Device for integrally forming cabin door of aircraft launching cabin

Abstract

The utility model belongs to the technical field of integrally-formed cabin door devices of aircraft launching cabins, and particularly relates to a cabin door structure adopting a carbon fiber integrally-formed technology, which has the advantages of light weight, high strength and excellent sealing performance. An integral forming technology is adopted, so that the structural strength of the cabin door is enhanced, and the failure rate is reduced; the sealing performance of the cabin door is improved through the integrated cabin door design, and the external environment is prevented from affecting equipment in the cabin; the integrated cabin door improves the safety and convenience of door opening, and can adapt to various launching conditions; the cabin door structure adopting the carbon fiber integral forming technology has the advantages of light weight, high strength, excellent sealing performance, high reliability and convenience in installation and maintenance, and the overall performance and the launching efficiency of an airplane are greatly improved.

Description

Technical Field

[0001] This utility model belongs to the technical field of launch cabin door device for unmanned aerial vehicles (UAVs), specifically relating to a door structure using carbon fiber integral molding technology, which has lightweight, high strength and excellent sealing performance. Background Technology

[0002] Currently, traditional unmanned aerial vehicle (UAV) launch bay door devices are typically made of metal and consist of multiple components such as an independent door opening mechanism and a door opening frame. They are complex in structure, heavy in weight, have low reliability, and are difficult to install and maintain, which affects the overall performance of the aircraft and launch efficiency. Summary of the Invention

[0003] The purpose of this invention is to provide a device for an aircraft launch bay door integrally molded from carbon fiber sheet, which can effectively reduce the weight of the door, improve structural strength, and optimize the opening operation. This device mainly uses carbon fiber sheet to cast components such as the upper door panel (3), bushing (1), and connecting plate (2) of the unmanned aerial vehicle. The bushing (1) is connected to the aircraft launch bay door. The shape of the upper door panel (3) conforms to the shape design of the aircraft launch bay, and has excellent aerodynamics and impact resistance. The upper door panel (3) and the connecting plate (2) are integrally cast from carbon fiber sheet, which facilitates the fastening of the bushing (1) to the upper door panel (3) and ensures that the door remains stable during opening and closing. The opening and closing of the door is carried out through the bushing (1) set on one side of the door. The connection between the bushing (1) and the connecting plate (2) is fixed with high-strength adhesive to ensure its firmness and durability.

[0004] Advantages of this invention: Lightweight: Carbon fiber significantly reduces the weight of the hatch compared to traditional metal materials; High strength: The one-piece molding technology enhances the structural strength of the hatch and reduces the failure rate; Good sealing: The one-piece hatch design improves the hatch's sealing performance, preventing external environmental factors from affecting the equipment inside; Convenient operation: The one-piece hatch improves the safety and convenience of opening the door and can adapt to various launch conditions. The hatch structure using one-piece carbon fiber molding technology is lightweight, high-strength, and has excellent sealing performance, high reliability, and is easy to install and maintain, significantly improving the overall performance and launch efficiency of the aircraft. Attached Figure Description

[0005] This invention has one accompanying drawing.

[0006] Appendix Figure 1 This is a schematic diagram of a device for a one-piece molded aircraft launch bay door.

[0007] As shown in the figure: bushing (1), connecting plate (2), upper door panel (3), long bushing (4). Detailed Implementation

[0008] A device for an integrated aircraft launch bay door is provided, in which components such as the unmanned aircraft door panel (3), bushing (1), and connecting plate (2) are cast using carbon fiber plates; the bushing (1) is connected to the aircraft launch bay door; the upper door panel (3) has a shape that conforms to the aircraft launch bay's external design and has excellent aerodynamics and impact resistance; the upper door panel (3) and the connecting plate are integrally cast using carbon fiber plates, which facilitates the fastening of the bushing (1) to the upper door panel (3) and ensures that the door remains stable during opening and closing; the opening and closing of the door is carried out by the bushing (1) set on one side of the door, and the connection between the bushing (1) and the connecting plate (2) is fixed with a high-strength adhesive to ensure its firmness and durability.

Claims

1. A device for an integrally molded aircraft launch bay door, characterized in that: This device consists of an upper door panel (3), a bushing (1), a connecting plate (2), and a long bushing (4). It is made of carbon fiber plate. The bushing (1) is connected to the aircraft launch bay door. The upper door panel (3) and the connecting plate (2) are integrally cast from carbon fiber plate. The opening and closing of the door is achieved by the bushing (1) located on one side of the door. The connection between the bushing (1) and the connecting plate (2) is fixed with high-strength adhesive.

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