Ultrahigh-speed pneumatic separation stable flight integrated front and back centering sabot for tailless projectile

Abstract

The invention belongs to the technical field of warheads of ammunition, and particularly relates to an ultra-high-speed pneumatic separation stable flight integrated front and back centering sabot for a tailless projectile, which comprises double ammunition belts, an outer sabot, a bottom support, a gasket, a hoop, a lining and a front and back centering part, through the structural design that the lining is convex outwards and the outer sabot is concave inwards to form a windward nest, the separation process of the sabot and a penetration body can be regulated and controlled under the action of ultra-high-speed airflow, the sabot is gradually separated backwards in the pneumatic separation process to achieve backward movement of a pressure center, and therefore pneumatic stability of the empennage-free unstable projectile body under long-distance flight is achieved; meanwhile, initial damage of the tail of the penetration body under the action of gunpowder gas and weakening of external threads of the penetration body on the structural strength can be avoided in an integrated bottom pushing mode, and influences on subsequent penetration results are avoided; and the stability of in-chamber movement of the projectile support and the penetration body is improved through double projectile belts and front-back centering.

Description

Technical Field

[0001] The invention belongs to the technical field of warheads of ammunition, and in particular relates to an integrated front and rear centering bullet support for ultra-high-speed aerodynamic separation stable flight of a tailless bullet. Background Art

[0002] As the weapon system's requirements for warhead penetration speed continue to increase, it is inevitable to use a large-caliber artillery firing platform to launch sub-caliber warheads. The sabot is an important component of the sub-caliber warhead artillery firing test. Its main functions are: to drive and guide the warhead to move under the action of the gunpowder gas pressure in the chamber to ensure the good movement of the warhead in the chamber; after leaving the chamber, under the action of high-speed airflow, the flight and separation process ensures the flight stability of the warhead. Under the action of the gunpowder gas pressure in the chamber and the high-speed incoming flow after leaving the chamber, the sabot gives the warhead a large target impact kinetic energy and a good target impact posture.

[0003] The commonly used sabot at present is the tail fin stabilized drag separated discarding sabot sabot, and its structure is as follows: Figure 1 The saddle-shaped clip valve shown in the figure mainly includes a clip valve, a belt and a tail fin, and generally adopts a three-flap type to facilitate stable separation after leaving the barrel. Its working process is as follows: after the gun barrel is ignited, the gunpowder gas in the barrel acts on the cartridge clip valve, and the air in the barrel is closed through the belt, which pushes the cartridge clip and the penetrator to move; the rear cavity of the clip valve generates a clamping force under the action of the gunpowder gas in the barrel, and combined with the thread between the clip valve and the penetrator, it ensures that the cartridge clip and the penetrator remain as one when moving in the barrel; after leaving the barrel, the gunpowder gas pressure at the base of the projectile decreases, and the wind resistance pressure difference caused by the diameter difference between the penetrator and the cartridge clip becomes apparent, and the high-speed airflow forms a shock wave at the front end of the clip valve, and forms a high-pressure area in the front cavity, generating a separation force and a separation torque, realizing the rapid separation of the clip valve and the penetrator, and giving the penetrator a better initial posture; after the clip valve separates, the penetrator continues to fly stably under the action of the tail fin at the tail of the projectile, and implements penetration with a good target-impacting posture.

[0004] The flap-type sabot can achieve rapid and stable separation for a flight-stabilized projectile with a tail, and the flap has little effect on the flight attitude of the projectile during aerodynamic separation. The penetrator with a tail can still maintain flight stability after the flap is separated. The flap-type discarding sabot is more suitable for a tail-stabilized projectile; however, in a large number of engineering practices, the purpose of the test determines that the test projectile is not allowed to install a tail. For a tailless projectile, the center of mass coefficient is usually above 0.52. When its speed is between 2.5Ma-3.5Ma (about 850-1020m / s), the projectile pressure center coefficient usually varies between 0.38-0.42. The pressure center is in front of the center of mass, and the aerodynamic shape of the projectile is statically unstable, which will inevitably lead to the instability of the projectile's attitude as the flight distance increases, and the higher the speed, the greater the possibility of instability. For an unstabilized projectile without a tail, after the clip-type sabot is quickly detached, the flight attitude of the projectile will quickly become unstable and diverge within a few meters, and the attitude angle will rapidly amplify nonlinearly, resulting in an irreversible change in attitude, causing the projectile to have a very large angle of attack and yaw before hitting the target, or even hit the target horizontally, and unable to complete normal penetration. At the same time, due to the presence of the tail, it is impossible to wrap the tail structure of the projectile, which may cause initial damage to the projectile material under the high speed, high pressure and high temperature of the gunpowder gas; on the other hand, the existence of the force transmission thread connecting the clip-type sabot with tail and the penetrator may reduce the structural strength of the penetrator. The above factors will affect the subsequent penetration results. Summary of the invention

[0005] 1. Technical issues to be resolved

[0006] The technical problem to be solved by the present invention is: how to provide an integrated front and rear centering bullet support for ultra-high-speed aerodynamic separation and stable flight for a tailless projectile, which can improve the flight stability of the penetrator in the bore without reducing the structural strength of the penetrator, and in the process of ultra-high-speed aerodynamic separation outside the bore, realize the long-distance flight stability of the tailless unstable projectile through pressure center control, so as to enable the penetrator to complete penetration in a good target-impacting posture during long-distance flight.

[0007] (II) Technical solution

[0008] In order to solve the above technical problems, the present invention provides a tailless projectile with an ultra-high-speed aerodynamic separation stable flight integrated front and rear centering support. Figure 2 As shown, the tailless bullet ultra-high-speed aerodynamic separation stable flight integrated front and rear centering bullet support comprises: double bullet belts, outer bullet support, bottom support, gasket, clamp, lining, front and rear centering;

[0009] The cartridge case adopts double elastic belts to realize reliable air sealing in the chamber, adopts cartridge case bottom push mode to realize acceleration of cartridge case and penetrator under the action of gunpowder gas, and prevents the projectile material from initial damage under the action of gunpowder gas at high speed, high pressure and high temperature by packaging the cartridge case, and adds a high-strength gasket at the joint between the cartridge case and the erosion body, thereby increasing the area of ​​the cartridge case acting on the recoil of the penetrator body and the bottom strength stiffness, and improving the strength reliability of the cartridge case;

[0010] The cartridge case is composed of a liner made of a light material and an outer cartridge case made of a strong material. The inner liner does not separately wrap the erosion body, and the outer cartridge case is arranged outside the inner liner. The outer cartridge case is arranged in a saddle-shaped structure to achieve the lightness of the cartridge case structure of the sub-caliber penetrator. A clamp made of a strong material is arranged at the bottom of the inner liner to ensure the centering of the penetrator in the cartridge case during the acceleration process in the bore, thereby avoiding stress concentration.

[0011] The cartridge case adopts front and rear centering to improve the in-bore movement stability of the cartridge case and the penetrator;

[0012] At the head of the sabot, the shape of the inner lining is set to a convex shape, and the shape of the outer sabot is set to a concave shape. A windward socket is formed by the convexity of the inner lining and the concaveness of the outer sabot, and a shock wave high-pressure area is formed at the head of the sabot. The windward socket structure is designed to realize the aerodynamic difference and separation process regulation between the sabot and the penetrator under the action of ultra-high-speed airflow. Through the aerodynamic separation process, the sabot gradually detaches backwards to achieve the gradual backward movement of the pressure center, thereby realizing aerodynamic stability of the tailless and unstable projectile during long-distance flight, ensuring that the penetrator can carry out subsequent penetration in a good target-impacting posture.

[0013] The tailless bullet uses ultra-high-speed aerodynamic separation to stabilize flight, and the integrated front and rear centering bullet support wraps the erosion body for a length that is not less than 2 / 3 of the total length of the penetrator.

[0014] The inner lining is made of nylon material.

[0015] The outer elastic support, the clamp and the bottom support are made of aluminum alloy material.

[0016] The gasket of the bottom bracket is made of lightweight and high-strength titanium alloy.

[0017] The double elastic belt is made of copper material.

[0018] The base support and the outer support are connected by threads, the clamp is in local contact with the penetrator, and the middle part of the outer support is formed into a saddle-shaped structure, which ensures strength while reducing the additional weight of the support.

[0019] The clamp adopts Figure 3 The step form shown is clamped in local contact with the penetrator.

[0020] When the constraints of the firing platform, the safety of the launch personnel and the site conditions under hypervelocity penetration are taken into account in the test, and the tailless projectile is required to fly stably over a long distance, a larger cone angle is used to form a convexity at the windward socket of the nylon liner, and a straight line segment + a smaller diameter arc segment are used to form a concaveness at the windward socket of the aluminum alloy outer support, so that the wind resistance difference between the support and the penetrator is appropriately reduced, thereby increasing the interaction time between the support and the tailless penetrator.

[0021] Under the condition of a speed of about 3Ma, when the ultra-high-speed flight distance is 30m-40m, it is more appropriate for the cone angle of the nylon lining windward socket to be about 15°, the length of the straight section of the windward socket of the aluminum alloy outer support to be about 0.5 times the total length of the windward socket, and the radius of the arc section to be about 2.2 times the total length of the windward socket, which can maintain the stable flight of the tailless projectile within a distance of about 30m-40m.

[0022] (III) Beneficial effects

[0023] Compared with the prior art, the key points of the present invention are:

[0024] (1) The present invention is an integrated bottom pusher cartridge case, wherein the bottom support and the outer support are connected by threads, and the bottom support is wrapped to prevent the projectile material from being initially damaged under the high speed, high pressure and high temperature of gunpowder gas; a high-strength gasket is used at the bottom of the cartridge case to increase the area of ​​the bottom support acted on by the recoil of the penetrator and the bottom strength and stiffness, thereby improving the strength reliability of the bottom support.

[0025] (2) The present invention adopts double elastic belts to achieve reliable air sealing in the chamber, and adopts front and rear centering to improve the movement stability of the cartridge case and the penetrator in the chamber.

[0026] (3) The present invention adopts a combination of a lightweight material liner + a strong material outer support and a saddle-shaped structure to achieve lightweight support for a strong sub-caliber penetrator. A strong material clamp is used at the bottom of the liner to ensure the centering of the penetrator in the support during the acceleration process in the bore, thereby avoiding stress concentration. The clamp is in a stepped form to locally contact and clamp the penetrator to achieve lightweight support.

[0027] (4) The present invention forms a windward fossa by the outward convexity of the inner lining and the inward concavity of the outer buttstock, and realizes the regulation of the separation process between the buttstock and the penetrator under the action of ultra-high-speed airflow through the structural design of the windward fossa. The buttstock gradually detaches backwards during the aerodynamic separation process to realize the rearward movement of the center of pressure, thereby realizing the aerodynamic stability of the tailless unstable projectile during long-distance flight.

[0028] (5) The wrapped length of the sabot of the present invention should not be less than 2 / 3 of the length of the penetrator. When the hyperspeed flight distance is about 30m-40m, it is recommended that the cone angle of the inner liner windward dimple be about 15°, and the windward dimple of the outer sabot adopts a combination of straight segment + arc segment. When the length of the straight segment is about 0.5 times the total length of the windward dimple and the radius of the arc segment is about 2.2 times the total length of the windward dimple, the wind resistance difference between the sabot and the penetrator and the rearward movement speed of the center of pressure are more appropriate.

[0029] (6) The inner lining of the present invention is recommended to be made of nylon material, the outer spring support, clamp and bottom support are recommended to be made of aluminum alloy material, the bottom gasket is recommended to be made of lightweight and high-strength titanium alloy material, and the elastic belt is recommended to be made of copper material.

[0030] Effects of the present invention:

[0031] The advantage of the cartridge case of the present invention is that, through the design of the windward dimple structure of the convex inner lining and the concave outer cartridge case, the separation process of the cartridge case and the penetrator under the action of ultra-high-speed airflow can be regulated, and the cartridge case gradually detaches backwards through the aerodynamic separation process to achieve the rearward movement of the center of pressure, thereby achieving aerodynamic stability of the tailless unstable projectile under long-distance flight; at the same time, the initial damage to the tail of the penetrator under the action of gunpowder gas and the weakening of the structural strength by the external thread of the penetrator can be avoided through the integrated bottom push method, thereby avoiding the impact on the subsequent penetration results; the movement stability of the cartridge case and the penetrator in the bore is improved through the double elastic belt and the front and rear centering. Figure 4 The flight process of the tailless unstable projectile after adopting the ultra-high-speed aerodynamic separation stable flight integrated sabot of the present invention is recorded at high speed. The backward shift of the center of pressure can be achieved by the gradual backward separation of the integrated sabot of the present invention during the flight, ensuring that the tailless unstable projectile maintains good flight stability above 40m and implements subsequent penetration with a good target-impacting posture.

[0032] The integrated front and rear centering cartridge case for the tailless projectile with ultra-high speed aerodynamic separation and stable flight is an indispensable and important component in the sub-caliber artillery firing test of the tailless unstable penetrator. It can achieve good flight stability of the tailless unstable penetrator in ultra-high speed and long-distance flight, and give the penetrator a good target-impacting posture, thus laying an important foundation for conducting ultra-high speed penetration research. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 This is a diagram of the main components of a traditional tail-stabilized drag-separating discarding sabot sabot.

[0034] Figure 2 Schematic diagram of the integrated front and rear centering supports for the ultra-high-speed aerodynamic separation and stable flight of the tailless missile.

[0035] Figure 3 Schematic diagram of a stepped contact clamp.

[0036] Figure 4Schematic diagram of the stable flight process of a tailless, unstable projectile as the integrated sabot gradually detaches. DETAILED DESCRIPTION

[0037] In order to make the purpose, content, and advantages of the present invention more clear, the specific implementation methods of the present invention are further described in detail below in conjunction with the accompanying drawings and examples.

[0038] In order to solve the above technical problems, the present invention provides a tailless projectile with an ultra-high-speed aerodynamic separation stable flight integrated front and rear centering support. Figure 2 As shown, the tailless bullet ultra-high-speed aerodynamic separation stable flight integrated front and rear centering bullet support comprises: double bullet belts, outer bullet support, bottom support, gasket, clamp, lining, front and rear centering;

[0039] The cartridge case adopts double elastic belts to realize reliable air sealing in the chamber, adopts cartridge case bottom push mode to realize acceleration of cartridge case and penetrator under the action of gunpowder gas, and prevents the projectile material from initial damage under the action of gunpowder gas at high speed, high pressure and high temperature by packaging the cartridge case, and adds a high-strength gasket at the joint between the cartridge case and the erosion body, thereby increasing the area of ​​the cartridge case acting on the recoil of the penetrator body and the bottom strength stiffness, and improving the strength reliability of the cartridge case;

[0040] The cartridge case is composed of a liner made of a light material and an outer cartridge case made of a strong material. The inner liner does not separately wrap the erosion body, and the outer cartridge case is arranged outside the inner liner. The outer cartridge case is arranged in a saddle-shaped structure to achieve the lightness of the cartridge case structure of the sub-caliber penetrator. A clamp made of a strong material is arranged at the bottom of the inner liner to ensure the centering of the penetrator in the cartridge case during the acceleration process in the bore, thereby avoiding stress concentration.

[0041] The cartridge case adopts front and rear centering to improve the in-bore movement stability of the cartridge case and the penetrator;

[0042] At the head of the sabot, the shape of the inner lining is set to a convex shape, and the shape of the outer sabot is set to a concave shape. A windward socket is formed by the convexity of the inner lining and the concaveness of the outer sabot, and a shock wave high-pressure area is formed at the head of the sabot. The windward socket structure is designed to realize the aerodynamic difference and separation process regulation between the sabot and the penetrator under the action of ultra-high-speed airflow. Through the aerodynamic separation process, the sabot gradually detaches backwards to achieve the gradual backward movement of the pressure center, thereby realizing aerodynamic stability of the tailless and unstable projectile during long-distance flight, ensuring that the penetrator can carry out subsequent penetration in a good target-impacting posture.

[0043] The tailless bullet uses ultra-high-speed aerodynamic separation to stabilize flight, and the integrated front and rear centering bullet support wraps the erosion body for a length that is not less than 2 / 3 of the total length of the penetrator.

[0044] The inner lining is made of nylon material.

[0045] The outer elastic support, the clamp and the bottom support are made of aluminum alloy material.

[0046] The gasket of the bottom bracket is made of lightweight and high-strength titanium alloy.

[0047] The double elastic belt is made of copper material.

[0048] The base support and the outer support are connected by threads, the clamp is in local contact with the penetrator and clamped, and the middle part of the outer support is formed into a saddle-shaped structure, which ensures strength while reducing the additional weight of the support.

[0049] The clamp adopts Figure 3 The step form shown is clamped in local contact with the penetrator.

[0050] When the constraints of the firing platform, the safety of the launch personnel and the site conditions under hypervelocity penetration are taken into account in the test, and the tailless projectile is required to fly stably over a long distance, a larger cone angle is used to form a convexity at the windward socket of the nylon liner, and a straight line segment + a smaller diameter arc segment are used to form a concaveness at the windward socket of the aluminum alloy outer support, so that the wind resistance difference between the support and the penetrator is appropriately reduced, thereby increasing the interaction time between the support and the tailless penetrator.

[0051] Under the condition of a speed of about 3Ma, when the ultra-high-speed flight distance is 30m-40m, it is more appropriate for the cone angle of the nylon lining windward socket to be about 15°, the length of the straight section of the windward socket of the aluminum alloy outer support to be about 0.5 times the total length of the windward socket, and the radius of the arc section to be about 2.2 times the total length of the windward socket, which can maintain the stable flight of the tailless projectile within a distance of about 30m-40m.

[0052] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the technical principles of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims

1. An integrated front and rear centering sabot for an ultra-high-speed aerodynamic separation stable flight for a tailless projectile, characterized in that: The tailless projectile ultra-high-speed aerodynamic separation stable flight integrated front and rear centering bullet support comprises: double bullet belts, an outer bullet support, a bottom support, a gasket, a clamp, an inner lining, and a front and rear centering; The cartridge case adopts double elastic belts to realize reliable air sealing in the chamber, adopts cartridge case bottom push mode to realize acceleration of cartridge case and penetrator under the action of gunpowder gas, and prevents the projectile material from initial damage under the action of high speed, high pressure and high temperature of gunpowder gas by packaging the cartridge case, and adds a gasket at the joint between the cartridge case and the erosion body, thereby increasing the area of ​​the cartridge case acting on the recoil of the penetrator body and the bottom strength stiffness, and improving the strength reliability of the cartridge case; The cartridge case is composed of a liner made of a light material and an outer cartridge case made of a strong material. The inner liner does not separately wrap the erosion body, and the outer cartridge case is arranged outside the inner liner. The outer cartridge case is arranged in a saddle-shaped structure to achieve the lightness of the cartridge case structure of the sub-caliber penetrator, and a clamp is arranged at the bottom of the inner liner to ensure the centering of the penetrator in the cartridge case during the acceleration process in the bore, thereby avoiding stress concentration. The cartridge case adopts front and rear centering to improve the in-bore movement stability of the cartridge case and the penetrator; At the head of the sabot, the shape of the inner lining is set to a convex shape, and the shape of the outer sabot is set to a concave shape. A windward socket is formed by the convexity of the inner lining and the concaveness of the outer sabot, and a shock wave high-pressure area is formed at the head of the sabot. The windward socket structure is designed to realize the aerodynamic difference and separation process regulation between the sabot and the penetrator under the action of ultra-high-speed airflow. Through the aerodynamic separation process, the sabot gradually detaches backwards to achieve the gradual backward movement of the pressure center, thereby realizing aerodynamic stability of the tailless and unstable projectile during long-distance flight, ensuring that the penetrator can carry out subsequent penetration in a good target-impacting posture.

2. The tailless projectile ultra-high-speed aerodynamic separation stable flight integrated front and rear centering bullet support as claimed in claim 1, characterized in that: The tailless bullet uses ultra-high-speed aerodynamic separation to stabilize flight, and the integrated front and rear centering bullet support wraps the erosion body for a length that is not less than 2 / 3 of the total length of the penetrator.

3. The tailless projectile ultra-high-speed aerodynamic separation stable flight integrated front and rear centering bullet support as claimed in claim 1, characterized in that: The inner lining is made of nylon material.

4. The tailless projectile ultra-high-speed aerodynamic separation stable flight integrated front and rear centering bullet support as claimed in claim 1, characterized in that: The outer elastic support, the clamp and the bottom support are made of aluminum alloy material.

5. The tailless projectile ultra-high-speed aerodynamic separation stable flight integrated front and rear centering bullet support as claimed in claim 1, characterized in that: The gasket of the bottom bracket is made of lightweight and high-strength titanium alloy.

6. The tailless projectile ultra-high-speed aerodynamic separation stable flight integrated front and rear centering bullet support as claimed in claim 1, characterized in that: The double elastic belt is made of copper material.

7. The tailless projectile ultra-high-speed aerodynamic separation stable flight integrated front and rear centering bullet support as claimed in claim 1, characterized in that: The base support and the outer support are connected by threads, the clamp is in local contact with the penetrator and clamped, and the middle part of the outer support is formed into a saddle-shaped structure, which ensures strength while reducing the additional weight of the support.

8. The tailless projectile ultra-high-speed aerodynamic separation stable flight integrated front and rear centering bullet support as claimed in claim 7, characterized in that: The clamp is in stepped form and is in local contact with the penetrating body.

9. The tailless projectile ultra-high-speed aerodynamic separation stable flight integrated front and rear centering bullet support as claimed in claim 8, characterized in that: When the constraints of the firing platform, the safety of the launch personnel and the site conditions under hypervelocity penetration are taken into account in the test, and the tailless projectile is required to fly stably over a long distance, a larger cone angle is used to form a convexity at the windward socket of the nylon liner, and a straight line segment + a smaller diameter arc segment are used to form a concaveness at the windward socket of the aluminum alloy outer support, so that the wind resistance difference between the support and the penetrator is appropriately reduced, thereby increasing the interaction time between the support and the tailless penetrator.

10. The tailless projectile ultra-high-speed aerodynamic separation stable flight integrated front and rear centering bullet support as claimed in claim 9, characterized in that: Under the speed of 3Ma, when the ultra-high-speed flight distance is 30m-40m, the cone angle of the nylon lining windward socket is 15°, the length of the straight section of the windward socket of the aluminum alloy outer support is 0.5 times the total length of the windward socket, and the radius of the arc section is 2.2 times the total length of the windward socket, which can maintain the stable flight of the tailless projectile within a distance of about 30m-40m.

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