Rotor wing striking type projectile body and construction method

Abstract

The invention relates to the technical field of air defense weapons, in particular to a rotor wing striking type projectile body and a construction method. The problem that a conventional weapon is too low in unmanned aerial vehicle blocking hit rate is mainly solved. The rotor wings are arranged by changing the structure of the projectile body, the blocking area of the projectile body is increased through the striking effect of the rotor wings of the projectile body, and the unmanned aerial vehicle is used for blocking low-altitude and low-speed incoming attacks such as small, light and micro unmanned aerial vehicles and groups thereof and has the advantages of being low in manufacturing cost, convenient to carry, rapid to use and high in hit rate. The projectile body has the same series of standard projectile body specification, does not need to be additionally provided with a launching device, has the advantages of being convenient to carry and rapid to use, can be comprehensively distributed to a basic combat unit and each soldier, complements the advantages of high-precision and advanced air defense weapons, and is beneficial to building a more perfect national defense system.

Description

Technical Field

[0001] The invention relates to the technical field of air defense weapons, in particular to a rotor-swinging missile body and a construction method thereof. Background Art

[0002] Currently, the known weapons and technical measures in the field of air defense mainly use modern military weapons such as interceptor missiles, close-in defense guns, electromagnetic guns, and high-tech weapons such as electronic interference, electromagnetic pulses, and laser interception. For small, light, and micro drones and their fleets, net guns are used to launch capture nets, and guns are used to launch bullets or shotguns. In addition, there are currently no other more effective military weapons.

[0003] Although these military weapons and technical measures have certain effects, they also have various drawbacks. Among them, interceptor missiles cannot intercept small, light, and micro drones and their fleets, and are expensive to manufacture; close-in defense guns consume a huge amount of ammunition and are only suitable for protecting key areas and important targets; electromagnetic guns, electronic interference, electromagnetic pulses, and laser interception are bulky and cannot be carried or are difficult for individual soldiers to carry; net guns and shotguns have short ranges and low hit rates, and require additional guns to be carried, which increases the load on individual soldiers; and the hit rate of other firearms is extremely low. Summary of the invention

[0004] The present invention provides a rotor-swinging missile body and a construction method to solve the problem that conventional weapons cannot effectively intercept UAVs. The missile can be specially used to intercept low-altitude, slow-moving incoming objects such as small, light and micro UAVs and their fleets, and has the characteristics and advantages of low cost, easy to carry, quick to use and high hit rate.

[0005] In order to solve the above technical problems, the technical solution of the present invention is: a rotor-swinging projectile and a construction method, in which a rotor is arranged on the projectile, and the impact area between the projectile and the incoming object is expanded by dozens or hundreds of times by its swinging method, thereby greatly improving the hit rate; the projectile specifications are the same as the standard projectiles in the same series, so that it can be launched with its matching guns and cannons; the projectile with an explosive warhead can be provided with a fuse at the root of the rotor blade, which will cause the projectile to explode when the rotor hits the incoming object; the rotor is divided into a rigid rotor and a flexible rotor, and the flexible rotor is used to entangle and capture small drones.

[0006] The present invention has the following advantages and positive effects:

[0007] (1) As an important supplement to the existing technical measures of air defense weapons, the present invention aims at the advantages of UAVs and their fleets in modern warfare, such as low cost, large number, flexibility, and difficulty in defense. It utilizes their limitations such as relatively slow flight speed, low altitude, small size, and no armor, especially the need to get close to the target when launching an attack, abandons the relatively excess mass of high-precision and cutting-edge interception weapons, transforms the outer structure of the missile body, removes many expensive components inside the missile body, and forms a suitable effect of blocking small UAVs and their fleets. It has the advantage of low cost and complements the advantages of high-tech air defense weapons to form a positive effect of all-round air defense.

[0008] (2) The specifications of the projectile of the present invention are the same as those of the standard projectiles of the same series, and it can be fired by the weapons it matches, without the need for additional guns and artillery. It has the advantages of being easy to carry, quick to use, and having a high hit rate, and can be fully distributed to basic combat units and every soldier.

[0009] (3) The projectile of the present invention has an increased swinging function, which changes the impact of the projectile from a small point to a large area, making it easier to form a protective barrier. This not only reduces the number of projectiles per unit time, but also reduces the cost of protection. Moreover, due to its popularity, it avoids the situation in which tanks, chariots and soldiers are subjected to rampant pursuit and bombing by small, light and micro drones as in the current battlefields of modern warfare, thereby reducing the loss of weapons and equipment and alleviating the casualties and fear of soldiers.

[0010] (4) The present invention simplifies the complex and returns to its original simplicity, which not only makes up for the shortcomings of high-tech air defense weapons, but also is not affected by the opponent's use of weapons such as electromagnetic pulses and laser interception, and gives full play to the advantages of each inch.

[0011] (5) The present invention reduces the war cost of the defender and increases the war cost and difficulty of the attacker, which is conducive to building a more complete national defense system. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 It is the front view of the projectile;

[0013] Figure 2 It is the top view of the projectile;

[0014] Figure 3 This is a top view of the rotor wing diameter and warhead;

[0015] Figure 4 This is a top view of the warhead;

[0016] Figure 5 It is a top view of the bottom section of the rotor single-axis missile body;

[0017] Figure 6 It is a top view of the bottom section of the rotor biaxial missile body;

[0018] Figure 7It is a front view of the section of the rotor single-axis missile body;

[0019] Figure 8 It is a front view of the cross section of the rotor biaxial missile body;

[0020] Fig. 9 It is a front view of the cross section of the rotor dual-axis pull rod type missile body;

[0021] Fig.10 This is a front view of the cross section of the rotor dual-axis flexible cable type missile body;

[0022] Fig.11 This is a schematic diagram of the rotor extension;

[0023] Fig.12 It is a schematic diagram of rotor twist;

[0024] Fig.13 It is a schematic diagram of the pull rod rotor extension;

[0025] Fig.14 This is a schematic diagram of the flexible cable rotor extension;

[0026] Fig.15 This is a schematic diagram of the propulsion of a single-axis rotor projectile for a smoothbore gun:

[0027] Fig.16 Schematic diagram of the propulsion of a single-axis rocket launcher with a rotor

[0028] Fig.17 It is a schematic diagram of the movement of a rotor-type dual-axis missile body;

[0029] Fig.18 This is a schematic diagram of the propulsion of a rotor dual-axis pull-rod type missile body;

[0030] Fig.19 This is a schematic diagram of the propulsion of a rotor dual-axis flexible cable-type projectile;

[0031] Fig. 20 It is a schematic diagram of the rotor dual-axis flexible cable type missile body moving from point to surface; Fig.21 This is a schematic diagram of the increase in the impact area of ​​a rotor dual-axis flexible cable projectile during its movement. DETAILED DESCRIPTION

[0032] The meanings of the reference numerals are as follows:

[0033] Projectile body front view Figure 1 , upper part of the missile body 1-1, rotor 1-2, rotor extension slot 1-3, bottom of the missile body 1-4, rotor extension slot 1-5, outer membrane of the missile body 1-6; top view of the missile body Figure 2 , rotor wing tip 2-1, outer membrane edge line of missile 2-2, warhead fuze 2-3; warhead and rotor wing diameter viewed from above Figure 3, rotor wing diameter 3-1, warhead fuze 3-2, warhead 3-3; warhead top view Figure 4 , warhead 4-1, warhead fuze 4-2; bottom section of the rotor single-axis warhead viewed from above Figure 5 , body bottom 5-1, gap between rotor wing diameter and warhead 5-2, rotor transverse axis 5-3, rotor wing diameter 5-4, warhead 5-5; top view of the bottom section of the rotor dual-axis body Figure 6 , rotor horizontal axis 6-1, rotor wing diameter and warhead gap 6-2, rotor vertical axis 6-3, rotor wing diameter 6-4, warhead 6-5; front view of rotor single-axis warhead section Figure 7 , rotor 7-1, transverse axis 7-2, warhead 7-3, warhead fuze 7-4, projectile bottom 7-5, rotor column 7-6, rotor extension slot 7-7; front view of rotor dual-axis projectile section Figure 8 , wing back 8-1, wing tip 8-2, wing blade 8-3, vertical axis 8-4, horizontal axis 8-5, vertical axis cap 8-6, wing diameter 8-7; front view of the rotor dual-axis pull rod type projectile section Fig. 9 , pull rod cap 9-1, pull rod and vertical axis 9-2, projectile cavity 9-3, horizontal axis 9-4, vertical axis support 9-5, rotor cavity 9-6; front view of the rotor dual-axis flexible cable projectile section Fig.10 , flexible cable winding shaft 10-1, rotor cavity 10-2, vertical shaft with support 10-3, flexible cable 10-4; schematic diagram of rotor extension Fig.11 ; Rotor twist indication Fig.12 ; Pull rod type rotor extension diagram Fig.13 ; Schematic diagram of flexible cable rotor extension Fig.14 ; Schematic diagram of the movement of a single-axis rotor missile Fig.15 : Schematic diagram of the movement of a rotor dual-axis missile Fig.16 ; Schematic diagram of the propulsion of the rotor dual-axis pull rod type projectile Fig.17 ; Schematic diagram of the propulsion of a rotor dual-axis flexible cable-type missile Fig.18 ; Schematic diagram of the rotor dual-axis flexible cable-type missile body moving from point to surface Fig.19 .

[0034] Implementation steps.

[0035] 1. The specifications and models of the projectile body are the same as those of the standard series projectile body.

[0036] The projectile can be directly fired by existing standard weapons without the need for additional launch devices; the projectile has a variety of specifications and models, which are the same as the specifications and models of shells and bullets used by various existing anti-aircraft guns, close-in defense guns, machine guns, rifles, pistols and other weapons. The difference is that in order to increase the swing function, the projectile is divided into different structural parts. Figure 1 As shown, the upper part of the projectile Figure 1 1-1, body rotor see Figure 1 1-2, rotor extension slot see Figure 11-3, see the bottom of the projectile Figure 1 1-4, the rotor extension is visible Figure 1 1-5, outer membrane of the projectile Figure 1 Here, it is assumed that the missile body has eight rotors, and different numbers of rotors can be set as needed.

[0037] 2. Add a swinging function to the projectile.

[0038] Swinging refers to the rotation of the projectile under the action of the rifling when it is fired. After it is ejected from the muzzle or gun, the rotor of the projectile is separated from the barrel or gun barrel and extends around the projectile under the action of centrifugal force, forming a rapidly rotating ejection plane with the projectile as the center. The rotor in circular motion swings and strikes the object it touches. The swinging function refers to the effectiveness of the projectile in increasing the hit rate of the projectile through the swinging action of the rotor. The occurrence of the swinging function is achieved through the interaction of different structures of the projectile.

[0039] 1. The upper part of the rotor surrounds the warhead, and the top view of the warhead is Figure 2 As shown, the rotor wing is slightly visible Figure 2 2-1, the outer membrane boundary line of the projectile is shown Figure 2 2-2, Warhead Fuze Figure 2 2-3; the lower part of the rotor surrounds the warhead, and the warhead and the rotor wing diameter are shown in the top view. Figure 3 As shown, the rotor blade diameter is Figure 3 3-1, Warhead Fuze Figure 3 3-2, warhead Figure 3 The warhead is the core part of the warhead. Figure 4 As shown, the warhead Figure 4 4-1, Warhead Fuze Figure 4 4-2. The bottom of the rotor is connected to the bottom of the missile body through a single shaft or a double shaft. The bottom section of the rotor single shaft missile body is viewed from above. Figure 5 , see the bottom of the projectile Figure 5 5-1. The clearance between rotor wing diameter and warhead is shown in Figure 5 5-2, rotor horizontal axis see Figure 5 5-3, rotor blade diameter Figure 5 5-4, warhead Figure 5 5-5; The top view of the bottom section of the rotor dual-axis missile body is Figure 6 As shown, the rotor horizontal axis is Figure 6 6-1, rotor wing diameter and warhead clearance Figure 6 6-2, rotor vertical axis see Figure 6 6-3, rotor blade diameter Figure 6 6-4, warhead Figure 6 of 6-5.

[0040] 2. Rotor extension can be single-axis extension or dual-axis extension. Figure 7 As shown, the rotor Figure 7 7-1, horizontal axis see Figure 7 7-2, warhead Figure 7 7-3, warhead fuze see Figure 7 7-4, the bottom of the projectile Figure 7 7-5, rotor column see Figure 7 7-6, rotor extension slot see Figure 7 7-7; The front view of the rotor biaxial missile body section is Figure 8 As shown, the back of the wing is Figure 8 8-1, wing tip Figure 8 8-2, Wing Blade Figure 8 8-3, vertical axis see Figure 8 8-4, horizontal axis see Figure 8 8-5, vertical axis cap see Figure 8 8-6, wing diameter see Figure 8 8-7.

[0041] 3. After the rotor is extended, it can be further stretched by a pull rod or a flexible cable to increase the distance from the center of the missile body and expand the impact area with the incoming object. Fig. 9 As shown, the rod cap is shown Fig. 9 9-1, tie rod and vertical axis Fig. 9 9-2, projectile cavity Fig. 9 9-3, horizontal axis see Fig. 9 9-4, vertical axis support Fig. 9 9-5, rotor cavity see Fig. 9 9-6; The front view of the rotor dual-axis flexible cable type missile body section is Fig.10 As shown, the flexible rope winding spool is shown Fig.10 10-1, rotor cavity see Fig.10 10-2, vertical shaft with support Fig.10 10-3, Rousuojian Fig.10 of 10-4.

[0042] 4. After the projectile is ejected, the rotor extends to a position perpendicular to the direction of travel of the projectile under the action of centrifugal force, as shown in the diagram of rotor extension Fig.11 ; The vertical axis rotor is twisted by aerodynamic force, the wing back turns from back to front, and the wing blade turns from front to back, see the rotor twisting diagram Fig.12 ; The pull-rod rotor is pulled away from the center of the missile body under the action of centrifugal force, see the diagram of the pull-rod rotor pulling Fig.13 ; The distance that the flexible cable rotor is pulled away from the center of the missile body can be further, see the flexible cable rotor pulling diagram Fig.14 .

[0043] 5. The single-axis rotor only extends, does not twist or stretch, the wing blade remains forward, and the wing back remains backward. The specific angle of the rotor to the front is determined by the angle of the horizontal axis relative to the center line of the projectile, and is based on the firing rate and rotation speed, meeting the aerodynamic requirements of minimum resistance. See the schematic diagram of the single-axis projectile with a rotor for a smoothbore gun. Fig.15 The propulsion diagram of a single-axis rocket launcher with a rotor Fig.16 .

[0044] 6. After the dual-axis rotor is extended, the blade and the back of the wing are twisted along the vertical axis due to the impact of the air. The angle is automatically adjusted under the combined effect of the firing rate and the rotation speed. See the schematic diagram of the movement of the dual-axis rotor projectile Fig.17 .

[0045] 7. The pull rod type rotor can also be stretched to increase the distance between the rotor and the center of the missile body, see the schematic diagram of the rotor dual-axis pull rod type missile body movement Fig.18 The distance that the soft-cable rotor is stretched is determined by the length of the soft-cable, and is generally stretched farther than the pull-rod rotor. See the schematic diagram of the rotor's dual-axis soft-cable projectile movement. Fig.19 ;

[0046] 8. The flexible cable rotor is mainly used to entangle and capture drones, and requires the rotor to form a larger disk. See the schematic diagram of the rotor dual-axis flexible cable body changing from point to surface when moving. Fig. 20 .

[0047] 3. Other specific implementation methods and their descriptions.

[0048] 1. The projectiles referred to in the present invention, except for the rotary wing single-axis projectiles for rocket launchers which require solid fuel booster, the rest also require cartridge cases, gunpowder, primers and other devices for launching, and thus belong to the nature of warheads.

[0049] 2. The rotor-swinging projectiles used in close-in defense guns and anti-aircraft guns generally have warheads, and can even set multiple explosive fuses through the rotors. The projectile volume is also larger. Smaller-caliber machine guns, rifles and pistols do not and cannot have warheads, so the projectile volume is smaller and the number of rotors is correspondingly reduced.

[0050] 3. For projectiles or warheads of the same specifications, the rotation speed is slowed down due to the extension and stretching of the rotor; since the impact area of ​​the projectile is expanded, the air resistance is increased, the firing rate is slowed down and the range is reduced, making it more suitable for blocking low-altitude, slow-speed UAVs and their fleets.

[0051] 4. The main function of the outer membrane of the projectile is to gather the rotors of the projectile so that they will not be loose. The existence of a margin and a gap at the wingtip allows air to rush into the projectile after it is launched, causing the rotors to extend. The outer membrane is cut or melted in the barrel during launch, and the projectile is shattered and disappears when it leaves the launch port.

[0052] 5. During the actual design and manufacturing process, the weight ratio between the upper part and the bottom of the projectile should be appropriately adjusted so that the projectile will not lower its head and run downward due to excessive weight on the upper part of the projectile.

Claims

1. A rotor-swinging missile body and a construction method, characterized in that: The projectile body is set to be composed of components with different structures, including several rotors; the rotors extend to the periphery of the projectile body after the projectile is launched, forming a rapidly rotating shooting plane with the projectile body as the center; the rotors performing circular motion swing against the objects they touch, thereby expanding the collision area between the projectile body and the shooting target, thereby improving the hit rate.

2. The rotor-swinging missile and the construction method according to claim 1, characterized in that: During design and manufacturing, adjusting the angle between the horizontal axis connecting the rotor and the bottom of the missile body and the line connecting the center of the missile body can determine the angle at which the line connecting the middle of the wing blade and the wing back arc deviates from the forward direction of the missile body after the rotor is extended, so as to reduce the air resistance encountered by the missile after launch.

3. The rotor-swinging missile and the construction method according to claim 1, characterized in that: In response to the need to reduce the air resistance encountered by the projectile during flight, the rotor automatically adjusts its rotation around the vertical axis so that the middle line connecting the wing blade and the wing back arc has an optimal deviation angle from the forward direction of the projectile.

4. The rotor-swinging missile and the construction method according to claim 1, characterized in that: The vertical axis is lengthened to become a pull rod, so that the inner cavity of the rotor can adapt to it, and the rotor is stretched again after being extended to increase its distance from the center of the missile body.

5. The rotor-swinging missile and the construction method according to claim 1, characterized in that: A flexible cable winding spool is arranged in the inner cavity of the rotor, and the other end of the flexible cable is connected to the vertical shaft with a support. After the rotor is extended, the flexible cable is stretched again to increase the distance between the rotor and the center of the missile body.

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