21 results about "Horizon" patented technology

The invention discloses a horizon astronomical telescope pointing error correction method based on machine learning. The method comprises the following steps: recording fixed star data; constructing a telescope rack pointing model, calculating a model coefficient, performing coarse correction on a new observation target, accumulating observation data, and preprocessing the observation data; training the preprocessed training set data by using an XGBoost regression model, predicting condition parameters of a new observation target by using a trained error prediction model to obtain normalized azimuth angle deviation and elevation angle deviation predicted values of the new observation target, and carrying out reverse normalization processing on the predicted values to obtain an actual rack deviation angle; and superposing the rough correction deviation angle and the actual rack deviation angle to serve as a final offset to be injected into a telescope rack tracking program so as to realize correction of a pointing error. According to the invention, the pointing error can be within a very small range, and the pointing precision of the horizon telescope can be effectively improved.

The invention relates to the technical field of geophysical exploration, and particularly discloses a weight control volume generation method and device based on horizon data, and the method comprises the steps: determining a to-be-updated region based on the analysis of an existing seismic section, and delineating an updating target; based on the update target, performing top-bottom interface interpretation to obtain top-bottom layer position information; resampling the top and bottom layer position information to obtain a chromatography grid; carrying out interpolation processing on the chromatography grid by adopting two-dimensional spline interpolation to obtain a speed model grid; and establishing a three-dimensional weight control body by utilizing horizon data under the speed model grid through weight control. The method comprises the following steps: firstly, picking up horizon information of a top-bottom interface of a target area, taking the horizon information as a data basis, carrying out resampling and local two-dimensional spline interpolation on the horizon to obtain a sampling horizon of a target grid, taking the sampled horizon as the top-bottom interface, and establishing an expected weight control body through weight control to realize real local updating.

Systems and methods for photography of a spacecraft during space flight are provided. An autonomous deployable camera (ADC) is configured to capture images and video of a portion of a rocket, such as a crew capsule, as it flies in space with the Earth's horizon in the background and astronauts within the crew capsule visible and recognizable through windows of the crew capsule. The ADC, being reusable, is configured to land on the ground independent of landings or flight trajectories of the crew capsule or other parts of a rocket. The ADC includes a parachute to slow the descent of the ADC and tracking hardware to allow the ADC to be relatively easily recovered on the ground. After recovery, images are downloadable from the ADC.

The invention discloses a ground surface settlement measuring device and a measuring method, and relates to the technical field of measurement, the ground surface settlement measuring device is characterized in that a reference rod is arranged in a reference area, a first measuring rod is arranged in an observation area, the reference rod and the first measuring rod are arranged perpendicular to the horizon, and the reference rod and the first measuring rod are connected through a measuring rope in a straightened state; the sensor assembly is arranged on the measuring rope, and the measuring rope is an elastic rope; and the sensor assembly is used for detecting an included angle between the measuring rope and the horizon so as to determine relative ground surface settlement data of the position of the first measuring rod relative to the position of the reference rod. Compared with ground surface settlement data measured through a static leveling instrument in the prior art, a measuring rod does not need to be installed in a high-precision mode, and the accuracy and efficiency of relative ground surface settlement data measurement can be improved.

The application discloses a method for finely depicting a shallow discontinuous channel based on seismic attributes, and relates to the technical field of oil and natural gas exploration and development. The method is based on amplitude attribute means and combined with a seismic section technology to open a time window in the time domain or the depth domain of a research object. On the basis of seismic horizon interpretation, the method controls two horizons of top and bottom surfaces, splits in the vertical direction along the horizon direction, splits a certain number of sections according to a certain proportion between the two horizons, and sequentially superimposes channel features recognized by amplitude attributes on a single section on a plane graph in sequence. Thus, the method achieves the technical method for identifying a delta front underwater channel with a mud-sand interbedding and mud-bundled sandstone combination in a shallow layer.

The application discloses a kind of synchronous satellite radar track initiation methods based on sky-wave gate correction, belong to the technical field of target tracking in radar data processing.This application is aimed at the problem of a large number of false tracks in track initiation in the target tracking of synchronous satellite radar.It includes establishing north-east sky right-angle coordinate system with sky-wave over-the-horizon radar receiving station as origin, determining the coordinates of synchronous satellite radar transmitting station, synchronous satellite radar receiving station and all measurement points in track initiation period;Determining the track tracking information of sky-wave over-the-horizon radar;According to the track information and state error of sky-wave over-the-horizon radar, establish the tracking gate of sky-wave over-the-horizon radar;Then, based on the traditional logical initiation method, establish the annular initiation gate of synchronous satellite radar;Finally, take the intersection of the annular gate of synchronous satellite radar and the tracking gate of sky-wave over-the-horizon radar as the correction gate of synchronous satellite radar, and perform track initiation, i.e.The starting track of synchronous satellite radar can be obtained.The application is suitable for track initiation in target tracking.

Systems and methods for photography of a spacecraft during space flight are provided. An autonomous deployable camera (ADC) is configured to capture images and video of a portion of a rocket, such as a crew capsule, as it flies in space with the Earth's horizon in the background and astronauts within the crew capsule visible and recognizable through windows of the crew capsule. The ADC, being reusable, is configured to land on the ground independent of landings or flight trajectories of the crew capsule or other parts of a rocket. The ADC includes a parachute to slow the descent of the ADC and tracking hardware to allow the ADC to be relatively easily recovered on the ground. After recovery, images are downloadable from the ADC.

The invention provides a method for calculating the connecting line height from the lowest scattering point of a troposphere to a receiving and transmitting antenna. The connecting line height from the lowest scattering point of the troposphere to the receiving and transmitting antenna is calculated. The spherical distance between the transmitting antenna and the receiving antenna is calculated; the prime unitary circle curvature radius of the earth reference ellipsoid at the transmitting antenna latitude and the receiving antenna latitude is calculated; the linear distance between the transmitting end and the receiving end is calculated; and the connecting line height from the lowest troposphere scattering point to the receiving antenna and the transmitting antenna is calculated. On the basis of the distance between the transmitting antenna and the receiving antenna and the included angle between the receiving antenna and the transmitting antenna, a mathematical model of the height between the lowest troposphere scattering point and the connecting line between the receiving antenna and the transmitting antenna is provided, compared with a method of an ITU-R.P.617 proposal, the troposphere scattering transmission requirement is better met, and in troposphere scattering loss prediction, the troposphere scattering loss prediction accuracy is improved. And the calculation accuracy of parameters such as a scatterer dependency coefficient, elevation angle offset loss and antenna low-frame loss can be improved.

The invention relates to the technical field of geophysical exploration, and discloses a ground penetrating radar horizon tracking method and system based on dynamic time warping. The method comprises the following steps: preprocessing radar data; picking up a layer position seed point; based on the seed points, determining horizon positions in adjacent search windows by using a dynamic time warping algorithm, and synchronously introducing a continuity constraint mechanism to limit horizon mutation; performing anomaly detection, removal and smoothing processing on a tracking result; and finally, the structured horizon information is exported. The system comprises corresponding function modules. According to the method, dynamic time warping and physical continuity constraint are combined, and the stability, accuracy and reliability of horizon tracking under noise interference, discontinuous horizon and complex geological conditions are effectively improved.

This invention provides an intelligent identification system and method for navigation environments during nighttime ship navigation. Addressing the problems of poor infrared image quality, large target scale differences, and difficulty in locating extremely small targets during nighttime navigation, this invention first employs a brightness-noise joint adaptive and structure-constrained wavelet enhancement method to preprocess images, brightening dark areas and suppressing clutter. Second, it constructs a horizon-constrained scale decoupling feature fusion module, based on horizon response weighted features, and decouples these features into branches for large and small targets for adaptive differential fusion. Finally, it designs a point-box collaborative detection head, using point detection for distant, weak targets and box detection for nearby, large targets, fusing the detection results and identifying navigation environment risks. The beneficial effects of this invention are: effectively overcoming the rigidity of scale fusion and unstable positioning defects of traditional methods, and significantly improving the robustness of target detection and intelligent environmental recognition capabilities in complex nighttime navigation scenarios.

Embodiments of the present application disclose a thin sand body reservoir position determination method and device, electronic equipment and a storage medium. The method comprises: determining at least two super-short-term cycles of a to-be-explored area and horizon data of the at least two super-short-term cycles; determining a paleo-channel plane distribution map of the to-be-explored area according to the horizon data of the super-short-term cycles and a paleo-current direction; determining a thin sand body prediction plane distribution map of the to-be-explored area according to the horizon data of the at least two super-short-term cycles by using a seismic inversion technique; and superimposing the paleo-channel plane distribution map and the thin sand body prediction plane distribution map to determine the thin sand body reservoir position. The technical solution of the embodiments of the present application determines the horizon data, the paleo-channel plane distribution map and the thin sand body prediction plane distribution map in turn through the idea of step-by-step constraint, and finally obtains the thin sand body reservoir position. The solution reduces the multiple solutions of seismic prediction and improves the accuracy of determining the thin sand body reservoir position.

The application relates to a sky-wave over-the-horizon radar coordinate registration method based on a reference source auxiliary, which comprises the following steps: firstly, acquiring prior information of ionospheric activity parameters in an estimated ionospheric region and reference source data; secondly, constructing a posterior distribution of the ionospheric activity parameters in the estimated ionospheric region under a Bayesian framework based on the prior information of the ionospheric activity parameters in the estimated ionospheric region and the reference source data; thirdly, solving a moment estimation value of the posterior distribution of the ionospheric activity parameters in the estimated ionospheric region based on a Markov chain, Gibbs sampling and importance sampling; fourthly, substituting the moment estimation value of the posterior distribution of the ionospheric activity parameters in the estimated ionospheric region into an international reference ionospheric model to obtain a posterior ionosphere; and finally, calculating an electromagnetic wave propagation path in the posterior ionosphere by using a three-dimensional ray tracing method to obtain a coordinate registration result of a to-be-positioned target. The application can significantly improve the coordinate registration precision and the sky-wave over-the-horizon radar target positioning precision.

The invention provides an integrated navigation method based on skyline positioning and IMU prior fusion, which belongs to the technical field of navigation, and specifically comprises the following steps: monitoring a GNSS (Global Navigation Satellite System) signal; constructing a priori search space matched with the skyline by using the pose information obtained by the IMU through short-time calculation after the GNSS fails, and generating a priori space constraint according to the current position and an error model; the method comprises the following steps: acquiring a panoramic image of a surrounding environment of a vehicle, processing the panoramic image to extract an actual skyline, matching the actual skyline with a preset digital elevation model (DEM) skyline library under a priori space constraint, and outputting a plurality of candidate positions, selecting an optimal visual positioning result and confidence thereof from the plurality of candidate positions based on the trajectory consistency score; and taking the optimal visual positioning result as pseudo observation information, and using the confidence coefficient of the pseudo observation information to adaptively adjust an observation noise covariance matrix of the integrated navigation filter. According to the scheme of the invention, the navigation precision and robustness are improved.

The present application provides a kind of geological envelope automatic generation method, comprising: defining target work area;The top interface and the bottom interface of the geological envelope in the defined target work area are sparse horizon picking to determine the horizon of top interface, bottom interface and corresponding top interface and bottom interface data;Based on the grid position corresponding to all picking points of top interface horizon and bottom interface horizon, according to the range of top interface data and bottom interface data, the boundary line of geological envelope at top interface and bottom interface in target work area is determined;Determine the horizon depth value in all grid points of top interface and bottom interface;According to horizon depth value, based on the boundary line of geological envelope at top interface and bottom interface, top interface boundary constraint and bottom interface boundary constraint are constructed to determine the intersection between top interface and bottom interface of envelope, to optimize the boundary line of geological envelope at top interface and bottom interface;Based on the optimized boundary line, generate geological envelope three-dimensional visualization model.

This invention discloses an over-the-horizon radar sea clutter propagation and scattering simulation system, belonging to the field of simulation technology. The system adopts a heterogeneous parallel computing architecture, including a radio wave propagation modeling module, a propagation-scattering bidirectional coupling module, and a sea surface electromagnetic scattering modeling module. The output of the radio wave propagation modeling module is connected to the input of the propagation-scattering bidirectional coupling module, the output of the propagation-scattering bidirectional coupling module is connected to the input of the sea surface electromagnetic scattering modeling module, and the output of the sea surface electromagnetic scattering modeling module is connected to the input of the propagation-scattering bidirectional coupling module. Using this system, through propagation-scattering bidirectional coupling, nonlinear time-varying sea surface generation, and a parallel architecture, this invention achieves physically self-consistent, high-fidelity, and high-efficiency sea clutter simulation, accurately reproducing the characteristics of all sea states, and providing key support for over-the-horizon radar performance evaluation, clutter suppression, and atmospheric waveguide inversion.

Using images acquired by a visible light camera, it becomes possible to detect the position of the horizon even at night based on the identification results of other ships' lights. [Solution] The navigation support device for assisting the navigation of a ship includes a light detection unit. The light detection unit detects lights based on color information contained in an image acquired by a visible light camera.

[Problem] A position of a horizon can be detected based on an identification result of a light of an other ship even in the nighttime by using an image acquired by a visible light camera. [Solution] A navigation support device that supports navigation of a ship includes a light detector. The light detector detects a light based on color information included in an image acquired by the visible light camera.

The application discloses an unmanned aerial vehicle horizon real-time detection method and system based on improved YOLO segmentation, and relates to the technical field of horizon detection, and comprises the following steps: S1, acquiring a front view image or a video frame sequence of an unmanned aerial vehicle; S2, performing sky region segmentation by using a lightweight sky segmentation network; S3, extracting a low sky boundary point set from a sky mask; S4, fitting a current frame horizon parameter based on the low sky boundary point set; S5, performing adaptive time sequence smoothing processing based on boundary integrity; and S6, outputting the horizon parameter after time sequence smoothing. The application adopts the unmanned aerial vehicle horizon real-time detection method and system based on improved YOLO segmentation, extracts a sky region by using a lightweight sky segmentation network, reduces the horizon search range from a complex original image to a real demarcation region between the sky and the non-sky, and effectively reduces the interference of buildings, ground textures, cloud changes and complex background edges on the detection result.

The application provides a kind of combination navigation method based on skyline positioning and IMU prior fusion, belong to navigation technical field, specifically includes: monitoring GNSS signal;The pose information obtained by IMU in short time after GNSS failure is used to construct the prior search space of skyline matching, and the prior space constraint is generated according to the current position and error model;Collect the panoramic image of the environment around the vehicle, process the panoramic image to extract the actual skyline, and match the actual skyline with the preset digital elevation model DEM skyline library under the prior space constraint, output multiple candidate positions, and select the optimal visual positioning result and its confidence from multiple candidate positions based on trajectory consistency score;The optimal visual positioning result is used as pseudo-observation information, and its confidence is used to adaptively adjust the observation noise covariance matrix of the combination navigation filter.The scheme of the application improves the navigation accuracy and robustness.

The present disclosure provides a method for drawing a 1% sediment thickness point of the seabed. It belongs to the field of marine surveying and mapping, seabed topography mapping and seabed science and technology, and the method comprises the following steps: interpreting and exporting the horizon data of the seabed and the base surface by Geoframe software; cleaning and sorting the horizon data to obtain the horizon data of a single survey line; cutting, interpolating, subtracting and time-depth conversion of the horizon data to calculate the sediment thickness in the depth domain; calculating the 1% sediment thickness point on each survey line; drawing the seabed surface, the base surface, the sediment thickness, the FOS point coordinates and the 1% sediment thickness point into a profile, and drawing the planar distribution map of the 1% sediment thickness point by QGIS software. The present disclosure guarantees the accuracy of the calculation of the 1% sediment thickness point to the maximum extent by interpreting the long cable seismic profile and using the high-precision time-depth conversion relationship, and meets the requirements of the calculation of the 1% sediment thickness point in the 76th article of the United Nations Convention on the Law of the Sea.

The invention relates to a method, a system and equipment for measuring an incident light compensation angle of a downlink light sensor. The method comprises the following steps: acquiring attitude information of an aircraft 1, time service of a global satellite navigation system and latitude and longitude coordinates of the aircraft 1; acquiring attitude information of the stability augmentation holder 2; the stability augmentation holder 2 is arranged in a yaw axis following mode and is used for realizing that the visual axis of the imaging spectrometer is in the nadir direction; according to the attitude information of the aircraft 1 and the attitude information of the stability augmentation holder 2, angle compensation values of a downlink light irradiance measurement sensor in the rolling and pitching directions are calculated; the downlink light irradiance measurement sensor is provided with a transverse rolling and pitching two-dimensional adjusting mechanism, and the optical axis of the downlink light irradiance measurement sensor points to the zenith according to the angle compensation values in the transverse rolling and pitching directions and the transverse rolling and pitching two-dimensional adjusting mechanism; a sunlight direct incidence angle is calculated according to latitude and longitude coordinates of the aircraft 1 and time service of a global satellite navigation system. According to the invention, more accurate measurement of the sunlight direct incidence angle is realized.