公开(公告)号：US20220115631A1

公开(公告)日：2022-04-14

申请号：US17065540

申请日：2020-10-08

Applicant: Shanghai Autoflight Co., Ltd.

Inventor： Yu Tian

IPC: H01M2/10 ,  H01M10/655 ,  H01M10/6563 ,  H01M10/625 ,  B64C39/02 ,  B64D27/24 ,  B60L50/64 ,  B60L58/27 ,  B60L53/14

Abstract: An unmanned aerial vehicle battery transport box having a box body shell and an upper cover. The unmanned aerial vehicle battery transport box further having a heat dissipating device and a heating device. When the temperature in the box body is lower than the lower limit of the set temperature range, the heating device heats the box body. When the temperature in the box body is higher than the upper limit of the set temperature range, the heat dissipating device dissipates heat of the box body. The temperature in the box body is adjusted by the heating device and the heat dissipating device.

公开(公告)号：US20220111958A1

公开(公告)日：2022-04-14

申请号：US17067770

申请日：2020-10-12

Applicant: Shanghai Autoflight Co., Ltd.

Inventor： Yu Tian

IPC: B64C35/00 ,  B64C39/02

Abstract: An amphibious drone having a fuselage, a vertical tail, a wing and a take-off and landing device. The take-off and landing device is on the lower surface of the fuselage or the vertical tail or the wing. The take-off and landing device has a buoyancy unit and a power device, and the power device is capable of generating thrust to push the buoyancy unit to move. The take-off and landing device can be on the lower surface of the drone, and realizes the water support of the drone by symmetrically providing the take-off and landing device. At the same time, the take-off and landing device is further provided with a power device for pushing the drone to be started. The amphibious drone can take off and land by relying on the take-off and landing device, which can be disassembled to adapt to different usage conditions.

公开(公告)号：US10988255B1

公开(公告)日：2021-04-27

申请号：US16838048

申请日：2020-04-02

Applicant: Shanghai Autoflight Co., Ltd.

Inventor： Yu Tian

IPC: B64C39/02 ,  B64C1/08 ,  B64C27/00

Abstract: The present invention discloses a multi-rotor aircraft with a multi-axis misalignment layout, which comprises a frame, a plurality of upper power sources, a plurality of lower power sources, a plurality of upper propellers, and a plurality of lower propellers. The plurality of upper propellers are provided at intervals and are connected to the upper part of the frame through the plurality of upper power sources. The plurality of lower propellers are provided at intervals and are connected to the lower part of the frame through the plurality of lower power sources. In the vertical projection direction of the frame, the plurality of upper propellers and the plurality of lower propellers are staggered. The upper propellers and the lower propellers are staggered so that the pitch between the upper propellers and the lower propellers is large.