High-g air cannon projectiles for spacecraft pyrotechnic shock testing

Abstract

The present invention relates to the technical field of pyrotechnic impact test of spacecraft products, and in particular to a high-g value air cannon projectile for pyrotechnic impact test of spacecraft, comprising a core, a first inner support, a second inner support, a first shell, a second shell, a locking nut, a first washer and a second washer; the first inner support is sleeved on the core; the second inner support is sleeved on the core; the first shell is sleeved outside the first inner support; the second shell is sleeved outside the second inner support; the locking nut is screwed on the tail of the projectile, and cooperates with a limiting ring, which can better limit the axial movement of the first inner support, the second inner support, the first shell and the second shell along the core; the first washer is cushioned between the first inner support and the limiting ring; the second washer is cushioned between the second inner support and the locking nut. Overall, a modular design is adopted, and when one or some parts are damaged, they can be replaced in time, thereby extending the overall service life of the air cannon projectile.

Description

Technical Field

[0001] The invention relates to the technical field of pyrotechnic impact test of spacecraft products, and in particular to a high-g value air cannon projectile used for pyrotechnic impact test of spacecraft. Background Art

[0002] The pyrotechnic shock suffered by spacecraft products in actual working conditions mainly comes from the separation of substructures such as the interstage separation and the fairing separation. Pyrotechnic shock has the characteristics of high g (gravitational acceleration) value, wide bandwidth, and short duration. Its acceleration amplitude can reach 300~300000g, the main frequency range is usually 100~1MHz, and the duration is generally not more than 20ms. Before delivery, spacecraft products need to be subjected to pyrotechnic shock simulation tests on the ground to assess their impact resistance. In order to truly simulate the pyrotechnic shock test, an air cannon can be used as the excitation source, and the high-pressure air is used to drive the projectile to impact the response plate to generate a high-frequency oscillation shock similar to the pyrotechnic shock.

[0003] With the development of technology, pyrotechnic impact tests require more refined impact response spectrum characteristics, such as higher acceleration amplitude (6000g ~ 10000g), steeper low-frequency slope (+12dB / Oct) and higher inflection point frequency (2000Hz). As the requirements of pyrotechnic impact tests become more and more diverse and the test magnitude becomes larger and larger, the impact force that the projectile needs to withstand during the pyrotechnic impact test is also increasing, making it very easy to be damaged.

[0004] Traditional air cannon projectiles have an integrated structure. When part of the projectile is damaged, the entire projectile becomes waste, and the number of times it can be recycled is still relatively low. Summary of the invention

[0005] The invention provides a high-g value air cannon projectile for a spacecraft pyrotechnic impact test, so as to solve the problem that a conventional air cannon projectile is an integrated structure, becomes waste as a whole when a part is damaged, and has a low number of recyclable uses.

[0006] The present invention provides a high-g value air cannon projectile for a spacecraft pyrotechnic impact test, comprising:

[0007] The core has a warhead at one end and a tail at the other end; a limit ring is provided at the end of the core close to the warhead;

[0008] The first inner bullet support is sleeved on the bullet core and arranged close to the bullet head;

[0009] The second inner support is sleeved on the core and arranged close to the tail of the bullet;

[0010] A first shell is sleeved outside the first inner elastic support;

[0011] The second shell is sleeved outside the second inner elastic support;

[0012] A locking nut, threadedly connected to the tail of the projectile, to limit the axial movement of the first inner support, the second inner support, the first shell and the second shell along the core;

[0013] A first washer, arranged between the first inner elastic support and the limiting ring;

[0014] The second washer is arranged between the second inner elastic support and the locking nut.

[0015] In some embodiments, a first buffer step ring is formed at one end of the first inner elastic support close to the first washer; one side surface of the first buffer step ring is attached to the first washer, and the other end surface is attached to the end surface of the first shell;

[0016] A plurality of first buffer cavities are uniformly formed between the inner wall and the outer wall of the first inner elastic support along the circumferential direction;

[0017] A second buffer step ring is formed at one end of the second inner elastic support close to the second gasket; one side surface of the second buffer step ring is attached to the second gasket, and the other end surface is attached to the end surface of the second shell;

[0018] A plurality of second buffer cavities are uniformly formed along the circumferential direction between the inner wall and the outer wall of the second inner elastic support.

[0019] In some embodiments, the first inner support and the second inner support are made of lightweight metal material;

[0020] The first shell and the second shell are made of high molecular polymer material.

[0021] In some embodiments, the cross section of each first buffer cavity is fan-shaped;

[0022] The cross section of each second buffer cavity is fan-shaped.

[0023] In some of the embodiments, a first impact-resistant structure is disposed in each first buffer cavity;

[0024] A second anti-impact structure is arranged in each second buffer cavity.

[0025] In some embodiments, the first impact-resistant structure comprises:

[0026] There are multiple rigid node rings, which are arranged in multiple rows and columns;

[0027] Flexible connecting belt; each rigid node ring is connected to a plurality of flexible connecting belts, and each flexible connecting belt is located on a tangent line of the rigid node ring;

[0028] Flexible filler, filled between multiple flexible connecting belts;

[0029] Rigid filler, filled in each rigid node ring;

[0030] The second impact-resistant structure is identical to the first impact-resistant structure.

[0031] In some of these embodiments, the edge of the bullet tip is chamfered.

[0032] In some of the embodiments, the wall thickness of the first shell and the second shell is 5 mm-10 mm.

[0033] In some embodiments, the first washer and the second washer are self-locking washers.

[0034] In some of these embodiments, the locking nut is a self-locking hexagonal cap nut.

[0035] The beneficial effects of the present invention are as follows: the high-g value air cannon projectile for a spacecraft pyrotechnic impact test of the present invention is provided with a core, a first inner support, a second inner support, a first shell, a second shell, a locking nut, a first washer and a second washer, one end of the core is a warhead, and the warhead is used to impact a response plate. The first inner support is sleeved on the core. The second inner support is sleeved on the core. The first shell and the first inner support are sleeved outside the first inner support in the form of interference fit. The second shell and the second inner support are sleeved outside the second inner support in the form of interference fit. The outer walls of the first shell and the second shell can be respectively fitted to the inner wall of the barrel. When the air cannon projectile is fired, the first shell, the second shell, the first inner support and the second inner support cooperate to limit the movement of the core in a straight line and prevent the core from unexpected eccentricity and rotation. The locking nut is screwed on the tail of the projectile to facilitate the assembly, use and disassembly and replacement of the locking nut and the core, and then facilitate the disassembly and assembly of the core, the first inner support, the second inner support, the first shell and the second shell. The locking nut cooperates with the limiting ring to better limit the axial movement of the first inner support, the second inner support, the first shell and the second shell along the core, so as to ensure the stability of the air cannon projectile structure under strong impact loads. The first washer is arranged between the first inner support and the limiting ring, and the second washer is arranged between the second inner support and the locking nut to prevent loosening between components under strong impact loads, further ensuring the stability of the overall structure of the air cannon projectile. On the whole, a modular design is adopted, and when one or some components are damaged, they can be replaced in time, which prolongs the service life of the air cannon projectile, increases the number of times the air cannon projectile can be recycled, reduces the test cost, has a high engineering application value, avoids the occurrence of unexpected eccentricity, rotation, and deformation aggravation caused by local damage to the air cannon projectile, ensures the accuracy of the results of later tests, and improves the test efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Figure 1 It is a schematic structural diagram of some specific embodiments of a high-g value air cannon projectile for a spacecraft pyrotechnic impact test of the present invention;

[0037] Figure 2 yes Figure 1 A cross-sectional view along AA of a high-g air cannon projectile used for pyrotechnic impact testing of a spacecraft is shown;

[0038] Figure 3 yes Figure 1 Explosion diagram of a high-g air cannon projectile used for pyrotechnic shock testing of spacecraft shown;

[0039] Figure 4 yes Figure 3 An end view of some embodiments of a first inner buttstock in a high-g air cannon projectile for use in a spacecraft pyrotechnic impact test is shown;

[0040] Figure 5 is an end view of some other embodiments of the first inner elastic support;

[0041] Figure 6 yes Figure 5 A partial enlarged view of area B.

[0042] In the accompanying drawings, 110, the core; 111, the warhead; 112, the tail; 113, the limiting ring; 120, the first inner support; 121, the first buffer step ring; 122, the first buffer cavity; 123, the first impact-resistant structure; 1231, the rigid node ring; 1232, the flexible connecting belt; 1233, the flexible filler; 1234, the rigid filler; 130, the second inner support; 131, the second buffer step ring; 132, the second buffer cavity; 140, the first shell; 150, the second shell; 160, the locking nut; 170, the first washer; 180, the second washer. DETAILED DESCRIPTION

[0043] The technical solution of the present invention will be clearly and completely described below in conjunction with the embodiments. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0044] As the background technology shows, due to the increasingly diversified requirements of pyrotechnic impact tests and the increasing test magnitude, the projectiles are subject to increasing impact forces during pyrotechnic impact tests, which makes them very susceptible to damage. Traditional air cannon projectiles are integrated structures, and when they are partially damaged, the entire projectile becomes waste, and the number of times they can be recycled is still low.

[0045] To solve the above problems, refer to Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 and Figure 6The present invention provides a high-g value air cannon projectile for a spacecraft pyrotechnic impact test, comprising a core 110, a first inner support 120, a second inner support 130, a first shell 140, a second shell 150, a locking nut 160, a first washer 170 and a second washer 180. One end of the core 110 is a warhead 111, and the other end is a tail 112. The warhead 111 is used to impact a response plate. A limiting ring 113 is provided at one end of the core 110 close to the warhead 111. The first inner support 120 is sleeved on the core 110 and is arranged close to the warhead 111. The second inner support 130 is sleeved on the core 110 and is arranged close to the tail 112. The first shell 140 and the first inner support are sleeved outside the first inner support 120 in the form of interference fit. The second shell 150 and the second inner support 130 are sleeved outside the second inner support 130 in the form of interference fit. The outer walls of the first shell 140 and the second shell 150 can be respectively fitted to the inner wall of the barrel. When the air cannon projectile is fired, the first shell 140, the second shell 150, the first inner support 120 and the second inner support 130 cooperate to limit the movement of the core 110 in a straight line and prevent the core 110 from unexpected eccentricity and rotation. The locking nut 160 is screwed on the tail 112 to facilitate the assembly, use and disassembly of the locking nut 160 and the core 110, and then facilitate the disassembly of the core 110, the first inner support 120, the second inner support 130, the first shell 140 and the second shell 150. The locking nut 160 cooperates with the limiting ring 113 to better limit the axial movement of the first inner support 120, the second inner support 130, the first shell 140 and the second shell 150 along the core 110 to ensure the stability of the air cannon projectile structure under strong impact loads. The first washer 170 is arranged between the first inner spring support 120 and the limit ring 113, and the second washer 180 is arranged between the second inner spring support 130 and the locking nut 160 to prevent loosening of the components under strong impact loads, and further ensure the stability of the overall structure of the air cannon projectile. On the whole, the modular design is adopted, and when one or some components are damaged, they can be replaced in time, which prolongs the service life of the air cannon projectile, increases the number of times the air cannon projectile can be recycled, reduces the test cost, has a high engineering application value, avoids the occurrence of unexpected eccentricity, rotation, and deformation aggravation caused by local damage to the air cannon projectile, ensures the accuracy of the results of the later tests, and improves the test efficiency.

[0046] It should be noted that when the air cannon projectile hits the response plate, the air cannon is subjected to a reaction force, which can be transmitted along the axial direction and radial direction of the core 110 .

[0047] Specifically, in the example, Figure 2 , Figure 3 and Figure 4As shown, a first buffer step ring 121 is formed at one end of the first inner support 120 close to the first gasket 170. One side of the first buffer step ring 121 is attached to the first gasket 170, and the other end surface is attached to the end surface of the first shell 140. A second buffer step ring 131 is formed at one end of the second inner support 130 close to the second gasket 180, one side of the second buffer step ring 131 is attached to the second gasket 180, and the other end surface is attached to the end surface of the second shell 150. The first buffer step ring 121 and the second buffer step ring 131 can buffer radial shock waves. A plurality of first buffer cavities 122 are uniformly formed along the circumferential direction between the inner wall and the outer wall of the first inner support 120. A plurality of second buffer cavities 132 are uniformly formed along the circumferential direction between the inner wall and the outer wall of the second inner support 130. The plurality of first buffer cavities 122 and the second buffer cavities 132 can effectively buffer the shock waves transmitted from the core 110 to the shell. On the whole, first-level shock absorption is achieved, which greatly improves the shock absorption and buffering capacity of the air cannon projectile and extends the service life of the air cannon projectile.

[0048] Preferably, a first buffer step groove adapted to the first buffer step ring 121 is formed on one end surface of the first shell 140 near the first buffer step ring 121. The first buffer step ring 121 cooperates with the first buffer step groove, which not only improves the air tightness of the contact position, but also improves the buffering effect. A second buffer step groove adapted to the second buffer step ring 131 is formed on one end surface of the second shell 150 near the second buffer step ring 131. The second buffer step ring 131 cooperates with the second buffer step groove, which not only improves the air tightness of the contact position, but also improves the buffering effect.

[0049] Preferably, the first inner support 120 and the second inner support 130 are made of lightweight metal materials such as aluminum alloy or titanium alloy, which have very high specific strength and specific modulus.

[0050] Preferably, the first shell 140 and the second shell 150 are made of a high molecular polymer material, which can absorb a certain shock wave from the core 110, provide a secondary shock absorption for the first buffer step ring 121 and the second buffer step ring 131, further extend the service life of the air cannon projectile, and facilitate the air cannon projectile to hit the response plate at a higher impact speed. In addition, since the first shell 140 and the second shell 150 are made of a high molecular polymer material, the friction on the barrel can be reduced, and the service life of the barrel can be extended.

[0051] Preferably, the wall thickness of the first shell 140 and the second shell 150 is 5 mm-10 mm, and the thickness of the first gasket 170 and the second gasket 180 is 3 mm.

[0052] Preferably, the cross section of each first buffer cavity 122 is fan-shaped, and the cross section of each second buffer cavity 132 is fan-shaped, which further improves the buffering capacity.

[0053] In other embodiments, such as Figure 5 and Figure 6 As shown, a first impact-resistant structure 123 is provided in each first buffer cavity 122. A second impact-resistant structure is provided in each second buffer cavity 132. The first impact-resistant structure 123 includes a plurality of rigid node rings 1231, flexible connecting belts 1232, flexible fillers 1233 and rigid fillers 1234. The plurality of rigid node rings 1231 are arranged in multiple rows and columns. Each rigid node ring 1231 is connected to a plurality of flexible connecting belts 1232, and each flexible connecting belt 1232 is located on the tangent of the rigid node ring 1231. The flexible filler 1233 is filled between the plurality of flexible connecting belts 1232. The rigid filler 1234 is filled in each rigid node ring 1231. When subjected to a strong impact load, the impact direction and the side are compressed, the material gathers at the impacted part, the local density of the structure increases, and the impact resistance is significantly improved. The second impact-resistant structure is the same as the first impact-resistant structure 123, and will not be repeated here. It should be noted that the first anti-impact structure 123 is connected to the inner wall of the first buffer cavity 122 by bonding, the second anti-impact structure is connected to the inner wall of the second buffer cavity 132 by bonding, and the flexible connecting belt 1232 is connected to the flexible filler 1233 by bonding. The flexible connecting belt 1232 can be made of carbon fiberglass, and the flexible filler 1233 can be low-density polyurethane, which is conducive to the lightweight design of the air cannon projectile. The rigid filler 1234 is a metal filler.

[0054] Preferably, the edge of the bullet 111 is chamfered, which can not only reduce the wind resistance of the air cannon projectile during flight, but also ensure the contact area between the bullet and the object being struck and the consistency of each impact.

[0055] Preferably, the first washer 170 and the second washer 180 are self-locking washers, which ensure that the clamping force is still maintained under strong vibration, can effectively prevent vibration loosening, have strong resistance to temperature deformation and durability, and can be reused.

[0056] Preferably, the locking nut 160 is a self-locking hexagonal cap nut, which has the advantages of light weight, high strength, good corrosion resistance, etc.

[0057] Preferably, the elastic core 110 , the first washer 170 , the second washer 180 and the locking nut 160 are all made of high-strength steel.

[0058] In the description of the present invention, it is to be understood that the terms “center”, “longitudinal”, “lateral”, “length”, “width”, “thickness”, “up”, “down”, “front”, “back”, “left”, “right”, “vertical”, “horizontal”, “top”, “bottom”, “inside”, “outside”, “clockwise”, “counterclockwise”, “axial”, “radial”, “circumferential”, etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0059] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0060] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral one; it can be a mechanical connection, an electrical connection, or communication with each other; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0061] In the present invention, the terms "one embodiment", "some embodiments", "examples", "specific examples", or "some examples" etc. mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the described specific features, structures, materials or characteristics may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0062] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations of the present invention. A person skilled in the art may change, modify, replace and vary the above embodiments within the scope of the present invention.

Claims

1. A high-g air cannon projectile for spacecraft pyrotechnic impact testing, characterized in that: include: The core has a bullet head at one end and a bullet tail at the other end; a limiting ring is provided at one end of the core close to the bullet head; A first inner support, which is sleeved on the bullet core and disposed close to the bullet head; A second inner spring support is sleeved on the spring core and disposed close to the spring tail; A first shell, sleeved outside the first inner elastic support; A second shell, sleeved outside the second inner elastic support; A locking nut, threadedly connected to the tail of the projectile, to limit the axial movement of the first inner support, the second inner support, the first shell and the second shell along the core; A first washer, arranged between the first inner elastic support and the limiting ring; The second washer is arranged between the second inner elastic support and the locking nut.

2. The high-g air cannon projectile for spacecraft pyrotechnic impact test according to claim 1, characterized in that: A first buffer step ring is formed at one end of the first inner elastic support close to the first gasket; one side surface of the first buffer step ring is attached to the first gasket, and the other end surface is attached to the end surface of the first shell; A plurality of first buffer cavities are uniformly formed along the circumferential direction between the inner wall and the outer wall of the first inner elastic support; A second buffer step ring is formed at one end of the second inner elastic support close to the second gasket; one side surface of the second buffer step ring is attached to the second gasket, and the other end surface is attached to the end surface of the second shell; A plurality of second buffer cavities are uniformly formed along the circumferential direction between the inner wall and the outer wall of the second inner elastic support.

3. The high-g air cannon projectile for spacecraft pyrotechnic impact test according to claim 2, characterized in that: The first inner spring support and the second inner spring support are made of lightweight metal material; The first shell and the second shell are made of high molecular polymer material.

4. The high-g air cannon projectile for spacecraft pyrotechnic impact test according to claim 2, characterized in that: The cross section of each of the first buffer chambers is fan-shaped; The cross section of each of the second buffer chambers is fan-shaped.

5. The high-g air cannon projectile for spacecraft pyrotechnic impact test according to claim 2, characterized in that: A first anti-impact structure is provided in each of the first buffer cavities; A second anti-impact structure is disposed in each of the second buffer cavities.

6. The high-g air cannon projectile for spacecraft pyrotechnic impact test according to claim 5, characterized in that: The first impact-resistant structure comprises: There are multiple rigid node rings, which are arranged in multiple rows and columns; Flexible connecting belt; each of the rigid node rings is connected to a plurality of flexible connecting belts, and each of the flexible connecting belts is located on a tangent line of the rigid node ring; Flexible filler, filled between the plurality of flexible connecting belts; A rigid filler filled in each of the rigid node rings; The second impact-resistant structure is the same as the first impact-resistant structure.

7. The high-g air cannon projectile for spacecraft pyrotechnic impact test according to any one of claims 1 to 6, characterized in that: The edge of the bullet head is chamfered.

8. The high-g air cannon projectile for spacecraft pyrotechnic impact test according to any one of claims 1 to 6, characterized in that: The wall thickness of the first shell and the second shell is 5mm-10mm.

9. The high-g air cannon projectile for spacecraft pyrotechnic impact test according to any one of claims 1 to 6, characterized in that: The first washer and the second washer are self-locking washers.

10. The high-g air cannon projectile for spacecraft pyrotechnic impact test according to any one of claims 1 to 6, characterized in that: The locking nut is a self-locking hexagonal cap nut.

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