Composite material front cover of missile launch canister
By using composite materials, the front cover of the missile launcher is combined with the cross-weaking groove, annularweaking groove and spring steel sheet structure, the problem of front cover crushing during missile launch is solved, and the purpose of safety flap separation, automatic rebound and environmental protection is achieved.
Patent Information
- Application Number
- CN202421890861.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-08-06
- Publication Date
- 2025-05-13
- Estimated Expiration
- 2034-08-06
AI Technical Summary
The front cover of the existing missile launcher is easily broken and crushed into pieces during the missile launch process, making it difficult to recover and pollute the environment.
The front cover of the missile launcher made of composite materials is equipped with cross-arranged cross-arranged cross-arranged annular weakening grooves on the outer surface. Combined with the spring steel sheet and the press ring structure, it ensures that the flap can be opened under the action of the missile tip and will automatically rebound and cover after the missile flies out.
It realizes safety splitting and automatic rebound of the front cover when missile is launched, avoiding splashing around the front cover, making it easy to recover, and has stable performance in extreme environments.
Smart Images
Figure CN222865738U_ABST
Abstract
Description
Technical Field
[0001] The utility model belongs to the field of aviation equipment manufacturing, and specifically relates to a composite material front cover of a missile launch tube. Background Art
[0002] With the continuous development of missile launch systems, more requirements have been put forward for missile launch devices. As an important part of the missile launch system, the front cover of the launch tube has been constantly updated in terms of structure and opening method. In order to meet the needs of modern warfare, more stringent requirements have been put forward in terms of functionality, volume, quality, environmental adaptability, etc., so that it is constantly developing in the direction of structural and functional integrated composite materials. At present, the front covers of missile launch tubes in service are mostly broken and shattered into fragments during the missile launch process, and splash around with the missile, which has problems such as difficult recovery and environmental pollution. Utility Model Content
[0003] The utility model aims to provide a composite front cover of a missile launch tube. By adopting this front cover, it is ensured that when the tube is stored horizontally, transported or in a vertical state, it can cooperate with the tube to form a closed environment so that the internal equipment is protected from the external environment, and the requirements of 10KPa tube internal sealing and 40KPa external pressure bearing are met; in the launching state, the cover is broken open under an impact force of ≯800kg, and under the action of the missile tip, it can be split along the preset cracks or grooves to make the missile fly away from the channel. After the missile flies out, it can be moored and rebound to cover the tube mouth, effectively avoiding splashing around the front cover, facilitating the recovery of the front cover, and achieving the purpose of environmental protection.
[0004] In order to realize the above technical features, the purpose of the utility model is achieved as follows: a composite front cover of a missile launch tube, comprising a front cover body, the outer surface of the front cover body is processed with cross weakening grooves arranged in a cross pattern; the periphery of the front cover body is processed with annular weakening grooves arranged in an annular pattern;
[0005] The front cover body is fixedly mounted on the front end of the cylinder body through a peripheral pressure ring;
[0006] A spring steel sheet is pre-buried inside the connection end where the front cover body matches the pressure ring. The spring steel sheet is evenly arranged in the circumferential direction at the middle part of the outer circumference of the four petals of the front cover body.
[0007] The front cover body adopts resin-based carbon fiber reinforced material as the main material.
[0008] The periphery of the front cover body is processed with cover body through holes arranged in a circumference, and the cover body through holes match with the pressing ring through holes on the pressing ring and match with the threaded holes at the front end of the cylinder body.
[0009] A top socket structure for positioning and guiding the missile warhead is arranged at the center of the inner surface of the front cover body.
[0010] The top nest structure is made of silicone material.
[0011] The spring steel sheet adopts an integrated structure, including an arc-shaped sheet for matching with the pressure ring, a matching hole is processed on the arc-shaped sheet, and the middle part of the inner arc of the arc-shaped sheet is connected to the transverse sheet through a connecting sheet.
[0012] The spring steel sheet is made of 65Mn plate.
[0013] The utility model has the following beneficial effects:
[0014] 1. By adopting the utility model, it is ensured that when the cylinder is stored or transported horizontally or in a vertical state, it can cooperate with the cylinder to form a closed environment so that the internal equipment is protected from the external environment, meeting the requirements of 10KPa cylinder internal sealing and 40KPa external pressure bearing; in the launching state, the cover is broken open under an impact force of ≯800kg, and under the action of the missile tip, it can be split along the preset cracks or grooves to make way for the missile to fly away, and the missile can be moored and rebound to cover the cylinder mouth after flying out.
[0015] 2. The utility model provides a composite material front cover of a missile launch tube, which can be split along a preset weakening groove or a groove under the action of the missile tip when the missile is launched, so as to allow the missile to fly away from the passage. After the missile is launched, it automatically rebounds and is reliably tied to the mouth of the launch tube, so as to be easy to recover.
[0016] 3. The spring steel sheet reserved inside the front cover body ensures that the front cover body can still be reliably connected to the front end of the cylinder after being broken by the petals, effectively preventing the cover body from splashing.
[0017] 4. The front cover of the missile launch tube uses resin-based carbon fiber reinforced material as the main material. This material has strong heat and corrosion resistance, stable performance under extreme environmental conditions, and can meet environmental adaptability requirements.
[0018] 5. The front cover of the missile launch tube has good corrosion resistance, high impact resistance and good fatigue resistance. BRIEF DESCRIPTION OF THE DRAWINGS
[0019] The utility model is further described below in conjunction with the accompanying drawings and embodiments.
[0020] Figure 1 This is a three-dimensional diagram of the utility model from the first perspective.
[0021] Figure 2 This is a three-dimensional diagram from the second viewing angle of the present invention.
[0022] Figure 3 This is a three-dimensional diagram of the front cover body of the utility model from the first perspective.
[0023] Figure 4This is a three-dimensional diagram of the front cover body of the utility model from the second viewing angle.
[0024] Figure 5 This is a three-dimensional diagram of the pressure ring of the utility model from the first perspective.
[0025] Figure 6 This is a three-dimensional diagram of the pressure ring of the utility model from the second viewing angle.
[0026] Figure 7 This is a three-dimensional diagram of the connection between the spring steel sheet and the pressure ring of the utility model from the first perspective.
[0027] Figure 8 This is a three-dimensional diagram from the second perspective of the connection between the spring steel sheet and the pressure ring of the utility model.
[0028] Fig. 9 This is a three-dimensional diagram of the spring steel sheet of the utility model.
[0029] In the figure: front cover body 1, pressing ring 2, pressing ring through hole 3, annular weakening groove 4, cross weakening groove 5, top socket structure 6, cover body through hole 7, spring steel sheet 8;
[0030] Horizontal piece 801 , connecting piece 802 , arc-shaped piece 803 , and matching hole 804 . DETAILED DESCRIPTION
[0031] The embodiments of the present utility model are further described below in conjunction with the accompanying drawings.
[0032] See also Figure 1-9 A composite front cover of a missile launch tube, comprising a front cover body 1, wherein the outer surface of the front cover body 1 is processed with cross weakening grooves 5 arranged in a cross pattern; the periphery of the front cover body 1 is processed with annular weakening grooves 4 arranged in an annular pattern; the front cover body 1 is fixedly mounted at the front end of the tube body through a peripheral pressure ring 2; a spring steel sheet 8 is pre-embedded inside the connecting end of the front cover body 1 and the pressure ring 2, and the spring steel sheet 8 is evenly arranged in the circumferential direction at the middle part of the outer circumference of the four petals of the front cover body 1. By arranging the cross weakening groove 5 and the annular weakening groove 4 on the front cover body 1, it is convenient for subsequent missiles to break through the front cover body 1 and form a petal structure, so that the missile can fly out from the center, and the spring steel sheet 8 inside it ensures that the petal structure will not scatter or splash, thereby ensuring safety and facilitating subsequent recovery.
[0033] Furthermore, the front cover body 1 is made of resin-based carbon fiber reinforced material as the main material. Through the above main material, combined with the cross weakening groove 5 and the annular weakening groove 4 on its outer surface, it is ensured that it can be divided into four petals under the action of external force, and then opened, which is convenient for the front cover body 1 to break through the petals and flip the petals.
[0034] Furthermore, the outer periphery of the front cover body 1 is processed with cover body through holes 7 arranged in a circumference, and the cover body through holes 7 match the pressing ring through holes 3 on the pressing ring 2 and match the threaded holes at the front end of the cylinder. Through the above-mentioned matching structure, it is ensured that the front cover body 1 can be reliably fixed and installed at the front end of the cylinder through the pressing ring 2.
[0035] Furthermore, a top socket structure 6 for positioning and guiding the missile warhead is provided at the center of the inner surface of the front cover body 1. The top socket structure 6 facilitates the positioning and guiding of the missile warhead.
[0036] Furthermore, the top socket structure 6 is made of a silicone material to prevent the missile from breaking through the front cover and scratching the surface of the missile body during the launch process.
[0037] Furthermore, the spring steel sheet 8 adopts an integrated structure, including an arc-shaped sheet 803 for matching with the pressure ring 2, a matching hole 804 is processed on the arc-shaped sheet 803, and the middle part of the inner arc of the arc-shaped sheet 803 is connected to the transverse sheet 801 through a connecting sheet 802. The spring steel sheet 8 ensures that after the front cover body 1 is torn, its four-petal structure can still be connected between the pressure plate and the cylinder, and can be automatically turned back to the cover later.
[0038] Furthermore, the spring steel sheet 8 is made of 65Mn plate. Made of the above materials, it is guaranteed to have a certain rebound effect.
[0039] Furthermore, the front cover body 1 is formed in one piece by a mold, and a special forming mold is designed. The carbon fiber prepreg is laid on the mold in layers to make a vacuum bag. The front cover body 1 uses USN15000 carbon fiber prepreg as the main material. According to the structure and stress characteristics of the cylinder, the composite layer structure of the front cover takes the length direction of the cylinder as the 0° direction, and pre-lays the carbon fiber prepreg on the surface of the mold body in the order of 0°, 90°, 45°, and -45°. After pre-laying, the subsequent processes such as pre-setting and hot pressing of embedded parts are carried out. It has high specific strength and high specific modulus, high strength, and the tensile strength in the 0-degree fiber direction can reach 2300MPa. It is light in weight and has a density of 1.8g / cm 3 It has the advantages of good corrosion resistance, high impact resistance and good fatigue resistance.
[0040] Working process and principle of this utility model:
[0041] First, the front cover body 1 is positioned at the front end of the cylinder, and the top socket structure 6 is ensured to be located inside the cylinder, thereby realizing the positioning of the missile warhead. Then, the front cover body 1 is fixed to the front end of the cylinder by bolts and a pressure ring 2. During the missile launching process, the front cover body 1 will be torn along the cross weakening groove 5 and the annular weakening groove 4 under the action of impact. At the same time, the missile will be protected by the top socket structure 6 during the launch process of breaking through the front cover to prevent scratches on the surface of the missile body.
Claims
1. A composite material front cover of a missile launch tube, characterized in that: It comprises a front cover body (1), the outer surface of the front cover body (1) being processed with cross weakening grooves (5) arranged in a cross pattern; the periphery of the front cover body (1) being processed with annular weakening grooves (4) arranged in annular pattern; The front cover body (1) is fixedly mounted on the front end of the cylinder body via a peripheral pressure ring (2); A spring steel sheet (8) is pre-buried inside the connection end where the front cover body (1) and the pressure ring (2) match, and the spring steel sheet (8) is evenly arranged in the circumferential direction at the middle part of the outer circumference of the four petals of the front cover body (1).
2. According to claim 1, a composite material front cover of a missile launch tube is characterized in that: The front cover body (1) uses a resin-based carbon fiber reinforced material as a main material.
3. According to claim 1, the composite material front cover of a missile launch tube is characterized in that: The outer periphery of the front cover body (1) is processed with cover body through holes (7) arranged in a circumferential manner, and the cover body through holes (7) cooperate with the pressure ring through holes (3) on the pressure ring (2) and match with the threaded holes at the front end of the cylinder.
4. The composite front cover of a missile launch tube according to claim 1, characterized in that: A top socket structure (6) for positioning and guiding the missile warhead is provided at the center of the inner surface of the front cover body (1).
5. The composite front cover of a missile launch tube according to claim 4, characterized in that: The top socket structure (6) is made of silicone material.
6. The composite front cover of a missile launch tube according to claim 1, characterized in that: The spring steel sheet (8) adopts an integrated structure, comprising an arc-shaped sheet (803) for matching with the pressure ring (2), a matching hole (804) being machined on the arc-shaped sheet (803), and a transverse sheet (801) being connected to the middle portion of the inner arc of the arc-shaped sheet (803) via a connecting sheet (802).
7. The composite front cover of a missile launch tube according to claim 6, characterized in that: The spring steel sheet (8) is made of 65Mn plate.