Flight control mounting structure of fixed-wing unmanned aerial vehicle

Abstract

According to the flight control mounting structure of the fixed-wing unmanned aerial vehicle, a boss is downwards arranged on the middle section of a wing and sinks into a fuselage, and the boss sinks and is integrally formed; the boss comprises an upper-layer boss, a middle-layer boss and a lower-layer boss; the flight controller is mounted on the middle-layer boss and can be arranged on the lower-layer boss, and a mounting space is provided between the lower-layer boss and the middle-layer boss for the flight controller; a screw column is arranged on the upper boss and is used for mounting a flight control cover plate; the second low-position connecting piece is provided with a threading hole used for leading in a flight control connecting line, and the flight control connecting line is fixed to the second low-position connecting piece through a line clamp. The flight controller is installed in the middle wing, the idle space of the aircraft body is fully utilized, the load space is not occupied, and the carrying performance of the unmanned aerial vehicle is improved; the flight controller is arranged on the rear half part of the wing, a wing main beam and a twisting box are not damaged, the sinking is integrally formed, and the influence on the strength of the wing is small; the flight controller is convenient to install and maintain, is located near the center of the unmanned aerial vehicle, and is sensitive to attitude change of the unmanned aerial vehicle.

Description

Technical Field

[0001] The present application belongs to the technical field of unmanned aerial vehicles, and in particular to a flight control installation structure for a fixed-wing unmanned aerial vehicle. Background Art

[0002] With the rapid development of the UAV field, fixed-wing UAVs are increasingly being used in production and life. Unmanned aircraft, referred to as "drones", are unmanned aircraft that are controlled by radio remote control equipment and self-contained program control devices, or are operated completely or intermittently autonomously by on-board computers. The flight control plays a vital role in the normal flight of UAVs. The UAV flight control is the central control component of the UAV. It is responsible for controlling and managing all aspects of the aircraft to ensure that the UAV can perform flight missions stably, safely and reliably; it is the control center of the UAV and plays a decisive role in the normal operation of the UAV.

[0003] Fixed-wing drones are large in size and usually require more sensors, interfaces, and computing resources, so the flight control needs a larger area to accommodate these components. In the prior art, installing the flight control inside the fuselage will, on the one hand, take up the load space and weaken the drone's load performance to a certain extent; on the other hand, the flight control needs to be maintained or replaced. The flight control is installed inside the drone, and the drone's shell or other components need to be disassembled before it can be operated. This will increase the complexity and time cost of maintenance, especially in the wild environment or in bad weather.

[0004] In view of the above problems, the appropriate flight control installation position is a problem that needs to be considered in modern UAV design. In order to solve the problem of UAV flight control installation, this paper proposes a fixed-wing UAV flight control installation structure. Utility Model Content

[0005] The present application provides a fixed-wing UAV flight control installation structure, the flight control occupies the load space and has the problem of complex maintenance.

[0006] To achieve the above objectives, this application provides the following solutions:

[0007] A fixed-wing UAV flight control installation structure, the flight control is installed on the middle section wing of the wing, especially on the rear half of the middle section wing, a boss is formed downward on the middle section wing and sunk into the inside of the fuselage; the boss is arranged on the rear half of the wing and is sunken and concave as a whole.

[0008] The bosses include an upper boss, a middle boss, and a lower boss;

[0009] The upper boss is connected to the middle boss via a first low-position connecting piece, and the middle boss is connected to the lower boss via a second low-position connecting piece.

[0010] Furthermore, the first low-position connecting member and the second low-position connecting member are both connecting members with an inclination, and the inclination of the first low-position connecting member is consistent with the inclination of the second low-position connecting member; the flight control is installed on the middle-level boss and can be placed on the lower-level boss, and an installation space is provided for the flight control between the lower-level boss and the middle-level boss; a screw column is provided on the upper-level boss for installing the flight control cover; the second low-position connecting member is provided with a threading hole for introducing the flight control connecting line, and is fixed to the second low-position connecting member with a wire clip.

[0011] Furthermore, the position of the boss is selected to avoid the main load-bearing components and the wing main beam, and the boss is designed together with the wing, and the whole is molded in batches without setting a separation surface, thereby reducing the impact on the strength of the wing.

[0012] Beneficial effects of the technical solution of this application:

[0013] In this application, the flight control is installed in the middle wing, which can make full use of the idle space of the fuselage without occupying the load space, thus improving the carrying performance of the UAV to a certain extent.

[0014] The present application installs the flight control in the rear half of the wing, does not damage the wing main beam and the torsion box, and forms a sunken and concave overall shape, which has little effect on the wing strength.

[0015] In the present application, the boss is sunken into a plane, which is convenient for installing the flight control, and is located near the center of the drone, so it is sensitive to the change of the drone's attitude.

[0016] In the present application, the bosses are multi-layer steps, and the joints are inclined, which increases the overall streamline of the drone, does not affect the overall shape and normal flight of the drone, and is easy to disassemble, facilitating the maintenance of the flight control. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For those skilled in the art, other drawings can be obtained based on these drawings without creative labor.

[0018] Figure 1 It is a schematic diagram of the mid-wing structure of a fixed-wing UAV flight control installation structure;

[0019] Figure 2 It is a schematic diagram of the flight control installation position of a fixed-wing UAV flight control installation structure;

[0020] Figure 3 It is a structural schematic diagram of a fixed-wing UAV flight control mounting structure boss;

[0021] FIG4 is a top view of a fixed-wing UAV flight control mounting structure boss;

[0022] Reference numerals:

[0023] 10. Flight control; 20. Middle wing; 30. Wing; 40. Boss; 401. Upper boss; 402. Middle boss; 403. Lower boss; 404. First low-position connector; 405. Second low-position connector; 406. Screw column; 407. Threading hole. DETAILED DESCRIPTION

[0024] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of this application.

[0025] In order to make the above-mentioned objects, features and advantages of the present application more obvious and easy to understand, the present application is further described in detail below in conjunction with the accompanying drawings and specific implementation methods.

[0026] like Figure 1 As shown, a fixed-wing UAV flight control installation structure, the flight control 10 is installed on the middle wing 20 of the wing 30, especially on the rear half of the middle wing 20, and a boss 40 is made downward on the middle wing 20 and sunk into the fuselage; the boss 40 is set at the rear half of the wing 30 and is sunken and concave as a whole.

[0027] The boss 40 includes an upper boss 401, a middle boss 402, and a lower boss 403;

[0028] The upper boss 401 is connected to the middle boss 402 via a first low-position connecting member 404 , and the middle boss 402 is connected to the lower boss 403 via a second low-position connecting member 405 .

[0029] The first low-position connecting member 404 and the second low-position connecting member 405 are both connecting members with an inclination, and the inclination of the first low-position connecting member 404 is consistent with the inclination of the second low-position connecting member 405; the flight control 10 is installed on the middle-level boss 402 and can be placed on the lower-level boss 403, and an installation space is provided for the flight control 10 between the lower-level boss 403 and the middle-level boss 402; a screw column 406 is provided on the upper-level boss 401 for installing the flight control 10 cover; the second low-position connecting member 405 is provided with a threading hole 407 for introducing the flight control 10 connecting wire, which is fixed to the second low-position connecting member 405 with a wire clip.

[0030] It is worth noting that the position of the boss 40 is chosen to avoid the main load-bearing components of the wing 30 and the main beam of the wing 30. The boss 40 and the wing 30 are designed together and are molded as a whole in batches without setting a separation surface, thereby reducing the impact on the strength of the wing 30.

[0031] It is worth noting that this embodiment only shows an application example of a fixed-wing UAV flight control installation structure, but it does not mean that the fixed-wing UAV flight control installation structure provided by this application is only in this form. The specific structural form can be adjusted according to the specific UAV structure and flight control size.

[0032] In the description of the present application, it should be understood that the terms "front", "back", "up", "down", "outside", "inside", "horizontal", "top", "bottom", "surface", "bottom layer", "top layer", "upper", "lower", "bottom", "top", "inside", "surface", "center", "right", "middle" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0033] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "connected", "connected" and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection; it can be directly connected, or indirectly connected through an intermediate medium, or it can be the internal connection of two elements. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0034] The embodiments described above are only descriptions of the preferred methods of the present application, and are not intended to limit the scope of the present application. Without departing from the design spirit of the present application, various modifications and improvements made to the technical solutions of the present application by those skilled in the art should all fall within the scope of protection determined by the claims of the present application.

Claims

1. A fixed-wing UAV flight control installation structure, characterized in that: The flight control is installed on the middle section wing of the wing, installed on the rear half of the middle section wing, and a boss is made downward on the middle section wing to sink into the fuselage; The bosses include an upper boss, a middle boss, and a lower boss; The upper boss is connected to the middle boss via a first low-position connecting piece, and the middle boss is connected to the lower boss via a second low-position connecting piece.

2. A fixed-wing UAV flight control installation structure according to claim 1, characterized in that: The first low-position connecting member and the second low-position connecting member are both connecting members with an inclination, and the inclination of the first low-position connecting member is consistent with the inclination of the second low-position connecting member.

3. The fixed-wing UAV flight control installation structure according to claim 1, characterized in that: The flight control is installed on the middle boss and can be placed on the lower boss. An installation space is provided between the lower boss and the middle boss for the flight control. A screw column is provided on the upper boss for installing a flight control cover.

4. The fixed-wing UAV flight control installation structure according to claim 2, characterized in that: The second low-position connecting member is provided with a threading hole for introducing the flight control connecting wire, which is fixed to the second low-position connecting member with a wire clip.

5. The fixed-wing UAV flight control installation structure according to claim 1, characterized in that: The boss is arranged on the rear half of the wing and is sunken and integrally formed.

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