118 results about "Landing zone" patented technology

Techniques for outputting landing area conditions to aircraft using standardized message protocols are provided. In an example method, a computing device accesses a configuration for generating messages using a predetermined message format for a first air traffic management device located at a first landing area. The computing device updates the configuration with information about a condition at the first landing area using the predetermined message format. The computing device outputs, using the first air traffic management device, a message based on the configuration, including transmitting the message to a second air traffic management device associated with an aircraft within a predetermined distance of the first landing area.

A method of facilitating the landing of a civil aircraft on a potential landing zone divided into sub-zones. The method includes a step of producing a digital surface model of the potential landing zone using topographic terrain data. In a placement step, the digital surface model is positioned and / or orientated in space to obtain a placed digital surface model. In a calculation step, an overall risk level is calculated for each sub-zone on the basis of the placed digital surface model and characteristics of the sub-zone including topography, accessibility, loss of visibility, and presence of living beings. A reporting step comprises generating an information signal dependent on the overall risk levels, and / or transmitting a control signal dependent on the overall risk levels.

The technology disclosed herein relates to a rooftop platform to facilitate a delivery of a parcel by an aerial vehicle. The rooftop platform may comprise an elevator apparatus at least partially accessible via the rooftop platform. The rooftop platform may also comprise a rotatable turntable mounted to the rooftop platform. The rotatable turntable can be rotated to position the parcel on the elevator apparatus. The rotatable turntable may have tracks for receiving track wheels of a parcel containment unit. In some embodiments, the parcel may be positioned on the elevator apparatus at a top surface of a lift cabin of the elevator apparatus. The rooftop platform may also comprise a landing area for the aerial vehicle to deliver or receive the parcel containment unit via the rotatable turntable.

The invention discloses a landing positioning method and system based on fusion of vision and inertial navigation. The method comprises the following steps: collecting vision information of a current landing area; the visual information of the front landing area is mapped to an aligned grid of a map coordinate system through homography transformation, correlation matching is conducted on the visual information and a map through a frequency domain FFT algorithm, a matching result of rough matching is obtained, and rough matching is completed; the method comprises the following steps of: mapping an area subjected to rough matching and positioning to a grid aligned with a map coordinate system by utilizing homography transformation, performing spatial domain multi-window division on a larger range of images around the area subjected to rough matching and positioning, selecting a landmark area in each sub-window by applying an interest operator, performing spatial correlation matching on the landmark area and a map by utilizing a spatial correlation method, and performing spatial correlation matching on the landmark area and the map by utilizing a spatial correlation method. Finishing fine matching; inputting all matched observation results into an extended Kalman filter, and carrying out joint estimation on the matched observation results and the observation results of the inertial measurement unit; the method has the advantages that the robustness, the precision and the engineering applicability of an existing navigation positioning method are improved.

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.

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 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 application discloses a safe landing area detection method, device, equipment, medium and product of a UAV, relates to the field of autonomous navigation and safety of a UAV, and comprises the following steps: inputting a visual image into a monocular metric geometry estimation model to obtain metric point cloud data, a surface normal and an effective mask in a camera coordinate system, and transforming the metric point cloud data, the surface normal and the effective mask into a world coordinate system according to pose information; filtering the effective mask to obtain effective point cloud; when the number of the effective point cloud meets a threshold value, performing rasterization processing to obtain a grid unit and calculate geometric features; inputting the visual image into an instance segmentation model to obtain a dangerous area mask, and mapping the dangerous area mask to each grid unit, and combining the geometric features and a ground reference height to determine a safety probability; determining an optimal landing area based on the safety probability, and calculating the center coordinates and the radius of the minimum circumscribed circle of the optimal landing area. The application improves the autonomous safe landing capability of the UAV in an unknown complex environment.

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 ).

This invention belongs to the field of contact lens technology, specifically providing a method for designing scleral lenses based on ocular surface and scleral topography. Based on the topography of the anterior surface of the patient's cornea and sclera, the method divides the anterior surface of the cornea and sclera into meridians at equal angles, and designs the surface profile curves of the anterior and posterior surfaces of the scleral lens according to the morphology of the patient's cornea and sclera. Finally, 3D reconstruction is used to obtain the 3D surface profile data of the scleral lens. The optical zone of the scleral lens can be designed in various ways depending on the different shapes of the patient's eyeball; the transition zone can be designed in diverse ways to ensure the thickness of the intraocular fluid at certain locations based on the ocular surface morphology; and the landing zone smoothly conforms to the anterior surface of the sclera. This invention maximizes conformity to the patient's ocular surface morphology, ensures the uniformity of the intraocular fluid, and maintains a high degree of matching with the ocular surface, thereby achieving trial-free scleral lens fitting, improving clinical accuracy and efficiency, and enhancing patient safety and satisfaction.

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.

Various aspects of the disclosure generally relate to credit card processing readers and related security features. Part of those features include landing pads which may be vulnerable to certain attacks and tamper attempts. Some landing pads are more easily accessed (vulnerable) in a tamper attempt, than others. In one aspect, this disclosure recites a direct electrical connection between landing areas, where one of the landing areas is more accessible and the other is less accessible. This may reduce device vulnerability when both landing areas must be accessed in a tamper attempt.

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.

When servo heads in a head chip of a servo write head assembly record servo patterns onto a tape's servo tracks, the servo heads are continuously being rapidly worn away by the tape. This general wear affects the servo heads' ability to record the servo patterns, impairing accurate positioning of the tape heads in the drive. However, by implementing, on the leading edge of the head chip, a support block that has a wear resistant skiving edge and landing zone for the tape “crow bar,” which forms when the tape is running over the servo head, the general wear of the servo heads from the tape is mitigated. The skiving edge, which may be formed by thin film technology process steps, causes the tape to fly over the head chip in those regions. An additional support block may be implemented at the trailing edge of the head chip.

A portal and method for a drone to transit from one side of door to the other. The portal having an opening for each side of the door and having at least two levels, and a temporary landing area. The portal structure with no moving parts that allows the drone to transit the door.

A computing system for landing and storing vertical take-off and landing (VTOL) aircraft can be configured to receive aircraft data, passenger data, or environment data associated with a VTOL aircraft and determine a landing pad location within a landing facility based on the aircraft data, passenger data, and / or environment data. The landing facility can include a lower level and an upper level. The lower level can include a lower landing area and a lower storage area. The upper level can include an upper landing area. At least a portion of the upper level can be arranged over the lower storage area. The landing pad location can include a location within the lower landing area or the upper landing area of the landing facility. The computing system can communicate the landing pad location to an operator or a navigation system of the VTOL aircraft.

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.

Systems and methods are presented for utilizing a drone swarm for firefighting purposes. Relevant information relating to a fire, priorities for fighting the fire, capabilities of the drones of the drone swarm, are evaluated. One or more deployment plans are developed for deploying the drone swarm for firefighting purposes. Each deployment plan includes a corridor for traversing drones of the drone swarm from launch zone to an attack zone, and a corridor for traversing the drones from attack zone to the landing zone. Each deployment plan also includes one or more objectives and corresponds to firefighting actions for each of the plurality of drones of the drone swarm. A pilot in charge (PIC) makes a section of and executes a first deployment plan. A DASA-configured computer or computer system, under the direction of the PIC, cooperatively directs the drones of the drone swarm to execute the deployment plan.

The invention relates to a system and method for calculating flight control for vehicle landing. Methods, systems, and non-transitory computer readable media for landing a vehicle are disclosed. For example, the method may include receiving a landing zone confirmation from a service prior to a descent transition point, the landing zone confirmation including landing zone location information and an indication of landing zone smoothness; determining a landing flight path based on the landing area position information; and when the vehicle begins to descend to the landing zone using the landing flight path: receiving landing zone data from at least one of a radar system, a camera system, an altitude and heading reference system (AHRS), and a GPS system; performing an analysis based on the landing zone data to determine whether an unsafe condition exists; and calculating a flight control for the vehicle to continue the descent or modify the descent based on the analysis.

The present application relates to a method of generating a receiving substrate (1) configured to receive one or more dies (3) thereon by hybrid bonding in one or more first landing zones (2a) and / or one or more dies (4) thereon by solder bonding in one or more second landing zones (2b). In both types of landing zones, contact pads (29, 35, 36) embedded in the dielectric layer (37, 50) or the stack of dielectric layers (27, 28) are formed, enabling hybrid bonding in the hybrid bonding landing zone. The contact pad in the solder landing area is configured to receive solder material directly on the contact pad after bonding of the hybrid bonding die without requiring formation of an under bump metal pad. According to a preferred embodiment, at least the solder contact pad comprises two layers (29a, 29b), a bottom layer and a top layer, the bottom layer being formed of a material formed of an intermetallic compound that exhibits slower than the top layer material when reacting with the solder.

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 invention relates to the technical field of digital twinning, in particular to a digital twinning decision-making method for city-level low-altitude economy. The method comprises the following steps: acquiring three-dimensional geographic information of a city; detecting a building three-dimensional contour in the urban three-dimensional geographic information; determining a landing area by using the three-dimensional contour of the building; performing unmanned aerial vehicle landing point optimization on the landable area by adopting a pre-trained digital twin model to generate landing point data; unmanned aerial vehicle distribution task information is acquired; determining a first distribution path based on the unmanned aerial vehicle distribution task information and the landing point data; continuously monitoring the flight state of the unmanned aerial vehicle in the first distribution path; and detecting the energy consumption of the unmanned aerial vehicle based on the flight state, and if the energy consumption of the unmanned aerial vehicle is greater than a preset energy consumption threshold, determining that the flight state is abnormal. The stability and the energy efficiency utilization rate of unmanned aerial vehicle distribution are improved based on the digital twin technology.

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.

The invention discloses a method for evaluating a safe landing area of a fast-spinning weak-gravity target, and belongs to the field of aerospace. The implementation method comprises the following steps: acquiring basic parameters of the small celestial body, wherein the basic parameters comprise a three-dimensional shape model, density, rotation axis direction, rotation angular velocity and friction angle; establishing a global coordinate system by taking the geometric center of the small celestial body model as an original point, and establishing a local coordinate system on the surface of the global coordinate system; according to the three-dimensional shape model and the density, the gravitational potential around the small celestial body is calculated, and the gravitational acceleration borne by the spacecraft at the landing point is calculated in combination with the position vector of the landing point; based on the rotation angular velocity of the small celestial body, the centrifugal force acceleration borne by the spacecraft at the landing point is calculated. And the resultant acceleration of the spacecraft in the normal direction is obtained by combining the propelling force acceleration of the spacecraft, and the friction force is calculated according to the friction angle. And calculating to obtain the dynamic characteristics of the spacecraft in different areas so as to judge whether the spacecraft can stably land or not, thereby realizing the identification of the safe landing area on the surface of the small celestial body.