A shock-resistant mounting transition seat for missile-borne mission equipment and its mounting method

Abstract

This invention discloses a high-impact resistant mounting transition seat and installation method for missile-borne mission devices. The mounting transition seat includes an upper connecting plate, a lower connecting plate, and an energy-absorbing device. The upper connecting plate is connected to a flange; the lower connecting plate is connected to a mounting plate; the energy-absorbing device is placed between the upper and lower connecting plates; the energy-absorbing device includes a double-layered corrugated pipe and an energy-absorbing body, the energy-absorbing body being made of energy-absorbing material and placed between the double-layered corrugated pipes, which are arranged axially within the missile body. This invention effectively absorbs collision energy under high-impact conditions, protecting the mission payload from damage; during unloading, the mounting transition seat prevents secondary collision damage during separation of the mission device from the missile body.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of anti-strong impact equipment, and particularly relates to a mounting transition seat for a missile-borne task device against strong impact and a mounting method. BACKGROUND

[0002] In a strong impact environment, a missile-borne task device will be subjected to strong impact overload, and the overload value can reach 50,000g-100,000g (g=9.8m / s 2 If no impact protection design is performed, the overload can easily cause the missile-borne task device to be damaged and fail. Generally, the missile-borne task device is rigidly connected with the inner wall of a missile body through a flange, and in a strong impact environment, impact load is directly transmitted to the task device through the flange. When the impact load exceeds the allowable stress of the task device, the task device is damaged or fails. On the other hand, at the end of the collision, the flange connection part starts to unload, and the unloading force drives the task device to separate from the flange. When the unloading force is large enough, the bolt connecting the task device and the flange can be pulled off, causing the task device to move backward and collide with the missile body again. This collision process can also cause the task device to be damaged or fail.

[0003] It can be seen that in a strong impact environment, the connection structure based on the flange rigid connection can easily cause the task device inside the missile body to be damaged, whether in the impact load loading process or in the unloading process.

[0004] Therefore, a mounting transition seat for a missile-borne task device against strong impact and a mounting method are developed to solve the above problems. SUMMARY

[0005] The purpose of the present application is to design a mounting transition seat for a missile-borne task device against strong impact and a mounting method to solve the above problems.

[0006] The present application achieves the above-mentioned purpose through the following technical solutions:

[0007] A mounting transition seat for a missile-borne task device against strong impact, the task device is placed inside a missile body, one end of the task device is provided with a flange, an annular mounting plate is radially arranged inside the missile body, and the task device can slide through the inside of the mounting plate; the mounting transition seat comprises:

[0008] an upper connecting plate, the upper connecting plate is connected with the flange;

[0009] a lower connecting plate, the lower connecting plate is connected with the mounting plate;

[0010] an energy absorption device, the energy absorption device is arranged between the upper connecting plate and the lower connecting plate.

[0011] Specifically, the energy-absorbing device comprises double-layer bellows and an energy-absorbing body, the energy-absorbing body is made of energy-absorbing material, and the energy-absorbing body is arranged between the double-layer bellows, and the double-layer bellows is arranged in the projectile along the axial direction thereof.

[0012] Preferably, the upper connecting plate and the lower connecting plate are both annular.

[0013] Specifically, the mounting transition seat further comprises a plurality of first bolts and a plurality of second bolts, the upper connecting plate and the lower connecting plate are respectively arranged at two ends of the double-layer bellows and the energy-absorbing body, a plurality of threaded connection holes are arranged on the upper connecting plate and the lower connecting plate, a plurality of through holes are correspondingly arranged on the flange and the mounting plate, the first bolts are screwed into the threaded connection holes on the lower connecting plate after passing through the through holes on the mounting plate, and the second bolts are screwed into the threaded connection holes on the upper connecting plate after passing through the through holes on the flange.

[0014] Further, the mounting transition seat further comprises a plurality of guide rods, the guide rod comprises a bolt head, a light segment and a threaded segment, a plurality of screw holes are correspondingly arranged on the mounting plate, a plurality of guide holes are correspondingly arranged in the flange, the upper connecting plate, the energy-absorbing body and the lower connecting plate, the bolt head is arranged above the upper connecting plate, the light segment is arranged by passing through the guide holes on the flange, the guide holes on the upper connecting plate, the guide holes on the energy-absorbing body and the guide holes on the lower connecting plate in sequence, and the threaded segment is threadedly connected with the screw hole on the mounting plate.

[0015] Preferably, the energy-absorbing body is a polymer or a foam material.

[0016] A mounting method of a mounting transition seat of a missile-borne task device against strong impact, comprising the following steps:

[0017] S1, connecting the flange of the task device with the upper connecting plate of the mounting transition seat through the second bolts, and connecting the mounting plate of the projectile with the lower connecting plate of the mounting transition seat through the first bolts;

[0018] S2, arranging the guide rod by passing through the through holes on the flange, the through holes on the upper connecting plate, the through holes on the energy-absorbing body and the through holes on the lower connecting plate, and threadedly connecting the threaded segment with the screw hole on the mounting plate;

[0019] S3, the yield force of the transition seat when absorbing energy satisfies the following condition:

[0020] ma0<F<<ma I

[0021] In the formula, m is the mass of the task device, a0 is the impact acceleration under normal use conditions, a I is the impact acceleration under high-speed collision;

[0022] S4, determining the buffer energy-absorbing stroke l according to the following formula: the buffer energy-absorbing stroke l is set to be less than the limit compression stroke of the mounting transition seat;

[0023]

[0024] Wherein, m is the mass of the task device, v is the high-speed collision velocity, sigma is the yield platform stress of the energy absorber, and A is the cross-sectional area of the contact surface between the energy absorber and the task device.

[0025] The present application has the following beneficial effects:

[0026] 1. The transition seat can effectively absorb collision energy and protect the task load from being damaged under a strong impact environment.

[0027] 2. The transition seat can prevent the task device from separating from the projectile and causing secondary collision damage during unloading. BRIEF DESCRIPTION OF DRAWINGS

[0028] Figure 1 is a sectional view of the transition seat;

[0029] Figure 2 is a top view of the transition seat;

[0030] Figure 3 is a perspective view of the transition seat;

[0031] Figure 4 is a schematic view of the installation structure of the transition seat (sectional view);

[0032] Figure 5 is a schematic view of the guide rod;

[0033] Figure 6 is a schematic view of the installation structure of the transition seat (perspective view);

[0034] In the figure: 1 - projectile; 2 - transition seat; 201 - upper connecting plate; 202 - double-layer corrugated pipe; 203 - energy absorber; 204 - lower connecting plate; 205 - threaded connection hole; 206 - guide hole; 3 - task device; 4 - first bolt; 5 - second bolt; 6 - guide rod. DETAILED DESCRIPTION

[0035] To make the objectives, technical solutions, and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be described below in connection with the drawings of the embodiments of the present application. Obviously, the described embodiments are some but not all of the embodiments of the present application. The components of the embodiments of the present application described and shown in the drawings herein can be arranged and designed in various different configurations.

[0036] Therefore, the following detailed description of the embodiments of the application provided in the drawings is not intended to limit the scope of the application claimed, but merely represents selected embodiments of the application. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the application without creative labor fall within the scope of protection of the application.

[0037] It should be noted that similar reference numbers and letters represent similar items in the following drawings, so once an item is defined in one drawing, it does not need to be further defined and explained in subsequent drawings.

[0038] In the description of the application, it should be understood that the terms "upper", "lower", "inner", "outer", "left", "right", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship commonly placed when the product of the application is used, or the orientation or positional relationship commonly understood by those skilled in the art, and are only for the convenience of describing the application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the application.

[0039] In addition, the terms "first", "second", etc. are only used for differentiation and cannot be understood as indicating or implying relative importance.

[0040] In the description of the application, it should also be noted that unless otherwise explicitly specified and limited, the terms "provided", "connected", etc. should be broadly understood, for example, "connected" can be fixedly connected, or detachably connected, or integrally connected; can be mechanically connected, or electrically connected; can be directly connected, or indirectly connected through an intermediate medium, or the internal communication of two elements. For those of ordinary skill in the art, the specific meaning of the above terms in the application can be understood according to the specific circumstances.

[0041] The specific embodiments of the application will be described in detail below with reference to the drawings.

[0042] As shown in Figures 1-6 A strong impact-resistant mounting transition seat for a missile-borne task device, the task device 3 is placed inside the missile body 1, one end of the task device 3 is provided with a flange, a ring-shaped mounting plate is radially provided inside the missile body 1, and the task device 3 can slide through the inside of the mounting plate; the mounting transition seat 2 comprises:

[0043] An upper connecting plate 201; the upper connecting plate 201 is connected with the flange;

[0044] A lower connecting plate 204; the lower connecting plate 204 is connected with the mounting plate;

[0045] The energy-absorbing device is arranged between the upper connecting plate 201 and the lower connecting plate 204.

[0046] In some embodiments, the energy-absorbing device comprises double-layer bellows 202 and energy-absorbing bodies 203, the energy-absorbing bodies 203 are made of energy-absorbing material, the energy-absorbing bodies 203 are arranged between the double-layer bellows 202, and the double-layer bellows 202 are arranged along the axial direction of the projectile 1. The energy-absorbing bodies 203 are plastic energy-absorbing material, which maintains the connection stiffness and support strength under the conditions of daily storage, transportation and launch flight, and compresses the energy-absorbing bodies 203 in the direction of the guide rod 6 under strong impact conditions. The double-layer bellows 202 filled with the energy-absorbing bodies 203 can be folded as expected under impact loading, and are not easy to be pulled apart under unloading.

[0047] In some embodiments, the upper connecting plate 201 and the lower connecting plate 204 are both formed in a ring shape.

[0048] In some embodiments, the mounting transition seat 2 further comprises a plurality of first bolts 4 and a plurality of second bolts 5, the upper connecting plate 201 and the lower connecting plate 204 are respectively arranged at two ends of the double-layer bellows 202 and the energy-absorbing bodies 203, and a plurality of threaded connection holes 205 are arranged on the upper connecting plate 201 and the lower connecting plate 204. Correspondingly, a plurality of through holes are arranged on the flange and the mounting plate, the first bolts 4 pass through the through holes on the mounting plate and are screwed into the threaded connection holes 205 on the lower connecting plate 204, and the second bolts 5 pass through the through holes on the flange and are screwed into the threaded connection holes 205 on the upper connecting plate 201.

[0049] In some embodiments, the mounting transition seat 2 further comprises a plurality of guide rods 6, the guide rod 6 comprises a bolt head, a light segment and a threaded segment, a plurality of screw holes are arranged on the mounting plate, a plurality of guide holes 206 are arranged in the flange, the upper connecting plate 201, the energy-absorbing bodies 203 and the lower connecting plate 204 in correspondence, the bolt head is arranged above the upper connecting plate 201, the light segment passes through the guide holes 206 on the flange, the guide holes 206 on the upper connecting plate 201, the guide holes 206 on the energy-absorbing bodies 203 and the guide holes 206 on the lower connecting plate 204 in sequence, and the threaded segment is threadedly connected with the screw hole on the mounting plate. The cooperation of the guide holes 206 and the guide rods 6 is used for guiding the compression process of the mounting transition seat 2, preventing the mounting transition seat 2 from tilting and twisting, and cooperating with the pin rod with the bolt head to prevent the task device 3 from separating from the projectile 1 during unloading to cause secondary impact.

[0050] In some embodiments, the energy-absorbing bodies 203 are high polymer or foam material.

[0051] In some embodiments, the buffer mounting seat is connected with the mounting plate, and the first bolts 4 are not higher than the upper surface of the lower connecting plate 204; the task device 3 is connected with the buffer connecting seat, and the second bolts 5 are not lower than the lower surface of the upper connecting plate 201.

[0052] The energy absorption device meets the rigid connection requirement under normal conditions such as daily storage, transportation and launching flight, and can plastically deform to absorb impact energy in the impact process at high speed, and prevent the secondary collision damage caused by the separation of the task device 3 and the projectile body 1 in the unloading process, which is an important innovation of the application, and effectively solves the impact resistance problem of the task device 3 in normal use, high-speed loading and unloading process.

[0053] A mounting method of a mounting transition seat of a missile-borne task device resistant to strong impact, comprising the following steps:

[0054] S1, connecting the flange of the task device 3 and the upper connecting plate 201 of the mounting transition seat 2 through the second bolt 5; connecting the mounting plate of the projectile body 1 and the lower connecting plate 204 of the mounting transition seat 2 through the first bolt 4;

[0055] S2, the guide rod 6 is arranged through the through hole on the flange, the through hole on the upper connecting plate 201, the through hole on the energy absorber 203 and the through hole on the lower connecting plate 204, and the threaded section is threadedly connected with the screw hole on the mounting plate;

[0056] S3, the yield force of the transition seat when absorbing energy satisfies the following condition:

[0057] ma0<F<<ma I

[0058] In the formula, m is the mass of the task device 3, a0 is the impact acceleration under normal use conditions, a I is the impact acceleration at high speed collision;

[0059] S4, the buffer energy absorption stroke l is determined according to the following formula: the buffer energy absorption stroke l is set to be less than the limit compression stroke of the mounting transition seat 2;

[0060]

[0061] In the formula, m is the mass of the task device 3, v is the high-speed collision speed, σ is the yield platform stress of the energy absorber 203, and A is the cross-sectional area of the contact surface between the energy absorber 203 and the task device 3.

[0062] Under strong impact environment, the force exerted by the task device 3 on the buffer transition seat is much greater than the platform yield force of the buffer transition seat, so that the buffer transition seat is compressed at an amplitude not higher than the failure stress of the task device 3;

[0063] In the compression process, the task device 3 and the buffer transition seat are compressed along the guide rod 6 under the constraint of the guide rod 6, avoiding the inclination and distortion of the buffer transition seat in the compression process;

[0064] At the end of the impact, the kinetic energy of the task device 3 is greatly absorbed, the speed is greatly attenuated, and the task device 3 moves in the opposite direction of the impact at the time of unloading, which will produce a stretching effect on the energy-absorbing device. In the stretching process, the energy-absorbing device again absorbs the rebound kinetic energy of the task device 3, so that the rebound speed of the task device 3 is extremely small. Therefore, under the constraint of the metal bellows of the energy-absorbing body 203 and the limiting of the bolt head of the guide rod 6, the task device 3 will not collide with the projectile body 1 again.

[0065] The above only describes the preferred embodiments of the present application, and it should be noted that those skilled in the art can make several improvements and refinements without departing from the technical principles of the present application, and these improvements and refinements should also be considered within the protection scope of the present application.

Claims

1. A shock-resistant mounting transition for a missile-borne mission device, the mission device being disposed inside a missile body, characterized in that One end of the task device is provided with a flange, and the inside of the elastic body is radially provided with an annular mounting plate, and the task device is slidably arranged inside the mounting plate. The upper connecting plate is connected with the flange. The lower connecting plate is connected with the mounting plate. The energy absorption device is arranged between the upper connecting plate and the lower connecting plate. The mounting transition seat is provided with: When the transition seat absorbs energy, the yield strength satisfies the following condition: wherein m is the quality of the task device, a 0 is the impact acceleration under normal use conditions, a I is the impact acceleration at high speed collision; The cushioning energy absorption travel is determined according to the following formula : cushioning energy absorption travel is set to be less than the limit compression travel of the mounting transition seat; wherein m is the mass of the mission device, v is the high velocity of impact, The upper connecting plate and the lower connecting plate are both annular. is the yield plateau stress of the energy absorber, A is the cross-sectional area of the interface between the energy absorber and the mission device; The mounting transition seat further comprises a plurality of guide rods, the guide rod comprises a bolt head, a light segment and a threaded segment, a plurality of screw holes are correspondingly arranged on the mounting plate, a plurality of guide holes are correspondingly arranged in the flange, the upper connecting plate, the energy absorption body and the lower connecting plate, the bolt head is arranged above the upper connecting plate, the light segment passes through the guide holes of the flange, the guide holes of the upper connecting plate, the guide holes of the energy absorption body and the guide holes of the lower connecting plate in sequence, and the threaded segment is threadedly connected with the screw hole of the mounting plate. The mounting transition seat further comprises a plurality of first bolts and a plurality of second bolts, the upper connecting plate and the lower connecting plate are respectively arranged at two ends of the double-layer bellows and the energy absorption body, a plurality of threaded connection holes are arranged on the upper connecting plate and the lower connecting plate, and a plurality of through holes are correspondingly arranged on the flange and the mounting plate.

2. The shock-resistant mounting transition of a missile-borne mission device according to claim 1, characterized in that The energy absorption body is made of a high polymer or a foam material.

3. The shock-resistant mounting transition of a missile-borne mission device according to claim 1, characterized in that The method comprises the following steps:

4. The method of claim 1-3, wherein, S1, connecting the flange of the task device with the upper connecting plate of the mounting transition seat through the second bolt, and connecting the mounting plate of the elastic body with the lower connecting plate of the mounting transition seat through the first bolt; S2, arranging the guide rod through the guide holes of the flange, the guide holes of the upper connecting plate, the guide holes of the energy absorption body and the guide holes of the lower connecting plate, and threadedly connecting the threaded segment with the screw hole of the mounting plate; S3, when the transition seat absorbs energy, the yield strength satisfies the following condition: ​ wherein m is the mass of the task device, a 0 is the impact acceleration under normal use conditions, a I is the impact acceleration at high speed collision; S4. Determine the cushion energy absorption travel according to the following formula : cushion energy absorption travel is set to be less than the limit compression travel of the mounting transition seat; wherein m is the mass of the target device, v is the high velocity of the impact, ​ is the yield plateau stress of the energy absorber, A is the cross-sectional area of the interface between the energy absorber and the target device.

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