Aircraft and arm construction method thereof

Abstract

The invention relates to the technical field of aircrafts, and discloses an arm construction method. The arm construction method is applied to the aircraft, the arm comprises an arm body and a direction control part, and the arm construction method comprises the steps that S1, the arm body and the direction control part are integrally connected, the direction control part extends outwards and is of a structure gradually reduced in the first direction, and the direction control part comprises a streamline surface structure; therefore, air resistance during flight of the aircraft is reduced. According to the vehicle arm construction method, the vehicle arm body and the vertical fin are integrally formed and connected, 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 field of aircraft technology, and in particular to an aircraft and a method for constructing an aircraft 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 a method for constructing an arm thereof. The arm construction method of the present application realizes an integrally formed connection between the arm body and the vertical tail, which 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 aircraft arm construction method, which is applied to an aircraft, wherein the arm includes: an arm body and a direction control part, and 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 narrowing 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.

[0005] An aircraft comprises a fuselage, and an arm constructed according to the above-mentioned arm construction method, wherein the arm is assembled on the fuselage.

[0006] Optionally, the direction control part includes a first part and a second part, and the step S1 specifically includes: integrally connecting the first part with the arm body, 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.

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

[0008] Optionally, the direction controlling portion extends downward and its thickness gradually decreases.

[0009] Optionally, the arm body and the direction control part are both made of carbon fiber, and before step S1, step S0 is also included: splicing at least two parts of carbon fiber shells up and down to form the arm body, and splicing at least two parts of carbon fiber shells left and right to form the direction control part.

[0010] 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.

[0011] 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 matching and connecting with the fuselage.

[0012] 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.

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

[0014] Optionally, the arm includes a plurality of transverse support beams and a plurality of vertical support beams.

[0015] The arm construction method of the present application realizes an integral 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 eliminating related parts costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a schematic diagram showing the flow of the arm construction method of the first embodiment of the present application;

[0017] Figure 2 It is a schematic diagram showing the structure of the machine arm of the first embodiment of the present application;

[0018] Figure 3 It is a schematic structural diagram of the rear end portion of the machine arm of the first embodiment of the present application;

[0019] Figure 4 Shown is a schematic structural diagram of an aircraft according to a second embodiment of the present application. DETAILED DESCRIPTION

[0020] 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.

[0021] 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.

[0022] 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.

[0023] The following describes the first embodiment of the present application with reference to the accompanying drawings. Figure 1 The arm construction method of the present application includes the following steps:

[0024] 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.

[0025] Specifically, Figure 2 and Figure 3As shown, the arm construction method of the first embodiment of the present application is applied to an aircraft, and the arm includes: an arm body 1 and a direction control part 2. The arm body 1 includes a front end part 11, a middle end part 12 and a rear end part 13, and the arm construction method includes: connecting the rear end part 13 of the arm body 1 with the direction control part 2 as a whole. However, it can be understood that the direction control part 2 can also be connected to other parts, such as the middle end part 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, and some support beams 14 and support beams 15 are interwoven with each other to enhance the structural strength of the arm. The direction control part 2 includes a first part 21 and a second part 22, and the first part 21 is a stabilizer part. The above-mentioned arm construction method specifically includes: connecting the first part 21 with 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 air flow passing through the surface of the first part 21 when the aircraft is flying, thereby adjusting the flight direction of the aircraft. The direction control part 2 can be used as a vertical tail connected to the aircraft arm. A servo can be installed inside the first part 21. The second part 22 is used as a rudder surface 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 an arm body 1, wherein the two parts of carbon fiber shells are the upper shell part and the lower shell part of the arm body 1 respectively, splicing the two parts of carbon fiber shells left and right to form a direction control part 2, wherein the two parts of carbon fiber shells are the left shell part and the right shell part of the direction control part 2 respectively, and finally bonding the arm body 1 and the direction control part 2 together as a whole. In this way, the composite material processing is maximized and the production cost is reduced while ensuring the strength of the fuselage. The integral molding connection between the arm body and the vertical tail 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 eliminating the cost of related parts.

[0026] Further, the middle end portion 12 includes a wing assembly notch 3, the wing assembly notch 3 includes inclined portions 31 on both sides and a transverse portion 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.

[0027] The second embodiment of the present application also provides an aircraft, such as Figure 4 As shown, it includes a fuselage 4 and the above-mentioned arm, and the arm 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 weight, and saving related parts costs.

[0028] 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 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).

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