Composite material propulsion landing rocket leg forming mold

Abstract

The utility model relates to composite material mould forming technical field especially relates to a kind of composite material propelling landing rocket supporting leg forming mould, including bottom frame, main body glass steel template, epoxy movable block and template adjusting assembly.The utility model realizes the welding of bottom frame by square tube frame structure, the structure welding deformation is smaller, combined with the stability of triangular reinforcing rib structure, ventilation is carried out in the contact hollow area of bottom frame and main body glass steel template, so that the mould is evenly heated in the hot-pressing tank working state, save cost and shorten manufacturing cycle;By using the main body glass steel template with uniform thickness, auxiliary heat conduction is used, the glass steel template is turned over by using transition mould, and the transition mould is machined by using numerical control machining center to ensure the turning-over precision, meet the product forming requirements;Epoxy movable block is used to assist the smooth demoulding of product, and positioning pin is used for insertion limiting, which meets the positioning requirements and realizes locking function, improves overall stability.

Description

Technical Field

[0001] This utility model relates to the field of composite material mold forming technology, and in particular to a composite material propulsion and landing rocket leg forming mold. Background Technology

[0002] The landing legs of a rocket primarily function in the rocket's recovery phase, especially during the first stage's reentry into the atmosphere and successful landing. The landing legs must withstand exceptionally complex and variable force and thermal environments. The rocket's return process involves coordination among multiple disciplines, including overall design, ballistics, aerodynamics, control, load management, thermal protection, and structure. From the initial research and design stages, high standards and strict requirements were considered regarding the coupling between these disciplines. The landing legs need to overcome various internal and external interferences arising from the complex flight environment of excessive weight and high power, thus posing new challenges to the rocket's molding process.

[0003] Meanwhile, existing molding dies are usually expensive and cannot guarantee the aerodynamic profile accuracy requirements of rocket legs, which will also reduce product molding quality and extend the manufacturing cycle of individual products. Summary of the Invention

[0004] To overcome the problems of existing molding dies being typically expensive, unable to guarantee the aerodynamic profile accuracy requirements of rocket legs, and also reducing product molding quality and extending the manufacturing cycle of individual products, this utility model provides a molding die for composite material propulsion and landing rocket legs.

[0005] The technical solution is as follows: A composite material propulsion landing rocket leg forming mold includes a bottom frame, a main fiberglass profile, epoxy movable blocks, and a profile adjustment assembly; the main fiberglass profile is fixedly installed on the upper end of the bottom frame, several sets of epoxy movable blocks are laid and installed on the upper end of the main fiberglass profile, positioning pins are installed inside the several sets of epoxy movable blocks, and several sets of profile adjustment assemblies are installed inside the main fiberglass profile.

[0006] Furthermore, the bottom frame includes lifting rings and casters. Several sets of lifting rings are symmetrically arranged at the outer end of the bottom frame, and these sets of lifting rings are welded and fixed to the bottom frame.

[0007] Furthermore, the lower end of the bottom frame is equipped with multiple sets of casters, and the upper ends of the multiple sets of casters are welded with connecting plates. The multiple sets of casters are fixedly connected to the bottom frame through the connecting plates.

[0008] Furthermore, the bottom frame is a square tube frame structure, and triangular reinforcing ribs are provided inside the bottom frame.

[0009] Furthermore, the profile adjustment assembly includes a front end plate, bolts and nuts, bolts are provided inside the bottom frame and the main fiberglass profile, and bolt connection holes are opened inside the bottom frame and the main fiberglass profile.

[0010] Furthermore, the outer wall of the bolt is provided with several sets of nuts, and the bolt is fixed to the bottom frame and the main fiberglass plate by the bolt thread.

[0011] Furthermore, the end of the bolt away from the nut is provided with a front end plate, which is welded and fixed to the bolt.

[0012] The beneficial effects are: This utility model achieves the following by using a square tube frame structure for welding the bottom frame, which results in less welding deformation. Combined with the stability of the triangular reinforcing rib structure, ventilation is provided in the hollow area where the bottom frame contacts the main fiberglass plate, so that the mold is heated evenly in the autoclave working state, saving costs and shortening the manufacturing cycle.

[0013] By using a main fiberglass profile with uniform thickness and auxiliary heat conduction, the curing time is shortened. The fiberglass profile is turned into a mold using a transition mold, which is machined by a CNC machining center to ensure the accuracy of the mold turning and meet the product molding requirements. Epoxy movable blocks are used to assist the product in smooth demolding, and positioning pins are used for insertion and limiting, which not only meets the positioning requirements but also realizes the locking function, improving the overall stability.

[0014] By using a front-end plate, bolts, and nuts, a streamlined device is constructed. Its operation is extremely simple, allowing for quick assembly and disassembly, reducing manpower input and improving work efficiency. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of a three-dimensional structure of a composite material propulsion and landing rocket leg molding die for this utility model;

[0016] Figure 2 This is a schematic diagram of the three-dimensional structure of the bottom frame of this utility model;

[0017] Figure 3 This is a schematic diagram of the three-dimensional structure of the main fiberglass profile of this utility model;

[0018] Figure 4 This is a schematic diagram of the three-dimensional structure of the epoxy movable block in this practical application;

[0019] Figure 5 This is a three-dimensional structural diagram of the template adjustment component for this practical application.

[0020] In the attached diagram, the following are the reference numerals: 1. Bottom frame; 101. Lifting ring; 102. Caster wheel; 2. Main fiberglass profile; 3. Epoxy movable block; 4. Profile adjustment assembly; 401. Front end plate; 402. Bolt; 403. Nut. Detailed Implementation

[0021] The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.

[0022] Composite materials are materials composed of two or more materials with different properties, combined macroscopically using physical or chemical methods to achieve novel properties. They are novel materials created by combining several different types of materials, such as organic polymers, inorganic non-metals, or metals, through composite processes. The components complement each other, producing a synergistic effect that makes the overall performance of the composite material superior to the original components. Different components and composite methods can be selected according to application requirements to design composite materials that meet specific performance requirements. They generally have high specific strength and specific modulus (i.e., a high ratio of strength and modulus to density), which can reduce structural weight and improve structural efficiency. Many composite materials have good resistance to chemical corrosion and natural environmental factors. The manufacturing of composite materials involves various processes, depending on the materials used and the required properties of the final product. Common manufacturing processes include lamination, molding, and extrusion. Composite materials are widely used in aerospace, automotive, wind power, sporting goods, construction, electronics, shipbuilding, medical devices, energy, and defense, among other fields.

[0023] Composite material propulsion and landing rocket legs are key components of reusable rockets. Typically mounted on the bottom of the rocket, they provide support and cushioning during landing. They usually consist of multiple parts, including the leg body, cushioning device, deployment and locking mechanism, and foot pads. The legs are retracted during rocket liftoff to reduce air resistance; during landing, they deploy and lock to absorb the immense impact force. They combine the lightweight and high-strength properties of composite materials with a complex mechanical structure design to achieve stable support and cushioning during the recovery and landing process. These legs are typically made of composite materials such as carbon fiber reinforced polymer (CFRP), possessing extremely high strength and low weight. They retract during liftoff to reduce air resistance and quickly deploy and lock during landing to absorb the massive impact force. In practical applications, landing legs generally consist of landing legs, cushioning device, deployment and locking mechanism, and foot pads. The cushioning device is a key component used to absorb the kinetic energy during rocket landing, while the outriggers themselves need to have sufficient rigidity and strength to ensure that they are not damaged during the collision and can be reused after simple inspection and repair. Composite material propulsion landing rocket outriggers are an indispensable part of modern aerospace technology. They not only improve the reusability of rockets but also reduce launch costs and promote the development of commercial spaceflight.

[0024] Composite material propulsion and landing rocket outrigger molding dies are specially designed tools used to cure composite prepreg or fiber-reinforced materials into predetermined shapes and sizes. These dies are typically made of high-strength materials with low coefficients of thermal expansion to ensure dimensional stability during high-temperature curing. The dies provide a precise profile for the composite material, ensuring the outrigger maintains its required shape during curing. Precise mold design enables high-precision dimensional control, crucial for the installation and function of the rocket outrigger. The mold design considers the layup direction and structural requirements of the composite material, ensuring the correct fiber arrangement and distribution during curing, thereby improving structural strength. During curing, the mold can uniformly transfer heat, avoiding localized overheating or uneven cooling, thus reducing thermal stress and deformation. High-quality molds can improve the surface finish of composite parts, reducing the need for subsequent processing. In practical applications, composite material propulsion and landing rocket outrigger molding dies are widely used in manufacturing high-performance rocket outriggers. With the continuous development of composite material technology, the design and manufacturing of molding dies are constantly being optimized to meet higher performance requirements. Composite material propulsion landing rocket leg molding dies are an indispensable part of modern aerospace manufacturing. Through precise shape definition, dimensional control, and thermal management, they ensure the high performance and reliability of rocket legs.

[0025] During the molding process, the prepreg is first laid on the mold according to the design requirements. Then, the outrigger is placed in a vacuum bag and cured in an autoclave to complete the final molding. The design and manufacture of this molding mold need to consider a variety of factors, including the structural complexity of the outrigger, the properties of the material, and the thermodynamic and mechanical behavior during the molding process. By using advanced manufacturing technologies and materials, such as 3D printing and automated fiber placement, the precision and efficiency of the mold can be improved, thereby producing lightweight, high-strength, and reliable composite rocket outriggers. It plays a crucial role in the production process of rocket outriggers. This mold not only determines the shape and dimensional accuracy of the outrigger, but also directly affects the structural integrity and performance of the outrigger.

[0026] like Figures 1-5 As shown, a composite material propulsion landing rocket leg molding mold includes a bottom frame 1, a main fiberglass profile 2, epoxy movable blocks 3, and a profile adjustment assembly 4; the main fiberglass profile 2 is fixedly installed on the upper end of the bottom frame 1, and several sets of epoxy movable blocks 3 are laid and installed on the upper end of the main fiberglass profile 2. Positioning pins are installed inside the several sets of epoxy movable blocks 3, and several sets of profile adjustment assemblies 4 are installed inside the main fiberglass profile 2.

[0027] Please see Figures 1-3The bottom frame 1 includes lifting rings 101 and casters 102. Several sets of lifting rings 101 are symmetrically arranged at the outer end of the bottom frame 1, and these sets of lifting rings 101 are welded and fixed to the bottom frame 1. Ventilation is achieved through the contact and hollow area between the bottom frame 1 and the main fiberglass plate 2, ensuring uniform heating of the mold during autoclave operation, saving costs and shortening the manufacturing cycle. Multiple sets of casters 102 are provided at the lower end of the bottom frame 1, and connecting plates are welded to the upper ends of the multiple sets of casters 102. The multiple sets of casters 102 are fixedly connected to the bottom frame 1 through the connecting plates.

[0028] Please see Figures 2-4 The bottom frame 1 is a square tube frame structure, and triangular reinforcing ribs are provided inside the bottom frame 1. The plate adjustment component 4 includes a front end plate 401, bolts 402 and nuts 403. Bolts 402 are provided inside the bottom frame 1 and the main fiberglass plate 2. Connection holes for accommodating bolts 402 are opened inside the bottom frame 1 and the main fiberglass plate 2. The main fiberglass plate 2 is uniformly 12 mm thick. The fiberglass plate uses phenolic modified resin matrix and fiberglass as reinforcing material. The main body is lightweight and hard, with stable performance, high mechanical strength and corrosion resistance.

[0029] Please see Figures 3-5 The outer wall of the bolt 402 is provided with several sets of nuts 403. The bolt 402 is threadedly fixed to the bottom frame 1 and the main fiberglass plate 2. The end of the bolt 402 away from the nuts 403 is provided with a front end plate 401, which is welded and fixed to the bolt 402.

[0030] When using the mold, the bottom frame 1 of the square tube frame structure is used to ventilate the contact area between the main glass mold plate and the hollowed-out area. This ensures uniform heating of the mold during autoclave operation, saving costs and shortening the manufacturing cycle. The main fiberglass mold plate 2 is uniformly 12 mm thick, which facilitates heat conduction and shortens curing time. A transition mold is used for mold making, and this transition mold is machined using a CNC machining center to ensure mold making accuracy. The fiberglass mold plate uses a phenolic modified resin matrix with fiberglass as a reinforcing material, resulting in a lightweight yet rigid main body with stable performance and high mechanical strength. With advantages such as corrosion resistance, it meets the product molding requirements. Combined with 28 epoxy movable blocks 3, positioning pins and bolts 402 are used for positioning and locking, which meets the positioning requirements and locks the function. At the same time, it meets the accuracy of repeated disassembly. The epoxy movable blocks 3 have stable performance, high mechanical strength, corrosion resistance and other advantages. After the overall mold is formed, it is inspected by laser measuring equipment. At this time, it is found that the local surface is not within the tolerance range. The mold plate adjustment device is used for adjustment. The mold plate adjustment device consists of a front plate 401, bolts 402 and nuts 403. The mechanism is simple and convenient to operate, saving the labor cost of stacking.

[0031] The above description is only a preferred embodiment of this utility model and is not intended to limit this utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. A molding die for a composite material propulsion and landing rocket leg, characterized in that, It includes a bottom frame (1), a main fiberglass profile (2), epoxy movable blocks (3) and a profile adjustment assembly (4); the main fiberglass profile (2) is fixedly installed on the upper end of the bottom frame (1), and several sets of epoxy movable blocks (3) are laid on the upper end of the main fiberglass profile (2). Positioning pins are installed inside the several sets of epoxy movable blocks (3), and several sets of profile adjustment assemblies (4) are installed inside the main fiberglass profile (2).

2. The composite material launch and landing rocket leg forming mold of claim 1, wherein, The bottom frame (1) includes lifting rings (101) and casters (102). Several sets of lifting rings (101) are symmetrically provided at the outer end of the bottom frame (1), and the several sets of lifting rings (101) are welded and fixed to the bottom frame (1).

3. The composite material launch and landing rocket leg forming mold of claim 2, wherein, The bottom frame (1) is provided with multiple sets of casters (102) at the lower end, and a connecting plate is welded to the upper end of the multiple sets of casters (102). The multiple sets of casters (102) are fixedly connected to the bottom frame (1) through the connecting plate.

4. The composite material launch and landing rocket leg forming mold of claim 3, wherein, The bottom frame (1) is a square tube frame structure, and triangular reinforcing ribs are provided inside the bottom frame (1).

5. The composite material launch and landing rocket leg forming mold of claim 1, wherein, The plate adjustment assembly (4) includes a front plate (401), bolts (402) and nuts (403). Bolts (402) are provided inside the bottom frame (1) and the main fiberglass plate (2). Connection holes for accommodating bolts (402) are opened inside the bottom frame (1) and the main fiberglass plate (2).

6. The composite material launch and landing rocket leg forming mold of claim 5, wherein, The outer wall of the bolt (402) is provided with several sets of nuts (403), and the bolt (402) is threadedly fixed to the bottom frame (1) and the main fiberglass plate (2) by the bolt (402).

7. The composite material launch and landing rocket leg forming mold of claim 5, wherein, The bolt (402) has a front end plate (401) at the end away from the nut (403), and the front end plate (401) is welded and fixed to the bolt (402).

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