Fixed-wing unmanned aerial vehicle launcher suitable for all wind directions and multiple terrains

Abstract

The utility model discloses a fixed-wing unmanned aerial vehicle launcher suitable for all wind directions and multiple terrains, comprising: a frame for supporting a fixed-wing unmanned aerial vehicle, four corners of which are provided with outer stay bars; the rack is arranged on the upper bracket, and the upper bracket is connected with the lower bracket through an adjusting mechanism and used for adjusting the direction of the rack; the inner supporting rod is arranged on the lower bracket and is used for adjusting the height of the rack; according to the utility model, the five fulcrums land simultaneously, if the wind direction is changed, the height of the four fulcrums on the periphery is adjusted, rotation is carried out by taking the middle fulcrum as the circle center, and the direction of the launcher is rapidly adjusted, so that the time of processes such as secondary erection and calibration of a launching angle can be shortened, the efficiency is improved, and meanwhile, more launching terrains can be met.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicle launching devices, in particular to a fixed-wing unmanned aerial vehicle launching rack applicable to all wind directions and various terrains. Background Art

[0002] At present, most medium and low-speed fixed-wing unmanned aerial vehicles / target drones take off by combining a launching rack with a booster. The take-off process is affected by various factors such as weather and airspace. After erection and debugging are completed, it is very difficult to take off in time. Sometimes, it is also necessary to adjust the launching direction according to meteorological changes and mission requirements. The overall design of the launching rack is basically the same, mainly composed of a front support assembly, a rear support assembly, a rack body, a movable vertical rod, etc. It is made of alloy material and uses basic fixing and assembling methods such as bolts and studs. This structure results in cumbersome assembly and slow erection of the launching rack, and it is very difficult to change the launching direction after being fixed. When the wind direction changes, it is impossible to quickly adjust the launching angle to achieve all-weather headwind take-off. Especially for terrains such as mountains and the seaside, the environment is complex and the wind direction changes frequently, which requires repeated erection and delays the launching progress. Content of the Utility Model

[0003] The main purpose of the utility model is to provide a fixed-wing unmanned aerial vehicle launching rack applicable to all wind directions and various terrains, aiming to solve the existing technical problems.

[0004] To achieve the above object, the utility model provides a fixed-wing unmanned aerial vehicle launching rack applicable to all wind directions and various terrains, including:

[0005] A rack for supporting a fixed-wing unmanned aerial vehicle, with outrigger rods provided at its four corners;

[0006] An upper support seat and a lower support seat, the rack is arranged on the upper support seat, and the upper support seat is connected to the lower support seat through an adjusting mechanism for adjusting the direction of the rack; and,

[0007] An inner support rod is arranged on the lower support seat for adjusting the height of the rack.

[0008] Further, the rack includes a first frame body and a second frame body, the first frame body and the second frame body form a rectangular frame structure, and the ends of the first frame body and the second frame body are inserted into each other, and rotating shafts connected to the upper support seat penetrate through the first frame body and the second frame body near the insertion end.

[0009] Further, the adjusting mechanism includes an adjusting block connected to the bottom of the upper support seat, the adjusting block is hinged to a support seat, the support seat is arranged on a rotating disk, the rotating disk is embedded in the lower support seat, and side support rods respectively connected to the first frame body and the second frame body are arranged on both sides of the rotating disk.

[0010] Further, the outer walls of the first frame body and the second frame body near the insertion end are provided with convex ribs, the inner wall of the upper support seat is provided with grooves adapted to the convex ribs, and the length of the convex ribs is less than the distance from the axis of the rotating shaft to the ends of the first frame body and the second frame body.

[0011] Further, a guide rail is provided on the rotating disk, and the end of the side support rod is slidably matched with the guide rail through a slider.

[0012] Further, a wind speed meter is further included, which is detachably arranged on the lower support seat and is used for measuring wind speed data.

[0013] Further, a gear groove is formed in the side wall of the rotating disk, a gear driven by a motor is arranged in the lower support seat, and the gear is meshed with the side wall of the rotating disk to drive the rotating disk to drive the frame to rotate.

[0014] Further, notches for the first frame body and the second frame body to rotate are formed at the bottoms of both ends of the upper support seat.

[0015] The beneficial effects of the present utility model are embodied in:

[0016] In the present utility model, by landing with five fulcrums simultaneously, if the wind direction changes, by adjusting the heights of the 4 fulcrums around, rotating with the middle fulcrum as the center, and quickly adjusting the direction of the launch rack, the time for the processes such as secondary erection and calibration of the launch angle can be reduced, the efficiency is improved, and at the same time, more launch terrains can be satisfied. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 is a schematic structural diagram of the present utility model;

[0018] Figure 2 is a schematic top view of the structure of the upper support seat of the present utility model;

[0019] Figure 3 is a schematic connection diagram of the rotating disk and the internal gear structure of the present utility model.

[0020] DESCRIPTION OF THE REFERENCE NUMERALS

[0021] 100, frame; 101, outer support rod; 102, first frame body; 103, second frame body; 104, rotating shaft; 105, convex rib; 200, upper support seat; 300, lower support seat; 400, inner support rod; 500, adjusting block; 501, support; 502, rotating disk; 503, side support rod; 504, guide rail; 505, gear; 506, motor; 600, wind speed meter. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0022] Next, the technical solutions in the embodiments of the present utility model will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all the embodiments. Without conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present utility model without creative efforts shall fall within the protection scope of the present utility model.

[0023] Please refer to Figure 1 , the present utility model provides a fixed-wing UAV launch rack applicable to all wind directions and various terrains, including:

[0024] The frame 100 is used to support the fixed-wing UAV, and outer support rods 101 are provided at its four corners;

[0025] The upper support seat 200 and the lower support seat 300, the frame 100 is arranged on the upper support seat 200, and the upper support seat 200 is connected to the lower support seat 300 through an adjustment mechanism for adjusting the direction of the frame 100; and,

[0026] The inner support rod 400 is arranged on the lower support seat 300 for adjusting the height of the frame 100.

[0027] In this embodiment, the five fulcrums land simultaneously. If the wind direction changes, by adjusting the heights of the 4 fulcrums around, and rotating with the middle fulcrum as the center, the direction of the launch rack can be quickly adjusted, which can reduce the time of the processes such as secondary erection and calibration of the launch angle, improve the efficiency, and at the same time can also meet more launch terrains.

[0028] Specifically, both the outer support rod 101 and the inner support rod 400 can adopt hydraulic rods.

[0029] In an embodiment, the frame 100 includes a first frame body 102 and a second frame body 103. The first frame body 102 and the second frame body 103 form a rectangular frame structure, and the ends of the first frame body 102 and the second frame body 103 are inserted into each other. Rotating shafts 104 connected to the upper support seat 200 penetrate through both the first frame body 102 and the second frame body 103 near the insertion ends.

[0030] With such a setting in this embodiment, by detachably connecting the first frame body 102 and the second frame body 103, after the UAV launch task is completed, the first frame body 102 and the second frame body 103 can be separated and rotated upward for folding, which is convenient for transfer and reduces the difficulty of transportation and transfer.

[0031] In one embodiment, the adjusting mechanism includes an adjusting block 500 connected to the bottom of the upper support base 200. The adjusting block 500 is hinged to a support base 501. The support base 501 is arranged on a rotating disk 502. The rotating disk 502 is embedded in the lower support base 300. Side support rods 503 respectively connected to the first frame body 102 and the second frame body 103 are arranged on both sides of the rotating disk 502.

[0032] With such an arrangement in this embodiment, when it is necessary to adjust the launching angle according to the wind direction, by driving the rotating disk 502 to act, the upper support base 200 is driven to rotate, so that the orientation of the frame 100 can be quickly adjusted. At the same time, by driving the side support rods 503 on both sides to act, the overall launching angle of the frame 100 can also be adjusted to meet different launching requirements.

[0033] In one embodiment, please refer to Figure 1 and Figure 2 , convex ridges 105 are arranged on the outer walls of the first frame body 102 and the second frame body 103 near the insertion end. Grooves adapted to the convex ridges 105 are formed in the inner wall of the upper support base 200. The length of the convex ridges 105 is less than the distance from the axis of the rotating shaft 104 to the ends of the first frame body 102 and the second frame body 103.

[0034] With such an arrangement in this embodiment, through the setting of the convex ridges 105, the connection strength between the first frame body 102 and the second frame body 103 can be improved after they are butted. At the same time, when the first frame body 102 and the second frame body 103 are separated, they are synchronously separated from the upper support base 200, so that the upward rotation and folding of the first frame body 102 and the second frame body 103 are not affected, and the applicability is good.

[0035] In one embodiment, a guide rail 504 is arranged on the rotating disk 502. The end of the side support rod 503 is in sliding fit with the guide rail 504 through a slider.

[0036] With such an arrangement in this embodiment, through the cooperation between the slider and the guide rail 504, the side support rod 503 can move synchronously when the first frame body 102 and the second frame body 103 are separated, so as to ensure that the first frame body 102 and the second frame body 103 are driven to rotate upward and fold subsequently, avoiding the problem of obstruction.

[0037] In one embodiment, a wind speed meter 600 is further included, which is detachably arranged on the lower support base 300 and is used for measuring wind speed data.

[0038] In one embodiment, please refer to Figure 1 and Figure 3 , a gear groove is formed in the side wall of the rotating disk 502. A gear 505 driven by a motor 506 is arranged in the lower support base 300. The gear 505 is meshed and connected with the side wall of the rotating disk 502 and is used for driving the rotating disk 502 to drive the frame 100 to rotate.

[0039] In this embodiment, the rotating disk 502 is driven by the motor 506 to rotate, so as to quickly adjust the orientation of the frame 100, reduce the difficulty of manual adjustment, and improve the launching efficiency.

[0040] In one embodiment, notches for the first frame body 102 and the second frame body 103 to rotate are formed at the bottoms of both ends of the upper support base 200.

[0041] In this embodiment, when the first frame body 102 and the second frame body 103 rotate upward and fold, their bottom ends can pass through the notches at both ends of the upper support base 200, avoiding the problem that the upper support base 200 blocks the first frame body 102 and the second frame body 103 from rotating to the vertical state due to the rotation radius.

[0042] It should be noted that if there are directional indications such as up, down, left, right, front, back... in the embodiments of the present utility model, the directional indications are only used to explain the relative position relationship and movement conditions between components in a specific posture as shown in the drawings. If the specific posture changes, the directional indications will also change accordingly.

[0043] In addition, if there are descriptions involving "first", "second", etc. in the embodiments of the present utility model, the descriptions of "first", "second", etc. are only for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one such feature. In addition, the meaning of "and / or" appearing throughout the text includes three parallel solutions. Taking "A and / or B" as an example, it includes solution A, solution B, or the solution where A and B are satisfied simultaneously. In addition, "a plurality" means two or more. In addition, the technical solutions between various embodiments can be combined with each other, but it must be based on the fact that those skilled in the art can implement them. When the combination of technical solutions results in contradictions or cannot be implemented, it should be considered that such a combination of technical solutions does not exist.

[0044] The above are only the preferred embodiments of the present utility model and are not intended to limit the present utility model. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present utility model shall be included within the protection scope of the present utility model.

Claims

1. A fixed-wing UAV launcher suitable for all wind directions and multiple terrains, characterized in that ,include: A frame (100) is used to support a fixed-wing UAV, and has external support rods (101) at its four corners; an upper supporting seat (200) and a lower supporting seat (300), the frame (100) being arranged on the upper supporting seat (200), the upper supporting seat (200) being connected to the lower supporting seat (300) via an adjusting mechanism for adjusting the direction of the frame (100); and The inner support rod (400) is arranged on the lower support seat (300) and is used to adjust the height of the frame (100).

2. A fixed-wing UAV launcher suitable for all wind directions and multiple terrains as claimed in claim 1, characterized in that: The frame (100) comprises a first frame body (102) and a second frame body (103), wherein the first frame body (102) and the second frame body (103) form a rectangular frame structure, and the ends of the first frame body (102) and the second frame body (103) are plugged into each other, and a rotating shaft (104) connected to the upper bracket (200) passes through the first frame body (102) and the second frame body (103) near the plug-in end.

3. A fixed-wing UAV launcher suitable for all wind directions and multiple terrains as claimed in claim 2, characterized in that: The adjustment mechanism comprises an adjustment block (500) connected to the bottom of the upper support seat (200), the adjustment block (500) is hinged to the support seat (501), the support seat (501) is arranged on a rotating disk (502), the rotating disk (502) is embedded in the lower support seat (300), and side support rods (503) are respectively connected to the first frame body (102) and the second frame body (103) on both sides of the rotating disk (502).

4. The fixed-wing UAV launcher suitable for all wind directions and multiple terrains as claimed in claim 2, characterized in that: The first frame (102) and the second frame (103) are provided with ridges (105) on the outer walls near the plug-in ends, and the inner wall of the upper bracket (200) is provided with grooves adapted to the ridges (105), and the length of the ridges (105) is less than the distance from the axis of the rotating shaft (104) to the ends of the first frame (102) and the second frame (103).

5. The fixed-wing UAV launcher suitable for all wind directions and multiple terrains as claimed in claim 3, characterized in that: A guide rail (504) is provided on the rotating disk (502), and the end of the side support rod (503) is slidably matched with the guide rail (504) via a slider.

6. The fixed-wing UAV launcher suitable for all wind directions and multiple terrains as claimed in claim 1, characterized in that: It also includes an anemometer (600) which is detachably arranged on the lower support seat (300) and is used to measure wind speed data.

7. The fixed-wing UAV launcher suitable for all wind directions and multiple terrains as claimed in claim 3, characterized in that: The side wall of the rotating disk (502) is provided with a gear groove, and the lower support seat (300) is provided with a gear (505) driven by a motor (506). The gear (505) is meshedly connected with the side wall of the rotating disk (502) and is used to drive the rotating disk (502) to drive the frame (100) to rotate.

8. The fixed-wing UAV launcher suitable for all wind directions and multiple terrains as claimed in claim 2, characterized in that: The bottoms of both ends of the upper support seat (200) are provided with notches for the first frame (102) and the second frame (103) to rotate.

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