Long-term evolution rapid analysis method for inclined geosynchronous orbit

A geosynchronous orbit, fast analysis technology, applied in design optimization/simulation, instrumentation, electrical digital data processing, etc., can solve the problems of slow and incomplete analysis of long-term evolution of IGSO orbit

Active Publication Date: 2020-12-04
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

[0003] The purpose of the present invention is to solve the problem of slow and incomplete analysis of the long-term evolution of the IGSO orbit in the prior art, and to provide a fast analysis method for the long-term evolution of the inclined geosynchronous orbit

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  • Long-term evolution rapid analysis method for inclined geosynchronous orbit
  • Long-term evolution rapid analysis method for inclined geosynchronous orbit
  • Long-term evolution rapid analysis method for inclined geosynchronous orbit

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Embodiment Construction

[0133] In order to better illustrate the purpose and advantages of the present invention, the specific implementation manners of the present invention will be further described below in conjunction with the accompanying drawings.

[0134]This embodiment discloses a fast analysis method for the long-term evolution of an inclined geosynchronous orbit. In order to verify the method, first, a typical IGSO orbit, which is a tundra orbit with a certain eccentricity, is selected as the main research object. Parameters such as initial orbital elements, satellite surface reflection coefficient, and surface-to-mass ratio are shown in the table below. The initial epoch time, InitialEpoch, is 11:17:04 UTC on May 15, 2020, and the corresponding Julian day is 2458984.97018519.

[0135] Table 1 Initial parameters of selected IGSO orbits

[0136]

[0137] Step 1: Deriving the average perturbation potential function;

[0138] From equations (8), (18), (34), (35), and (40), the quadratic a...

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Abstract

A long-term evolution rapid analysis method for an inclined geosynchronous orbit comprises the following steps: firstly, deducing a primary or secondary average perturbation force function of each perturbation item, including 1:1 resonance parts of earth non-spherical perturbation field harmonic items J22, J31, J32, J33, J41, J42, J43 and J44 with harmonic items, sun-moon gravitation perturbationLegendre expansion intercepting 4-order items and solar light pressure perturbation; secondly, establishing a secondary average semi-analytical orbit recursor of the IGSO orbit through a Lagrange typeorbit perturbation equation in combination with an average perturbation force function; comparing and analyzing IGSO orbit long-term evolution conditions under consideration of different perturbationsources and orders, so that the model is simplified, and the orbit recursion efficiency is further improved; and finally, by means of efficient orbit recursion, drawing a series of dynamic grid diagrams of complete orbit elements and initial epoch moment combinations, wherein the divisible orbit elements are (e, i, [Omega], [omega]), all binary combinations of the divisible orbit elements are e-i, [omega]-[Omega];e-[omega], i-[Omega], e-[Omega], i-[omega], all binary combinations of the initial epoch moment are InitialEpoch-e, InitialEpoch-i, InitialEpoch-[Omega], and InitialEpoch-[omega], and rapid and comprehensive analysis of IGSO orbit long-term evolution is completed according to the dynamic grid chart.

Description

technical field [0001] The invention relates to a long-term evolution fast analysis method of an inclined geosynchronous orbit, in particular to a spacecraft orbit semi-analytic recursion and dynamic grid diagram analysis method, and belongs to the field of spacecraft orbit dynamics. Background technique [0002] Inclined geosynchronous orbit (IGSO) has important application value in satellite communication and satellite navigation. The long-term evolution analysis of the IGSO orbit provides important information for the mission design and mission post-processing of the corresponding satellites, and the rapidity of the long-term evolution analysis helps to provide more information and is conducive to the rapid iteration of mission design. In the long-term evolution analysis of the earth satellite orbit, it is an effective means to use the semi-analytical orbit recurrence method to draw the corresponding dynamic grid diagram. Literature (Gkolias Ioannis, Colombo Camilla. "To...

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Application Information

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IPC IPC(8): G06F30/20G06F119/14
CPCG06F30/20G06F2119/14
Inventor 张景瑞肖前李林澄陈国玖张尧
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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