An integrated aircraft warhead structure

Abstract

This utility model discloses an integrated aircraft warhead structure, including a shell and a support frame. The shell has a spherical section at the front end and a conical section at the rear end, which are integrally formed. The support frame supports the conical section at the rear end of the shell and includes multiple support rings and multiple support rods in the shape of a frustum. The lower part of the support frame has a retaining ring concentric with the support rings, and the retaining ring has a locking slot. The retaining ring and the support ring are connected by a connecting rod to optimize the support structure. The spherical structure at the front end ensures strength by utilizing the spherical shape itself and will not deform. The conical section at the rear end forms a skeleton structure through the support rings and support rods, providing effective support strength. An ablation-resistant material is selected because, on the one hand, the ablation-resistant material has sufficient high-temperature resistance to meet the requirements of the application scenario, and on the other hand, the ablation-resistant material can also be used to process large-sized workpieces.

Description

Technical Field

[0001] This utility model relates to the field of aircraft warhead technology, specifically an integrated aircraft warhead structure. Background Technology

[0002] Hypersonic aircraft generally refer to aircraft with flight speeds exceeding Mach 5. During high-speed flight, the surface of the warhead generates a large amount of heat due to friction with the air. As the speed increases, the surface temperature of the warhead can reach as high as 1500 degrees Celsius. This requires the warhead to be made of specific materials. At present, ceramic matrix composites (CMC) are mainly used to meet the high-temperature resistance requirements. However, in actual operation, due to the limitations of the manufacturing process and the inherent characteristics of the materials, larger CMCs are prone to cracking and deformation due to uneven shrinkage during sintering. Therefore, only smaller patches can be manufactured for assembly. However, the assembled warhead cannot achieve zero gaps in its structure. These gaps cause significant wind resistance during warhead flight, resulting in excessively high local temperatures. Therefore, a warhead structure that can be molded in one piece is needed. However, the support structure of the one-piece molded warhead still needs optimization and adjustment to ensure that it will not deform due to insufficient strength during use. Utility Model Content

[0003] (I) Technical Solution

[0004] To solve the above-mentioned technical problems, this utility model provides an integrated aircraft warhead structure.

[0005] The specific technical solution is as follows:

[0006] An integrated aircraft warhead structure includes a shell and a support frame. The shell has a spherical section at its front end and a conical section at its rear end, which are integrally formed. The support frame supports the conical section at the rear end of the shell. The support frame includes multiple support rings and multiple support rods. The multiple support rings are concentrically arranged with gradually decreasing diameters and are fixedly connected by the multiple support rods to form a frustum shape, which corresponds to the shape of the inner wall of the conical section of the shell. Each support ring has an arc-shaped groove at its bottom offset from the support rod. The support rod includes an arc-shaped protrusion and an arc-shaped support portion, and the cross-section of the support rod is convex. The lower part of the support frame has a retaining ring concentric with the support ring, and the retaining ring has a locking slot. The retaining ring is connected to the support ring by a connecting rod.

[0007] Furthermore, the housing is equipped with a cold source for cooling the outer surface of the housing and a driving device for converting the cold source into high-pressure gas and sending it to the outer surface of the housing. The housing has a hole at the head end, and the cold source is pushed out of the hole at the head end of the housing by the driving device. The housing is made of ablation-resistant material.

[0008] Furthermore, there are four support rings and four support rods, and the four support rods are set at equal angles. There are also four baffles between the support frame and the housing. The thickness of the baffles is the same as the thickness of the protrusions. The four baffles and the protrusions of the four support rods form a frustum side surface, which is the same as the inner wall of the conical section of the housing. The baffles are riveted to the support rings and the support rods. The protrusions are provided with bolt holes. The conical section of the housing is bolted to the support rods.

[0009] Furthermore, the support frame is an integral structure made of aluminum alloy, and the baffle is also made of aluminum alloy.

[0010] (ii) Beneficial effects

[0011] Compared with the prior art, the technical solution proposed in this utility model has the following advantages: the optimized support structure, with a spherical head end that utilizes the inherent strength of the sphere to ensure strength and prevent deformation, and a tapered rear end forming a skeleton structure through a support ring and a support rod to provide effective support strength. The support ring is grooved, which facilitates riveting and effectively reduces weight. Furthermore, the addition of a cold source and drive mechanism that can form a film cooling system reduces the temperature of the warhead surface during flight. This allows for a wider selection of raw materials for the integrated warhead structure. In this utility model, an ablation-resistant material is selected because it possesses sufficient high-temperature resistance to meet the requirements of the application scenario, and it also enables the processing of large-sized workpieces. Attached Figure Description

[0012] To more clearly illustrate the technical solutions in the embodiments of this utility model, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0013] Figure 1 This is a schematic diagram of the structure of this utility model;

[0014] Figure 2 This is a schematic diagram of the assembly of the support frame and the baffle.

[0015] Figure 3 Exploded view of the support frame and baffle;

[0016] Figure 4 This is a schematic diagram of the drive device structure. Detailed Implementation

[0017] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. The described embodiments are only some embodiments of the utility model, not all embodiments. Based on the embodiments of the utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the utility model.

[0018] To address the problems existing in the relevant prior art, this utility model proposes an integrated aircraft warhead structure. The principle and structure of this utility model will be described in detail below with reference to the accompanying drawings and embodiments.

[0019] An integrated aircraft warhead structure includes a shell 1 and a support frame 2. The shell 1 has a spherical section at its front end and a conical section at its rear end, which are integrally formed. The support frame 2 corresponds to the conical section of the shell 1 and supports the conical section at its rear end. The front end utilizes the spherical structure and the inherent strength of the material to ensure strength, while the conical section is supported by the support frame 2. The support frame 2 includes multiple support rings 2a and multiple support rods 2b. The multiple support rings 2a are concentrically arranged with gradually decreasing diameters and are fixedly connected by multiple support rods 2b. The outer contour of the support frame 2 is generally shaped like a frustum, and this frustum shape corresponds to the shape of the inner wall of the conical section of the shell 1. Each support ring 2a has an arc-shaped groove at the misalignment position between its bottom and the support rod 2b. On the one hand, the arc-shaped groove can effectively reduce the overall weight of the support frame 2; on the other hand, the connection position between the support ring 2a and the support rod 2b and the arc-shaped groove... The misalignment also ensures the strength of the connection between the support ring 2a and the support rod 2b, avoiding damage to the strength of the support frame 2 due to weight reduction. The support rod 2b includes an arc-shaped protrusion 2c and an arc-shaped support 2d. The cross-section of the support rod 2b is convex. The lower part of the support frame 2 is provided with a retaining ring 2e concentric with the support ring 2a. The retaining ring 2e is provided with a locking slot 2f. The retaining ring 2e is connected to the support ring 2a through a connecting rod 2g. The retaining ring is used for positioning, which facilitates the docking and positioning of the warhead with the rear end of the aircraft. The retaining ring 2e, the locking slot 2f, and the connecting rod 2g are integrated with the support ring 2a, which can also provide some support for the support ring 2a and improve its strength. In the above structure, the spherical structure at the head end and the strength of the material itself ensure strength and prevent deformation. The tapered part at the rear end forms a skeleton structure through the support ring and the support rod, providing effective support strength.

[0020] The casing 1 contains a cold source for cooling the outer surface of the casing 1 and a drive device 3 for converting the cold source into high-pressure gas and delivering it to the outer surface of the casing 1. The casing 1 has a hole (not shown in the figure) at its head end. The cold source is propelled out of the hole at the head end of the casing 1 by the drive device 3. The casing is made of an ablation-resistant material. In this design, the drive device vaporizes the cold source and ejects the vaporized cold source from the hole, forming a gas film on the surface of the projectile. This gas film effectively insulates against temperature, reducing the surface temperature by 500–1000 degrees Celsius. This also allows the selected ablation-resistant material to be used effectively. To meet the requirements of high temperature resistance, ablation-resistant materials are solid heat-resistant materials. Under the action of heat flow, these materials can undergo physical and chemical changes such as decomposition, melting, evaporation, sublimation, and erosion. By consuming a large amount of heat through the mass of the material surface, a large amount of heat can be carried away, thereby achieving the purpose of temperature insulation. Generally, when the speed reaches Mach 5, the surface temperature of the warhead can reach up to 2000 degrees Celsius. However, by using gas film cooling in conjunction with ablation-resistant materials, the internal temperature of the warhead can be kept below 150 degrees Celsius. At this temperature, it can ensure that all components inside the warhead can work normally, and the frame as a whole can also work normally. The specific cold source and driving device are existing technologies. For details, please refer to the description of the cold source and cold source driving device in patent number CN104608942B. The following is an example: The cold source is liquid nitrogen. The driving device 3 specifically includes an air pump 3a, a storage device 3b, and a buffer 3c. Liquid nitrogen is filled in the storage device 3b. The air pump 3a is connected to the storage device, and the storage device 3b is connected to the buffer 3c. The other end of the buffer is connected to the hole at the head end of the housing 1. In actual use, the air pump 3a pumps compressed air into the storage device 3b, pressurizes the liquid nitrogen in the storage device 3b, and delivers it to the buffer 3c. The liquid nitrogen is vaporized by the buffer 3c. The vaporized nitrogen gas is ejected from the hole at the head end of the housing 1 through a pipeline. There are multiple holes, which are evenly distributed on the spherical surface at the head end of the housing 1. In this way, a uniform gas film can be formed at the head end of the housing 1, which plays a role in cooling the surface of the housing.

[0021] There are four support rings and four support rods. The four support rings are evenly spaced, with a 1-meter distance between adjacent support rings. The four support rods are set at equal angles to ensure uniform strength at all positions. Four baffles 4 are also provided between the support frame 2 and the shell 1. The thickness of the baffles 4 is the same as the thickness of the protrusions. The outer side of the baffles 4 is curved, and the protrusions 2c are also curved. Thus, the four baffles and the protrusions of the four support rods form a frustum side, which is the same as the inner wall of the conical section of the shell 1. When the shell 1 is fixed to the support frame 2, it can be tightly secured. The close contact without gaps ensures effective support. Specifically, the baffle 4 is riveted to the support ring 2a and the support rod 2b. The riveting position of each baffle 4 corresponds to the arc-shaped groove of the support part 2d and the four support rings 2a. The groove position also facilitates riveting. At the same time, the protrusion 2c is provided with bolt holes. The tapered section of the shell 1 is bolted to the support rod 2b. The bolts used are ceramic high-temperature resistant bolts. Furthermore, the support frame 2 is an integral structure made of aluminum alloy. The baffle 4 is also made of aluminum alloy, thus ensuring uniform support strength.

[0022] The above are merely preferred embodiments of this utility model and are not intended to limit the scope of this utility model. Various modifications and variations can be made to this utility model by those skilled in the art. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. An integrated aircraft warhead structure, characterized in that: The device includes a shell and a support frame. The shell has a spherical section at the front end and a conical section at the rear end, which are integrally formed. The support frame supports the conical section at the rear end of the shell. The support frame includes multiple support rings and multiple support rods. The multiple support rings are concentrically arranged with gradually decreasing diameters and are fixedly connected by the multiple support rods to form a frustum shape. The shape of the frustum corresponds to the inner wall shape of the conical section of the shell. Each support ring has an arc-shaped groove at its bottom offset from the support rod. The support rod includes an arc-shaped protrusion and an arc-shaped support portion. The cross-section of the support rod is convex. The lower part of the support frame has a retaining ring concentric with the support rings. The retaining ring has a locking slot and is connected to the support rings by a connecting rod.

2. The integrated aircraft warhead structure according to claim 1, characterized in that: The housing is equipped with a cold source for cooling the outer surface of the housing and a driving device for converting the cold source into high-pressure gas and sending it to the outer surface of the housing. The housing has a hole at the head end, and the cold source is pushed out of the hole at the head end of the housing by the driving device. The housing is made of ablation-resistant material.

3. The integrated aircraft warhead structure according to claim 2, characterized in that: The number of support rings and support rods is four, and the four support rods are set at equal angles. Four baffles are also provided between the support frame and the housing. The thickness of the baffles is the same as the thickness of the protrusions. The four baffles and the protrusions of the four support rods form a frustum side surface, which is the same as the inner wall of the conical section of the housing. The baffles are riveted to the support rings and support rods. The protrusions are provided with bolt holes. The conical section of the housing is bolted to the support rods.

4. The integrated aircraft warhead structure according to claim 3, characterized in that: The support frame is an integral structure made of aluminum alloy, and the baffle is also made of aluminum alloy.

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