A structure for measuring the damage information of small projectiles penetrating across cabin sections

Abstract

The present invention discloses a structure for measuring the damage information of a small projectile that penetrates across cabin sections, comprising a support liner; the support liner is a hollow structure, the support liner is fixed inside the projectile to be measured, the outer surface of the support liner is engraved with a cable groove, and the damage information measurement cable is laid in the cable groove; the shape of the outer surface of the support liner is the same as the shape of the inner surface of the projectile. The present invention solves the technical problem that laying cables on the outer surface of the projectile cannot effectively characterize whether the projectile is penetrated and destroys the structural integrity of the projectile, and realizes the damage measurement of a small projectile that penetrates across cabin sections.

Description

Technical Field

[0001] The invention belongs to the field of shell damage measurement, and in particular relates to a structure for realizing cross-chamber small shell body damage information measurement. Background Art

[0002] In order to test the damage effectiveness of artillery weapons on targets, it is usually necessary to use target shooting tests to arrange a damage measurement system on the target projectile body. Generally, cables are arranged in a longitude and latitude pattern on the surface of the projectile body. During the test, the on-off of the cable signal at a certain position of the damage measurement system on the target projectile body is identified to determine whether the artillery weapon has penetrated and damaged the target projectile body. For the identification of penetration damage, the most ideal installation method for the cable of the measurement system is to lay it close to the inner surface of the projectile body. However, in practice, for small target projectiles, it is difficult to lay cables directly on the inner surface of the projectile body due to process factors such as the narrow inner wall space. For target projectiles that need to cross cabin sections, the process implementation is even more difficult. In practice, equivalent measurements are also carried out by laying cables on the outer surface of the projectile. However, there are two significant defects in laying cables on the outer surface of the projectile: first, the measurement can only characterize the damage position of the projectile body, and cannot effectively characterize whether the projectile body is penetrated. Second, laying cables on the outer surface of the projectile will inevitably damage the aerodynamic shape of the projectile body. If cable grooves are pre-set on the outer surface of the projectile body to lay cables, the structural integrity of the projectile body will also be destroyed. Summary of the invention

[0003] The purpose of the present invention is to overcome the above-mentioned defects and provide a structure for measuring the breakdown damage information of small projectiles across cabin sections, which solves the technical problem that laying cables on the outer surface of the projectile cannot effectively characterize whether the projectile is penetrated and destroys the structural integrity of the projectile. The present invention realizes the measurement of the breakdown damage of small projectiles across cabin sections.

[0004] In order to achieve the above-mentioned object of the invention, the present invention provides the following technical solutions:

[0005] A structure for measuring the penetration damage information of a small projectile across cabin sections, comprising a supporting liner;

[0006] The support liner is a hollow structure, the support liner is fixed inside the projectile to be measured, and a cable groove is engraved on the outer surface of the support liner, and the damage information measurement cable is laid in the cable groove;

[0007] The shape of the outer surface of the supporting liner is the same as the shape of the inner surface of the projectile.

[0008] Furthermore, the cable grooves carved on the outer surface of the support inner tank are cable grooves with staggered longitude and latitude, the damage information measurement cable is laid in the cable grooves, and the damage information measurement cable is fixed in the cable grooves using silicone rubber.

[0009] Furthermore, the supporting liner is made of engineering plastic.

[0010] Furthermore, the width of the cable slot is (1.5-2)d0, where d0 is the diameter of the damage information measurement cable;

[0011] If the warp is pressed against the weft, the depth of the warp groove is d0+2mm, and the depth of the weft groove is d0+3mm; if the weft is pressed against the warp, the depth of the warp groove is d0+3mm, and the depth of the weft groove is d0+2mm;

[0012] The number and spacing of cable troughs are determined based on the damage information measurement accuracy index.

[0013] Further, the projectile body includes a rear projectile body and a front projectile body;

[0014] The rear projectile body and the front projectile body are sleeved with the front installation positioning pins, and are fixed with screws after being sleeved in place.

[0015] Furthermore, the outer surface of the supporting liner is provided with an annular boss along the circumferential direction, the outer surface of the annular boss cooperates with the inner surface of the rear body or the front body, and the annular boss is fixedly connected with the rear body or the front body by screws;

[0016] The outer diameter of the portion of the supporting liner where the annular boss is not provided is 4 to 6 mm smaller than the outer diameter of the annular boss.

[0017] Furthermore, a wire screw sleeve is embedded in the annular boss, and a screw hole is provided in the rear body or the front body. The screw passes through the screw hole and is tightened with the wire screw sleeve to achieve a fixed connection between the annular boss and the rear body or the front body.

[0018] Furthermore, the outer surface of the supporting inner container is provided with three groups of annular bosses, which are distributed along the axis and are sequentially recorded as the first annular boss, the second annular boss and the third annular boss;

[0019] In the rear body or the front body, the screw holes corresponding to the wire screw sleeves of the first annular boss and the third annular boss are elliptical holes with the major axis parallel to the axial direction, and the screw holes corresponding to the wire screw sleeves of the second annular boss are round holes.

[0020] Furthermore, when fixing the supporting liner to the inside of the projectile to be measured, first pass the screw through the screw hole and reach the inside of the wire screw sleeve without tightening it temporarily. After the rear projectile and the front projectile are sleeved in place, tighten the screw with the wire screw sleeve of the second annular boss, and then tighten the screw with the wire screw sleeves of the first annular boss and the third annular boss.

[0021] Further, it is assumed that the screw holes corresponding to the wire screw sleeves of the first annular boss and the third annular boss are respectively located on the rear elastic body and the front elastic body, and the screw hole corresponding to the wire screw sleeve of the second annular boss, i.e. the circular hole, is located on the rear elastic body;

[0022] Assume that the length of the elliptical hole of the rear projectile is D+ΔL1, the length of the elliptical hole of the front projectile is D+ΔL2, and D is the diameter of the circular hole;

[0023] ΔL1 is calculated according to the following formula:

[0024] ΔL1=L1×ΔT×(α 0 -α 1 )

[0025] Among them, L1 is the distance between the elliptical hole of the rear projectile and the circular hole, α 0 is the linear expansion coefficient of the supporting liner material, α 1 is the linear expansion coefficient of the rear body, ΔT is the difference between the highest and lowest operating temperatures;

[0026] ΔL2 is calculated according to the following formula:

[0027] ΔL2=[L21×(α 0 -α 1 )+L22×(α 0 -α 2 )]×ΔT

[0028] Among them, L21 is the distance between the circular hole and the front body sleeve end face, L22 is the distance between the front body sleeve end face and the front body elliptical hole, α 2 is the linear expansion coefficient of the front body material.

[0029] Compared with the prior art, the present invention has at least one of the following beneficial effects:

[0030] (1) The present invention realizes the measurement of the damage of a small cross-cabin projectile, avoids grooving the projectile surface to arrange the measurement cables, can effectively maintain the integrity of the projectile's aerodynamic shape and the actual wall thickness of the projectile, and is not limited by the internal space size of the projectile;

[0031] (2) The damage measurement structure of the present invention is connected to the projectile body by fasteners, which is convenient to install and operate, and can be disassembled and reused repeatedly, thereby improving the versatility of the product;

[0032] (3) The present invention realizes the independence of the projectile breakdown damage measurement information and the projectile structure, so that the self-test, fault detection and repair of the damage information measurement system are independent of the projectile structure, thereby reducing costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 This is a schematic diagram of the cross-cabin section projectile penetration damage measurement structure of the present invention;

[0034] Figure 2 The supporting liner structure diagram of the present invention; wherein (a) is an overall diagram, and (b) is a partial enlarged diagram;

[0035] Figure 3 The schematic diagram of the connection structure between the supporting liner and the elastic body of the present invention; wherein (a) is an overall diagram, and (b) is a partial enlarged diagram;

[0036] Figure 4 A schematic diagram of the opening of the support liner connection on the elastic body of the present invention;

[0037] In the figure, 1-rear body, 2-support liner, 3-front body, 4-first screw, 5-locating pin, 6-wire thread sleeve, 7-flat washer, 8-spring washer, 9-second screw; 21-matching step 21, 22-warp groove, 23-weft groove, 11-round hole, 12-first elliptical hole, 31-second elliptical hole. DETAILED DESCRIPTION

[0038] The following detailed description of the present invention will make the features and advantages of the present invention more clear and explicit.

[0039] The word "exemplary" is used exclusively herein to mean "serving as an example, embodiment, or illustration." Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. Although various aspects of the embodiments are shown in the drawings, the drawings are not necessarily drawn to scale unless otherwise noted.

[0040] The present invention proposes a structure for measuring the breakdown damage information of a small projectile across cabin sections. By designing a supporting liner structure that is closely attached to the inner wall of the projectile, a measuring cable is laid on the supporting liner structure. When the target projectile is attacked by a shell and suffers penetration damage, the cable at the corresponding position of the supporting liner is destroyed, thereby characterizing the breakdown damage at the corresponding position of the projectile. This structure does not require the arrangement of damage measurement cables on the surface of the projectile, but instead lays the damage measurement cables on a supporting structure close to the inner wall of the cabin, thus avoiding grooving on the surface of the projectile to destroy the structural integrity. In addition, the supporting structure is mechanically connected to the inner wall of the projectile, which is convenient for installation and disassembly, and is convenient for independent testing and maintenance of damage information. The present invention is suitable for projectile damage effectiveness testing, especially for target projectiles across cabin sections.

[0041] According to the target missile structure, the invention designs a structure that is easy to install, can be repeatedly disassembled and assembled, and can meet the needs of measuring the damage of a small missile through a cross-cabin section. The cross-cabin section missile breakdown damage information measurement structure of the invention mainly includes: a support liner 2, which is fixedly installed inside the missile body composed of a rear missile body 1 and a front missile body 3. In a specific embodiment, the support liner 2 is fixedly installed with the missile body using a wire screw sleeve 6, a flat washer 7, a spring washer 8, and a second screw 9.

[0042] The rear projectile 1 and the front projectile 3 are two sections of nested compartments, which are the target projectiles to be measured, and are circumferentially positioned by the positioning pins 5 and connected and fixed by the first screws 4. The support liner 2 spanning the rear projectile 1 and the front projectile 3 is designed according to the inner profiles of the front and rear projectiles. Its structural shape is equidistantly offset inward according to the inner profiles of the projectile 1 and the front projectile 3 to ensure that the support liner can be close to the inner wall of the projectile. A matching step 21 (annular boss) corresponding to the rear projectile 1 and the front projectile 3 is designed in the axial direction of the support liner 2. The outer wall of the matching step is closely matched with the inner wall of the rear projectile 1 and the front projectile 3. The remaining surfaces of the support liner 2 are all lower than the outer surface of the matching step to ensure smooth installation. A wire screw sleeve 6 is pre-embedded at the matching step to connect and install the rear projectile 1 and the front projectile 3 of the support liner 2. The surface of the support liner 2 is engraved with cable grooves with alternating longitude and latitude for laying damage information measurement cables. The structural material can be selected from materials such as engineering plastics with lower strength to ensure that the projectile is penetrated and the cables on the support liner are also penetrated smoothly.

[0043] The damage information measurement cable is laid in advance in the warp groove and weft groove of the support liner 2, and the cable is fixed by locally coating the groove with silicone rubber. When installing with the projectile, the support liner 2 containing the damage measurement cable is connected to the rear projectile 1 through 2 rows of 8 sets of flat washers 7, spring washers 8, and second screws 9; the front projectile 3 is sleeved with the rear projectile 1, and the positioning pin 5 is installed during the sleeve connection. After the sleeve is in place, the first screw 4 is installed and tightened; then the support liner 2 is connected to the front projectile 3 through a total of 4 sets of flat washers 7, spring washers 8, and second screws 9. When the damage information measurement equipment needs to be repaired or disassembled, first remove the second screw 9, spring washers 8, and flat washers 7 between the support liner 2 and the rear projectile 1 and the front projectile 3; then remove the first screw 4 and positioning pin 5 of the rear projectile 1 and the front projectile 3; remove the front projectile 3, and finally remove the support liner 2 from the rear projectile 1.

[0044] During the test, when the shell hits the target projectile, if it is able to penetrate the projectile, the measuring cable on the supporting liner 2 will be penetrated. At this time, the location of the damage to the target projectile and the size of the damaged area can be extracted through the collected information; if it is unable to penetrate the projectile or the shell does not hit the target projectile, the measuring cable on the supporting liner 2 will remain intact, and the projectile has no penetration damage.

[0045] Example:

[0046] like Figures 1 to 4 As shown, the cross-cabin section projectile damage information measurement structure of the present invention mainly includes: a support liner 2, which is fixedly installed inside the projectile composed of a rear projectile 1 and a front projectile 3, and the support liner 2 is fixedly installed with the projectile by using a wire thread sleeve 6, a flat washer 7, a spring washer 8, and a second screw 9.

[0047] like Figure 2 and Figure 3, the rear projectile 1 and the front projectile 3 are two sections of the sleeve compartment, which are the target projectile to be measured; first, according to the actual length of the two sections of the projectile, the number and position of the matching steps 21 (annular bosses) between the projectile and the supporting liner 2 are determined respectively. In this example, the rear projectile 1 has two sets of matching steps and the front projectile 3 has one set of matching steps. It should be noted that, if Figure 4 The opening of the body at the middle matching step is a circular hole 11, and the openings at the matching steps on both sides should be elliptical long holes, among which the elliptical hole set in the rear body is recorded as the first elliptical hole 12, and the elliptical hole set in the front body is recorded as the second elliptical hole 31 to release the structural stress during the installation and use of the support liner 2.

[0048] The structural material of the support liner 2 can be selected from materials such as engineering plastics with relatively low strength, so as to ensure that the projectile can smoothly penetrate the cables laid on the support liner 2 after being penetrated. The structural shape is determined according to the inner profile of the rear projectile 1 and the front projectile 3, and the structural length is determined according to the measurement area required by the projectile, and it is also necessary to consider avoiding the equipment installed inside the projectile. The support liner 2 has three groups of annular bosses distributed axially (corresponding to the rear projectile 1 and the front projectile 3), and the outer wall of the boss is in contact with the inner wall of the rear projectile 1 and the front projectile 3. The diameter of the remaining surface of the support liner 2 needs to be 4mm to 6mm smaller than the boss diameter to ensure smooth installation.

[0049] The sizes of the elliptical long holes of the rear spring body 1 and the front spring body 3 that cooperate with the supporting liner 2 are determined according to the following principles:

[0050] (1) Calculate the most severe ambient temperature difference ΔT during use:

[0051] ΔT=T h -T c

[0052] In the above formula, T h is the maximum operating temperature, T c The lowest operating temperature.

[0053] (2) Since the first elliptical hole 12 and the circular hole 11 are both located in the rear body, the length of the elliptical hole in the rear body 1 is D+ΔL1, where ΔL1 is calculated according to the following formula:

[0054] ΔL1=L1×ΔT×(α 0 -α 1 )

[0055] In the above formula, L1 is the distance between the elliptical hole of the rear body 1 and the central circular hole, α 0 α is the linear expansion coefficient of the support liner 2 material, 1 is the linear expansion coefficient of the rear body 1.

[0056] (3) Since the second elliptical hole 31 and the circular hole 11 are located in the front body and the rear body respectively, the length of the elliptical hole in the front body 3 is D+ΔL2, where ΔL2 is calculated according to the following formula:

[0057] ΔL2=[L21×(α 0 -α 1 )+L22×(α 0 -α 2 )]×ΔT

[0058] In the above formula, L21 is the distance between the center circle hole and the sleeve end face, L22 is the distance between the sleeve end face and the elliptical hole of the front body 3, α 0 α is the linear expansion coefficient of the support liner 2 material, 1 is the linear expansion coefficient of the rear body 1 material, α 2 is the linear expansion coefficient of the front body 2 material.

[0059] When designing the wall thickness of the support liner 2, it is necessary to consider the overall rigidity of the structure to meet the use requirements. The surface is engraved with interlaced longitude and latitude cable grooves, which are used to lay damage information measurement cables. The width of the warp groove 22 and the latitude groove 23 is (1.5~2)d0, where d0 is the cable diameter. If the warp is pressed on the latitude, the depth of the warp groove 22 is d0+2mm, and the depth of the latitude groove 23 is d0+3mm; if the latitude is pressed on the warp, the depth of the warp groove 22 is d0+3mm, and the depth of the latitude groove 23 is d0+2mm. The number and spacing of the warp grooves and the latitude grooves are determined according to the damage measurement accuracy index. Due to the use of low-strength materials such as engineering plastics, the annular boss of the support liner 2 needs to be pre-embedded with a wire screw sleeve 6 to facilitate installation with the rear body 1 and the front body 3 by screws, and to meet the use requirements of repeated disassembly and assembly. When the structural features of the support liner 2 are complex, the molding method can be 3D printing.

[0060] The damage information measurement cable is laid in advance in the warp groove and weft groove of the support liner 2, and silicone rubber is used to partially coat the groove; when installing with the projectile body, the support liner 2 containing the damage measurement cable is connected to the rear projectile body 1 through 2 rows of 8 groups of flat washers 7, spring washers 8, and second screws 9, and the screws are not tightened temporarily; the front projectile body 3 is sleeved with the rear projectile body 1, and the positioning pin 5 is installed before the sleeve connection. After the sleeve connection is in place, the first screw 4 is installed and tightened; the support liner 2 is connected to the front projectile body 3 through a total of 4 groups of flat washers 7, spring washers 8, and second screws 9; after confirming that each interface is in place, tighten the second screw 9 in the middle of the support liner and the second screws 9 on both sides of the support liner 2 in the order of the middle first and then the two sides, and the screws apply the specified torque as required.

[0061] When the damage information measuring equipment needs to be repaired or disassembled, first remove the second screw 9, spring washer 8, and flat washer 7 between the support liner 2 and the rear body 1 and the front body 3; then remove the first screw 4 and positioning pin 5 between the rear body 1 and the front body 3; after separating the front body 3 from the rear body 1, finally take the support liner 2 out of the rear body 1.

[0062] During the test, when the shell hits the target projectile, if it is able to penetrate the projectile, the measuring cable on the supporting liner 2 will be penetrated. At this time, the location of the damage to the target projectile and the size of the damaged area can be extracted through the collected information; if it is unable to penetrate the projectile or the shell does not hit the target projectile, the measuring cable on the supporting liner 2 will remain intact, and the projectile has no penetration damage.

[0063] The present invention has been described in detail above in conjunction with specific implementations and exemplary examples, but these descriptions cannot be understood as limiting the present invention. Those skilled in the art understand that, without departing from the spirit and scope of the present invention, a variety of equivalent substitutions, modifications or improvements may be made to the technical solution of the present invention and its implementation methods, all of which fall within the scope of the present invention. The scope of protection of the present invention shall be subject to the attached claims.

[0064] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

Claims

1. A structure for measuring the damage information of a small projectile that penetrates across cabin sections, characterized in that: including a support liner (2); The support inner liner (2) is a hollow structure, the support inner liner (2) is fixed inside the projectile to be measured, the outer surface of the support inner liner (2) is engraved with a cable groove, and the damage information measurement cable is laid in the cable groove; The shape of the outer surface of the supporting liner (2) is the same as the shape of the inner surface of the projectile.

2. The structure for measuring the damage information of a small-sized projectile across cabin sections according to claim 1 is characterized in that: The cable grooves carved on the outer surface of the support inner tank (2) are cable grooves with interlaced longitude and latitude, the damage information measurement cable is laid in the cable grooves, and the damage information measurement cable is fixed in the cable grooves by using silicone rubber.

3. The structure for measuring the damage information of a small-sized projectile across cabin sections according to claim 1 is characterized in that: The supporting liner (2) is made of engineering plastic.

4. The structure for measuring the damage information of a small cross-cabin projectile according to claim 2 is characterized in that: The width of the cable slot is (1.5~2)d0, where d0 is the diameter of the damage information measurement cable; If the warp is pressed against the weft, the depth of the warp groove is d0+2mm, and the depth of the weft groove is d0+3mm; if the weft is pressed against the warp, the depth of the warp groove is d0+3mm, and the depth of the weft groove is d0+2mm; The number and spacing of cable troughs are determined based on the damage information measurement accuracy index.

5. The structure for measuring the damage information of a small cross-cabin projectile according to claim 1 is characterized in that: The projectile body comprises a rear projectile body (1) and a front projectile body (3); The rear spring body (1) and the front spring body (3) are sleeved with the front mounting positioning pins and fixed with screws after being sleeved in place.

6. The structure for measuring the damage information of a small cross-cabin projectile according to claim 1 is characterized in that: The outer surface of the supporting inner shell (2) is provided with an annular boss along the circumferential direction, the outer surface of the annular boss cooperates with the inner surface of the rear body (1) or the front body (3), and the annular boss is fixedly connected to the rear body (1) or the front body (3) by screws; The outer diameter of the portion of the supporting liner (2) not provided with the annular boss is 4 to 6 mm smaller than the outer diameter of the annular boss.

7. The structure for measuring the damage information of a small-sized projectile across cabin sections according to claim 6 is characterized in that: A wire screw sleeve (6) is embedded in the annular boss, and a screw hole is provided in the rear body (1) or the front body (3). The screw passes through the screw hole and is tightened with the wire screw sleeve (6), thereby achieving a fixed connection between the annular boss and the rear body (1) or the front body (3).

8. The structure for measuring the damage information of a small-sized projectile across cabin sections according to claim 7 is characterized in that: The outer surface of the supporting inner container (2) is provided with three groups of annular bosses, which are distributed along the axis and are sequentially recorded as a first annular boss, a second annular boss and a third annular boss; In the rear body (1) or the front body (3), the screw holes corresponding to the wire screw sleeves (6) of the first annular boss and the third annular boss are elliptical holes with the major axis parallel to the axial direction, and the screw holes corresponding to the wire screw sleeves (6) of the second annular boss are round holes.

9. The structure for measuring the damage information of a small-sized projectile across cabin sections according to claim 8 is characterized in that: When the support liner (2) is fixed inside the body to be measured, the screw is first passed through the screw hole and reaches the inside of the wire screw sleeve (6) without being tightened temporarily. After the rear body (1) and the front body (3) are sleeved in place, the screw is tightened with the wire screw sleeve (6) of the second annular boss, and then the screw is tightened with the wire screw sleeves (6) of the first annular boss and the third annular boss.

10. The structure for measuring the damage information of a small-sized projectile across cabin sections according to claim 8 is characterized in that: The screw holes corresponding to the wire screw sleeves (6) of the first annular boss and the third annular boss are respectively located on the rear body (1) and the front body (3), and the screw hole corresponding to the wire screw sleeve (6) of the second annular boss, i.e. the circular hole, is located on the rear body (1); Assume that the length of the elliptical hole of the rear body (1) is D+ΔL1, the length of the elliptical hole of the front body (3) is D+ΔL2, and D is the diameter of the circular hole; ΔL1 is calculated according to the following formula: ΔL1=L1×ΔT×(α0-α1) Wherein, L1 is the distance between the elliptical hole of the rear body (1) and the circular hole, α0 is the linear expansion coefficient of the support liner (2) material, α1 is the linear expansion coefficient of the rear body (1), and ΔT is the difference between the maximum use temperature and the minimum use temperature; ΔL2 is calculated according to the following formula: ΔL2=[L21×(α0-α1)+L22×(α0-α2)]×ΔT Wherein, L21 is the distance between the circular hole and the sleeve end face of the front body (3), L22 is the distance between the sleeve end face of the front body (3) and the elliptical hole of the front body (3), and α2 is the linear expansion coefficient of the material of the front body (3).

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