Therefore, there is an urgent need for a new solution for cutting and separating composite materials, enabling precise pre-planning and guidance of crack propagation paths. This would allow for efficient separation while preserving the original properties of the material to the greatest extent possible, meeting the urgent demands of high-end industrial sectors for high-quality, low-damage, and controllable manufacturing processes. Summary of the Invention

[0005] The purpose of this invention is to provide a low-damage secondary focused jet cutting device for fiber composite materials. This solution aims to transform the traditional cutting mode of "passive penetration-tearing" or pre-defect mode into an "active guidance-separation" mode. Through the synergy and release of secondary energy, it solves problems such as fiber tearing, delamination and rough cutting surface during the cutting process, and achieves high-quality, low-damage smooth cutting.

[0006] The technical solution to achieve the purpose of this invention is: a low-damage two-stage shaped charge jet cutting device for fiber composite materials, comprising a buffer protective cover, a linear cutter module and a shaped charge module, and an explosion-proof body disposed between the linear cutter module and the shaped charge module;

[0007] The shaped charge module consists of multiple linearly arranged micro-shaped charge units, which are used to pre-penetrate a row of pre-guided holes to form a continuous stress concentration line and a pre-prepared crack propagation path; the linear cutter module is detonated after a delay and completes the final cut along the pre-prepared path.

[0008] Furthermore, the linear cutter module includes a housing I, a linear cutter charge, a linear shaped charge liner, and a fuse;

[0009] It also includes a positioning plate and a fixing plate.

[0010] The positioning plate is provided with threaded holes, and each micro shaped charge unit is threaded to the positioning plate through the external thread of the housing II; the two ends of the positioning plate are fixed by bolts connecting the fixing plate and the buffer protective cover.

[0011] Furthermore, each miniature shaped charge unit includes a fuze, a casing II, a shaped charge pellet, and a conical shaped charge liner. The fuze is electronically delayed initiation controlled to ensure that the shaped charge module detonates before the linear cutter module.

[0012] Furthermore, the explosion-proof enclosure is a piston-type structure with a lateral pressure relief channel.

[0013] Furthermore, the buffer shield is made of foamed metal or high-damping polymer material to absorb the detonation shock wave and restrain debris; the buffer shield is fixed to the object to be cut by a detachable mechanical connection.

[0014] The linear and conical shaped charge liner materials are made of copper, titanium, titanium alloy, or copper alloy.

[0015] Shell I and Shell II are made of steel or high-strength aluminum alloy;

[0016] The linear cutter module uses end-initiation; the shaped charge module uses center-synchronized initiation.

[0017] The positioning plate is made of low-damping polymer and is used to position and control the spacing of the shaped charge module.

[0018] Furthermore, the radius r, depth h, and spacing d of the guide holes for the prefabricated path formed by the shaped charge module are determined in the following way:

[0019] ,

[0020] In the formula, r is the radius of the guide hole, which is usually... h is the guide hole depth; d is the guide hole spacing; T is the thickness of the cutting plate; B is the width of the pre-cutting path, the width of which satisfies... k is the damage zone expansion coefficient, representing the outer radius of the damage zone. The ratio of the guide hole radius r to 1 is reduced by 1, i.e. For composite materials, the value is usually between 0.5 and 2, obtained through experimental measurement;

[0021] First, determine the radius r and depth h of the pilot hole. The pre-pilot hole depth h is controlled by adjusting the charge amount and detonation height. The target depth must form a continuous weakened surface in the thickness direction, and the relationship is determined by empirical formulas. Then, the guide hole spacing d is calculated using the damage factor D relationship:

[0022] ,

[0023] The upper limit of the pre-guide hole spacing d opt Calculate according to the following formula:

[0024] ,

[0025] in, The net stress generated by the main cutting load between the holes, namely the peak value of the dynamic tensile stress caused by the stress wave generated by the subsequent linear cutter and the impact of the previous jet in the ligament region between the pre-guided holes, is obtained by recording the peak value of the tensile stress by attaching dynamic strain gauges to the ligament region between the pre-guided holes. This is the geometric correction factor.

[0026] Furthermore, the charge radius of each micro-shaped charge unit Calculated based on engineering empirical formulas ,in This is an empirical coefficient, with a value range of 3 to 5;

[0027] The charge amount N is calculated based on the pilot hole depth h using steady penetration theory, i.e. ,in This is a depth coefficient, applicable to typical carbon fiber plates, PETN-based explosives, and copper shaped charge liner. ;

[0028] Drug liner cone angle A large cone angle is adopted to meet the requirements. ,in The jet divergence angle is 0° to 8° for a shaped charge liner with a cone angle of 60° to 120°.

[0029] The wall thickness of the propellant liner in the shaped charge structure satisfy: ,in This is an empirical coefficient, with a value between 0.015 and 0.03. For the density of the explosive, For the detonation velocity of the explosive, The dynamic flow stress of the propellant shroud under high pressure and high strain rate.

[0030] Furthermore, the effective specific kinetic energy of the cutting jet from the linear cutter module... The dynamic separation specific energy greater than that required for material separation along the pre-guided path Characterized as:

[0031] ,

[0032] in, Let be the kinetic energy component of the jet perpendicular to the target plate. To maximize the effective area; by optimizing the geometry of the shaped charge liner and the detonation method. This enables efficient cutting with minimal main charge energy.

[0033] Based on effective specific kinetic energy Determine the linear charge density of the linear cutter , The energy conversion efficiency is 0.15 to 0.25, and Q is the specific energy of the explosive.

[0034] Linear cutter liner linear density For drug-type liner wall thickness ,in Density of the drug-formed shroud; The cone angle has a range of values. .

[0035] Furthermore, the minimum safe thickness of the explosion-proof enclosure Based on the one-dimensional stress wave attenuation theory, the critical condition for the impact initiation of the subsequent charge must be met, namely:

[0036] ,

[0037] in, The initial impact pressure of the front-end interface. Where is the damping coefficient of the explosion-proof material, and n is the geometric attenuation factor. x is the critical pressure for the impact detonation of the subsequent explosive, and x0 is the distance between the explosion-proof body's blast-facing surface and the detonation position.

[0038] Furthermore, the fuse delay satisfy Where k is the safety factor, with a value ranging from 1.2 to 1.5;

[0039] Effective action time ,in These are empirical parameters; the stress wave arrival time and damage completion time are obtained through experiments; propagation time... S is the stress wave propagation distance, i.e., the distance between the centers of action of the linear cutter module and the shaped charge module, and C is the average wave velocity in the material.

[0040] Furthermore, the cutting device is arc-shaped as a whole, with multiple cutting devices connected end to end along a circular path to form an integral structure, which performs circumferential cutting.

[0041] Compared with the prior art, the significant advantages of this invention are:

[0042] (1) By using the two-stage collaborative cutting mechanism of “pre-guided-precision cutting”, the micro-focused jet perforation technology of linear array is organically coupled with the linear cutter technology. By actively guiding the crack propagation through the pre-made defect path, the disorderly tearing and delamination of fiber composite materials are fundamentally avoided.

[0043] (2) A design method based on dynamic fracture mechanics and stress wave theory is introduced. By theoretically modeling and optimizing key parameters such as pre-piercing spacing, depth, two-stage energy ratio and detonation delay, the quantitative design and precise control of the entire cutting process can be achieved.

[0044] (3) By using a functional piston-type explosion-proof body with lateral pressure relief, not only are the two-stage explosive charges isolated, but also the harmful shock waves are actively managed and dispersed, ensuring a stable environment for subsequent cutting.

[0045] (4) The device integrates control, detonation and protection. Through the buffer protective cover and detachable and reinstallable interface, it ensures operational safety and ease of use. Attached Figure Description

[0046] Figure 1 This is a three-dimensional structural schematic diagram of the low-damage two-stage focused jet cutting device for fiber composite materials according to the present invention;

[0047] Figure 2 This is a partial cross-sectional view of the low-damage two-stage focused jet cutting device for fiber composite materials according to the present invention;

[0048] Figure 3 This is a schematic diagram of the cross-sectional structure of the low-damage two-stage focused jet cutting device for fiber composite materials according to the present invention;

[0049] Figure 4 This is a schematic diagram of the vertical cross-section of the low-damage two-stage focused jet cutting device for fiber composite materials according to the present invention;

[0050] Figure 5 This is a schematic diagram of the linear cutter module structure of the low-damage two-stage focused jet cutting device for fiber composite materials according to the present invention;

[0051] Figure 6 This is a schematic diagram of the shaped charge module unit structure of the low-damage two-stage shaped charge jet cutting device for fiber composite materials of the present invention;

[0052] Figure 7 This is a schematic diagram of the annular cutting structure of the low-damage two-stage focused jet cutting device for fiber composite materials according to the present invention;

[0053] Figure 8 This is a schematic diagram of the cutting process of the low-damage two-stage shaped charge jet cutting device for fiber composite materials of the present invention; wherein (a) the device is ready; (b) the shaped charge module acts to form a pre-guide hole; and (c) the linear cutter module detonates to complete the final cut.

[0054] Explanation of reference numerals in the attached figures:

[0055] 1-Buffer protection cover, 2-Linear cutter module, 3-Explosion-proof body, 4-Shaped charge module, 5-Positioning plate, 6-Fixing plate, 7-Shell I, 8-Linear cutter charge, 9-Linear charge liner, 10-Bolt, 11-Fuse, 12-Shell II, 13-Shaped charge charge, 14-Conical charge liner. Detailed Implementation

[0056] The present invention will now be described in further detail with reference to the accompanying drawings.

[0057] This device employs a series-connected two-stage energy release structure, based on a collaborative working mode of "pre-guidance, followed by precision cutting." By precisely controlling the spatiotemporal sequence and energy ratio of the two stages, it actively manages the dynamic fracture process of the material, fundamentally improving cutting quality. The device mainly includes a buffer protective layer, a shaped charge module, an explosion-proof body, and a linear cutter module. All modules are integrated and encapsulated within a housing, forming a stable and easy-to-install integrated cutting tool.

[0058] A low-damage two-stage shaped charge jet cutting device for fiber composite materials includes a buffer protective cover 1, a linear cutter module 2, an explosion-proof body 3, a shaped charge module 4, a positioning plate 5, and a fixing plate 6. The linear cutter module 2 includes a housing I 7, a linear cutter charge 8, a linear shaped charge liner 9, and a fuse. The shaped charge module 4 includes at least one row of linearly arranged shaped charge units, each unit including a fuse 11, a housing II 12, a shaped charge charge 13, and a conical shaped charge liner 14. An explosion-proof body 3 with a lateral pressure relief channel is provided between the linear cutter module 2 and the shaped charge module 4. The linear cutter module 2 and the explosion-proof body 3 are fixedly positioned to the buffer protective cover 1 by bolts. The shaped charge module 4 is threaded to the positioning plate 5 through the external thread of the housing II 12. The positioning plate 5 and the buffer protective cover 1 are fixed at both ends by bolts connected to the fixing plate 6. The shaped charge module 4 is located in the cutting direction of the linear cutter module 2 and is used to form a row of pre-guided holes on the material to be cut; the linear cutter module 2 is used to complete the final cut along the path formed by the pre-guided holes; the fuse 11 performs electronic delay detonation control to control the shaped charge module 4 to detonate before the linear cutter module 2 and to achieve precise and adjustable delay control between the two.

[0059] The charge quantity, charge spacing, and detonation height configuration of the shaped charge unit are used to penetrate the fiber composite plate to form a row of pre-guided holes with a depth of 1 / 3 to 2 / 3 of the plate thickness and a spacing optimized according to dynamic fracture toughness, so as to form a continuous stress concentration and crack propagation guidance path.

[0060] The explosion-proof body 3 is a piston-type structure with a lateral pressure relief channel, which is used to laterally disperse the main shock wave and products generated by the detonation of the front-stage shaped charge module 4, so as to avoid affecting the jet forming and cutting stability of the subsequent linear cutter module 2.

[0061] The buffer shield 1 is made of foamed metal or high-damping polymer material and is used to absorb the detonation shock wave and restrain the debris; the buffer shield 1 is fixed to the object to be cut by a detachable mechanical connection.

[0062] The fuse 11 is electronically delayed initiation control. The delay can be preset or adaptively adjusted according to different fiber composite material types and thicknesses to achieve optimal matching and synergistic effect of two-stage cutting energy.

[0063] The linear shaped charge liner 9 and the conical shaped charge liner 13 are made of copper or titanium and their alloys.

[0064] Shell I7 and shell II12 are made of steel or high-strength structural aluminum.

[0065] The linear cutter module 3 adopts an end-initiation method; the shaped charge module 6 adopts a center-synchronous initiation method.

[0066] The positioning plate 5 is made of low-damping polymer and is used to position and control the spacing of the shaped charge module 4.

[0067] The smallest constituent units of multiple devices are connected end to end along a circular path to form an integral structure or a 4-bisecting arc structure, which can be used for circumferential cutting.

[0068] The shaped charge module, used for active guidance, consists of multiple micro-shaped charge units arranged in one or more rows of linear arrays. Each shaped charge unit includes a shell, a fuse, a shaped charge grain, and a conical shaped charge liner. This module is triggered by central synchronous detonation. Its function is to utilize the high energy density of the shaped charge jet to pre-perforate a row of micro-holes with theoretically optimized depth and spacing along the target cutting line of the fiber composite plate to be cut. These holes are not isolated defects, but rather artificially constructed continuous stress concentration lines and pre-established crack initiation points within the material, laying a definite, low-energy-threshold separation path for the subsequent main cut. To achieve quantitative design and optimization of the pre-cutting path, a damage factor D is introduced to quantify the weakening effect of the pre-guided holes on the predetermined cutting path. Its range is 0 to 1, where D=0 indicates no material damage, and D=1 indicates complete separation along the predetermined path. A critical value is defined for the damage factor. (Typically, the value is taken as 0.7~0.85), satisfying the requirement of guiding the stable propagation of the crack without excessively damaging the material and causing excessive deformation on the back side. The damage factor D satisfies the following formula:

[0069]

[0070] In the formula, r is the radius of the guide hole, which is usually... h is the guide hole depth; d is the guide hole spacing; T is the thickness of the cutting plate; B is the width of the pre-cutting path, which generally meets the following requirements to obtain a smooth cut and cover the pre-damaged area. k is the damage zone expansion coefficient, representing the outer radius of the damage zone. The ratio of the guide hole radius r to 1 is reduced by 1, i.e. For composite materials, the value is usually between 0.5 and 2, which can be obtained through experimental measurement.

[0071] The module structure is first determined based on experience or process constraints, prioritizing the radius r and depth h of the pre-guided hole. The pre-guided hole depth h is controlled by adjusting the charge amount and detonation height. The target depth must form a continuous weakened surface in the thickness direction, ensuring significant damage while avoiding back-side spalling and excessive structural weakening. The relationship is determined using empirical formulas. Then, the guide hole spacing d is calculated using the damage factor D relationship.

[0072]

[0073] Furthermore, the pre-guided hole spacing d is verified for crack propagation stability according to the principles of dynamic fracture mechanics to ensure that the main cutting stress wave can drive the stable connection of the inter-hole cracks. The dot is estimated based on the following formula:

[0074]

[0075] in, The net stress generated by the main cutting load between the holes, i.e. the peak value of dynamic tensile stress caused by the stress wave generated by the subsequent linear cutter and the impact of the preceding jet in the ligament region between the pre-guided holes, can be obtained by attaching dynamic strain gauges to the ligament region between the pre-guided holes and recording the peak value of tensile stress. This is a geometric correction factor. Ultimately, it simultaneously satisfies the theoretical design requirements for the guide hole section, including the guide hole radius r, depth h, and spacing d of the pre-cut path, thereby guiding the structural design of the shaped charge section.

[0076] Charge radius Estimate based on engineering empirical formulas ,in This is an empirical coefficient, typically 3-5; the charge amount N is calculated based on the pilot hole depth h using steady penetration theory, i.e. ,in This is a depth coefficient, related to explosive properties and target impedance. For typical carbon fiber plates, PETN-based explosives, and copper shaped charges... ; Drug liner cone angle A large cone angle is adopted to meet the requirements. ,in The jet divergence angle is typically taken as 0° to 8° for shaped charge liner cones with a cone angle of 60° to 120°. The wall thickness of the shaped charge liner in a shaped charge structure is... satisfy ,in The empirical coefficient is between 0.015 and 0.03. For the density of the explosive, For the detonation velocity of the explosive, For the dynamic flow stress of the propellant liner under high pressure and high strain rate, for copper .

[0077] The linear cutter module is the execution unit that completes the final separation. Located after the shaped charge module, it mainly consists of a cutter charge and a linear shaped charge liner. This module uses end-initiation, and its function is to drive the crack through a predetermined path that has been significantly weakened, achieving rapid and smooth penetration and connection, thus completing the complete separation of materials. Because the material continuity has been pre-disrupted and the crack propagation path has been effectively guided, the linear cutter can complete the cut efficiently and accurately with relatively small forces, thereby minimizing excessive stress on the material and avoiding disordered tearing. Its core design principle is to ensure the effective specific kinetic energy of the formed cutting jet. The dynamic separation specific energy greater than that required for material separation along the pre-guided path . It can be characterized as:

[0078]

[0079] in, Let be the kinetic energy component of the jet perpendicular to the target plate. This refers to the effective area. By optimizing the geometry of the shaped charge liner and the detonation method, the effective area is maximized. This achieves efficient cutting with minimal main charge energy. Based on effective specific kinetic energy... Determine the linear charge density of the linear cutter Where B is the preset cutting width. Where is the energy conversion efficiency (typically 0.15~0.25), and Q is the specific energy of the explosive. Therefore, the linear density of the shaped charge liner in the linear cutter... For drug-type liner wall thickness ,in Density of the drug-formed shroud; The cone angle is used to form a "blade-shaped" jet with a relatively large effective width and uniform energy distribution; the value range is [value missing]. .

[0080] The explosion-proof enclosure is the core component ensuring the independent and orderly operation of the two stages. It employs a piston-type explosion-proof enclosure with lateral pressure relief channels. Its function is to actively manage the detonation products and shock waves of the preceding stage, allowing the subsequent shaped charge jet to function normally through its central channel. Simultaneously, it rapidly discharges and dissipates most of the generated lateral shock waves and high-speed fragments through the lateral pressure relief channels. This effectively prevents the detonation of the preceding stage from interfering with the stable shaping of the subsequent linear cutter jet, ensuring that the subsequent cutting can proceed without interference. Its minimum safe thickness... Based on the one-dimensional stress wave attenuation theory, the critical condition for impact initiation of the subsequent charge must be met, satisfying:

[0081]

[0082] in, The initial impact pressure of the front-end interface. Where is the damping coefficient of the explosion-proof material, and n is the geometric attenuation factor. x is the critical pressure for the impact detonation of the subsequent explosive, and x0 is the distance between the explosion-proof enclosure's blast-facing surface and the detonation position. The device employs a piston-type structure with a pressure relief channel, which, while meeting the aforementioned safety thickness, actively disperses the lateral shock wave and products from the preceding stage.

[0083] Electronic delay-based detonation control is crucial for two-stage coordination, ensuring the shaped charge module detonates first, and then automatically triggers the linear cutter module after a precisely calculated and adjustable delay. Delay time. The design is based on the propagation and attenuation characteristics of stress waves in materials, aiming to ensure that the cutting action intervenes precisely when the instantaneous stress field caused by pre-perforation is at its optimal state, thereby achieving optimal coupling of the two-stage energy and stable crack drive. Its detonation delay is determined according to the laws governing stress wave propagation and material response. Considering the stress wave propagation distance s (the distance between the centers of action of the linear cutter module and the shaped charge module) and the average wave velocity c in the material, the propagation time can be calculated. Simultaneously considering the amplitude attenuation caused by material damping, the effective action time... ,in This is an empirical parameter, determined by obtaining the stress wave arrival time and damage completion time through experiments. (Delay) Should meet , where k is the safety factor (taken as 1.2~1.5).

[0084] The buffer cover is made of foamed metal or high-damping polymer material and covers the entire exterior of the device. Its main purpose is to absorb and attenuate the residual shock wave generated when the device is working, restrain flying debris, and protect other areas to be cut and the surrounding environment, reflecting the engineering design concept of a safe and controllable operating device.

[0085] Based on modular design, the basic units of this invention can be flexibly arranged along a predetermined cutting path. In particular, by arranging multiple units along a circular path and integrating control, a circular cutting system for nonlinear application scenarios can be constructed. Through multi-point synchronous detonation technology, quasi-synchronous and clean separation on the circumference can be achieved, which is significantly superior to traditional explosive separation.

[0086] This invention's device is also applicable to applications requiring ring-shaped cutting, achieved through modular splicing ring devices and integrated flexible ring devices. The modular splicing method connects multiple linear or slightly curved modular units end-to-end via mechanical interfaces, fixing them to the separation surface. The circuits and detonation lines of each module are connected in series via connectors and controlled by a unified delayed detonation mechanism. To ensure the synchronicity of the entire ring-shaped cutting path, the control system employs an N-point symmetrical synchronous detonation strategy to reduce separation asynchrony. The integrated flexible ring device integrates and encapsulates this device within a continuous flexible composite material, forming a ring-shaped band that can be wound around the cabin.

[0087] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A low-damage two-stage focused jet cutting device for fiber composite materials, characterized in that, It includes a buffer protective cover (1), a linear cutter module and a shaped charge module, and an explosion-proof body (3) disposed between the linear cutter module and the shaped charge module. The shaped charge module consists of multiple linearly arranged micro-shaped charge units, which are used to pre-penetrate a row of pre-guided holes to form a continuous stress concentration line and a pre-prepared crack propagation path; the linear cutter module is detonated after a delay and completes the final cut along the pre-prepared path.

2. The cutting device according to claim 1, characterized in that, The linear cutter module includes a housing I (7), a linear cutter charge (8), a linear shaped charge liner (9), and a fuse; It also includes a positioning plate (5) and a fixing plate (6). The positioning plate (5) is provided with threaded holes. Each micro shaped charge unit is threadedly connected to the positioning plate (5) through the external thread of the housing II (12). The two ends of the positioning plate (5) are fixed by bolts to the fixing plate (6) and the buffer protective cover (1).

3. The cutting device according to claim 2, characterized in that, Each miniature shaped charge unit includes a fuse (11), a casing II (12), a shaped charge charge (13), and a conical shaped charge liner (14). The fuse (11) is electronically delayed to control the detonation of the shaped charge module (4) before the linear cutter module (2).

4. The cutting device according to claim 3, characterized in that, The explosion-proof body (3) is a piston-type structure with a lateral pressure relief channel.

5. The cutting device according to claim 3, characterized in that, The buffer shield (1) is made of foamed metal or high-damping polymer material and is used to absorb the detonation shock wave and confine the debris. The buffer protective cover (1) is fixed to the object to be cut by a detachable mechanical connection; The linear shaped charge liner (9) and the conical shaped charge liner (13) are made of copper, titanium, titanium alloy or copper alloy; Shell I (7) and Shell II (12) are made of steel or high-strength aluminum alloy; The linear cutter module uses end-initiation; the shaped charge module uses center-synchronized initiation. The positioning plate (5) is made of low-damping polymer and is used to position and control the spacing of the shaped charge module (4).

6. The cutting device according to claim 3, characterized in that, The radius r, depth h, and spacing d of the guide holes for the prefabricated path formed by the shaped charge module are determined in the following way: ， In the formula, r is the radius of the guide hole, which is usually... h is the guide hole depth; d is the guide hole spacing; T is the thickness of the cutting plate; B is the width of the pre-cutting path, the width of which satisfies... k is the damage zone expansion coefficient, representing the outer radius of the damage zone. The ratio of the guide hole radius r to 1 is reduced by 1, i.e. For composite materials, the value is usually between 0.5 and 2, obtained through experimental measurement; First, determine the radius r and depth h of the pilot hole. The pre-pilot hole depth h is controlled by adjusting the charge amount and detonation height. The target depth must form a continuous weakened surface in the thickness direction, and the relationship is determined by empirical formulas. Then, the guide hole spacing d is calculated using the damage factor D relationship: ， The upper limit of the pre-guide hole spacing d opt Calculate according to the following formula: ， in, The net stress generated by the main cutting load between the holes, namely the peak value of the dynamic tensile stress caused by the stress wave generated by the subsequent linear cutter and the impact of the previous jet in the ligament region between the pre-guided holes, is obtained by recording the peak value of the tensile stress by attaching dynamic strain gauges to the ligament region between the pre-guided holes. This is the geometric correction factor.

7. The cutting device according to claim 6, characterized in that, The charge radius of each micro shaped charge unit Calculated based on engineering empirical formulas ,in This is an empirical coefficient, with a value range of 3 to 5; The charge amount N is calculated based on the pilot hole depth h using steady penetration theory, i.e. ,in This is a depth coefficient, applicable to typical carbon fiber plates, PETN-based explosives, and copper shaped charge liner. ; Drug liner cone angle A large cone angle is adopted to meet the requirements. ,in The jet divergence angle is 0° to 8° for a shaped charge liner with a cone angle of 60° to 120°. The wall thickness of the propellant liner in the shaped charge structure satisfy: ,in This is an empirical coefficient, with a value between 0.015 and 0.

03. For the density of the explosive, For the detonation velocity of the explosive, The dynamic flow stress of the propellant shroud under high pressure and high strain rate.

8. The cutting device according to claim 7, characterized in that, Effective specific kinetic energy of the cutting jet from the linear cutter module The dynamic separation specific energy greater than that required for material separation along the pre-guided path Characterized as: ， in, Let be the kinetic energy component of the jet perpendicular to the target plate. To maximize the effective area; by optimizing the geometry of the shaped charge liner and the detonation method. This enables efficient cutting with minimal main charge energy. Based on effective specific kinetic energy Determine the linear charge density of the linear cutter , The energy conversion efficiency is 0.15 to 0.25, and Q is the specific energy of the explosive. Linear cutter liner linear density For drug-type liner wall thickness ,in Density of the drug-formed shroud; The cone angle has a range of values. .

9. The cutting device according to claim 8, characterized in that, Minimum safe thickness of explosion-proof enclosure Based on the one-dimensional stress wave attenuation theory, the critical condition for the impact initiation of the subsequent charge must be met, namely: ， in, The initial impact pressure of the front-end interface. Where is the damping coefficient of the explosion-proof material, and n is the geometric attenuation factor. x is the critical pressure for the impact detonation of the subsequent explosive, and x0 is the distance between the explosion-proof body's explosion-facing surface and the detonation position. Delay of fuse (11) satisfy Where k is the safety factor, with a value ranging from 1.2 to 1.5; Effective action time ,in These are empirical parameters; the stress wave arrival time and damage completion time are obtained through experiments; propagation time... S is the stress wave propagation distance, i.e., the distance between the centers of action of the linear cutter module and the shaped charge module, and C is the average wave velocity in the material.

10. A cutting device according to any one of claims 1-9, characterized in that, The cutting device is arc-shaped, with multiple cutting devices connected end to end along a circular path to form a whole structure, which performs circumferential cutting.

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