公开(公告)号：EP4368504A1

公开(公告)日：2024-05-15

申请号：EP23209861.6

申请日：2023-11-14

申请人： Autoflight (Kunshan) Co., Ltd.

发明人： TIAN, Yu

IPC分类号： B64C27/26 ,  B64C29/00 ,  B64D27/30 ,  B64U10/16 ,  B64U10/25 ,  B64U20/00

CPC分类号： B64U20/65 ,  B64U10/16 ,  B64U10/25 ,  B64U20/00 ,  B64U50/19 ,  B64D27/30 ,  B64C27/26 ,  B64C29/0008 ,  B64C29/0025

摘要： An aircraft and its associated aircraft linear support arms. The aircraft linear support arms include at least a rotor motor (1) and a propeller (100). The rotor motor (1) is connected to the propeller (100), and the linear support arm has a cross-sectional shape of an inverted teardrop shape. The streamlined structure of the inverted teardrop-shaped arm can reduce eddy currents formed by the propeller's downwash flow due to interference caused by the aircraft body, thereby reducing the wear and tear of the lift motor (1) and increasing the efficiency of the lift motor (1).

公开(公告)号：EP4239432A1

公开(公告)日：2023-09-06

申请号：EP21885233.3

申请日：2021-10-28

申请人： Autoflight (Kunshan) Co., Ltd.

发明人： JU, Han

IPC分类号： G05D1/10 ,  G01C21/20

摘要： A three-dimensional trajectory planning method and apparatus, a device, and a storage medium is disclosed. The method includes: according to a driving mode, horizontal position information and heading information of a starting point, and horizontal position information and heading information of a target point, determining a horizontal Dubins path from the starting point to the target point; determining a vertical Dubins path from the starting point to the target point according to height information of the starting point and height information of the target point; and determining a three-dimensional driving trajectory from the starting point to the target point according to the horizontal Dubins path and the vertical Dubins path.

公开(公告)号：EP4220086A1

公开(公告)日：2023-08-02

申请号：EP21871490.5

申请日：2021-09-22

申请人： Autoflight (Kunshan) Co., Ltd.

发明人： QIAN, Shaochen

IPC分类号： G01C21/16

摘要： This application discloses an initialization method, device, medium and electronic equipment of an integrated navigation system. The method comprises: acquiring the current motion state estimation of the aircraft and the sensor measurement values; acquiring the motion state estimation values by filtering according to the current motion state estimation and the attributes of the sensor measurement values, and obtaining the motion state estimation prediction results by performing the prediction based on the motion state estimation values; inputting the motion state estimation values into Kalman linear filter to initialize the Kalman linear filter if the motion state estimation prediction results converge; and correcting the integrated navigation system according to the initialized Kalman linear filter.