A forming die for an aircraft head casing and a method of forming the same

Abstract

The application provides a forming die of an aircraft head shell and a forming method thereof, and relates to the technical field of aircraft shell forming dies. The forming die of the aircraft head shell comprises a left forming frame, a right forming frame and a top compression ring. The left forming frame comprises a left frame body and a left forming die, and the left forming die is arranged in the inside of the left frame body. The right forming frame comprises a right frame body and a right forming die, and the right forming die is arranged in the inside of the right frame body. The inside of the left frame body is connected with the inside of the right frame body, and the left forming die is connected with the right forming die in a buckling mode. A product forming die cavity is arranged between the left forming die and the right forming die. The top compression ring is connected with the top of the forming die. The technical problem of complex structure design of the existing die, low product forming efficiency and poor safety of the manual operation mode is solved. The left forming frame, the right forming frame and the top compression ring are combined, the product is rapidly formed, the forming efficiency is high, and the safety is good.

Description

Technical Field

[0001] This invention relates to the technical field of aircraft shell molding dies, and in particular to a molding die for an aircraft nose shell and its molding method. Background Technology

[0002] A rocket is a spacecraft that uses a rocket engine to eject propellant to generate reaction force and propel itself forward. Because rockets can carry all the propellant themselves and do not rely on external propellant to generate thrust, they can fly both inside and outside the dense atmosphere, making them the primary means of spaceflight.

[0003] In the aforementioned existing technologies, the rocket's structure mainly includes the nose cone, fuel tank, and tail fins. Due to the rocket's unique structure, various irregular structures are involved in the product manufacturing process. Especially for the production of the rocket nose cone shell, the complex mold design makes the manufacturing process time-consuming and labor-intensive. During the product molding process, most work requires manual operation, resulting in low production efficiency. Furthermore, the varying support strength of each individual increases the probability of the product slipping, posing a safety hazard. Summary of the Invention

[0004] The purpose of this invention is to provide a molding die for the nose shell of an aircraft, so as to solve the technical problems existing in the prior art, such as complex mold structure design, time-consuming and labor-intensive molding process of rocket nose shell, low production efficiency and poor safety due to manual operation.

[0005] The present invention also provides a method for forming the nose shell of an aircraft, in order to solve the technical problems of time-consuming and labor-intensive forming process and low production efficiency of rocket nose shell in the prior art.

[0006] The present invention provides a molding die for a nose shell of an aircraft, comprising a left molding frame, a right molding frame and a top pressure ring;

[0007] The left forming frame includes a left frame body and a left forming mold, with the left forming mold located inside the left frame body;

[0008] The right forming frame includes a right frame body and a right forming mold, with the right forming mold located inside the right frame body;

[0009] The inner side of the left frame is connected to the inner side of the right frame, so that the opening of the left forming mold is engaged with the opening of the right forming mold; the product forming cavity of the aircraft nose shell is located between the left forming mold and the right forming mold, and the opening of the product forming cavity is set at the top of the forming mold.

[0010] The top pressure ring is connected to the top of the molding die and is fitted onto the opening of the product molding cavity.

[0011] Furthermore, it also includes an inner ring positioning bracket;

[0012] One end of the inner ring positioning bracket is connected to the top of the molding mold, and the other end is connected to the inner ring on the lower inner side of the aircraft head shell inside the product molding cavity.

[0013] Furthermore, the inner ring positioning bracket includes the first Model frame and model frame;

[0014] First One end of the mold frame is connected to the top of the forming mold, and the other end is connected to the top of the mold frame;

[0015] The inner side of the frame is connected to the inner ring on the lower inner side of the aircraft head shell inside the product molding cavity.

[0016] Furthermore, it also includes an outer ring positioning bracket;

[0017] One end of the outer ring positioning bracket is connected to the top of the molding mold, and the other end is connected to the outer ring on the upper inner side of the aircraft head shell inside the product molding cavity.

[0018] Furthermore, the outer ring positioning bracket includes a second frame and ] frame;

[0019] second One end of the frame is connected to the top of the forming mold, and the other end is connected to... ] The top of the frame;

[0020] The inner side of the frame is connected to the outer ring on the upper inner side of the aircraft head shell inside the product molding cavity.

[0021] Furthermore, the first universal joint is connected to the left frame;

[0022] The second universal joint is connected to the right frame.

[0023] Furthermore, the left frame has a hollow structure;

[0024] The right frame has a hollow structure.

[0025] Furthermore, the inner side of the left forming mold is provided with a diamond-shaped spacer mold;

[0026] The inner side of the right forming mold is provided with a circular placeholder mold.

[0027] The present invention provides a method for forming a nose shell of an aircraft, comprising the following steps:

[0028] a. Assembly mold

[0029] The first universal joint is connected to the left frame, and the second universal joint is connected to the right frame;

[0030] The inner side of the left forming mold is connected to the diamond-shaped stationary mold, and the inner side of the right forming mold is connected to the circular stationary mold.

[0031] The left and right frames are hoisted to the assembly position using a crane; the inner side of the left frame is connected to the inner side of the right frame using connectors, and the opening of the left forming mold is fastened to the opening of the right forming mold to form the product forming cavity, thus completing the connection between the left and right forming frames.

[0032] b. Laying the prepreg

[0033] Composite material prepreg is laid sequentially on the inner wall of the product molding cavity, so that the product is formed on the inner wall of the product molding cavity;

[0034] c. Top molding of the product

[0035] A connector is used to connect the top pressure ring to the top of the above-mentioned molding mold and to fit it into the opening of the product molding cavity. The top pressure ring presses against the top of the product to shape the top of the product.

[0036] After the top of the product is formed, the top pressure ring is removed;

[0037] d. Install the inner ring

[0038] The inner ring is installed on the lower inner side of the product and fixed using multiple inner ring positioning brackets;

[0039] e. Install outer ring

[0040] Place the outer ring on the upper inner side of the product and secure it using multiple outer ring positioning brackets;

[0041] f. Product molding

[0042] Place the above products at room temperature for a certain period of time to allow the inner and outer rings to form on the products;

[0043] Then, disassemble the inner ring positioning bracket and the outer ring positioning bracket in sequence.

[0044] By disassembling the left and right frames and separating them, the required aircraft nose shell can be manufactured.

[0045] The present invention provides a molding die for the nose shell of an aircraft, which has the following technical advantages:

[0046] The left forming frame of this invention includes a left frame body and a left forming mold. The left forming mold is located inside the left frame body and is used to form the left half of the product. The right forming frame includes a right frame body and a right forming mold. The right forming mold is located inside the right frame body and is used to form the right half of the product. After the inner side of the left frame body is connected to the inner side of the right frame body, the opening of the left forming mold inside the right forming mold is engaged with the opening of the right forming mold. At this time, a product forming cavity for the aircraft head shell is formed between the left and right forming molds. The opening direction of the product forming cavity is set at the top of the forming mold, which facilitates the product forming inside the product forming cavity. A top pressure ring is connected to the top of the forming mold and is fitted onto the opening of the product forming cavity. The top pressure ring is used to form the top of the product. This invention utilizes the combination of the left forming frame, the right forming frame, and the top pressure ring to enable rapid forming of the rocket head shell with high forming efficiency. The structure of the two forming frames combined reduces manual operation and ensures that the product is stably formed inside the product forming cavity, resulting in good safety.

[0047] The present invention provides a method for forming the nose shell of an aircraft, which sequentially employs steps such as assembling a molding mold, laying prepreg, forming the top of the product, installing the inner ring, installing the outer ring, and forming the product, ensuring rapid product forming and high product forming efficiency. Attached Figure Description

[0048] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0049] Figure 1 A schematic diagram of the structure of a molding die for an aircraft nose shell provided in an embodiment of the present invention;

[0050] Figure 2 A front view of a molding die for an aircraft nose shell provided in an embodiment of the present invention;

[0051] Figure 3 A top view of a molding die for a nose shell of an aircraft provided in an embodiment of the present invention;

[0052] Figure 4 A schematic diagram illustrating the usage state of a molding die for an aircraft nose shell, provided in an embodiment of the present invention;

[0053] Figure 5 This is a schematic diagram of the structure of the left forming frame provided in an embodiment of the present invention;

[0054] Figure 6 This is a schematic diagram of the structure of the right forming frame provided in an embodiment of the present invention;

[0055] Figure 7 This is a side view of the inner ring positioning bracket provided in an embodiment of the present invention;

[0056] Figure 8 This is a schematic diagram of another side of the inner ring positioning bracket provided in an embodiment of the present invention;

[0057] Figure 9 This is a side view of the outer ring positioning bracket provided in an embodiment of the present invention;

[0058] Figure 10 This is a schematic diagram of another side of the outer ring positioning bracket provided in an embodiment of the present invention;

[0059] Figure 11 A flowchart illustrating a method for forming the nose shell of an aircraft, as provided in an embodiment of the present invention.

[0060] icon:

[0061] 100 - Left forming frame; 200 - Right forming frame; 300 - Top pressure ring; 400 - Inner ring positioning bracket; 500 - Outer ring positioning bracket; 600 - Aircraft nose shell;

[0062] 101-Left frame; 102-Left forming mold; 103-Product forming mold cavity; 104-First universal lifting ring; 105-Rhombus-shaped placeholder mold;

[0063] 201-Right frame; 202-Right forming mold; 203-Second universal joint; 204-Circular placeholder mold;

[0064] 401-First Frame; 402-ョ Frame;

[0065] 501-Second Frame; 502-] Frame;

[0066] 601 - Inner ring; 602 - Outer ring. Detailed Implementation

[0067] The technical solution of the present invention will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0068] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0069] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0070] like Figures 1-10 As shown, this embodiment provides a molding die for an aircraft head shell, including a left molding frame 100, a right molding frame 200, and a top pressure ring 300;

[0071] Reference Figure 5 The left forming frame 100 includes a left frame body 101 and a left forming mold 102. The left forming mold 102 is located inside the left frame body 101. The left forming mold 102 is a cone shape that is narrow at the bottom and wide at the top to adapt to the shape of the rocket head shell. The left forming mold 102 is directly formed inside the left frame body 101, which has a simple structural design and good product forming effect.

[0072] Reference Figure 6 The right forming frame 200 includes a right frame body 201 and a right forming mold 202. The right forming mold 202 is located inside the right frame body 201. The structure of the right forming mold 202 is the same as that of the left forming mold 102. It is a cone shape that is narrow at the bottom and wide at the top to adapt to the shape of the rocket head shell. The right forming mold 202 is directly formed inside the right frame body 201. The structural design is simple and the product forming effect is good.

[0073] Reference Figure 1 , Figure 3 The inner side of the left frame 101 is connected to the inner side of the right frame 201 by positioning screws, so that the opening of the left molding mold 102 is engaged with the opening of the right molding mold 202; the left molding mold 102 and the right molding mold 202 are located between the product molding cavity 103 of the aircraft head shell 600, and the opening direction of the product molding cavity 103 is set at the top of the molding mold.

[0074] Reference Figure 1 , Figure 3 The top pressure ring 300 is connected to the top of the molding die by positioning screws and is fitted into the opening of the product molding cavity 103.

[0075] This invention combines a left forming frame 100, a right forming frame 200, and a top pressure ring 300 to directly form the product in the product forming cavity 103 between the left forming mold 102 and the right forming mold 202. The entire mold has a simple structural design, high product forming efficiency, and the use of forming frames reduces manual operation and ensures high product safety.

[0076] Reference Figure 1 , Figure 2 , Figure 3 , Figure 4 As a further improvement to the above embodiments, an inner ring positioning bracket 400 is also included;

[0077] The upper end of the inner ring positioning bracket 400 is connected to the top of the molding mold by positioning screws, and the lower end is connected to the inner ring 601 on the lower inner side of the aircraft head shell 600 inside the product molding cavity 103 by positioning screws.

[0078] In this embodiment, five inner ring positioning brackets 400 are used, and the five inner ring positioning brackets 400 are evenly connected to the inner ring 601 so that the force is evenly distributed at each position of the inner ring 601.

[0079] Since the inner ring 601 is located on the lower inner side of the aircraft head shell 600, the inner ring positioning bracket 400 adopts a large positioning bracket to fix the inner ring 601 by going deep into the inner side of the aircraft head shell 600.

[0080] Reference Figure 7 , Figure 8 As a further improvement to the above embodiments, the inner ring positioning bracket 400 includes a first Model 401 and Model 402;

[0081] First The left end of the mold frame 401 is connected to the top of the forming mold by a positioning screw, and the right end is connected to the top of the mold frame 402 by a positioning screw.

[0082] The inner side of the frame 402 engages with the inner ring 601 on the lower inner side of the aircraft head shell 600 inside the product molding cavity 103, and the outer side of the inner ring 601 is fixed by the cavity inside the frame 402.

[0083] Reference Figure 1 , Figure 2 , Figure 3 , Figure 4 As a further improvement to the above embodiments, an outer ring positioning bracket 500 is also included;

[0084] The upper end of the outer ring positioning bracket 500 is connected to the top of the molding mold by positioning screws, and the lower end is connected to the outer ring 602 on the upper inner side of the aircraft head shell 600 inside the product molding cavity 103 by positioning screws.

[0085] In this embodiment, five outer ring positioning brackets 500 are used, and the five outer ring positioning brackets 500 are evenly connected to the outer ring 602 so that the force is evenly distributed at each position of the outer ring 602.

[0086] Since the outer ring 602 is located on the upper inner side of the aircraft head shell 600, the outer ring positioning bracket 500 adopts a small positioning bracket, which can fix the upper outer ring 602 without going deep into the inner side of the aircraft head shell 600.

[0087] Reference Figure 9 , Figure 10 As a further improvement to the above embodiments, the outer ring positioning bracket 500 includes a second Frame 501 and ] Frame 502;

[0088] second The left end of the mold frame 501 is connected to the top of the molding die via a positioning screw, and the right end is connected via a positioning screw. ] The top of frame 502;

[0089] The inner side of the frame 502 engages with the outer ring 602 on the upper inner side of the aircraft head shell 600 inside the product molding cavity 103, utilizing... ] The cavity inside the frame 502 is used to fix the outer surface of the outer ring 602.

[0090] Reference Figure 5 As a further improvement to the above embodiment, a plurality of first universal lifting rings 104 are connected to the left frame 101 by positioning screws, so as to facilitate the lifting of the left frame 101 by a crane;

[0091] Reference Figure 6 Multiple second universal joints 203 are connected to the right frame 201 by positioning screws, which makes it easy to lift the right frame 201 with a crane.

[0092] Reference Figure 5 , Figure 6 As a further improvement to the above embodiment, the left frame 101 has a hollow structure;

[0093] The right frame 201 has a hollow structure;

[0094] Both the left frame 101 and the right frame 201 adopt a hollow structure, which reduces the weight of the entire molding mold.

[0095] As a further improvement to the above embodiments, refer to Figure 5 The inner side of the left forming mold 102 is provided with a diamond-shaped occupier mold 105, which is used to form a diamond-shaped hole on the left side of the aircraft head shell 600.

[0096] Reference Figure 6 The inner side of the right forming mold 202 is provided with a circular occupant mold 204, which is used to form a circular hole on the right side of the aircraft head shell 600.

[0097] like Figure 11 As shown, the present invention provides a method for forming the nose shell of an aircraft, comprising the following steps:

[0098] a. Assembly mold

[0099] Reference Figure 5 Multiple first universal joints 104 are connected to the left frame 101 via positioning screws, as shown in the reference. Figure 6 Multiple second universal joints 203 are connected to the right frame 201 by positioning screws;

[0100] The inner side of the left forming mold 102 is connected to the diamond-shaped stationary mold 105, and the inner side of the right forming mold 202 is connected to the circular stationary mold 204.

[0101] Using a crane, the left frame 101 and right frame 201 are hoisted to the assembly position via the first universal joint 104 and the second universal joint 203, respectively. Locating screws are used to connect the inner sides of the left frame 101 and the right frame 201, and the openings of the left molding mold 102 and the right molding mold 202 are engaged to form the product molding cavity 103, thus completing the connection between the left molding frame 100 and the right molding frame 200. (Refer to...) Figure 1 ;

[0102] b. Laying the prepreg

[0103] Reference Figure 1 Composite material prepreg is sequentially laid on the inner wall of the product molding cavity 103 so that the product is formed on the inner wall of the product molding cavity 103.

[0104] c. Top molding of the product

[0105] Reference Figure 1 The top pressure ring 300 is connected to the top of the above-mentioned molding mold by using positioning screws and is sleeved on the opening of the product molding cavity 103. The top pressure ring 300 presses on the top of the product, so that the top of the product is formed.

[0106] After the top of the product is formed, the top pressure ring 300 is removed;

[0107] d. Install the inner ring

[0108] Reference Figure 1 The inner ring 601 is installed on the lower inner side of the product and fixed by positioning screws using five inner ring positioning brackets 400.

[0109] e. Install outer ring

[0110] Reference Figure 1 Place the outer ring 602 on the upper inner side of the product and fix it with positioning screws using five outer ring positioning brackets 500;

[0111] f. Product molding

[0112] Reference Figure 4 Place the above product at room temperature for 2 hours to allow the inner ring 601 and outer ring 602 to be formed on the product.

[0113] Then, disassemble the inner ring positioning bracket 400 and the outer ring positioning bracket 500 in sequence.

[0114] By disassembling the left frame 101 and the right frame 201 to separate them, the required aircraft head shell 600 can be manufactured.

[0115] The present invention discloses a method for forming the nose shell of an aircraft, which adopts a structure combining a left forming frame 100 and a right forming frame 200, enabling the product to be quickly formed in the product forming mold cavity 103. The forming process is simple, the production efficiency is high, and manual operation is reduced, resulting in good safety.

[0116] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A molding die for the nose shell of an aircraft, characterized in that, Includes a left forming frame (100), a right forming frame (200), and a top pressure ring (300); The left forming frame (100) includes a left frame body (101) and a left forming mold (102), wherein the left forming mold (102) is disposed inside the left frame body (101); The right forming frame (200) includes a right frame body (201) and a right forming mold (202), wherein the right forming mold (202) is disposed inside the right frame body (201); The inner side of the left frame (101) is connected to the inner side of the right frame (201), so that the opening of the left molding mold (102) is engaged with the opening of the right molding mold (202); the left molding mold (102) and the right molding mold (202) are located between the left molding mold (102) and the right molding mold (202) to form a product molding cavity (103) for the aircraft head shell (600), and the opening of the product molding cavity (103) is located at the top of the molding mold; The top pressure ring (300) is connected to the top of the molding die and is fitted onto the opening of the product molding cavity (103); It also includes an inner ring positioning bracket (400); One end of the inner ring positioning bracket (400) is connected to the top of the molding mold, and the other end is connected to the inner ring (601) on the lower inner side of the aircraft head shell (600) inside the product molding cavity (103); The inner ring positioning bracket (400) includes a first Frame (401) and Frame (402); The first One end of the mold frame (401) is connected to the top of the molding die, and the other end is connected to the... The top of the frame (402); The The inner side of the frame (402) is connected to the inner ring (601) on the lower inner side of the aircraft head shell (600) inside the product molding cavity (103); It also includes an outer ring positioning bracket (500); One end of the outer ring positioning bracket (500) is connected to the top of the molding mold, and the other end is connected to the outer ring (602) on the upper inner side of the aircraft head shell (600) inside the product molding cavity (103); The outer ring positioning bracket (500) includes a second Frame (501) and frame (502); The second One end of the frame (501) is connected to the top of the forming mold, and the other end is connected to the top of the frame (502); The inner side of the frame (502) is connected to the outer ring (602) on the upper inner side of the aircraft head shell (600) inside the product molding cavity (103).

2. The molding die for an aircraft nose shell according to claim 1, characterized in that, The first universal joint (104) is connected to the left frame (101); The second universal joint (203) is connected to the right frame (201).

3. The molding die for an aircraft nose shell according to claim 1, characterized in that, The left frame (101) has a hollow structure; The right frame (201) has a hollow structure.

4. The molding die for an aircraft nose shell according to claim 1, characterized in that, The inner side of the left forming mold (102) is provided with a diamond-shaped occupier mold (105); The inner side of the right forming mold (202) is provided with a circular placeholder mold (204).

5. A method for forming the nose shell of an aircraft, characterized in that, Includes the following steps: a. Assembly mold The first universal joint (104) is connected to the left frame (101), and the second universal joint (203) is connected to the right frame (201); The inner side of the left forming mold (102) is connected to the diamond-shaped stationary mold (105), and the inner side of the right forming mold (202) is connected to the circular stationary mold (204). The left frame (101) and the right frame (201) are hoisted to the assembly position using a crane. The inner side of the left frame (101) is connected to the inner side of the right frame (201) using a connector. The opening of the left molding mold (102) is fastened to the opening of the right molding mold (202) to form the product molding cavity (103), thus completing the connection between the left molding frame (100) and the right molding frame (200). b. Laying the prepreg Composite material prepreg is laid sequentially on the inner wall of the product molding cavity (103) so that the product is formed on the inner wall of the product molding cavity (103); c. Top molding of the product A top pressure ring (300) is connected to the top of the above-mentioned molding die using a connector and fitted onto the opening of the product molding cavity (103). The top pressure ring (300) presses against the top of the product, thereby shaping the top of the product. After the top of the product is formed, remove the top pressure ring (300); d. Install the inner ring The inner ring (601) is installed on the lower inner side of the product and fixed by multiple inner ring positioning brackets (400); e. Install outer ring Place the outer ring (602) on the upper inner side of the product and secure it using multiple outer ring positioning brackets (500); f. Product molding The above product is placed at room temperature for a certain period of time to allow the inner ring (601) and outer ring (602) to be formed on the product; Then, disassemble the inner ring positioning bracket (400) and the outer ring positioning bracket (500) in sequence; By disassembling the left frame (101) and the right frame (201) to separate them, the required aircraft head shell (600) can be obtained.

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