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公开(公告)号：EP4219320A1
公开(公告)日：2023-08-02
申请号：EP23153179.9
申请日：2023-01-25
发明人： TIAN, Yu
IPC分类号： B64U60/50 , B64U40/10 , B64U30/40 , B64U20/80 , H01R13/627
摘要： The present invention relates to the technical field of unmanned aerial vehicle (UAV) and discloses a vertical tail for a composite-wing UAV, comprising: a body (1), a rudder face section (2), a rotor section (3), a shock absorbing component (4) and a quick installation assembly of circuit (5). The body (1) includes a tail body frame (11) and a shell (12). The rudder face section (2) comprises a rudder machine (21) and a rudder surface (22). The rudder surface (22) is connected to one end of the tail for steering the directional deflection of the UAV. The rudder machine (21) is used to drive the rudder surface (22). The shock absorbing component (4) is connected to the lower end plate (111) and the shock absorbing component (4) absorbs the shock to the body (1). The quick installation assembly of circuit (5) includes a plug (51), a positioning sleeve (52) and a bias piece (513), the positioning sleeve (52) is located on the outer circumference of the plug (51) and slidingly connected to the plug (51), the bias piece (513) is set between the plug (51) and the positioning sleeve (52), the bias piece (513) can absorb the impact on the plug (51). When the composite-wing UAV lands, the shock absorbing component (4) can absorb the energy generated by the rigid impact of the composite-wing UAV with the ground, and the quick installation assembly of circuit (5) can ensure the reliable connection of the electrical system of the composite-wing UAV, thus protecting the body of the composite-wing UAV and the internal electronic devices.
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公开(公告)号：EP4151540A1
公开(公告)日：2023-03-22
申请号：EP22196541.1
申请日：2022-09-20
发明人： YU, Tian
摘要： A long-distance drone is disclosed having a canard wing configuration with a cabin (270) attached to a left main wing (213) and a right main wing (214). There is a left forewing (211) and a right forewing (212) connected together to form a single-piece forewing. There is a left linear support (220) connecting the left forewing (211) to the left main wing (213), and a right linear support (221) connecting the right forewing (212) to the right main wing (214). A plurality of propellers is disposed on the left and the right linear supports (220, 221).
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公开(公告)号：EP4092824A2
公开(公告)日：2022-11-23
申请号：EP22174353.7
申请日：2022-05-19
发明人： TIAN, Yu
IPC分类号： H01M50/533
摘要： The application discloses a battery tab connection structure and a battery pack, which relates to the technical field of lithium batteries. The battery tab connection structure includes a first tab 1, a second tab 2 and a fastener 4, at least one of the first tab 1 and the second tab 2 is provided with a notch 11, the first tab 1 and the second tab 2 are inserted and fixed through the notch 11 and fit with each other, and the fastener 4 can be detachably and fixedly connected with the first tab 1 and the second tab 2. The application is provided with the notch 11 on at least one of the first tab 1 and the second tab 2, the first tab 1 and the second tab 2 are inserted and fixed through the notch 11 and fit with each other, and then detachably and fixedly connected with the first tab 1 and the second tab 2 through the fastener 4, so that the first tab 1 and the second tab 2 can ensure the insertion stability and fit of the two through the notch insertion. At the same time, it achieves the detachable fixation of the first tab 1 and the second tab 2, which is convenient for the disassembly and maintenance of a single tab, thus saving the economic cost.
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公开(公告)号：EP3708492A1
公开(公告)日：2020-09-16
申请号：EP20163169.4
申请日：2020-03-13
发明人： TIAN, Yu
摘要： A vertical takeoff and landing (VTOL) fixed-wing aircraft having overlapping propellers (131, 133, 135, 137) disposed on a top surface of each of the left and right lateral supports (130) connecting the left and right main and secondary wings (122, 124) and low hanging vertical stabilizers (140) disposed on the rear end of the aircraft. A vertical takeoff and landing (VTOL) fixed-wing aircraft having a plurality of propellers (131, 133, 135, 137) disposed on a top surface of each of the left and right lateral supports (130) connecting the left and right main and secondary wings (122, 124), wherein the propellers (134, 138) disposed at the rear end of the aircraft are vertically offset to the other propellers.
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公开(公告)号：EP4257427A1
公开(公告)日：2023-10-11
申请号：EP23166129.9
申请日：2023-03-31
发明人： TIAN, Yu
摘要： An aircraft transport trailer having a frame (100), a wheel assembly, a lower bracket, and an upper bracket. The wheel assembly is rotationally installed on the frame (100) to support and move the frame (100). The lower bracket is fixedly installed on the frame (100), and the top of the lower bracket is provided with a body slot. The preset first surface of the inner wall of the body slot is fitted with the part of the lower surface of the body, the aircraft body can be partially seated in the aircraft body slot under the action of gravity.
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公开(公告)号：EP4253227A1
公开(公告)日：2023-10-04
申请号：EP23164693.6
申请日：2023-03-28
发明人： TIAN, Yu
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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公开(公告)号：EP4212715A1
公开(公告)日：2023-07-19
申请号：EP23151494.4
申请日：2023-01-13
发明人： TIAN, Yu
摘要： An aircraft having an engine and a throttle thereof. The throttle has a throttle body (1), the throttle body (1) is provided with a cavity (10) and comprises an inlet port (11) and an outlet port (12) both of which are connected to the cavity (10); a plurality of fuel injectors (2), each of the fuel injectors (2) is arranged on the throttle body (1) and can spray fuel into the cavity (10) of the throttle body (1); and an air filter (3). The air filter (3) is arranged on the throttle body (1) and connected to the inlet port (11). There is an air door (4) that can rotate in the cavity (10) to connect or block the inlet port (11) and the outlet port (12). Additionally, there is an air door driving part connected to the air door (4) and controls the rotation of the air door (4).
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公开(公告)号：EP4180327A1
公开(公告)日：2023-05-17
申请号：EP22207366.0
申请日：2022-11-15
发明人： TIAN, Yu
IPC分类号： B64D1/22 , B66C1/38 , B64U101/64
摘要： The invention relates to the technical field of unmanned aerial vehicle manufacturing, and discloses an unmanned aerial vehicle (UAV). The UAV comprises an unmanned aerial vehicle body and a releasing mechanism, the releasing mechanism comprises a mounting piece and a reset component; the mounting piece is provided with a mounting groove; the opening direction of the mounting groove extends upwards; and a to-be-transported piece can be hooked in the mounting groove. The reset component is configured to deform under the gravity effect of the to-be-transported piece when the to-be-transported piece is lifted, and when the to-be-transported piece (100) lands to the ground, the reset component is reset to drive the to-be-transported piece to be separated from the mounting groove. During transportation, the to-be-transported piece is hooked to the bottom of the mounting groove under the gravity effect of the to-be-transported piece and deform the reset component. When the to-be-transported piece lands to the ground, the force of the to-be-transported piece on the reset component disappears, and the to-be-transported piece moves towards the opening direction of the mounting groove under the reset function of the reset component and is automatically separated from the mounting groove. The UAV can realize automatic releasing of a to-be-transported piece, the structure is simple and easy to realize, and can reduce the manufacturing cost of the UAV and improve the endurance ability of the UAV.
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公开(公告)号：EP4242114A1
公开(公告)日：2023-09-13
申请号：EP23160562.7
申请日：2023-03-07
发明人： TIAN, Yu
摘要： A data monitoring method, a data monitoring system, data monitoring equipment and a data monitoring medium. The method has: acquiring current vibration data of a target flight device in real time (S110); Determining an anomaly protection strategy of the target flight device based on the current vibration data (S120); The target flight equipment is controlled to execute corresponding operations (S130) according to an abnormality protection strategy. Embodiments of the invention, by acquiring the current vibration data of the target flight equipment in real time, determining an anomaly protection strategy of the target flight device based on the current vibration data.
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