Missile shell machining method and missile shell thereof

Abstract

The invention provides a guided missile shell machining method and a guided missile shell thereof, and relates to the technical field of carrier rockets, the guided missile shell comprises a shell extending in the first direction, a heat insulation layer covers the inner surface of the shell and is bonded to the inner surface, an artificial debonding layer is arranged on the inner surface of the side, away from the shell, of the heat insulation layer, and an air channel is formed in an air guide strip; the gas path extends in the length direction of the gas guide strip, the gas guide strip is fixedly arranged between the artificial debonding layer and the heat insulation layer, and the gas guide strip and the artificial debonding layer both extend in the first direction. The air guide strip and the manual debonding layer are produced separately, production molds of the air guide strip and the manual debonding layer are simple, the mold opening period is short, the air guide strip is bonded to one side of the heat insulation layer in a bonding mode, the production technology is simplified, and the production period is shortened.

Description

Technical Field

[0001] The present application relates to the field of launch vehicles, and in particular to a missile casing processing method and a missile casing thereof. Background Art

[0002] As the comprehensive performance of missiles continues to improve, the overall requirements for the endurance and reliability of solid propulsion systems are becoming increasingly higher.

[0003] In order to avoid the uneven intake of the long manhole during the initial ignition of the end-burning high-burning-rate fully loaded solid engine, which causes the pressure difference at various places of the manhole seam, resulting in the manhole tearing, abnormal increase of the combustion surface, and even the engine piercing or explosion, different numbers of air guide grooves are usually set in the long manhole seam to quickly balance the pressure inside and outside the manhole seam. In the prior art, the air guide strip and the artificial debonding layer are connected in one piece, and the step of integrally molding the air guide strip on the artificial debonding layer is complex in processing technology and has a long production cycle. Summary of the invention

[0004] The purpose of this application is to provide a missile casing processing method and a missile casing thereof in order to simplify the missile casing processing technology and shorten the production cycle in view of the above problems.

[0005] In one aspect, the present application provides a missile casing, comprising: an outer shell, the outer shell extending along a first direction; a heat-insulating layer, the heat-insulating layer covering the inner surface of the outer shell and bonded to the inner surface; An artificial debonding layer, the artificial debonding layer being arranged on an inner surface of a side of the thermal insulation layer away from the outer shell; An air guide strip is provided with an air path, and the air path extends along the length direction of the air guide strip; the air guide strip is fixedly arranged between the artificial debonding layer and the thermal insulation layer, and both the air guide strip and the artificial debonding layer extend along the first direction.

[0006] According to the technical solution provided in certain embodiments of the present application, the artificial debonding layer includes a bonding portion and a mounting portion sequentially arranged along a first direction, the bonding portion is bonded to the thermal insulation layer, the mounting portion is separately arranged from the thermal insulation layer and an mounting space is provided therebetween, and the air guide strip is fixed inside the mounting space.

[0007] According to the technical solution provided in certain embodiments of the present application, the air guide strip is provided with a through groove along its length direction, and the cross-section of the air guide strip is C-shaped; one side of the opening of the through groove on the air guide strip abuts against the artificial debonding layer to form the air path, and the other side of the air guide strip is bonded and fixed to the insulation layer.

[0008] According to the technical solutions provided in some embodiments of the present application, the number of the air guide strips is at least two, and the air guide strips are arranged at intervals around the central axis of the shell.

[0009] According to the technical solutions provided in some embodiments of the present application, the air guide strip is provided with side holes; The side hole penetrates the air guide strip in the width direction of the air guide strip, and the side hole is communicated with the air path in the length direction of the air guide strip.

[0010] According to the technical solutions provided in certain embodiments of the present application, each of the air guide strips is provided with at least two side holes, and the side holes are arranged in sequence along the length direction of the air guide strip.

[0011] According to the technical solutions provided in some embodiments of the present application, the number of the upper side holes of each of the air guide strips is the same, and they are arranged relatively to each other in the width direction of the air guide strip.

[0012] On the other hand, the present application also provides a missile casing processing method for producing the above-mentioned missile casing, comprising: S1, produce the outer shell, thermal insulation layer, air guide strip and artificial debonding layer respectively; S2, cutting the air guide strip, and bonding the side surface of the cut air guide strip away from the through groove opening to the side surface of the insulation layer; S3, bonding the bonding portion of the artificial debonding layer to the thermal insulation layer, and abutting the mounting portion of the artificial debonding layer to the through-slot opening of the air guide strip; S4, bonding the other side surface of the thermal insulation layer to the inner surface of the shell.

[0013] According to the technical solutions provided in some embodiments of the present application, cutting the air guide strip includes: Determining a position on the thermal insulation layer corresponding to a boundary line between the bonding portion and the mounting portion; The air guide strip is cut according to the position and the distance between the edge of the mounting portion away from the bonding portion and the boundary line.

[0014] According to the technical solution provided in some embodiments of the present application, S1, producing the outer shell, the heat insulation layer, the air guide strip and the artificial debonding layer respectively includes: Processing a C-shaped through groove along the length direction of a long strip of gas guide strip blank on one surface thereof; A side hole is processed through the air guide strip in a width direction of the air guide strip.

[0015] In summary, the technical scheme specifically discloses a method for processing a missile shell and a missile shell thereof, wherein the missile shell includes an outer shell extending in a first direction, an insulating layer covers the inner surface of the outer shell and is bonded to the inner surface, an artificial debonding layer is arranged on the inner surface of the insulating layer away from the outer shell, an air path is provided on the air guide strip, and the air path extends along the length direction of the air guide strip; the air guide strip is fixedly arranged between the artificial debonding layer and the insulating layer, and both the air guide strip and the artificial debonding layer extend in the first direction. By producing the air guide strip and the artificial debonding layer separately, the production molds of the two are simple and the mold opening cycle is short; the air guide strip is bonded to one side of the insulating layer by bonding, which simplifies the production process and effectively shortens the production cycle.

[0016] It should be understood that the description of technical features, technical solutions, beneficial effects or similar language in this application does not imply that all features and advantages can be realized in any single embodiment. On the contrary, it is understood that the description of features or beneficial effects means that specific technical features, technical solutions or beneficial effects are included in at least one embodiment. Therefore, the description of technical features, technical solutions or beneficial effects in this specification does not necessarily refer to the same embodiment. Furthermore, the technical features, technical solutions and beneficial effects described in the present embodiment can also be combined in any appropriate manner. Those skilled in the art will understand that the embodiment can be realized without one or more specific technical features, technical solutions or beneficial effects of a specific embodiment. In other embodiments, additional technical features and beneficial effects can also be identified in a specific embodiment that does not embody all embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0018] Figure 1 A cross-sectional view of a transverse section of a missile casing provided in an embodiment of the present application; Figure 2 for Figure 1 A local enlarged schematic diagram of the middle A; Figure 3 A partial cross-sectional view of a radial cross section of a missile casing provided in an embodiment of the present application; Figure 4 A flowchart of a missile casing processing method provided in an embodiment of the present application.

[0019] The text labels shown in the figure represent: 1. Shell; 2. Insulation layer; 3. Artificial debonding layer; 4. Air guide strip; 41. Air path; 42. Side hole. DETAILED DESCRIPTION

[0020] In order to enable those skilled in the art to better understand the technical solution of the present application, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the accompanying drawings. The description in this section is only exemplary and explanatory and should not have any limiting effect on the protection scope of the present application. Specifically, the described embodiments are only embodiments of a part of the present application, not all embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without creative work should fall within the scope of protection of the present invention.

[0021] It should be noted that similar reference numerals and letters represent similar items in the following figures, so once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures. In addition, the terms "including" and "having" and any variations thereof are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device that includes a series of steps or units is not necessarily limited to those steps or units clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0022] As mentioned in the background technology, in view of the problems in the prior art, this embodiment provides a missile casing, including: A housing 1 extending along a first direction; Specifically, the shell 1 is a cylindrical sleeve with a hollow interior, extending along a first direction, and the interior of the shell is used for pouring slurry to form a drug column after solidification; the first direction is the axial direction of the shell 1.

[0023] A heat-insulating layer 2, the heat-insulating layer 2 covers the inner surface of the outer shell 1 and is bonded to the inner surface; Specifically, Figure 1 As shown, the insulation layer 2 covers the inner surface of the outer shell 1. Preferably, the insulation layer 2 is glued and fixed to the inner wall surface of the outer shell 1. The outer wall of the insulation layer 2 and the inner wall of the outer shell 1 may be fixed in other ways, which can be set and adjusted according to actual conditions and are not specifically limited here.

[0024] An artificial debonding layer 3, wherein the artificial debonding layer 3 is arranged on an inner surface of the thermal insulation layer 2 away from the outer shell 1; Specifically, the artificial debonding layer 3 covers the inner surface of the insulation layer 2 away from the outer shell 1 and is partially bonded to the insulation layer 2. The portion where the artificial debonding layer 3 is not bonded to the insulation layer 2 forms an installation space for installing the air guide strip 4 with the insulation layer 2.

[0025] An air guide strip 4 is provided with an air path 41, and the air path 41 extends along the length direction of the air guide strip 4; the air guide strip 4 is fixedly arranged between the artificial debonding layer 3 and the insulation layer 2, and the air guide strip 4 and the artificial debonding layer 3 both extend along the first direction.

[0026] Specifically, Figure 2 As shown, the air guide strip 4 is evenly distributed around the axis of the shell 1, and an air path 41 is extended along the length direction of the air guide strip 4. The air guide strip 4 is used to increase the gap between the heat insulating layer 2 and the artificial debonding layer 3. When the engine is ignited, the gas can smoothly enter and quickly fill the debonding gap, so that the pressure distribution of the debonding gap is uniform. The air guide strip 4 is fixedly installed in the installation space, and the side of the air guide strip 4 close to the heat insulating layer 2 is fixedly connected to the heat insulating layer 2 by gluing, and the side of the air guide strip 4 away from the heat insulating layer 2 is in contact with the artificial debonding layer 3, and the air guide strip 4 and the artificial debonding layer 3 both extend along the first direction.

[0027] The present application provides a missile shell, comprising an outer shell extending along a first direction, a heat-insulating layer covering the inner surface of the outer shell and bonded to the inner surface of the outer shell, an artificial debonding layer arranged on the inner surface of the heat-insulating layer away from the outer shell, an air path provided on an air guide strip, and the air path extending along the length direction of the air guide strip; the air guide strip is fixedly arranged between the artificial debonding layer and the heat-insulating layer, and both the air guide strip and the artificial debonding layer extend along the first direction, and by producing the air guide strip and the artificial debonding layer separately, the production molds of the two are simple and the mold opening cycle is short; the air guide strip is bonded to one side of the heat-insulating layer by bonding, which simplifies the production process and effectively shortens the production cycle.

[0028] In a preferred embodiment, the artificial debonding layer 3 includes a bonding portion and a mounting portion sequentially arranged along a first direction, the bonding portion is bonded to the insulation layer 2, the mounting portion is separately arranged from the insulation layer 2 and there is an installation space between the two, and the air guide strip 4 is fixed inside the installation space.

[0029] Specifically, Figure 3As shown, the artificial debonding layer 3 includes a bonding portion and a mounting portion sequentially arranged along a first direction, there is a dividing line between the bonding portion and the mounting portion, the side of the dividing line close to the missile warhead is the bonding portion, the bonding portion and the thermal insulation layer 2 are bonded by adhesive, the side of the dividing line close to the missile tail is the mounting portion, the mounting portion and the thermal insulation layer 2 are separated and there is an installation space between the two, the side of the gas guide strip 4 away from the outer shell 1 in the installation space is in contact with the artificial debonding layer 3, and the side of the gas guide strip 4 close to the outer shell 1 in the installation space is bonded to the thermal insulation layer 2 by adhesive.

[0030] In a preferred embodiment, the air guide strip 4 has a through groove along its length direction, and the cross-section of the air guide strip 4 is C-shaped; one side of the opening of the through groove on the air guide strip 4 abuts against the artificial debonding layer 3 to form the air path 41, and the other side of the air guide strip 4 is bonded and fixed to the insulation layer 2.

[0031] Specifically, Figure 2 As shown, the gas guide strip 4 is a prism, and a through groove is provided along the extension direction of the gas guide strip 4, the extension direction of the gas guide strip 4 is the length direction of the gas guide strip 4, and the cross section of the gas guide strip 4 is C-shaped; the side of the gas guide strip 4 having the through groove opening is in contact with the artificial debonding layer 3, and the artificial debonding layer 3 covers the through groove opening so that the through groove and the artificial debonding layer 3 form a gas path 41, and the gas path 41 is used to transport the gas; wherein, the shape of the cross section of the gas path 41 may also be of other types, and the shape of the through groove may be set and adjusted according to actual conditions, and is not specifically limited here.

[0032] In a preferred embodiment, the number of the air guide strips 4 is at least two, and the air guide strips 4 are arranged at intervals around the central axis of the housing 1 .

[0033] Specifically, Figure 1 As shown, the number of the air guide strips 4 is at least two; the specific number can be set and adjusted according to actual conditions and is not specifically limited here. The air guide strips 4 are evenly spaced and arranged on the outer wall of the artificial debonding layer 3 around the central axis of the shell 1.

[0034] In a preferred embodiment, the air guide strip 4 is provided with a side hole 42; The side hole 42 penetrates the air guide strip 4 in the width direction of the air guide strip 4 , and the side hole 42 is communicated with the air path 41 in the length direction of the air guide strip 4 .

[0035] Specifically, the side hole 42 passes through the gas guide strip 4, and the side hole 42 is provided on the first side wall and the second side wall perpendicular to the insulation layer 2, the distribution direction of the two side walls is the width direction of the gas guide strip 4, the side hole 42 passes through the gas guide strip 4, and the side hole 42 is interconnected with the gas path 41 on the length direction of the gas guide strip 4, so that the installation space is interconnected with the gas path 41 through the two side holes 42. When the engine is ignited, the gas can enter smoothly and quickly fill the gas gap, so that the pressure of the gas gap is evenly distributed, avoiding abnormal increase of the combustion surface due to gas gap tearing.

[0036] In a preferred embodiment, each of the air guide strips 4 is provided with at least two side holes 42 , and the side holes 42 are sequentially arranged along the length direction of the air guide strip 4 .

[0037] Specifically, there are at least two side holes 42 that penetrate the first side wall and the second side wall, and the specific number can be set and adjusted according to actual conditions, and is not specifically limited here. The side holes 42 are uniformly arranged in sequence along the length direction of the gas guide strip 4, so that the side holes 42 are evenly distributed in the coverage area of ​​the artificial debonding layer 3, ensuring the fluidity of the gas between the artificial debonding layer 3 and the insulation layer 2.

[0038] In a preferred embodiment, the number of the side holes 42 on each of the air guide strips 4 is the same, and the holes 42 are arranged opposite to each other in the width direction of the air guide strips 4 .

[0039] Specifically, the number of the side holes 42 on each of the gas guide strips 4 is the same, and they are relatively arranged in the width direction of the gas guide strips 4, so that the gas output from the side holes 42 of adjacent gas guide strips 4 can flow into the installation space after convection, thereby improving the efficiency of the side holes 42 in balancing and regulating the pressure of different blocks between the artificial debonding layer 3 and the insulation layer 2.

[0040] like Figure 4 As shown, the present application also provides a missile casing processing method for producing the missile casing in the above embodiments, comprising: S1, respectively produce the outer shell 1, the heat insulation layer 2, the air guide strip 4 and the artificial debonding layer 3; The shell 1, the heat insulating layer 2, the air guide strip 4 and the artificial debonding layer 3 are produced and processed respectively, and in the process of processing the air guide strip 4, a C-shaped through groove is processed on one surface of the long strip of the air guide strip 4 blank along its length direction, and a side hole 42 penetrating the air guide strip 4 is processed in the width direction of the air guide strip 4 blank; S2, cutting the air guide strip 4, and bonding the side surface of the cut air guide strip 4 away from the through groove opening to the side surface of the insulation layer 2; Determine the position of the dividing line between the bonding portion and the mounting portion on the thermal insulation layer 2, cut the air guide strip 4 according to the position and the distance from the edge of the mounting portion away from the dividing line to the dividing line until the air guide strip 4 meets the requirements of the mounting portion in the length direction, and bond the side surface of the cut air guide strip 4 away from the through-slot opening to the side surface of the thermal insulation layer 2 close to the artificial debonding layer 3; Among them, Figure 3 As shown, point B is a point on the dividing line. In the actual processing process, there is a bonding boundary between the mounting portion and the bonding portion at the dividing line B. During production, the dividing line is moved 0-100 mm toward the missile tail. Similarly, the length of the gas guide strip 4 is 0-100 mm shorter than the distance from the dividing line to the missile tail. S3, bonding the bonding portion of the artificial debonding layer 3 to the thermal insulation layer 2, and abutting the mounting portion of the artificial debonding layer 3 to the through-slot opening of the air guide strip 4; Bond the bonding portion of the artificial debonding layer 3 to the surface of the heat insulating layer 2 on the side where the air guide strip 4 is bonded, and abut the mounting portion of the artificial debonding layer 3 against the side of the air guide strip 4 having the through groove opening; S4, bonding the other side surface of the thermal insulation layer 2 to the inner surface of the shell 1.

[0041] The present application provides a method for processing a missile shell, which separately produces an outer shell, an insulation layer, an air guide strip and an artificial debonding layer, cuts the air guide strip, and bonds the side surface of the cut air guide strip away from the through-slot opening to the side surface of the insulation layer, bonds the bonding portion of the artificial debonding layer to the insulation layer, abuts the mounting portion of the artificial debonding layer against the through-slot opening of the air guide strip, and bonds the other side surface of the insulation layer to the inner surface of the outer shell; by producing the air guide strip and the artificial debonding layer separately, the production molds of the two are simple and the mold opening cycle is short; by bonding the air guide strip to one side of the insulation layer by bonding, the production process is simplified and the production cycle is effectively shortened.

[0042] This article uses specific examples to illustrate the principles and implementation methods of this application. The description of the above embodiments is only used to help understand the method and its core ideas of this application. The above is only the preferred implementation method of this application. It should be pointed out that due to the limitations of textual expression and the objective existence of infinite specific structures, ordinary technicians in this technical field can make several improvements, modifications or changes without departing from the principles of the present invention, and can also combine the above technical features in an appropriate manner; these improvements, modifications, changes or combinations, or the direct application of the inventive concept and technical solution to other occasions without improvement, should be regarded as the scope of protection of this application.

Claims

1. A missile casing, characterized in that: include: A housing (1), wherein the housing (1) extends along a first direction; A heat insulating layer (2), the heat insulating layer (2) covers the inner surface of the outer shell (1) and is bonded to the inner surface; An artificial debonding layer (3), the artificial debonding layer (3) being arranged on an inner surface of a side of the thermal insulation layer (2) away from the outer shell (1); An air guide strip (4), wherein an air path (41) is provided on the air guide strip (4), and the air path (41) extends along the length direction of the air guide strip (4); the air guide strip (4) is fixedly arranged between the artificial debonding layer (3) and the thermal insulation layer (2), and the air guide strip (4) and the artificial debonding layer (3) both extend along the first direction.

2. A missile casing according to claim 1, characterized in that: The artificial debonding layer (3) comprises a bonding portion and a mounting portion sequentially arranged along a first direction, the bonding portion is bonded to the thermal insulation layer (2), the mounting portion is separately arranged from the thermal insulation layer (2) and a mounting space is provided between the two, and the air guide strip (4) is fixed inside the mounting space.

3. A missile casing according to claim 1, characterized in that: The air guide strip (4) is provided with a through groove along its length direction, and the cross section of the air guide strip (4) is C-shaped; one side of the opening of the through groove on the air guide strip (4) abuts against the artificial debonding layer (3) to form the air path (41), and the other side of the air guide strip (4) is bonded and fixed to the thermal insulation layer (2).

4. A missile casing according to claim 1, characterized in that: The number of the air guide strips (4) is at least two, and the air guide strips (4) are arranged at intervals around the central axis of the outer shell (1).

5. A missile casing according to claim 4, characterized in that: The air guide strip (4) is provided with a side hole (42); The side hole (42) penetrates the air guide strip (4) in the width direction of the air guide strip (4), and the side hole (42) is connected to the air path (41) in the length direction of the air guide strip (4).

6. A missile casing according to claim 5, characterized in that: Each of the air guide strips (4) is provided with at least two of the side holes (42), and the side holes (42) are arranged in sequence along the length direction of the air guide strip (4).

7. A missile casing according to claim 6, characterized in that: The number of the upper side holes (42) of each of the air guide strips (4) is the same, and they are arranged opposite to each other in the width direction of the air guide strips (4).

8. A method for processing a missile casing, used to produce the missile casing as claimed in any one of claims 1 to 7, characterized in that: include: S1, respectively producing an outer shell (1), a heat insulating layer (2), an air guide strip (4) and an artificial debonding layer (3); S2, cutting the air guide strip (4), and bonding a side surface of the cut air guide strip (4) away from the through groove opening to a side surface of the heat insulation layer (2); S3, bonding the bonding portion of the artificial debonding layer (3) to the thermal insulation layer (2), and abutting the mounting portion of the artificial debonding layer (3) to the through-slot opening of the air guide strip (4); S4, bonding the other side surface of the thermal insulation layer (2) to the inner surface of the outer shell (1).

9. A missile casing processing method according to claim 8, characterized in that: Cutting the air guide strip (4) comprises: Determining the position of the boundary line between the bonding portion and the mounting portion on the thermal insulation layer (2); The air guide strip (4) is cut according to the position and the distance between the edge of the mounting portion away from the bonding portion and the dividing line.

10. A missile casing processing method according to claim 9, characterized in that: S1. The outer shell (1), the heat insulating layer (2), the air guide strip (4) and the artificial debonding layer (3) are produced separately, including: Processing a C-shaped through groove on one surface of a long strip of gas guide strip blank along its length direction; A side hole (42) is machined through the air guide strip (4) in the width direction of the air guide strip (4).

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