Aircraft and arm thereof

Abstract

The invention relates to the technical field of aircrafts, and discloses an aircraft and an arm thereof. The vehicle arm is applied to the aircraft and comprises a vehicle arm body and an external extending part, the vehicle arm body and the external extending part are integrally connected, the external extending part extends outwards and is of a structure gradually reduced in the first direction, and the external extending part comprises a streamline surface structure so as to reduce air resistance when the aircraft flies. The machine arm main body and the vertical fin are integrally formed and connected, so that the stabilizer rigidity of the vertical fin can be improved, the loosening risk of the vertical fin is reduced, the number of parts is reduced, and the weight is reduced.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft, and in particular to an aircraft and an arm thereof. Background Art

[0002] At present, many aircraft arms and vertical tails are installed in a detachable manner. Due to poor assembly workmanship, the detachable vertical tail often leads to gaps in the vertical tail stabilizer, which can easily induce vertical tail vibration and is not conducive to flight stability. Because the detachable installation structure of the vertical tail requires a corresponding structure to meet the requirements, the vertical tail is often heavy. In addition, certain auxiliary tools are required to install the vertical tail in the field, which is more troublesome. Summary of the invention

[0003] The purpose of the present application is to provide an aircraft and its arm. The integrally formed connection between the arm body and the vertical tail of the present application can improve the stiffness of the vertical tail stabilizer surface, reduce the risk of the vertical tail coming loose, and reduce the number of parts and weight.

[0004] In order to solve the above-mentioned technical problems, the present application provides an arm, which is applied to an aircraft, comprising: an arm body and an external extension part, the arm body and the external extension part are integrally connected, the external extension part extends outward and presents a gradually narrowing structure along a first direction, wherein the external extension part includes a streamlined surface structure to reduce the air resistance of the aircraft during flight.

[0005] The present application provides an aircraft, comprising a fuselage and the above-mentioned arm, wherein the arm is assembled on the fuselage.

[0006] Optionally, the external extension part includes a first part and a second part, the first part is integrally connected to the arm body, and the second part is a movable part and can rotate freely around the first part to control the flow of air passing through the surface of the first part when the aircraft is flying, thereby adjusting the flight direction of the aircraft.

[0007] Optionally, the first direction is a direction away from the arm body.

[0008] Optionally, the outer extension portion extends downward and its thickness gradually decreases.

[0009] Optionally, the arm body and the external extension part are both made of carbon fiber, the arm body is formed by at least two carbon fiber shells spliced ​​together from top to bottom, and the external extension part is formed by at least two carbon fiber shells spliced ​​together from left to right.

[0010] Optionally, the arm body includes a front end portion, a middle end portion and a rear end portion, and the rear end portion is integrally connected to the external extension portion.

[0011] Optionally, the middle end portion includes a wing assembly notch, the wing assembly notch includes oblique portions on both sides and a flat portion in the middle, and the wing assembly notch is used for matching and connecting with the fuselage.

[0012] Optionally, it includes an arm opening, which is connected to the inside of the arm, and a bowl-shaped structure that expands outward is provided at the end of the arm opening.

[0013] Optionally, the cross-section of the arm body at each position is in the shape of an inverted water drop.

[0014] The integrally formed connection between the arm body and the vertical tail of the present application can improve the rigidity of the vertical tail stabilizer, reduce the number of large components installed in the field, and eliminate the positioning structure and locking structure required for installing the vertical tail, thereby reducing the risk of loosening, reducing weight, and saving related parts costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 The figure shows a schematic diagram of the structure of the machine arm of the first embodiment of the present application;

[0016] Figure 2 It is a schematic structural diagram of the rear end portion of the machine arm of the first embodiment of the present application;

[0017] Figure 3 Shown is a schematic structural diagram of an aircraft according to a second embodiment of the present application. DETAILED DESCRIPTION

[0018] The following embodiments further illustrate the technical solution of the present application. It is to be understood that the specific embodiments described herein are only used to explain the present application. It should also be noted that, for ease of description, only the parts related to the present application are shown in the drawings, not all.

[0019] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0020] In the present application, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0021] The following describes the first embodiment of the present application with reference to the accompanying drawings. Figure 1 and Figure 2 As shown, the arm of the first embodiment of the present application is applied to an aircraft, including: an arm body 1 and an external extension part 2, the arm body 1 and the external extension part 2 are integrally connected, the external extension part 2 extends outward and presents a gradually narrowing structure along a first direction, wherein the external extension part 2 includes a streamlined surface structure to reduce the air resistance of the aircraft during flight.

[0022] Specifically, the arm body 1 includes a front end portion 11, a middle end portion 12 and a rear end portion 13, and the rear end portion 13 is integrally connected to the external extension portion 2. However, it is understandable that the external extension portion 2 can also be connected to other parts, such as the middle end portion 12. The arm includes a plurality of transverse support beams 14 and a plurality of vertical support beams 15 inside, which are used to support the arm body 1. Some support beams 14 and support beams 15 are interwoven with each other to enhance the structural strength of the arm. The external extension portion 2 includes a first portion 21 and a second portion 22. The first portion 21 is a stabilizer portion, which is integrally connected to the arm body 1. The second portion 22 is a movable portion and can rotate freely around the first portion 21 to control the air flow passing through the surface of the first portion 21 when the aircraft is flying, thereby adjusting the flight direction of the aircraft. The external extension portion 2 can be used as a vertical tail connected to the aircraft arm. A steering gear can be installed inside the first portion 21. The second portion 22 is used as a rudder surface that can rotate left and right, which is controlled by the steering gear in the stabilizer portion to achieve left and right rotation, thereby adjusting the direction of the airflow. The first direction is the direction away from the arm body 1. Preferably, the first direction is perpendicular to the direction of the aircraft. The vertical tail gradually shrinks in the direction away from the arm body 1, and the windward side of at least one side presents a streamlined surface structure to reduce the air resistance of the aircraft during flight. In addition, the external extension part 2 extends downward and its thickness direction gradually decreases. Preferably, the arm body 1 and the external extension part 2 are both made of carbon fiber. The carbon fiber material also has excellent mechanical properties and thermal expansion coefficient, can withstand extreme environments such as high temperature, high pressure and mechanical vibration, and the weight is also very conducive to the lightweight design of the aircraft. The arm body 1 can be formed by splicing two parts of carbon fiber shells up and down, and the external extension part 2 is also formed by splicing two parts of carbon fiber shells left and right, which maximizes the processing of composite materials and reduces production costs while ensuring the strength of the fuselage. The arm body and the vertical tail are connected in one piece, which can improve the stiffness of the vertical tail stabilizer, reduce the number of large components installed in the field, and the positioning structure and locking structure required for installing the vertical tail can also be omitted, reducing the risk of loosening, reducing weight, and saving related parts costs.

[0023] Further, the middle end portion 12 includes a wing assembly notch 3, the wing assembly notch 3 includes oblique openings 31 on both sides and a flat opening 32 in the middle, and the wing assembly notch 3 is used to cooperate with the fuselage. Further, the arm also includes an arm opening 5, the arm opening 5 is connected to the inside of the arm, and the port of the arm opening 5 is provided with a bowl-shaped structure that expands outward, the rotor motor of the aircraft enters the inside of the arm through the arm opening 5, and the centrifugal fan on the upper part of the rotor motor enters the bowl-shaped structure of the arm opening 5 (and is exposed outside the arm at the same time), but is not exposed on the windward surface, thereby ensuring the streamline of the windward surface and avoiding the airflow resistance caused by the centrifugal fan being exposed to the arm. Further, the cross-sections of each position of the arm body 1 are in the shape of an inverted water drop, especially the cross-sections of the positions on both sides of the arm motor are in the shape of an inverted water drop, the wind flow generated by the arm motor can go down along the water drop shape, and the water drop shape can avoid the generation of vortices under the arm, thereby causing unnecessary arm vibration.

[0024] The second embodiment of the present application also provides an aircraft, such as Figure 3 As shown, it includes a fuselage 4 and the above-mentioned arm body 1, and the arm body 1 is assembled on the fuselage 4. The arm body and the vertical tail of the aircraft in the embodiment of the present application are integrally connected, which can improve the rigidity of the vertical tail stabilizer, reduce the number of large components installed in the field, and the positioning structure and locking structure required for installing the vertical tail can also be omitted, reducing the risk of loosening, reducing the weight, and saving the cost of related parts.

[0025] The above embodiments are merely illustrative of the principles and effects of the present application. Anyone familiar with the technology may modify or change the above embodiments without violating the purpose of the present application. Therefore, all equivalent modifications or changes made by a person with ordinary knowledge in the relevant technical field without departing from the purpose disclosed in the present application shall still be covered by the claims of the present application.

Claims

1. A machine arm, applied to an aircraft, characterized in that: include: The invention relates to an arm body (1) and an external extension part (2), wherein the arm body (1) and the external extension part (2) are integrally connected, and the external extension part (2) extends outward and presents a structure that gradually decreases along a first direction, wherein the external extension part (2) includes a streamlined surface structure to reduce the air resistance of the aircraft when it is flying.

2. The machine arm according to claim 1, characterized in that: The external extension part (2) comprises a first part (21) and a second part (22), wherein the first part (21) is integrally connected to the arm body (1), and the second part (22) is a movable part and can rotate freely around the first part (21) to control the flow of air passing through the surface of the first part (21) when the aircraft is flying, thereby adjusting the flight direction of the aircraft.

3. The machine arm according to claim 1, characterized in that: The first direction is a direction away from the arm body (1).

4. The machine arm according to claim 1, characterized in that: The outer extension part (2) extends downward and its thickness gradually decreases.

5. The machine arm according to claim 1, characterized in that: The arm body (1) and the external extension part (2) are both made of carbon fiber. The arm body (1) is formed by at least two carbon fiber shells spliced ​​together from top to bottom, and the external extension part (2) is formed by at least two carbon fiber shells spliced ​​together from left to right.

6. The machine arm according to claim 1, characterized in that: The arm body (1) comprises a front end portion (11), a middle end portion (12) and a rear end portion (13), and the rear end portion (13) is integrally connected to the external extension portion (2).

7. The machine arm according to claim 6, characterized in that: The middle end portion (12) comprises a wing assembly notch (3), wherein the wing assembly notch (3) comprises oblique openings (31) on both sides and a flat opening (32) in the middle, and the wing assembly notch (3) is used for being connected with the fuselage.

8. The machine arm according to claim 1, characterized in that: It comprises an arm opening (5), the arm opening (5) being in communication with the interior of the arm, and a bowl-shaped structure expanding outward is provided at the end of the arm opening (5).

9. The machine arm according to claim 1, characterized in that: The cross-section of each position of the machine arm body (1) is in the shape of an inverted water drop.

10. An aircraft, characterized in that: It comprises a fuselage (4) and an arm as claimed in any one of claims 1 to 9, wherein the arm is assembled on the fuselage (4).

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