A rapid prototyping method for a seat of an amphibious manned vehicle and the seat

Abstract

The application discloses a kind of land-air amphibious manned machine seat rapid forming method and its seat, belong to seat forming technical field, comprising the following steps: S1, obtain the model seat of manned machine seat for production, the model seat is consistent with the profile of manned machine seat to be made;S2, carbon fiber prepreg is laid on the front of the model seat, and the laying surface includes the back of the model seat and the upper surface of the model seat chair surface;S3, the model seat that carbon fiber prepreg is laid is cured, and the cured manned machine seat is formed on the surface of model seat;S4, manned machine seat is separated from model seat.The application can use existing mature seat as model seat, effectively exempts from mold cost, greatly saves the production cost of seat, and while saving cost, greatly shortens the development cycle of seat.

Description

Technical Field

[0001] This invention belongs to the field of seat molding technology, and in particular relates to a rapid prototyping method for amphibious manned aircraft seats and the seat thereof. Background Technology

[0002] Amphibious manned aircraft (with a cockpit capable of carrying passengers on land and in low-altitude flight) are advanced transportation tools and a key research focus for various research institutions and universities. Typically, to showcase interim research results, participate in large-scale exhibitions, or complete project phases, research institutions need to produce physical prototypes that embody theoretical research findings within a short period (the normal prototype production cycle is 6-7 months, but shorter cycles are often only half the normal prototype production cycle, or even shorter). A physical prototype is one capable of both land-based and air-based flight. Because the primary goal of prototype manufacturing is to achieve amphibious manned driving or flight capabilities within a short timeframe, production time is often limited. This limited timeframe leads to unforeseen circumstances that are inherent to the research and development process, such as adjustments to the prototype design and problems encountered during functional debugging. To achieve the goal of manned flight, the prototype cabin must have sufficient rigidity while being extremely lightweight. Only by balancing rigidity and lightness can manned flight be accomplished.

[0003] Currently, there are no suitable seats on the market that meet the requirements (the requirement for amphibious aircraft is that they can support a weight of 100kg for extended periods, with each seat weighing ≤6kg). The lightest and most readily available vehicle seats are the plastic seats used in buses, each weighing ≥10kg. The cabin weight requirement for an aircraft is ≤70kg, and the cabin needs to support two seats. The current situation, where each seat weighs ≥10kg, is clearly unacceptable. Because there are no suitable seats available on the market, and because a suitable seat needs to be manufactured within a shorter timeframe (≤15 days) during the production of the amphibious prototype, a suitable seat must be produced.

[0004] Due to the production cycle limit of ≤15d, the traditional seat development process, which involves a long production process from design, mold making and manufacturing, cannot be accepted. However, the functional prototype of the amphibious drone does not have strict requirements for shape. Therefore, it is necessary to manufacture it in the shortest possible time and strengthen the structure in the corresponding parts to achieve a seat with sufficient rigidity and a weight of ≤6kg in a short time. Summary of the Invention

[0005] This invention overcomes the shortcomings of the prior art by providing a rapid prototyping method for amphibious manned aircraft seats and the seats thereof, thereby solving the problems existing in the prior art.

[0006] To achieve the above objectives, the technical solution adopted by this invention is: a rapid prototyping method for an amphibious manned aircraft seat, comprising the following steps:

[0007] S1. Obtain a model seat for manufacturing the manned aircraft seat, wherein the model seat has the same outline as the manned aircraft seat to be manufactured;

[0008] S2. Lay the carbon fiber prepreg on the front of the model seat, including the front of the backrest of the model seat and the upper surface of the seat surface.

[0009] S3. Curing process is carried out on the model seat with carbon fiber prepreg to form a cured manned aircraft seat on the surface of the model seat.

[0010] S4. Detach the manned aircraft seat from the model seat.

[0011] In a preferred embodiment of the present invention, the carbon fiber prepreg includes at least two carbon fiber components and a PVC foam board, wherein the PVC foam board is located between two adjacent carbon fiber components.

[0012] In a preferred embodiment of the present invention, the carbon fiber component is a mixture of carbon fiber cloth and resin.

[0013] In a preferred embodiment of the present invention, the surface of the PVC foam board is provided with a honeycomb structure.

[0014] In a preferred embodiment of the present invention, step S2 further includes the following steps:

[0015] S21. A reinforcing interlayer is provided on the side of the model seat, the reinforcing interlayer clamping the side of the carbon fiber prepreg.

[0016] In a preferred embodiment of the present invention, the reinforcing interlayer is a PVC board with a thickness of 2mm-3mm.

[0017] In a preferred embodiment of the present invention, in step S3, the model seat with carbon fiber prepreg is placed in a temperature chamber for curing, and after curing, it is cooled to the ambient temperature before the model seat is taken out.

[0018] In a preferred embodiment of the present invention, after step S4, the following step is further included:

[0019] S5. The manned aircraft seat is covered with skin to form a modern amphibious seat.

[0020] The present invention also discloses an amphibious manned aircraft seat, which is manufactured using a rapid prototyping method for amphibious manned aircraft seats.

[0021] This invention addresses the shortcomings of the prior art and has the following beneficial effects:

[0022] (1) This invention can use existing mature seats as model seats, effectively eliminating the cost of mold opening, greatly saving the manufacturing cost of the seats, and greatly shortening the development cycle of the seats while saving costs;

[0023] (2) Before manufacturing, a comprehensive weighing analysis can be performed on the selected model seat to meet the load-bearing requirements of lightweight and rigidity of the manned aircraft seat.

[0024] (3) PVC foam board with honeycomb structure can make the cured carbon fiber parts have high hardness, avoiding the softness of the passenger aircraft seat.

[0025] (4) The presence of the reinforcing interlayer can further strengthen the carbon fiber prepreg from the side. After the manned aircraft seat is formed, the reinforcing interlayer can further enhance the rigidity of the manned aircraft seat. Attached Figure Description

[0026] The present invention will be further described below with reference to the accompanying drawings and embodiments;

[0027] Figure 1 A flowchart of a preferred embodiment of the present invention;

[0028] Figure 2 This is a schematic diagram of the structure of a preferred embodiment of the carbon fiber prepreg of the present invention;

[0029] Figure 3 This is a schematic diagram of the structure of the model seat after it has been laid out according to a preferred embodiment of the present invention;

[0030] In the diagram: 100, model seat; 200, carbon fiber prepreg; 201, carbon fiber component; 202, PVC foam board; 300, reinforcing interlayer. Detailed Implementation

[0031] The following drawings disclose several embodiments of the present invention. For clarity, many practical details will be described in the following description. However, it should be understood that these practical details are not intended to limit the invention. That is, in some embodiments of the invention, these practical details are not essential. Furthermore, for the sake of simplicity, some conventional structures and components will be shown in the drawings in a simple schematic manner.

[0032] Furthermore, in this invention, the use of terms such as "first" and "second" is for descriptive purposes only and does not specifically refer to any order or sequence, nor is it intended to limit the invention. They are merely used to distinguish components or operations described using the same technical terms, and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the technical solutions of various embodiments can be combined with each other, but only if they are feasible for those skilled in the art. If a combination of technical solutions is contradictory or impossible to implement, such a combination should be considered nonexistent and not within the scope of protection claimed by this invention.

[0033] Combination Figures 1 to 3 As shown, this embodiment provides a rapid prototyping method for an amphibious manned aircraft seat, including the following steps:

[0034] S1. Obtain the model seat 100 for manufacturing the passenger aircraft seat. The model seat 100 has the same outline as the passenger aircraft seat to be manufactured. In this embodiment, a bus seat is used as the model seat 100, which is convenient to obtain and can also effectively reduce the mold opening cost.

[0035] S2. The carbon fiber prepreg 200 is laid on the front of the model seat 100. The laying surface includes the front of the backrest of the model seat 100 and the upper surface of the seat of the model seat 100. The front of the backrest of the model seat 100 and the upper surface of the seat of the model seat 100 are the stress positions of the manned aircraft seat, so carbon fiber prepreg 200 is used for laying.

[0036] S3. The model seat 100 with carbon fiber prepreg 200 is cured to form a cured manned aircraft seat on the surface of the model seat 100. The curing conditions are to stand at 130°C for 30 minutes in a temperature chamber, and then raise the temperature to 140°C and stand for 10 minutes to complete the curing of the manned aircraft seat.

[0037] S4. Remove the manned aircraft seat from the model seat 100, i.e., demolding.

[0038] S5. The manned aircraft seat is covered with skin to form a modern amphibious seat with a modern technological feel.

[0039] In this embodiment, the carbon fiber prepreg 200 includes at least two carbon fiber parts 201 and a PVC foam board 202. The PVC foam board 202 is located between two adjacent carbon fiber parts 201 to form a carbon fiber sandwich process, which enhances the rigidity of the passenger car seat. The surface of the PVC foam board 202 is provided with a honeycomb structure, which enables the cured carbon fiber parts 201 to have high rigidity and avoids the passenger car seat from becoming soft.

[0040] Specifically, in this embodiment, the carbon fiber component 201 is a mixture of carbon fiber cloth and resin, which has a stable structure and can form a high-strength manned aircraft seat.

[0041] In step S2 of this embodiment, the following steps also need to be performed:

[0042] S21. A reinforcing interlayer 300 is provided on the side of the model seat 100. The reinforcing interlayer 300 clamps the side of the carbon fiber prepreg 200. The reinforcing interlayer 300 is a PVC board with a thickness of 2mm-3mm. The presence of the reinforcing interlayer 300 can further strengthen the carbon fiber prepreg 200 from the side. After the manned aircraft seat is formed, the reinforcing interlayer 300 can further enhance the rigidity of the manned aircraft seat.

[0043] In this embodiment, during the fabrication of the manned aircraft seat, the back and bottom surfaces of the seat are not covered with carbon fiber prepreg 200, resulting in a hollow structure on the back and bottom surfaces. This ensures the structural strength of the manned aircraft seat while maximizing its lightweight design. The comparison between the manned aircraft seat fabricated in this embodiment and the model seat 100 is shown in the table below.

[0044]

[0045] In this embodiment, the amphibious manned aircraft seat is manufactured using a rapid prototyping method for amphibious manned aircraft seats.

[0046] In summary, this invention can use existing mature seats as model seats 100, effectively eliminating mold opening costs, greatly saving the manufacturing cost of the seats, and significantly shortening the development cycle of the seats while saving costs.

[0047] While the invention has been described above with reference to various embodiments, it should be understood that many changes and modifications can be made without departing from the scope of the invention. That is, the methods, systems, or devices discussed above are merely examples. Various configurations can be appropriately omitted, substituted, or added to various processes or components. For example, in alternative configurations, methods can be performed in a different order than described, and / or various stages can be added, omitted, and / or combined. Moreover, features described with respect to certain configurations can be combined in various other configurations. Different aspects and elements of the configuration can be combined in a similar manner. Furthermore, as technology develops, many elements are merely examples and do not limit the scope of this disclosure or the claims.

[0048] Specific details are provided in the specification to offer a thorough understanding of exemplary configurations, including implementations. However, configurations can be practiced without these specific details; for example, well-known circuits, processes, algorithms, structures, and techniques have been shown without unnecessary detail to avoid obscuring the configuration. This description provides only exemplary configurations and does not limit the scope, applicability, or configuration of the claims. Rather, the foregoing description of the configurations will provide those skilled in the art with an enabling description for implementing the described techniques. Various changes can be made to the function and arrangement of the elements without departing from the spirit or scope of this disclosure.

[0049] Furthermore, although each operation can be described as a sequential process, many operations can be executed in parallel or simultaneously. Additionally, the order of operations can be rearranged. A process may have additional steps. Moreover, examples of methods can be implemented using hardware, software, firmware, middleware, code, hardware description languages, or any combination thereof. When implemented in software, firmware, middleware, or code, the program code or code segments used to perform the necessary tasks can be stored in a non-transitory computer-readable medium such as a storage medium and executed by a processor.

[0050] In summary, the above detailed description is intended to be illustrative rather than restrictive, and it should be understood that the claims (including all equivalents) are intended to define the spirit and scope of the invention. These embodiments should be understood as illustrative only and not as limiting the scope of protection of the invention. After reading the description of this invention, those skilled in the art can make various alterations or modifications to the invention, and these equivalent changes and modifications also fall within the scope defined by the claims of this invention.

Claims

1. A rapid prototyping method for an amphibious manned aircraft seat, characterized in that, Includes the following steps: S1. Obtain a model seat (100) for manufacturing a manned aircraft seat, wherein the model seat (100) has the same outline as the manned aircraft seat to be manufactured; S2. The carbon fiber prepreg (200) is laid on the front of the model seat (100), and the laying surface includes the front of the backrest of the model seat (100) and the upper surface of the seat surface of the model seat (100). S3. The model seat (100) covered with carbon fiber prepreg (200) is cured to form a cured manned aircraft seat on the surface of the model seat (100). S4. Detach the manned aircraft seat from the model seat (100); The carbon fiber prepreg (200) includes at least two carbon fiber parts (201) and a PVC foam board (202), wherein the PVC foam board (202) is located between two adjacent carbon fiber parts (201); The carbon fiber component (201) is a mixture of carbon fiber cloth and resin; The PVC foam board (202) has a honeycomb structure on its surface; In step S2, the following steps also need to be performed: S21. A reinforcing interlayer (300) is provided on the side of the model seat (100), the reinforcing interlayer (300) clamping the side of the carbon fiber prepreg (200); Following step S4, the following steps are also included: S5. The manned aircraft seat is covered with skin to form a modern amphibious seat.

2. The rapid prototyping method for an amphibious manned aircraft seat according to claim 1, characterized in that, The reinforcing interlayer (300) is a PVC board with a thickness of 2mm-3mm.

3. The rapid prototyping method for an amphibious manned aircraft seat according to claim 1, characterized in that, In step S3, the model seat (100) with carbon fiber prepreg (200) laid on it is placed in a temperature chamber for curing. After curing, it is cooled to the ambient temperature and then the model seat (100) is taken out.

4. A type of amphibious manned aircraft seat, characterized in that, The manned aircraft seat is manufactured using a rapid prototyping method for an amphibious manned aircraft seat as described in any one of claims 1-3.

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