Rapid design method of near-earth inclined orbit launch window

A technology of launch window and inclined orbit, which is applied in computing, special data processing applications, instruments, etc., can solve the problems of insufficient design accuracy, large amount of calculation, and accuracy impact, so as to facilitate secondary development, ensure design accuracy, and facilitate rapid development. design effect

Active Publication Date: 2017-05-31
SHANGHAI SATELLITE ENG INST
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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

Method used

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  • Rapid design method of near-earth inclined orbit launch window
  • Rapid design method of near-earth inclined orbit launch window
  • Rapid design method of near-earth inclined orbit launch window

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Embodiment Construction

[0019] The preferred embodiments of the present invention are given below in conjunction with the accompanying drawings to describe the technical solution of the present invention in detail.

[0020] Such as Figure 1 to Figure 3 As shown, the rapid design method of launch window in near-Earth inclined orbit includes the following steps:

[0021] Step 1. Set the calculation conditions, including the calculation time period, networking conditions constraints, illumination angle and its change direction conditions constraints, satellite trajectory into orbit and other information;

[0022] Step 2: Calculate the front and back intervals of all windows that meet the constraints of the networking conditions within the specified time period at one time, and give them in the form of Julian days for subsequent calls;

[0023] Step 3: Calculate the front and back intervals of all windows that meet the illumination conditions within the specified time period at one time, and give them ...

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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 ...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/00G06F2111/04
Inventor 许哲沈庆丰叶小舟黄欣李绿萍李楠陆启省李鉴邓武东袁双
Owner SHANGHAI SATELLITE ENG INST
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