Missile water-entry ice-breaking load-reducing device

Abstract

The application discloses a missile water-entry ice-breaking load-reducing device and belongs to the technical field of missile ice breaking. The device comprises an ice-breaking needle, a missile protective head cover, an ice-breaking needle tray, a buffer spring, a spring base, a connecting pin seat, a pin shaft, a damper, a supporting rod, a bearing plate and damping material. The protected object is the head of the missile. The lower part of the ice-breaking needle is a cylinder, and the upper part is an elongated sharp cone. The damper, the supporting rod and the bearing plate form a load-reducing structure, which gradually consumes the impact force generated when the ice-breaking needle hits the ice layer. The device is installed on the head of the missile, the missile protective head cover completely wraps the head of the missile, when the missile contacts the ice layer, the device is used to break the ice layer, thereby avoiding the influence of the floating ice on the trajectory and the motion posture of the missile, meanwhile, the device can also play a buffering and load-reducing role, protect the head of the missile, reduce the damage of the ice layer to the structure of the missile, and reduce the strength requirement of the material of the head of the missile, so that the missile can smoothly carry out underwater attack tasks in the floating ice area.

Description

Technical Field

[0001] This invention belongs to the field of missile ice-breaking technology and relates to a missile water entry ice-breaking and load-reducing device. Background Technology

[0002] The Arctic and Antarctic regions are rich in natural resources such as oil, minerals, and natural gas. In recent years, with the increasing strategic importance of the polar regions and the intensifying competition among countries in these regions, the development of ice-breaking missiles suitable for polar ice floes has become an urgent task.

[0003] Currently, missile ice-breaking technology faces severe challenges in dealing with the thick ice conditions of polar regions. Due to the extreme cold of the polar regions, most of the sea is covered by ice, making it difficult to strike underwater enemy targets with missiles. First, when a missile receives a launch command to strike an underwater enemy target, it must first penetrate the ice floes. At this point, the missile's nose is highly susceptible to direct collision with the ice floes, generating a huge impact load that severely affects the missile's structure, causing deformation or even complete destruction. Furthermore, the missile generates a massive shock wave upon high-speed entry into the water; interference from the surrounding ice floes further exacerbates the problem. The fluid cannot dissipate freely, thus reflecting into the flow field near the missile, causing fluid oscillations. This leads to drastic changes in the fluid load on the missile surface, altering its entry attitude and ultimately causing it to deviate from its original trajectory, rendering it unable to complete its mission. Furthermore, missiles typically enter water at a small, acute angle. When the missile penetrates the ice, the underside of the missile's nose contacts the ice first, generating a significant asymmetric force at the moment of impact. This affects the missile's entry attitude, causing it to deviate from its original trajectory and potentially even bounce off the ice. Therefore, researching missile icebreaking devices is of great significance for conducting underwater strike missions in areas with floating ice. Summary of the Invention

[0004] To address the aforementioned problems, the main objective of this invention is to provide a missile water entry ice-breaking and load-reducing device, installed on the missile nose. When the missile comes into contact with ice, this device breaks the ice, thereby preventing the floating ice from affecting the missile's trajectory and attitude. At the same time, this device can also buffer and reduce load, protect the missile nose, reduce the damage of the ice to the missile structure, and lower the strength requirements of the missile nose material, thus enabling the missile to successfully carry out underwater strike missions in floating ice areas.

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

[0006] This invention discloses a missile water entry ice-breaking and load-reducing device, comprising an ice-breaking needle, a missile protective hood, an ice-breaking needle tray, a buffer spring, a spring base, a connecting pin seat, a pin shaft, a damper, a support rod, a load-bearing plate, and damping material. The protected object is the missile nose.

[0007] The missile protective hood has an external shape that is a pointed conical shell to meet the aerodynamic requirements of the missile. A through-hole is provided at the top of the hood, the diameter of which is the same as the bottom diameter of the ice-breaking needle. The missile protective hood is fixed to the missile nose. The space between the hood and the nose is used to house the ice-breaking needle, ice-breaking needle tray, buffer spring, spring base, connecting pin, pin shaft, damper, support rod, load-bearing plate, and damping material. Preferably, the missile protective hood is fixed to the missile nose using a clamping sleeve.

[0008] The ice-breaking needle has a cylindrical lower section and a slender, pointed upper section. It is made of high-strength, high-hardness cemented carbide. The ice-breaking needle is positioned on top of the missile's protective visor and mates with a through-hole on the visor. Before breaking the ice, the needle is sealed because its bottom diameter matches the diameter of the through-hole. During ice breaking, the needle moves up and down along the through-hole based on the force difference between the impact on the ice surface and the buffer spring. The bottom of the ice-breaking needle has a tray for connecting to the buffer spring.

[0009] One end of the buffer spring is fixedly installed below the ice-breaking needle tray, and the other end is fixedly installed on the spring base. The buffer spring is used to absorb part of the impact force generated when the missile hits the ice layer, preventing the missile head from being damaged by excessive impact force.

[0010] The damper's two ends are fixedly connected to connecting pin seats via pins. One connecting pin seat is fixedly connected to a spring base, and the other connecting pin seat is fixedly connected to a support rod. The support rod is a slender cylindrical structure with a load-bearing plate at its bottom. The load-bearing plate conforms to the shape of the missile's nose and is directly fixedly installed on the missile's nose. The damper, support rod, and load-bearing plate form a load-reducing structure. The damper in the load-reducing structure absorbs some of the energy when the missile impacts the ice layer, thus buffering the load.

[0011] Furthermore, the missile water entry ice-breaking and load-reducing device is provided with 6 load-reducing structures, and the 6 load-reducing structures are arranged equidistantly along the circumference of the spring base to achieve uniform load distribution and transmission, and avoid overload stress concentration from ice breaking overload to the missile head.

[0012] Furthermore, since the support rods are slender structures and the impact force generated when the missile strikes the ice is significant, direct contact between the support rods and the missile's nose cone could lead to localized stress concentration or even cause the support rods to penetrate the nose cone, damaging the missile. Therefore, this invention incorporates load-bearing plates at the bottom of the six support rods, conforming to the shape of the missile's nose cone. These circumferentially spaced load-bearing plates effectively disperse the impact force generated when the missile strikes the ice, thus reducing the impact on the missile's nose cone. On the other hand, the fixed, evenly distributed support rods transfer the buffered load to the missile's nose cone, ensuring that the force acting on the missile is evenly distributed along the axial load-bearing plates. This significantly reduces the asymmetric forces generated when the missile penetrates the ice. Therefore, this invention has minimal impact on the missile's entry attitude, avoiding the "ice bounce" phenomenon and ensuring the missile flies along a pre-set trajectory.

[0013] The working method of the missile water entry ice breaking and load reduction device disclosed in this invention is as follows:

[0014] Before the missile enters the water and breaks ice to reduce load, the bottom diameter of the ice-breaking needle is the same as the diameter of the through hole of the missile's protective head cover, thus achieving an airtight seal. This prevents airflow from entering the missile's protective head cover and affecting the aerodynamic parameters during the missile's flight. The buffer spring is in a relaxed state and does not transmit load to the damper, ensuring the stability of the missile's trajectory.

[0015] When the missile's water-entry ice-breaking and load-reduction device enters the ice-breaking state, the ice-breaking needle impacts the ice layer, generating a pre-ice-breaking impact force. When impacting a thin ice surface, the pre-ice-breaking impact force breaks the ice layer, and the missile's nose cone enters the water along with the device, avoiding the influence of floating ice on the missile's trajectory and attitude. When impacting a thick ice surface, the pre-ice-breaking impact force generated by the ice-breaking needle impacts the ice layer creates a pre-ice-breaking channel for the missile's protective helmet to follow. The missile's protective helmet then impacts the pre-ice-breaking channel and enters the water. Because the ice-breaking needle pre-drills the pre-ice-breaking channel, the impact on the missile's protective helmet is reduced. The ice-breaking impact load reduces the impact of ice on the missile's trajectory and attitude. In addition, the impact force on the ice-breaking needle compresses the buffer spring, which absorbs part of the impact force generated when the missile hits the ice. While the buffer spring is compressed, the impact force generated when the ice-breaking needle hits the ice is transmitted to the damper through the buffer spring and spring base. The impact force is gradually dissipated through the combined action of the buffer spring, damper, support rod, and load-bearing plate, thereby reducing the vibration and impact generated when the missile hits the ice. The damper, support rod, and load-bearing plate form a load-reducing structure. Because the support rod is a slender structure and the impact force generated when the missile hits the ice layer is very large, if the support rod directly contacts the missile nose, it may cause local stress concentration in the missile nose, or even cause the support rod to penetrate the missile nose directly, damaging the missile body. Therefore, the missile water entry ice breaking and load reduction device uses circumferentially equidistant load reduction structures to disperse the impact force generated when the missile hits the ice layer. The buffered load is applied to the missile nose through fixed and evenly distributed support rods, so that the force on the missile is evenly distributed along the axial load-bearing plates, avoiding the overload stress concentration transmitted to the missile nose from ice breaking, thereby further reducing the impact on the missile nose. Moreover, because the load-bearing plates are evenly distributed, they can reduce the asymmetric force generated when the missile penetrates the ice layer, significantly reducing the impact of asymmetric force on the missile's water entry attitude during ice breaking, avoiding the phenomenon of "ice surface bounce" of the missile, and thus ensuring that the missile flies along the pre-set trajectory. Because the missile warhead utilizes dampers, support rods, and load-bearing plates to achieve coordinated load reduction and stability enhancement, it improves the accuracy of the missile in striking underwater targets in ice-covered areas, reduces the structural strength and material requirements of the missile warhead, and thus reduces the manufacturing cost of the missile warhead.

[0016] Beneficial effects:

[0017] 1. The present invention discloses a missile water entry ice breaking and load reduction device, which sets a high-strength, high-hardness ice-breaking needle on the missile head without changing the streamlined structure of the missile head, and can rely on the huge inertia generated when the missile enters the water at high speed to drive the ice-breaking needle to break the ice layer, avoiding the excessive impact force generated by the missile directly hitting the thick ice layer, thereby changing the missile's water entry attitude and trajectory, and improving the success rate of the missile hitting underwater targets.

[0018] 2. The present invention discloses a missile water entry ice breaking and load reduction device. The missile protective head cover completely covers the missile head, which can avoid damage to the missile head from ice fragments. Moreover, a buffer spring, damper, support rod, load-bearing plate and damping material are provided between the missile protective head cover and the missile head, which can gradually consume the huge impact force generated when the missile hits the ice layer, thereby effectively protecting the missile head and significantly ensuring the structural strength of the missile.

[0019] 3. The present invention discloses a missile water entry ice-breaking and load reduction device. The device uses circumferentially equidistant load reduction structures to disperse the impact force generated when the missile impacts the ice layer. The buffered load is transferred to the missile head through fixed, evenly distributed support rods. This ensures that the force on the missile is evenly distributed along the axial load-bearing plates, preventing the overload stress concentration from being transmitted to the missile head during ice breaking. This further reduces the impact on the missile head. Furthermore, the evenly distributed load-bearing plates reduce the asymmetric force generated when the missile penetrates the ice layer, significantly reducing the impact of the asymmetric force on the missile's water entry attitude during ice breaking and preventing the missile from "ice surface bounce". This ensures that the missile flies along a pre-set trajectory. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the appearance of a missile water entry ice breaking and load reduction device installed on a missile, as disclosed in this invention.

[0021] Figure 2 This is a front view of a missile water entry ice breaking and load reduction device installed on a missile, as disclosed in this invention.

[0022] Figure 3 This is a schematic diagram of the structure of a missile water entry ice breaking and load reduction device disclosed in this invention;

[0023] Figure 4 This is a cross-sectional view of the missile nose of a missile water entry ice breaking and load reduction device disclosed in this invention;

[0024] Figure 5 This is a comparison diagram of the positions of various parts in a missile water entry ice breaking and load reduction device disclosed in this invention before and after the missile impacts the ice layer.

[0025] Figure 6 This invention discloses a missile water entry ice breaking and load reduction device, which discloses the changes of the damper before and after the missile impacts the ice layer and the AA cross-sectional view.

[0026] Figure 7 This is a schematic diagram of a missile about to impact an ice layer, as disclosed in this invention, which is a missile water entry ice breaking and load reduction device.

[0027] Figure 8 This is a schematic diagram of a missile impacting ice, according to a missile water entry ice breaking and load reduction device disclosed in this invention.

[0028] Figure 9 A schematic diagram of a missile penetrating ice and striking a target using a missile water entry and ice breaking and load reduction device disclosed in this invention;

[0029] In the diagram: 1—Ice-breaking needle, 2—Missile protective hood, 3—Ice-breaking needle tray, 4—Buffer spring, 5—Spring base, 6—Connecting pin seat, 7—Pin shaft, 8—Damper, 9—Support rod, 10—Bearing plate, 11—Damping material. Detailed Implementation

[0030] 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.

[0031] Example 1:

[0032] like Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, this embodiment discloses a missile water entry ice breaking and load reduction device, including an ice breaking needle 1, a missile protective head cover 2, an ice breaking needle tray 3, a buffer spring 4, a spring base 5, a connecting pin seat 6, a pin shaft 7, a damper 8, a support rod 9, a load-bearing plate 10, and a damping material 11.

[0033] The missile protective helmet hood 2 is made of steel, such as Figure 1 As shown, the external shape is a pointed conical shell that meets the missile's launch requirements, and the missile protective head cover 2 has a through hole at the top. The diameter of the through hole is the same as the bottom diameter of the ice-breaking needle 1. The missile protective head cover 2 is fixed to the missile head. The space between the missile protective head cover 2 and the missile head is used to house the ice-breaking needle 1, the ice-breaking needle tray 3, the buffer spring 4, the spring base 5, the connecting pin seat 6, the pin shaft 7, the damper 8, the support rod 9, the load-bearing plate 10, and the damping material 11. Preferably, the missile protective head cover 2 is fixed to the missile head using a clamping sleeve.

[0034] like Figure 4 As shown, the ice-breaking needle 1 has a cylindrical lower section and a slender, pointed upper section. The ice-breaking needle 1 is made of a high-strength, high-hardness hard alloy. It is positioned on top of the missile protective hood 2 and mates with a through-hole on the upper part of the hood 2. Before ice breaking, the bottom diameter of the ice-breaking needle 1 is the same as the diameter of the through-hole in the missile protective hood 2, achieving a seal. During ice breaking, the ice-breaking needle 1 moves up and down along the through-hole on the upper part of the missile protective hood 2 based on the force difference between the overload from impacting the ice surface and the buffer spring 4. The bottom of the ice-breaking needle 1 is equipped with an ice-breaking needle tray 3 for connection with the buffer spring 4.

[0035] One end of the buffer spring 4 is fixedly installed below the ice-breaking needle tray 3, and the other end is fixedly installed on the spring base 5. The buffer spring 4 can absorb part of the impact force generated when the missile hits the ice layer, preventing the missile head from being damaged by excessive impact force.

[0036] like Figure 3 and Figure 4 As shown in the enlarged view, the two ends of the damper 8 are fixedly connected to the connecting pin seats 6 via pins 7. One connecting pin seat 6 is fixedly connected to the spring base 5, and the other connecting pin seat 6 is fixedly connected to the support rod 9. The damper 8 can provide resistance to motion and dissipate the energy of motion. The damper 8 used in this invention is a hydraulic damper, such as... Figure 6 The AA section cross-sectional view of the damper 8 shows that the damper 8 uses the movement of the piston rod to drive the piston to squeeze the hydraulic oil. The viscosity and resistance of the hydraulic oil are used to absorb the impact force generated when the missile hits the ice layer, thereby reducing vibration and impact.

[0037] The support rod 9 is a slender cylindrical structure, and a load-bearing plate 10 is provided at the bottom of the support rod 9. The load-bearing plate 10 fits the shape of the missile nose and is directly fixed to the missile nose. The damper 8, the support rod 9, and the load-bearing plate 10 form a load-reducing mechanism. The damper 8 in the load-reducing structure absorbs part of the energy when the missile hits the ice layer, playing a role in buffering and reducing load. In this invention, there are 6 load-reducing structures, and these 6 load-reducing structures are arranged equidistantly along the circumference of the spring base 5 to achieve uniform load distribution and avoid overload stress concentration from ice breaking overload to the missile nose.

[0038] like Figure 5 As shown, a damping material 11 is provided between the missile protective hood 2 and the missile head. The damping material 11 is made of rubber. The setting of the damping material 11 will not affect the movement of the components in this device. The damping material 11 can absorb some energy when the missile hits the ice layer, and play a role in buffering and reducing load.

[0039] The working method of a missile water entry ice-breaking and load-reducing device disclosed in this embodiment is as follows:

[0040] like Figure 7 As shown, before the missile enters the water and breaks the ice, the ice-breaking needle 1 has the same bottom diameter as the through hole diameter of the missile protective head cover 2, thus achieving an airtight seal. This prevents airflow from entering the missile protective head cover 2 and affecting the aerodynamic parameters during missile flight. The buffer spring 4 is in a relaxed state and does not transmit load to the damper 8, ensuring the stability of the missile's trajectory.

[0041] like Figure 8As shown, when the missile's water entry ice-breaking and load-reduction device enters the ice-breaking state, the ice-breaking needle 1 impacts the ice layer, generating a pre-ice-breaking impact force. When impacting a thin ice surface, the pre-ice-breaking impact force breaks the ice layer, and the missile's nose cone enters the water along with the missile's water entry ice-breaking and load-reduction device, avoiding the impact of floating ice on the missile's trajectory and attitude. When impacting a thick ice surface, the pre-ice-breaking impact force generated by the ice-breaking needle 1 impacting the ice layer forms a pre-ice-breaking channel for the missile's protective helmet to follow. The missile's protective helmet then impacts the pre-ice-breaking channel and enters the water. Because the ice-breaking needle 1 pre-drills the pre-ice-breaking channel, the ice-breaking impact load on the missile's protective helmet is reduced. This reduces the impact of ice on the missile's trajectory and attitude. In addition, the impact force on the ice-breaking needle 1 compresses the buffer spring 4, which absorbs part of the impact force generated when the missile hits the ice layer. While the buffer spring 4 is compressed, the impact force generated when the ice-breaking needle 1 hits the ice layer is transmitted to the damper 8 through the buffer spring 4 and the spring base 5. The impact force is gradually consumed through the combined action of the buffer spring 4, the damper 8, the support rod 9, and the load-bearing plate 10, thereby reducing the vibration and impact generated when the missile hits the ice layer. The damper 8, the support rod 9, and the load-bearing plate 10 form a load-reducing structure. Because the support rod 9 is a slender structure and the impact force generated when the missile hits the ice layer is large, if the support rod 9 directly contacts the missile head, it may cause local stress concentration in the missile head, or even cause the support rod 9 to penetrate the missile head directly, damaging the missile body. Therefore, the missile water entry ice breaking and load reduction device uses circumferentially equidistant load reduction structures to disperse the impact force generated when the missile hits the ice layer. The buffered load is applied to the missile head through the fixed and uniformly distributed support rod 9, so that the force on the missile is evenly distributed along the axially distributed load-bearing plate 10, avoiding the overload stress concentration transmitted to the missile head, thereby further reducing the impact on the missile head. Moreover, because the load-bearing plate 10 is evenly distributed, it can reduce the asymmetric force generated when the missile penetrates the ice layer, significantly reducing the influence of the asymmetric force on the missile's water entry attitude during the ice breaking process, avoiding the phenomenon of "ice surface bounce" of the missile, and thus ensuring that the missile flies along the pre-set trajectory. Because the missile warhead utilizes dampers 8, support rods 9, and load-bearing plates 10 to achieve coordinated load reduction and stability enhancement, it improves the missile's accuracy in striking underwater targets in ice-covered areas, reduces the structural strength and material requirements of the missile warhead, and thus lowers the manufacturing cost of the missile warhead. Figure 9 As shown, after the ice-breaking needle 1 of the missile's water entry ice-breaking and load-reducing device completes its ice-breaking task, the missile can accurately strike underwater targets after entering the water.

[0042] like Figure 5As shown, during the missile's ice-breaking process, the ice-breaking needle 1 impacts the ice layer, generating a significant impact force. This compresses the buffer spring 4, which absorbs some of the impact force generated when the missile hits the ice layer. Simultaneously, the impact force generated by the ice-breaking needle 1 impacting the ice layer is transmitted to the damper 8. The damper 8 then uses the viscosity and resistance of the hydraulic oil to dissipate the impact force generated when the missile hits the ice layer, thereby reducing vibration and impact. Figure 6 As shown, the missile impacts the ice layer, causing the damper 8 to be compressed. ΔL in the figure represents the displacement change of the cylinder. Furthermore, this invention incorporates six support rods 9. When the missile impacts the ice layer, these six support rods 9 can evenly distribute the impact force generated by the missile impact across the entire missile nose, preventing excessive localized load on the missile nose and thus avoiding damage.

[0043] Furthermore, since the support rod 9 is a slender structure and the impact force generated when the missile hits the ice layer is very large, if the support rod 9 directly contacts the missile head, it may cause local stress concentration in the missile head, or even cause the support rod 9 to directly penetrate the missile head and damage the missile body. Therefore, the present invention also provides a load-bearing plate 10 at the bottom of the 6 support rods 9 that fits the shape of the missile head, so as to effectively disperse the impact force generated when the missile hits the ice layer, thereby reducing the impact on the missile head.

[0044] Furthermore, by applying the buffered load to the missile head through the fixed and evenly distributed support rods 9, the force on the missile is evenly distributed along the axial distribution of the load-bearing plate 10, thereby greatly reducing the asymmetric force generated by the missile penetrating the ice layer. Therefore, the present invention has minimal impact on the missile's water entry attitude and will not cause the phenomenon of "ice surface bounce", thus ensuring that the missile flies along the pre-set trajectory.

[0045] The present invention achieves the gradual dissipation of impact force through the combined action of buffer spring 4, damper 8, support rod 9 and load-bearing plate 10, thereby reducing the vibration and impact generated when the missile hits the ice layer and effectively protecting the missile's nose structure.

[0046] 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 missile water entry, ice breaking, and load reduction device, characterized in that: It includes an ice-breaking needle (1), a missile protective head cover (2), an ice-breaking needle tray (3), a buffer spring (4), a spring base (5), a connecting pin seat (6), a pin shaft (7), a damper (8), a support rod (9), a load-bearing plate (10), and a damping material (11). The missile protective head cover (2) has a pointed conical shell shape on the outside. The missile protective head cover (2) is fixed to the missile head. The missile protective head cover (2) has a through hole on the top. The ice-breaking needle (1) is set on the top of the missile protective head cover (2), and the ice-breaking needle (1) cooperates with the through hole above the missile protective head cover (2). The ice-breaking needle (1) can extend and retract along the through hole above the missile protective head cover (2). The bottom of the ice-breaking needle (1) is provided with an ice-breaking needle tray (3). One end of the buffer spring (4) is fixed to the bottom of the ice-breaking needle tray (3), and the other end is fixed to the spring base (5); The two ends of the damper (8) are fixedly connected to the connecting pin seat (6) by the pin shaft (7), one of the connecting pin seats (6) is fixedly connected to the spring base (5), and the other connecting pin seat (6) is fixedly connected to the support rod (9). The support rod (9) is a slender cylindrical structure. The bottom of the support rod (9) is provided with a load-bearing plate (10) and is directly installed and fixed to the missile head. The damper (8), support rod (9) and load-bearing plate (10) form a load-reducing mechanism, which is arranged equidistantly along the circumference of the spring base (5). Damping material (11) is provided between the missile protective hood (2) and the missile head. When the missile passes through the ice floe area, the missile's motion generates huge inertia, which drives the ice-breaking needle (1) to directly impact the ice layer and break it into ice fragments.

2. The missile water entry ice-breaking and load-reducing device according to claim 1, characterized in that: The ice-breaking needle (1) has a cylinder at the bottom and a slender cone at the top. The ice-breaking needle (1) is made of hard alloy with high strength and high hardness.

3. The missile water entry ice-breaking and load-reducing device according to claim 1, characterized in that: The load-bearing plate (10) is fitted to the shape of the missile head to disperse the impact force generated when the missile hits the ice layer.

4. A missile water entry ice-breaking and load-reducing device according to claim 1, characterized in that: The diameter of the through hole above the missile protective head cover (2) is the same as the diameter of the bottom of the ice-breaking needle (1).

5. A missile water entry ice-breaking and load-reducing device according to claim 1, characterized in that: The load-reducing mechanism is provided in 6 sets, and the 6 sets of load-reducing mechanisms are arranged at equal intervals along the circumference of the spring base (5).

6. A missile water entry ice-breaking and load-reducing device according to claim 1, characterized in that: The missile protective head cover (2) is fixed to the missile head using a clip.

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