阅读说明：本技术 一种飞行器 (Aircraft ) 是由 缪顺文 于 2019-11-01 设计创作，主要内容包括：本发明涉及一种飞行器,涉及飞行器技术领域,以解决现有技术中折叠机翼飞行器无法在空中对机翼进行折叠的问题,本装置包括机身、第一机翼、第二机翼、第一折叠装置和第二折叠装置,第一机翼和第二机翼分别通过第一折叠装置和第二折叠装置安装于机身的两侧,第一机翼与第一负载的重量之和为A,第二机翼与第二负载的重量之和为B,机身与负载的重量之和为C,且C＝2A＝2B。本发明的飞行器,通过将机身上的部分负载转移至第一机翼和第二机翼上,从而平衡第一机翼和第二机翼两端的载荷,减少第一折叠装置和第二折叠装置所受应力,从而使飞行器在空中飞行时,第一折叠装置和第二折叠装置能够分别使第一机翼和第二机翼相对于机身进行折叠变形。(The invention relates to an aircraft, relates to the technical field of aircraft, and aims to solve the problem that a folding wing aircraft in the prior art can not fold wings in the air, wherein the folding wing aircraft comprises a fuselage, a first wing, a second wing, a first folding device and a second folding device, the first wing and the second wing are respectively installed on two sides of the fuselage through the first folding device and the second folding device, the sum of the weights of the first wing and a first load is A, the sum of the weights of the second wing and a second load is B, the sum of the weights of the fuselage and the loads is C, and C is 2A-2B. According to the aircraft, partial load on the fuselage is transferred to the first wing and the second wing, so that loads at two ends of the first wing and the second wing are balanced, and stress borne by the first folding device and the second folding device is reduced, so that the first wing and the second wing can be folded and deformed relative to the fuselage by the first folding device and the second folding device when the aircraft flies in the air.)

1. The aircraft is characterized by comprising a fuselage, a first wing, a second wing, a first folding device and a second folding device, wherein the first wing is installed on one side of the fuselage through the first folding device, the second wing is installed on the other side of the fuselage through the second folding device, a first load is arranged on the first wing, a second load is arranged on the second wing, a load is arranged on the fuselage, the sum of the weights of the first wing and the first load is A, the sum of the weights of the second wing and the second load is B, and the sum of the weights of the fuselage and the load is C, wherein C is 2A or 2B.

2. The aircraft of claim 1, further comprising a first torsion device mounted on the fuselage between the first folding device and the second folding device, wherein the first torsion device is provided on both sides with a power output end capable of outputting torsion power, the first wing is mounted on the power output end of one side of the first torsion device, and the second wing is mounted on the power output end of the other side of the first torsion device.

3. The aircraft of claim 1, wherein the first wing and the second wing are foldable wings, each foldable wing comprises an inner section wing and an outer section wing, the outer section wing is movably mounted on the inner section wing, and the inner section wing is connected to the fuselage in a folding manner.

4. The aircraft of claim 3, further comprising a buttress wing, one end of the buttress wing being movably connected to the outer section wing and the other end of the buttress wing being movably connected to the fuselage.

5. The aircraft of claim 4, further comprising a second twisting device, wherein the second twisting device is installed on the fuselage and located between the first folding device and the second folding device, a power output end capable of outputting twisting power is arranged on each of two sides of the second twisting device, the first folding device is installed on the power output end on one side of the second twisting device, and the second folding device is installed on the power output end on the other side of the second twisting device.

6. The aircraft of any one of claims 1 to 5, wherein the first load comprises a power supply or a fuel tank for supplying power to the aircraft and the second load comprises a power supply or a fuel tank for supplying power to the aircraft.

7. The aircraft of claim 6, further comprising a propeller, wherein the propeller is disposed on each of the first wing and the second wing.

8. The aircraft of claim 7, further comprising a connecting block and a tilting device, wherein the connecting block is mounted to the upper or lower fuselage by the tilting device.

9. A tandem aircraft comprising a first aircraft and a second aircraft, both the aircraft of claim 8, the connection block of the first aircraft being connected to the connection block of the second aircraft, and the fuselage head of the first aircraft and the fuselage head of the second aircraft being oriented in the same direction.

10. A parallel aircraft comprising at least a third aircraft and a fourth aircraft, both of which are the aircraft of claim 8, a first wing of the third aircraft being connected to a second wing of the fourth aircraft, and a nose of the third aircraft and a nose of the fourth aircraft being oriented in the same direction.

Technical Field

The invention relates to the technical field of aircrafts, in particular to an aircraft.

Background

The wing-changing aircraft can better adapt to unstable airflow in flight by locally or integrally changing the shape of the aircraft, and can reduce flight energy consumption by means of gust, so that the aircraft is efficient, high-performance and real-time to adapt to various flight environments and task requirements, and the wing-changing aircraft can be used more and more along with the continuous improvement of the aircraft automatic control technology.

The present variable wing aircraft is generally two types of variable rear (front) sweep wing aircraft and folding wing aircraft. Among them, the folding wing aircraft is a variable wing aircraft which has attracted much attention in recent years. However, in the existing folding wing aircraft, the moment of a wing folding mechanism is large due to large stress of a connecting part of a wing and a fuselage, so that the wing can only be folded in the air at the tail end part of the wing, and the wing cannot be folded in the air.

Disclosure of Invention

The invention aims to provide an aircraft to solve the problem that a folding wing aircraft in the prior art cannot fold wings in the air.

The invention is realized by the following technical scheme: the aircraft comprises a fuselage, a first wing, a second wing, a first folding device and a second folding device, wherein the first wing is installed on one side of the fuselage through the first folding device, the second wing is installed on the other side of the fuselage through the second folding device, a first load is arranged on the first wing, a second load is arranged on the second wing, a load is arranged on the fuselage, the sum of the weights of the first wing and the first load is A, the sum of the weights of the second wing and the second load is B, the sum of the weights of the fuselage and the load is C, and C is 2A or 2B.

Further, in order to better implement the present invention, the aircraft further includes a first torsion device, the first torsion device is mounted on the fuselage and located between the first folding device and the second folding device, both sides of the first torsion device are provided with power output ends capable of outputting torsion power, the first wing is mounted on the power output end of one side of the first torsion device, and the second wing is mounted on the power output end of the other side of the first torsion device.

Further, in order to better implement the present invention, the first wing and the second wing are foldable wings, each foldable wing includes an inner wing and an outer wing, the outer wing is movably mounted on the inner wing, and the inner wing is connected to the fuselage in a folding manner.

Furthermore, in order to better realize the invention, the aircraft further comprises a support wing, wherein one end of the support wing is movably connected with the outer section of the wing, and the other end of the support wing is movably connected with the aircraft body.

Further, in order to better implement the present invention, the present invention further includes a second twisting device, the second twisting device is mounted on the body and located between the first folding device and the second folding device, two sides of the second twisting device are respectively provided with a power output end capable of outputting twisting power, the first folding device is mounted on the power output end of one side of the second twisting device, and the second folding device is mounted on the power output end of the other side of the second twisting device.

Further, in order to better implement the present invention, the first load includes a power supply device or a fuel tank that supplies power to the aircraft, and the second load includes a power supply device or a fuel tank that supplies power to the aircraft.

Further, in order to better implement the invention, the aircraft further comprises propellers, and the propellers are arranged on the first wing and the second wing.

Further, in order to better implement the invention, the connecting device further comprises a connecting block and a tilting device, wherein the connecting block is arranged on the upper part or the lower part of the machine body through the tilting device.

The series aircraft comprises a first aircraft and a second aircraft, wherein the first aircraft and the second aircraft are both the aircraft, the connecting block of the first aircraft is connected with the connecting block of the second aircraft, and the fuselage head of the first aircraft and the fuselage head of the second aircraft face to the same direction.

The parallel connection aircraft at least comprises a third aircraft and a fourth aircraft, wherein the third aircraft and the fourth aircraft are both the aircraft, a first wing of the third aircraft is connected with a second wing of the fourth aircraft, and a fuselage head of the third aircraft and a fuselage head of the fourth aircraft face to the same direction.

Compared with the prior art, the invention has the following beneficial effects:

(1) the aircraft provided by the invention has the advantages that the first wing is arranged on one side of the fuselage through the first folding device, the second wing is arranged on the other side of the fuselage through the second folding device, the first folding device and the second folding device are respectively used for driving the first wing and the second wing to fold or reset relative to the fuselage, and by transferring part of the load on the fuselage to the wings, the sum of the weights of the first wing and the first load is equal to the sum of the weights of the second wing and the second load and is equal to half of the sum of the weights of the fuselage and the load, thereby balancing the loads at the two ends of the wing, reducing the stress at the connecting parts of the fuselage and the first wing and the fuselage and the second wing, reducing the torque borne by the first folding device and the second folding device when the first folding device and the second folding device drive the wing to deform relative to the fuselage, so that the first folding device and the second folding device can fold and deform the wing relative to the fuselage when the aircraft flies in the air.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.

Fig. 1 is a schematic structural view of an aircraft in embodiment 1 of the invention;

FIG. 2 is a schematic structural view of an aircraft according to embodiment 2 of the present invention;

FIG. 3 is a schematic structural view of an aircraft according to embodiment 3 of the present invention;

FIG. 4 is a first schematic structural diagram of an aircraft according to embodiment 4 of the present invention;

FIG. 5 is a second structural schematic diagram of an aircraft according to embodiment 4 of the present invention;

FIG. 6 is a schematic structural view III of an aircraft according to embodiment 4 of the present invention;

FIG. 7 is a schematic structural view of an aircraft according to embodiment 5 of the present invention;

FIG. 8 is a schematic structural view of an aircraft according to embodiment 6 of the present invention;

in the figure: 11-a first airfoil; 12-a second airfoil; 13-inner section wing; 14-outer section wing; 2-a fuselage; 21-the keel; 3-a power supply device; 41-a first folding device; 42-a second folding device; 43-a third folding device; 51-a first torsion device; 52-second twisting means; 53-connecting pieces; 6-a tilting device; 7-connecting blocks; 8-a propeller; 9-a landing support device; 10-support wings; 101-inner wing; 102-the outboard wing; 110-a first aircraft; 120-a second aircraft; 130-a third aircraft; 140-fourth aircraft.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention will be described in detail below. It is to be understood that the described embodiments are merely exemplary of the invention, and not restrictive of the full scope of the invention. All other embodiments, which can be derived by a person skilled in the art from the examples given herein without any inventive step, are within the scope of the present invention.

The following describes embodiments of the present invention in further detail with reference to the accompanying drawings.