A lift-integrated biplane layout aircraft

Abstract

The utility model relates to a kind of buoyancy integrated dual-wing layout aircraft, including inflatable fuselage and inflatable wing, vertical tail mounted at the rear of fuselage, horizontal tail and the cargo compartment mounted at the bottom of inflatable fuselage, the inflatable wing adopts row type dual-wing layout, symmetrically mounted at the both sides of inflatable fuselage;The inflatable fuselage, inflatable row type wing all adopt high tenacity fiber material, lining fish row type framework.The utility model inflatable aircraft structure is light in weight, and can produce buoyancy after inflation.Row type layout is due to the beneficial aerodynamic interference between two wings, and aerodynamic efficiency is higher, the utility model is combined by flexible inflatable material and row type dual-wing layout, can effectively utilize static buoyancy and dynamic lift to realize the increase of lift, to realize short take-off and landing flight on plateau.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft technology, specifically relating to a floating integrated biplane layout aircraft. Background Technology

[0002] Compared to airports in plains areas, airports in high-altitude areas have higher altitudes and thinner air. As a result, the aerodynamic efficiency of traditional aircraft decreases significantly in high-altitude environments, leading to a substantial reduction in payload and a significant increase in takeoff / landing distances, requiring longer runways for takeoff and landing. Utility Model Content

[0003] This utility model provides a floating integrated biplane layout aircraft, and the technical problem to be solved is: to achieve short take-off and landing flight on plateaus.

[0004] To solve the above technical problems, this utility model provides a floating integrated biplane layout aircraft, characterized in that: it includes an inflatable fuselage 1 and inflatable wings 2, a vertical tail 3 and a horizontal tail 4 installed at the rear of the fuselage 1, and a cargo compartment 5 installed at the bottom of the inflatable fuselage. The inflatable wings 2 adopt a row-type biplane layout and are symmetrically installed on both sides of the inflatable fuselage 1. Both the inflatable fuselage 1 and the inflatable row-type wings 2 are made of high-toughness fiber material and lined with a fish raft-type frame.

[0005] Beneficial effects: The inflatable aircraft structure of this invention is lightweight and generates buoyancy when inflated. The wing-and-plane layout, due to the favorable aerodynamic interference between the wings, has high aerodynamic efficiency. This invention, through the combination of flexible inflatable material and a wing-and-plane layout, can effectively utilize static buoyancy and dynamic lift to increase lift, thereby enabling short takeoff and landing flights at high altitudes.

[0006] This invention employs an inflatable flexible wing / fuselage structure, which occupies a small volume and generates both static buoyancy and dynamic lift when inflated. The wing adopts a biplane configuration, and the relative position between the two wings is optimized, utilizing the aerodynamic interference between the wings to achieve improved aerodynamic efficiency compared to a monoplane configuration. Compared to a monoplane configuration, the overall aerodynamic efficiency of the biplane configuration can be increased by 50%.

[0007] The overall structure of the aircraft is a frame structure, with a fixed tricycle landing gear installed in the front and middle sections, and the engine and tail fixed in the rear. The flexible fuselage and wings are fixed to the upper part of the support. The overall structure is simple and easy to assemble quickly. This utility model adopts an inflatable flexible wing / fuselage structure, which occupies a small volume and can generate static buoyancy and dynamic lift when inflated. The wings adopt a biplane layout, and the relative position between the two wings has been optimized. The aerodynamic efficiency can be improved compared to the single-wing layout by utilizing the aerodynamic interference between the two wings.

[0008] The aircraft has a frame structure, with a fixed tricycle landing gear installed in the front and middle sections, and the engine and tail fixed in the rear. The flexible fuselage and wings are fixed to the upper part of the support frame. The overall structure is simple and easy to assemble quickly. Attached Figure Description

[0009] Figure 1 This is a front view of an integrated buoyancy transport machine according to an embodiment of the present invention.

[0010] Figure 2 This is a side view of an integrated buoyancy transport machine according to an embodiment of the present invention.

[0011] Figure 3 This is a top view of an integrated buoyancy transport machine according to an embodiment of the present invention. Detailed Implementation

[0012] To make the purpose, content and advantages of this utility model clearer, the specific embodiments of this utility model will be described in further detail below.

[0013] This utility model proposes an integrated buoyancy biplane aircraft, comprising an inflatable fuselage 1 and inflatable wings 2, a vertical tail 3 and a horizontal tail 4 mounted at the rear of the fuselage 1, an engine, landing gear mounted at the bottom of the inflatable fuselage, and a cargo hold 5 mounted at the bottom of the inflatable fuselage. The inflatable wings 2 adopt a row-type biplane layout, symmetrically mounted on both sides of the inflatable fuselage 1. The cargo hold 5 and the landing gear are independent structures, fixed to a rigid frame on the underside of the fuselage. This layout has a simple overall structure, is easy to assemble quickly, and has excellent aerodynamic characteristics. The thicker fuselage can generate greater buoyancy, the longer row-type wings can also generate greater buoyancy, and the double-row layout can also generate greater aerodynamic lift. The independent cargo hold facilitates loading and unloading of goods.

[0014] The propeller and its engine can be installed at the front or rear of the inflatable fuselage 1.

[0015] Both the inflatable fuselage 1 and the inflatable wing 2 are made of high-toughness fiber material and lined with a fish raft-style frame. They are lightweight and strong. When filled with air, they can form wings to provide the aerodynamic lift required for flight. When filled with helium, they can provide buoyancy and increase the effective payload.

[0016] The inflatable wing has multiple independent airbags inside, achieving a sufficiently large wing area and inflation volume while ensuring airtightness. The wing can significantly improve the lift and lift-to-drag ratio of the entire aircraft within a certain angle of attack range, ensuring the safety of takeoff / landing.

[0017] In this embodiment, a biplane configuration is adopted, and the relative positions between the two wings are optimized. Relative to the forewing, the rear wing is positioned 70%-90% of the chord length further back in the chord direction and 10%-30% of the chord length lower in the normal direction. Aerodynamic efficiency can be improved compared to a single-wing configuration by utilizing the aerodynamic interference between the two wings.

[0018] This layout itself has excellent aerodynamic characteristics. The thicker fuselage can generate greater buoyancy, the longer wing-like structure can also generate greater buoyancy, the double-row layout can also generate greater aerodynamic lift, and the independent cargo hold facilitates loading and unloading of goods.

[0019] The aircraft has a frame structure, with a fixed tricycle landing gear installed in the front and middle sections, and the engine and tail fin fixed in the rear. The overall structure is simple and easy to assemble quickly.

[0020] This invention employs an inflatable flexible wing / fuselage structure, which occupies a small volume and generates both static buoyancy and dynamic lift when inflated. The wing adopts a biplane configuration, and the relative position between the two wings is optimized, utilizing the aerodynamic interference between the wings to achieve improved aerodynamic efficiency compared to a monoplane configuration. Compared to a monoplane configuration, the overall aerodynamic efficiency of the biplane configuration can be increased by 50%.

[0021] The above description is only a preferred embodiment of the present utility model. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of the present utility model, and these improvements and modifications should also be considered within the protection scope of the present utility model.

Claims

1. A floating integrated biplane aircraft, characterized in that: It includes an inflatable fuselage (1) and an inflatable wing (2), a vertical tail (3) and a horizontal tail (4) installed at the rear of the fuselage (1) and a cargo hold (5) installed at the bottom of the inflatable fuselage. The inflatable wing (2) adopts a row-type double wing layout and is symmetrically installed on both sides of the inflatable fuselage (1). The inflatable fuselage (1) and the inflatable row-type wing (2) are both made of high-toughness fiber material and lined with a fish raft-type frame.

2. The integrated floating biplane aircraft according to claim 1, characterized in that: The inflatable fuselage is equipped with landing gear at the bottom.

3. The integrated floating biplane aircraft according to claim 1, characterized in that: The warehouse (5) is an independent structure.

4. The integrated floating biplane aircraft according to claim 2, characterized in that: The landing gear is an independent structure.

5. A floating integrated biplane layout aircraft according to claim 2, characterized in that: The cargo hold (5) and landing gear are fixed to a rigid frame on the underside of the fuselage.

6. The integrated floating biplane aircraft according to claim 1, characterized in that: The inflatable fuselage (1) is equipped with a propeller and its engine at the front or rear.

7. The integrated floating biplane aircraft according to claim 1, characterized in that: When the inflatable fuselage (1) and inflatable wing (2) are filled with air, they can form wings to provide the aerodynamic lift required for flight. When filled with helium, they can also provide buoyancy.

8. The integrated floating biplane aircraft according to claim 1, characterized in that: The inflatable wing contains multiple independent airbags.

9. A floating integrated biplane aircraft according to claim 1, characterized in that: The pneumatic wing (2) has a double-wing configuration. Relative to the forewing, the rear wing is positioned 70%-90% further back in the chord direction than the forewing, and 10%-30% lower in the normal direction than the forewing.

10. A floating integrated biplane aircraft according to claim 1, characterized in that: The inflatable fuselage (1) has a fixed tricycle landing gear installed in the front middle section and the engine and tail fin fixed in the rear section.

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