16 results about "Earth ellipsoid" patented technology

The invention provides an intelligent quality control and inversion method for electric power meteorological multi-source data, and relates to the field of data processing. In the method, a multi-view polarized brightness temperature vector structure is constructed by using original brightness temperature observation data acquired by a plurality of satellite-borne microwave radiometers in a near-synchronous orbit intersection area, and a multi-dimensional radiation transmission equation set driven by an earth ellipsoid path integral model is input to generate a brightness temperature prediction result; an inversion optimization model is constructed based on view angle invariant residual constraint, initialization is carried out based on historical data and ground data, and variational inversion solving is carried out to obtain a joint inversion result; and evaluating the credibility through a profile quality vector, and finally supporting stability early warning and load correction in electric power meteorology. By implementing the technical scheme provided by the invention, the quality control and inversion precision of the power meteorological multi-source data profile can be improved.

The present application relates to the technical field of satellite, in particular to a kind of solar elevation angle calculation method of multi-view axis reference.The view axis is executed for each view axis, and reference coordinate system of view axis is constructed;According to the current attitude of the satellite carrying the view axis and the reference coordinate system of the view axis, the attitude of the view axis under the reference coordinate system is calculated;According to the scaling matrix of the earth ellipsoid under the inertial system, the satellite position vector under the inertial system, the attitude of the view axis under the reference coordinate system, the conversion matrix from the inertial system to the orbital system and the earth radius, the distance vector from the center of the earth to the view axis pointing point in the inertial system is determined;According to the distance vector from the center of the earth to the view axis pointing point in the inertial system, the scaled vector from the center of the earth to the view axis under the inertial system and the unit vector of the sun under the inertial system, the solar elevation angle of the view axis pointing point is determined.The present application can simultaneously accurately calculate the solar elevation angle for multi-view axis reference.

The invention discloses a data fusion processing method based on a meteorological satellite and electronic equipment. The method comprises the following steps: receiving load data for an observation target obtained by MERSI scanning on the meteorological satellite; calculating to obtain a visual vector of the load in the system; converting the visual vector under the load body system into the visual vector under the satellite body system; converting a visual vector under a satellite orbit system into a visual vector under a geocentric rotation system; calculating an intersection point of the visual vector under the geocentric rotation system and a preset earth ellipsoid model; the coordinates of the intersection points are converted into latitude and longitude information to serve as latitude and longitude information of an observation target; based on the brightness value of the MERSI in the load data, calculating to obtain the radiance value of the observation target; and calculating the latitude and longitude information and the radiance value of the observation target to obtain the information of the observation target corresponding to the target service. According to the method and the system, the meteorological satellite data can be quickly and accurately processed, and the processed data can be effectively applied to specific businesses.

The invention relates to the technical field of satellite remote sensing, in particular to a geometric calibration and correction method for an infrared hyperspectral atmospheric detector, which comprises the following steps of: constructing the direction of optical axis light of a field of view of the detector in a satellite body coordinate system pixel by pixel; acquiring the rotation angle of the scanning mirror, calculating the normal direction of the plane mirror, and calculating the direction of reflected light by adopting a reflector formula; acquiring an orbit position and an attitude rotation matrix of a satellite body under an earth-fixed coordinate system; constructing an infrared hyperspectral detector imaging geometric positioning equation, and intersecting a visual axis direction with an earth ellipsoid to obtain a three-dimensional coordinate of a ground point; registering data of the infrared hyperspectral detector with a high-resolution image on the same platform, acquiring geometric coordinates of the high-resolution image as control points, and solving an installation error matrix of the rotating mirror by adopting least square iteration; and substituting the view field parameters of different detectors for calculation to generate the image element geographic coordinates of the infrared hyperspectral detector after geometric correction, thereby realizing error correction from an imaging source.

The present application belongs to the technical field of wireless signal positioning, and discloses a ground-based radiated source TDOA positioning method based on the constraint of the earth ellipsoid. First, the TDOA observation quantity about the ground-based radiated source is obtained by using multiple adjacent space observation platforms, and is converted into a distance difference observation quantity. Then, a scalar product matrix is constructed by using the distance difference observation quantity, and a pseudo-linear observation equation is constructed based on the same. Next, the influence of the distance difference observation error and the prior observation error of the observation platform position vector on the pseudo-linear observation equation is quantitatively analyzed by using a first-order error analysis method, and the singularity problem of the pseudo-linear observation error covariance matrix is avoided by using matrix QR decomposition, so that an optimal weighting matrix is obtained. Then, by using the earth ellipsoid constraint to which the ground-based radiated source is subjected and the algebraic characteristics of the auxiliary variable, a positioning optimization model containing double quadratic equality constraints is constructed. The present application utilizes the earth ellipsoid constraint to which the ground-based radiated source is subjected, and effectively improves the positioning precision.

The invention discloses a calculation method and device for a satellite VDES load coverage area, a storage medium and calculation equipment, and the method comprises the steps: determining the position and attitude of a satellite according to the orbital element number of the satellite, a designated moment and a satellite working mode; determining the direction of a VDES antenna based on the position and attitude of the satellite and the load installation parameters; based on the VDES antenna pointing, constructing a polar plane of a satellite about the surface of an earth ellipsoid, and determining a parameter equation of a space ellipse where the polar plane intersects with the surface of the earth ellipsoid; according to the parameter equation, traversing angle parameters in the space ellipse to obtain a tangent point track and an intersection point track; and calculating a load coverage area of the VDES antenna based on the tangent point track and the intersection point track. The technical problem that the VDES load coverage area is difficult to calculate in the prior art is solved.

The present application belongs to the technical field of wireless signal positioning, and discloses a ground-based radiating source multi-star TDOA / FDOA joint positioning method based on the constraint of the earth ellipsoid. In order to avoid multi-dimensional parameter joint optimization, two binary polynomial equations about the distance and distance rate of change between the ground-based radiating source and the main star are constructed, and a monomial seventh-degree polynomial equation about the distance between the ground-based radiating source and the main star is constructed based on sequential linear convolution operation. A Newton iteration method for explicit optimization of only a single Lagrange multiplier is proposed based on polynomial root operation and implicit function derivation theory. Finally, the optimal value of the Lagrange multiplier and the optimal value of the two auxiliary variables are used to obtain the position parameters of the ground-based radiating source. The simulation experiment results show that, compared with the existing multi-star TDOA / FDOA joint positioning method, the present application can greatly improve the positioning accuracy.

The application discloses a landing point prediction method based on terrain elevation matching, which converts received aircraft track data into coordinates in a geocentric rectangular coordinate system, then performs polynomial fitting on an XYZ data linked list by using a least square method, then calculates intersection points of a fitted track and an earth ellipsoid after superimposing an elevation, iteratively calculates from the intersection points, finally verifies a time point between a time t1 when a target reaches a starting elevation and a predicted landing point time t0, and verifies N time points in a loop, and if the track elevation of each time point is greater than an altitude of the track point projected on a terrain, the verification is passed, and a final predicted landing point position is output. The method verifies the predicted landing point in view of real problems such as a complex terrain environment in a landing point area, finds a first intersection point of a track and a terrain, improves the accuracy of the predicted landing point, and provides a strong support for smoothly carrying out a target range flight test.

The application discloses a slant-axis spherical projection method suitable for a strip-shaped project, calculates the geocentric space rectangular coordinates of each control point of the strip-shaped project area; rotates the central meridian of the earth ellipsoid to obtain a slant-axis ellipsoid E1, so that the sum of the distances from each control point of the strip-shaped project area to the central meridian of the slant-axis ellipsoid E1 is the shortest; changes the slant-axis ellipsoid E1 into a slant-axis sphere E2, and the radius of the slant-axis sphere E2 is the distance from the average elevation of the whole strip-shaped project area to the coordinate origin; calculates the geodetic coordinates of each control point on the slant-axis sphere E2; and finally, performs Gauss projection based on the slant-axis sphere E2 to obtain the Gauss plane coordinates of each control point. The application makes the meridian direction of the strip-shaped project consistent with that of the slant-axis sphere by rotating the ellipsoid, and reduces the deformation caused by the Gauss projection process.

The invention provides a method and a device for determining parameters of a near-equator launched aerospace vehicle. The method comprises the following steps: acquiring target launching demand data, environment data of a target launching area and a target function of an aerospace vehicle launched near the equator; determining a target launching point location according to a preset earth ellipsoid model and a preset atmosphere model; according to the target launch demand data and the environment data of the target launch area, determining design parameters of the space launch vehicle; according to the target function, the target launching point location, design parameters of the aerospace vehicle and a preset system architecture optimization model, first aerospace vehicle parameters are obtained; and performing simulation verification on the first spaceflight vehicle parameter to obtain a second spaceflight vehicle parameter. According to the invention, integrated coupling optimization is carried out on the geographic position of the launching site, the environmental characteristics and the design of the carrier, so that near-equatorial benefits are utilized to the maximum extent, and the overall transportation efficiency is improved.

The application provides a kind of optical remote sensing satellite image dark weak earth edge extraction method and system, it is related to image processing technical field.The method is first to remote sensing image Gauss smoothing and Canny edge detection, obtain initial edge binary image;Then, combined with satellite auxiliary data and earth ellipsoid model, the distance of pixel to earth surface is calculated point by point, the effective edge is screened through distance constraint, and the interference such as cloud layer, noise and the like is eliminated;Then, the boundary is smoothed by morphological closing operation, the contour is extracted and the longest arc length contour is screened, and pixel-level edge positioning is completed;Finally, based on generalized quadratic curve iterative fitting and equidistant real number solution, sub-pixel level edge extraction is realized.The application fuses geometric prior constraint, image detection and high-precision fitting, effectively solves the problem that dark weak low-contrast edge is easy to break and has high false detection rate, and the extraction result is continuous and stable, the precision reaches sub-pixel level, and can meet the high-precision application requirements of satellite edge observation, atmospheric detection, attitude determination and the like.

The present application belongs to the technical field of inertial navigation, and discloses a polar double-inertial navigation state monitoring method based on a Psi angle correction model, which is suitable for state monitoring of a carrier equipped with multiple sets of inertial navigation systems with a rotation mechanism in a polar environment. The present application is aimed at the problem of limited state monitoring of an inertial navigation system under the condition of no external reference information during long navigation in the polar region. Based on a Psi angle error model, the model is defined in a calculation coordinate system, and the position error is decoupled, which is suitable for the characteristics of long navigation in the polar region. A horizontal calculation coordinate system under an earth ellipsoid model is used as a navigation coordinate system, the relative attitude, relative velocity and relative position between two sets of inertial navigation systems are used as constraint observations, and through correction of a velocity error model, the present application avoids the influence of inaccurate solution caused by differential of specific force under dynamic conditions on the state monitoring precision of devices. Strong tracking filtering based on residual normalization is used to monitor the gyro drift and accelerometer zero offset of the two sets of systems online. Further, the state of inertial devices is evaluated according to the monitored error parameters. The method of the present application is completely autonomous and does not depend on external reference information, which has important engineering significance.

The invention provides a distance calculation method and device, a storage medium and computer equipment, and the method comprises the steps: loading a plurality of pieces of first signaling data which are signaling data of track points of a user terminal; performing data preprocessing on the plurality of pieces of first signaling data to obtain a first list containing a plurality of pieces of second signaling data; and calculating a spherical distance between a first track point corresponding to the previous second signaling data and a second track point corresponding to the current second signaling data based on an earth ellipsoid model, a Vincity algorithm and the first list. Considering that the earth surface has the ellipsoid characteristic, the calculation of the distance between the two track points of the user terminal based on the earth ellipsoid model is more accurate, so that the accuracy of calculating the distance between the two track points of the user terminal can be improved.

The invention provides an airborne laser radar-based tide-gauge-free pelagic water depth calculation method and device, electronic equipment and a storage medium, and the method comprises the steps: obtaining laser point cloud data of a to-be-measured sea area, carrying out the preprocessing and classification of the laser point cloud data of the to-be-measured sea area, and obtaining the laser point cloud data of the to-be-measured sea area; outputting submarine topography geodetic high point cloud data under the earth ellipsoid reference; dTU21 global average sea surface model data are obtained, and average sea surface geodetic height data of the sea area to be measured are obtained through interpolation; determining a depth reference plane L value of the sea area to be measured; the water depth value is calculated according to the submarine topography geodetic high point cloud data, the average sea surface geodetic height data and the depth reference surface L value, model transmission errors are reduced, dependence on a tide gauge station is avoided, seamless splicing of water depths between different sea areas can be achieved, the tide gauge station does not need to be erected in an open sea area, and the cost is reduced. And the implementation difficulty and cost of airborne laser water depth measurement are greatly reduced.

The invention relates to the technical field of satellites, in particular to a multi-visual-axis reference solar altitude calculation method. For each visual axis, the following steps are executed: constructing a reference coordinate system of the visual axis; according to the current attitude of the satellite carrying the optical axis and the reference coordinate system of the optical axis, calculating the attitude of the optical axis in the reference coordinate system; according to the earth ellipsoid scaling matrix under the inertial system, the inertial system satellite position vector, the attitude of the optical axis under the reference coordinate system, the conversion matrix from the inertial system to the orbit system and the earth radius, determining a distance vector from the earth center in the inertial system to the pointing point of the optical axis; and determining the solar elevation angle of the visual axis pointing point according to the distance vector from the geocenter to the visual axis pointing point in the inertial system, the scaled vector from the geocenter to the visual axis under the inertial system and the unit vector of the sun under the inertial system. According to the method, the solar elevation angle can be accurately calculated at the same time according to the multi-visual-axis reference.

This invention discloses a method for analyzing and simulating spaceborne SAR coverage performance, used for accurate and efficient analysis of spaceborne SAR coverage indicators and visualization. The method comprises two parts: First, by combining antenna pointing and real-time satellite position, a nadir trajectory map is generated. The intersection of the beam and the Earth ellipsoid is solved using a vector triangle coverage model to visualize the beam coverage area. Second, after coordinate transformation of the target position, the relative radius vector between the satellite and the target is calculated. Target visibility is determined through multi-dimensional coordinate system transformation, and then the single illumination time and revisit time are calculated. This invention uses an accurate Earth ellipsoid model as a benchmark, integrating satellite orbital dynamics, precise coordinate transformation under multi-factor perturbations, and TLE parameter analysis to ensure high-precision analysis. Its process is clear, core steps can be efficiently implemented using mature algorithms, and it features both visualization output and high customizability. It can adapt to different SAR system parameters and scenarios, achieving targeted performance evaluation and optimization, demonstrating outstanding efficiency and practicality.