CN210681125U - Control surface skin for small aircraft - Google Patents
Control surface skin for small aircraft Download PDFInfo
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- CN210681125U CN210681125U CN201921736383.3U CN201921736383U CN210681125U CN 210681125 U CN210681125 U CN 210681125U CN 201921736383 U CN201921736383 U CN 201921736383U CN 210681125 U CN210681125 U CN 210681125U
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- skin
- control surface
- skin body
- small aircraft
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The application belongs to the field of aircraft structure design, and particularly relates to a control surface skin for a small aircraft, which comprises a skin body, wherein elongated protrusions are arranged on the surface of the skin body along the course direction, the number of the protrusions is multiple, and the protrusions are parallel and uniformly distributed on the skin body along the control surface unfolding direction; the skin body and the protruding portion are integrally formed components of metal plates and metal plates. According to the control surface skin for the small aircraft, the skin is made of metal materials through a sheet metal process, the stability and the strength of the skin are improved through a method of designing the reinforcing stems on the skin, the number of the wing ribs and the number of the fastening pieces can be reduced in the using process, and the structural weight and the manufacturing cost are reduced.
Description
Technical Field
The application belongs to the field of aircraft structural design, in particular to control surface skin for a small aircraft.
Background
Small general-purpose aircraft are, for their purpose, generally low-speed, low-altitude aircraft; in consideration of factors such as manufacturing cost and structural weight, the skin structure is usually designed into a sheet metal thin skin structure made of aluminum alloy materials, the thickness of the skin is more than 1mm, in order to ensure the stability of the thin skin when the thin skin is subjected to pneumatic load, more wing ribs are usually designed to support the skin, the wing ribs are connected with the skin through fasteners, and the structural weight and the manufacturing cost are increased.
SUMMERY OF THE UTILITY MODEL
In order to solve at least one of the technical problems, the application provides a control surface skin for a small airplane.
The application discloses a control surface skin for a small airplane, which comprises a skin body, wherein strip-shaped protruding portions are arranged on the surface of the skin body along the course direction, the number of the protruding portions is multiple, and the protruding portions are parallel and uniformly distributed on the skin body along the control surface unfolding direction; wherein
The skin body and the protruding portion are integrally formed components of metal plates and metal plates.
According to at least one embodiment of this application, the bellying is triangle-shaped along the cross-section of control surface exhibition direction, the apex angle department on triangle-shaped cross-section and with both sides base angle department that the covering body links to each other all is provided with the fillet.
According to at least one embodiment of this application, covering body and bellying are aluminium alloy plate panel beating integrated into one piece component.
The application has at least the following beneficial technical effects:
according to the control surface skin for the small aircraft, the skin is made of metal materials through a sheet metal process, the stability and the strength of the skin are improved through a method of designing the reinforcing stems on the skin, the number of the wing ribs and the number of the fastening pieces can be reduced in the using process, and the structural weight and the manufacturing cost are reduced.
Drawings
FIG. 1 is a schematic structural view of a control surface skin for a small aircraft according to the present application;
FIG. 2 is a knot size diagram of an embodiment of a control surface skin for a small aircraft according to the present application;
fig. 3 is a use state diagram of the control surface skin for the small aircraft according to the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "central," "longitudinal," "lateral," "front," "back," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like may be used in the orientations and positional relationships indicated in the drawings for the convenience of description and simplicity of description, but do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed in a particular orientation, and be operated in a particular manner, and are not to be considered limiting of the scope of the present application.
The control surface skin for a small aircraft according to the present application is described in further detail below with reference to fig. 1 to 3.
The application discloses a control surface skin for a small airplane, which comprises a skin body 1, wherein a strip-shaped bulge part 11 (namely a reinforcing stem) is arranged on the surface of the skin body 1 along the course direction; and the quantity of bellying 11 is a plurality of, and a plurality of bellyings 11 are parallel and evenly arranged along control plane spanwise direction on covering body 1.
In addition, the skin body 1 and the convex part 11 are integrally formed (manufactured by a sheet metal process) by sheet metal plates. Further, in this embodiment, the skin body 1 and the protruding portion 11 are aluminum alloy plate and metal plate integrated components, so that the stemmed skin is light in weight and the manufacturing process is mature and reliable.
Further, as shown in fig. 2, the cross section of the protruding portion 11 along the spanwise direction of the control surface is preferably triangular, and rounded corners are disposed at the top corners of the triangular cross section and at the bottom corners of the two sides connected to the skin body 1.
It should be noted that, the number, the interval, the size of the protruding portion 11, the size of each rounded corner, and the like of the protruding portions 11 may be optimally designed according to actual needs, as shown in fig. 2, in a specific embodiment, preferably, the thickness of the skin body 1 is about 0.406mm, the height of the protruding portion 11 is about 10mm, the width of the bottom of the protruding portion 11 is about 12mm, the radius of the rounded corner at the top corner is equal to 1.5mm, and the radius of the rounded corner at the bottom corners at both sides is equal to 2 mm; in addition, the distance between two adjacent bosses 11 is about 90 mm.
To sum up, the control surface skin for the small aircraft is made of metal materials through a sheet metal process, the stability and the strength of the skin are improved through a method of designing the reinforcing stems on the skin, the number of wing ribs and fasteners can be reduced in the using process, and the structural weight and the manufacturing cost are reduced.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (3)
1. The control surface skin for the small airplane is characterized by comprising a skin body (1), wherein strip-shaped protruding portions (11) are arranged on the surface of the skin body (1) along the course direction, the number of the protruding portions (11) is multiple, and the protruding portions (11) are arranged on the skin body (1) in parallel and uniformly along the control surface unfolding direction; wherein
The skin body (1) and the protruding portion (11) are integrally formed components of metal plates and metal plates.
2. The rudder surface skin for a small airplane according to claim 1, wherein the cross section of the bulge part (11) along the spanwise direction of the rudder surface is triangular, and fillets are arranged at the top corners of the triangular cross section and the bottom corners of two sides connected with the skin body (1).
3. The rudder surface skin for a small airplane according to claim 1, wherein the skin body (1) and the boss (11) are integrally formed members of aluminum alloy plates.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921736383.3U CN210681125U (en) | 2019-10-16 | 2019-10-16 | Control surface skin for small aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921736383.3U CN210681125U (en) | 2019-10-16 | 2019-10-16 | Control surface skin for small aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210681125U true CN210681125U (en) | 2020-06-05 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921736383.3U Active CN210681125U (en) | 2019-10-16 | 2019-10-16 | Control surface skin for small aircraft |
Country Status (1)
| Country | Link |
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| CN (1) | CN210681125U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111591433A (en) * | 2019-11-12 | 2020-08-28 | 中国科学院兰州化学物理研究所 | Flexible skin and preparation method and application thereof |
-
2019
- 2019-10-16 CN CN201921736383.3U patent/CN210681125U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111591433A (en) * | 2019-11-12 | 2020-08-28 | 中国科学院兰州化学物理研究所 | Flexible skin and preparation method and application thereof |
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