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公开(公告)号：USD1032409S1
公开(公告)日：2024-06-25
申请号：US35515568
申请日：2022-10-24
设计人： Yu Tian
摘要： The patent or application file contains at least one drawing executed in color. Copies of this patent or patent application publication with color drawing(s) will be provided by the Office upon request and payment of the necessary fee.
1. Drone
FIG. 1.1 is a right elevation view of a drone;
FIG. 1.2 is a front elevation view thereof;
FIG. 1.3 is a rear elevation view thereof;
FIG. 1.4 is a top plan view thereof;
FIG. 1.5 is a perspective view thereof;
FIG. 1.6 is a bottom plan view thereof;
FIG. 1.7 is a left side view thereof;
FIG. 1.8 is another perspective view thereof;
FIG. 1.9 is another perspective view thereof; and
FIG. 1.10 is another perspective view thereof.
A new ornamental design for a drone as shown and described; the parts shown by means of green coloring in the reproductions are not part of the claimed design.-
公开(公告)号：US11952151B2
公开(公告)日：2024-04-09
申请号：US18161084
申请日：2023-01-29
发明人： Yu Tian
摘要： A vertical tail of a composite-wing unmanned aerial vehicle (UAV) having a body, a rudder face section, a rotor section, shock absorbing component and a quick installation assembly of circuit. The body includes a tail body frame and a shell. The rudder face section has a rudder machine and a rudder surface. The rudder surface is connected to one end of the tail for steering the directional deflection of the UAV. The shock absorbing component is connected to the lower end plate and the shock absorbing component absorbs the shock to the body. The quick installation assembly of circuit includes a plug, a positioning sleeve and a bias piece, the positioning sleeve is located on the outer circumference of the plug and slidingly connected to the plug, the bias piece is set between the plug and the positioning sleeve, the bias piece can absorb the impact on the plug.
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公开(公告)号：US11855387B2
公开(公告)日：2023-12-26
申请号：US18161087
申请日：2023-01-29
发明人： Yu Tian
IPC分类号： H01R13/627 , B64U30/10 , B64U20/70 , B64U50/30 , H01R13/631 , B64C1/26 , B64C1/30 , H01R4/50 , H01R12/91 , H01R13/62
CPC分类号： H01R13/6276 , B64U20/70 , B64U30/10 , B64U50/30 , H01R13/631 , B64C1/26 , B64C1/30 , H01R4/5058 , H01R12/91 , H01R13/62
摘要： A plug-in assembly structure for a UAV includes a first component (1), a second component (2) and a limit assembly (3). The first component (1) includes a first plug (11) and a positioning sleeve (12), and the positioning sleeve (12) is provided with a first through hole (121). The second component (2) includes a second plug (21), the radial direction of the second plug (21) is provided with a limit hole (2111), the second plug (21) can be electrically connected to the first plug (11), and the limit hole (2111) is facing the first through hole (121). The limit assembly (3) is installed in the limit hole (2111). The limit assembly (3) includes a first elastic element (31) and a limit element (32).
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公开(公告)号：US11820508B2
公开(公告)日：2023-11-21
申请号：US18058262
申请日：2022-11-22
发明人： Yu Tian
CPC分类号： B64C39/024 , B64U10/00 , B64U70/20 , B64U70/80 , B64U80/82
摘要： A combined vertical takeoff and landing UAV having a large vertical takeoff and landing UAV, a connecting device, and a small vertical takeoff and landing UAV. The connecting device having a clamping component and an adsorption component. The clamping component includes a clamping part, and a clamping groove is arranged on the clamping part. The clamping component having a snap-fitting part, and a snap-fitting groove is arranged on the snap-fitting part. The clamping groove and the snap-fitting groove are correspondingly set. A first holding space is arranged on the clamping part, and a second holding space is arranged on the snap-fitting part. The adsorption component comprises a first magnetic element located in the first holding space, and the adsorption component also comprises a second magnetic element, which is located in the second holding space.
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公开(公告)号：US20230303273A1
公开(公告)日：2023-09-28
申请号：US18191861
申请日：2023-03-28
发明人： Yu Tian
IPC分类号： B64U30/14
CPC分类号： B64U30/14
摘要： A quick-release wing structure includes a lock cylinder assembly and a lock head. The lock cylinder assembly is installed in the fuselage. The lock cylinder assembly includes a shell and a lock plate. An installation slot is opened inside the shell. The side wall of the installation slot is provided with a clamping hole connected with the installation slot. The lock plate is sliding and arranged in the installation slot. The lock head is installed in the wing. A locking slot is set on the periphery of the lock head. The lock head can pass through the clamping hole and drive the lock plate to move. When the locking slot is facing the lock plate, the lock head is clamped onto the locking slot and fixed. The UAV includes the quick-release wing structure described above.
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36.发明公开公开(公告)号：US20230230324A1
公开(公告)日：2023-07-20
申请号：US18157542
申请日：2023-01-20
发明人： Yu Tian
IPC分类号： G06T17/20
CPC分类号： G06T17/205
摘要： A method, a system, an equipment and a medium for modifying the layering layer information of finite element model (FEM) unit. The method includes: obtaining a unit ID to be modified; determining the file to be modified according to the unit ID to be modified; receiving the new layering layer attribute ID regarding to the unit ID to be modified inputted by user; and replacing the original layering layer attribute ID corresponding to the unit ID to be modified in the file to be modified with the new layering layer attribute ID to complete the modifying the layering layer information of FEM unit. The method can directly modify the layering layer information of the units in the model file, without importing the model file into the pre-processing software to modify it and then exporting it again, thereby reducing the workload of technical staff and saving development time.
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