Autonomous celestial navigation method for deep space explorer on swing-by trajectory

Abstract

The invention relates to an autonomous celestial navigation method for a deep space explorer on a swing-by trajectory. The autonomous celestial navigation method comprises the following steps: establishing the corresponding equation of state according to the distance to a planet; calculating the location information of the planet by using the sensitive starlight angle distance detected by a star sensor and calculated by pure astronomic and geometry analytic method; and estimating the parameters of the navigation system by using a fuzzy multiple-model adaptive unscented Kalman filtering (FMMUKF) method. The invention is suitable for the navigation location of a deep space probe on a swing-by trajectory and applicable to the determination of navigation parameters of the deep space probe on a multi-celestial-body intersection swing-by trajectory, belonging to the technical field of aerospace navigation.

Description

technical field [0001] The invention relates to a navigation method for a deep-space probe on a power-flying orbit, which can be used for accurately determining the navigation parameters of the deep-space probe on a multi-celestial body rendezvous and flying orbit. Background technique [0002] The leveraged flight orbit is different from the free flight orbit. It uses the second gravitational body to change the energy of the probe relative to the central gravitational body, thereby changing the magnitude or direction of the probe’s velocity to save launch energy. Accelerate the detector without any power consumption, complete the detection task, and even realize the long-distance detection task that cannot be realized by the detector carried by the launch vehicle at present. Although the leveraged flight orbit has the advantages of requiring less launch energy and multiple missions can be realized in one launch, its disadvantage is that the design is very complicated, the o...

AI Technical Summary

Problems solved by technology

However, there are still many deficiencies: (1) There is an error between the switching of the state model and the actual model, and the filter has a low self-adaptive ability to the accuracy of the model. Filtering accuracy; (2) The adaptive ability of the filter to the measurement noise is low, because the measurement information used is the position information obtained through pure astronomical geometry calculation, rather than direct astronomical measurement, resulting in The measurement noise covariance matrix of the measurement noise is not only the measurement noise variance of the measuring instrument, but also various other calculation errors, and these errors will be affected by the measurement error, the geometric relationship between the navigation star and the detector, and the detector Due to the influence of various factors such as the distance from the sun and Mars, these factors make the measurement noise covariance matrix not a constant matrix, resulting in the filter not being able to track changes in measurement noise in real time

[0005] To sum up, at present, the determination of the navigation information of deep space probes on the leveraged flight track is usually carried out by pure astronomical geometric analysis method alone for navigation and positioning, and the accuracy of different state models is different, and the accuracy of the model itself is also constantly changing, resulting in low navigation accuracy; and because The accuracy of the pure astrogeometric analysis method is greatly affected by the measurement noise, so the filtering method cannot track the change of the measurement noise in real time, and the navigation accuracy cannot be guaranteed

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