Sniper bullet head multi-section type resistance reduction structure based on fluid dynamics

Abstract

The invention relates to the technical field of bullets, in particular to a hydrodynamics-based sniper bullet multi-section type resistance reduction structure which comprises a shock wave control section, a pneumatic transition section and a wake flow regulation and control section, and the shock wave control section, the pneumatic transition and friction reduction section and the wake flow regulation and control section are of an integrally formed structure; the shock wave control section comprises a precise flat head, a flat head fillet, a front wedge angle surface and a rear wedge angle surface which are connected in sequence; the pneumatic transition section is of a variable-curvature ellipsoid structure and is made of tungsten alloy, and a laser micro-texture layer is arranged on the outer surface of the pneumatic transition section. The shock wave control section is arranged, and the wave resistance is reduced by more than 25%; due to the variable-curvature structure of the pneumatic transition section, the airflow adhesion rate is increased to 95% or above, and the differential pressure resistance is remarkably reduced; the wake flow regulation and control section effectively inhibits tail vortexes, the differential pressure resistance is further reduced, a continuous airflow regulation and control chain of shock wave control, friction reduction and wake flow stabilization is formed, and the total resistance coefficient is reduced by 50%.

Description

Technical Field

[0001] This invention relates to the field of projectile technology, and more specifically to a multi-segment drag reduction structure for sniper projectiles based on hydrodynamics. Background Technology

[0002] Sniper rifle ammunition is primarily used for long-range precision strikes against key personnel targets. It typically consists of four main components: the bullet, the cartridge case, the primer, and the propellant. To ensure high accuracy and consistent trajectory, the bullet usually consists only of a jacket and a lead core. To achieve effective engagement at greater distances, sniper bullets are generally slightly heavier than other ammunition of the same caliber, allowing them to travel a longer distance through the air.

[0003] In sniper operations, the effective range, accuracy, and flight stability of a projectile are the core indicators determining the success or failure of a mission, and these indicators are all directly related to the hydrodynamic characteristics of the projectile during flight. When a sniper bullet flies at supersonic speeds, air resistance increases dramatically, mainly including wave drag, pressure drag, and friction drag. Among these, wave drag and pressure drag account for more than 70% of the total drag and are the key factors limiting projectile performance.

[0004] Current sniper bullets mostly employ a single-stage structure, such as a simple pointed or blunt-nosed design. Blunt-nosed bullets generate strong detached shock waves during supersonic flight, resulting in extremely high wave drag and rapid energy decay, thus limiting effective range. While simple pointed bullets can reduce some wave drag, they are prone to generating large vortex regions due to airflow separation during the transition from supersonic to subsonic speeds, increasing pressure drag and compromising flight stability, thus reducing accuracy. Furthermore, current bullets have a flat tail section. Due to this flatness, air flowing through the cylindrical part of the bullet cannot immediately reach the bottom due to inertia, creating a low-pressure area at the bottom. Air entering this low-pressure area forms vortices, compressing the air at the front of the bullet and increasing pressure. This creates a pressure difference between the front and rear ends of the bullet. Summary of the Invention

[0005] The purpose of this invention is to solve the problems existing in the prior art and to propose a multi-segment drag reduction structure for sniper projectiles based on fluid dynamics.

[0006] To achieve the above objectives, the present invention adopts the following technical solution:

[0007] A multi-segment drag reduction structure for a sniper projectile based on fluid dynamics includes a shock wave control section, an aerodynamic transition section, and a wake control section. The shock wave control section, the aerodynamic transition and friction reduction section, and the wake control section are integrally formed structures.

[0008] The shock wave control section includes a precision flat head, a flat head with rounded corners, a front wedge surface, and a rear wedge surface connected in sequence.

[0009] The aerodynamic transition section is a variable curvature ellipsoidal structure, the aerodynamic transition section is made of tungsten alloy, and the outer surface of the aerodynamic transition section is provided with a laser microtextured layer;

[0010] The wake control section includes a spiral stabilizing groove and a tail cone outlet end face.

[0011] Preferably, the diameter of the precision flat head is 0.8-1.2mm, forming a dual shock wave system to reduce transonic drag fluctuations. The radius of the rounded corner of the flat head is 0.15mm to avoid excessive airflow stripping that could cause turbulence. The angle of the front wedge is 9.7°±0.2° to guide shock wave deflection and reduce axial shock wave superposition. The angle of the rear wedge is 11.3°±0.2° to connect the mid-section airflow and suppress shock wave intensity.

[0012] Preferably, the shock wave control section is made of a nickel-chromium alloy with a density of 7.8 g / cm³. 3 The length of the shock wave control section accounts for 10-15% of the total length of the warhead.

[0013] Preferably, the shock wave control section and the aerodynamic transition section are connected by a heterogeneous alloy bonding surface to achieve a tight connection between the nickel-chromium alloy and the tungsten alloy.

[0014] Preferably, the laser microtextured layer has a thickness of 8 μm and is used to form an air film to reduce the surface friction coefficient. The laser microtextured layer is coated with a polytetrafluoroethylene coating with a thickness of 3-5 μm to further reduce frictional resistance and improve wear resistance. The length of the aerodynamic transition section accounts for 50%-60% of the total length of the warhead.

[0015] Preferably, the pitch of the spiral stabilizing groove is 12 mm and the depth is 0.5 mm, which is used to enhance rotational stability and reduce lateral deviation. The diameter of the tail cone exit end face is 4-5 mm, which is used to guide the accelerated airflow out and compensate for drag loss. The length of the wake control section accounts for 22%-35% of the total length of the warhead.

[0016] Preferably, the maximum diameter of the aerodynamic transition section is the maximum outer diameter of the warhead, and the surface expansion rate between the maximum diameter section and the connection end of the shock wave control section is 0.05-0.08 mm / mm, while the surface contraction rate between the maximum diameter section and the connection end of the wake control section is 0.03-0.06 mm / mm.

[0017] Preferably, the top curvature radius of the precision flat head is ≤0.1mm, and the length of the precision flat head accounts for 30%-40% of the total length of the shock wave control section.

[0018] Compared with existing technologies, the advantages of this invention are:

[0019] 1. The shock wave control section reduces wave drag by more than 25%; the variable curvature structure of the aerodynamic transition section increases the airflow adhesion rate to more than 95%, significantly reducing pressure drag; the wake control section effectively suppresses the wake vortex, further reducing pressure drag, forming a continuous airflow control chain of "shock wave control - friction reduction - wake stabilization", reducing the total drag coefficient by 50%.

[0020] 2. The coordinated design of the shock wave control section, aerodynamic transition section and wake control section enables the warhead to maintain a low drag coefficient throughout the entire ballistic range at different sonic speeds, avoiding the problem of sudden drag changes during the transition of traditional warheads.

[0021] 3. The integrated molding structure of the shock wave control section, aerodynamic transition section and wake control section is compatible with existing ammunition manufacturing processes, facilitates mass production, and the manufacturing cost is only 5%-8% higher than that of traditional warheads, making it highly practical and economical. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the multi-segment drag reduction structure for sniper projectiles based on fluid dynamics proposed in this invention.

[0023] In the diagram: 1. Shock wave control section; 101. Precision flat head; 102. Flat head rounded corner; 103. Front wedge surface; 104. Rear wedge surface; 2. Aerodynamic transition section; 201. Heterogeneous alloy bonding surface; 202. Laser microtexture layer; 3. Wake flow control section; 301. Spiral stabilizing groove; 302. Tail cone exit end face. Detailed Implementation

[0024] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0025] Reference Figure 1 The multi-segment drag reduction structure of the sniper projectile based on fluid dynamics includes a shock wave control section 1, an aerodynamic transition section 2, and a wake control section 3. The shock wave control section 1, the aerodynamic transition and friction reduction section 2, and the wake control section 3 are integrally formed structures.

[0026] The shock wave control section 1 includes a precision flat head 101, a flat head with rounded corners 102, a front wedge surface 103, and a rear wedge surface 104 connected in sequence.

[0027] The aerodynamic transition section 2 is a variable curvature ellipsoidal structure. The aerodynamic transition section 2 is made of tungsten alloy and has a laser microtextured layer 202 on its outer surface.

[0028] The wake control section 3 includes a spiral stabilizing groove 301 and a tail cone outlet end face 302.

[0029] The precision flat head 101 has a diameter of 0.8-1.2mm, forming a dual shock wave system to reduce transonic drag fluctuations. The radius of the flat head rounded corner 102 is 0.15mm to avoid excessive airflow stripping that could cause turbulence. The angle of the front wedge surface 103 is 9.7°±0.2°, which is used to guide shock wave deflection and reduce axial shock wave superposition. The angle of the rear wedge surface 104 is 11.3°±0.2°, which is used to connect the mid-section airflow and suppress shock wave intensity.

[0030] Shock control section 1 is made of nickel-chromium alloy with a density of 7.8 g / cm³. 3 The length of shock wave control section 1 accounts for 10-15% of the total length of the warhead.

[0031] The shock wave control section 1 and the aerodynamic transition section 2 are connected by a heterogeneous alloy bonding surface 201, which achieves a tight connection between the nickel-chromium alloy and the tungsten alloy.

[0032] The laser microtextured layer 202 has a thickness of 8μm and is used to form a gas film to reduce the surface friction coefficient. The laser microtextured layer 202 is coated with a polytetrafluoroethylene coating with a thickness of 3-5μm to further reduce frictional resistance and improve wear resistance. The length of the aerodynamic transition section 2 accounts for 50%-60% of the total length of the warhead.

[0033] The spiral stabilizing groove 301 has a pitch of 12 mm and a depth of 0.5 mm, which is used to enhance rotational stability and reduce lateral deviation. The diameter of the tail cone exit end face 302 is 4-5 mm, which is used to guide the accelerated airflow out and compensate for drag loss. The length of the wake control section 3 accounts for 22%-35% of the total length of the warhead.

[0034] The maximum diameter of the aerodynamic transition section 2 is the maximum outer diameter of the warhead. The surface expansion rate between this maximum diameter section and the connection end of the shock wave control section 1 is 0.05-0.08 mm / mm, and the surface contraction rate between this maximum diameter section and the connection end of the wake control section 3 is 0.03-0.06 mm / mm.

[0035] The top curvature radius of the precision flat head 101 is ≤0.1mm, and the length of the precision flat head 101 accounts for 30%-40% of the total length of the shock wave control section 1.

[0036] This invention features a shock wave control section that reduces wave drag by more than 25%; a variable curvature structure in the aerodynamic transition section that increases airflow adhesion to over 95% and significantly reduces pressure drag; and a wake control section that effectively suppresses wake vortices and further reduces pressure drag, forming a continuous airflow control chain of "shock wave control - friction reduction - wake stabilization," resulting in a 50% reduction in the total drag coefficient.

[0037] Meanwhile, the coordinated design of the shock wave control section, aerodynamic transition section and wake control section enables the warhead to maintain a low drag coefficient throughout the entire ballistic range at different speeds of sound, avoiding the problem of sudden drag changes when traditional warheads switch operating conditions.

[0038] Furthermore, the integrated molding structure of the shock wave control section, aerodynamic transition section, and wake control section is compatible with existing ammunition manufacturing processes, facilitating mass production. The manufacturing cost is only 5%-8% higher than that of traditional warheads, making it highly practical and economical.

[0039] The above are merely preferred embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A multi-segment drag reduction structure for sniper projectiles based on hydrodynamics, characterized in that, It includes a shock wave control section (1), an aerodynamic transition section (2), and a wake control section (3), wherein the shock wave control section (1), the aerodynamic transition and friction reduction section (2), and the wake control section (3) are integrally formed structures; The shock wave control section (1) includes a precision flat head (101), a flat head rounded corner (102), a front wedge surface (103), and a rear wedge surface (104) connected in sequence; The aerodynamic transition section (2) is a variable curvature ellipsoidal structure. The aerodynamic transition section (2) is made of tungsten alloy and has a laser microtextured layer (202) on its outer surface. The wake control section (3) includes a spiral stabilizing groove (301) and a tail cone outlet end face (302).

2. The multi-segment drag reduction structure for sniper projectiles based on fluid dynamics according to claim 1, characterized in that, The precision flat head (101) has a diameter of 0.8-1.2 mm, forming a dual shock wave system to reduce transonic drag fluctuations. The radius of the rounded corner (102) of the flat head is 0.15 mm to avoid excessive airflow stripping and turbulence. The angle of the front wedge surface (103) is 9.7°±0.2°, which is used to guide shock wave deflection and reduce axial shock wave superposition. The angle of the rear wedge surface (104) is 11.3°±0.2°, which is used to connect the mid-section airflow and suppress shock wave intensity.

3. The multi-segment drag reduction structure for sniper projectiles based on fluid dynamics according to claim 1, characterized in that, The shock wave control section (1) is made of nickel-chromium alloy with a density of 7.8 g / cm³. 3 The length of the shock wave control section (1) accounts for 10-15% of the total length of the warhead.

4. The multi-segment drag reduction structure for sniper projectiles based on fluid dynamics according to claim 1, characterized in that, The shock wave control section (1) and the aerodynamic transition section (2) are connected by a heterogeneous alloy bonding surface (201) to achieve a tight connection between the nickel-chromium alloy and the tungsten alloy.

5. The multi-segment drag reduction structure for sniper projectiles based on fluid dynamics according to claim 1, characterized in that, The laser microtextured layer (202) has a thickness of 8 μm and is used to form an air film to reduce the surface friction coefficient. The laser microtextured layer (202) is coated with a polytetrafluoroethylene coating with a thickness of 3-5 μm to further reduce frictional resistance and improve wear resistance. The length of the aerodynamic transition section (2) accounts for 50%-60% of the total length of the warhead.

6. The multi-segment drag reduction structure for sniper projectiles based on fluid dynamics according to claim 1, characterized in that, The spiral stabilizing groove (301) has a pitch of 12 mm and a depth of 0.5 mm, which is used to enhance rotational stability and reduce lateral deviation. The diameter of the tail cone exit end face (302) is 4-5 mm, which is used to guide the accelerated airflow out and compensate for drag loss. The length of the wake control section (3) accounts for 22%-35% of the total length of the warhead.

7. The multi-segment drag reduction structure for sniper projectiles based on fluid dynamics according to claim 1, characterized in that, The maximum diameter of the aerodynamic transition section (2) is the maximum outer diameter of the warhead. The surface expansion rate between the maximum diameter and the connection end of the shock wave control section (1) is 0.05-0.08 mm / mm, and the surface contraction rate between the maximum diameter and the connection end of the wake control section (3) is 0.03-0.06 mm / mm.

8. The multi-segment drag reduction structure for sniper projectiles based on fluid dynamics according to claim 2, characterized in that, The top curvature radius of the precision flat head (101) is ≤0.1mm, and the length of the precision flat head (101) accounts for 30%-40% of the total length of the shock wave control section (1).

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