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Formation-flying-oriented relative navigation speed measurement and combined navigation method

A technology of formation flight and relative navigation, applied in the field of autonomous navigation of formation flight based on astronomical speed measurement and ranging information, can solve the problems of limited navigation accuracy and need to be improved, and achieve the effect of high precision

Inactive Publication Date: 2014-07-02
WUHAN UNIV OF SCI & TECH
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Problems solved by technology

However, the relative navigation accuracy is still limited and needs to be improved

Method used

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  • Formation-flying-oriented relative navigation speed measurement and combined navigation method
  • Formation-flying-oriented relative navigation speed measurement and combined navigation method
  • Formation-flying-oriented relative navigation speed measurement and combined navigation method

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Embodiment Construction

[0054] The technical scheme of the invention can adopt computer software to support the automatic operation process. The technical solution of the present invention will be described in detail below in conjunction with the drawings and embodiments.

[0055] In the present invention, the number of flying spacecraft in formation is 2, which can be recorded as spacecraft 0 and spacecraft 1. The embodiment deals with the formation flight of Mars probes, which can be recorded as Mars probe 0 and Mars probe 1 respectively.

[0056] Firstly, the orbits of the formation flying spacecraft are given, as shown in Table 1.

[0057] Table 1 Initial orbital parameters of formation flight

[0058]

[0059]

[0060] A relative navigation speed measurement method provided in the embodiment is based on a relative speed measurement model to perform relative navigation speed measurement, specifically:

[0061] The navigation star is a star, and the embodiment adopts 2 stars, Sirius and C...

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Abstract

The invention discloses a formation-flying-oriented relative navigation speed measurement and combined navigation method. Relative navigation speed measurement comprises the following steps of acquiring relative speeds of each space vehicle and each navigation star, calculating a difference value between the speed of each space vehicle and the speed of each navigation star, and constructing a relative speed measurement model based on starlight Doppler. The combined navigation method comprises the following steps of constructing a formation-flying-oriented orbit dynamics model, constructing an X-ray pulse star navigation ranging model, constructing an inter-star link ranging model, and constructing a relative navigation speed measurement model based on the starlight Doppler. An expanded kalman filter is used for filtration; during pulse star observation, a measurement model in the filter adopts the formation-flying-oriented orbit dynamics model and the relative navigation speed measurement model based on the starlight Doppler and is also integrated with the X-ray pulse star navigation ranging model once the pulse time of arrival is acquired.

Description

technical field [0001] The invention belongs to the field of autonomous navigation of spacecraft, in particular to an autonomous navigation method for formation flight based on astronomical speed measurement and ranging information. Background technique [0002] Formation flight is a new field in aerospace technology. Flying in formation can increase redundancy, reduce costs, and provide a multi-point platform. In the field of deep space exploration formation flight, both absolute and relative navigation accuracy are very important, especially relative navigation accuracy. [0003] At present, in the cruising segment of deep space exploration, the following methods can be used for autonomous navigation: (1) X-ray pulsar navigation. X-ray pulsar navigation provides ranging information. The difference between the ranging information obtained by the two spacecraft is the relative navigation information. However, the accuracy of the relative navigation information is low. (...

Claims

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Application Information

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IPC IPC(8): G01C21/24
CPCG01C21/24
Inventor 刘劲钟敏吴谨熊凌李娟邓慧萍杨莘
Owner WUHAN UNIV OF SCI & TECH
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