Secondary folding method for Y-shaped arm of unmanned aerial vehicle and unmanned aerial vehicle applying method

Abstract

The invention discloses a two-stage folding method for a Y-shaped arm of an unmanned aerial vehicle, and particularly relates to an efficient volume compression method applied to a heavy-load multi-rotor unmanned aerial vehicle. The method sequentially comprises the following steps: a first-stage horizontal folding step: rotating and folding four groups of Y-shaped vehicle arms towards the center of a vehicle body respectively so as to shorten the transverse wheelbase of the unmanned aerial vehicle; and a second-stage vertical folding step: integrally and downwards folding the horizontally folded arm assembly to the lower part of the fuselage. Through ordered two-stage folding actions, the storage volume of the unmanned aerial vehicle can be compressed to 13% of the working state of the unmanned aerial vehicle on the premise that the structural strength and the loading capacity are not sacrificed, so that the technical problem that a large unmanned aerial vehicle is difficult to transport, store and quickly deploy due to the large volume is fundamentally solved.

Description

Technical Field

[0001] This invention belongs to the field of unmanned aerial vehicle (UAV) technology, and specifically relates to a folding method for a two-stage folding arm with high payload and high folding ratio. Technical Background

[0002] Existing large transport drones (such as those with a maximum takeoff weight exceeding 500 kg) mostly feature fixed arm structures or only support single-stage horizontal folding. This design results in the drone occupying a significant amount of space even when not in operation, making it difficult to adapt to standardized transport vehicles (such as containers). This severely limits their rapid deployment and application in dynamic logistics scenarios and emergency responses. Furthermore, some folding designs sacrifice structural rigidity and load-bearing capacity, failing to meet the requirements of heavy-load operations. Therefore, there is an urgent need in this field for a novel technological solution that achieves a balance between high load-bearing capacity and an extremely compact storage volume. Summary of the Invention

[0003] To address the aforementioned technical problems, this invention provides a two-stage folding method for a UAV's Y-shaped arm, the specific steps of which are as follows:

[0004] Preparation phase: Confirm that the drone is in a standby state on the ground and that all propellers (if they are foldable propellers) are retracted.

[0005] First-level fold: Horizontal inward folding

[0006] Action Description: Control the four sets of Y-shaped arm assemblies to rotate horizontally around the vertical axis of the Y-shaped hinge (203) connected to the main arm (201). Figure 2 As shown in states A and B). Specifically, unlocking the Y-shaped folding joint ( Figure 3 The quick-release pin (232) in the main arm (201) folds the auxiliary arm (202) inward relative to the main arm (201), so that each arm is nearly parallel to the side wall of the fuselage.

[0007] Technical effect: After completing this step, the overall wheelbase of the drone is significantly reduced from 5.2 meters in the deployed state to 3.6 meters. Figure 4 This process utilizes the folding freedom provided by the Y-shaped structure and is the first key operation to achieve volume compression.

[0008] Second fold: Fold vertically downwards

[0009] Action Description: After all arms have completed horizontal retraction, control the second folding mechanism (204) at the connection between the arms and the fuselage to fold the entire "horizontally folded" arm assembly downwards by approximately 80 degrees around the horizontal axis, as shown. Figure 5 The states C and D in the diagram.

[0010] Technical effects: After this step, the UAV finally forms a regular cuboid configuration with a size of only 1.8m x 1.8m x 1.6m (as shown in Figure 5 ). This step is the core of achieving extreme space optimization, which reduces the final storage volume to 5.2m³, which can seamlessly adapt to the loading requirements of standard freight containers.

[0011] The beneficial effects of the present application are:

[0012] Method innovation: For the first time, the method of combining "Y-shaped arms" with "horizontal + vertical" two-stage folding is proposed, which realizes an unprecedented volume compression ratio through an orderly two-step dynamic process.

[0013] Maximize space efficiency: This method makes the UAV storage volume only 13% of the unfolded state, solving the core pain point of large UAV transportation and storage.

[0014] Non-destructive performance: The folding method cleverly avoids affecting the main load-bearing structure of the arm, combined with carbon fiber-titanium alloy composite materials and high-strength Y-shaped joints, ensuring that the UAV has excellent performance of 640kg maximum take-off weight and 400kg net load after unfolding, with a load ratio as high as 62.5%. BRIEF DESCRIPTION OF DRAWINGS

[0015] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following will briefly introduce the drawings needed to be used in the embodiment description.

[0016] Figure 1 is a structure schematic diagram of an unfolded state of an embodiment of the present application. Figure 2 is a structure schematic diagram of a top view Y-shaped arm folding process of an embodiment of the present application. Figure 3 is a structure exploded view of a Y-shaped folding joint in the present application. Figure 4 is a structure schematic diagram of a two-stage folding joint at the connection between the arm and the fuselage in the present application. Figure 5 is a state schematic diagram of the present application after completing the first stage (horizontal) folding. Figure 6 is a final storage state schematic diagram of the present application after completing the second stage (vertical) folding.

[0017] Figure 2 A-Y-shaped hinge in the unfolded state, B-Y-shaped hinge in the folded state

[0018] Figure 4 C-vertical hinge in the folded state, D-vertical hinge in the unfolded state

[0019] In the figure: 100 - fuselage; 201 - main arm; 202 - sub-arm; 231 - sub-arm sleeve; 232 - quick release pin; 233 - main arm sleeve; 234 - hinge body; 300 - motor.

Claims

1. A two-stage folding method of a UAV arm, applied to a UAV comprising a central fuselage and at least one Y-shaped arm assembly, the Y-shaped arm assembly comprising a main arm connected to the fuselage and a sub-arm hinged to the main arm, characterized in that, The method comprises the following steps: A first folding step: rotating the sub-arm in a horizontal plane relative to the main arm; A second folding step: folding the entire Y-shaped arm assembly after the first folding step in a vertical plane relative to the center fuselage.

2. The method of claim 1, wherein: The UAV includes four groups of Y-shaped arm assemblies arranged in 90° orthogonal symmetry outside the center fuselage, and the first folding step specifically includes rotating the sub-arm of all four groups of Y-shaped arm assemblies inward in a horizontal plane.

3. The method of claim 2, wherein: After the first folding step, the maximum lateral dimension (wheelbase) of the UAV is reduced from 5.2 meters to 3.6 meters.

4. The method of claim 1 or 2, wherein: The second folding step specifically includes folding all the horizontally folded Y-shaped arm assemblies downward and storing them under the center fuselage.

5. The method of claim 4, wherein: After the second folding step, the UAV as a whole forms a cuboid configuration with an external size of 1.8m x 1.8m x 1.6m.

6. The method of claim 1, wherein: The first folding step is realized by unlocking the locking mechanism in the Y-shaped folding joint between the main arm and the sub-arm.

7. The method of claim 1, wherein: By performing the complete first and second folding steps, the storage volume of the UAV is compressed to 13% of the volume in the fully unfolded state.

8. A delivery drone, comprising: It is configured to perform the two-stage folding method according to any one of claims 1 to 7.

9. The transport drone of claim 8, wherein: The UAV includes eight groups of coaxial dual-propeller power systems, respectively installed at the end of the sub-arm of the Y-shaped arm assembly, and the maximum take-off weight of the entire machine is 640kg, and the net load capacity is 400kg.

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