131results about "Landing aids" patented technology

The invention provides a Fresnel optical image target detection and identification method based on event stream data enhancement, and the method comprises the steps: carrying out the data preprocessing of collected Fresnel optical image event data through employing a denoising algorithm based on time-space continuity, and screening the original event stream data; converting the screened event stream data of the target area into pixel data under an image coordinate system by adopting a dual threshold limiting strategy of event quantity and accumulation time; existing image features are enhanced, and pixel-level fusion, feature-level fusion and decision-level fusion are carried out on event stream data of an event camera and RGB camera data; and the target detection module is used for performing target detection and recognition on the fused data by using a YOLO target detection model. According to the method, the detection of the Fresnel optical image target is realized, so that the detection and recognition capability of the Fresnel optical image target in a complex environment is improved, and the method is particularly suitable for scenes such as seaborne landing guidance and the like.

Systems and methods of providing guidance to assist eVTOL aerial vehicles in performing landing and takeoff operations at landing locations in GPS-denied environments are disclosed. An exemplary system includes an aerial vehicle comprising a camera configured to generate images based on information transmitted by a plurality of light sources located adjacent a landing surface for the aerial vehicle and a controller circuit configured to receive the generated images and determine a position and an orientation of the aerial vehicle based on the received images, wherein the light sources are arranged in a predetermined pattern on the landing surface, and wherein a characteristic of light emitted from each of the light sources is modulated with respect to time.

The invention introduces a tethered unmanned aerial vehicle follow-up and precise landing target system, which comprises a multi-level visual target, and the visual target sequentially comprises a central positioning area, a target positioning area and a target positioning area from the center to the periphery, and the central positioning area is formed by arranging four aruco marks of a first size in a 2 * 2 array mode; the middle transition area is formed by arranging eight aruco marks of the first size in the upper direction, the lower direction, the left direction and the right direction of the center positioning area; four aruco marks of a second size are respectively arranged at the left upper part, the right upper part, the left lower part and the right lower part of the central positioning area; the peripheral auxiliary area is formed by arranging four aruco marks of a third size at four corners of the whole visual target respectively; the maximum peripheral frame is an aruco mark of a fourth size, and the outer frame of the aruco mark of the fourth size forms the outermost layer area of the whole target. According to the invention, continuous and stable visual features can be provided for the mooring unmanned aerial vehicle at different flight heights and attitudes, and the landing reliability is improved.

A system for coordinating aircraft servicing tasks of a plurality of ground support equipment at an airport includes a plurality of beacons and one or more processing circuits. The plurality of beacons are configured to couple to the plurality of ground support equipment. The one or more processing circuits include one or more processors storing instructions thereon that, when executed by the one or more processors, cause the one or more processing circuits to acquire signals from the plurality of beacons and coordinate movement of the plurality of ground support equipment based on the signals and in accordance with an aircraft servicing plan.

A flight management system includes a communications system configured to receive weather data from a remote source, a display system configured to generate an output for a flight display of an aircraft, and at least one processor with a non-transitory processor-readable medium storing processor-executable code. The output includes weather information based on the received weather data. The processor-executable code causes the processor to receive a user input from a user interface element of the aircraft where the user input requests updated weather information. The processor-executable code causes the processor to retrieve, via the communications system and in response to the user input, updated weather data from the remote source; calculate a departure or arrival performance flight parameter based at least in part on the updated weather data; and provide, via the display system, an output for the flight display of the aircraft where the output includes the flight parameter.

A towbarless tractor for towing an airplane having a nose landing gear includes a chassis, a body supported on the chassis, and a capture system. The capture system includes a lift body coupled to at least one of the body or the chassis, a cradle coupled to the lift body, and a side-shift actuator configured to selectively move the cradle along a lateral direction relative to the body.

The invention relates to the technical field of low-altitude aircraft supporting facilities, and one embodiment of the invention provides a low-altitude aircraft solar wireless charging platform which comprises a wireless charging platform, solar power generation platforms are arranged on the two opposite sides of the wireless charging platform, a charging energy supply assembly is arranged on the wireless charging platform, and the charging energy supply assembly is arranged on the wireless charging platform. The locking and positioning assembly is arranged in the wireless charging platform; the charging energy supply assembly comprises a warning groove, and the warning groove is formed in the upper end face of the wireless charging platform. By means of the technical scheme, the problems that in the prior art, charging equipment is generally simple in structure, energy storage, charging and other processes cannot be stably controlled, and the problem that in the wireless charging process, a high-intensity magnetic field generated by a magnetic coupling transmitting coil has adverse effects on internal metal or electrical structures of an unmanned aerial vehicle and the charging equipment is solved; the technical problem that the low-altitude aircraft does not need to return and is convenient to charge during field operation is solved.

The invention discloses an overturning shading type flickering HAPI lamp of a helicopter field visual approach gradient indication system. The system comprises a supporting frame assembly, a protection assembly, an optical assembly, a shading assembly, a light-emitting assembly, a control assembly and a main control board. The core lies in that the shading assembly is of a mechanical turnover structure, corresponding shading pieces are driven by an upper driving mechanism and a lower driving mechanism to conduct periodic turnover motion, constant light beams generated by the light emitting assembly are mechanically shielded and released regularly, and color filtering is conducted in combination with light filtering glass arranged in a partitioned mode; therefore, the constant light beam is converted into four standard indicating light beams which accord with specifications, namely red / green and constant bright / flickering. Light beam flickering is achieved in a physical and mechanical mode, a traditional LED direct electronic flickering mode is replaced, the problems of light intensity attenuation, inaccurate color, high electronic failure rate, poor environmental adaptability and the like are effectively solved, and the LED light source has the advantages of being accurate in indication, stable in work, long in service life and high in reliability.

A streaming policy management system and method wherein bandwidth may be allocated based on external device information received from a streaming client device connected to one or more external audio / video (A / V) devices. When a streaming network back office receives a request from the streaming client device for delivery of a particular content, wherein the request includes external device information of one or more external A / V devices connected to the streaming client device, a bandwidth is determined for streaming the particular content to the streaming client device and a request may be made to a content delivery network to create a distribution pipe having the bandwidth to accommodate the delivery of the particular content. A manifest file is provided to the streaming client device that includes one or more pointers that point to content segments of the particular content.

The invention discloses a dynamic compensation method and system for guiding lamplight in the manual landing process of a shipborne aircraft, and belongs to the field of shipborne aircraft guiding lamplight compensation. The problems that in an existing lamplight compensation method, adaptability to complex motion of a ship is insufficient, the dynamic relative position relation between the pilot eye position and a guiding lamplight coordinate system is not fully considered, and compensation precision is low in different stable states are solved. The method comprises: defining a coordinate system; ship motion parameters are obtained in real time; based on the coordinate system and the ship motion parameters, calculating the coordinate of the pilot eye position under the guide lamp coordinate system; calculating the coordinate of the focus of the Fresnel lamp in the guide lamp coordinate system; determining a height error, a transverse error and a pitch angle based on the pilot eye position coordinate and the light focus coordinate; executing longitudinal compensation and transverse compensation; and dynamically adjusting the guide light based on the compensated light control angle. The method is mainly used for guiding lamplight to accurately counteract ship swing in real time.

The utility model is suitable for the technical field of airport equipment, and provides a guiding device for an airport, which comprises a guiding vehicle fixedly provided with a control system, the common indicator light board used for guiding an airplane to take off and land is fixedly mounted on the guide vehicle; the through opening is formed in the top of the guide vehicle; the hydraulic rod is fixedly mounted in the guide vehicle; the fog lamp indicating lamp board is used for guiding an airplane in rainy and foggy weather, the fog lamp indicating lamp board is fixedly installed on an output shaft of the hydraulic rod, and the fog lamp indicating lamp board is arranged in the guiding vehicle; the fixing plate is fixedly installed on the fog lamp indicating lamp board and is in sliding connection with the through opening. The airport guiding device provided by the scheme can improve the definition of the indicating lamp in rainy days and foggy days, is beneficial to guiding airplanes, and improves the guiding efficiency.

A system for global auto-configuration of at least one airport signaling device (11) of an aerodrome, said system comprising: a central control unit (14) and signaling devices (11), wherein the central control unit (14) is capable of communicating with the airport signaling devices (11) via the communication module (119) once a communication channel has been initiated; wherein the system is configured to communicate configuration data of at least one signaling device (11) to an Internet of Things (loT) hub (210), namely the identity code and the estimated location of the at least one signaling device; wherein the Internet of Things (loT) hub is capable of data communication with plurality of servers (220) configured to store inventory data related to a set of registered airport aeronautical signaling devices for at least one aerodrome for a predefined geographical area.

To provide a mounting device for an aircraft landing guidance flash light which does not require adjustment of an angle of a flashlight when the aircraft landing guidance flashlight is mounted to the mounting device for the aircraft landing guidance flashlight, and an aircraft landing guidance flashlight device.SOLUTION: Mounting devices 10, 20 for an aircraft landing guidance flashlight comprise a pair of mounting arms 11, a U-shaped light emission part fixing plate 12, and rotation shaft fixing means. A rotation shaft 13a is arranged on one of the pair of mounting arms 11 and the U-shaped light emission part fixing plate 12, and a bearing of the rotation shaft 13a is arranged on the other of them. Before the detachable aircraft landing guidance flashlight is provided on the U-shaped light emission part fixing plate 12, an angle of the U-shaped light emission part fixing plate 12 to the pair of mounting arms 11 is adjusted to a predetermined angle by the rotation shaft 13a and the bearing, so as to make a fixing condition by the rotation shaft fixing means.SELECTED DRAWING: Figure 1

The invention discloses a bus-based static lamplight landing assisting system for a shipboard helicopter. The static lamplight landing assisting system for the shipboard helicopter comprises a control panel, a landing assisting system control box, a static landing assisting lamp, a landing signal lamp repeater and a buzzer. And the control panel is in communication connection with the landing assisting system control box. The landing assisting system control box, the static landing assisting lamp, the rising and falling signal lamp repeater and the buzzer are all located in the same CAN bus control network. The method has the advantages that helicopter landing assisting tasks of small and medium-sized ships such as law enforcement ships are protected, and the method has high practical value.

The present application relates to the technical field of parking apron, and proposes an assembled helicopter parking apron, which is arranged on a high-rise roof and ground and further comprises: a whole frame structure apron support frame formed by interconnecting and locking a first support pipe and a second support pipe of modular design, a modular frame body is laid on the apron support frame and locked, thereby forming a whole parking apron, the first support pipe and the second support pipe can enhance the bearing strength of the connecting part after being connected and locked, are suitable for hoisting and transportation and rapid assembly on site, the modular design of the parking apron meets the take-off and landing requirements of different areas of various types of helicopters, solves the technical defects of the prior art, such as high difficulty, environmental pollution, long construction period, high construction cost and complex design of the connecting part of the steel-aluminum structure parking apron, and the parking apron cannot be disassembled, moved and reassembled after being built, and cannot be added or modified on the already built high-rise building, and the parking apron can realize the advantages of lightweight design, factory production standardization and on-site assembly convenience.

The present invention relates to a system for locating an aircraft (502) at a geographic location, the system including an aircraft (502) having one or more infrared (IR) detectors and a positioning beacon (504) disposed at the geographic location, the positioning beacon (504) configured to wirelessly transmit a landing identifier that is detected by the aircraft (502) and including one or more emitters or reflectors configured to emit or reflect IR signals, respectively, and the aircraft (502) configured to receive the landing identifier and the emitted or reflected IR signal, compare the received landing identifier with a stored unique identifier, and if the received landing identifier matches the stored unique identifier, use the emitted or reflected signal to control movement of the aircraft (502) relative to the positioning beacon.

A method comprises providing a vehicle landing pad with a reference frame origin at a center thereof, and X and Y axes through the reference frame origin; arranging a first group of markers, each having a first size, on the pad such that the first group of markers form a first convex hull about the center of the pad; and arranging a second group of markers, each having a second size less than the first size, on the pad such that the second group of markers form a second convex hull within the first convex hull. The first and second groups of markers are located symmetrically with respect to the center of the pad along the X and Y axes so as to yield a position estimation solution for landing a vehicle having a highest accuracy when compared with placing markers at other locations along the X and Y axes.

Described herein are systems for automated docking of an unmanned aerial vehicle. For example, some systems include an unmanned aerial vehicle including a propulsion mechanism, an image sensor, and processing apparatus; and a dock including a landing surface configured to hold the unmanned aerial vehicle and a fiducial on the landing surface, wherein the processing apparatus is configured to: control the propulsion mechanism to cause the unmanned aerial vehicle to fly to a first location in a vicinity of the dock; access one or more images captured using the image sensor; detect the fiducial in at least one of the one or more images; determine a pose of the fiducial based on the one or more images; and control, based on the pose of the fiducial, the propulsion mechanism to cause the unmanned aerial vehicle to land on the landing surface.

Decision support method for approach phase for landing an aircraft on a runway. The present invention relates to a decision support method (40) for the approach phase for landing an aircraft on a runway, the method (40) comprising the following steps: - obtaining (42) characteristic elements detected via an image capture device, - determining (44) an approach scene recognition score associated with said detected characteristic elements, based on a reference approach scene; - comparing (46) said score to a predetermined decision threshold value; - decision support (48) by providing the comparison result to a pilot, or to an autopilot system, capable of continuing the approach phase if the score is higher than said predetermined decision threshold value, or of interrupting the approach phase, by going around, if the score is lower.Figure for the abbreviation: Figure 4.

A vehicle for towing an airplane includes a chassis, a body coupled to the chassis, the body and the chassis having a first side and a second side opposite the first side, a tractive assembly, a tow mechanism configured to engage with a nose landing gear of the airplane, a light system including a first lighting element positioned along the first side and a second lighting element positioned along the second side, and a control system configured to monitor a direction of travel of the vehicle and control operation of the light system to selectively illuminate the first lighting element and the second lighting element to provide an indication of the direction of travel of the vehicle, thereby making the direction of travel of the vehicle perceivable to an operator positioned outside of the vehicle.

Airfield ground lighting system (10), comprising: a plurality of light units (11) arranged in a serial circuit (13), a power supply (12), said power supply (12) comprising a constant current regulator (121); wherein each light unit (11) comprises at least one light source (114) and optionally at least one activatable device; wherein the airfield ground lighting system or a power supply control unit (14) of said system is configured to determine an expected power demand of the serial circuit (13) based on at least one of an expected light intensity level output to be applied, to at least one, in particular each light unit (11) and / or an expected activation state of the at least one activatable device of said light unit (11).

To provide a runway-embedded flash device that is light-weight, has a long life and high effective luminous intensity, can switch luminous intensity, has small power consumption, and can be placed on the ground surface with its bottom facing down without requiring a stand or the like.SOLUTION: A runway-embedded flash device comprises a cylindrical body 10, a ceiling member 11, a light guide member 12, an LED flashlight source 13, and a bottom cover member 16. The ceiling member is arranged on an upper opening part of the cylindrical body 10 in a state of being exposed to a runway surface. The ceiling member 11 is provided with a window for flashlight irradiation. The light guide member 12 is arranged at the window for flashlight irradiation. The LED flashlight source 13 is arranged in the cylindrical body 10 in a state of being capable of emitting flashlight toward the light guide member 12 arranged at a window for flashlight source. The light guide member 12 allows the flashlight emitted from the LED flashlight source 13 to be emitted from the window for flashlight irradiation to the outside. The bottom cover member 16 is arranged in a state of being capable of closing a lower opening part of the cylindrical body 10. The bottom cover member 16 has a support part 17 protruding from an external surface of the bottom cover member 16 on a side opposite the cylindrical body 10 side.SELECTED DRAWING: Figure 1

Devices, methods, and systems for securing a light assembly of an airfield light are described herein. One device includes a light assembly, a base, and a locking assembly configured to secure the light assembly to the base. The locking assembly includes a plunging mechanism configured to compress against a cover of the light assembly while the cover is being rotated relative to the base, and extend into an opening of the cover of the light assembly to secure the light assembly to the base.

An automated aircraft taxi system for an aircraft taxiing within an airport environment implements a collision-avoidance function. The collision-avoidance function triggers revision of guidance instructions and or alerts the pilots of the aircraft when a predicted trajectory of moving objects intersects a taxi path trajectory of the aircraft. The collision-avoidance function disregards an identified object that is moving on a taxiway in the airport environment when a predicted trajectory of the identified object does not intersect the taxi path trajectory of the aircraft according to the location of the identified object and the layout of taxiways on the airport map.

The present invention relates to a system for detecting a foreign object on a runway. The system includes a thermal camera having a first field of view and adapted to capture a thermal image of an area of interest on the runway, a visible light camera having a second field of view and adapted to capture a visible light image of the area of interest on the runway, such that the first field of view overlaps the second field of view. The system further includes a processor configured to detect a thermal object image in the thermal image, detect a visible light object image in the visible light image, and determine that the foreign object is detected when the thermal object image and the visible light object image are detected in the thermal image and the visible light image respectively.

The present disclosure relates to precision approach path indicator (PAPI) systems. An example system includes a heatsink assembly and a plurality of optical channels. Each optical channel of the plurality of optical channels includes a light emitting diode (LED) source coupled to a first surface of the heatsink assembly. Each optical channel also includes a back collimating lens coupled to a second surface of the heatsink assembly. The LED source is configured to emit light through the back collimating lens to provide collimated light. Each optical channel also includes an optical filter disposed to interact with a first portion of the collimated light to form filtered light. Each optical channel also includes a front collimating lens configured to interact with the filtered light and a second portion of the collimated light to form output light.

Disclosed in an example embodiment herein is an airfield luminaire, comprising a housing, a light source in an interior of the housing, a sensor for sensing a condition associated with the housing, and control logic comprising a processor coupled with the light source and the sensor. The control logic is operable to obtain data from the sensor and determine a status of the airfield luminaire. In another example embodiment, a controller is operable to receive data representative of sensor data from the plurality of airfield lighting fixtures and determine the status of a selected one of the plurality if lighting fixtures based on the sensor data. In yet another example embodiment control logic that comprises a processor is operable to determine the present light output of a LED based on aging rate and amount of time the LED is operated at a plurality of temperatures.

The invention discloses an energy storage type helicopter field light beacon, and relates to the technical field of intelligent lighting, the energy storage type helicopter field light beacon comprises an upper cover, a lower cover, a vertically arranged central connecting pipe, a transparent glass lampshade, a semi-reflective reflecting cover and an LED light source module, the central connecting pipe penetrates through the upper cover and the lower cover and is connected into a whole; the transparent glass lampshade is clamped between the upper cover and the lower cover and wraps the outer side of the central connecting pipe, the semi-reflective reflecting cover is arranged on the inner side of the transparent glass lampshade and is connected with the central connecting pipe, and the LED light source module is arranged at the arc-shaped root of the semi-reflective reflecting cover and is in direct contact with the pipe wall of the central connecting pipe through a large-area aluminum substrate; the multiple LED light source modules are arranged in the circumferential direction in a staggered mode according to a preset angle, so that the main optical axis directions of the adjacent LED light source modules deflect mutually in the horizontal plane, and complementation and uniformization of light intensity distribution in the horizontal plane are achieved. The LED lamp is uniform in light intensity distribution, efficient in heat dissipation and high in environment durability.

Described herein are systems for automated docking of an unmanned aerial vehicle. For example, some systems include an unmanned aerial vehicle including a propulsion mechanism, an image sensor, and processing apparatus; and a dock including a landing surface configured to hold the unmanned aerial vehicle and a fiducial on the landing surface, wherein the processing apparatus is configured to: control the propulsion mechanism to cause the unmanned aerial vehicle to fly to a first location in a vicinity of the dock; access one or more images captured using the image sensor; detect the fiducial in at least one of the one or more images; determine a pose of the fiducial based on the one or more images; and control, based on the pose of the fiducial, the propulsion mechanism to cause the unmanned aerial vehicle to land on the landing surface.