Wing quick release structure

Abstract

The utility model discloses a wing quick release structure which comprises a first wing spar, a second wing spar and hasp locks, the first wing spar and the second wing spar transversely penetrate through a fuselage, the two ends of the first wing spar and the two ends of the second wing spar are inserted into wings on the two sides of the fuselage respectively, and the contact positions of the wings and the fuselage are connected through the hasp locks. The wing is reasonable and ingenious in structural design, balance and stability of the wing are guaranteed through the two wing spars, and the wing can be conveniently and rapidly mounted and dismounted through the hasp locks.

Description

Technical Field

[0001] The utility model relates to a wing quick-detachable structure, in particular to a wing quick-detachable structure for a model airplane. Background Art

[0002] Some existing aircraft models are large. To reduce weight, they are often constructed from lightweight materials like foam plastic, which are not impact-resistant. Therefore, if the entire aircraft needs to be transported outdoors for flight or shipping, a large amount of space is required for the transport tools. Furthermore, the model is prone to bumps and collisions during transportation, causing damage. Assembled aircraft models can address these issues, but because the model must withstand significant air pressure after takeoff, the assembled structure must ensure stability during flight and be lightweight, otherwise it will affect flight stability. Utility Model Content

[0003] In order to overcome the above-mentioned deficiencies, the present invention provides a wing quick-disassembly structure, which is convenient and quick to use and has a stable structure.

[0004] To achieve this purpose, the structure adopted by the utility model is: a wing quick-release structure, including a first wing spar, a second wing spar and a buckle lock, the first wing spar and the second wing spar cross the fuselage, the two ends of the first wing spar and the second wing spar are respectively inserted into the wings on both sides of the fuselage, and the contact surface of the wings and the fuselage are connected to each other by a buckle lock.

[0005] The first wing spar is located at the front end of the fuselage, the second wing spar is located at the rear end of the fuselage, and the length of the first wing spar is smaller than that of the second wing spar.

[0006] The first spar and the second spar are carbon fiber tubes.

[0007] The beneficial effects are as follows: the utility model has a reasonable and ingenious structural design, the two wing spars ensure the balance and stability of the wing, and the buckle lock facilitates the rapid installation and disassembly of the wing. BRIEF DESCRIPTION OF THE DRAWINGS

[0008] The present invention will be described by way of examples with reference to the accompanying drawings, in which:

[0009] Figure 1 This is a bottom-up structural diagram of the present utility model;

[0010] Figure 2 It is a three-dimensional structural diagram of the utility model. DETAILED DESCRIPTION

[0011] The present invention will now be described in further detail with reference to the accompanying drawings, which are simplified schematic diagrams that illustrate the basic structure of the present invention in a schematic manner.

[0012] In the description of the utility model, it should be noted that the terms "upper," "lower," "inner," "outer," "front end," "rear end," "both ends," "one end," "the other end," and the like, indicating positions or relationships, are based on the positions or relationships shown in the accompanying drawings and are intended solely to facilitate the description of the utility model and simplify the description. They do not indicate or imply that the devices or components referred to must have a specific orientation, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limitations on the utility model. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0013] In the description of the utility model, it should be noted that, unless otherwise expressly specified or limited, the terms "installed," "provided with," "connected," etc., should be understood in a broad sense. For example, "connected" can mean a fixed connection, a detachable connection, or an integral 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, or it can be internal communication between two components; a fixed connection can be welding or gluing. Those skilled in the art will understand the specific meanings of the above terms in this utility model based on specific circumstances.

[0014] like Figure 1 、 Figure 2 The wing quick-release structure shown has two wings 2 symmetrically arranged on either side of the fuselage 1. The first spar 4 and the second spar 5 are two hollow tubes. The first spar 4 and the second spar 5 are parallel to each other and cross the fuselage 1. The first spar 4 and the second spar 5 extend beyond the fuselage 1 at both ends. The portions extending beyond the fuselage 1 are inserted into the wings 2 on both sides of the fuselage 1, so that the wings 2 on both sides remain balanced. A snap lock 3 is provided on the contact surface between the wing 2 and the fuselage 1, and the snap lock 3 enables quick installation and removal of the wing 2 and the fuselage 1. The first spar 4 is close to the front end of the fuselage 1, and the second spar 5 is close to the rear end of the fuselage 1. The length of the first spar 4 is shorter than the second spar 5, so that the wings 2 are evenly supported. The first spar 4 and the second spar 5 are carbon fiber tubes with a higher specific strength than steel tubes. While ensuring the support strength of the wing 2, the overall weight is reduced. A fixing plate is provided on the side of the wing 2 that contacts the fuselage 1 , and through holes are provided on the fixing plate corresponding to the first wing spar 4 and the second wing spar 5 . The buckle lock 3 is connected to the fixing plate, and the fixing plate is bonded to the fuselage.

[0015] The utility model has a reasonable and ingenious structural design, the two wing spars ensure the balance and stability of the wing, and the buckle lock facilitates the rapid installation and disassembly of the wing.

[0016] The above description is based on the present invention. Based on the above description, relevant personnel can make various changes and modifications without departing from the technical concept of this utility model. The technical scope of this utility model is not limited to the content of the specification. Its technical scope must be determined according to the scope of the claims.

Claims

1. Wing quick-release structure, characterized in that: The invention comprises a first wing spar (4), a second wing spar (5) and a buckle lock (3). The first wing spar (4) and the second wing spar (5) cross the fuselage (1). The two ends of the first wing spar (4) and the second wing spar (5) are respectively inserted into the wings (2) on both sides of the fuselage (1). The contact surfaces of the wings (2) and the fuselage (1) are connected to each other through the buckle lock (3).

2. The wing quick-release structure according to claim 1, characterized in that: The first wing spar (4) is located at the front end of the fuselage (1), the second wing spar (5) is located at the rear end of the fuselage (1), and the length of the first wing spar (4) is smaller than that of the second wing spar (5).

3. The wing quick-release structure according to claim 1, characterized in that: The first spar (4) and the second spar (5) are carbon fiber tubes.

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