An icebreaking projectile based on high-thickness sea ice drone launch and a method of using the same

Abstract

The application provides an ice-breaking bomb based on unmanned aerial vehicle launching of high-thickness sea ice and a use method thereof, and relates to the technical field of special blasting engineering for emergency rescue and disaster relief. The bomb comprises a bullet head, a primary warhead, a bomb body shell, a secondary warhead and a bullet tail. The primary warhead comprises a primary warhead main charge, an EFP shaped charge liner, an EFP shaped charge liner fixing gasket, an expanding tube and a detonator. The secondary warhead comprises a circumferential linear EFP shaped charge liner, a secondary warhead main charge, a linear center booster column and a circumferential linear EFP shaped charge liner fixing block. The high-speed and high-temperature metal jet generated by the application is used to cut the ice layer, complete the hole opening and ice breaking, and the ice-breaking bomb is not affected by the terrain and has good mobility. The generated shock wave overpressure and bubble pulsation have little influence on the sea bottom organisms, and the danger is small. The application realizes precise blasting and rapid emergency risk removal, and solves the problem of sea ice disaster.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of emergency rescue and disaster relief special blasting engineering, in particular to an ice-breaking bomb based on unmanned aerial vehicle (UAV) launching for high-thickness sea ice and a use method thereof. BACKGROUND

[0002] Sea ice layer blasting belongs to ice cover blasting, and the existing ice-breaking methods mainly include three kinds: airplane bomb launching method, artillery bombardment method and artificial fixed-point blasting method.However, these three methods have their own limitations, and there are some problems in the application to near-shore port ice layer blasting, which has high risk. For the sea ice in the emergency period, artificial drilling and throwing explosives are mainly used for blasting ice breaking. The compressive strength of sea ice mainly depends on the salinity, temperature and ice age of sea ice. In general, the firmness of sea ice is about 75% of that of fresh water ice. When artificial drilling is performed, the mobility on the sea ice layer is poor, and dangerous accidents are prone to occur. Moreover, this method produces too much concentrated energy, which has certain harmfulness to the marine organisms. SUMMARY

[0003] In view of the above problems, the present application provides an ice-breaking bomb based on unmanned aerial vehicle (UAV) launching for high-thickness sea ice and a use method thereof. The high-speed and high-temperature metal jet generated by the ice-breaking bomb is used to cut the ice layer to complete the hole opening and ice breaking. The ice-breaking bomb has good mobility regardless of the terrain, and the shock wave overpressure and bubble pulsation generated by the ice-breaking bomb have little influence on the marine organisms, which has small risk. The ice-breaking bomb realizes precise blasting and rapid emergency risk removal, and solves the problem of sea ice disaster.

[0004] In order to solve the above problems, the application provides an icebreaking bomb based on unmanned aerial vehicle launching of high-thickness sea ice and a use method thereof, which comprises a bullet head, a first warhead, a bullet shell, a second warhead and a bullet tail, the upper end of the bullet shell is provided with the bullet head, the first warhead is arranged between the bullet shell and the bullet head, the first warhead comprises a first warhead main charge, an EFP shaped charge, an EFP shaped charge fixing gasket, an expanding tube and a detonator, the upper end of the first warhead main charge is provided with the EFP shaped charge, the two ends of the EFP shaped charge are fixed through the EFP shaped charge fixing gasket, the lower end of the first warhead main charge is provided with the expanding tube, the lower end of the expanding tube is provided with the detonator, the lower end of the bullet shell is provided with the bullet tail, the second warhead is arranged in the bullet shell, the second warhead comprises a circumferential linear EFP shaped charge, a second warhead main charge, a linear center booster column and a circumferential linear EFP shaped charge fixing block, the second warhead main charge is located at the center of the bullet shell, the center of the second warhead main charge is provided with the linear center booster column, the outer side of the second warhead main charge is fixed through the circumferential linear EFP shaped charge, and the circumferential linear EFP shaped charge is fixed with the bullet shell through the circumferential linear EFP shaped charge fixing block.

[0005] Preferably, the bullet head is internally provided with a height sensor, the height sensor is located at the top end of the bullet head, and the height sensor is connected with the first warhead through an internal cable.

[0006] Preferably, the bullet head is internally provided with a height sensor, the height sensor is located at the top end of the bullet head, and the height sensor is connected with the first warhead through an internal cable.

[0007] Preferably, the bullet head is internally provided with a height sensor, the height sensor is located at the top end of the bullet head, and the height sensor is connected with the first warhead through an internal cable.

[0008] Preferably, the bullet shell is internally provided with a groove, the groove is located at the opposite position of the circumferential linear EFP shaped charge, and the groove is formed every 15° in the bullet shell, so that the shell is broken at the moment of explosion, and the linear circumferential metal jet is prevented from being affected.

[0009] Preferably, the bullet tail is provided with a tail wing, and the tail wing is located at the end of the bullet tail.

[0010] A use method of an icebreaking bomb based on unmanned aerial vehicle launching of high-thickness sea ice, which comprises the following steps:

[0011] S10, the unmanned aerial vehicle flies to the specified explosion point and hovers at the specified height;

[0012] S20, the projectile separates from the unmanned aerial vehicle and falls freely, when the bullet head penetrates the sea ice layer, the height sensor triggers the primary warhead, the primary warhead main charge collapses the liner, forms an explosive formed projectile, and penetrates the sea ice layer to form an opening;

[0013] S30, the secondary warhead continues to follow due to inertia and enters the opening of the primary warhead, at this time the delay sensor triggers the secondary warhead, the secondary warhead main charge collapses the four linear spherical shell cover, forms four LEFPs to cut the circumferential ice layer, and breaks the surrounding ice layer to achieve the effect of ice breaking;

[0014] S40, according to the ice breaking effect, the next bomb dropping is predicted.

[0015] Preferably, the off-aircraft projectile switch is opened at the moment of leaving the unmanned aerial vehicle, and the delay sensor and the height sensor are powered, the two sensors start to work normally, when the height sensor reaches the set explosion height, the primary warhead is triggered, and a feedback signal is given to the delay sensor, the primary warhead is triggered for a set time, the delay sensor triggers the secondary warhead, in order to prevent special cases of the primary warhead, the delay sensor triggers the primary warhead again when triggering the secondary warhead.

[0016] Preferably, when the projectile reaches the predetermined explosion point for a certain time without detonation, the artificial control detonation switch directly detonates the two warheads, and the artificial control detonation switch directly controls the two warhead detonators to directly detonate the two warheads.

[0017] Compared with the prior art, the present application has the following advantages:

[0018] 1. The present application is simple to launch and drop, does not need to be launched by a cannon or a large aircraft, and only needs to be carried by an unmanned aerial vehicle to reach the specified explosion point and drop at the appropriate height.

[0019] 2. After the projectile separates from the unmanned aerial vehicle, it falls by gravity, when the bullet head penetrates the sea ice layer, the height sensor triggers the primary warhead, the primary warhead main charge collapses the liner, forms an explosive formed projectile, penetrates the sea ice layer to form an opening, realizes automatic opening, does not need human intervention, saves manpower and material resources, and ensures safety.

[0020] 3, the secondary combat continues to follow the opening of the first stage of combat department, the delay sensor triggers the secondary combat, the secondary combat department main charge collapsed four linear ball cover, forming four LEFP cutting around the ice layer, the surrounding ice layer is broken, to achieve the effect of ice breaking, the body will not enter the seabed, relying on the metal jet cutting on the ice layer, the damage to the organism is small, according to the ice breaking effect, the next bomb is predicted, the ice breaking rate can reach 80%-90%. BRIEF DESCRIPTION OF DRAWINGS

[0021] Fig. 1 is the overall structure of the embodiment of the present application schematic diagram;

[0022] Fig. 2 is the secondary combat department structure schematic diagram of the embodiment of the present application;

[0023] Fig. 3 is the first stage of combat department structure schematic diagram of the embodiment of the present application;

[0024] Fig. 4 is the control system work flow schematic diagram of the embodiment of the present application. DETAILED DESCRIPTION

[0025] In order to make the purpose, technical scheme and advantages of the present application more clear, the present application is further described in detail below with the help of examples and drawings, but the examples are not limited to the present application.

[0026] As shown in Figs. 1 to 4 the embodiment of the present application includes warhead 1, first stage of combat department 2, head fixed gasket 3, shell 4, secondary combat department 5, control system cabin 6, tail 7, tail wing 8, tail fixed gasket 9, height sensor 10, internal cable 11, explosion-proof body 12.

[0027] In this embodiment, the first stage of combat department includes the first stage of combat department main charge 2.1, EFP shaped charge 2.2, EFP shaped charge fixed gasket 2.3, booster tube 2.4, detonator 2.5, internal cable 11. The first stage of combat department 2 adopts shaped charge, adopts high explosive, such as B explosive, RDX / TNT 50 / 50, RDX / TNT 20 / 80, etc., the charge amount is 1.5kg-2.5kg; EFP shaped charge 2.2, adopts large cone angle cover, the cone angle is 160°-165°, adopts equal wall thickness red copper, cast iron as shaped charge material, the wall thickness is 6mm-8mm, the inner diameter is 42mm-44mm, the outer diameter is 50mm; Booster tube 2.4 charge is mainly passivated RDX, the charge is 8g-12g; Detonator 2.5, adopts No.8 detonator, reaches a certain height, the height sensor controls the excitation of the detonator, and the explosion sequence (booster tube) is detonated, and finally the main center is initiated.

[0028] In this embodiment, the secondary warhead 5 includes four circumferential linear EFP liners 5.4, a secondary warhead main charge 5.1, a linear central booster column 5.3, and four circumferential linear EFP liner fixing blocks 5.2. The secondary warhead 5 uses high-explosive charges such as B explosive, RDX / TNT 50 / 50, RDX / TNT 20 / 80, and the like, and the charge amount is 4.5 kg-5.5 kg. The four circumferential linear EFP liners 5.4 mainly use linear spherical segment liners, the wall thickness is 5 mm-6.2 mm, the length is 250 mm-450 mm, the spherical segment liner outer diameter is 68 mm-70 mm, the inner diameter is 63 mm-65 mm, and the linear spherical segment liner material is red copper, copper, or cast iron. The linear central booster column 5.3 uses RDX as the main charge, the mass is 24 g-36 g, the length is consistent with the length of the main charge, and is also ignited by No. 8 detonator, and the initiation is controlled by a delay sensor. The four circumferential linear EFP liner fixing blocks 5.2 respectively have suitable grooves reserved in the center, and the four liners are fixed by welding. The four fixing blocks are fixed to the shell 4 by welding, and the fixing blocks can be made of light alloy. There is a certain space gap between the secondary warhead 5 and the shell, which provides a favorable burst height for the linear metal jet to form and invade the circumferential ice layer.

[0029] In this embodiment, the bullet head 1 has a flat head with a radius of 5 mm, which is used to prevent the bullet from bouncing when it contacts the ice layer and affects the opening of the ice layer by the primary warhead 2. The bullet head 1 adopts a circular arc generatrix, the curvature center of which is on the vertical line of the contact point between the bullet head 1 and the shell, the connection contact angle is 0°, and the curvature radius is 425 mm-445 mm. The bullet head 1 is made of 58SiMn steel or D60 carbon steel, and the wall thickness of the bullet head 1 is 5 mm. The bullet head 1 and the shell 4 are connected by threads, and can be sheared when a certain strength is reached.

[0030] In this embodiment, the shell 4 has a length of 350 mm-450 mm, and a radius of 50 mm-52 mm. The shell 4 has a thickness of 5 mm and is made of 58SiMn or D60 steel. A 1 mm thick groove is reserved inside the shell 4, which is located opposite the four liners and is engraved every 15° in the circumferential direction, so as to facilitate the shell to break at the moment of explosion and prevent interference with the linear circumferential metal jet formed.

[0031] In this embodiment, the material of the tail part 7 is selected as 58SiMn or D60 steel, and the length is 100 mm; the tail part ensures the stern angle of 6°-9°, and the shell thickness of the tail part 7 is 5 mm; further, the tail part 7 mainly stores the control system cabin 6, and the control system cabin 6 mainly includes a missile opening switch, a missile leaving switch, a delay sensor, a manual detonation switch, and a battery; the missile opening switch is in a closed state before being assembled with the unmanned aerial vehicle, and can be manually controlled; when the missile opening switch is in the closed state, the missile is in a complete power-off state and a completely safe state; the missile leaving switch is opened at the moment of leaving the unmanned aerial vehicle, and supplies power to the delay sensor and the height sensor 10, so that the two sensors start to work normally; when the height sensor 10 reaches the set burst height, the first warhead 2 is triggered, and a feedback signal is given to the delay sensor; after the first warhead 2 is triggered for a set time, the delay sensor triggers the second warhead 5; in order to prevent special situations of the first warhead 2, the delay sensor triggers the first warhead 2 again when triggering the second warhead 5. The manual detonation switch is used in extremely special situations of the missile, and when the missile reaches the predetermined burst point without explosion for a certain time, the remote control detonation switch directly detonates the two warheads. The missile opening switch, the missile leaving switch, the height sensor 10, and the delay sensor are in an AND relationship, and the manual detonation switch directly controls the two warhead detonators to directly detonate the two warheads, which is in an independent relationship with the above four.

[0032] In this embodiment, the first warhead EFP shaped charge fixing gasket 2.3 is used for fixing the first warhead shaped charge, is fixed at the head of the missile shell 4, has a cylindrical vacancy with a radius of 400 mm in the center, and has a thickness determined according to actual assembly conditions and adopts high-density metal material; the explosion-proof body 12 is mainly used for explosion-proof between the first warhead 2 and the second warhead 5, is made of polyurethane foam with a thickness of 40 mm, and has a cone in the center with a top height of 20 mm; the head fixing gasket 3 is used for fixing the first warhead 2 and the second warhead 5, can be made of high-density metal material combined with polyurethane foam, and the contact end with the first warhead 2 is polyurethane foam (a cone also exists in the center, and the actual condition is determined according to assembly conditions); the rear section selects high-density metal material, and the total thickness of the explosion-proof body 12 and the head fixing gasket 3 is 150 mm; the tail fixing gasket 9 is used for fixing the second warhead tail, is made of low-density alloy, and has a thickness determined according to actual assembly conditions; the tail wing 8 is made of aluminum alloy material with a thickness of 6 mm-10 mm, and meets the aerodynamics of low-resistance missiles; and the cable has a reserved line groove during assembly.

[0033] In this embodiment, the mass center of the missile is ensured to be concentrated in the front 1 / 3 of the whole missile during assembly, and the missile counterweight can be arranged in the reserved space.

[0034] Example 1

[0035] The high-energy flexible ice-breaking bomb based on high-thickness sea ice and capable of being precisely dropped by an unmanned aerial vehicle mainly comprises a bullet head 1, a primary warhead 2, a head fixing gasket 3, a bullet body shell 4, a secondary warhead 5, a control system cabin 6, a bullet tail 7, a tail wing 8, a tail fixing gasket 9, a height sensor 10, an internal cable 11 and an explosion-proof body 12. The primary warhead 2 mainly comprises a primary warhead main charge 2.1, an EFP liner 2.2, an EFP liner fixing gasket 2.3, an expansion tube 2.4, a detonator 2.5 and the internal cable 11. The primary warhead 2 mainly adopts a shaped charge, the main charge adopts high-explosive B explosive, and the charge amount is 1.5 kg. The EFP liner 2.2 mainly adopts a large-cone-angle liner, the cone angle is 160°, the liner is made of equal-wall-thickness red copper, the wall thickness is 6 mm, the inner diameter is 42 mm, and the outer diameter is 50 mm. The expansion tube 2.4 is mainly charged with passivated RDX, and the charge amount is 8 g. The detonator 2.5 adopts No. 8 detonator, reaches a certain height, the height sensor gives a command, excites the detonator, and detonates the transmission sequence (the expansion tube), and finally reaches the main center initiation. The secondary warhead 5 mainly comprises four circumferential linear EFP liners 5.4, a secondary warhead main charge 5.1, a linear center transmission explosive column 5.3 and four circumferential linear EFP liner fixing blocks 5.2. The secondary warhead charge mainly adopts high-explosive RDX / TNT 50 / 50, and the charge amount is 4.5 kg. The four circumferential linear EFP liners 5.4 mainly adopt linear spherical segment liners, the wall thickness is 5 mm, the length is 250 mm, the spherical segment liner outer diameter is 68 mm, the inner diameter is 63 mm, and the linear spherical segment liner material is red copper. The linear center transmission explosive column 5.3 is mainly charged with RDX, the mass is 24 g, the length is consistent with that of the main charge, is also initiated by No. 8 detonator, and the initiation time is controlled by a delay sensor. The four circumferential linear EFP liner fixing blocks 5.2 respectively reserve appropriate grooves in the center, fix the four liners by welding, and the four fixing blocks are fixed with the bullet body shell by welding. The fixing blocks can be made of light alloy material. There is a certain space gap between the secondary warhead and the shell, which provides a certain favorable burst height for the linear metal jet to form and invade the four-way ice layer. The bullet head 1 is provided with a flat head with a radius of 5 mm, which is used to prevent skip when contacting the ice layer and affect the opening of the ice layer by the primary warhead 2. The bullet head 1 adopts a circular arc generatrix, the curvature center is on the vertical line of the contact point between the bullet head 1 and the bullet body, the connecting contact angle is 0°, and the curvature radius is 425 mm. The bullet head 1 is made of 58SiMn steel, and the wall thickness of the bullet head 1 is 5 mm. The bullet head 1 and the bullet body shell 4 are connected by threads, and the threads can be sheared when a certain strength is reached.The elastic shell 4 has a length of 400 mm, an elastic radius of 50 mm, and a thickness of 5 mm, and is made of 58SiMn. A groove with a thickness of 1 mm is reserved in the elastic shell 4, and is located at the positions opposite to the four shaped charges. The groove is formed every 15°, so as to facilitate the breaking of the shell at the moment of explosion and prevent the influence on the linear circumferential metal jet. The tail part is made of 58SiMn and D60 steel, has a length of 100 mm, and has a thickness of 5 mm. The tail part 7 ensures a stern angle of 6°. The tail part 7 mainly stores the control system cabin 6, and the control system cabin 6 mainly includes an elastic body opening switch, a separation elastic body switch, a delay sensor, a manual control switch, and a battery.

[0036] The first warhead EFP shaped charge fixing pad 2.3 is used for fixing the first warhead shaped charge, is fixed at the head of the elastic shell 4, has a cylindrical vacancy with a radius of 400 mm in the center, and has a thickness determined according to the actual assembly condition and is made of high-density metal material. The explosion-proof body 12 is mainly used for explosion-proof between the first warhead 2 and the second warhead 5, is made of polyurethane foam with a thickness of 40 mm, and has a cone in the center with a top height of 20 mm. The head fixing pad 3 is used for fixing the first warhead 2 and the second warhead 5, and is made of high-density metal material combined with polyurethane foam. The contact end of the first warhead 2 is made of polyurethane foam (a cone also exists in the center, and the actual condition is determined according to the assembly condition), the rear section is made of high-density metal material, the total thickness of the explosion-proof body 12 and the head fixing pad 3 is 150 mm, and the tail fixing pad 9 is used for fixing the tail part of the second warhead, is made of low-density alloy, and has a thickness determined according to the actual assembly. The tail wing 8 is made of aluminum alloy material, has a thickness of 6-10 mm, and meets the aerodynamics of a low-resistance projectile. The cable is reserved in a line groove during assembly.

[0037] The ice breaking rate at the designated ice breaking position can reach 80%.

[0038] Example 2

[0039] The high-energy flexible ice-breaking bomb based on high-thickness sea ice and capable of being precisely dropped by an unmanned aerial vehicle mainly comprises a bullet head 1, a first warhead 2, a head fixing gasket 3, a bullet body shell 4, a second warhead 5, a control system cabin 6, a bullet tail 7, a tail wing 8, a tail fixing gasket 9, a height sensor 10, an internal cable 11 and an explosion-proof body 12. The first warhead 2 mainly comprises a first warhead main charge 2.1, an EFP liner 2.2, an EFP liner fixing gasket 2.3, an expanding tube 2.4 and a detonator 2.5. The first warhead 2 mainly adopts a shaped charge, the main charge adopts high-explosive B explosive, and the charge amount is 2 kg. The EFP liner 2.2 mainly adopts a large-cone-angle liner, the cone angle is 165°, the liner is made of equal-wall-thickness cast iron, the wall thickness is 6.5 mm, the inner diameter is 44 mm, and the outer diameter is 50 mm. The expanding tube 2.4 is mainly charged with passivated RDX, and the charge amount is 12 g. The detonator 2.5 adopts No. 8 detonator. When reaching a certain height, the height sensor 10 gives a command to excite the detonator 2.5 to detonate the transmission sequence (expanding tube) and finally detonate the main center initiation. The second warhead 5 mainly comprises four circumferential linear EFP liners 5.4, a second warhead main charge 5.1, a linear center transmission explosive column 5.3 and four circumferential linear EFP liner fixing blocks 5.2. The second warhead 5 is mainly charged with high-explosive explosives such as B explosive and RDX / TNT 20 / 80, and the charge amount is 5.5 kg. The four circumferential linear EFP liners 5.4 mainly adopt linear spherical segment liners, the wall thickness is 6 mm, the length is 300 mm, the spherical segment liner outer diameter is 70 mm, the inner diameter is 65 mm, and the linear spherical segment liner material is copper. The linear center transmission explosive column 5.3 is mainly charged with RDX, the mass is 36 g, the length is consistent with that of the main charge, and the same No. 8 detonator is used for detonation. The detonation time is controlled through a delay sensor. The four circumferential linear EFP liner fixing blocks 5.2 are respectively provided with appropriate grooves in the center, four liners are fixed through welding, the four fixing blocks are fixed with the bullet body shell 4 through welding, and the fixing blocks can be made of light alloy. There is a certain space gap between the second warhead and the shell, which provides a certain favorable burst height for the linear metal jet to form and invade the four-way ice layer. The bullet head 1 is provided with a flat head with a radius of 5 mm for preventing skip when contacting the ice layer and affecting the opening of the ice layer by the first warhead. The bullet head 1 adopts a circular arc generatrix, the curvature center is on the vertical line of the contact point between the bullet head 1 and the bullet body, the connection contact angle is 0°, and the curvature radius is 445 mm. The bullet head 1 is made of D60 carbon steel, and the wall thickness is 5 mm. The bullet head 1 and the bullet body shell 4 are connected through threads, and the threads can be sheared when reaching a certain strength.The elastic shell 4 has a length of 450 mm, an elastic radius of 52 mm, and a thickness of 5 mm, and is made of D60 steel. A groove with a thickness of 1 mm is reserved inside the elastic shell 4, and is located at the positions opposite to the four horn covers. The groove is formed every 15°, so as to facilitate the breaking of the shell at the moment of explosion and prevent the influence on the linear circumferential metal jet.

[0040] The ice breaking rate of the ice breaking site can reach 85%.

[0041] Although the embodiments of the present application have been shown and described above, it should be understood by those skilled in the art that the above embodiments are exemplary and cannot be construed as limiting the present application, and those skilled in the art can make changes, modifications, replacements and variations to the above embodiments within the scope of the present application.

[0042] In the description of the present specification, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the technical solutions of the present patent and simplifying the description, and therefore cannot be construed as indicating or implying that the devices or elements indicated must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be construed as limiting the present patent application.

[0043] In addition, the terms "first" and "second" are only for descriptive purposes, and cannot be construed as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined with "first" and "second" can explicitly or implicitly include at least one of the features. In the description of the present patent application, the meaning of "a plurality of" is at least two, such as two, three, etc., unless otherwise explicitly specified and limited.

[0044] In the present specification, unless otherwise explicitly specified and limited, the terms "mounting", "connection", "connection", "fixing" and the like should be understood in a broad sense, for example, can be fixedly connected, or can be detachably connected, or can be integrated; can be mechanically connected, or can be electrically connected; can be directly connected, or can be indirectly connected through an intermediate medium; can be the internal communication of two elements or the interaction relationship between two elements, unless otherwise explicitly limited. For those skilled in the art, the specific meaning of the above terms in the present specification can be understood according to the specific circumstances.

[0045] In this specification, unless specifically stated and limited otherwise, a first feature "on" or "above" a second feature can be directly on or above the second feature or intervening medium can be present between the first and second features. Also, a first feature "on", "above", or "over" a second feature can be directly on, above, or over the second feature or can be indirectly on, above, or over the second feature with one or more intervening features present between the first and second features. A first feature "under", "below", or "underneath" a second feature can be directly under, below, or underneath the second feature or can be indirectly under, below, or underneath the second feature with one or more intervening features present between the first and second features.

[0046] In the description of the specification, the description using the terms "one embodiment", "some embodiments", "an example", "a specific example", or "some examples" etc. means that the particular feature, structure, material or characteristic following the term is included in at least one embodiment or example of the present application. The illustrative examples described in this specification should not be construed as being exclusive of other embodiments or examples of the present application. In other words, the illustrative examples described in this specification are included in at least one embodiment or example of the present application. In addition, the illustrative examples described in this specification can be combined with each other in any manner.

[0047] Although the embodiments of the present application have been shown and described above, it is understood that the above-described embodiments are exemplary and are not to be construed as limiting the present application, and that variations, modifications, substitutions and changes can be made to the above-described embodiments by those skilled in the art without departing from the scope of the present application.

Claims

1. An ice-breaking projectile deployed by an unmanned aerial vehicle (UAV) based on high-thickness sea ice, characterized in that, The projectile includes a warhead, a primary warhead, a projectile casing, a secondary warhead, and a tail section. The warhead is located at the upper end of the projectile casing, and the primary warhead is positioned between the projectile casing and the warhead. The primary warhead includes a main explosive charge, an EFP shaped charge liner, an EFP shaped charge liner fixing gasket, a detonator, and a detonator. The EFP shaped charge liner is located at the upper end of the main explosive charge, and both ends of the EFP shaped charge liner are fixed by the EFP shaped charge liner fixing gasket. The detonator is located at the lower end of the main explosive charge, and the detonator is located at the lower end of the detonator. The projectile body... The lower end of the shell is provided with the tail section of the projectile, and the secondary warhead is provided inside the shell. The secondary warhead includes a circumferential linear EFP shaped charge liner, a main charge of the secondary warhead, a linear center-detonating charge, and a circumferential linear EFP shaped charge liner fixing block. The main charge of the secondary warhead is located at the center of the shell, and the linear center-detonating charge is located at the center of the main charge. The outer side of the main charge is fixed by the circumferential linear EFP shaped charge liner, and the circumferential linear EFP shaped charge liner is fixed to the shell by the circumferential linear EFP shaped charge liner fixing block. An altitude sensor is installed inside the warhead, located at the top of the warhead, and is connected to the first-stage warhead via an internal cable. The tail section of the missile houses a control system compartment, which includes a missile body opening switch, an off-board missile body switch, a delay sensor, a manual detonation switch, and a battery. The missile body opening switch is in the off state before being assembled with the UAV. The off-board missile body switch supplies power to the delay sensor and the altitude sensor. The altitude sensor triggers the primary warhead and simultaneously sends a feedback signal to the delay sensor. After the primary warhead is triggered, the delay sensor triggers the secondary warhead. The delay sensor triggers the primary warhead again while triggering the secondary warhead. The manual detonation switch can remotely control the direct detonation of the primary and secondary warheads.

2. The ice-breaking projectile deployed by an unmanned aerial vehicle (UAV) based on high-thickness sea ice as described in claim 1, characterized in that, It also includes fixing shims, which include a head fixing shim and a tail fixing shim. The upper end of the projectile shell is connected to the projectile head through the head fixing shim, and the lower end of the projectile shell is connected to the projectile tail through the tail fixing shim.

3. The ice-breaking projectile deployed by a drone based on high-thickness sea ice as described in claim 2, characterized in that, It also includes an explosion-proof body, which is disposed inside the projectile casing. The secondary warhead is disposed at the lower end of the explosion-proof body, and the head fixing pad is disposed at the upper end of the explosion-proof body.

4. The ice-breaking projectile deployed by a drone based on high-thickness sea ice as described in claim 3, characterized in that, The projectile casing has grooves inside, which are located directly opposite the circumferential linear EFP shaped charge liner. The projectile casing is grooved once every 15° in the circumferential direction to facilitate casing breakage at the moment of explosion and prevent it from affecting the formed linear circumferential metal jet.

5. An ice-breaking projectile deployed by an unmanned aerial vehicle (UAV) based on high-thickness sea ice as described in claim 4, characterized in that, The projectile is provided with a tail fin, which is located at the end of the projectile's tail section.

6. A method for using an icebreaking projectile deployed by an unmanned aerial vehicle (UAV) based on high-thickness sea ice as described in claim 1, characterized in that, Includes the following steps: S10. The drone flies to the designated detonation point and hovers at the designated altitude; S20: The missile leaves the aircraft and falls freely. When the warhead penetrates the sea ice, the altitude sensor triggers the first-stage warhead. The main charge of the first-stage warhead crushes the shaped charge liner and forms an explosively formed projectile, which penetrates the sea ice. S30, the second-stage warhead continues to advance due to inertia and enters the opening of the first-stage warhead. At this time, the delay sensor triggers the second-stage warhead. The main charge of the second-stage warhead crushes the four linear spherical canopies, forming four LEFPs that cut the circumferential ice layer, causing the surrounding ice layer to break and achieve the effect of breaking ice. S40. Based on the ice-breaking effect, predict the next bombing.

7. The method of using an icebreaking projectile deployed by an unmanned aerial vehicle (UAV) based on high-thickness sea ice as described in claim 6, characterized in that, The off-board switch activates the moment the missile leaves the drone, powering the delay sensor and altitude sensor. The two sensors then begin normal operation. When the altitude sensor reaches the set detonation altitude, it triggers the primary warhead and simultaneously sends a feedback signal to the delay sensor. After a set time following the triggering of the primary warhead, the delay sensor triggers the secondary warhead. To prevent any unforeseen circumstances with the primary warhead, the delay sensor triggers the primary warhead again at the same time as triggering the secondary warhead.

8. The method of using an icebreaking projectile deployed by an unmanned aerial vehicle (UAV) based on high-thickness sea ice as described in claim 6, characterized in that, If the projectile does not detonate within a certain time after reaching the predetermined detonation point, the detonation control switch can be manually controlled to directly detonate both warheads. The detonation control switch can directly control the detonators of the two warheads, allowing for the direct detonation of both warheads.

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