Aircraft and aircraft arm construction method therefor

Abstract

The present application relates to the technical field of aircrafts, and discloses an aircraft arm construction method. The aircraft arm construction method of the present application is applied to an aircraft. An aircraft arm comprises an aircraft arm body and a direction control part. The aircraft arm construction method comprises: step S1: integrally connecting an aircraft arm body and a direction control part, wherein the direction control part extends outwards and presents a structure that gradually decreases in size in a first direction, and the direction control part comprises a streamlined surface structure, so as to reduce air resistance during the flight of an aircraft. The aircraft arm construction method of the present application achieves integrated connection between an aircraft arm body and a vertical tail, and can improve the stiffness of a vertical stabilizer, thereby lowering the risk of the vertical tail becoming loose and detaching, and reducing the number of components and the weight.

Description

Aircraft and method for constructing its arm Technical Field

[0001] The present application relates to the field of aircraft technology, and in particular to an aircraft and a method for constructing an aircraft arm thereof. 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 this application is to provide an aircraft and a method for constructing its arm. The arm construction method of this application realizes an integrated connection between the arm body and the vertical tail, which can improve the stiffness of the vertical tail stabilizer, reduce the risk of the vertical tail loosening, and reduce the number of parts and weight.

[0005] In order to solve the above technical problems, the present application provides an aircraft arm construction method, which is applied to an aircraft, wherein the arm includes: an arm body and a direction control part. The arm construction method includes: S1: connecting the arm body and the direction control part as an integral whole, wherein the direction control part extends outward and presents a gradually shrinking structure along a first direction, and the direction control part includes a streamlined surface structure to reduce the air resistance of the aircraft during flight.

[0006] An aircraft comprises a fuselage and an arm constructed according to the above-mentioned arm construction method, wherein the arm is assembled to the fuselage.

[0007] Optionally, the direction control part includes a first part and a second part, and step S1 specifically includes: connecting the first part to the arm body as an integral whole, wherein 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 direction control portion extends downward and its thickness gradually decreases.

[0010] Optionally, the arm body and the direction control part are both made of carbon fiber. Before step S1, step S0 is also included: splicing at least two carbon fiber shells up and down to form the arm body, and splicing at least two carbon fiber shells left and right to form the direction control part.

[0011] Optionally, the arm body includes a front end portion, a middle end portion and a rear end portion, and the step S1 specifically includes: integrally connecting the rear end portion with the direction control portion.

[0012] Optionally, the middle end portion includes a wing assembly notch, the wing assembly notch includes inclined portions on both sides and a transverse portion in the middle, and the wing assembly notch is used for coupling and connection with the fuselage.

[0013] Optionally, the arm includes an arm opening, the arm opening 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] Optionally, the interior of the arm includes multiple transverse support beams and multiple vertical support beams.

[0016] The arm construction method of the present application realizes an integrated connection between the arm and the vertical tail, which can improve the stiffness 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

[0017] FIG1 is a schematic diagram showing a flow chart of a method for constructing an arm according to a first embodiment of the present application;

[0018] FIG2 is a schematic structural diagram of the machine arm according to the first embodiment of the present application;

[0019] FIG3 is a schematic structural diagram of the rear end portion of the machine arm according to the first embodiment of the present application;

[0020] FIG4 is a schematic structural diagram of an aircraft according to a second embodiment of the present application. DETAILED DESCRIPTION

[0021] 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.

[0022] 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.

[0023] 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.

[0024] The following describes a first embodiment of the present application with reference to the accompanying drawings. As shown in FIG1 , the arm construction method of the present application includes the following steps:

[0025] S1: The arm body 1 and the direction control part 2 are connected as one body, wherein the direction control part 2 extends outward and presents a structure that gradually shrinks along a first direction, and the direction control part (2) includes a streamlined surface structure to reduce the air resistance of the aircraft during flight.

[0026] Specifically, as shown in Figures 2 and 3, the arm construction method of the first embodiment of the present application is applied to an aircraft. The arm comprises an arm body 1 and a directional control section 2. The arm body 1 comprises a front portion 11, a middle portion 12, and a rear portion 13. The arm construction method comprises integrally connecting the rear portion 13 of the arm body 1 to the directional control section 2. However, it is understood that the directional control section 2 can also be connected to other parts, such as the middle portion 12. The arm interior comprises a plurality of transverse support beams 14 and a plurality of vertical support beams 15 for supporting the arm body 1. Some support beams 14 and 15 are interwoven to enhance the arm's structural strength. The directional control section 2 comprises a first portion 21 and a second portion 22. The first portion 21 is the stabilizer portion. The arm construction method specifically comprises integrally connecting the first portion 21 to the arm body 1. The second portion 22 is a movable portion that can freely rotate about the first portion 21 to control the flow of air over the surface of the first portion 21 during flight, thereby adjusting the aircraft's flight direction. The direction control part 2 can serve as a vertical tail connected to the aircraft arm. A servo can be installed inside the first part 21. The second part 22 serves as a rudder that can rotate left and right. It is controlled by the servo in the stabilizer part 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 direction control part 2 extends downward and its thickness direction gradually decreases. Preferably, the arm body 1 and the direction control 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. Before step S1, step S0 is also included: splicing two parts of carbon fiber shells up and down to form the arm body 1, wherein the two parts of carbon fiber shells are the upper half shell part and the lower half shell part of the arm body 1 respectively, splicing the two parts of carbon fiber shells left and right to form the direction control part 2, wherein the two parts of carbon fiber shells are the left half shell part and the right half shell part of the direction control part 2 respectively, and finally gluing the arm body 1 and the direction control part 2 together as a whole. In this way, the composite material processing is maximized while ensuring the strength of the fuselage, and the production cost is reduced. The integral molding connection between the 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 the positioning structure and locking structure required for installing the vertical tail can also be omitted, thereby reducing the risk of loosening, reducing weight, and eliminating the cost of related parts.

[0027] Furthermore, the middle portion 12 includes a wing assembly notch 3, which includes inclined portions 31 on both sides and a transverse 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 at various positions of the arm body 1 are in the shape of an inverted teardrop, especially the cross-sections at the positions 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.

[0028] A second embodiment of the present application further provides an aircraft, as shown in FIG4 , comprising a fuselage 4 and the aforementioned arm, which is 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 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 saving the cost of related parts.

[0029] 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 method for constructing an arm, applied to an aircraft, characterized in that: The arm comprises: an arm body (1) and a direction control part (2), and the arm construction method comprises the following steps: S1: integrally connecting the arm body (1) and the direction control part (2), wherein the direction control part (2) extends outward and presents a structure that gradually shrinks along a first direction, and the direction control part (2) comprises a streamlined surface structure to reduce the air resistance of the aircraft during flight.

2. The machine arm construction method according to claim 1, characterized in that: The direction control part (2) comprises a first part (21) and a second part (22), and the step S1 specifically comprises: connecting the first part (21) to the arm body (1) as a whole, wherein 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 construction method according to claim 1, characterized in that: The first direction is a direction away from the arm body (1).

4. The machine arm construction method according to claim 1, characterized in that: The direction control portion (2) extends downward and its thickness gradually decreases.

5. The machine arm construction method according to claim 1, characterized in that: The arm body (1) and the direction control part (2) are both made of carbon fiber. Before step S1, step S0 is also included: at least two parts of carbon fiber shells are spliced ​​up and down to form the arm body (1), and at least two parts of carbon fiber shells are spliced ​​left and right to form the direction control part (2).

6. The machine arm construction method 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 step S1 specifically comprises: integrally connecting the rear end portion (13) and the direction control portion (2).

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

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

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

10. An aircraft, characterized in that: The invention comprises a fuselage (4), and an arm formed by the assembly of the method for constructing an arm according to any one of claims 1 to 9, wherein the arm is assembled on the fuselage (4).

Images