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A Calculation Method of Space Operation Relative Orbit Control Error Based on Unscented Recursion

A technology of relative orbits and calculation methods, applied in navigation calculation tools, integrated navigators, etc., can solve problems such as difficulty in solving work

Active Publication Date: 2018-12-21
BEIJING INST OF CONTROL ENG
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Problems solved by technology

However, this method needs to solve the analytical Jacobian matrix for the nonlinear function before the simulation analysis, and the complex function mapping relationship in the relative orbit control system will make this solution work more difficult

Method used

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  • A Calculation Method of Space Operation Relative Orbit Control Error Based on Unscented Recursion
  • A Calculation Method of Space Operation Relative Orbit Control Error Based on Unscented Recursion
  • A Calculation Method of Space Operation Relative Orbit Control Error Based on Unscented Recursion

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Embodiment Construction

[0111] Below in conjunction with accompanying drawing and specific embodiment the present invention is described in further detail:

[0112] Such as figure 1 Shown is a schematic diagram of the calculation process of the calculation method of the relative orbit control error of space operation based on traceless recursion. It can be seen from the figure that a calculation method of relative orbit control error of space operation based on traceless recursion is characterized in that: the error calculation method Including the following steps:

[0113] Step (1), error recursive calculation

[0114] set t k The mean value of time error recursion state is The error covariance matrix is It can be expressed as:

[0115]

[0116]

[0117] in,

[0118] for t k The position of the target spacecraft in the geocentric equatorial inertial coordinate system at any time, m;

[0119] for t k The velocity of the target spacecraft at the moment in the earth-centered equato...

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Abstract

The invention provides a method for calculating control errors of relative orbits of space operation based on traceless recursion and relates to the field of analysis of the distribution condition of the relative orbits in a space operation task aiming at design parameters of initial positions, sensors, execution mechanisms and the like. According to the method, the deterministic sampling is carried out according to the number of dimensions of a system, and recursion processing is carried out on the mean value of main random variables and an error covariance matrix by virtue of traceless conversion in a time domain. The method is superior to an error calculation method based on Monte Carlo calculation in the aspects of data processing capacity and processing time. Meanwhile, the traceless conversion is only similar to Gaussian distribution of state variables of the system but not similar to nonlinear functions of the system, so that the dissolving of a Jacobian matrix is avoided; and compared with a linear covariance calculation method, the method is easier to be realized.

Description

technical field [0001] The invention relates to the field of analyzing the distribution status of relative orbit control errors in space operation tasks, in particular to a method for calculating relative orbit control errors of space operations based on traceless recursion. Background technique [0002] Relative orbit control technology is an indispensable core technology in space operation missions. This technology is mainly to enable the spacecraft to safely and effectively approach the space mission target, establish and maintain a stable relative orbital motion state near the target, and provide strong support for subsequent on-orbit operations. The error of relative orbit control is a core index to measure the technology. [0003] The error of relative orbit control is mainly described by the mean value and covariance matrix of the error. Since the relative orbit control system is a complex nonlinear stochastic system, the dynamic characteristics of the system are re...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C21/24G01C21/20
CPCG01C21/20G01C21/24
Inventor 王楷汤亮王大轶何英姿魏春岭石恒
Owner BEIJING INST OF CONTROL ENG
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