60 results about "Landing zone" patented technology

The invention provides a hovercar landing decision-making method and device based on heterogeneous multiple sensors, and the method comprises the steps: carrying out the semantic segmentation of an RGB image collected by a hovercar through a semantic segmentation model when the hovercar is in a low-altitude middle-layer region, obtaining a ground static obstacle, and determining a plurality of landing regions; determining an optimal landing area from the plurality of landing areas based on safety, energy consumption and interactivity evaluation; when the hovercar enters a low-altitude low-layer area, dynamic obstacles in an optimal landing area are detected through the collected RGB images and point cloud data; and performing dynamic prediction on the dynamic obstacles in the optimal landing area, establishing a risk potential field, and taking a point with the minimum risk value in the risk potential field as an optimal landing point. According to the method, frequent switching of the hovercar can be avoided, the landing path is optimized, and energy consumption is reduced.

The invention provides a heavy-load unmanned aerial vehicle landing point identification processing method and system based on visual identification, and relates to the technical field of computer vision, and the method comprises the steps: obtaining the airflow speed direction and airflow change data above a landing area of a heavy-load unmanned aerial vehicle, real-time flight data, and an enhanced panoramic image; based on the initial positioning position of the heavy-load unmanned aerial vehicle, the initial coordinates of the preset landing area and the flight task parameters, generating an initial landing trajectory to determine a qualified landing point position; based on the qualified landing point position, the enhanced panoramic image, the airflow velocity direction and the airflow change data, simulating a fuselage stress simulation result of the heavy-load unmanned aerial vehicle in the landing process; based on the qualified landing point position and the fuselage stress simulation result, obtaining corrected flight data; and based on the qualified landing point position and the corrected flight data, an optimized landing trajectory is obtained, and high-precision and high-stability landing control of the heavy-load unmanned aerial vehicle in a complex environment is realized.

A system and method for managing autonomous aerial vehicle ingress and payload exchange is disclosed. A beacon unit receives a digitally encoded ingress request from an autonomous aerial vehicle, the request comprising an identity token. A smart contract engine evaluates the identity token against mission-specific conditions to authorize ingress. An environmental analysis processor generates a map of the region surrounding the beacon unit using data from multiple sensor modules, including LiDAR, radar, infrared, audio, and weather sensors. A trajectory guidance engine computes an ingress path based on the environmental map. A virtual protected area generation module defines a three-dimensional protected zone for descent, and a classification engine assigns a safety classification to the zone based on predefined criteria. A beacon control interface transmits the ingress path to the vehicle and monitors descent for compliance. A user authentication subsystem verifies the identity of a human user at the landing zone prior to payload release.

The application discloses an aneurysm segmentation landing zone positioning and identifying method and system based on an optimal blood flow guiding model, and the method comprises the following steps: collecting image data of a target blood vessel region, and pre-processing the image data to obtain a blood vessel enhanced image; performing binaryzation on the blood vessel enhanced image to obtain a blood vessel cavity binary mask; extracting a tree-shaped blood vessel center line from the blood vessel enhanced image by using a blood vessel center line extraction algorithm; analyzing the tree-shaped blood vessel center line to obtain a multi-modal fusion feature vector; predicting a neck aneurysm probability value of the multi-modal fusion feature vector by using a pre-constructed neck aneurysm detection deep learning model, and screening a candidate neck aneurysm region and a parent artery region; and performing membrane membrane on the candidate neck aneurysm region and the parent artery region by using a blood vessel cavity three-dimensional binary mask, and extracting a device anchoring landing zone. According to the scheme, the neck aneurysm precisely positioned by the membrane membrane is taken as a starting point, and an anchoring landing zone section can be accurately screened out by searching upstream and downstream along the parent artery center line.

The present invention relates to a method for locating an aircraft (2) relative to a VTOL landing area (4) comprising at least one element (20A, 20B, 22A, 22B) that is reflective to a radio signal, the method comprising the following steps: - transmitting a radio signal from the aircraft (2) to the landing area (4), - receiving a signal reflected by the landing area (4) in response to the signal, - extracting a pattern from the received reflected signal, each pattern being the variation over time in the radio signal reflected by one reflective element (20A, 20B, 22A, 22B), - calculating a vertical distance (D y ) from the pattern, and - determining a vertical location of the aircraft (2) in relation to the landing area (4) depending on the vertical distance (D y ).

A disposable absorbent article is disclosed that includes a first waist region, a second waist region, a crotch region disposed between the first waist region and second waist region, a waist edge in the first waist region, at least one waistband in the first waist region, at least one fastener in the second waist region, and at least one discrete landing zone in the first waist region, the discrete landing zone comprising an lateral inboard edge, wherein the discrete landing zone and the waistband overlap to form an overlap region in the first waist region, and wherein the waistband does not overlap the lateral inboard edge of the discrete landing zone.

A system for wireless power transmission is disclosed, and includes a plurality of UAVs, each having a transfer medium reservoir, an onboard power conversion unit, a communication module, a navigation module, a power delivery interface, and at least one sensor. Each UAV is configured to interface with a transfer medium source, receive a chemical power transfer medium into the transfer medium reservoir, fly to a target area containing a power recipient having a power demand, identify and land within a landing zone, provide chemical power transfer medium to an endpoint power conversion, and evaluate at least one directive to decide what action to take based on feedback. The system also includes a fleet control system communicatively coupled to the plurality of UAVs and configured to operate the plurality of UAVs as a swarm, generate at least one directive, and distribute the directive to the communication module of each UAV.

The invention relates to the technical field of unmanned aerial vehicle control, and discloses an unmanned aerial vehicle accurate landing method based on image recognition, which comprises the following steps: an unmanned aerial vehicle receives a guide signal or a GPS coordinate from a landing platform, and flies to the sky of a landing area; the unmanned aerial vehicle vertically and downwards shoots an image containing a preset landing mark through an airborne camera; preprocessing and feature enhancement are carried out on the shot image, then the image is input to a target detection network, and a center pixel coordinate of a landing mark and contour information of the landing mark in the image are identified; and combining flight height sensor data of the unmanned aerial vehicle according to the corresponding relationship between the pixel size of the identified landing mark and the real-world size of the landing mark. The method is switched to a high-frame-rate image acquisition mode in a short-distance landing stage, realizes sub-centimeter-level position alignment precision through real-time visual servo fine adjustment, effectively eliminates accumulated deviation before final grounding, and provides key space alignment guarantee for stable and accurate landing of the unmanned aerial vehicle.

The present disclosure provides a memory device and a manufacturing method of the memory device. The memory device includes: a substrate, a landing area over the substrate, a bottom electrode over the landing area, and a high-k layer over the bottom electrode, wherein the bottom electrode includes a lower portion over the landing area, a middle portion over the lower portion, and an upper portion over the middle portion, and the bottom electrode has a container-shaped profile.

Embodiments provide a landing and approach navigation system. The navigation system can use a radar system onboard an aircraft to transmit radio energy. A rotating reflector at a landing area can reflect the radio energy back to the radar system with an amplitude-modulation that is due to the rotation. With synchronized timing between the reflector and the radar system, and known rotation characteristics of the reflector, the radar system can use the reflected radio energy to calculate the bearing of the aircraft relative to the reflector and landing area.

A system for controlling aeraulic conditions existing above an aerial arrival zone includes anemometric components and aeraulic components. The anemometric components deliver speed and bearing angle values that characterize a relative wind speed with respect to the aerial arrival zone and to a superstructure located close to the aerial arrival zone. The aeraulic components are capable of modifying air movements above the aerial arrival zone, and are controlled according to the wind speed and bearing angle values. Such a system is particularly suitable for use on board a ship able to carry a helicopter, in particular on its afterdeck.

An absorbent article is provided comprising a chassis comprising a central longitudinal axis and an absorbent core. The base structure includes a front waist region and a landing region and an elastic waist feature both positioned in the front waist region. The resilient waist feature includes a first end edge positioned proximate the front waist edge. The elastic waist feature: overlaps a portion of the landing zone at a longitudinal distance Y; and in overlapping relationship with a portion of the absorbent core in the front waist region at a longitudinal distance X. The resilient waist feature has a longitudinal distance W between the first end edge and the second end edge. The ratio of the distance X to the distance W is at least 0.4, and the ratio of the distance Y to the distance W is at least 0.4.

The present disclosure provides a memory device and a manufacturing method of the memory device. The memory device includes: a substrate, a landing area over the substrate, a bottom electrode over the landing area, and a high-k layer over the bottom electrode, wherein the bottom electrode includes a lower portion over the landing area, a middle portion over the lower portion, and an upper portion over the middle portion, and the bottom electrode has a container-shaped profile.

A high visibility aerial landing system for providing improved visibility and landing indication at short range or close range for a helicopter to help distinguish between safe or preferred landing zones from hazardous landing zones. The system has a flexible panel, a mooring assembly, and an indicator system. Further embodiments are specialized to be carried by the EMS or hikers.

Method for detecting an airport comprising a landing area, and associated method for automatic takeoff or landing. The present invention relates to a method for detecting an airport (10) comprising a landing area (12) and equipped with reflectors (14) configured to reflect an incident electromagnetic wave, each reflector (14) having a polarization rotation property. The method comprises the following steps: - approach to the airport (10) by an aircraft (18) or presence of the aircraft (18) at the airport (10), the aircraft (18) being equipped with at least one radar, - emission by the at least one radar of a signal having an initial polarization, - reception by the at least one radar of a reflected signal, and - determination of the presence and, where applicable, the respective location of the reflectors (14) from the polarization of the reflected signal. The invention further relates to an associated method for automatic takeoff or landing.Figure for the abridged version: Fig 1.

A method and apparatus for runway estimation in GNSS-denied environments for unmanned aerial vehicles (UAVs). When GNSS signals are denied to the UAV, motion data is acquired, a runway image sequence is captured, and runway distance data is obtained. The runway image sequence is input into a convolutional neural network to extract the pixel coordinates of the runway boundary, runway centerline, and runway landing zone markers, and to identify the runway number. A body coordinate system is constructed. The motion data, runway boundary pixel coordinates, runway centerline pixel coordinates, runway landing zone marker pixel coordinates, and runway distance data are transformed into the body coordinate system to generate initial runway geometric parameters. Environmental features of the target area are scanned to generate a 3D point cloud, which is matched with the standard coordinates of runway marker points, and a scale constraint factor is output. The initial runway geometric parameters are optimized, and the runway magnetic heading angle is fused to output the target runway geometric parameters. Implementing this technical solution can meet the landing requirements of UAVs in GNSS-denied environments.

In various embodiments, provided herein are methods, devices and systems to optimize delivery of ring-shaped articles for receiving transcatheter valves or stents. These methods, devices and systems are used to treat patients with valvular diseases. In some embodiments, the device includes at least three cables configured to hold a ring-shaped article having a center hole. The at least three cables are further configured to be anchored to supra-annular tissue at a heart valve peri-annular region. The ring-shaped article is positioned and deployed by means of at least three cables used to embed screws or anchors attached to the ring-shaped article into the supra-annular tissue; this deployed ring-shaped article is configured to receive a replacement heart valve in its inner lumen, thereby acting as a landing zone.

An adhesive absorbent article 20 is provided that includes a crotchway 26 having a crotchway bond strength and a frontway 56 that has no bond or a frontway bond strength that is weaker than the crotchway bond strength. The frontway at least partially overlaps a landing zone 44 on which the rear ear belt 42 can releasably fasten. During use, the frontway can delaminate to reduce stress on the landing zone and avoid accidental disengagement of the belt 42.

The utility model discloses a comfortable wearing type sclera lens, which comprises an optical area which is positioned in the center of the sclera lens and is used for correcting vision, a transition area which surrounds the periphery of the optical area and a landing area which surrounds the periphery of the transition area, the optical area and the transition area are of an integrally formed structure, and the transition area and the landing area are of a split type structure. The optical area and the transition area are hard areas, the landing area is a soft area, at least three clamping holes are evenly distributed in the transition area in the circumferential direction of the transition area, the landing area is correspondingly provided with connecting protrusions matched with the clamping holes in shape, the transition area and the landing area are connected in a clamped mode through the clamping holes and the connecting protrusions, and the landing area is further provided with a plurality of cone-like micro holes with the hole diameters large inside and small outside. The landing area is well matched with the sclera and softly lands on the sclera, the pressure borne by the sclera can be reduced, the micropore design of the landing area can not only promote circulation of internal and external aqueous humor of the sclera lens and provide enough oxygen for the cornea, but also promote discharge of bubbles and metabolites below the lens, and the wearing comfort of the eyes of a patient is improved.

Apparatuses and systems to assist in pressure sintering operations. The apparatus can include a base plate. The base plate can receive a heat sink. The base plate can include a landing zone. The landing zone can include a protrusion. The protrusion can at least partially define an opening. The opening can receive a fin of the heat sink.

The invention provides a laser point cloud-based helicopter auxiliary landing method, device, equipment and medium, and relates to the field of helicopter low-altitude perception, and the method comprises the steps: determining a to-be-evaluated region according to coordinates or the position and orientation of a helicopter, dividing the to-be-evaluated region into grids, and obtaining to-be-evaluated grids; acquiring point cloud data acquired by the laser radar and dividing the point cloud data into grids to be evaluated; obtaining the maximum elevation and the minimum elevation of the point cloud data in each grid, calculating the maximum elevation difference, and obtaining a basic evaluation grid; constructing a sliding window on the basic evaluation grid, and evaluating regional terrain information in the window to obtain a terrain evaluation result; and generating a landable area list according to a terrain evaluation result, sorting the landable areas according to a set landing point optimization criterion, and outputting an optimal landing point. According to the invention, the active detection of the to-be-landed area is realized with low calculation power, and the real-time evaluation of the terrain situation and the calculation of the landing point are carried out, so that the take-off and landing capabilities of the helicopter in different scenes are ensured.

The invention provides a lunar back and bipolar landing area observation orbit design and task planning method, relates to the field of lunar exploration, and solves the problems that an existing lunar exploration satellite orbit is insufficient in adaptability, observation and data transmission planning is split, observation coverage of lunar back and bipolar areas is incomplete, data return is low in efficiency, and the satellite orbit adaptability is poor. And the requirements of long-term lunar exploration continuous observation and real-time data support cannot be met. According to the method, 14 key observation targets on the back of the moon and the two poles are screened, a 500 km height polar circle orbit is designed, an observation and data transmission joint model containing multiple constraints is constructed, a genetic algorithm-simulated annealing hybrid algorithm is adopted to optimize a task sequence and imaging parameters, and efficient observation and data return are achieved. According to the method, full coverage and high revisit of the lunar back and the two poles are achieved through the 500 km polar circle orbit, the communication pain point is solved through the combined planning model, the task efficiency and quality are optimized through the genetic algorithm-simulated annealing mixed algorithm, observation and data return can be efficiently completed through simulation verification, and stable support is provided for long-term lunar exploration.

A system operates an elevator door upon an elevator car residing at a landing zone of a landing and includes a locking mechanism having a rotatable lock hook assembly and a lock latch. The lock hook assembly includes a lock hook portion arranged to selectively engage or disengage the lock latch via rotation of the lock hook assembly to set the locking mechanism, respectively, into a locked state or an unlocked state, and an actuation assembly for rotating the lock hook assembly. A safety circuit indicates a state of the locking mechanism and includes a switch that is closed in the locked state of the locking mechanism and that is open in the unlocked state of the locking mechanism. A door controller is arranged to operate a door driving system, in dependence of movement of the elevator door.

A landing zone is established in an open table format object storage. More specifically, the landing zone is implemented as a local ingestion table file. This represents a special subtype of the local data file that is used in the inbound layer when ingesting data from an external system. This local ingestion table file is further subdivided into an active data portion and an inbound buffer. When data is written from the external system, it is first placed in the inbound buffer. This data is then merged into the active data, after processing and postprocessing. The result of these postprocessing operations is then stored in the active data portion of the local ingestion table file.

A landing platform for a base station that is configured to dock with an unmanned aerial vehicle (UAV). The landing platform includes: a stage that defines landing areas, which are configured to receive the UAV during docking; alignment members that are configured to engage and reposition the UAV during a first stage of alignment; and a charging hub that is configured for electrical connection to the UAV. The charging hub includes a registration member, which is configured to mechanically interface with and reposition the UAV on the landing platform during a second stage of alignment, and a charging head that is repositionable in relation to the registration member from a normal position into a deflected position during a third stage of alignment to facilitate engagement of corresponding electrical contacts on the UAV and the charging head.

The present invention relates to a cartridge for the uptake and analysis of a fluid sample, comprising an inlet which allows to take up the sample; a filter zone comprising a filter membrane which allows for separating different components within the sample and for adding reagents to the sample; a landing zone which allows for delaying the movement of the sample and for blending the sample; a transport zone which allows for transporting the sample from the landing zone to a reaction chamber, comprising one or more fluidic channels; one or more reaction chambers, which are designed for mixing of reagents with the sample; one or more reaction chambers, which are designed to capture analytes from the sample and other reactants; a reaction chamber zone, which is designed for washing, examination and verification of assay reactions; and one or more stop zones where fluidic flow within the cartridge is stopped.

The application discloses a triaxial normalization search system, a helicopter and a method for searching a manned spaceship return capsule. The method for searching the manned spaceship return capsule comprises the following steps: adjusting a first position of a helicopter standby, so that the helicopter approaches a landing area of the manned spaceship return capsule; starting searching according to the landing area, if there is a specific event, a specific strategy is adopted to search for the manned spaceship return capsule, so as to output a second position of the manned spaceship return capsule; and based on the second position, search and rescue guarantee is implemented on the manned spaceship return capsule.

The present invention relates to a method for detecting an airport (10) comprising a landing zone (12) and provided with reflectors (14) configured to reflect an incident electromagnetic wave, each reflector (14) having a polarization-rotating property. The method comprises the following steps: - an aircraft (18) approaches the airport (10) or the aircraft (18) is present in the airport (10), the aircraft (18) being provided with at least one radar, - the at least one radar emits a signal having an initial polarization, - the at least one radar receives a reflected signal, and - the presence and, where applicable, the respective location of the reflectors (14) is determined based on the polarization of the reflected signal. The invention also relates to an associated automatic take-off or landing method.

The present application relates to the technical field of artificial skiing sports facilities, and in particular to a ski jump having a granular dry ski landing slope, comprising a landing slope and a dry ski granule lifting device. The landing slope comprises a slope body, and an underlying support structure, a waterproof plate, a ski mat and dry ski granules are sequentially laid on the slope surface of the slope body; the slope body comprises a knuckle located at the top of the slope, a platform zone, and a landing zone; the angle of repose of the dry ski granules is designed to match the slope gradient of the landing zone, with the same gradient of 20-40 degrees; a granule drain plate is provided at the root of the slope body, is used for granule recovery, and is always covered by the dry ski granules; and the dry ski granule lifting device is configured to lift the dry ski granules that have rolled down to the root of the landing slope to the platform zone at the top of the landing slope, thereby enabling recycling of the dry ski granules. The present application provides safe skiing conditions for jumpers while facilitating the completion of a complete "ski jumping" maneuver by the jumpers.