Method for optimizing orbital transfer strategy of geostationary orbit satellite

An optimization method and geostationary orbit technology, applied in the direction of artificial satellites, etc., can solve problems such as large amount of calculation, increased calculation amount, and time-consuming

Active Publication Date: 2012-04-25
CHINA ACADEMY OF SPACE TECHNOLOGY
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Problems solved by technology

According to the actual situation, there are many algorithms for nonlinear programming problems. Generally, the exhaustive method can be used. It is characterized by a simple, time-consuming, and computationally intensive algorithm. Its disadvantage is that the sampling points need to be dense enough to find a comparison Accurate global optimal solution, and it is difficult to determine a reasonable sampling range and sampling density when the nature of the function is not clear enough. In addition, when the number of parameters to be optimized increases, the amount of calculation will increase rapidly

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  • Method for optimizing orbital transfer strategy of geostationary orbit satellite
  • Method for optimizing orbital transfer strategy of geostationary orbit satellite

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Embodiment Construction

[0038] Such as figure 1 As shown, the present invention provides a method for optimizing the orbit change strategy of a geostationary orbit satellite, and the steps are as follows:

[0039] (1) Determine the number of orbit changes n required for the satellite to start from the current orbit to the target orbit, specifically through the following steps:

[0040] (1.1) by formula Calculate the total velocity delta dv required to maneuver from the current orbit to the target orbit in pulses, where v 0 and v 1 the velocity of the satellite at the apogee before and after the orbit change, and Among them, μ is the gravitational constant, r a is the earth center distance of the satellite at the apogee; a 0 , a 1 Indicates the semi-major axis of the current orbit of the satellite; δ indicates the angle between the two orbital planes;

[0041] (1.2) Through the formula dm=m 0 (1-exp(-dv / Isp / g)) calculates the propellant mass dm required to maneuver from the current orbit t...

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Abstract

The invention relates to a method for optimizing an orbital transfer strategy of a geostationary orbit satellite, which comprises the following steps of: 1, determining orbital transfer times, orbital transfer circle times and the controlled variable of each-time orbital transfer; and 2, determining time and a thrust direction in each-time orbital transfer. The process of launching the geostationary orbit satellite at present generally comprises the following steps of: launching the satellite into a highly elliptic transfer orbit with an inclination angle by using a carrier rocket; performing apogee/perigee orbital transfer for several times by using a self-contained liquid engine of the satellite, and transferring to a geosynchronous orbit; and correcting and rounding the inclination angle of the orbit to realize a geostationary orbit. For the satellite, operation for changing the transfer orbit into the geostationary orbit by performing apogee/perigee orbital transfer for several times is complex, so too many orbital transfer times is not suitable, and orbital transfer complexity and risk are prevented from being increased; in addition, factors such as the capacity of the liquid engine of the satellite, arc segment loss in an orbital transfer period, and the like are considered, so too few orbital transfer times is not suitable.

Description

technical field [0001] The invention relates to a strategy optimization method for orbit change of geostationary orbit satellites. Background technique [0002] The orbit change strategy design of geostationary satellites is a kind of orbit maneuvering problem, which can be solved by using the maximum and minimum value method in mathematics, or it can be classified as a nonlinear programming problem, and the corresponding algorithm can be used to solve it. According to the actual situation, there are many algorithms for nonlinear programming problems. Generally, the exhaustive method can be used. It is characterized by a simple, time-consuming, and computationally intensive algorithm. Its disadvantage is that the sampling points need to be dense enough to find a comparison Accurate global optimal solution, and it is difficult to determine a reasonable sampling range and sampling density when the nature of the function is not clear enough. In addition, when the number of para...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/10
Inventor 侯芬经姚翔刘建功石明杨凌轩吕红剑
Owner CHINA ACADEMY OF SPACE TECHNOLOGY
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