24 results about "Aircraft vectoring" patented technology

The invention relates to the technical field of aircraft navigation, and discloses an aircraft return path construction method based on visual intelligence. According to the method, a flight environment multi-view image sequence is collected through an airborne vision sensor, and vision observation data with a unified timestamp and space coordinates are generated through space-time alignment processing; calculating a motion vector field of the aircraft relative to a ground reference object based on continuous inter-frame optical flow characteristics in the data, and establishing a three-dimensional environment kinematics model by combining attitude data of the inertial measurement unit; reversely deducing a current flight path by using the model, extracting a historical path key waypoint set, and constructing a return path initial topology network according to the spatial distribution density of the historical path key waypoint set; carrying out dynamic weight distribution on a network node connection relationship, and generating a wind disturbance resistance candidate return path set in combination with a real-time meteorological wind field intensity parameter; and evaluating the candidate set by using a multi-objective optimization algorithm, and outputting an optimal return path meeting a fuel consumption threshold value and a flight time constraint.

A landing site selection system selects landing sites for unplanned landings for small aircraft. The landing site selection system may generate a landing site database comprising parameters for landing sites. The landing sites may be any location where an aircraft may potentially land. The landing site selection system may monitor aircraft conditions and determine that an unplanned landing may be desirable. The landing site selection system may select potential landing sites based on the aircraft conditions and the landing site parameters. The landing site selection system may display landing site parameters for the selected landing sites to a pilot to allow the pilot to select a landing site. The landing site selection may provide navigation instructions or autonomously navigate the aircraft to the landing site.

A landing site selection system selects landing sites for unplanned landings for small aircraft. The landing site selection system may generate a landing site database comprising parameters for landing sites. The landing sites may be any location where an aircraft may potentially land. The landing site selection system may monitor aircraft conditions and determine that an unplanned landing may be desirable. The landing site selection system may select potential landing sites based on the aircraft conditions and the landing site parameters. The landing site selection system may display landing site parameters for the selected landing sites to a pilot to allow the pilot to select a landing site. The landing site selection may provide navigation instructions or autonomously navigate the aircraft to the landing site.

The invention discloses a self-adaptive feedback orientation estimation method, device and system, and belongs to the field of navigation.The method comprises the steps that in the orientation estimation process of an aircraft navigation system or a ground simulation navigation system, a self-adaptive error decision feedback mechanism is introduced and used for adjusting the angle allowable range according to an error result; the influence of large fluctuation on a measurement calculation result is reduced, and error correction is carried out on a test result; the stepping size is adjusted according to an error correction result to support rapid convergence to an error range under the condition of large errors; and finally, after the error is reduced, the stepping is slowed down, so that the error is further accurately corrected, and a final accurate result is obtained. According to the invention, the problem of inaccurate azimuth angle calculation caused by noise or other interferences is solved.

The application designs a camera self-calibration and target tracking method based on multi-mode information reference in a large airport scene, and belongs to the technical field of computer vision. The application obtains three-level coordinates of an airplane geographic coordinate, actual pixel coordinate and theoretical pixel coordinate through airplane navigation information and camera related parameters, then solves the corresponding matrix of the pixel coordinate and the geographic coordinate according to the geometric characteristics of the geographic coordinate and the corresponding relationship among the three-level coordinates, introduces a typical reference point for external parameter calibration, obtains a detection error through the real-time position of a typical target point solved by the internal and external parameters of the camera, and finally solves the real-time position of a non-cooperative detection target by using the corresponding matrix and combining a target detection algorithm, which has great significance in the field of safety monitoring in a large airport scene.

The present disclosure envisages in the field of navigation of aircrafts, their landing and take-off in low visibility situations. The system (100) comprises User device (200), Terminal (300), Aircraft Speed, Brake & Engine Control Module (500), a server (400) and pass-through points (600). Terminal (300) is configured to Aircraft Speed, Brake & Engine Control Module (500) which is configured to Aircraft Speed System. The server (400) through user device (200) with air traffic controller creates geofences (on the defined stretched of aircraft flight paths, runway zones / taxi bay lanes) and stores rules associated with each such geofences. Terminal (300) when it is found in a geofence gets instructions / messages from server (400) and communicate to Aircraft Speed, Brake & Engine Control Module (500). Aircraft Speed, Brake & Engine Control Module (500) connected to aircraft speed management system accordingly changes / regulates the speed of the aircraft which remains valid until Terminal (300) gets a new instruction / message from server (400) once Terminal (300) is at a new geofence. Precise location coordinates-based navigation map (based on multiple geofences fusion / intersection / overlap) and glidepath is created connecting the centerline of touchdown zone of runway to the terminal (300) of the aircraft when terminal (300) is found at desired descent zone geofence location coordinates. Pilot follows the glidepath i.e. precise navigation map and altitude (and after considering other usual parameters like speed, wind speed and direction) at various stages of landing and take-off without a need of visuals / lighting system which is not available in low visibility situations like fog, heavy rains, night-time etc. The present disclosure provides a solution for landing and take-off in low visibility situation without investing heavily on infrastructure and certification of operations levels of airports like CAT II and CAT III.

A method comprises capturing, with a vehicle vision sensor, a color image of a landing site including landing surface markers; converting the color image to a gray scale image; and performing multi-scale-binarization to detect multiple edges of the gray scale image and produce binary images. The method determines contours of edges of the binary images having closed shapes, detects closed shapes of contours of edges having four corners, and verifies whether four-sided candidate contours are valid as potential landing surface markers. If more than one contour is associated with a valid ID within a surface marker library, then the contour within the smallest window size is selected. If multiple contours with the same window size can be associated with a valid ID, then a mean of corresponding corners of multiple contours is computed. The method then performs corner refinement of valid four-sided candidate contours identified as potential landing surface markers.

The invention discloses a real-time GNSS interference and deception monitoring method and device based on ADS-B time sequence data, and the method comprises the steps: determining the number of effective GNSS satellites according to the GNSS satellite navigation information and ADS-B monitoring data received by ground equipment in real time; if the number of the effective GNSS satellites reaches a first threshold value, whether the GNSS satellite navigation information is interfered or not is judged through the NIC value of the ADS-B monitoring data; if the GNSS satellite navigation information is not interfered, whether the GNSS satellite navigation information is deceived or not is judged according to the current speed of the aircraft; if the number of the effective GNSS satellites does not reach the first threshold value, and / or if the GNSS satellite navigation information is interfered, and / or the GNSS satellite navigation information is deceived, real-time alarming is carried out. The problems that in the prior art, the data demand quantity is large, and the real-time detection requirement of aviation operation is difficult to meet are solved. Technical support is provided for guaranteeing reliability of aircraft navigation information, and improvement of flight safety is facilitated.

Method for controlling a flight path of a controllable aircraft (7) during a flyover of a mirror surface (5) of a reflector (3), preferably a reflector (3) of a heliostat (1) of a solar tower power plant, comprising the following steps: a) Providing the controllable aircraft (7) which has a camera (9) and a stationary marker (11) with a predetermined position which is reflected by the mirror surface (5) of the reflector (3), b) Taking an image of the mirror surface (5) of the reflector (3) using the camera (9) at a position of the controllable aircraft (7) above the reflector (3), c) Evaluating the image and determining a reflection (13) of the marker (11) on the mirror surface (5) in the image, d) Estimating the position of the reflection (13) of the marker (11) on the mirror surface (5), wherein a navigation vector (16) extending from the estimated position of the reflection (13) of the marker (11) on the mirror surface (5) and the position of the controllable aircraft (7) is estimated, and e) Steering the controllable aircraft (7) to a new position of the controllable aircraft (7) by specifying a velocity vector in the direction of the new position, wherein the velocity vector has velocity vector components (20) that are orthogonal to the navigation vector (16) and lie in a navigation plane (19) that is orthogonal to the navigation vector (16), or by specifying a waypoint at the new position, wherein the specified waypoint lies in a navigation plane (19) that is orthogonal to the navigation vector (16).

Systems, apparatuses, methods, and computer program products are provided herein. For example, a method may include generating a vehicle navigation prediction model of a vehicle based at least in part on vehicle configuration data. In some embodiments, the method may include identifying vehicle operational data. In some embodiments, the vehicle operational data is representative of operations of the vehicle when the vehicle is operating. In some embodiments, the method may include generating, based at least in part on applying the vehicle operational data to the vehicle navigation prediction model, navigational performance prediction data. In some embodiments, the method may include initiating performance of one or more navigational prediction actions based at least in part on the navigational performance prediction data.

A computing system for combined aviation and ground mapping for aircraft navigation includes memory storing aviation map data, road map data, and instructions of an air-ground navigation program, and processing circuitry configured to implement the air-ground navigation program. The processing circuitry receives aircraft location data and destination data for a user of the aircraft. The destination data is cross-referenced with the road map data to validate a destination of the user, and a landing site proximate the destination is determined via the aviation map data. An air route segment from the location of the aircraft to the landing site and a ground route segment from the landing site to the destination are generated via respective algorithms. The air and ground route segments are combined to produce a combined air-ground navigation route, and a visual representation of the combined air-ground navigation route is output to a display device.

The present disclosure envisages in the field of navigation of aircrafts, their landing and take-off in low visibility situations. The system (100) comprises User device (200), Terminal (300), Aircraft Speed, Brake & Engine Control Module (500), a server (400) and pass-through points (600). Terminal (300) is configured to Aircraft Speed, Brake & Engine Control Module (500) which is configured to Aircraft Speed System. The server (400) through user device (200) with air traffic controller creates geofences (on the defined stretched of aircraft flight paths, runway zones / taxi bay lanes) and stores rules associated with each such geofences. Terminal (300) when it is found in a geofence gets instructions / messages from server (400) and communicate to Aircraft Speed, Brake & Engine Control Module (500). Aircraft Speed, Brake & Engine Control Module (500) connected to aircraft speed management system accordingly changes / regulates the speed of the aircraft which remains valid until Terminal (300) gets a new instruction / message from server (400) once Terminal (300) is at a new geofence. Precise location coordinates-based navigation map (based on multiple geofences fusion / intersection / overlap) and glidepath is created connecting the centerline of touchdown zone of runway to the terminal (300) of the aircraft when terminal (300) is found at desired descent zone geofence location coordinates. Pilot follows the glidepath i.e. precise navigation map and altitude (and after considering other usual parameters like speed, wind speed and direction) at various stages of landing and take-off without a need of visuals / lighting system which is not available in low visibility situations like fog, heavy rains, night-time etc. The present disclosure provides a solution for landing and take-off in low visibility situation without investing heavily on infrastructure and certification of operations levels of airports like CAT II and CAT III.

The invention discloses an aircraft autonomous navigation system and method based on feature targeting, belongs to the technical field of aviation navigation, and solves the problems that existing aircraft navigation depends on a GPS (Global Positioning System), the anti-interference capability is weak, and continuous navigation cannot be performed in a GPS denial environment. The system comprises a completely airborne landform and landmark feature perception module, a feature target matching module, a navigation control module and a closed loop verification module, satellite navigation signals and ground navigation station real-time data access are completely eliminated, and landform / landmark inherent features are used as unique target references; the sensing module is integrated with a multi-sensor cooperation and environment self-adaptive compensation unit, a spectral range and a signal-to-noise ratio index are defined, and the sensing module is adaptive to all-weather multi-terrain scenes; the matching module dynamically updates a feature library based on a WGS-84 coordinate system and a terrain parallax correction model, and solves the problem of feature single scene matching drift through an improved algorithm; the control module integrates a multi-algorithm fusion and fuel optimization strategy and generates a constraint control instruction; the closed-loop verification module determines a safety threshold and a priority emergency program, and guarantees the flight safety. The method is free of external dependence in the whole process, airborne full-autonomous navigation regulation is completed, and the whole flight stage of the aircraft is covered. According to the invention, continuous and reliable autonomous navigation in a GPS denial environment is realized, the anti-interference and anti-severe environment capability is strong, the positioning precision is high, the method is adaptive to multiple models and multiple scenes, and the engineering practicability is strong.

Method and device for aircraft navigation aid The present invention relates to a method (200) for aircraft navigation aid (100) comprising a GNSS receiver (110) and a barometric altimeter (120), comprising the provision (210) of a mesh comprising a plurality of cells (M_i) of an area of ​​evolution of the aircraft comprising a current position (A(t)) of the aircraft at a current date (t); the calibration (220) of the mesh, comprising the assignment to each cell of a calibration model (C_i(t)) on the basis of GNSS signals and a barometric measurement at the current date, and of a model of propagation of uncertainties between the current position and the cell over a geometric altitude (Z_geo, rec (A',t_est)) which would be determined at a position (A') of this cell (M_i) from a barometric measurement;and for a planned future aircraft position (Aplan(tplan)), the estimate (230) of an uncertainty (DPV(Aplan,tplan)) on a geometric altitude (Z_geo,rec(Aplan,tplan)) which would be determined from a barometric measurement (Z_baro (Aplan,tplan)) at the future position and the calibration of the selected mesh. Figure for the abstract: 2;

The present invention relates to the field of aircraft technology, and more particularly to a method and device for displaying an aircraft instrument interface. The method comprises obtaining the current track of an aircraft and displaying the current track based on first identification information; obtaining the current heading of the aircraft and displaying the current heading based on second identification information; obtaining the current roll slope of the aircraft and displaying the current roll slope based on third identification information; and obtaining the current pitch angle of the aircraft and displaying the current pitch angle based on fourth identification information. The method achieves the simultaneous display of the aircraft's current track, current heading, current roll slope, and current pitch angle, enabling the pilot to monitor aircraft attitude changes while taking into account aircraft navigation information, while also saving space resources of the human-computer interaction interface to a certain extent.

The application relates to the technical field of aircraft navigation and discloses a flight path construction method based on visual intelligence. The method collects a multi-view image sequence of a flight environment through an airborne visual sensor, generates visual observation data with unified time stamps and spatial coordinates through space-time alignment processing, calculates a motion vector field of an aircraft relative to a ground reference based on the light flow features between continuous frames in the data, builds a three-dimensional environmental kinematic model in combination with attitude data of an inertial measurement unit, inversely deduces a current flight path, extracts a key flight path point set of a historical path, constructs an initial topological network of a return flight path according to the spatial distribution density of the key flight path point set, dynamically allocates the connection relationship of network nodes, generates a wind disturbance-resistant candidate return flight path set in combination with real-time meteorological wind field intensity parameters, evaluates the candidate set by using a multi-objective optimization algorithm, and outputs an optimal return flight path meeting a fuel consumption threshold and a flight time constraint.

A system for facilitating navigation of an aircraft comprises one or more processors and a memory coupled to the processors. The memory stores data into a data store and program code that, when executed by the processors, causes the system to detect an infrared site signal indicating a site code transmitted by one or more infrared beacons that form a beacon network around a site. The site code represents a site. In response to detecting the infrared site signal, the system determines the site indicated by the site code. The system searches for two or more infrared beacon signals and detects the two or more infrared beacon signals. In response to detecting the two or more infrared beacon signals, the system determines a location of the aircraft based on the two or more infrared beacon signals.

The application provides an aircraft navigation evaluation method and system based on a combined weight evaluation method, and belongs to the technical field of navigation evaluation. The method comprises the following steps: obtaining original flight parameter data of an aircraft and performing preprocessing, and reconstructing a standard flight path by using a filtering algorithm; calculating the value of a navigation system index by using environmental data, navigation equipment state data, the preprocessed original flight parameter data and the reconstructed standard flight path, generating an index value sequence changing with time; judging a matrix and calculating a subjective weight vector of the index; calculating an objective weight vector of the index; linearly weighting and fusing the subjective weight vector and the objective weight vector according to a dynamic combination factor to generate a final combined weight vector; calculating the arithmetic mean value of the index sequence, and then weighting and synthesizing the combined weight vector to calculate the comprehensive performance score of the navigation system; and generating an evaluation report. The application uses the combined weight evaluation method to comprehensively evaluate the navigation performance, and improves flight safety and task success rate.

An system and method for providing navigational assistance to an aircraft pilot in real time. A series of photos with a fixed field of view are captured and combined to create a panoramic image using an inexpensive still camera mounted on an electric pan motor. The panoramic image is layered with stored terrain data having identical location, and any abnormalities (such as ground or airborne obstructions) are identified. AI software may be used to determine if / what corrective action is required to avoid a collision or other dangerous outcomes.

This invention belongs to the field of aircraft navigation and positioning technology, specifically relating to a method and system for correcting synthetic visual scenes based on a head-up display (HUD). The method involves acquiring airport environment images from airborne visual sensors based on the aircraft's current operational phase; identifying airport ground marking features from these images and matching them with elements in an airport ground feature database; calculating the aircraft's current geographical location using the geographical location information of the matched elements and their relative position to the aircraft's current location; using this geographical location information to correct errors in the airborne positioning equipment; transmitting the corrected image to an airborne synthetic visual scene system; and acquiring aircraft attitude data from airborne sensors to generate a synthetic airport visual scene image from the aircraft operator's perspective, at an angle equal to the external airport road. This invention improves the display accuracy of HUD-based synthetic visual scenes and increases their usability during aircraft operational phases.

Systems and methods for autonomously guiding aircraft are described. The systems and methods may provide a final approach and take off area (FATO) with a guidance system, such as an autonomous approach guidance system, which is configured to facilitate the navigation of the aircraft onto (or out of) the FATO. For example, a FATO may include one or more beacons that assist in the navigation or guidance of aircraft as the aircraft approach and land at the FATO. The guidance system may utilize the beacons, which may include approach beacons and adjustment beacons, to provide information to the aircraft that facilitates a proper approach and landing by the aircraft to or on the FATO.

The invention provides an aircraft navigation evaluation method and system based on a combined weight evaluation method, and belongs to the technical field of navigation evaluation.The method comprises the steps that original flight parameter data of an aircraft are obtained and preprocessed, and a standard flight path is reconstructed through a filtering algorithm; calculating a quantity value of a navigation system index according to the environment data, the navigation equipment state data, the preprocessed original flight parameter data and the reconstructed standard flight path, and generating an index value sequence changing along with time for the index; judging the matrix and calculating subjective weight vectors of the indexes; calculating objective weight vectors of the indexes; performing linear weighted fusion on the subjective weight vector and the objective weight vector according to the dynamic combination factor to generate a final combined weight vector; calculating an arithmetic average value of the index sequence, carrying out weighted synthesis through a combined weight vector, and calculating a comprehensive effectiveness score of the navigation system; and generating an evaluation report. The navigation efficiency is comprehensively evaluated by adopting a combined weight evaluation method, and the flight safety and the task success rate are improved.

The invention provides an aircraft navigation evaluation method and system based on fuzzy comprehensive evaluation, and belongs to the technical field of aircraft navigation evaluation.The method comprises the steps that original flight parameter data of an aircraft are obtained and preprocessed, and a standard flight path is reconstructed through a filtering algorithm; calculating the magnitude of each index of the navigation system based on the original flight parameter data and the reconstructed standard flight path; determining the weight of each index by adopting a combined weight method based on a triangular fuzzy number to form a weight vector; mapping the magnitude of each index to a unified fuzzy comment set through each membership function to obtain the membership of each index to each comment level, and constructing a fuzzy relation matrix; performing fuzzy synthesis operation on the weight vector and the fuzzy relation matrix to obtain a fuzzy comprehensive evaluation result vector; and performing defuzzification processing on the fuzzy comprehensive evaluation result vector, and outputting a comprehensive efficiency score and evaluation report of the navigation system. According to the method, multi-source data and expert knowledge are fused, the navigation efficiency is accurately evaluated, and the flight safety is guaranteed.

The invention relates to the technical field of aircraft navigation and control, in particular to a low-altitude aircraft detection and avoidance method, which comprises the following steps: configuring DAA parameters and dividing an airspace; defining an adaptive net airspace of the flight stage and obtaining an adaptive net airspace detection result; acquiring a maneuvering conflict belt, a maneuvering guide belt and a maneuvering recovery belt; and carrying out intrusion alarm and obtaining the optimal maneuvering mode and direction of the aircraft for avoiding the invading aircraft. The method is used for effectively identifying possible threats of the airspace in which the aircraft is located in a complex low-altitude flight environment, and provides an optimal avoidance strategy with relatively high adaptability.