Main wing cable-stayed adjustable device

Abstract

The utility model discloses a main wing cable-stayed adjustable device which comprises a fuselage and main wings, cable-stayed components are installed between two sides of the fuselage and two corresponding main wings, each cable-stayed component is composed of a cable-stayed steel wire, a connecting piece and an adjusting rod, the cable-stayed steel wire is connected with the fuselage through the connecting piece, and the adjusting rod is connected with the fuselage through the connecting piece. And the cable-stayed steel wire is connected with the main wing through an adjusting rod. The lower ends of the cable-stayed assemblies are installed on the two sides of the aircraft body, the upper ends of the cable-stayed assemblies are installed on the main wing lower fixing seats, after the aircraft lifts off and the main wings are subjected to upward lifting force, the cable-stayed assemblies are closed to enable the main wings to deform and bend under stress, at the moment, the cable-stayed assemblies can be pulled downwards, and the main wings and the aircraft body can always keep stable angles and controllable deformation. Meanwhile, the risk that the main wings are damaged is also reduced; due to the influence of machining precision in the production process, the length of the cable-stayed device cannot be unified, and the length must be adjustable; the length of the device is controlled by rotating the adjusting rod and through threads on the inclined pulling steel wire.

Description

Technical Field

[0001] This utility model relates to the field of model aircraft technology, specifically an adjustable main wing cable pull device. Background Technology

[0002] Most of the main wing tie rods on existing aircraft are fixed to the fuselage and main wing, making them impossible to disassemble quickly or adjust in length. This results in the main wing not being able to be removed separately in packaging, increasing packaging and transportation costs. In particular, the inability to adjust the length means that the tie rod may be too long or too short due to the limitations of manufacturing tolerances. This can easily lead to deformation of the main wing or the tie rod assembly due to prolonged tension on the main wing or bending of the tie rod assembly. Utility Model Content

[0003] The purpose of this invention is to provide an adjustable main wing cable pull device to solve the problems in the prior art.

[0004] To achieve the above objectives, this utility model provides the following technical solution: an adjustable main wing cable pull device, comprising a fuselage and a main wing, wherein cable pull assemblies are installed on both sides of the fuselage and between the corresponding two main wings, the cable pull assembly consists of cable pull steel wires, connectors and adjusting rods, the cable pull steel wires are connected to the fuselage through connectors, and the cable pull steel wires are connected to the main wings through adjusting rods.

[0005] Preferably, the inclined steel wire has a V-shaped structure, and the connector is provided with a collar for the inclined steel wire to pass through.

[0006] Preferably, the adjusting rod and the inclined steel wire are connected by a thread.

[0007] Compared with the prior art, the beneficial effects of this utility model are:

[0008] 1. The lower end of the cable-stayed assembly is installed on both sides of the fuselage, and the upper end is installed on the fixed base under the main wing. After the aircraft takes off, the main wing is subjected to an upward lift force, which causes the main wing to deform and bend under the force. At this time, the cable-stayed assembly may pull it down, which can keep the main wing and the fuselage at a stable angle and controllable deformation, and at the same time reduce the risk of damage to the main wing.

[0009] 2. Due to the influence of processing precision during the production process, the length of the inclined cable device cannot be uniform and must be adjustable; this device controls the length by rotating the adjusting rod and connecting it to the thread on the inclined cable. Attached Figure Description

[0010] The accompanying drawings are provided to further illustrate the present invention and form part of the specification. They are used together with the embodiments of the present invention to explain the present invention, but do not constitute a limitation thereof. In the drawings:

[0011] Figure 1 This is a schematic diagram of the structure of this utility model;

[0012] Figure 2 This is the front view of this utility model;

[0013] Figure 3 This is a bottom view of the present invention;

[0014] Figure 4 This is a side view of the present invention;

[0015] Figure 5 This is a structural schematic diagram of the inclined cable assembly of this utility model.

[0016] In the diagram: 1. Fuselage; 2. Main wing; 3. Cable tie assembly; 31. Cable tie wire; 32. Connector; 33. Adjusting rod. Detailed Implementation

[0017] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this utility model. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model. Therefore, the following detailed description of the embodiments of this utility model provided in the accompanying drawings is not intended to limit the scope of the claimed utility model, but merely to represent selected embodiments of this utility model.

[0018] Please see Figure 1-5 In this embodiment of the present invention, an adjustable main wing cable pull device includes a fuselage 1 and a main wing 2. Cable pull assemblies 3 are installed on both sides of the fuselage 1 and between the corresponding two main wings 2. Each cable pull assembly 3 consists of a cable pull wire 31, a connector 32, and an adjusting rod 33. The cable pull wire 31 is connected to the fuselage 1 through the connector 32 and to the main wing 2 through the adjusting rod 33. The cable pull wire 31 has a V-shaped structure. The connector 32 is provided with a collar for the cable pull wire 31 to pass through. The adjusting rod 33 and the cable pull wire 31 are connected by threads. The lower end of the cable pull assembly is installed on both sides of the fuselage, and the upper end is installed on the lower fixed seat of the main wing. After the aircraft takes off, the main wing is subjected to an upward lifting force, which causes the main wing to deform and bend under the force. At this time, the cable pull assembly can pull downward, so that the main wing and the fuselage can always maintain a stable angle and controllable deformation, while also reducing the risk of damage to the main wing. Due to the influence of processing precision during production, the length of the inclined cable device cannot be uniform and must be adjustable. This device controls the length by rotating the adjusting rod and connecting it to the thread on the inclined cable.

[0019] The working principle of this invention is as follows: the lower end of the cable-stayed assembly is installed on both sides of the fuselage, and the upper end is installed on the fixed base under the main wing. After the aircraft takes off, the main wing is subjected to an upward lift force, causing it to deform and bend. At this time, the cable-stayed assembly pulls it downward, ensuring that the main wing and fuselage maintain a stable angle and controllable deformation, while also reducing the risk of damage to the main wing. Due to the influence of processing precision during the manufacturing process, the length of the cable-stayed device cannot be standardized and must be adjustable. This device controls the length by rotating the adjusting rod, which is connected to the thread on the cable-stayed steel wire.

[0020] Finally, it should be noted that the above description is merely a preferred embodiment of this utility model and is not intended to limit the utility model. Although the utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. A main wing adjustable cable pull device, comprising a fuselage (1) and a main wing (2), characterized in that: A cable-stayed assembly (3) is installed on both sides of the fuselage (1) and between the two corresponding main wings (2). The cable-stayed assembly (3) consists of a cable-stayed steel wire (31), a connector (32), and an adjusting rod (33). The cable-stayed steel wire (31) is connected to the fuselage (1) through the connector (32), and the cable-stayed steel wire (31) is connected to the main wing (2) through the adjusting rod (33).

2. The adjustable main wing cable-stayed device according to claim 1, characterized in that: The inclined steel wire (31) has a V-shaped structure, and the connector (32) is provided with a collar for the inclined steel wire (31) to pass through.

3. The adjustable main wing cable-stayed device according to claim 2, characterized in that: The adjusting rod (33) and the inclined steel wire (31) are connected by a thread.

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