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Solar TDOA measuring method faced to formation flying and combined navigation method

A formation flight and integrated navigation technology, applied in the field of formation flight autonomous navigation, can solve the problems that need to be improved and the navigation accuracy is limited, and achieve the effect of great application significance and market value

Inactive Publication Date: 2018-03-23
WUHAN UNIV OF SCI & TECH
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AI Technical Summary

Problems solved by technology

Xiong Kai combines pulsar navigation and inter-satellite links to improve relative navigation accuracy, but relative navigation accuracy is still limited and needs to be improved

Method used

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  • Solar TDOA measuring method faced to formation flying and combined navigation method
  • Solar TDOA measuring method faced to formation flying and combined navigation method
  • Solar TDOA measuring method faced to formation flying and combined navigation method

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Embodiment Construction

[0043] The technical solutions of the present invention will be clearly and completely described below in conjunction with the embodiments of the present invention and the accompanying drawings.

[0044] An embodiment of the present invention provides a solar TDOA measurement method for formation flight, comprising the following steps,

[0045] Step A1, establish the solar TDOA (difference of photon arrival time measured by the detectors flying in formation) measurement model as follows,

[0046] Z 1 (t)=h 1 [X(t),t]+V 1 (t) (Formula 1)

[0047] where Z 1 (t) is the measured value of the relative distance between the two detectors in the radial direction of the sun, V 1 (t) is the measurement noise, h 1 [X(t),t] is the measurement equation, X(t) is the state vector of the detector, t is time, h1 [X(t),t] is expressed as follows,

[0048]

[0049] Among them, c is the speed of light in vacuum, |r 1 |and|r 2 | are the distances between the two detectors in the solar ...

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Abstract

The invention discloses a solar TDOA measuring method faced to formation flying and a combined navigation method. The method includes steps of building a solar TDOA measuring model as below, executingand building a track dynamics model faced to the formation flying by a detector in the formation flying; building a Mars direction measuring model and building an inter-satellite link spacing model;using an expanded kalman filter EKF as a navigation filter; applying a star sensor to acquire celestial body azimuth information, inter-satellite link spacing value and relative distance on solar radial direction; combining with the detector track dynamics model faced to the formation flying to obtain the estimated detector position and speed information under the effect of EKF. The invention provides the solar TDOA measuring technical scheme faced to formation flying, and can provide relative position information on the radial direction; by fully using the much navigation measuring information, the absolute and relative navigation information with higher precision can be provided for the formation flying aircraft in the whole space.

Description

technical field [0001] The invention belongs to the field of autonomous navigation of spacecraft, and in particular relates to a technical solution for autonomous navigation of formation flight based on astronomical direction-finding 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] The autonomous navigation of deep space exploration often uses the measurement information of the sun for navigation, including angle measurement, velocity measurement and distance measurement. Solar angle measurement navigation uses the sun's azimuth vector as the measurement information. This method is the most traditional, but the distance between the probe and the s...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/02G01C21/24
CPCG01C21/02G01C21/24
Inventor 刘劲韩雪侠喻子原陈璇康志伟吴谨
Owner WUHAN UNIV OF SCI & TECH
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