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Method of maintaining relative orbits of near-Earth spacecraft in Earth's perturbed gravitational field

A technology of relative motion, gravity, applied in the field of aerospace

Active Publication Date: 2018-01-19
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

In general, there is currently no accurate, reliable, and adaptable periodic orbit initialization method for the relative motion of spacecraft in low-Earth orbit, nor a universally effective, Control strategy to save fuel consumption

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  • Method of maintaining relative orbits of near-Earth spacecraft in Earth's perturbed gravitational field
  • Method of maintaining relative orbits of near-Earth spacecraft in Earth's perturbed gravitational field
  • Method of maintaining relative orbits of near-Earth spacecraft in Earth's perturbed gravitational field

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Embodiment Construction

[0083] The present invention is described in further detail below:

[0084] The time-discrete method is used to solve the master-slave star relative motion model, and the three components of the relative motion state vector are assumed to be the periodic solution form of Fourier series. Then, through time discretization in the period, the algebraic equations of the discretized system are obtained. By selecting the appropriate fixed point iterative calculation method and the iterative initial value, the estimated solution of the periodic solution is obtained, which is the accurate initial value of the relative periodic motion. After solving the system model with the time-discrete method, an estimated solution with high accuracy can be obtained, but due to calculation errors in the solution process, the relative motion trajectory obtained from the initial condition is not completely closed, but a drift rate is relatively slow The approximate periodic orbit of . We project the s...

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Abstract

The invention discloses a method for keeping a relative motion orbit of a near-earth spacecraft in an earth's perturbation gravitational field. Through modeling relative motion of a near-earth orbit satellite under an effect of earth's oblateness perturbation and providing a periodic solution estimation scheme based on a time discretion method, an initial condition of periodic relative motion can be accurately estimated in a simple and effective way and the dynamic characteristic variation of the relative motion orbit of the near-earth spacecraft under an effect of earth gravity perturbation is quantitatively studied. An accurate and reliable mathematical model and data reference are provided to orbit design of an aircraft in a fly-around stage in a formation flying task and other tasks of the aircraft. And moreover, a keeping scheme of introducing a closed projection orbit to the relative motion orbit is combined with a DLQR control method to design a control strategy with high efficiency and low fuel consumption.

Description

technical field [0001] The invention belongs to the field of aerospace technology, and relates to a method for maintaining a relative motion orbit of a near-earth spacecraft, in particular to a method for maintaining a relative motion orbit of a near-earth spacecraft in an earth perturbation gravitational field. Background technique [0002] The relative motion of spacecraft in low-Earth orbit has attracted the attention of a large number of related researchers in the past few decades. Many dynamics and kinematics models of the two-body problem have been proposed one after another, and the most famous mathematical model of relative motion is the C-W equation. The C-W equation provides a method for solving the periodic orbit of the relative motion of a spacecraft in a near-circular orbit. However, some assumptions adopted in the C-W equation (assuming a circular orbit, ignoring the oblateness of the earth, etc.) will cause the error of the model to seriously deviate from rea...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24G06F17/50
CPCB64G1/242G06F30/20
Inventor 代洪华汪雪川孙冲岳晓奎袁建平
Owner NORTHWESTERN POLYTECHNICAL UNIV
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