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An autonomous positioning method for spacecraft based on nonlinear h∞ filtering

A technology for autonomous positioning and spacecraft, applied in the direction of integrated navigators, etc., to achieve strong practicability, enhance the ability to overcome the influence of star catalog errors, and increase the effect of calculation

Active Publication Date: 2018-01-05
BEIJING INST OF CONTROL ENG
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  • Application Information

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Problems solved by technology

Limited by the current level of astronomical observations of X-ray pulsars and the accuracy of the model, the angular position data of pulsars used to establish the observation equation will inevitably have errors

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  • An autonomous positioning method for spacecraft based on nonlinear h∞ filtering
  • An autonomous positioning method for spacecraft based on nonlinear h∞ filtering
  • An autonomous positioning method for spacecraft based on nonlinear h∞ filtering

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Embodiment Construction

[0039] Specific embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0040] In the pulsar navigation system, the pulsar catalog error is reflected as the uncertainty of the measurement model. In a system with model uncertainty, how to design a filter so that its estimated results meet certain design index requirements belongs to the research category of H∞ filtering. Different from optimal filtering algorithms such as traditional Kalman filtering, H∞ filtering considers the influence of model uncertainty in the design stage, and uses the prior knowledge about model uncertainty to optimize the design of the filter gain array, so that the The information in the system model and observations is used reasonably, thereby suppressing the adverse effects of model uncertainty on the estimation accuracy. The process of the pulsar navigation method based on nonlinear H∞ filtering can be summarized as follows: se...

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Abstract

The invention provides a self-locating method for a spacecraft based on non-linear H-infinity filtering. According to the method, the projections of the position vector and velocity vector of the spacecraft on an earth-centered inertial reference frame are selected as state variables, the orbital kinetic equation of the spacecraft is used as a system model, the time transformation equation of a pulsar is used as a measurement model, ephemeris errors of the pulsar are described as bounded errors in the model, and a non-linear H-infinity filtering algorithm used for state estimation is designed based on the models; and then, the designed non-linear H-infinity filtering algorithm is used to process a sequence of observed quantities of pulse arrival time, and the position and velocity of the spacecraft are calculated and estimated through recursion. The method provided by the invention can strengthen the capability of an X-ray pulsar navigation system in overcoming influence of ephemeris errors and enhance self-locating precision of the spacecraft.

Description

technical field [0001] The invention relates to a spacecraft autonomous positioning method based on nonlinear H∞ filtering, and belongs to the technical field of spacecraft autonomous navigation. Background technique [0002] X-ray pulsar navigation, as a new autonomous navigation technology for spacecraft, is one of the research hotspots in the field of aerospace technology at home and abroad. The results obtained by the research team funded by NASA (National Aeronautics and Space Administration) and DARPA (Defense Advanced Research Projects Agency) have demonstrated the great potential of X-ray pulsars in the field of navigation. The Institute and others are developing X-ray detectors for space navigation. [0003] A typical pulsar navigation method is to establish the state equation based on the orbital dynamics model of the spacecraft, establish the observation equation based on the pulsar angular position information and the pulsar time model, and use an appropriate fi...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C21/24
CPCG01C21/24
Inventor 熊凯石恒王磊魏春岭
Owner BEIJING INST OF CONTROL ENG