Rapid Design Method of Launch Window in Low-Earth Inclined Orbit

Abstract

The invention discloses a rapid design method of a near-earth inclined orbit launch window. The method comprises the following steps of (1) setting computing conditions which include a computing time period, networking condition constraints, an illumination angle and change direction condition constraints thereof and a satellite orbit entering trajectory; (2) computing front edge or back edge intervals of all windows which meet the networking condition constraints in the specified time period once, and giving the front edge or back edge intervals in a Julian day form for transferring by subsequent links; and (3) calculating front edge or back edge intervals of all windows which meet the illumination condition in the specified time period once, and giving the front edge or back edge intervals in a Julian day form for transferring by subsequent links. Typical launch window constraints can be combed, input and output are clear, and the constraints are calculated and then collected independently, so that secondary development of increasing or reducing constraints is facilitated, fast design of the launch window by an overall designer of a satellite is facilitated, and the design accuracy is ensured.

Description

technical field [0001] The invention relates to a design method, in particular to a rapid design method of a near-earth inclined orbit launch window. Background technique [0002] Near-Earth inclined (non-sun-synchronous) orbit satellites have many characteristics such as traversal, freezing, and low-latitude coverage. They are suitable for a variety of application scenarios and have been increasingly adopted by satellite designers. Unlike sun-synchronous orbits, which have the same daily launch window, non-sun-synchronous orbits have different daily launch windows. For the calculation of the window, the currently widely used traversal calculation method sequentially determines whether the orbital characteristics corresponding to each time element meet the design constraints, and sorting out the set of all eligible elements is called the launch window. This method is simple and reliable, but it has a large amount of calculation. If the window calculation is performed for a ...

AI Technical Summary

Problems solved by technology

This method is simple and reliable, but the amount of calculation is large. If the window calculation is performed for a whole year, the calculation time will be long, and the accuracy will also be affected by the size of the microelement.

[0003] With the development of aerospace technology, the shortening of satellite development cycle and the increase of development tasks, due to the slow design speed and insufficient design accuracy of traditional design methods, it can no longer meet the current satellite design requirements

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