Autonomous astronomical navigation method of Mars probe in cruise section

A Mars probe and celestial navigation technology, applied in astronomical navigation and other directions, can solve problems such as low precision, high requirements for probe orbit design, and a small number of navigation asteroids or navigation pulsars

Active Publication Date: 2011-09-07
BEIHANG UNIV
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Problems solved by technology

[0005] The technical problem to be solved by the present invention is: to overcome the shortcomings of the small number of navigation asteroids or navigation pulsars in the autonomous navigation method based on asteroids and pulsars, low precision, and high requirements for detector or

Method used

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  • Autonomous astronomical navigation method of Mars probe in cruise section
  • Autonomous astronomical navigation method of Mars probe in cruise section
  • Autonomous astronomical navigation method of Mars probe in cruise section

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Embodiment Construction

[0057] like figure 1 Shown, the concrete implementation method of the present invention is as follows:

[0058] 1. Establish the state equation of the Mars rover navigation system based on the orbital dynamics of the cruising segment;

[0059] First initialize the position and speed, set the state quantity X=[x y z v x v y v z ] T ,x,y,z,v x , v y , v z are the three-axis position and velocity of the detector in the heliocentric inertial coordinate system, respectively. According to the orbit design of the detector, the initial values ​​of the position and velocity of the detector are selected as

[0060] X(0)=[-2.024×10 11 m-5.336×10 10 m-2.276×10 10 m-1.384×10 3 m / s-2.194×10 4 m / s-9.520×10 3 m / s] T

[0061] Considering the effects of the gravitational force at the center of the sun, the center of Mars and the center of the earth on the probe, and selecting the heliocentric ecliptic inertial coordinate system, the state model of the Mars probe can be obtained...

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Abstract

The invention relates to an autonomous astronomical navigation method of a Mars probe in a cruise section. The method comprises the following steps: building a state model of the Mars probe according to a round limited four-body track kinetic model; obtaining pixel wire information of the sun, the earth, the Mars and the fixed stars by a solar sensor, an earth sensor, a Mars sensor and a star sensor, converting the obtained pixel wire information into angle information of the sun, the earth and the Mars, and building angle information measurement models of the sun, the earth and the Mars; andestimating gesture information of the probe by a q-method method, and estimating the position and speed of the Mars probe by combining with Unscented recurrence minimum variance estimation. The method in the invention is high in estimation precision, and suitable for autonomous navigation of the Mars probe at the cruise section. The method belongs to the technical field of aerospace navigation, not only can provide a high-precision navigation parameter for the Mars probe, but also can provide reference for an autonomous navigation system design.

Description

technical field [0001] The invention relates to an autonomous astronomical navigation method based on the angle information of the sun, the earth and Mars when the Mars probe is in the cruising section, and is an autonomous navigation method very suitable for the Mars probe's cruising section. Background technique [0002] Mars is the closest planet to the earth, and the exploration of Mars will help humans further understand the formation and evolution of the earth, Mars and the solar system. With the continuous development of my country's deep space exploration technology, my country's deep space exploration capabilities continue to improve, and my country already has the deep space exploration capabilities to detect celestial bodies beyond the moon. For the Mars exploration mission, the traditional navigation method based on ground radio measurement and control has the following disadvantages: because the probe is far away from the earth, the communication delay is large;...

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Application Information

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IPC IPC(8): G01C21/02
Inventor 吴伟仁宁晓琳马辛房建成白鑫贝
Owner BEIHANG UNIV
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