A manned aircraft

Abstract

The utility model relates to the technical field of aircraft, and disclose a manned aircraft, including fuselage, be provided with seat in the fuselage, the head and tail of fuselage all are provided with the installation area of penetrating both sides, all be provided with folding wing in the installation area, the folding wing includes wing force beam, wing installation rod and rotor, wing installation rod fixedly arranged in the installation area, two wing force beam are arranged respectively in wing installation rod both ends, and are connected through rotating shaft rotation with wing installation rod, the rotor sets up in the other end of wing force beam, wing force beam and wing installation rod junction still be provided with wing force beam locking mechanism quick -release handle. Possess can fold folding wing and store, and simple structure, operation efficient etc. advantage, solved the problem of weak carrying capacity, and inconvenient folding operation of complex design.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, specifically to a manned aircraft. Background Technology

[0002] In the field of eVTOL aircraft, rotorcraft have advantages such as vertical takeoff and landing, simple structure, and easy maintenance, but their shortcomings are also quite obvious, including small payload and short endurance. To improve the payload and endurance of rotorcraft, researchers have attempted to combine wings with rotorcraft, but the large footprint of wings makes transportation and storage difficult. If the transportation and storage problems of wings can be solved, this composite eVTOL aircraft will have a much broader application prospect.

[0003] Existing wing folding structures typically involve two steps to achieve a better folding effect by fitting the wing to the fuselage: first, rotating the wing 90° along the wing chord, and then rotating it vertically along the ground to fold the wing. This type of structure is complex, has a weak load-bearing capacity, and is inconvenient to fold, making it difficult to meet the future aircraft's requirements for efficiency and stability under complex operating conditions.

[0004] Therefore, we propose a manned aircraft to solve the above problems. Utility Model Content

[0005] (a) Technical problems to be solved To address the shortcomings of existing technologies, this utility model provides a manned aircraft that has the advantages of being able to fold and store its folding wings, having a simple structure, and being highly efficient in operation. It solves the problems of complex design, weak load-bearing capacity, and inconvenient folding operation.

[0006] (II) Technical Solution To achieve the above-mentioned goal of being able to fold and store folding wings, with a simple structure and efficient operation, this utility model provides the following technical solution: a manned aircraft, including a fuselage, a seat is provided inside the fuselage, and mounting areas extending through both sides are provided at the head and tail of the fuselage, and folding wings are provided in each mounting area; The folding wing includes a wing load-bearing beam, a wing mounting rod, and a rotor. The wing mounting rod is fixedly installed within the installation area. Two wing load-bearing beams are respectively installed at both ends of the wing mounting rod and are rotatably connected to the wing mounting rod via a rotating shaft. The rotor is installed at the other end of the wing load-bearing beam. A quick-release handle for a wing load-bearing beam locking mechanism is also provided at the connection between the wing load-bearing beam and the wing mounting rod. The quick-release handle for the wing load-bearing beam locking mechanism is used to control the angle between the wing load-bearing beam and the wing mounting rod.

[0007] As a further optimization of this utility model: the fuselage is provided with a fuselage skin, and the fuselage skin has a notch at the installation area, the notch being used to place a folding wing.

[0008] As a further optimization of this utility model: an wing skin is provided outside the wing load-bearing beam, and a mounting hole is provided at one end of the wing skin near the wing mounting rod, through which the equipment wiring harness is routed.

[0009] As a further optimization of this utility model: the fuselage is also provided with multiple wing fixing mechanisms, which are used to fix the folded wings after folding, so that they are stationary relative to the fuselage.

[0010] As a further optimization of this utility model: a roller assembly is also provided at the bottom of the fuselage, the roller assembly including a front wheel and a rear wheel, the front wheel being located in the head area of ​​the fuselage and the rear wheel being located in the tail area of ​​the fuselage.

[0011] As a further optimization of this utility model: the rotation angle of the folding wing provided at the head of the fuselage is 62°, and the rotation angle of the folding wing provided at the tail of the fuselage is 90°.

[0012] As a further optimization of this utility model: the wing skin can be removed and replaced with wing shapes of different shapes.

[0013] As a further optimization of this utility model: the wing mounting rod is made of high-strength carbon steel, which ensures the strength of the wing mounting rod, and the surface is coated with anti-rust paint to prevent the wing mounting rod from rusting and affecting its strength.

[0014] As a further optimization of this utility model: the wing load-bearing beam is made of high-strength carbon steel, and multiple structural holes are provided on the wing load-bearing beam. By providing multiple structural holes, the weight of the wing load-bearing beam is greatly reduced without affecting its strength.

[0015] As a further optimization of this utility model: the rotor is a dual-engine rotor with upper and lower rotors, which can improve the lift of the rotor, and the dual-engine rotor with upper and lower rotors can also improve the stability of the fuselage.

[0016] (III) Beneficial Effects Compared with the prior art, this utility model provides a manned aircraft with the following advantages: 1. This manned aircraft, through its modular wings, fuselage design, and the arrangement of seats and armrests, enables the folding and storage of the wings of a quadcopter single-seat aircraft, and its structure is simple and its operation is efficient; 2. This manned aircraft, through the rapid folding of its wings, can avoid occupying a large space, thus improving the aircraft's transportation and storage capabilities. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the overall structure of this utility model; Figure 2 This is a schematic diagram of the folding wing structure of this utility model; Figure 3 This is a schematic diagram of the folding effect structure of the folding wing of this utility model.

[0018] In the diagram: 1. Wing skin; 2. Wing load-bearing beam; 3. Wing mounting bracket; 4. Quick-release handle for wing load-bearing beam locking mechanism; 5. Rotary shaft; 6. Fuselage skin; 7. Seat; 8. Fuselage; 9. Wing fixing mechanism; 10. Mounting hole. Detailed Implementation

[0019] 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.

[0020] Please see Figure 1-3 A manned aircraft includes a fuselage 8, a seat 7 is provided inside the fuselage 8, and mounting areas extending through both sides are provided at the head and tail of the fuselage 8, with folding wings provided in each mounting area. The folding wing includes a wing load-bearing beam 2, a wing mounting rod 3, and a rotor. The wing mounting rod 3 is fixedly installed within the installation area and is made of high-strength carbon steel to ensure its strength. Its surface is coated with anti-rust paint to prevent corrosion and maintain its strength. Two wing load-bearing beams 2 are respectively located at both ends of the wing mounting rod 3 and are rotatably connected to it via a rotating shaft 5. The wing load-bearing beams 2 are also made of high-strength carbon steel and have multiple structural components on them. By setting multiple structural holes, the weight of the wing load-bearing beam 2 is greatly reduced without affecting its strength. The rotor is located at the other end of the wing load-bearing beam 2. The rotor is a twin-engine rotor with upper and lower rotors, which can improve the lift of the rotor. At the same time, the twin-engine rotor with upper and lower rotors can also improve the stability of the fuselage 8. A quick-release handle 4 for the wing load-bearing beam locking mechanism is also provided at the connection between the wing load-bearing beam 2 and the wing mounting rod 3. The quick-release handle 4 for the wing load-bearing beam locking mechanism is used to control the angle between the wing load-bearing beam 2 and the wing mounting rod 3.

[0021] The fuselage 8 is equipped with a fuselage skin 6. The fuselage skin 6 has a notch at the installation area for placing the folding wing, thus avoiding interference between the folding wing and the fuselage 8 during folding. The wing support beam 2 is equipped with a wing skin 1. The wing skin 1 can be removed and replaced with different airfoils and different wing installation angles to adapt to different usage scenarios. The end of the wing skin 1 near the wing mounting rod 3 is provided with a mounting hole 10 for wiring the equipment harness.

[0022] The fuselage 8 is also equipped with multiple wing fixing mechanisms 9, which are used to fix the folded wings so that they are stationary relative to the fuselage 8. The bottom of the fuselage 8 is also equipped with a roller system, which includes a front wheel and a rear wheel. The front wheel is located in the nose area of ​​the fuselage 8, and the rear wheel is located in the tail area of ​​the fuselage 8. The folding wing located at the nose of the fuselage 8 has a rotation angle of 62°, and the folding wing located at the tail of the fuselage 8 has a rotation angle of 90°.

[0023] The folding operation of the folding wing is as follows: First, pull the quick-release handle 4 of the wing load-bearing beam locking mechanism at the connection between the wing load-bearing beam 2 and the wing mounting rod 3 to release the locking structure of the wing load-bearing beam 2. Then, rotate the folding wing at the head of the fuselage 8 backward by 62° and rotate the head and tail of the fuselage 8 forward by about 90°. After all the folding wings at the head and tail of the fuselage 8 are locked, fix the folding wings to the fuselage 8 through the folding fixing structure 9 installed on the fuselage 8. The folding operation of the folding wing is the reverse of the opening operation.

[0024] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A manned aircraft, comprising a fuselage (8), wherein a seat (7) is disposed within the fuselage (8), characterized in that: The fuselage (8) has mounting areas extending through both sides at its head and tail, and folding wings are provided in each mounting area. The folding wing includes a wing support beam (2), a wing mounting rod (3), and a rotor. The wing mounting rod (3) is fixedly installed in the installation area. Two wing support beams (2) are respectively installed at both ends of the wing mounting rod (3) and are rotatably connected to the wing mounting rod (3) through a rotating shaft (5). The rotor is installed at the other end of the wing support beam (2). A quick-release handle (4) of the wing support beam locking mechanism is also provided at the connection between the wing support beam (2) and the wing mounting rod (3). The quick-release handle (4) of the wing support beam locking mechanism is used to control the angle between the wing support beam (2) and the wing mounting rod (3).

2. A manned aircraft according to claim 1, characterized in that: The fuselage (8) is provided with a fuselage skin (6), and the fuselage skin (6) has a notch at the installation area for placing a folding wing.

3. A manned aircraft according to claim 1, characterized in that: The wing load-bearing beam (2) is provided with a wing skin (1), and the wing skin (1) is provided with a mounting hole (10) at one end near the wing mounting rod (3) for wiring of equipment harnesses.

4. A manned aircraft according to claim 1, characterized in that: The fuselage (8) is also provided with multiple wing fixing mechanisms (9), which are used to fix the folded wings after folding so that they are stationary relative to the fuselage (8).

5. A manned aircraft according to claim 1, characterized in that: The bottom of the fuselage (8) is also provided with a roller assembly, which includes a front wheel and a rear wheel. The front wheel is located in the head area of ​​the fuselage (8), and the rear wheel is located in the tail area of ​​the fuselage (8).

6. A manned aircraft according to claim 1, characterized in that: The rotation angle of the folding wing at the head of the fuselage (8) is 62°, and the rotation angle of the folding wing at the tail of the fuselage (8) is 90°.

7. A manned aircraft according to claim 3, characterized in that: The wing skin (1) can be removed and replaced with different wing shapes.

8. A manned aircraft according to claim 1, characterized in that: The wing mounting rod (3) is made of high-strength carbon steel and is coated with anti-rust paint.

9. A manned aircraft according to claim 1, characterized in that: The wing load-bearing beam (2) is made of high-strength carbon steel and has multiple structural holes.

10. A manned aircraft according to any one of claims 1-9, characterized in that: The rotor is a twin-engine rotor with upper and lower rotors.

Images