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X-ray pulsar/time difference astronomical Doppler combined navigation method of deep space probe

A time-difference and pulsar technology, applied to combined navigators and other directions, can solve problems that affect navigation accuracy, do not have complete observability, and cannot work alone for a long time

Active Publication Date: 2017-08-08
BEIHANG UNIV
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Problems solved by technology

However, this method is not fully observable and cannot work alone for a long time, and the dynamic changes of the stellar spectrum will affect its navigation accuracy

Method used

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  • X-ray pulsar/time difference astronomical Doppler combined navigation method of deep space probe
  • X-ray pulsar/time difference astronomical Doppler combined navigation method of deep space probe
  • X-ray pulsar/time difference astronomical Doppler combined navigation method of deep space probe

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Embodiment Construction

[0051] figure 1 The system flow chart of X-ray pulsar / time difference astro-Doppler integrated navigation method for deep space probe is given. Here, taking the approaching section of Mars exploration as an example, the specific implementation process of the present invention is described in detail:

[0052] 1. Establish a system state model based on orbital dynamics

[0053] The motion of the spacecraft during the approach to Mars is described as a heliocentric three-body model, and other perturbations are considered as process noise. The dynamic model in the sun center inertial coordinate system (J2000.0) can be written as:

[0054]

[0055] Where ||·|| represents the 2-norm of the vector, ||·|| 3 Represents the cube of ||·||, r and v are the position and velocity of the spacecraft relative to the sun. mu s and μ m are the gravitational constants of the sun and Mars, r m is the position vector of Mars relative to the sun, r sm =r-r m is the position vector of the...

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Abstract

The invention discloses an X-ray pulsar / time difference astronomical Doppler combined navigation method of a deep space probe. The method comprises the following steps: establishing a state model of a spacecraft according to orbital dynamics, adopting an X-ray pulsar probe to obtain a pulse arrival time measured value, adopting a spectrograph to obtain an astronomical Doppler velocity measured value, and then respectively establishing a pulse arrival time measured model and a time differential astronomical Doppler velocity measured model according to the measured values. The position and the velocity of the spacecraft are estimated through UKF filter after discretization. The method belongs to the field of autonomous navigation of the spacecraft, can provide high-accuracy position and speed information for the deep space probe, and has important practical significance for the autonomous navigation of the spacecraft.

Description

technical field [0001] The invention belongs to the field of autonomous navigation of spacecraft, and relates to an autonomous astronomical navigation method based on pulse arrival time measurement and time difference astronomical Doppler velocity measurement. Background technique [0002] As an important feature and symbol of a country's comprehensive national strength and scientific and technological development level, deep space exploration technology has attracted great attention from all countries in the world. With the continuous development of my country's deep space exploration technology, my country's deep space exploration capabilities continue to improve. Our country already has the ability to detect the moon, and plans to launch a Mars probe in 2020. [0003] For deep space exploration missions, navigation accuracy has an important impact on the success or failure of the mission. At present, the navigation information is mainly provided for the spacecraft throug...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/24
CPCG01C21/24
Inventor 宁晓琳桂明臻吴伟仁房建成刘刚孙晓函
Owner BEIHANG UNIV
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