On-satellite rapid calculation method and system suitable for multiple time windows of ground detection tasks

Abstract

The invention provides an on-satellite rapid calculation method and system suitable for multiple time windows of a ground detection task. The method comprises the steps that S1, determining task window calculation constraints ; S2, calculating coordinates of longitude and latitude of tasks under a J2000 system; S3, calculating a time parameter and a longitude parameter of the latitude where a first orbit passes through a target point after the set time of each satellite; S4, calculating the time when 2N satellites pass through the latitude where the target point is located within the set timeN circles of orbit periods, finding out a time point when the longitude difference between each orbit and the ground target point is small, and obtaining the orbit number information corresponding tothe vertex; S5, performing orbit recursion to obtain a minimum value point of the distance between each satellite and each target point, and calculating a side swing angle and a solar altitude angle.S6, outputting a window calculation result according to the constraint condition and the screening rule; and S7, obtaining on-satellite rapid calculation result information suitable for multiple timewindows of the ground detection task. The invention can be well applied to various satellites.

Description

technical field [0001] The present invention relates to the field of earth detection technology, in particular to a method and system for on-board rapid calculation applicable to multiple time windows for earth detection missions. Background technique [0002] Satellite-to-earth exploration tasks generally include electromagnetic environment detection, meteorological and hydrological information acquisition, target area imaging remote sensing, etc. These tasks require satellites to perform when the relevant geographical location or area is over the top or visible, and must meet certain load or platform constraints. These constraints usually include the mission center point, the size of the mission area, the effective field of view of the payload, the altitude angle of the sun when the satellite passes through the mission area, the duration of the visible arc, the roll angle, etc. For electromagnetic environment detection tasks, the satellite is oriented to the ground, the an...

AI Technical Summary

Problems solved by technology

The patent adopts a hypothetical model of circular orbit, which only supports fast and rough calculation within one orbit, and there is still room for improvement in modeling methods and technical effects

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