Solar powered unmanned aerial vehicle transport device

Abstract

The utility model relates to a solar unmanned plane transport device, including truckle (1), chassis (2), shock absorber (3), side support board (4), support foam (5), support frame (6), fixed foam (7), lift wheel (8), container (9), transport frame fixed plate (10), container guide rail (11). The device can be repeatedly used, and the operation is convenient, safe and reliable, can satisfy the size and weight requirement of large -scale solar energy single -section size more than 10 meters, and the storage and transportation dress cost are reduced through the stacking package.

Description

Technical Field

[0001] This invention relates to the field of aviation technology, and more specifically to a large solar-powered unmanned aerial vehicle (UAV) transport device. Background Technology

[0002] Large solar-powered drones need to be disassembled, properly packaged, and transported when moving between assembly plants and various test flight sites to ensure the safety and integrity of the airframe structure and solar cells during transportation. Therefore, reusable, easy-to-operate, and safe and reliable transportation devices are crucial for the protection of large solar-powered drones.

[0003] Currently, most small drones are transported using flight cases, which cannot meet the size and weight requirements of large solar panel segments exceeding 10 meters. Existing solar panel drone transport methods utilize large metal box structures to transport segments longer than 10 meters, but these methods have the following drawbacks: 1. Storage stage: Solar-powered drones have large component sizes, occupying a lot of space in the factory. Distributed support structures can only support one component at a time, resulting in a large demand for tooling and further increasing the space occupied in the factory.

[0004] 2. Transportation stage: The separate packaging of each segment of the large solar-powered drone increases the manufacturing cost of the transportation equipment; and it requires the use of other hoisting equipment to stack and transport multiple segments, which is inconvenient to operate. Utility Model Content

[0005] To avoid the aforementioned technical defects in the background art, this utility model provides a solar-powered drone transportation device, including casters, chassis, shock absorbers, support plates, support foam, support frame, and fixing foam. The lower part of the chassis is connected to the casters, and the upper part of the chassis is connected to the support frame through the shock absorbers. Support plates are provided on the sides of the support frame, and the support frame supports the various components of the disassembled aircraft through multiple support foam pieces connected to it. Among them, multiple wing components are arranged alternately with their trailing edges facing inward. The fuselage components are detachably placed on the top layer of the support frame and fixed by fixing foam.

[0006] Furthermore, the support frame is provided with a connector fixing seat and a connector fixing strap. The connector fixing seat supports the connector of the UAV wing, and the connector fixing strap works with the fixing cable to press the connector from above.

[0007] Furthermore, the fuselage component is placed at an angle on the fuselage support frame located at the top of the support frame, and the fuselage component is provided with a joint, which is connected to a fuselage joint tensioner provided on the support frame.

[0008] Furthermore, the fuselage support frame is a detachable component, connected to the support frame by pins.

[0009] Furthermore, it includes a lifting device connected to the support frame, which can adjust the horizontal height of the support frame.

[0010] Furthermore, the lifting device consists of multiple sets of lifting wheels, symmetrically arranged on the support frame and threadedly connected thereto.

[0011] Furthermore, at least a portion of the supporting foam is curved to conform to the curvature of the aircraft component it supports.

[0012] Furthermore, at least a portion of the supporting foam is provided with grooves to avoid protrusions of aircraft components.

[0013] Furthermore, it also includes a container, a transport frame fixing plate, and a container guide rail. The chassis is connected to the container guide rail via the transport frame fixing plate, and the container guide rail is connected to the bottom frame of the container.

[0014] Furthermore, the container is a double-door container with doors on both sides, and the transport rack fixing plate is connected to the chassis and container rails by threaded connection.

[0015] This utility model offers convenient transportation operations. Multiple drone wing segments exceeding 10 meters in length can be placed sequentially into corresponding positions on the transport device without relying on other hoisting equipment. Only 2-3 people are required to perform the function. When storing drones in a factory or hangar without transportation, the transport device can be used as a drone segment support, allowing for direct power-on testing. This saves factory and hangar space and indoor handling workload, achieving multiple uses and reducing costs. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of a solar-powered drone transport assembly consisting of a large solar-powered drone transport device after aircraft components are installed. Figure 2 This is the lower structure of the transport frame of the transport device of this utility model; Figure 3 This is the upper structure of the transport frame of the transport device of this utility model; Figure 4 This utility model relates to the fixed structure of the transport frame of the transport device; Figure 5 This utility model relates to the lifting structure of a transport device; Figure 6 This utility model relates to the fixing structure of the body components of the transport device; Figure 7 This is another perspective on the fuselage component fixing structure of the transportation device of this utility model; Figure 8 This utility model relates to the container component structure of a transportation device; Figure 9It is a large solar drone that needs to be disassembled, packaged, and transported. Detailed Implementation

[0017] For ease of description, the direction perpendicular to the paper and outwards will be called "front," and the opposite direction will be called "back." The vertically upward direction will be called "up," and the opposite direction will be called "down."

[0018] The embodiments of this utility model are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this utility model, and should not be construed as limiting this utility model. All other embodiments obtained by those skilled in the art based on the embodiments of this utility model without inventive effort are within the scope of protection of this utility model.

[0019] In this utility model, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0020] See Figure 1 The disassembled aircraft components B of the large solar-powered drone are stacked and secured sequentially onto transport rack A. Transport rack A is then pushed into container C and secured, forming the large solar-powered drone transport assembly D. Finally, it is transported via container. If only the aircraft components are placed on transport rack A, power can be supplied through inter-section extension cables for powering and debugging each section, avoiding the need for significant space occupation within the factory.

[0021] See Figure 9 A component B, after being disassembled from a large solar-powered unmanned aerial vehicle (UAV), includes wing components B-1 through B-4 with a relatively wide chord length, a fuselage component B-5, and a vertical tail component, wherein the vertical tail component includes a left vertical tail B-6 and a right vertical tail B-7. It is packaged and transported using the transport device of this invention.

[0022] Transport support A includes a lower structure and an upper structure. See also... Figure 2The lower structure supports the weight of aircraft component B and includes casters 1, chassis 2, and shock absorbers 3. Casters 1 are pre-installed and feature braking and omnidirectional rotation with a directional lock. Chassis 2 has threaded holes 2-1 at its ends for subsequent securing during transport. Multiple shock absorbers 3 are evenly distributed between the chassis and the upper structure of the transport support A; they can be screwed or welded together to cushion vibrations during transport. See also... Figure 3 The upper structure includes side support plates 4, support foam 5, support frame 6, and fixing foam 7. The support frame 6, composed of several longitudinal and transverse beams, serves as the support frame for aircraft components. For wing components B-1 to B-4 with a relatively wide chord length, they can be arranged alternately with the trailing edges facing inwards (as shown in the attached diagram). Figure 9 and attached Figure 4 As shown in the figure, this cross-stacked arrangement increases space utilization, further saves space, and facilitates transportation.

[0023] Side support plates 4 are provided on the sides of frame 6, and are connected to the support frame 6 to assist in the longitudinal stiffness of the longitudinal beams of support frame 6. There can be one or more side support plates, such as multiple sets of side support plates including upper side support plate 4-1, lower side support plate 4-2, etc. Support foam 5 is divided into support foam groups for each section, such as section one support foam 5-1, section two support foam 5-2, section three support foam 5-3, section four support foam 5-4, section five support foam 5-5, and section six support foam 5-6, which support aircraft parts B-1 to B-6 respectively. Each group of foam supports one large section or multiple small sections. As needed, the support foam 5 is designed with curved conformal surfaces for heavier parts and straight groove designs for lighter parts to reduce manufacturing costs. Grooves are reserved on the support foam 5 as partial avoidance points 5.a for protruding parts of the parts. All support foams 5 are installed on the support frame 6 and directly contact and support the aircraft parts. The fixed foam 7 is used as a small component to fix the top of the support frame 6. Together with the fixed cable, it applies appropriate preload to the tail component and plays a role in safe fixation.

[0024] See Figure 4 The support frame 6 is provided with a component joint fixing seat 6-2 and a joint fixing strap 6-3. The joint fixing seat 6-2 supports the wing joint, and the joint fixing strap 6-3 works with the fixing cable 6-6 to press the component joint from above, thus completing the component fixing.

[0025] See Figure 5 The lifting structure includes lifting wheels 8. The lifting wheels 8 are configured as left lifting wheel 8-1 and right lifting wheel 8-2, with 4 sets on each side, all connected to the support frame 6 by screws. When moving in and out of containers, the height of the lifting wheels 8 can be adjusted step-by-step from front to back, allowing the entire transport rack to move in and out of containers in a straight line.

[0026] As attached Figure 6 Appendix Figure 7 As shown, fuselage component B-5 is placed at an angle on the top layer of support frame 6, specifically on fuselage support frame 6-5. Fuselage component B-5 has a connector, which is connected and secured via fuselage connector tensioner 6-4. Fuselage support frame 6-5 is a detachable component, detachably connected to the main structure of support frame 6 via quick-release pins 6-5.a. It is temporarily disassembled when placing wing component B-4 to facilitate its installation. The angled arrangement of the top fuselage section further reduces the width and height of the container, resulting in a compact structure that facilitates transportation.

[0027] As attached Figure 8 As shown, the container assembly consists of container 9, transport rack fixing plates 10, and container guide rails 11. Container 9 can be a double-door container with doors on both sides; there are multiple transport rack fixing plates 10. Figure 8 There are four in the middle, used to connect the chassis 2 and the container guide rail 11; the container guide rail 11 is welded or threaded to the bottom frame of the container, and an interface is reserved on the chassis 2 for connecting the transport frame fixing plate 10, which can be set as a threaded hole 10.a.

[0028] The above embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit it. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A solar-powered unmanned aerial vehicle (UAV) transport device, comprising casters (1), chassis (2), shock absorbers (3), support plates (4), support foam (5), support frame (6), and fixing foam (7), characterized in that: The chassis (2) is connected to the casters (1) at the bottom and the chassis (2) is connected to the support frame (6) via the shock absorber (3) at the top. The support frame (6) is provided with a support plate (4) on the side. The support frame (6) supports the various parts of the aircraft after disassembly by multiple support foams (5) connected to it. Among them, multiple wing parts are arranged alternately with their rear edges facing inward. The fuselage parts are detachably placed on the top layer of the support frame (6) and fixed by fixing foams (7).

2. The solar-powered unmanned aerial vehicle (UAV) transport device as described in claim 1, characterized in that: The support frame (6) is provided with a connector fixing seat (6-2) and a connector fixing strap (6-3). The connector fixing seat (6-2) supports the connector of the UAV wing, and the connector fixing strap (6-3) works with the fixing cable (6-6) to press the connector from above.

3. The solar-powered unmanned aerial vehicle (UAV) transport device as described in claim 1, characterized in that: The fuselage component (B-5) is placed at an angle on the fuselage support frame (6-5) located at the top of the support frame (6). The fuselage component (B-5) is provided with a connector that is connected to the fuselage connector tensioner (6-4) provided on the support frame (6).

4. The solar-powered unmanned aerial vehicle (UAV) transport device as described in claim 3, characterized in that: The fuselage support frame (6-5) is a detachable component, which is connected to the support frame (6) by a pin (6-5.a).

5. The solar-powered unmanned aerial vehicle (UAV) transport device as described in claim 1, characterized in that: It includes a lifting device (8) which is connected to the support frame (6) and can adjust the horizontal height of the support frame (6).

6. The solar-powered unmanned aerial vehicle (UAV) transport device as described in claim 5, characterized in that: The lifting device (8) consists of multiple sets of lifting wheels, symmetrically arranged on the support frame (6) and threadedly connected thereto.

7. The solar-powered unmanned aerial vehicle (UAV) transport device as described in claim 1, characterized in that: At least a portion of the supporting foam (5) is curved, designed to conform to the curvature of the aircraft component it supports.

8. The solar-powered unmanned aerial vehicle (UAV) transport device as described in claim 1, characterized in that: At least a portion of the supporting foam (5) is provided with grooves to avoid protrusions of aircraft components.

9. The solar-powered unmanned aerial vehicle (UAV) transport device as described in any one of claims 1-8, characterized in that: It also includes a container (9), a transport frame fixing plate (10), and a container rail (11). The chassis (2) is connected to the container rail (11) through the transport frame fixing plate (10), and the container rail (11) is connected to the bottom frame of the container (9).

10. The solar-powered unmanned aerial vehicle (UAV) transport device as described in claim 9, characterized in that: The container (9) is a double-door container on both sides. The transport rack fixing plate (10) is connected to the chassis (2) and the container guide rail (11) by means of threaded connection.

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