An overhang missile ice breaking device

Abstract

The application discloses a kind of stretch-out missile ice-breaking device, including missile main body, missile head cover, ice-breaking cone, cone buffer pad, gear, motor, motor support, rubber pad and foam.Missile head cover is installed in the outside of missile head, and the external shape is semicircular pointed arch body satisfying the aerodynamic requirements of missile, and the head of missile head cover is provided with opening for placing ice-breaking cone.The shape of the head of ice-breaking cone is the pointed cone formed by the rotation of two tangent circular arcs, and the pointed cone of the head of ice-breaking cone is long rack, and one side is provided with tooth.The ice-breaking cone penetrates the missile head cover and goes deep into the missile head.The cone buffer pad is placed in the pointed cone inside the head of ice-breaking cone.The gear teeth are engaged with the teeth of ice-breaking cone rack.The application actively stretches out ice-breaking cone to break ice layer before missile contacts with ice layer, and protects missile and its internal structure from impact through missile head cover, reduces the strength requirement of missile material under the premise of improving the hitting accuracy of missile, and reduces the manufacturing cost of missile.

Description

Technical Field

[0001] This invention belongs to the field of missile ice-breaking technology, specifically relating to a retractable missile ice-breaking device. Background Technology

[0002] Missile weapons are the crystallization and embodiment of modern high technology. With their great power, long range, high accuracy, and strong penetration capability, they have become weapons with super offensive and powerful deterrent capabilities, a pillar for maintaining strategic balance, and an essential weapon for achieving precision warfare.

[0003] Today, missiles have an increasingly wide strike range, capable of strategic strikes across sea, land, and air domains. However, when striking underwater targets in cold or even extremely cold conditions, missiles need to penetrate thick layers of ice, necessitating the consideration of ice-breaking methods. Currently, the common method is to use the missile itself to break the ice. However, due to the thickness of the ice, the reaction force generated by the missile impact affects its trajectory, reducing accuracy and impacting the mission. Furthermore, the impact can cause significant damage to the missile and its internal structure, deforming the missile casing and requiring high-strength materials, thus increasing manufacturing costs. Therefore, many challenges remain in missile ice-breaking methods. Summary of the Invention

[0004] The purpose of this invention is to provide an extendable missile ice-breaking device, which adds a missile hood to the outside of the missile head and installs an ice-breaking cone on the missile head. The ice-breaking cone actively extends and breaks the ice before the missile comes into contact with the ice layer. The missile hood protects the missile and its internal structure from impact. This reduces the strength requirements of the missile materials and lowers the manufacturing cost of the missile while improving the missile's strike accuracy.

[0005] The objective of this invention is achieved through the following technical solution:

[0006] The present invention discloses a retractable missile ice-breaking device, comprising a missile body, a missile nose cone, an ice-breaking cone, a cone buffer pad, gears, a motor, a motor bracket, a rubber pad, and foam.

[0007] The missile radome is mounted on the outside of the missile's nose cone. Its external shape is a semi-circular pointed arch to meet the missile's aerodynamic requirements. The radome has an opening at its head for placing an ice-breaking cone. The radome is bonded to the missile body to ensure its airtightness. The radome primarily protects the missile nose cone from damage caused by impacts or ice fragments. The space between the radome and the nose cone is used to house the ice-breaking cone, cone-shaped buffer pad, gears, motor, motor support, rubber pads, and foam.

[0008] The ice-breaking cone head is shaped like a pointed cone formed by rotating two tangent circular arcs. Below the pointed cone is a long rack with teeth on one side. The ice-breaking cone penetrates the missile's nose cone and extends deep into the missile's nose. A cone-shaped buffer pad is placed inside the pointed cone of the ice-breaking cone head to absorb the impact force experienced by the pointed cone when breaking through ice. The gear is a standard spur gear, and its teeth mesh with the teeth of the ice-breaking cone rack.

[0009] The motor is positioned between the missile's nose cone and the missile's warhead, on the ice-breaking cone side, and is connected to the gear. It has a self-locking function to control the gear's rotation. The motor bracket is placed below the motor to support it. When the missile nose cone is impacted, the force on the motor can be transferred to the rubber pad through the motor bracket, achieving the effect of shock absorption and load reduction.

[0010] The rubber pad is placed above the missile's nose cone and fits snugly against it. It is made of elastic rubber. The rubber pad absorbs and reduces vibrations, decreasing the force on the missile's nose cone and protecting it from damage.

[0011] The foam is filled between the ice-breaking cone head and the missile hood head, and between the inside of the missile hood and the missile head, and adheres to the missile hood. It plays a role in maintaining the shape of the missile head and the missile hood, and can also play a role in shock absorption and load reduction during the missile ice-breaking process, thus better protecting the missile and its internal structure from damage.

[0012] The working method of the extendable missile ice-breaking device disclosed in this invention is as follows:

[0013] When the missile body of the extended missile ice-breaking device disclosed in this invention approaches the ice layer, the motor starts to run, driving the gear to rotate. Through the meshing of the gear teeth and the ice-breaking cone rack, the rotational motion of the gear is converted into the linear motion of the ice-breaking cone, pushing the ice-breaking cone to break the foam and extend out of the missile's nose cone. After the ice-breaking cone extends to its limit position, the motor stops running. At this time, the extended missile ice-breaking device disclosed in this invention completes the preparation before ice breaking.

[0014] This invention discloses an extendable missile ice-breaking device. When the ice-breaking cone contacts the ice layer, the missile begins the ice-breaking process. Because the motor has a self-locking function, the ice-breaking cone will not retract during the ice-breaking process. Furthermore, the missile's high thrust allows this extendable missile ice-breaking device to achieve better ice-breaking results. During the ice-breaking process, the pointed cone shape formed by the rotation of two tangent arcs of the ice-breaking cone causes the ice fragments generated during breaking to disperse outwards, preventing damage to the missile's nose cone. Additionally, the presence of the cone buffer pad, motor support, rubber pad, and foam helps to reduce shock and load when the ice-breaking cone and missile nose cone collide with the ice layer, protecting the missile body and its internal structure. After the ice-breaking cone breaks through the ice layer, the missile enters the target water area and completes its mission of striking the target.

[0015] Beneficial effects:

[0016] 1. The present invention discloses a protruding missile ice-breaking device, which installs a missile head cover on the outside of the missile head to prevent the missile head from directly contacting the ice layer and to block ice fragments outside the missile head, thereby preventing ice fragments from damaging the missile head and its internal structure.

[0017] 2. The present invention discloses an extendable missile ice-breaking device, which has an ice-breaking cone on the missile head to break the ice layer instead of using the missile itself to break the ice. This reduces the force on the missile body, has less impact on the missile's trajectory, protects the missile from damage, and reduces the requirements for missile materials, thus significantly reducing the missile's manufacturing cost.

[0018] 3. This invention discloses a protruding missile ice-breaking device. The ice-breaking cone head is shaped like a pointed cone formed by rotating two tangent circular arcs. This pointed cone shape allows ice fragments to disperse along the circular arcs, preventing the ice fragments from affecting the missile. Below the pointed cone of the ice-breaking cone head is a long rack with teeth on one side. The ice-breaking cone penetrates the missile's nose cone and extends deep into the missile's nose. A cone-shaped buffer pad is placed inside the pointed cone of the ice-breaking cone head to absorb the impact force experienced by the pointed cone during ice breaking, protecting the pointed cone and achieving a better ice-breaking effect. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of an extendable missile ice-breaking device disclosed in this invention;

[0020] Figure 2 This is a schematic diagram of the missile body in a protruding missile ice-breaking device disclosed in this invention;

[0021] Figure 3 This is an AA cross-sectional view of the missile nose in a protruding missile ice-breaking device disclosed in this invention;

[0022] Figure 4This is a comparison image of the ice-breaking cone before and after extension in an extendable missile ice-breaking device disclosed in this invention, wherein: Figure 4 (a) is a schematic diagram showing the icebreaker cone extending from the missile's nose cone. Figure 4 (b) is a schematic diagram showing the icebreaker extending from the missile's nose cone before and after;

[0023] Figure 5 This is a schematic diagram of a missile approaching an ice layer in a missile-type ice-breaking device disclosed in this invention.

[0024] Figure 6 This is a schematic diagram of a missile breaking through ice and entering water using a protruding missile ice-breaking device disclosed in this invention.

[0025] Figure 7 This is a schematic diagram of the shape of the ice-breaking cone head of a protruding missile ice-breaking device disclosed in this invention;

[0026] Figure 8 This is a schematic diagram of a missile striking a target after entering water, according to a missile-type ice-breaking device disclosed in this invention.

[0027] In the diagram: 1—missile body, 2—missile hood, 3—icebreaker cone, 4—cone buffer pad, 5—gear, 6—motor, 7—motor bracket, 8—rubber pad, 9—foam. Detailed Implementation

[0028] To better illustrate the purpose and advantages of the present invention, the invention will be further described below in conjunction with the accompanying drawings and examples.

[0029] Example 1:

[0030] like Figure 1 , Figure 3 As shown, this embodiment discloses a retractable missile ice-breaking device, including a missile body 1, a missile nose cone 2, an ice-breaking cone 3, a cone buffer pad 4, a gear 5, a motor 6, a motor bracket 7, a rubber pad 8, and a foam 9.

[0031] The missile nose cone 2 is installed on the outside of the missile nose. Its external shape is a semi-circular pointed arch to meet the missile's aerodynamic requirements. It is made of steel, and the nose cone has an opening at its head for placing an ice-breaking cone 3. The nose cone 2 is bonded to the missile body 1 to ensure its airtightness. The nose cone 2 primarily protects the missile nose from damage caused by impact or ice fragments. The space between the nose cone 2 and the missile nose is used to house the ice-breaking cone 3, cone-shaped buffer pad 4, gear 5, motor 6, motor bracket 7, rubber pad 8, and foam 9.

[0032] The ice-breaking cone 3 has a pointed cone shape formed by rotating two tangent circular arcs. This cone shape allows ice fragments to disperse along the arcs, preventing them from affecting the missile. Below the pointed cone of the ice-breaking cone 3 is a long rack with teeth on one side. The ice-breaking cone 3 penetrates the missile's nose cone 2 and extends deep into the missile's nose. The cone-shaped buffer pad 4 is placed inside the pointed cone of the ice-breaking cone 3 to absorb the impact force on the pointed cone during ice breaking, protecting it and achieving better ice-breaking performance. The gear 5 is a standard spur gear, and its teeth mesh with the teeth of the lower rack of the ice-breaking cone 3.

[0033] The motor 6 is positioned between the missile nose cone 2 and the missile head, on one side of the ice-breaking cone 3, and is connected to the gear 5 to control the rotation of the gear 5. The motor 6 has a self-locking function to ensure that the ice-breaking cone 3 cannot retract after it extends.

[0034] The motor bracket 7 is placed below the motor 6 to support the motor 6. When the ice-breaking cone 3 breaks the ice and the missile hood 2 impacts the ice layer, the force on the motor 6 can be transmitted to the rubber pad 8 through the motor bracket 7, achieving the effect of shock absorption and load reduction.

[0035] The rubber pad 8 is placed above the missile's nose cone and fits snugly against it. It is made of elastic rubber. The rubber pad 8 effectively absorbs and reduces shock, minimizing the force on the missile's nose cone and protecting it from damage.

[0036] The foam 9 fills the space between the head of the ice-breaking cone 3 and the head of the missile hood 2, as well as between the inside of the missile hood 2 and the missile head, and adheres to the missile hood 2. It plays a role in maintaining the shape of the missile head and the missile hood 2, making the overall curve of the missile smoother and the shape more beautiful. Moreover, during the ice-breaking process, when the ice-breaking cone 3 extends, it causes the foam 9 to break, which can better absorb the vibration and force generated when impacting the ice layer, reduce the force on the missile head, and protect the missile and its internal structure from damage.

[0037] In addition, such as Figure 7 The schematic diagram of the icebreaker cone 3's head shape shows that the lower end of the tip of the icebreaker cone 3 is a convex arc with radius R1, and the upper end is a concave arc with radius R2, with the two arcs tangent to each other. The center of arc R1 is located at the center of the bottom of the tip of the icebreaker cone 3's head. A dashed line connects the tangent point of the two arcs to the center of R1, and the line intersects the vertical tangent of arc R1 at a single point. This intersection point is the center of arc R2, and the center of R2 is on the same horizontal line as the tip of the icebreaker cone 3's head. The shape of the tip of the icebreaker cone 3's head allows the ice fragments generated when the icebreaker cone 3 breaks the ice to disperse outwards along the arc, protecting the missile from interference by the ice fragments. The distance H between the center of arc R2 and the bottom of the tip of the icebreaker cone 3's head satisfies the following formula:

[0038]

[0039] In this embodiment, it is specified that: Figure 4 As shown in (a), the initial position of the ice-breaking cone 3 is when it is completely placed inside the missile nose cone 2; as Figure 4 As shown in (b), the extreme position of the ice-breaking cone 3 is when the lowest point of the ice-breaking cone 3 is about to leave the missile head but has not yet left the missile head.

[0040] The working method of the extendable missile ice-breaking device disclosed in this invention is as follows:

[0041] like Figure 5 As shown, when the missile body 1 of the extended missile ice-breaking device disclosed in this invention approaches the ice layer, the motor 6 starts to operate, driving the gear 5 to rotate. Through the meshing of the gear teeth of the gear 5 and the rack of the ice-breaking cone 3, the rotational motion of the gear 5 is converted into the linear motion of the ice-breaking cone 3, pushing the ice-breaking cone 3 to break the foam 9 and extend out of the missile nose cone 2. After the ice-breaking cone 3 extends to its limit position, the motor 6 stops operating. At this time, the extended missile ice-breaking device disclosed in this invention completes the preparation before ice breaking.

[0042] like Figure 6 As shown, the ice-breaking process begins when the ice-breaking cone 3 of the extended missile ice-breaking device disclosed in this invention contacts the ice layer. Because the motor 6 has a self-locking function, the ice-breaking cone 3 will not retract into the missile nose cone 2 during the ice-breaking process. Furthermore, the missile's thrust is significant, thus this extended missile ice-breaking device achieves a better ice-breaking effect. During the ice-breaking process, the arc shape of the pointed tip of the ice-breaking cone 3 allows the ice fragments generated during ice breaking to disperse outwards, preventing damage to the missile nose cone. Additionally, the presence of the cone buffer pad 4, motor bracket 7, rubber pad 8, and foam 9 provides shock absorption and load reduction when the ice-breaking cone 3 and missile nose cone 2 collide with the ice layer, protecting the missile body 1 and its internal structure. After the ice-breaking cone 3 breaks the ice layer, as... Figure 8 As shown, the missile enters the target waters and completes its mission to strike the target.

[0043] This embodiment discloses a protruding missile ice-breaking device, which has a missile head cover 2 installed on the outside of the missile head. This can prevent the missile head from directly contacting the ice layer and causing impact damage. It can also completely block the ice fragments generated during ice breaking outside the missile head, preventing the ice fragments from splashing onto the missile head and causing it to be impacted or scratched, thus protecting the missile head and its internal structure from damage.

[0044] Furthermore, in the extended missile ice-breaking device disclosed in this embodiment, an ice-breaking cone 3 is provided on the missile's nose. Compared to the method of the missile breaking the ice itself, the method of using the ice-breaking cone 3 to break the ice layer has less impact on the missile's trajectory, improves the missile's strike accuracy, and enables it to better complete its strike mission. Moreover, using the ice-breaking cone 3 to break the ice reduces the strength requirements of the missile materials, significantly reducing the missile's manufacturing cost and demonstrating good economic efficiency.

[0045] The above detailed description further illustrates the purpose, technical solution, and beneficial effects of the invention. It should be understood that the above description is only a specific embodiment of the present invention and is not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A retractable missile ice-breaking device, characterized in that: It includes the missile body (1), missile hood (2), ice-breaking cone (3), cone buffer pad (4), gear (5), motor (6), motor bracket (7), rubber pad (8) and foam (9); The missile hood (2) is installed on the outside of the missile head. Its external shape is a semi-circular pointed arch. Its head has an opening for placing an ice-breaking cone (3). The missile hood (2) is glued to the missile body (1) to ensure its airtightness. The icebreaker cone (3) has a pointed cone shape formed by rotating two tangent circular arcs. Below the pointed cone is a long rack with teeth on one side, which penetrates the missile head cover (2) and extends into the missile head. The cone buffer pad (4) is placed inside the pointed cone of the icebreaker cone (3). The gear (5) is a common spur gear, and its teeth mesh with the teeth of the lower rack of the icebreaker cone (3). The motor (6) is placed between the missile hood (2) and the missile head, on one side of the ice-breaking cone (3), and connected to the gear (5); The motor bracket (7) is placed below the motor (6). When the ice-breaking cone (3) breaks the ice and the missile head cover (2) hits the ice layer, the force on the motor (6) can be transmitted to the rubber pad (8) through the motor bracket (7), thereby achieving the effect of vibration reduction and load reduction. The rubber pad (8) is placed above the missile head and fits against the missile head. Its material is elastic rubber. The foam (9) is filled between the head of the icebreaker cone (3) and the head of the missile hood (2), between the inside of the missile hood (2) and the missile head, and is bonded to the missile hood (2) to maintain its shape and absorb vibration.

2. The extendable missile ice-breaking device according to claim 1, characterized in that: The lower end of the icebreaker cone (3) is a convex arc with radius R1, and the upper end is a concave arc with radius R2. The two arcs are tangent to each other. The center of arc R1 is at the center of the bottom of the cone. Connecting the tangent point of the two arcs and the center of R1 intersects the vertical tangent line of R1 at a point. This point is the center of arc R2. The center of R2 and the tip of the cone are on the same horizontal line. The distance H between the center of R2 and the bottom of the cone satisfies the following formula: .

3. The extendable missile ice-breaking device according to claim 1, characterized in that: When the missile approaches the ice layer, the motor (6) starts to run, driving the gear (5) to rotate, which in turn drives the ice-breaking cone (3) to move outward in a straight line from the initial position, breaking the foam and extending out of the missile's nose cone (2). When the ice-breaking cone (3) extends outward to its limit position, it stops and begins to break the ice after hitting the ice layer. After the ice-breaking cone (3) breaks the ice layer, the missile enters the target water area.

Images