Earth-fixed reference system data-based rapid satellite transit time calculation method
A technology for transit time and rapid calculation, applied in the fields of calculation, electrical digital data processing, special data processing applications, etc., can solve the problems of large amount of calculation, complex model, high calculation accuracy, and achieve the effect of satisfying fast response
Active Publication Date: 2016-12-21
CHINA XIAN SATELLITE CONTROL CENT
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[0003] The traditional satellite transit time calculation method calculates the intersection point between the center of the satellite payload beam and the earth through the step-by-step conversion of the satellite body coordinate system, satellite orbit coordinate system, inertial system, and ground-fixed system, and regards the projection area of the payload beam on the earth as a Ellipse, the advantage is high calculation accuracy, the disadvantage is that the model is complicated, the calculation amount is large, and it is not suitable for fast calculation
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[0020] The present invention will be further described below in conjunction with the accompanying drawings and embodiments, and the present invention includes but not limited to the following embodiments.
[0021] The invention provides a fast calculation method of satellite transit time based on satellite ground-fixed data, the main idea is: use satellite ground-fixed data to calculate the intersection point between the satellite load beam center and the earth's surface, and project the load beam on the ground The area is simplified into a circle, so that the satellite transit time of the ground target point can be quickly calculated, which has the advantages of fast calculation and high accuracy. The calculation process is as figure 1 shown, including the following steps:
[0022] Step 1: Set the maximum roll angle β that can cover the ground when the satellite payload is working. Set the roll angle β according to the maximum roll angle of the satellite in the rolling dire...
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The invention provides an earth-fixed reference system data-based rapid satellite transit time calculation method. The method comprises the following steps of firstly setting a maximum side swing angle <beta> for covering the ground during the effective load work of a satellite; calculating the normal vector (the symbol is as shown in the specification) of the orbit plane; calculating a coordinate of an intersection point E between a load wave beam center of the satellite under an earth-fixed reference system and the earth surface; and calculating a radius arc length of a projection circle, on the earth surface, of a load wave beam and a spherical distance from a ground detection point to the intersection point E in sequence by utilizing earth-fixed reference system data of the satellite, so as to finally obtain a satellite transit time of the ground detection point. According to the method provided by the invention, a simple and easy calculation model is adopted, the calculated result basically accord with the practical condition; and the method has the advantages of being rapid and satisfying the rapid response to coverage tasks in hotspot regions.
Description
technical field [0001] The invention relates to a calculation method of satellite transit time, belongs to the field of measurement and control management of in-orbit spacecraft, and is suitable for calculating the transit time of a small viewing angle under the side swing condition of a near-earth satellite. Background technique [0002] In order to quickly respond to the observation needs of special areas, it is necessary to calculate whether multiple satellites can observe special areas as soon as possible and accurately calculate the transit time. With the continuous increase of the number of earth observation satellites, it is urgent to allocate and dispatch resources reasonably, realize multi-satellite joint earth observation, and improve observation efficiency. The prerequisite is to quickly calculate the satellite's coverage of ground target points. To sum up, a method for quickly calculating satellite transit time is needed. [0003] The traditional satellite trans...
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IPC IPC(8): G06F19/00
CPCG16Z99/00
Inventor 赵鞭王安王西京洪涛陈军李剑锋高敏赵军陈学军徐晓慧曹继宏张国云张莹刘涌袁勇张伟张波龙定央
Owner CHINA XIAN SATELLITE CONTROL CENT