11 results about "Aircraft vectoring" patented technology

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.

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.

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 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.

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.

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 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.