Rocket model arrow connecting mechanism, mold and application of rocket model arrow connecting mechanism

Abstract

The invention discloses a rocket model arrow connecting mechanism, a mold and application of the rocket model arrow connecting mechanism. The invention relates to the technical field of rocket models. The connecting mechanism comprises at least one first connector used for being connected with a rocket body. And the at least one second interface is used for being connected with a rocket arrow. The design ensures the stability and separability of the connection. The main body and the arrow can be separated from each other through the connecting mechanism, so that the arrow part can be recycled for reuse after launching; composite materials such as glass fibers or carbon fibers are selected as main raw materials, the weight is obviously reduced, necessary tensile strength and elastic modulus are provided, and the connecting mechanism can bear large impact force in the launching process and is not prone to deformation or fracture. Advanced processes such as 3D printing, injection molding or cutting forming are utilized, the geometric shape and size precision of the product can be accurately controlled, and the consistency and quality stability of the finished product are greatly improved.

Description

Technical Field

[0001] The invention relates to the technical field of rocket models, in particular to a connection technology between an arrow and a main body of a rocket model, and in particular to a rocket model arrow connection mechanism, a mold and applications thereof. Background Art

[0002] In the Space Model Championship and related competitions in various provinces and cities, the reliable separation of the arrow head and the arrow body is one of the key technologies to ensure the performance of the model rocket. It places extremely high demands on the lightness, stability and durability of the equipment. Traditionally, participating teams need to design and make the parts that connect the arrow head and the arrow body by themselves to comply with the provisions on the separation function in the competition rules. Currently, most teams use ring-shaped objects based on foam materials (especially polystyrene) as connectors. However, this practice exposes a series of technical defects in actual applications. Including:

[0003] (1) Poor material properties: Ideal connectors should be made of lightweight materials to maximize the model rocket's launch height. However, although commonly used foam materials (such as polystyrene) are easy to obtain, they are large in size and high in density, which increases the overall weight and is not conducive to improving competition results. Although some metal materials or synthetic materials have sufficient strength, they are either too heavy or insufficiently rigid, making it difficult to meet the competition's requirements for light weight and high strength.

[0004] (2) Difficulty in production and low yield: The low structural density of the foam material makes it extremely difficult to accurately process it into a ring of the required size. The manual cutting and polishing process is cumbersome and can easily lead to dimensional deviations due to improper operation. Even with laser cutting technology, due to the large thickness of the foam (20-30 mm), the cutting penetration is limited and it is difficult to ensure the verticality of the cut surface. A lot of manual polishing is still required afterwards, which increases the difficulty of production and time cost.

[0005] (3) Poor durability and environmental adaptability: In outdoor competition environments, foam materials are easily eroded by wind and rain, resulting in loose structures and particle separation, which seriously affects the stability and service life of connectors. Foam materials are prone to deformation during multiple assembly and disassembly processes and cannot maintain precise size and shape for a long time, resulting in reduced connection effects, increasing the debugging burden on athletes during competitions, and affecting the stability of performance.

[0006] To this end, the present invention proposes a rocket model arrow connection mechanism, a mold and applications thereof. Summary of the invention

[0007] In view of this, the present invention hopes to provide a rocket model arrow connection mechanism, a mold and its application to solve or alleviate the technical problems existing in the prior art, namely, poor material properties, low manufacturing difficulty and yield, and poor durability and environmental adaptability, and at least provide a beneficial option for this; the technical solution of the present invention is implemented as follows:

[0008] First, the rocket model arrow connection mechanism:

[0009] 1. Overview:

[0010] The present invention relates to an arrow connection mechanism for a model rocket and a production method thereof, which is particularly suitable for application scenarios where it is necessary to ensure that the arrow and the arrow body are firmly combined during the launch process and can be smoothly separated at a predetermined time. In order to meet these requirements, the present invention comprehensively considers multiple aspects such as material selection, production process and structural design to achieve the unity of light weight, high strength and easy operation.

[0011] (II) Technical solution:

[0012] In view of the shortcomings of foam materials (such as polystyrene) and plastic sheets (such as PU / PE) used in the prior art in terms of strength, weight and adhesion, the present invention selects composite materials as the main raw materials, specifically glass fiber or carbon fiber. This type of material ensures that the connection mechanism can withstand multiple plug-in and unplug operations without damage, and supports frequent adjustment and installation of carrier components; compared with traditional materials, composite materials can significantly reduce the weight of the finished product, which is beneficial to improving the overall performance of the model rocket; in addition, based on long-term practice and repeated experiments, we found that composite materials not only solve various problems encountered before, but also provide more possibilities for subsequent design optimization. Therefore, the specific solution is:

[0013] The connection mechanism includes at least one first interface for connecting with the rocket body and at least one second interface for connecting with the rocket arrow. This design ensures the stability and separability of the connection. The connection mechanism can separate the body and the arrow from each other, so that the arrow part can be recovered for reuse after launch.

[0014] In order to reduce weight and maintain sufficient mechanical strength, the connection mechanism adopts a hollow or porous structure design. This not only reduces the amount of material used, but also improves the structural rigidity.

[0015] As an alternative, the connecting mechanism can be designed to be annular and be in a sleeve-connected relationship with the main body and the arrow. Such a design simplifies the assembly process and enhances the connection stability.

[0016] Another alternative is to directly form the connection mechanism on the arrow head and realize the self-locking connection with the main body through the annular ratchet mechanism. This method further improves the consistency and stability of the overall structure.

[0017] The molding process of the connection mechanism includes but is not limited to 3D printing, injection molding or cutting molding. These methods can flexibly adjust product specifications according to actual needs while ensuring efficient production and high-quality output.

[0018] Regardless of the connection method used, a sealing gasket is provided between the connection mechanism and the main body to prevent leakage under high-pressure environment and ensure the safety and success rate of rocket launch.

[0019] (III) Mechanism for solving technical problems:

[0020] Choosing carbon fiber or glass fiber as the main material not only has high tensile strength, but also has low density, which can significantly reduce the total weight of the model rocket. In addition, they also have a good elastic modulus, ensuring that the connection mechanism is not easily deformed or broken when it withstands a large impact during the launch process. Since the main body and the arrow are also made of the same composite material, this ensures that the bonding interface between the two has a higher bonding strength and reduces the stress concentration problem caused by material differences.

[0021] The choice of 3D printing, injection molding or cutting molding processes allows designers to precisely control the geometric shape and dimensional accuracy of the product, thereby improving the consistency and quality stability of the finished product. Especially for complex structures (such as hollow or porous designs), traditional processing methods are difficult to achieve, but these new technologies can easily cope with them. By directly forming the connecting mechanism on the arrow, the assembly steps are simplified, the error accumulation during the assembly process is reduced, and the overall yield rate is improved. At the same time, this design scheme can also enhance the close bonding between components and avoid loosening caused by vibration or temperature changes. The hollow or porous structure design not only helps to reduce weight, but also maintains sufficient mechanical strength to meet the requirements for the stability of the connecting mechanism when the model rocket is launched. In addition, this lightweight structure is also conducive to improving flight efficiency and extending flight time.

[0022] Second aspect, a mold for producing the arrow connection mechanism as described above:

[0023] The mold is mainly composed of two parts, the upper mold and the lower mold, and at least one molding cavity is provided inside. These components together form a closed working space to accommodate and fix the material to be processed, ensuring that the connection mechanism is accurately formed according to the preset shape. The internal contour of the molding cavity is customized according to the actual shape of the connection mechanism.

[0024] Thirdly, the application of the arrow connection mechanism described above in a rocket model:

[0025] The arrowhead connection mechanism of the arrow model is made of high-strength composite materials, combined with precision mold forming technology, to ensure that it has excellent mechanical properties and low weight. At the same time, through the optimized design of the connection surface and locking device, the arrowhead and the main body are closely fitted and quickly fixed.

[0026] Compared with the prior art, the present invention has the following beneficial effects:

[0027] 1. Reduce weight while enhancing mechanical strength: The present invention selects composite materials such as glass fiber or carbon fiber as the main raw materials, which not only achieves significant weight reduction but also provides the necessary tensile strength and elastic modulus, so that the connecting mechanism can withstand a large impact force during the launch process without being easily deformed or broken.

[0028] 2. Improve production accuracy and yield rate: The present invention utilizes advanced processes such as 3D printing, injection molding or cutting molding to accurately control the geometric shape and dimensional accuracy of the product, greatly improving the consistency and quality stability of the finished product, especially for the design of complex structures.

[0029] 3. Simplify the assembly process and improve reliability: The present invention directly integrates the connecting mechanism on the arrow head and realizes a self-locking connection with the main body through an annular ratchet mechanism, which not only simplifies the assembly steps and reduces assembly errors, but also enhances the close combination between components and avoids loosening caused by vibration or temperature changes.

[0030] 4. Enhanced environmental adaptability and durability: The composite material selected by the present invention has good weather resistance and is not easily affected by natural environmental factors; the design of the sealing gasket prevents leakage under high pressure environment, further ensuring the safety and success rate of rocket launch. The hollow or porous structure design helps to reduce weight, maintain sufficient mechanical strength, meet the requirements for the stability of the connection mechanism during launch, and is also conducive to improving flight efficiency and extending flight time. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or technical descriptions will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0032] Figure 1 A schematic diagram of a rocket model of the present invention;

[0033] Figure 2 A schematic diagram of a rocket arrow of the present invention;

[0034] Figure 3 It is a schematic diagram showing the details of the rocket arrow of the present invention. DETAILED DESCRIPTION

[0035] In order to make the above-mentioned purposes, features and advantages of the present invention more obvious and easy to understand, the specific implementation methods of the present invention are described in detail below in conjunction with the accompanying drawings. In the following description, many specific details are set forth to facilitate a full understanding of the present invention. However, the present invention can be implemented in many other ways different from those described herein, and those skilled in the art can make similar improvements without violating the connotation of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below;

[0036] It should be noted that the various embodiments in this specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments, and the same or similar parts between the various embodiments can be referred to each other. For the device disclosed in the embodiment, since it corresponds to the method disclosed in the embodiment, the description is relatively simple, and the relevant parts can be referred to the method part description.

[0037] Embodiment 1, as Figures 1 to 3 As shown, this embodiment provides an arrow connection mechanism for a model rocket, which ensures that the arrow is firmly combined with the arrow body during the launch process and can be smoothly separated at a predetermined time. In order to meet these requirements, the present invention comprehensively considers multiple aspects such as material selection, production process and structural design to achieve the unity of light weight, high strength and easy operation.

[0038] The main body 1 and the arrow 2 are connected by a connecting mechanism 3. This connecting mechanism not only needs to ensure stability during launch, but also needs to be easy to separate for easy recovery and reuse.

[0039] The connecting mechanism 3 is made of the same composite material as the main body 1 and the arrow 2, and specifically uses carbon fiber or glass fiber as the main material. This type of material not only has high tensile strength and low density, but also has a good elastic modulus, which ensures that the connecting mechanism is not easily deformed or broken when it withstands a large impact force during the launch process. In addition, the selection of composite materials also helps to reduce the overall weight and improve flight performance.

[0040] Preferably, the connection mechanism 3 comprises at least one first interface for connecting with the rocket body; and at least one second interface for connecting with the rocket arrow. This design ensures the stability and separability of the connection. To improve reliability, an enhanced design is adopted at the interface, such as adding an additional support structure or using a special sealing gasket to prevent loosening or falling off due to vibration.

[0041] Specifically, in order to reduce weight and maintain sufficient mechanical strength, the connection mechanism 3 adopts a hollow or porous structure design. This not only reduces the amount of material used, but also improves the structural rigidity, so that the connection mechanism can reduce weight as much as possible without affecting strength. The hollow part can be filled with lightweight foam or other non-metallic materials to further optimize weight distribution without affecting overall strength.

[0042] In order to achieve the precise control of the separation function, a ring ratchet mechanism is integrated inside the connection mechanism. This mechanism allows the arrow to be firmly locked on the arrow body under normal conditions, but can be quickly unlocked after receiving a specific signal (such as time delay, altitude sensor trigger, etc.), ensuring that the arrow is separated as planned. The design of the ring ratchet also facilitates the adjustment of the locking force to meet the needs of different types of rockets.

[0043] Considering the complex shape and high precision requirements of the connection mechanism, advanced molding technologies such as injection molding, thermoforming or 3D printing are used to ensure the quality and consistency of the finished product. For some key parts, such as interfaces and annular ratchets, special treatments are performed, such as surface hardening or coating with wear-resistant coatings, to extend the service life.

[0044] Embodiment 2: Based on the pursuit of light weight, high strength and easy operation in Embodiment 1, this embodiment further optimizes the design of the connection mechanism 3 and introduces a ring structure to achieve a simpler assembly process and enhanced connection stability. In addition, this embodiment also describes in detail the molding process of the connection mechanism and the measures to improve the sealing performance.

[0045] In this embodiment, the connection mechanism 3 is designed to be ring-shaped and is in a sleeve-connected relationship with the main body 1 and the arrow 2. This design not only simplifies the assembly process, making installation and disassembly more convenient, but also significantly enhances the stability of the connection by increasing the contact area. The ring structure can evenly distribute stress and reduce the situation of excessive local stress, thereby improving the safety of the overall structure. In order to adapt to different production needs and technical conditions, the molding process of the connection mechanism 3 includes but is not limited to 3D printing, injection molding or cutting molding;

[0046] Considering the high pressure environment that may be encountered during rocket launch, this embodiment provides a sealing gasket between the connecting mechanism 3 and the main body 1. The sealing gasket is made of high temperature resistant and corrosion resistant elastic material, which can maintain a good sealing effect under extreme conditions, effectively prevent leakage, and ensure the safety and success rate of rocket launch.

[0047] In view of the temperature changes that may occur during rocket launch, the connection mechanism adopts a temperature compensation design. For example, by selecting materials with appropriate thermal expansion coefficients or designing flexible connection parts, the connection mechanism can maintain stable size and performance under different temperature environments, avoiding loose connection or failure caused by thermal expansion and contraction.

[0048] Embodiment 3: Based on Embodiment 1, this embodiment further introduces the following technical solutions:

[0049] The connecting mechanism 3 is directly integrally formed on the arrow 2, and realizes a self-locking connection with the main body 1 through an annular ratchet mechanism. This method not only further improves the consistency and stability of the overall structure, but also simplifies the assembly steps and reduces the error accumulation during the assembly process.

[0050] Specifically, the molding process of the connection mechanism 3 is 3D printing, injection molding or cutting molding. These manufacturing processes allow designers to accurately control the geometric shape and dimensional accuracy of the product, thereby improving the consistency and quality stability of the finished product.

[0051] It can be understood that, as in the second embodiment, a sealing gasket is also provided between the connecting mechanism 3 and the main body 1 to prevent leakage under high pressure environment and ensure the safety and success rate of rocket launch.

[0052] Embodiment 4: This embodiment discloses a mold specifically used for manufacturing the rocket model arrow connection mechanism 3 as described in the above embodiments 1 to 3. The design of the mold fully considers the complex geometric shape and material properties of the connection mechanism, and aims to provide a high-precision and high-efficiency manufacturing solution to ensure that each connection mechanism can be accurately formed according to the preset specifications and meet high quality standards.

[0053] Specifically, the mold is mainly composed of two parts: the upper mold and the lower mold. These two parts form a closed working space through precise matching to accommodate and fix the material to be processed, ensuring that the material will not be displaced or deformed during the molding process.

[0054] Specifically, at least one molding cavity is provided inside the mold, and the internal contours of these molding cavities are customized according to the actual shape of the connecting mechanism 3, accurately matching the specific size and shape requirements of the connecting mechanism. The number and layout of the molding cavities depend on the number of products produced in a single time and the efficiency requirements.

[0055] The upper mold and the lower mold are tightly matched to prevent material overflow during the molding process, ensuring the surface finish and flatness of the finished product. Considering that the connection mechanism 3 may use a variety of composite materials (such as carbon fiber or glass fiber), the mold material is selected to have good thermal stability and wear resistance, can withstand high temperature and high pressure environment, and is not easy to react chemically with the composite material, ensuring a smooth molding process.

[0056] All the above embodiments only express the implementation methods of the relevant practical applications of the present invention, and the descriptions thereof are relatively specific and detailed, but they cannot be understood as limiting the scope of the invention patent. It should be pointed out that, for ordinary technicians in this field, several variations and improvements can be made without departing from the concept of the present invention, which all belong to the protection scope of the present invention. Therefore, the protection scope of the patent of the present invention shall be based on the attached claims.

Claims

1. A rocket model arrow connection mechanism, comprising a main body (1) and an arrow (2), wherein the main body (1) and the arrow (2) are connected via a connection mechanism (3), characterized in that: The connecting mechanism (3) is made of a composite material of the same material as the main body (1) and the arrow (2); The connecting mechanism (3) comprises at least one first interface for connecting with a rocket body and at least one second interface for connecting with a rocket arrowhead; The connecting mechanism (3) can separate the main body (1) and the arrow (2) from each other.

2. The arrow connection mechanism according to claim 1, characterized in that: The composite material is selected from carbon fiber or glass fiber.

3. The arrow connection mechanism according to claim 2, characterized in that: The connecting mechanism (3) adopts a hollow or porous structure design.

4. The arrow connection mechanism according to any one of claims 1 to 3, characterized in that: The connecting mechanism (3) is annular and is sleeved with the main body (1) and the arrow (2).

5. The arrow connection mechanism according to any one of claims 1 to 3, characterized in that: The connecting mechanism (3) is integrally formed on the arrow (2) and is self-lockingly connected to the main body (1) via an annular ratchet mechanism.

6. The arrow connection mechanism according to any one of claims 1 to 3, characterized in that: The connection mechanism (3) is formed by 3D printing, injection molding or cutting.

7. The arrow connection mechanism according to claims 1 to 3, characterized in that: A sealing gasket is provided between the connecting mechanism (3) and the main body (1).

8. A mould for producing the arrow connection mechanism as claimed in any one of claims 1 to 7.

9. The mold according to claim 8, characterized in that: The mold comprises an upper mold, a lower mold and at least one molding cavity, and the shape of the molding cavity matches the outer shape of the connecting mechanism (3) to be molded.

10. Use of the arrow connection mechanism as claimed in any one of claims 1 to 7 in a rocket model.

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