Empennage stabilizing device of jamming bomb and jamming bomb

Abstract

The invention relates to the technical field of guidance, in particular to an empennage stabilizing device of a jamming bomb and the jamming bomb. The device comprises an empennage assembly, the empennage assembly comprises an empennage seat, an empennage piece, an ignition assembly, a propellant powder bag and a delay ignition piece, and the empennage seat is used for supporting the whole empennage assembly; the wing piece is arranged on the outer side of the empennage seat, and the wing piece is used for achieving a flight balance effect on the whole empennage assembly; the ignition assembly is installed in the tail end of the empennage base. The propellant bag is installed in the middle of the empennage base and used for providing power for the whole empennage assembly. And the delay ignition piece is mounted at the front end of the empennage seat. The front end of the pull ring is sealed through the delay gasket, meanwhile, the delay ignition tube is installed on the inner ring of the powder box so that the delay ignition tube can be conveniently supported through the delay gasket, the propellant powder bag is located between the delay ignition tube and the ignition assembly, and then the time for the propellant powder bag to reach the front end of the empennage assembly is prolonged after the propellant powder bag is ignited.

Description

Technical Field

[0001] The invention relates to the field of guidance technology, and in particular to a tail wing stabilization device of a jamming bomb and the jamming bomb. Background Art

[0002] The tail fin of a missile body refers to a tail stabilization device installed at the tail of the missile body to control ballistic flight. The tail fin of a missile body is usually designed to have a certain airfoil, and the flight attitude and direction of the missile body are controlled by changing its angle or position, thereby ensuring that the missile body maintains stability and accuracy during flight. The main functions of the tail fin of a missile body include: Stability control: The tail fin of the missile body can help adjust the attitude of the missile body to keep it stable during flight. By adjusting the position and angle of the tail fin, the missile body can be balanced and uncontrolled rotation can be reduced; Flight control: The tail fin of the missile body can be used to adjust the flight direction of the missile body so that it can accurately hit the target or fly along a predetermined path. By controlling the movement of the tail fin, the flight trajectory and flight speed of the missile body can be adjusted. Deceleration and stabilization: Some tail fin designs of missile bodies can also play a role in deceleration, slowing down the flight speed of the missile body by increasing resistance, while improving flight stability.

[0003] The tail mechanism in the prior art includes a tail inner shell, a tail outer shell, a wing root, a wing surface, a rotating shaft, a torsion spring, a rolling bearing, a bayonet, a compression spring, a blocking screw, and a bottom screw, and a locking mechanism composed of the bayonet, the compression spring, and the blocking screw; however, the rotation of the tail during flight depends on the air resistance of the wing surface to rotate, but this rotation speed is relatively low, resulting in poor stability in the flight of the tail-controlled projectile, which easily causes the projectile to deviate from the designed trajectory during flight. Summary of the invention

[0004] In view of the above-mentioned shortcomings of the prior art, the present invention solves the problem that the tail wing rotates during flight by relying on the air resistance of the wing surface. However, this rotation speed is relatively low, resulting in poor stability of the tail wing controlling the flight of the projectile, which can easily cause the projectile to deviate from the designed trajectory during flight.

[0005] In order to achieve the above-mentioned object and other related objects, the present invention provides a tail stabilization device for a jamming bomb, including a tail assembly, wherein the tail assembly includes:

[0006] A tail wing seat, which is used to support the entire tail wing assembly;

[0007] A wing member, which is arranged on the outside of the tail wing seat, and is used to provide flight balance for the entire tail wing assembly;

[0008] An ignition assembly installed inside the tail end of the tail wing seat;

[0009] A propellant charge, which is installed in the middle of the tail seat and is used to provide power to the entire tail assembly;

[0010] The delayed ignition component is installed at the front end of the tail wing seat.

[0011] In one embodiment of the present invention, the tail wing seat comprises:

[0012] A cylinder body, the outer side of which is provided with a wing member;

[0013] A mounting ring, which is mounted on the front end of the cylinder;

[0014] Install a tailstock, which is installed at the tail end of the barrel;

[0015] The surfaces of the mounting ring and the mounting tailstock are both provided with positioning pins.

[0016] In one embodiment of the present invention, the mounting ring and the mounting tailstock are integrally formed.

[0017] In one embodiment of the present invention, a ventilation hole is opened in the middle of the cylinder.

[0018] In one embodiment of the present invention, the wing member comprises:

[0019] A tail pin shaft, which is installed inside the positioning pin control;

[0020] a wing, one end of which contacts the center of the torsion spring;

[0021] A torsion spring is movably sleeved on the outer side of the tail wing pin shaft, one end of the torsion spring contacts the wing piece, and the other end of the torsion spring contacts the cylinder body.

[0022] In one embodiment of the present invention, the delayed ignition component comprises:

[0023] A medicine box, which is installed at the front end of the tail wing seat;

[0024] A delayed ignition tube, which is installed at the inner circle of the medicine box, and the propellant bag is arranged between the delayed ignition tube and the ignition component;

[0025] A delay washer is arranged on the side of the delay ignition tube, and the delay washer is in contact with the front end of the tail wing seat.

[0026] In one embodiment of the present invention, the wing comprises:

[0027] The sheet body has two integrally formed sleeves at its ends;

[0028] A shaft sleeve is sleeved on the outer side of the tail wing pin shaft, and the middle part of the torsion spring is located between the two shaft sleeves.

[0029] In one embodiment of the present invention, four of the winglets and the mounting tail seat are provided, and the four winglets are distributed in a circular array about the axis of the tail wing seat, two locating pin controls are provided on the mounting tail seat, the tail wing pin shafts inserted in the two locating pin controls are arranged in parallel, and the winglet and the torsion spring are both sleeved on the outside of one of the tail wing pin shafts, and are in contact with the outer surface of the other tail wing pin shaft and the winglet.

[0030] In one embodiment of the present invention, the wing is a non-metallic sheet member.

[0031] The present invention also provides a jamming bomb, comprising the above-mentioned tail wing stabilization device of the jamming bomb, the jamming bomb also includes a smoke warhead, the tail of the smoke warhead is installed with the tail wing stabilization device of the jamming bomb, a projectile charge is installed at the connection between the smoke warhead and the tail wing stabilization device of the jamming bomb, a waterproof cap for sealing is installed at the front end of the smoke warhead, a pull ring is installed at the front end of the waterproof cap, the projectile charge is installed in a medicine box, and the projectile charge is in contact with the delayed ignition tube, and the axes of the waterproof cap, the smoke warhead and the tail wing stabilization device of the jamming bomb coincide.

[0032] As described above, the tail fin stabilization device of a jammer and the jammer of the present invention have the following beneficial effects:

[0033] (1) A tail stabilization device of a jamming bomb of the present invention is a tail stabilization device composed of a tail assembly, and the tail assembly is composed of a tail seat, a wing member, an ignition assembly, a propellant bag and a delayed ignition member, and the tail seat plays a supporting role for the wing member, the ignition assembly, the propellant bag and the delayed ignition member, so that the tail structure of the jamming bomb remains stable, and the wing member installed outside the tail seat enables the tail seat to maintain stable flight through the deployment of the wing member during flight, and the ignition assembly installed inside the rear end of the tail seat enables the ignition assembly to ignite the propellant bag installed at the front end of the tail seat, and the propellant bag provides flight power for the tail seat after ignition.

[0034] (2) The tail wing seat in the tail wing stabilization device of a jamming bomb of the present invention is composed of a cylinder, a mounting ring, a mounting tail seat and a positioning pin control, and the cylinder is used to support the mounting ring and the mounting tail seat integrally formed at both ends, and the air vents opened in the middle of the cylinder facilitate the high-temperature gas discharged after the propellant is ignited to be discharged through the air vents, and then facilitate the high-temperature gas discharged from the air vents to carry the tail wing seat to rotate during flight through the reaction force, thereby improving the stability of the tail wing seat during flight and solving the problem of insufficient rotation speed of the tail wing seat when rotating during flight.

[0035] (3) The wing parts in the tail stabilization device of a jamming bomb of the present invention include wing pieces, torsion springs and tail pin shafts, and the two ends of the tail pin shaft are respectively installed in the positioning pin controls opened on the surfaces of the mounting ring and the mounting tail seat, and the wing pieces and torsion springs are both sleeved on the outside of the tail pin shaft, so that the tail pin shaft can support the wing pieces and torsion springs, and the two ends of the torsion spring are respectively in contact with the wing pieces and the tail seat, so that the wing pieces can be unfolded under the action of the torsion springs, so that the tail assembly can maintain balance through the wing pieces during flight, and the delayed ignition part consists of a medicine box, a delayed gasket and a delayed ignition tube, the delayed ignition tube seals the front end of the pull ring through the delayed gasket, and the delayed ignition tube is installed on the inner ring of the medicine box, so that the delayed ignition tube is supported by the delayed gasket, and the propellant is located between the delayed ignition tube and the ignition assembly, so that the time for the propellant to reach the front end of the tail assembly is extended after ignition.

[0036] (4) The tail wing stabilization device of a jamming bomb of the present invention is a wing composed of a sheet body and a sleeve, and two sleeves are integrally formed at the end of the sheet body, and the two sleeves are sleeved on the outside of the tail wing pin shaft, and the middle part of the torsion spring is located between the two sleeves, so as to facilitate the torsion spring to unfold with the wing after being twisted.

[0037] (5) The tail wing stabilization device of a jammer bomb of the present invention has four winglets in a circular array, so that the tail wing assembly can maintain flight stability through the four winglets during flight, and two positioning pins are installed on the tail seat. At the same time, the tail wing pin shaft inserted in one of the positioning pin controls is used for supporting the wing and the torsion spring, and the tail wing pin shaft inserted in the other positioning pin control is in contact with the outer surface of the wing, so that the wing is supported by the two tail wing pin shafts after it is unfolded.

[0038] (6) The tail fin stabilization device of a jammer bomb of the present invention uses a fin having a non-metallic sheet structure to prevent the fin from being melted by the high-temperature gas discharged from the air vent.

[0039] (7) The tail stabilization device of a jammer of the present invention is a jammer composed of a pull ring, a waterproof cap, a smoke warhead, a projectile charge and a tail assembly, wherein the tail assembly provides tail stabilization for the jammer during flight, and the projectile charge is used to eject the tail assembly during flight of the smoke warhead. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] Figure 1 A structural diagram of a jammer provided in an embodiment of the present application.

[0041] Figure 2 A structural diagram of a tail stabilization device for a jammer provided in an embodiment of the present application.

[0042] Figure 3 A cross-sectional structural diagram along line AA of a tail fin stabilization device of a jamming missile provided in an embodiment of the present application.

[0043] Figure 4 A structural diagram of a tail wing seat of a tail wing stabilization device of a jamming missile provided in an embodiment of the present application.

[0044] Figure 5 A wing structure diagram of a tail stabilization device of a jammer provided in an embodiment of the present application.

[0045] Component number description

[0046] 1 Pull ring

[0047] 2 Waterproof cap

[0048] 3 Smoke warhead

[0049] 4 Projectile Charge

[0050] 5 Tail assembly

[0051] 51 Tail Wing Seat

[0052] 511 Cylinder

[0053] 512 Mounting ring

[0054] 513 Installing the tailstock

[0055] 514 Positioning pin control

[0056] 52 Medicine Box

[0057] 53 Delay washer

[0058] 54 Delayed ignition tube

[0059] 55 Propellant Charge

[0060] 56 Ignition Components

[0061] 57 Wing

[0062] 571 Sheet

[0063] 572 Bushing

[0064] 58 Torsion spring

[0065] 59 Tail pin DETAILED DESCRIPTION

[0066] The following describes the embodiments of the present invention by specific examples, and those skilled in the art can easily understand other advantages and effects of the present invention from the contents disclosed in this specification. The present invention can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present invention. It should be noted that the following embodiments and features in the embodiments can be combined with each other without conflict.

[0067] It should be noted that the illustrations provided in the following embodiments are only used to illustrate the basic concept of the present invention in a schematic manner, and thus the illustrations only show components related to the present invention rather than being drawn according to the number, shape and size of components in actual implementation. In actual implementation, the type, quantity and proportion of each component may be changed arbitrarily, and the component layout may also be more complicated.

[0068] Terms such as first or second can be used to describe various components, but these components are not limited by the above terms. The above terms are used to distinguish one component from another component, for example, without departing from the scope of the concept according to the present disclosure, a first component can be referred to as a second component, and similarly, a second component can be referred to as a first component.

[0069] In addition, "connected / coupled" means that one component is directly electrically coupled to another component or is indirectly electrically coupled through another component. The singular form may include the plural form unless explicitly stated in the sentence. In addition, "include / comprise" or "includes / comprises" used in this specification indicates that one or more components, steps, operations, and elements exist or have been added. The specific structural or functional descriptions of the examples of the implementation of the concepts disclosed in this specification are only illustrated to describe the examples of the implementation of the concepts, and the examples of the implementation of the concepts can be implemented in various forms, but these descriptions are not limited to the examples of the implementation described in this specification.

[0070] According to the concept, various modifications and changes can be applied to the examples of the embodiments, so that the examples of the embodiments will be illustrated in the drawings and described in the specification. However, the examples of the embodiments according to the concept are not limited to the specific embodiments, but include all changes, equivalents or replacements included in the spirit and technical scope of the present disclosure.

[0071] It should be understood that when an element is described as being "coupled" or "connected" to another element, the element may be directly coupled or directly connected to the other element, or may be coupled or connected to the other element through a third element. Conversely, it should be understood that when an element is referred to as being "directly coupled to" or "directly coupled to" another element, no other element is placed between them. Other expressions describing the relationship between components (i.e., "between" and "directly between" or "adjacent to" and "directly adjacent to") need to be interpreted in the same manner.

[0072] The terms used in this specification are only used to describe specific examples of the embodiments and are not intended to limit the present disclosure. If there is no clear opposite meaning in the context, the singular form may include the plural form. In this specification, it should be understood that the term "including" or "having" indicates the presence of the features, quantities, steps, operations, components, parts or combinations thereof described in the specification, but the possibility of the presence or addition of one or more other features, quantities, steps, operations, components, parts or combinations thereof cannot be precluded.

[0073] If there is no contrary definition, all terms (including technical terms or scientific terms) used herein have the same meaning as those generally understood by ordinary technicians in the field. If the terms defined in the commonly used dictionary are not clearly defined in this specification, they should be interpreted as having the same meaning as in the context of the relevant technology, and not interpreted as ideal or overly formal meanings.

[0074] Descriptions of well-known components and processing techniques may be omitted so as not to unnecessarily obscure the embodiments of the disclosure.

[0075] Throughout the specification, the same reference numerals refer to the same elements. Thus, even if a reference numeral is not mentioned or described with reference to one figure, it may be mentioned or described with reference to another figure. Furthermore, even if a reference numeral is not shown in one figure, it may be mentioned or described with reference to another figure.

[0076] In addition, the logic level of the signal may be different or opposite to the described logic level. For example, a signal described as having a logic "high" level may alternatively have a logic "low" level, and a signal described as having a logic "low" level may alternatively have a logic "high" level.

[0077] The following will describe the various embodiments of the present disclosure in detail with reference to the accompanying drawings. However, it will be appreciated by those skilled in the art that in the various embodiments of the present disclosure, many technical details are provided in order to enable the reader to better understand the present disclosure. However, even without these technical details and various changes and modifications based on the following embodiments, the technical solutions claimed in the present disclosure can be implemented.

[0078] In order to overcome the problem in the prior art that the tail wing rotates during flight by relying on the resistance of the air on the wing surface, but this rotation speed is relatively low, resulting in poor flight stability of the tail wing-controlled missile, which easily causes the missile to deviate from the designed trajectory during flight, the present invention provides a tail wing stabilization device for a jamming missile.

[0079] See also Figure 1-5 , Figure 1 A structural diagram of a jammer provided in an embodiment of the present application. Figure 2 A structural diagram of a tail stabilization device for a jammer provided in an embodiment of the present application. Figure 3 A cross-sectional structural diagram along line AA of a tail fin stabilization device of a jamming missile provided in an embodiment of the present application. Figure 4 A structural diagram of a tail wing seat of a tail wing stabilization device of a jamming missile provided in an embodiment of the present application. Figure 5 A wing structure diagram of a tail stabilization device of a jamming bomb provided in an embodiment of the present application. A tail stabilization device of a jamming bomb of the present invention comprises a tail assembly 5, and the tail assembly 5 comprises: a tail seat 51, a wing, an ignition assembly 56, a propellant bag 55, and a delayed ignition component. The tail seat 51 is used to support the entire tail assembly 5; the wing is arranged on the outside of the tail seat 51, and the wing is used to balance the entire tail assembly 5 in flight; the ignition assembly 56 is installed inside the tail end of the tail seat 51; the propellant bag 55 is installed in the middle of the tail seat 51, and is used to provide power to the entire tail assembly 5; the delayed ignition component is installed at the front end of the tail seat 51.

[0080] In one embodiment of the present invention, a tail stabilization device for a jamming bomb includes a tail assembly 5; the tail assembly 5 includes a tail seat 51 that serves as a support, a wing member located outside the tail seat 51 for flight balance, and an ignition assembly 56 installed inside the tail end of the tail seat 51, a propellant bag 55 located in the middle of the tail seat 51 for providing power, and a delayed ignition member installed at the front end of the tail seat 51.

[0081] Specifically, the tail wing seat 51 includes a cylinder 511, a mounting ring 512, and a mounting tail seat 513. A wing piece is arranged on the outside of the cylinder 511; the mounting ring 512 is mounted on the front end of the cylinder 511; the mounting tail seat 513 is mounted on the rear end of the cylinder 511; and positioning pin controls 514 are provided on the surfaces of the mounting ring 512 and the mounting tail seat 513.

[0082] Specifically, the mounting ring 512 and the mounting tailstock 513 are integrally formed.

[0083] Specifically, a ventilation hole is opened in the middle of the cylinder 511.

[0084] In one embodiment of the present invention, the tail wing seat 51 includes a cylinder 511, a mounting ring 512 integrally formed at the front end of the cylinder 511, a mounting tail seat 513 integrally formed at the rear end of the cylinder 511, and an air vent opened in the middle of the cylinder 511. Positioning pin controls 514 are opened on the surfaces of the mounting ring 512 and the mounting tail seat 513.

[0085] Specifically, the wing member includes a tail wing pin 59, a wing 57, and a torsion spring 58. The tail wing pin 59 is installed inside the positioning pin control 514; one end of the wing 57 is in contact with the center of the torsion spring 58; the torsion spring 58 is movably sleeved on the outside of the tail wing pin 59, and one end of the torsion spring 58 is in conflict with the wing 57, and the other end of the torsion spring 58 is in conflict with the cylinder 511.

[0086] In one embodiment of the present invention, the wing member includes a tail pin shaft 59 installed in the positioning pin control 514, and a wing 57 and a torsion spring 58 are movably sleeved outside the tail pin shaft 59, and the two ends of the torsion spring 58 are respectively in contact with the wing 57 and the tail seat 51.

[0087] Specifically, the delayed ignition component includes a medicine box 52, a delayed ignition tube 54, and a delayed gasket 53. The medicine box 52 is installed at the front end of the tail wing seat 51; the delayed ignition tube 54 is installed at the inner circle of the medicine box 52, and the propellant bag 55 is arranged between the delayed ignition tube 54 and the ignition assembly 56; the delayed gasket 53 is arranged on the side of the delayed ignition tube 54, and the delayed gasket 53 is in contact with the front end of the tail wing seat 51.

[0088] In one embodiment of the present invention, the delayed ignition component includes a medicine box 52 installed at the front end of the tail fin seat 51, a delayed ignition tube 54 is arranged at the inner circle of the medicine box 52, and a delayed gasket 53 for support is arranged on the side of the delayed ignition tube 54, the delayed gasket 53 is in contact with the front end of the tail fin seat 51, and the propellant charge 55 is located between the delayed ignition tube 54 and the ignition assembly 56.

[0089] In the first embodiment of the present invention, a tail stabilizing device is formed by a tail assembly 5, and the tail assembly 5 is composed of a tail seat 51, a wing, an ignition assembly 56, a propellant 55 and a delayed ignition component, and the tail seat 51 plays a supporting role for the wing, the ignition assembly 56, the propellant 55 and the delayed ignition component, so that the tail structure of the jamming bomb remains stable, and the wing installed outside the tail seat 51 enables the tail seat 51 to maintain a stable flight through the deployment of the wing during the flight, and the ignition assembly 56 installed inside the tail end of the tail seat 51 enables the ignition assembly 56 to ignite the propellant 55 installed at the front end of the tail seat 51, and the launch After the propellant charge 55 is ignited, it provides flight power for the tail wing seat 51; the tail wing seat 51 is composed of a barrel 511, a mounting ring 512, a mounting tail seat 513 and a positioning pin control 514, and the barrel 511 is used to support the mounting ring 512 and the mounting tail seat 513 integrally formed at both ends, and the air vents opened in the middle of the barrel 511 facilitate the high-temperature gas discharged after the propellant charge 55 is ignited to be discharged through the air vents, and then the high-temperature gas discharged from the air vents facilitates the tail wing seat 51 to rotate during the flight through the reaction force, thereby improving the stability of the tail wing seat 51 during the flight and solving the problem of insufficient rotation speed of the tail wing seat 51 during rotation during the flight.

[0090] The wing assembly of the present invention comprises a wing 57, a torsion spring 58 and a tail pin 59, and the two ends of the tail pin 59 are respectively mounted in the positioning pin 514 opened on the surface of the mounting ring 512 and the mounting tail seat 513, and the wing 57 and the torsion spring 58 are both sleeved on the outside of the tail pin 59, so that the tail pin 59 can support the wing 57 and the torsion spring 58, and the two ends of the torsion spring 58 are respectively in contact with the wing 57 and the tail seat 51, so that the wing 57 can be unfolded under the action of the torsion spring 58, so that the tail assembly 5 During flight, the balance is maintained by the wing 57, and the delayed ignition component consists of a medicine box 52, a delayed gasket 53 and a delayed ignition tube 54. The delayed ignition tube 54 seals the front end of the pull ring 1 through the delayed gasket 53. At the same time, the delayed ignition tube 54 is installed on the inner circle of the medicine box 52, so that the delayed ignition tube 54 is supported by the delayed gasket 53, and the propellant charge 55 is located between the delayed ignition tube 54 and the ignition assembly 56, so that the time for the propellant charge 55 to reach the front end of the tail assembly 5 is extended after ignition.

[0091] Specifically, the wing 57 includes a sheet body 571 and a sleeve 572 . Two integrally formed sleeves 572 are provided at the end of the sheet body 571 . The sleeve 572 is sleeved on the outside of the tail wing pin 59 , and the middle of the torsion spring 58 is located between the two sleeves 572 .

[0092] In one embodiment of the present invention, the wing 57 includes a sheet body 571 and two shaft sleeves 572 integrally formed at the ends of the sheet body 571 . The shaft sleeves 572 are sleeved on the outside of the tail wing pin 59 , and the middle part of the torsion spring 58 is located between the two shaft sleeves 572 .

[0093] Specifically, there are four winglets 57 and four mounting tail seats 513, and the four winglets 57 are distributed in a circular array about the axis of the tail seat 51, and two positioning pin controls 514 are provided on the mounting tail seat 513. The tail pin shafts 59 inserted in the two positioning pin controls 514 are arranged in parallel, and the winglets 57 and the torsion springs 58 are both sleeved on the outside of one of the tail pin shafts 59, and are in contact with the outer surface of the other tail pin shaft 59 and the winglet 57.

[0094] In one embodiment of the present invention, a wing 57 is formed by a sheet body 571 and a sleeve 572, and two sleeves 572 are integrally formed at the ends of the sheet body 571, and the two sleeves 572 are sleeved on the outside of the tail wing pin 59, and the middle part of the torsion spring 58 is located between the two sleeves 572, so that it is convenient for the torsion spring 58 to be twisted and then unfolded with the wing 57.

[0095] In one embodiment of the present invention, there are four winglets 57 and four tail seat installation seats 513 in a circular array, and the four winglets 57 are distributed in a circular array about the axis of the tail seat 51, two positioning pin controls 514 are provided on the tail seat installation seat 513, and the tail pin shafts 59 inserted in the two positioning pin controls 514 are arranged in parallel, and the winglets 57 and the torsion springs 58 are both sleeved outside one of the tail pin shafts 59, and the other tail pin shaft 59 is in contact with the outer surface of the winglet 57.

[0096] In one embodiment of the present invention, there are four winglets 57 in a circular array, so that the tail assembly 5 can maintain flight stability through the four winglets 57 during flight, and two positioning pin controls 514 are installed on the tail seat 513. At the same time, the tail pin shaft 59 inserted in one of the positioning pin controls 514 is used to support the winglet 57 and the torsion spring 58, and the tail pin shaft 59 inserted in the other positioning pin control 514 is in contact with the outer surface of the winglet 57, so that the winglet 57 is supported by the two tail pin shafts 59 after it is unfolded.

[0097] In one embodiment of the present invention, the fin 57 is a non-metallic sheet member.

[0098] In one embodiment of the present invention, the fins 57 are non-metallic sheet-like structures to prevent the fins 57 from being melted by the high-temperature gas discharged from the air holes.

[0099] In a second embodiment of the present invention,

[0100] See also Figure 1-5The present invention also provides a jamming bomb, comprising the above-mentioned tail wing stabilization device of the jamming bomb, the jamming bomb also comprising a smoke warhead 3, the tail of the smoke warhead 3 is installed with the tail wing stabilization device of the jamming bomb, a projectile charge 4 is installed at the connection between the smoke warhead 3 and the tail wing stabilization device of the jamming bomb, a waterproof cap 2 for sealing is installed at the front end of the smoke warhead 3, a pull ring 1 is installed at the front end of the waterproof cap 2, the projectile charge 4 is installed in a medicine box 52, and the projectile charge 4 is in contact with the delayed ignition tube 54, and the axes of the waterproof cap 2, the smoke warhead 3 and the tail wing stabilization device of the jamming bomb coincide.

[0101] In one embodiment of the present invention, a jamming bomb is composed of a pull ring 1, a waterproof cap 2, a smoke warhead 3, a projectile charge 4 and a tail assembly 5, and the tail assembly 5 provides tail stability for the jamming bomb during flight, and the projectile charge 4 is used to throw the tail assembly 5 when the smoke warhead 3 is flying.

[0102] In summary, a tail stabilization device of a jamming bomb of the present invention is a tail stabilization device composed of a tail assembly, and the tail assembly is composed of a tail seat, a wing member, an ignition assembly, a propellant package and a delayed ignition member, and the tail seat plays a supporting role for the wing member, the ignition assembly, the propellant package and the delayed ignition member, so that the tail structure of the jamming bomb remains stable, and the wing member installed outside the tail seat enables the tail seat to maintain stable flight through the deployment of the wing member during flight, and the ignition assembly installed inside the rear end of the tail seat enables the ignition assembly to ignite the propellant package installed at the front end of the tail seat, and the propellant package provides flight power for the tail seat after ignition. The tail seat in the present invention is composed of a cylinder, a mounting ring, a mounting tail seat and a positioning pin control, and the cylinder is used to support the mounting ring and the mounting tail seat integrally formed at both ends, and the air hole opened in the middle of the cylinder is convenient for the high-temperature gas discharged after the propellant charge is ignited to be discharged through the air hole, and then the high-temperature gas discharged from the air hole is convenient for the tail seat to rotate during the flight through the reaction force, thereby improving the stability of the tail seat during the flight and solving the problem of insufficient rotation speed of the tail seat when rotating during the flight. The wing member in the present invention includes a wing, a torsion spring and a tail pin shaft, and the two ends of the tail pin shaft are respectively installed in the positioning pin control opened on the surface of the mounting ring and the mounting tail seat, and the wing and the torsion spring are both sleeved on the outside of the tail pin shaft, so that the tail pin shaft can support the wing and the torsion spring, and the two ends of the torsion spring are respectively in contact with the wing and the tail seat, so that the wing is easy to unfold under the action of the torsion spring, so that the tail assembly can maintain balance through the wing during flight, and the delayed ignition component is composed of a medicine box, a delayed gasket and a delayed ignition tube, the delayed ignition tube seals the front end of the pull ring through the delayed gasket, and the delayed ignition tube is installed in the inner ring of the medicine box, so that the delayed ignition tube is supported by the delayed gasket, and the propellant is located between the delayed ignition tube and the ignition assembly, so that the time for the propellant to reach the front end of the tail assembly is extended after ignition.

[0103] The above embodiments are merely illustrative of the principles and effects of the present invention, and are not intended to limit the present invention. Anyone familiar with the art may modify or alter the above embodiments without departing from the spirit and scope of the present invention. Therefore, all equivalent modifications or alterations made by a person of ordinary skill in the art without departing from the spirit and technical concept disclosed by the present invention shall still be covered by the claims of the present invention.

Claims

1. A tail fin stabilization device for a jamming bomb, characterized in that: The invention comprises a tail assembly (5), wherein the tail assembly (5) comprises: A tail wing seat (51), which is used to support the entire tail wing assembly (5); A wing member, which is arranged on the outside of the tail wing seat (51), and is used to provide flight balance for the entire tail wing assembly (5); An ignition assembly (56) installed inside the tail end of the tail wing seat (51); A propellant charge (55) is mounted in the middle of the tail seat (51) and is used to provide power to the entire tail assembly (5); A delayed ignition component is installed at the front end of the tail wing seat (51).

2. The tail fin stabilization device of a jamming bomb according to claim 1, characterized in that: The tail wing seat (51) comprises: A cylinder (511) having wings disposed on its outer side; A mounting ring (512) mounted on the front end of the cylinder (511); Installing a tailstock (513), which is installed at the tail end of the barrel (511); Positioning pins (514) are provided on the surfaces of the mounting ring (512) and the mounting tailstock (513).

3. The tail fin stabilization device of a jamming bomb according to claim 2 is characterized in that: The mounting ring (512) and the mounting tailstock (513) are integrally formed.

4. The tail fin stabilization device of a jamming bomb according to claim 2, characterized in that: A ventilation hole is provided in the middle of the cylinder (511).

5. The tail fin stabilization device of a jamming bomb according to claim 2, characterized in that: The wing member comprises: A tail pin shaft (59), which is installed inside the positioning pin control (514); A wing (57), one end of which contacts the center of the torsion spring (58); A torsion spring (58) is movably sleeved on the outside of the tail wing pin shaft (59), and one end of the torsion spring (58) is in contact with the wing (57), and the other end of the torsion spring (58) is in contact with the cylinder (511).

6. The tail fin stabilization device of a jamming bomb according to claim 5, characterized in that: The delayed ignition component comprises: A medicine box (52) mounted on the front end of the tail wing seat (51); A delayed ignition tube (54) is installed at the inner circle of the medicine box (52), and the propellant bag (55) is arranged between the delayed ignition tube (54) and the ignition component (56); A delay washer (53) is arranged on the side of the delay ignition tube (54), and the delay washer (53) is in contact with the front end of the tail wing seat (51).

7. The tail fin stabilization device of a jamming bomb according to claim 6, characterized in that: The wing (57) comprises: The sheet body (571) has two integrally formed shaft sleeves (572) disposed at its ends; A shaft sleeve (572) is sleeved on the outside of the tail wing pin shaft (59), and the middle part of the torsion spring (58) is located between the two shaft sleeves (572).

8. The tail fin stabilization device of a jamming bomb according to claim 7, characterized in that: The wing (57) and the mounting tail seat (513) are both provided with four, and the four wing (57) are distributed in a circular array about the axis of the tail seat (51), and the mounting tail seat (513) is provided with two positioning pin controls (514), and the tail pin shafts (59) inserted into the two positioning pin controls (514) are arranged in parallel, and the wing (57) and the torsion spring (58) are both sleeved on the outside of one of the tail pin shafts (59), and are in contact with the outer surface of the other tail pin shaft (59) and the wing (57).

9. The tail fin stabilization device of a jamming bomb according to claim 8, characterized in that: The wing (57) is a non-metallic sheet-shaped component.

10. A jamming bomb, characterized in that: The jamming bomb comprises a tail stabilization device of a jamming bomb as claimed in any one of claims 1 to 9, wherein the jamming bomb further comprises a smoke warhead (3), the tail of the smoke warhead (3) is installed with the tail of the jamming bomb, a projectile charge (4) is installed at the connection between the smoke warhead (3) and the tail of the jamming bomb, a waterproof cap (2) for sealing is installed at the front end of the smoke warhead (3), a pull ring (1) is installed at the front end of the waterproof cap (2), the projectile charge (4) is installed in a medicine box (52), and the projectile charge (4) is in contact with a delayed ignition tube (54), and the axes of the waterproof cap (2), the smoke warhead (3) and the tail of the jamming bomb coincide with each other.

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