A multiple-fragment spatial distribution and time-to-target interval adjustable sabot

Abstract

The application discloses a multi-fragment space distribution and target time interval adjustable projectile holder, and relates to the technical field of pneumatic launching test equipment. The projectile holder comprises an outer bearing shell, a multi-channel core body detachably installed in the outer bearing shell, and an axial positioning member. The outer bearing shell is adapted to the inner cavity of a barrel. The multi-channel core body is provided with a plurality of fragment channels arranged according to a predetermined array and used for accommodating fragments, and the transverse coordinates of the fragment channels determine the space distribution of the fragments on a target. The axial positioning member is fixed in the channels and provides an axial positioning reference surface for the fragments. The initial loading depth of the fragments is adjusted by changing the axial position of the axial positioning member, so that the target time interval is controlled. The application can independently and cooperatively preset the space distribution and target time sequence of a fragment group without changing the main structure of a launching device, and has the advantages of compact structure, flexible adjustment and good repeatability.

Description

Technical Field

[0001] This invention relates to the field of pneumatic launch test equipment technology, and in particular to a projectile sabot with adjustable spatial distribution of multiple fragments and target arrival time interval. Background Technology

[0002] Gas pressure-driven launching devices (such as air cannons and light gas cannons) are core equipment for conducting high-speed impact dynamics tests and are widely used in research fields such as material dynamic response and structural impact resistance evaluation. In these tests, the sabot, as a key component that bears and guides the launched object, directly affects the reliability and repeatability of the test results.

[0003] In real-world engineering scenarios, the impact loads borne by structures often do not originate from a single projectile, but rather from multiple discrete high-speed fragments acting together within a specific spatial range and in a certain temporal sequence. To realistically reproduce such coupled impact conditions under laboratory conditions, the launching system must be able to simultaneously launch multiple fragments in a single test, ensuring that their impact positions and arrival times in the target area meet preset spatial distribution and temporal requirements.

[0004] However, existing gas-driven launchers and their accompanying sabots are primarily designed for launching single or a small number of simultaneous fragments, focusing on the sabot's load-bearing capacity, gas tightness, in-bore guidance stability, and reliable separation after exiting the barrel. When faced with the requirement of launching multiple fragments, existing technical solutions have the following shortcomings: First, regarding the spatial distribution control of multiple fragments, conventional sabots lack precise means to define and calibrate the lateral launch positions of multiple fragments. The spatial dispersion of the impact points after fragments leave the barrel has poor repeatability, making it difficult to form a pre-set and reproducible spatial array distribution. If multiple launch devices are used in concert to achieve spatial distribution, practical problems such as system complexity, difficulty in synchronous control, and long debugging cycles arise.

[0005] Secondly, in terms of controlling the time interval between multiple fragments, existing solutions rarely consider the order in which different fragments arrive at the target. For fragments launched using a random dispersion method, their relative positions and timing of impact are uncontrollable, failing to meet the requirements for conducting repeatable experiments and parametric comparative studies. If multiple sets of equipment are used for time-division triggering to simulate the time series, the inherent triggering delay and synchronization error will severely affect the accuracy and consistency of the experimental data.

[0006] Furthermore, existing sabot designs primarily prioritize the ability to accommodate and launch multiple fragments, neglecting the joint and independent control of the spatial and temporal coordinates of these fragments. In other words, there is a lack of a comprehensive technical solution that allows for the simultaneous pre-setting of the fragment group spatial array and the target arrival sequence on a single launching device by adjusting the sabot's structural parameters.

[0007] In summary, given the significant limitations of existing gas-driven launch sabots in achieving coordinated control of the spatial distribution of multiple fragments and the time interval between impacts with the target, there is an urgent need in this field to develop a new type of sabot that can achieve precise and adjustable spatiotemporal distribution of multiple fragments through sabot structural innovation without altering the main structure of the launch device. Summary of the Invention

[0008] To address the problems of existing technologies, this invention provides a projectile sabot with adjustable spatial distribution and target arrival time of multiple fragments. It aims to achieve flexible selection and rapid replacement of the fragment channel spatial array without altering the main structure of the launching device through a modular combination of an outer bearing shell and a detachable multi-channel core. Simultaneously, by utilizing independently installed axial positioning components within each fragment channel, the initial fragment loading depth can be precisely and independently adjusted. This allows for coordinated control of the spatial distribution and target arrival time of multiple fragments during the same test, solving the technical challenge of existing projectile sabots' inability to jointly preset and repeatedly control the spatiotemporal distribution of multiple fragments. This provides a comprehensive technical solution with a compact structure, flexible adjustment, and high control precision for laboratory simulation of complex coupled impact conditions.

[0009] To achieve the above objectives, the present invention provides the following solution: a projectile sabot with adjustable spatial distribution and target arrival time of multiple fragments, comprising: an outer bearing shell, the shape of which is adapted to the inner cavity of the barrel of the launching device; a multi-channel core, detachably installed within the outer bearing shell, the multi-channel core having multiple fragment channels extending along the firing direction, the multiple fragment channels being distributed in a predetermined spatial array within the cross-section of the projectile sabot, each fragment channel being used to accommodate at least one fragment, the lateral coordinate of the fragment channel determining the spatial distribution of the fragments upon impact with the target; and an axial positioning component, fixed within the fragment channels, providing an axial positioning reference surface for the fragments, the rear end face of the fragment abutting against the axial positioning reference surface, the initial loading depth of the fragments being changed by altering the axial position of the axial positioning component within the fragment channels, thereby adjusting the target arrival time of each fragment.

[0010] Optionally, the multiple fragment channels are arranged in a honeycomb pattern, a concentric ring pattern, or a rectangular matrix.

[0011] Optionally, multiple fragments are sequentially loaded in the same fragment channel along the firing direction, and a spacer is provided between two adjacent fragments to determine the initial distance between two adjacent fragments.

[0012] Optionally, the adjustable fragment spatial distribution and target time interval sabot further includes a fragment holding assembly, which is disposed within the fragment channel or at the exit of the fragment channel, and is used to constrain the fragments to the current axial loading position.

[0013] Optionally, the fragment holding assembly is a thin film seal that covers the outlet of the fragment channel, and the fragment breaks through the thin film seal during firing.

[0014] Optionally, the fragment holding assembly is an elastic retaining ring, which is disposed on the inner wall of the fragment channel and is used to apply a radial clamping force to the outer surface of the fragment.

[0015] Optionally, the unfilled channels in the multi-channel core are provided with sealing components and / or balancing components. The sealing components are used to block high-pressure gas from entering the unfilled channels, and the balancing components are used to compensate for the displacement of the sabot's center of gravity caused by the asymmetrical loading of the fragments.

[0016] Optionally, the axial positioning component is one or more of the following: a limiting plug, a pad assembly, and a threaded adjusting component.

[0017] Optionally, the axial positioning component is a limiting plug, which is adapted to the inner diameter of the fragment channel. The limiting plug is inserted from the rear end of the fragment channel, and the front end face of the limiting plug forms the axial positioning reference surface. The initial filling depth of the fragments can be changed by selecting limiting plugs with different axial lengths.

[0018] Optionally, the axial positioning component includes a pad group, which consists of multiple pads. The multiple pads are sequentially inserted from the rear end of the fragment channel. The front end face of the pad group forms the axial positioning reference surface. The initial filling depth of the fragments can be changed by changing the number and / or thickness of the pads.

[0019] Optionally, the axial positioning component is a threaded adjustment component. The inner wall of the rear end of the fragment channel is provided with an internal thread, and the outer periphery of the threaded adjustment component is provided with an external thread. The threaded adjustment component is screwed in from the rear end of the fragment channel, and the front end face of the threaded adjustment component forms the axial positioning reference surface. The initial filling depth of the fragments is continuously adjusted by rotating the threaded adjustment component.

[0020] Optionally, the rear end of the threaded adjustment component is provided with a locking nut for locking its axial position after the threaded adjustment component is adjusted to the correct position.

[0021] Optionally, the outer bearing housing is provided with a front positioning shoulder for pressing and fixing the multi-channel core.

[0022] Optionally, the outer periphery of the outer bearing housing is provided with a sealing ring groove, which is used to install a sealing ring to form an air seal between the outer bearing housing and the inner wall of the gun barrel.

[0023] Compared with the prior art, the present invention discloses at least the following beneficial effects: This invention, through the detachable connection between the outer bearing shell and the multi-channel core, allows for the rapid replacement of core modules with different channel arrays according to test requirements without altering the main structure of the launching device. This enables flexible pre-setting of the spatial distribution of fragments upon impact. Simultaneously, the independently installed axial positioning components within each fragment channel allow for precise and independent adjustment of the initial loading depth of each fragment. This ensures a controllable time difference in target arrival due to differences in the travel distance between fragments upon separation from the sabot, thereby achieving coordinated control of spatial and temporal coordinates. Furthermore, the fragment holding assembly reliably constrains the fragments to their current loading position, preventing movement during transport and acceleration, ensuring the repeatability and consistency of initial loading parameters. The sealing components in the unloaded channels prevent high-pressure gas leakage, maintaining the stability of the pressure field within the barrel, while the balancing components compensate for the center-of-gravity shift caused by asymmetrical loading, ensuring stable attitude of the sabot during high-speed movement within the barrel. The synergistic effect of the above structures enables this sabot to simultaneously obtain a pre-programmable and reproducible multi-fragment spatial array and time sequence in a single test, significantly improving the simulation realism and control accuracy of the coupled impact test. Attached Figure Description

[0024] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0025] Figure 1 This is a schematic diagram of a multi-fragment spatial distribution and target-reaching adjustable sabot provided in an embodiment of the present invention; Figure 2 for Figure 1 The front view of the embodiment shown; Figure 3 yes Figure 2 Sectional view at point AA; Figure 4 A schematic diagram of the cross-section of a sabot with fragmentation channels arranged in one configuration; Figure 5 A schematic diagram of the longitudinal section of the sabot with one arrangement of fragmentation channels; Figure 6 This is a partially enlarged view of the fragment channel, fragments, and axial positioning element in an embodiment of the present invention; Figure 7 This is a schematic diagram of an axial positioning component under various structural combinations disclosed in the embodiments of the present invention; Figure 8This is a schematic diagram of another structure of the multi-fragment spatial distribution and target-reaching adjustable sabot provided in an embodiment of the present invention; Figure 9 A flowchart illustrating an adjustment method for a sabot provided in an embodiment of the present invention; Figure 10 This is a schematic diagram showing the correspondence between the spatial distribution of fragments and the time interval to the target in an embodiment of the present invention.

[0026] In the figure: 1. Outer bearing shell; 11. Front positioning shoulder; 12. Sealing ring groove; 13. Rear bearing surface; 2. Multi-channel core; 21. Empty channel; 22. Fragment channel; 3. Axial positioning component; 31. Pad assembly; 32. Limiting plug; 33. Threaded adjustment component; 4. Fragment. Detailed Implementation

[0027] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0028] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0029] like Figure 1 As shown, the adjustable fragment spatial distribution and target time interval sabot provided in this embodiment of the invention mainly includes an outer support shell 1 and a multi-channel core 2 disposed within the outer support shell 1. The overall shape of the outer support shell 1 is constructed as a cylindrical structure adapted to the inner cavity of the gun barrel of the gas pressure-driven launching device. Its outer diameter and the inner diameter of the gun barrel are in clearance fit or slight interference fit to ensure that the sabot can be smoothly guided along the firing direction within the gun barrel, while also possessing good airtightness. The outer support shell 1 can be made of high-strength engineering plastics, such as polyetheretherketone (PEEK) or nylon, integrally formed by injection molding or machining, or it can be made of lightweight metal materials, such as aluminum alloy, formed by machining.

[0030] In one specific embodiment, the outer bearing housing 1 is provided with a front positioning shoulder 11 at the front end near the launch direction and a rear bearing surface 13 at the rear end opposite to the launch direction. The housing body is provided with a core mounting cavity that runs through the axial direction to accommodate the multi-channel core 2.

[0031] The multi-channel core 2 is installed in the core mounting cavity inside the outer bearing housing 1, and its overall shape is adapted to the core mounting cavity. Multiple fragmentation channels 22 extending along the firing direction are formed within the multi-channel core 2. These fragmentation channels 22 are distributed in a predetermined spatial array within the cross-section of the sabot. Each fragmentation channel 22 has an independent lateral coordinate, which corresponds to the ejection position of the fragment 4 within that channel, thus determining the spatial distribution of the fragment 4 upon impact. The inner diameter of the fragmentation channel 22 is slightly larger than the outer diameter of the fragment 4 to be launched, allowing the fragment 4 to slide freely along the channel while simultaneously radially limiting it, ensuring the stability of the fragment 4's attitude during launch.

[0032] In one specific assembly method, the multi-channel core 2 is installed as an independent module detachably in the core mounting cavity.

[0033] Specifically, the outer peripheral wall of the multi-channel core 2 is provided with a positioning structure, such as a positioning key or an anti-rotation plane. Correspondingly, the inner wall of the core mounting cavity of the outer bearing housing 1 is provided with a keyway, boss or limiting surface that cooperates with it.

[0034] During assembly, the multi-channel core 2 is pushed into the core mounting cavity in a predetermined direction, and the positioning structure ensures that the two do not rotate relative to each other in the circumferential direction. Subsequently, the multi-channel core 2 is axially pressed and fixed using the front positioning shoulder 11 located at the front end of the outer bearing housing 1. The front positioning shoulder 11 can be an independent annular pressure plate, fixedly connected to the housing body of the outer bearing housing 1 by threads or screws; or it can be a flange structure integrally formed with the housing body, which is pressed by the rear bearing surface 13 or a special tool after the multi-channel core 2 is installed. This detachable structural design allows users to quickly replace multi-channel cores 2 with different fragment channel 22 array configurations according to different test requirements, in order to adapt to different fragment spatial distribution requirements.

[0035] Based on the above embodiments, further, such as Figure 1 and Figure 2 As shown, the outer bearing housing 1 has at least one sealing ring groove 12 on its outer periphery. This sealing ring groove 12 is used to install an O-ring or a labyrinth seal. When the sabot is installed into the gun barrel, the sealing ring fits tightly against the inner wall of the gun barrel, effectively preventing the propellant gas from leaking forward in the gap between the sabot and the inner wall of the gun barrel. This ensures that most of the gas pressure acts on the rear bearing surface 13, thereby improving the firing efficiency and ensuring the uniformity of the force on the sabot during acceleration.

[0036] Based on the above embodiments, in order to further reduce the frictional resistance and sway when the sabot moves at high speed in the barrel, guide rings or low-friction coatings, such as polytetrafluoroethylene (PTFE) coatings, can be provided on the front and rear sides of the sealing ring groove 12 on the outer periphery of the shell body.

[0037] In one specific embodiment, the arrangement of the multiple fragment channels 22 within the multi-channel core 2 in the cross-section can vary depending on the experimental requirements.

[0038] In a preferred embodiment, the multiple fragmentation channels 22 are arranged in a honeycomb pattern, consisting of a central channel located at the center of the cross-section and multiple layers of annular channels arranged in a regular hexagon around the central channel. This honeycomb arrangement maximizes the loading density of the fragmentation channels 22 within a given barrel caliber limit, increasing the number of fragments 4 that can be loaded. Simultaneously, each channel in the honeycomb arrangement has a clearly defined geometric position, facilitating the establishment of a correspondence between channel numbers and lateral coordinates.

[0039] In another embodiment, the fragment channels 22 can also be arranged in a concentric ring, a rectangular matrix, or a non-uniform array designed according to specific test requirements. The cross-sectional shape of the fragment channels 22 is usually circular to facilitate the processing and adaptation of spherical or near-spherical fragments. However, for non-spherical fragments such as cylindrical or sheet-like fragments, the cross-section of the fragment channels 22 can be set as elliptical, rectangular, polygonal, or an irregular cross-section adapted to the shape of the fragment 4, and guide grooves or anti-rotation planes are provided on the inner wall of the channel to limit the attitude changes of the fragment 4 during flight.

[0040] In one specific embodiment, in order to accurately control the axial loading position of each fragment 4 in its corresponding fragment channel 22, and thereby adjust the time interval between each fragment 4 and the target, an independent axial positioning element 3 is provided in each fragment channel 22.

[0041] like Figure 3 , Figure 5 and Figure 6 As shown, the axial positioning member 3 provides an axial positioning reference surface for the fragment 4 within the fragment channel 22, and the rear end face of the fragment 4 (the end away from the firing direction) abuts against this reference surface. By changing the axial position of the axial positioning member 3 within the fragment channel 22, the initial loading depth of the fragment 4 can be changed.

[0042] In a specific embodiment, such as Figure 6As shown, the axial positioning element 3 can be a limiting plug 32. This limiting plug 32 is a short cylinder that matches the inner diameter of the fragment channel 22, with its outer diameter having a clearance fit or transition fit with the inner wall of the channel. The limiting plug 32 is inserted into the channel from the rear end (i.e., the end near the rear bearing surface 13). The front face of the limiting plug 32 forms a fragment abutment surface. The rear face of the limiting plug 32 abuts against the rear face of the multi-channel core 2 or a removable rear cover plate. By selecting limiting plugs 32 of different axial lengths, the depth of the fragment abutment surface within the channel can be changed, thereby achieving discrete adjustment of the fragment 4 loading position. For easy identification and replacement, limiting plugs 32 of different lengths can be equipped with different color markings or size markings.

[0043] In another specific embodiment, such as Figure 7 As shown, the axial positioning component 3 is formed by a set of pad blocks 31. The pad block set 31 includes multiple annular pads of standard thickness. These pads are inserted sequentially from the rear end of the fragment channel 22. By changing the number and thickness combination of the inserted pads, the axial position of the fragment abutment surface formed by the front end face of the pad block set 31 can be precisely adjusted. This pad block combination method is highly flexible and easy to implement various discrete filling depth configurations.

[0044] In yet another specific embodiment, such as Figure 8 As shown, the axial positioning component 3 can be a threaded adjusting component 33. An internal thread is provided on the inner wall of the rear end of the fragment channel 22, while an external thread is provided on the outer periphery of the threaded adjusting component 33 to mate with it. The threaded adjusting component 33 is screwed in from the rear end of the channel, with its front end serving as the fragment abutment surface. By rotating the threaded adjusting component 33, the axial position of the fragment abutment surface within the channel can be continuously and steplessly adjusted. For convenient and precise control and reading, a scale and pointer can be provided at the rear end of the threaded adjusting component 33, or a dedicated adjusting tool can be provided. Furthermore, to prevent the threaded adjusting component 33 from rotating due to vibration during launch, a locking nut can be provided, or anti-reverse adhesive can be applied to its threads to achieve reliable locking after adjustment.

[0045] It should be understood that the axial positioning element 3 can be one or more of the following combinations: limit plug 32, pad group 31, and threaded adjustment element 33.

[0046] Regardless of the type of axial positioning element 3 used, the shape of its fragment abutment surface can be optimized according to the shape of the fragment 4. For spherical fragments, the abutment surface is preferably a concave spherical groove or a conical groove to increase the contact area with the fragment 4, providing automatic centering and stable support for the fragment 4 and preventing eccentric rolling of the fragment 4 during high-speed acceleration. For cylindrical or sheet-like fragments, the abutment surface is preferably a flat or stepped surface to ensure that the axial posture of the fragment 4 remains stable.

[0047] Based on the above embodiments, in order to prevent the fragments 4 from slipping or shifting prematurely relative to the fragment channel 22 due to gravity, vibration or airflow impact during the loading, transportation and high-speed acceleration in the gun barrel, each fragment channel 22 is also provided with a fragment holding component.

[0048] In one specific embodiment, the fragment holding assembly is a thin film seal disposed at the outlet of the fragment channel 22. This thin film seal is a thin plastic film or aluminum foil, fixed to the front end face of the multi-channel core 2 by adhesive bonding or heat pressing, completely covering the outlet of the entire fragment channel 22. Upon firing, the sabot accelerates inside the barrel, and the fragment 4, under the influence of enormous inertial force, impacts forward, sufficient to break through the thin film seal, subsequently separating from the sabot and flying towards the target. The thin film seal effectively confines the fragment 4 within the channel before firing.

[0049] In another specific embodiment, the fragment holding component is an elastic retaining ring disposed on the inner wall of the fragment channel 22. The elastic retaining ring engages with a pre-set annular groove in the inner wall of the channel and protrudes slightly from the surface of the inner wall. When the fragment 4 is loaded into the channel, the elastic retaining ring generates a slight radial clamping force on the outer surface of the fragment 4. The magnitude of this clamping force is precisely designed to be less than the axial inertial force experienced by the fragment 4 during launch acceleration. Therefore, during launch, the fragment 4 can overcome the constraint of this clamping force, move forward normally along the channel, and disengage. This structure is simple and reliable, and does not cause additional interference to the launch attitude of the fragment 4.

[0050] Furthermore, in actual experiments, it is often unnecessary to use all the fragment channels 22 in the multi-channel core 2. Empty channels 21 that are not filled with fragments 4 require appropriate processing. In a preferred embodiment, such as... Figure 4 As shown, a sealing element is installed in the empty channel 21. This sealing element can be a rubber plug, a plastic plug, or a lightweight foam plug, and its shape is adapted to the inner diameter of the fragment channel 22. It is used to block high-pressure gas from entering the empty channel 21, thereby avoiding pressure field disturbance inside the barrel due to local leakage, which would affect the overall acceleration performance of the sabot and the launch attitude of the fragments 4. The sealing element should have sufficient strength to withstand the action of high-pressure gas during the firing process without being pushed into the depth of the channel or ejected. At the same time, in order to balance the sabot's center of gravity shift caused by the asymmetrical loading of fragments 4, a balancing element can be installed in the empty channel 21, which is symmetrical to the channel filled with fragments 4. The balancing element is made of a high-density material, and its mass and position are calculated and determined according to the actual loading situation to ensure the dynamic stability of the sabot during high-speed rotation or flight.

[0051] like Figure 4As shown, this embodiment specifically describes a sabot employing a honeycomb array multi-channel core 2 and its spatial distribution adjustment method. Within the cross-section of the multi-channel core 2, dozens of circular fragment channels 22 are arranged in a standard honeycomb pattern. Each fragment channel 22 has a unique number engraved at a corresponding position on the outer surface of the core, such as A1, A2, ..., B1, B2, ... etc. Before use, the test personnel will find the channel number combination matching the spatial distribution according to the preset target impact spatial distribution requirements on the target surface, in a table corresponding to channel numbers and horizontal coordinates. For example, if it is necessary to form a cluster of fragments densely packed in the center and sparsely packed on the periphery of the target surface, the channels in the central area of ​​the honeycomb array are selected for loading; if it is necessary to form a ring-shaped impact area, one or more rings of channels on the periphery are selected for loading; if it is necessary to simulate an asymmetric impact, channels in a specific area are selected for loading.

[0052] After selecting the fragmentation channels 22 to be loaded, the operator loads the fragments 4 into these selected channels. Unselected empty channels 21 are then fitted with the aforementioned sealing and balancing components. After loading, the relative positions of the multiple fragments 4 within the sabot's cross-section are precisely determined. This positional relationship will approximately map onto the target surface after exiting the barrel, forming a predetermined spatial distribution. During initial use, the mapping relationship between the channel's lateral coordinates and the actual impact position on the target surface can be calibrated using high-speed photography or target plate measurements. Based on the calibration results, the channel selection for subsequent tests can be fine-tuned.

[0053] This embodiment combines Figure 9 and Figure 10 This paper focuses on describing a method for controlling the time interval between fragments reaching the target by adjusting the axial loading position. Assume that in a single test, three fragments 4 need to arrive at the target surface sequentially at a set time interval. The operator first calculates the required loading depth for each of the three fragments 4 based on the target time sequence and the previously calibrated "axial loading depth - target arrival time" curve. For example, fragments 4 that need to arrive at the same time should have the same loading depth; fragments 4 that need to arrive earlier should be loaded closer to the channel exit (smaller loading depth); fragments 4 that need to arrive later should be loaded closer to the rear end of the channel (larger loading depth).

[0054] Based on the calculated filling depth, the axial positioning elements 3 within each fragment channel 22 are selected or adjusted. For example, a longer limiting plug 32 can be used for channels requiring a shallower filling depth, while a shorter limiting plug 32 is used for channels requiring a greater filling depth. In another embodiment using the threaded adjusting element 33, the number of turns the threaded adjusting element 33 should be precisely calculated based on the depth value, and a tool is used to rotate it to the designated position and lock it.

[0055] After setting all the axial positioning elements 3 within the channels, the corresponding fragments 4 are then loaded into the channels, with their rear ends firmly abutting against the fragment abutment surfaces of the positioning elements. At this point, the initial positions (i.e., axial coordinates) of each fragment 4 in the firing direction are different. When the sabot is accelerated by gas pressure, all fragments 4 acquire the same acceleration and velocity along with the sabot. However, at the moment the sabot leaves the barrel and decelerates, the fragments 4 located closer to the exit position will break free from the sabot's constraint earlier and fly towards the target first; while the fragments 4 located deeper in the channel need to travel a longer distance to exit the channel, thus their departure from the sabot is relatively delayed. This initial distance difference is converted into a repeatable target arrival time difference during high-speed flight, thereby achieving precise presetting and control of the time interval between fragment 4 and the target.

[0056] Based on the above embodiments, to further expand the applicability of the sabot and reduce its usage cost, this invention provides an implementation scheme with a replaceable core. In this scheme, the outer bearing shell 1 is a standardized universal component, and the size and interface of its core mounting cavity are fixed. The multi-channel core 2 is designed as a series of interchangeable modules with different parameters. For example, there are cores with dense honeycomb channels specifically for small-caliber fragments, and cores with sparse array channels specifically for large-caliber fragments; there are cores with all channels arranged in parallel, and cores with some channels having a slight inclination angle to create fragment convergence or divergence effects. Test personnel only need to select the appropriate core module according to the specific test task, install it into the outer bearing shell 1, and fix it with the front positioning shoulder 11, without redesigning and manufacturing the entire sabot, greatly improving the flexibility and efficiency of the test.

[0057] In another extended implementation, such as Figure 5 As shown in the longitudinal section, two or more fragments 4 can be loaded at intervals along the launch direction within the same fragment channel 22. Adjacent fragments 4 are isolated and positioned by an axial positioning element 3 (e.g., a short pad or spacer ring). Thus, during launch, multiple fragments 4 within the same channel will be ejected sequentially at extremely short time intervals (determined by the thickness of the spacer), creating multiple consecutive impacts at approximately the same position on the target surface. This "single-point multi-impact" mode can be combined with the "multi-point single-impact" mode (fragments loaded in different channels) to simulate more complex and realistic explosion or fragment impact load conditions under laboratory conditions.

[0058] like Figure 9 As shown in the embodiments of the present invention, an adjustment method for the spatial distribution of multiple fragments and the time interval between impacts to the target is also disclosed. The method aims to independently and collaboratively preset the spatial distribution and time interval between impacts of multiple fragments in a single launch test through systematic operation steps, so as to meet the test requirements of complex coupled impact conditions.

[0059] In one specific embodiment, the adjustment method includes the following steps.

[0060] Step S1: Determine the target parameters for the experiment.

[0061] According to the test outline requirements, several key indicators required for this launch were specified, including: the total number of fragments to be launched, the preset target-landing spatial distribution pattern of each fragment on the target surface, and the preset time sequence of each fragment reaching the target surface or the preset target-landing time interval between adjacent fragments.

[0062] Step S2: Select the channel to be filled with fragments.

[0063] Based on the preset target impact space distribution determined in step S1, and referring to the pre-established correspondence table between channel numbers and channel lateral coordinates, select the channel number combination that matches the target impact position from the multiple fragment channels of the multi-channel core. After selection, record the list of selected channel numbers as the basis for subsequent loading operations.

[0064] Step S3: Determine the axial filling depth of each channel.

[0065] Based on the preset target arrival time sequence determined in step S1, and combined with the correlation curve between axial loading depth and fragment arrival time obtained from previous calibration tests, the target axial loading depth value corresponding to each fragment channel selected in step S2 is calculated or obtained by referring to a table. For multiple fragments that need to arrive at the target surface at the same time, their corresponding loading depth values ​​should be set to the same value; for fragments that need to arrive sequentially, their loading depth values ​​should be set to different values ​​according to the length of the time interval.

[0066] Step S4: Install the axial positioning component.

[0067] Based on the target axial filling depth of each channel calculated in step S3, install axial positioning components of the corresponding specifications in each selected fragment channel. Specifically, when the axial positioning component is a limiting plug, select a limiting plug with a corresponding length according to the filling depth and push it from the rear end of the channel to the predetermined depth position; when the axial positioning component is a shim block set, calculate the required number and thickness combination of standard shims according to the filling depth, and place the shims into the channel sequentially; when the axial positioning component is a threaded adjusting component, convert the filling depth into the number of turns required for the threaded adjusting component, use a tool to rotate it to the designated position, and lock it with a lock nut. After installation, check whether the fragment abutment surface of each axial positioning component reaches the target position.

[0068] Step S5: Load the fragments and install the retaining assembly.

[0069] The fragments to be launched are loaded from the rear or front end of the channel into the corresponding fragment channel where the axial positioning components have been installed in step S4, ensuring that the rear end face of each fragment is tightly abutted against the fragment abutment surface of the corresponding axial positioning component. After the fragments are loaded, fragment holding components are installed at the exit of each fragment channel or at a position adjacent to the fragment within the channel to constrain the fragments to their current axial loading position and prevent axial movement during subsequent handling, loading, and acceleration.

[0070] Step S6: Balance the unfilled channels.

[0071] For unselected empty channels in the multi-channel core, install sealing and / or balancing components as needed. The purpose of installing sealing components is to prevent high-pressure gas from entering the empty channels, avoiding adverse effects of localized gas leakage on the stability of the sabot's movement within the barrel. The purpose of installing balancing components is to compensate for the sabot's center of gravity shift caused by asymmetrical fragment loading, ensuring stable attitude of the sabot during high-speed movement within the barrel. In situations where strict balancing or sealing is not required, this step can be selectively performed based on the actual situation.

[0072] Step S7: Assemble the sabot.

[0073] The multi-channel core, pre-loaded with fragments and with channel processing completed, is inserted into the core mounting cavity of the outer carrier housing. The multi-channel core is then pressed and secured by the front positioning shoulder at the front end of the outer carrier housing. Subsequently, a sealing ring is installed in the sealing ring groove on the outer circumference of the outer carrier housing, completing the overall assembly of the sabot. The assembled sabot is then placed into the barrel of the gas pressure-driven firing device. Step S8: Execute the launch and acquire test data.

[0074] The launch test was conducted according to the operating procedures. During the launch test, high-speed photography equipment, light curtain velocimeters, or trigger-type sensors on the target surface were used to record in real time the flight velocity of each fragment after leaving the barrel, the actual target impact position coordinates on the target surface, and the actual target impact time. After the launch, the actual target impact position was compared with the preset spatial distribution set in step S1 to calculate the target impact deviation; at the same time, the actual target impact time was compared with the preset time series set in step S1 to calculate the time deviation.

[0075] Step S9: Correct the loading parameters.

[0076] Based on the target landing deviation and time deviation obtained in step S8, the mapping relationship between the channel's lateral coordinates and the target landing position, as well as the correspondence between the axial loading depth and the target arrival time, are corrected and updated. Based on the corrected mapping relationship, the channel selection scheme and / or the installation parameters of each channel's axial positioning component in the next test are adjusted to improve the control accuracy of subsequent launch tests.

[0077] Based on the above embodiments, the method for establishing the correspondence table between channel numbers and channel lateral coordinates in step S2 is as follows: During the sabot design stage, based on the CAD drawings of the multi-channel core cross-section or actual measurement results, each fragment channel is assigned a unique number, and the lateral coordinate value (including horizontal and vertical components) of the channel center relative to the sabot axis is recorded. This correspondence table can be printed on paper for manual reference or stored in a computer database for use by automated loading systems. When a new type of multi-channel core is used for the first time, the target position data in step S8 is used for initial calibration of this correspondence table to calibrate the systematic deviation between the theoretical coordinates and the actual target position.

[0078] Based on the above embodiments, the method for establishing the correlation curve between axial loading depth and target arrival time in step S3 is as follows: Before the formal test, using the same launching device and sabot structure, one or more fragments are launched at different axial loading depths. The muzzle velocity and target arrival time of the fragments at each loading depth are recorded using high-speed velocity measurement and timing equipment. Multiple sets of collected data are then subjected to curve fitting to establish a functional relationship between loading depth and target arrival time. In subsequent formal tests, the required loading depth value can be quickly calculated based on the target time interval by referring to this curve or substituting it into the functional relationship.

[0079] Based on the above embodiments, further, in step S4, when a threaded adjusting member is used for continuous adjustment, the method also includes preventing the adjusting member from rotating and loosening under the impact of the launch by tightening the locking nut at its outer end or applying anti-reverse adhesive to the thread surface after the threaded adjusting member is screwed into place. Simultaneously, the scale line on the outer end of the threaded adjusting member can indicate the current screw-in depth in real time, facilitating verification and recording by the operator.

[0080] Based on the above embodiments, the correction process in step S9 further adopts an iterative approximation method: for high-precision comparative tests requiring multiple repeated launches, the measured target position and time data are used as feedback after each launch to fine-tune the channel selection and axial loading depth for the next launch. After several rounds of iteration, the target position and time deviation will converge to the allowable error range, thereby establishing a high-precision loading parameter database for specific test conditions.

[0081] Building upon the above embodiments, for test conditions requiring "multiple consecutive impacts at the same lateral position," in step S5, multiple fragments are sequentially loaded along the launch direction within the same selected fragment channel, with a spacer installed between each adjacent fragment. The axial thickness of the spacer determines the initial distance between the two fragments, thus determining the time interval between their arrival at the target surface. After loading, the foremost fragment in the same channel exits first, followed by the fragments behind, resulting in multiple intermittent impacts at approximately the same position on the target surface. This method can be used alone or in combination with methods that load fragments in different channels.

[0082] Based on any of the above-described embodiments of the adjustment method, it should be understood that in practical applications, the specific execution order of steps S1 to S9 can be appropriately adjusted or combined according to the test site conditions. For example, for mature operating conditions that have been calibrated multiple times, the data verification and correction steps of steps S8 and S9 can be simplified or omitted as needed, and existing loading parameters can be directly used. This adjustment method can achieve precise and repeatable control of the spatial distribution of multiple fragments and the time interval to the target by adjusting only the structural parameters of the sabot itself, without changing the main structure of the gas pressure driven launching device.

[0083] In the description of this invention, it should be understood that the terms "longitudinal", "lateral", "up", "down", "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, and are only for the convenience of describing this invention, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0084] The embodiments described above are merely preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Various modifications and improvements made by those skilled in the art to the technical solutions of the present invention without departing from the spirit of the present invention should fall within the protection scope defined by the claims of the present invention.

Claims

1. A projectile sabot with adjustable spatial distribution of multiple fragments and adjustable time interval to the target, characterized in that, include: The outer bearing housing (1) is adapted to the inner cavity of the gun barrel of the launching device; The multi-channel core (2) is detachably installed inside the outer bearing housing (1). The multi-channel core (2) has multiple fragment channels (22) extending along the firing direction. The multiple fragment channels (22) are distributed in a predetermined spatial array within the cross-section of the sabot. Each fragment channel (22) is used to accommodate at least one fragment (4). The lateral coordinate of the fragment channel (22) determines the spatial distribution of the fragment (4) when it hits the target. An axial positioning component (3) is fixed in the fragment channel (22) to provide an axial positioning reference surface for the fragments (4). The rear end face of the fragments (4) abuts against the axial positioning reference surface. The initial loading depth of the fragments (4) is changed by changing the axial position of the axial positioning component (3) in the fragment channel (22) to adjust the time interval between each fragment (4) reaching the target.

2. The sabot with adjustable spatial distribution of multiple fragments and adjustable time interval to the target as described in claim 1, characterized in that, The multiple fragment channels (22) are arranged in a honeycomb pattern, a concentric ring pattern, or a rectangular matrix pattern.

3. The sabot with adjustable spatial distribution of multiple fragments and adjustable time interval to the target as described in claim 1, characterized in that, Multiple fragments (4) are sequentially loaded in the same fragment channel (22) along the firing direction. A spacer is provided between two adjacent fragments (4) to determine the initial distance between two adjacent fragments (4).

4. The sabot with adjustable spatial distribution of multiple fragments and adjustable time interval to the target as described in claim 1, characterized in that, It also includes a fragment holding assembly disposed within the fragment channel (22) or at the outlet of the fragment channel (22) for constraining the fragments (4) to the current axial loading position.

5. The sabot with adjustable spatial distribution of multiple fragments and adjustable time interval to the target as described in claim 4, characterized in that, The fragment holding assembly is a thin film seal, which covers the outlet of the fragment channel (22), and the fragment (4) breaks through the thin film seal when it is launched.

6. The sabot with adjustable spatial distribution of multiple fragments and adjustable time interval to the target as described in claim 4, characterized in that, The fragment holding assembly is an elastic retaining ring, which is disposed on the inner wall of the fragment channel (22) and is used to apply radial clamping force to the outer surface of the fragment (4).

7. The sabot with adjustable spatial distribution of multiple fragments and adjustable time interval to the target as described in claim 1, characterized in that, The empty channel (21) of the multi-channel core (2) without fragments (4) is provided with a sealing element and / or a balancing element. The sealing element is used to block high-pressure gas from entering the empty channel (21), and the balancing element is used to compensate for the displacement of the sabot center of mass caused by the asymmetrical loading of fragments (4).

8. The sabot with adjustable spatial distribution of multiple fragments and adjustable time interval to the target as described in claim 1, characterized in that, The axial positioning component (3) is one or more of the following: limit plug (32), pad group (31), and threaded adjustment component (33).

9. The sabot with adjustable spatial distribution of multiple fragments and adjustable time interval to the target as described in claim 1, characterized in that, The outer bearing housing (1) is provided with a front positioning shoulder for pressing and fixing the multi-channel core (2).

10. The sabot with adjustable spatial distribution of multiple fragments and adjustable time interval to the target as described in claim 1, characterized in that, The outer bearing housing (1) is provided with a sealing ring groove (12) on its outer periphery. The sealing ring groove (12) is used to install a sealing ring to form an air seal between the outer bearing housing (1) and the inner wall of the barrel.

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