13 results about "Automatic landing" patented technology

An automatic landing control method for a large-scale fixed-wing unmanned aerial vehicle. The method comprises: dividing a landing phase of an unmanned aerial vehicle into an approach level flight phase, a final approach glide slope phase, a first landing flare phase, a second landing flare phase and a landing rollout phase; in the approach level flight phase, controlling the unmanned aerial vehicle to maintain a target level flight speed and a target approach level flight altitude, and to align a lateral offset and a track angle with a runway extended centerline and track the runway extended centerline; in the final approach glide slope phase, controlling the unmanned aerial vehicle to maintain a target glide speed and a target glide angle; in the first landing flare phase, controlling the unmanned aerial vehicle to maintain a target vertical speed and an airspeed; in the second landing flare phase, controlling the unmanned aerial vehicle to maintain the target vertical speed and the airspeed; and in the landing rollout phase, controlling the unmanned aerial vehicle to decelerate to 0, and at the same time, controlling the unmanned aerial vehicle to maintain a target lateral offset and a target heading angle and keep same on a runway centerline. The control method enables precise control over the automatic landing of an unmanned aerial vehicle, thereby greatly improving the robustness and safety of the automatic landing of the unmanned aerial vehicle.

The application provides an automatic landing method for a power inspection unmanned aerial vehicle in a landing stage, and the main design includes or is based on: 1, a landing gear structure design based on multiple sensors; 2, a judgment logic considering multiple ground contact conditions; 3, an automatic landing method for the power inspection unmanned aerial vehicle in the landing stage, which comprises landing area judgment and landing process sensing, that is, a complete landing detection scheme is provided in the landing-ground contact stage of the power inspection unmanned aerial vehicle, the ground sensor and the unmanned aerial vehicle antenna are integrated on the landing gear, the load of the machine body is reduced, the design complexity is reduced, the design cost and time of the machine body of the unmanned aerial vehicle are reduced, the safety of the unmanned aerial vehicle in the landing-ground contact stage is improved, the cost of the machine body of the unmanned aerial vehicle is reduced, and the inspection efficiency of the unmanned aerial vehicle is improved.

This invention discloses a dynamic obstacle avoidance and automatic landing optimization system for unmanned aerial vehicles (UAVs) in multiple scenarios and across the entire domain, relating to the fields of UAV defense and environmental perception technology. The method includes: controlling a scanning UAV equipped with a camera array to collect spatial and ground images, simultaneously acquiring attitude and positioning data; a processing center preprocessing and seamlessly stitching the images to generate a panoramic image of the entire environment; fusing multi-source monitoring data to form a complete dataset covering both indoor and outdoor environments; constructing a multi-index evaluation model to identify safe, landable areas through semantic segmentation and target detection; transmitting environmental data to a receiving device, guiding it to automatically aim and send appropriate landing commands. This invention achieves 360-degree, all-around environmental detection without blind spots, expands the coverage of landable areas, and improves the accuracy of safe area identification and the coordination between scanning and landing.

A system and method of transmitting an aircraft report (AIREP) from a first aircraft having an enabled aircraft autoland system includes retrieving, via a first processing system, standard AIREP data from one or more avionic systems within the first aircraft, the standard AIREP data including standard AIREP reporting information. The first processing system retrieves autoland enablement data that indicates whether the autoland system was manually or automatically enabled, and also retrieves autoland information data from the one or more avionics systems, where the autoland information data includes current aircraft state data and current flight plan data and is different from the standard AIREP data. The autoland information data is appended to the standard AIREP data to generate an AIREP-autoland message and the AIREP-autoland message is transmitted.

This invention discloses an intelligent monitoring system and method for low-altitude unmanned service stations, relating to the field of low-altitude intelligent logistics and transportation monitoring. The system includes: an intelligent control center for global task scheduling, resource coordination, status monitoring, and remote management; multiple service stations, each including a takeoff and landing platform, a door control device, a charging / battery swapping interface, and an identification module; and an intelligent aircraft docking module for enabling automatic landing, identification, charging, and task data interaction for UAVs. This intelligent monitoring system and method for low-altitude unmanned service stations achieves "unmanned operation, remote monitoring, and self-recovery from anomalies" through the establishment of unmanned service stations. Furthermore, by establishing a dynamic adaptation model between flight tasks and ground resources, it supports high-frequency and diverse task operations. Based on the collaboration of edge intelligence and central intelligence, it ensures stable station operation and high task completion rates.

The utility model discloses a prefabricated cabin rainproof pressure relief valve, including the installation in the cabin pressure relief mouth outside position's flap, including the installation in the cabin pressure relief mouth inside position's self -inclined louver, still have the frame between the flap and the pressure relief mouth, and the frame is fixed to the pressure relief mouth side side, and the flap upside position has the pin shaft, is used for with the frame corresponding upside position flip type hinged installation, the downside position of frame is provided with the magnetic attraction piece, is used for the magnetic attraction type fixed flap downside. The cabin internal pressure normal state, the flap automatic drooping, and the magnetic attraction closes, when the battery in the cabin appears the fault, produces VOC, CO gas time, in order to prevent the explosion, and the pressure rise effect pushes open the flap, and the flap turns over, and the downside appears the pressure relief side, and the pressure relief is completed after the pressure balance, and the flap automatic landing forms the seal, prevents dust and rainwater etc. from entering the cabin inside.

An embodiment provides convergent tracking for Global Navigation Satellite System (GNSS) signals (e.g., binary offset carrier (BOC), etc.) in GNSS applications, such as positioning, navigation, timing, and guidance. The embodiment employs a situation-aware two-dimensional (2D) routing algorithm that provides fast convergence to stable tracking. Further, an embodiment may provide subcarrier phase ambiguity resolution that resolves carrier phase with assurance to support high integrity navigation, including high integrity real-time kinematic (RTK) applications. Moreover, an embodiment may provide tracking to more accurate subcarrier phase estimates. This may provide up to four times better ranging accuracy. Accordingly, an embodiment provides robust tracking performance of BOC signals under varying levels of dynamics, high jamming tolerance, more ranging accuracy, support for high integrity navigation, and support for high integrity RTK based positioning and high precision navigation and automatic landing.

This application belongs to the field of unmanned aerial vehicle (UAV) control technology, and provides a method and apparatus for automatic landing control of UAVs. The method includes: collecting operational state parameters and environmental disturbance data of the UAV during the automatic landing phase; determining the dynamic model and landing constraints of the UAV landing process based on the operational state parameters and environmental disturbance data; constructing a multi-objective fitness function for evaluating landing performance based on the landing constraints; globally optimizing the landing control parameters of the UAV using a particle swarm optimization algorithm, with the goal of optimizing the multi-objective fitness function, to determine the target landing control parameters; and controlling the UAV to complete the automatic landing based on the target landing control parameters. This application improves the landing accuracy and attitude stability of UAVs in disturbed environments, and achieves safe, accurate, and efficient autonomous landing of UAVs in complex scenarios such as strong winds and turbulence without relying on precise mathematical models.

This invention discloses a fixed-wing automatic landing method based on inverse dynamics planning and time-varying LQR, relating to the field of aerospace control technology. This method addresses the nonlinear dynamic characteristics of fixed-wing aircraft during the landing phase by proposing a control scheme combining inverse dynamics trajectory planning and a time-varying linear quadratic regulator. Based on initial landing conditions and the ideal touchdown point, an exponential function is used to plan the altitude and descent rate trajectory, and the ideal pitch angle and pitch rate reference trajectory are obtained by inverse solving the longitudinal inverse dynamics model of the aircraft, establishing consistent physical constraints. An augmented objective function based on state deviation is constructed, and the time-varying feedback gain matrix and feedforward compensation vector are obtained by solving the time-varying matrix Riccati equation. The proposed method can more smoothly track the ideal landing trajectory, significantly reduce vertical velocity and attitude errors during landing, and improve the safety and comfort of the automatic landing process.

This invention relates to the field of unmanned aerial vehicle (UAV) technology and discloses an automatic landing method for UAVs, comprising the following steps: S1 pre-landing preparation; S2 landing point safety prediction; S3 dynamic adjustment and interaction of landing point; S4 autonomous return and phased landing; S5 dynamic target identification, prediction and obstacle avoidance; S6 landing feedback and self-check. It possesses advantages such as quantifiable safety assessment, dynamic trajectory prediction, remote interactive landing point adjustment, and phased adaptive landing, thus solving the problem of accidents easily occurring during UAV landing.

This invention discloses a control method for safe landing of a UAV in abnormal barometer data states. It is based on a dual-loop cascade PID control algorithm for UAV barometer altitude hold-up, with an outer loop of altitude and an inner loop of velocity. The altitude measurement value of the altitude loop and the velocity measurement value of the velocity loop are respectively obtained by fusing the relative altitude H of the UAV measured by the barometer as the observation value and fusing the UAV IMU data using a Kalman filter algorithm. 融合 and fusion speed V 融合 The control method of this invention is not easily affected by barometer fluctuations, and can control the drone throttle more stably and linearly, reducing the possibility of full-amplitude throttle fluctuations, thereby improving the stability and robustness of drone landing, avoiding problems such as large-scale drone ascent and descent, and the drone's payload becoming lighter, resulting in the inability to reach the target speed. The control method of this invention can be unified into the automatic landing mode to simplify the control logic and improve the robustness of control.

This invention relates to an automatic landing method and system for unmanned aerial vehicles (UAVs). The method includes: acquiring and calculating the position of the UAV based on real-time visible light images and real-time infrared images to obtain a first calculated position and a second calculated position; fusing the ranging distance, the first calculated position, and the second calculated position according to a fusion strategy to obtain a fused position of the UAV, thereby guiding the UAV to land in a target area. The fusion strategy includes: when both the first and second calculated positions are obtained simultaneously, using either the first calculated position or the second calculated position as the fused position based on the error between the first calculated position and the ranging distance; when the real-time visible light images and real-time infrared images are incomplete, and the ranging distance of the UAV is less than a second preset value, using either the first calculated angle or the second calculated angle, along with the ranging distance, as the fused position. The method of this invention can improve the positioning and recognition accuracy and reliability during the UAV landing process.