An aerial vehicle employing a buoyant sink-preventing material shell

Abstract

The utility model relates to aviation aircraft technical field, concretely is an aviation aircraft with floating anti -sinking material quality shell, including aviation aircraft main part, be equipped with fuselage frame body on the aviation aircraft main part, and the fuselage frame body upper end is fixed with fuselage framework, the fuselage framework outside cover is equipped with mutually sealed clamping nose shell, backrest shell and chassis shell, and the inside of fuselage framework, backrest shell and chassis shell is clamped with lining shell respectively, and sets up sealable gas filling layer in lining shell, the bottom of fuselage frame body is equipped with chassis protection ring. The aviation aircraft with floating anti -sinking material quality shell whole frame body adopts lightweight design, and through setting up lining shell with gas filling layer in the nose shell, can provide floating dust sink function under the condition that aviation aircraft self load is not increased, guarantees the buoyancy of aviation aircraft when flying, improves the security of aviation aircraft near water area near execution task.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, specifically to an aircraft with a buoyancy-resistant outer shell. Background Technology

[0002] Aircraft are devices capable of flying within the atmosphere. They can be categorized into several types based on their purpose and characteristics, primarily including fixed-wing aircraft, helicopters, drones, and gliders. With advancements in technology, the design and functionality of aircraft are constantly evolving. Lightweighting aircraft is one of the key measures to improve their fuel efficiency, increase range, and payload capacity.

[0003] Existing aircraft typically use composite materials or alloys to manufacture frame components and shells, which have high strength and rigidity while being much lighter than traditional metal materials. However, the shell and other components have a certain weight, which can significantly reduce flight efficiency in small aircraft. Utility Model Content

[0004] The purpose of this invention is to provide an aircraft with a floating, anti-sinking material shell, in order to solve the problem mentioned in the background art that the shell and other components of current aircraft on the market have a certain weight, which greatly reduces flight efficiency in small aircraft.

[0005] To achieve the above objectives, this utility model provides the following technical solution: an aircraft using a floating and anti-sinking material shell, comprising an aircraft body, a fuselage frame on the aircraft body, and a fuselage frame fixed to the upper end of the fuselage frame, the fuselage frame being covered by a nose shell, a back shell, and a chassis shell that are mutually sealed and interlocked, and an inner liner shell being interlocked inside the nose shell, back shell, and chassis shell, and a sealable gas filling layer being provided inside the inner liner shell, the bottom of the chassis shell being provided with a chassis protective ring, and clamps being evenly spaced and connected to the chassis protective ring, and the clamps being fastened to the chassis shell.

[0006] Preferably, the edges of the head shell, backrest shell, and chassis shell are integrally provided with inwardly curved snap-fit ​​edges, and the snap-fit ​​edges are securely snapped to the body frame.

[0007] Preferably, the outer side of the inner liner shell is tightly fitted to the inner side of the machine head shell, and the thickness of the inner liner shell is less than the width of the snap-fit ​​edge.

[0008] Preferably, the chassis protective ring and the inner liner shell are made of the same material, and the chassis protective ring has a hollow circular cross-section.

[0009] Preferably, the shape of the chassis protective ring is the same as the shape of the outer frame of the chassis shell, and the size of the chassis protective ring is larger than the shape of the outer frame of the chassis shell.

[0010] Preferably, the gas filling layer is filled with an inert gas with a density less than that of air.

[0011] Compared with existing technologies, the beneficial effects of this utility model are as follows: The aircraft using a floating and anti-sinking material shell has a lightweight design for its entire frame. By setting an inner liner with a gas-filled layer inside the nose shell, it can provide floating and anti-dust-sinking functions without increasing the aircraft's own weight. This ensures the aircraft's buoyancy during flight and improves the safety of the aircraft when performing missions near water. The aircraft also features a chassis protection ring at the bottom of the fuselage frame. The chassis protection ring uses the same material and structure as the inner liner and has buoyancy. Simultaneously, the chassis protection ring provides collision protection for equipment installed at the bottom of the fuselage frame. Attached Figure Description

[0012] Figure 1 This is a side view of an aircraft using a floating, anti-sinking material shell, according to the present invention.

[0013] Figure 2 This is a schematic diagram of the connection structure between the nose shell and the inner liner shell of an aircraft using a floating and anti-sinking material shell according to the present invention.

[0014] Figure 3 This is a schematic diagram of the chassis protective ring structure of an aircraft using a floating, anti-sinking material shell, according to the present invention.

[0015] In the diagram: 1. Main body of the aircraft; 2. Nose shell; 3. Chassis protective ring; 4. Fuselage frame; 5. Clamp; 6. Backrest shell; 7. Fuselage frame; 8. Inner liner shell; 9. Snap-fit ​​edge; 10. Gas filling layer; 11. Chassis shell. Detailed Implementation

[0016] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0017] Please see Figure 1-3This utility model provides a technical solution: an aircraft using a floating, anti-sinking material shell, including an aircraft body 1, a fuselage frame 4 on the aircraft body 1, and a fuselage frame 7 fixed to the upper end of the fuselage frame 4. The fuselage frame 7 is covered by a nose shell 2, a back shell 6, and a chassis shell 11 that are mutually sealed and interlocked. The edges of the nose shell, back shell 6, and chassis shell 11 are integrally provided with inwardly curved interlocking edges 9, which are securely interlocked with the fuselage frame 7. This structure is made of polyurethane foam for the nose shell 2, back shell 6, and chassis shell 11, and is lightweight. It has the advantages of being lightweight and has a certain degree of buoyancy. The fuselage frame 4 and fuselage frame 7 are made of lightweight materials such as aluminum alloy, which ensures structural strength while reducing flight load. The snap-fit ​​edge 9 improves the structural strength of the edge of the nose shell 2 and provides a positioning connection point for the installation of the nose shell 2. The nose shell 2, the back shell 6 and the chassis shell 11 are respectively snap-fitted with inner shells 8. The outer side of the inner shell 8 is tightly fitted with the inner side of the nose shell 2, and the thickness of the inner shell 8 is less than the width of the snap-fit ​​edge 9. This structure allows the inner shell 8 to be firmly snapped into the nose shell 2, and the inner shell 8 can be fixed by adhesive. The nose shell 2 has unique structural features for drag reduction, while the inner liner 8, through the gas-filled layer 10, can improve the buoyancy of the nose shell 2, thereby reducing the impact of gravity on the nose shell 2. Furthermore, the inner liner 8 contains a sealable gas-filled layer 10 filled with an inert gas with a density less than air. This structure allows the chassis protective ring 3 to also have a certain degree of buoyancy, providing a floating and anti-sinking function during the flight of the aircraft body 1. Simultaneously, when the aircraft body 1 operates near water, it also provides a certain degree of buoyancy, serving a safety protection function. The chassis shell 11 has a chassis at its bottom. The protective ring 3, chassis protective ring 3, and inner liner shell 8 are made of the same material, and the chassis protective ring 3 has a hollow circular cross-section. This structure allows the chassis protective ring 3 and inner liner shell 8 to be made of polyethylene, which is lightweight, impact-resistant, and has buoyancy. The chassis protective ring 3 is evenly spaced with clamps 5, and the clamps 5 are bolted to the chassis shell 11. The shape of the chassis protective ring 3 is the same as the shape of the outer frame of the chassis shell 11, and the size of the chassis protective ring 3 is larger than the shape of the outer frame of the chassis shell 11. This structure can provide side safety protection for the chassis shell 11 through the chassis protective ring 3, reduce the impact of collision, and increase buoyancy.

[0018] Working Principle: When using an aircraft with a floating, anti-sinking outer shell, the main body 1 of the aircraft first forms a basic frame structure through the fuselage frame 4 and the fuselage frame 7. The inner shell 8 is tightly bonded and fixed inside the nose shell 2, the back shell 6, and the chassis shell 11. The nose shell 2 has mounting positioning points relative to the fuselage frame 7 through snap-fit ​​edges 9. The nose shell 2, the back shell 6, and the chassis shell 11 are assembled onto the fuselage frame 7, covering the front, rear, and bottom of the fuselage frame 7 respectively. At the same time, the nose shell 2... The backrest shell 6 and the chassis shell 11 are sealed with sealant to provide waterproofing and dustproofing. The chassis protective ring 3 is fixed to the bottom of the chassis shell 11 by clamps 5. By filling the gas filling layer 10 inside the chassis protective ring 3 and the inner liner shell 8 with an inert gas with a density less than air, buoyancy can be increased, eliminating some of the effects of gravity and providing a floating and anti-sinking function. At the same time, when the aircraft body 1 performs missions near water, even if it falls into the water, it will still have a certain buoyancy, improving safety performance and thus completing a series of tasks.

[0019] Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. An aircraft using a floating, anti-sinking material shell, comprising an aircraft body (1), characterized in that: The main body (1) of the aircraft is provided with a fuselage frame (4), and a fuselage frame (7) is fixed at the upper end of the fuselage frame (4). The fuselage frame (7) is covered with a nose shell (2), a back shell (6) and a chassis shell (11) that are sealed and interlocked with each other. The nose shell (2), the back shell (6) and the chassis shell (11) are respectively interlocked with an inner liner shell (8), and a sealable gas filling layer (10) is provided inside the inner liner shell (8). The bottom of the chassis shell (11) is provided with a chassis protection ring (3), and clamps (5) are evenly spaced on the chassis protection ring (3), and the clamps (5) are fastened to the chassis shell (11).

2. An aircraft with a buoyancy-resistant outer shell according to claim 1, characterized in that: The machine head shell (2), backrest shell (6) and chassis shell (11) are integrally provided with inwardly curved snap-fit ​​edges (9), and the snap-fit ​​edges (9) are fastened to the body frame (7).

3. An aircraft with a buoyancy-resistant outer shell according to claim 2, characterized in that: The outer side of the inner liner (8) is closely fitted with the inner side of the head shell (2), the back shell (6) and the chassis shell (11), and the thickness of the inner liner (8) is less than the width of the snap-fit ​​edge (9).

4. An aircraft with a buoyancy-resistant outer shell according to claim 1, characterized in that: The chassis protective ring (3) and the inner liner shell (8) are made of the same material, and the chassis protective ring (3) has a hollow circular cross-section.

5. An aircraft with a buoyancy-resistant outer shell according to claim 1, characterized in that: The shape of the chassis protective ring (3) is the same as the outer frame shape of the chassis shell (11), and the size of the chassis protective ring (3) is larger than the outer frame shape of the chassis shell (11).

6. An aircraft with a buoyancy-resistant outer shell according to claim 1, characterized in that: The gas filling layer (10) is filled with an inert gas with a density less than that of air.

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