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Formation flight control method of relative orbit with fixed quasi periodicity J2

A technology of formation flight and relative orbit, applied in the field of control of formation flight spacecraft, can solve problems such as difficult implementation and large amount of calculation

Active Publication Date: 2012-12-12
AEROSPACE DONGFANGHONG SATELLITE
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  • Abstract
  • Description
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  • Application Information

AI Technical Summary

Problems solved by technology

[0007] 4) The existing formation flight control method has a large amount of calculation and is not easy to realize in engineering

Method used

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  • Formation flight control method of relative orbit with fixed quasi periodicity J2
  • Formation flight control method of relative orbit with fixed quasi periodicity J2
  • Formation flight control method of relative orbit with fixed quasi periodicity J2

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Embodiment Construction

[0027] Assuming that one of the satellites in the formation is flying in its scheduled earth orbit or the Halo orbit of the solar-earth system without deviation, for the sake of brevity, it is called the main satellite; the pseudo period J of the present invention 2 The unchanging relative orbit formation flight control method only separately controls the other satellites in the formation except this satellite, and calls these satellites slaves. Control each satellite separately with the same control method, such as figure 1 As shown, through the following steps to complete:

[0028] 1. The initial value of the relative position vector Δr between the slave star and the master star in any given master star orbit coordinate system 0 .

[0029] Define the orbital coordinate system S of the main star (Leader) L (x y z): The origin is taken as the center of mass of the main star, the x-axis is the direction of the vector diameter (earth center to the center of mass), the z-axis is the d...

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Abstract

The invention discloses a formation flight control method of a relative orbit with fixed quasi periodicity J2. The method comprises the steps of: taking a satellite flying on a nominal orbit in a formation flight satellite as a reference layer; exerting control torque Tc on the satellite which does not fly on the nominal orbit in the formation flight satellite to adjust; as for each moment, after giving an initial value of a relative position, calculating a hyperbolic characteristic value with Hamiltonian structure non-controlled J2-type C-W equation and stable and unstable manifolds; and selecting proper control gain, and finally calculating a feedback control torque Tc. According to the method, the control law is obtained on the basis of a more accurate model; just relative position feedback information between two satellites is required; no constraint is generated on the initial value of the relative position, the calculated quantity is small, the fuel consumption is low and a project is easy to realize.

Description

Technical field [0001] The invention relates to a control method of formation flying spacecraft. Background technique [0002] When flying in formation, limited by the effective range of inter-satellite links, the relative positions of formation satellites need to be kept within a certain range. At the same time, position keeping also ensures the relative configuration of the formation satellite group, avoiding collisions between satellites. In addition, special detection tasks such as interferometry also need to maintain the relative azimuth between the satellites, which places higher requirements on maintaining the position of the formation satellites. [0003] The relative periodic motion designed by the C-W equation will no longer be closed under the influence of the earth's J2 perturbation, which is mainly caused by the different meridian rotation rates of the master and slave stars. (When there are more than two formation satellites, it is said that the master satellite ope...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/10
Inventor 刘胜利杨志徐明朱佳敏
Owner AEROSPACE DONGFANGHONG SATELLITE
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