Aircraft and arm thereof

Abstract

The present application relates to the technical field of aircrafts, and discloses an aircraft and an arm thereof. The arm of the present application is applied to an aircraft, and comprises an arm main body and an external extension part, wherein the arm main body and the external extension part are integrally connected, the external extension part extends outwards and presents a structure gradually reducing in a first direction, and the external extension part comprises a streamline surface structure so as to reduce the air resistance during the flight of the aircraft. According to the present application, the arm main body and a vertical stabilizer are integrated formed and connected, so that the rigidity of the vertical stabilizer can be improved, the loosening risk of the vertical stabilizer is reduced, the number of parts is reduced, and the weight is reduced.

Description

Aircraft and its arms Technical Field

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

[0002] Many aircraft currently utilize detachable mounting systems for their arms and vertical tails. However, poor assembly workmanship often results in gaps between the stabilizer and the tail, which can easily induce tail vibration and compromise flight stability. This detachable tail mounting structure requires corresponding structural support, often resulting in a heavy tail. Furthermore, field installation requires specialized tools, making it a complex process.

[0003] Summary of the Invention

[0004] 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, reduce the risk of the vertical tail coming loose, and reduce the number of parts and weight.

[0005] In order to solve the above technical problems, the present application provides an arm for use in an aircraft, comprising: an arm body and an external extension part, the arm body and the external extension part being integrally connected, the external extension part extending outward and presenting 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.

[0006] The present application provides an aircraft, comprising a fuselage and the aforementioned arm, wherein the arm is assembled on the fuselage.

[0007] 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.

[0008] Optionally, the first direction is a direction away from the arm body.

[0009] Optionally, the outer extension portion extends downward and its thickness gradually decreases.

[0010] 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.

[0011] 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.

[0012] 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 coupling and connection with the fuselage.

[0013] Optionally, it includes an arm opening, which is connected to the interior of the arm, and a bowl-shaped structure that expands outward is provided at the end of the arm opening.

[0014] Optionally, the cross-section of each position of the arm body is in the shape of an inverted water drop.

[0015] The integral 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

[0016] FIG1 is a schematic structural diagram of a machine arm according to a first embodiment of the present application;

[0017] FIG2 is a schematic structural diagram of the rear end portion of the arm according to the first embodiment of the present application;

[0018] FIG3 is a schematic structural diagram of an aircraft according to a second embodiment of the present application. DETAILED DESCRIPTION

[0019] The following embodiments further illustrate the technical solutions of the present application. It is understood that the specific embodiments described herein are merely for the purpose of explaining the present application. It should also be noted that, for ease of description, only portions relevant to the present application are shown in the accompanying drawings, not all of them.

[0020] In the description of this application, it should be noted that, unless otherwise specified or limited, the terms "mounted," "connected," and "connected" should be understood broadly. For example, they can refer to fixed or detachable connections; mechanical or electrical connections; direct or indirect connections through an intermediate medium; and internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in this application in specific contexts.

[0021] In this application, unless otherwise expressly specified or limited, a first feature being "above" or "below" a second feature may include the first and second features being in direct contact, or may include the first and second features being in contact not directly but through another feature between them. Moreover, a first feature being "above," "above," and "above" a second feature may include the first feature being directly above or obliquely above the second feature, or may simply mean that the first feature is higher in level than the second feature. A first feature being "below," "below," and "below" a second feature may include the first feature being directly below or obliquely below the second feature, or may simply mean that the first feature is lower in level than the second feature.

[0022] The following describes the first embodiment of the present application with reference to the accompanying drawings. As shown in Figures 1 and 2, 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.

[0023] Specifically, the main arm 1 comprises a front portion 11, a mid-portion 12, and a rear-portion 13. The rear-portion 13 is integrally connected to the external extension 2. However, it is understood that the external extension 2 can also be connected to other portions, such as the mid-portion 12. The interior of the arm includes multiple transverse support beams 14 and multiple vertical support beams 15, which support the main arm 1. Some of the support beams 14 and 15 are interwoven to enhance the arm's structural strength. The external extension 2 comprises a first portion 21 and a second portion 22. The first portion 21 is the stabilizer, integrally connected to the main arm 1. The second portion 22 is a movable portion that can freely rotate around the first portion 21 to control airflow over the surface of the first portion 21 during flight, thereby adjusting the aircraft's flight direction. The external extension 2 can serve as a vertical tail connected to the aircraft's arm. A servo can be installed within the first portion 21, while the second portion 22 serves as a rotatable control surface, controlled by the servo within the stabilizer, to achieve left and right rotation, thereby adjusting the direction of airflow. The first direction is away from the main arm body 1. Preferably, the first direction is perpendicular to the direction of the aircraft. The vertical tail gradually tapers away from the main arm body 1, and at least one side of the windward side presents a streamlined surface structure to reduce air resistance during flight. In addition, the external extension 2 extends downward and its thickness gradually decreases. Preferably, both the main arm body 1 and the external extension 2 are made of carbon fiber. 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 its weight is also very conducive to the lightweight design of the aircraft. The main arm body 1 can be formed by splicing two carbon fiber shells together from top to bottom, and the external extension 2 can also be formed by splicing two carbon fiber shells together from left to right. This maximizes the composite material processing while ensuring the strength of the fuselage and reduces production costs. The integral connection between the main arm body and the vertical tail can improve the rigidity of the vertical tail stabilizer, reduce the number of large components installed in the field, and eliminate the positioning and locking structures required for installing the vertical tail, thereby reducing the risk of loosening, reducing weight, and eliminating the cost of related parts.

[0024] Furthermore, the middle portion 12 includes a wing assembly notch 3, which includes oblique portions 31 on both sides and a flat portion 32 in the middle. The wing assembly notch 3 is used to cooperate with the fuselage. Furthermore, the arm also includes an arm opening 5, which is connected to the interior of the arm. The end of the arm opening 5 is provided with a bowl-shaped structure that expands outward. The rotor motor of the aircraft enters the interior 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 (while being exposed outside the arm) instead of being exposed on the windward side, thereby ensuring the streamlined shape of the windward side and avoiding the airflow resistance caused by the centrifugal fan being exposed to the arm. Furthermore, the cross-sections of the various positions of the arm body 1 are in the shape of an inverted teardrop, especially the cross-sections on both sides of the arm motor are in the shape of an inverted teardrop. The wind flow generated by the arm motor can descend along the teardrop shape. The teardrop shape can avoid the generation of vortices under the arm, thereby causing unnecessary arm vibration.

[0025] A second embodiment of the present application further provides an aircraft, as shown in FIG3 , comprising a fuselage 4 and the aforementioned arm body 1, the arm body 1 being assembled to the fuselage 4. The arm body and the vertical tail of the aircraft in this embodiment of the present application are integrally connected, which can improve the rigidity of the vertical tail stabilizer, reduce the number of large components to be installed in the field, and eliminate the positioning and locking structures required for installing the vertical tail, thereby reducing the risk of loosening, lowering weight, and saving the cost of related parts.

[0026] The above embodiments are merely illustrative of the principles and effects of this application. Anyone skilled in the art may modify or alter the above embodiments without departing from the objectives of this application. Therefore, all equivalent modifications or alterations made by persons skilled in the art without departing from the objectives disclosed herein are intended to be covered by the claims of this 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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