An unmanned aerial vehicle (UAV) control method includes: obtaining a distance between the UAV and a home point; obtain, based on the distance, a first image captured by photographing a home point with a first photographing device; sending the first image to a terminal device for display; and upon receiving a first control instruction sent by the terminal device, adjusting an attitude of the UAV based on the first control instruction. The present disclosure can improve the safety of the UAV during returning and landing. A UAV, a system and a storage medium are also provided.

A drone loaded with a package takes off from a takeoff device and uses a GPS system to fly to a user house that is a delivery destination of the package as the destination. Further, when the drone approaches the user house that is the destination, the flight of the drones is switched from autonomous navigation using the GPS system to remote control performed by a landing device and an in-house control device installed in the user house. The drone lands on the landing device by remote control from the landing device and the in-house control device, separates the package, and then returns to the warehouse using the GPS system and lands on the takeoff device.

The embodiments are a landing control method, an aircraft, and a storage medium. The method is applied to the aircraft, and includes: the current frame template image is subjected to image feature extraction, and the extracted image features are used to train the position filter and the scale filter of the first template image; the position information of the first template image in the next frame image is predicted by using the position filter and the scale filter; and the landing of the aircraft is corrected by using the position information, such that the aircraft can dynamically track the preset takeoff and landing point for landing, so as to realize the accurate landing of the aircraft.

A vision-based navigation method that does not depend on GPS signal for landing AAM aircraft. The Vision-Based Approach and Landing System (VALS) uses images captured from a camera for Advanced Air Mobility (AAM) approach and landing in GPS-denied environments, which offers a potential Alternative Position, Navigation, and Timing (APNT) solution. VALS utilizes a computer vision algorithm called Coplanar Pose from Orthography and Scaling with Iterations (COPOSIT) to estimate the position and orientation of the camera based on coplanar features. VALS also includes an extended Kalman filter that uses IMU measurements in a prediction step and the COPOSIT estimation results in a correction element. Combining IMU with vision creates a sensor fusion navigation solution for GPS-denied environments.

A landing method, etc., for a flight vehicle having directional characteristics, which can improve the landing performance of the flight vehicle having directional characteristics by turning the airframe in a nose direction with a good balance between lift and drag based on wind speed data and wind direction data related to the landing site. In the method for landing a flight vehicle of the present invention, the flight vehicle comprises to generate lift in response to wind from the nose direction of the airframe and based on wind speed data and wind direction data related to the landing site, the nose direction of the airframe is controlled and the descent of the airframe is initiated.

A system and a method for operating an aircraft during a descent phase of flight include a control unit configured to receive data regarding one or both of a current flight or one or more previous flights of the aircraft from one or more sensors of the aircraft. The control unit is further configured to determine efficient descent phase parameters for the aircraft based on the data. The aircraft is operated during the descent phase of one or both of the current flight or one or more future flights according to the efficient descent phase parameters.

Aspects described herein may relate to aerial structures such as aircraft. An aerial structure may include a fuselage, a wing attached to the fuselage, and a plurality of propulsion systems configured to generate thrust. A propulsion system may include a plurality of propulsors, such as propulsor fans. A propulsor fan may be configured to be actuated between a conventional take-off and landing (CTOL) flight mode, a short take-off and landing (STOL) flight mode, and a vertical take-off and landing (VTOL) flight mode.

An electromechanically steered passive directional arrays and ESA antenna with the rectangular apertures' mathematically separable radiation pattern array lattice rotated to rotate the higher cardinal plane side lobes to 45 relative to the vertical plane. Rotation minimizes clutter returns that mask weaker power returns and generates larger mean side lobe path loss. The higher sidelobe power levels are directed away from the critical area along the runway during approach. Individual array elements may be counter rotated to maintain desired antenna polarization state.

Systems and methods are provided for promoting stable aircraft approach conditions. The system comprises a display device that is onboard an aircraft and a controller in communication with the display device. The controller is configured to, by a processor: receive data that includes information relating to an action configured to stabilize an approach of the aircraft during landing thereof and a recommended timing of performing the action relative to a predetermined flight plan of the aircraft, and render a first visual element on the display device that is configured to display the action relative to the flight plan and dynamically indicate the recommended timing of performing the action relative to a geographic position of the aircraft along the flight plan.

A method, apparatus, system, and computer program product for controlling landing of a vertical landing vehicle. In one illustrative example, a method controls landing of a vertical landing vehicle. A landing profile for landing the vertical landing vehicle is determined by the computer system using a third derivative of a position equation, an initial position, an initial speed, a final speed, and a touchdown point for the vertical landing vehicle. Landing of the vertical landing vehicle is controlled using the landing profile.