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Deep space explorer acquisition phase celestial navigation method based on target object ephemeris correction

A technology for deep space probes and target celestial bodies is applied in the field of astronomical navigation in the capture segment of deep space probes based on target celestial ephemeris correction.

Active Publication Date: 2015-12-30
BEIHANG UNIV
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AI Technical Summary

Problems solved by technology

X-pulsar can obtain high-precision measurement information, but the measurement update cycle of the X-pulsar-based astronomical navigation system is long, making it difficult to achieve real-time navigation

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  • Deep space explorer acquisition phase celestial navigation method based on target object ephemeris correction
  • Deep space explorer acquisition phase celestial navigation method based on target object ephemeris correction

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Embodiment Construction

[0091] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

[0092] Such as figure 1 As shown, the target celestial bodies involved in the foregoing technical solutions can be celestial bodies in the solar system such as Mars, Venus, Jupiter, Saturn, etc., and Mars is used as an example below to illustrate the specific implementation process of the present invention:

[0093] 1. Establish a state model of deep space probes based on the gravitational orbital dynamics of the sun and eight planets

[0094] First initialize the position and velocity, set X=[xyzv x v y v z ] T is the state vector in the heliocentric inertial coordinate system, are the three-axis position and velocity of the detector in the heliocentric inertial coordinate system, X′=[x′y′z′v x 'v y 'v z '] T is the state vector in the center of fire inertial coordinate system, x′, y′, z′, v′ x , v′ y , v′ z are the three-axis po...

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Abstract

The invention relates to a deep space explorer acquisition phase celestial navigation method based on target object ephemeris correction. According to the method, firstly, a Martian explorer state model, a startlight angle navigation sub system measuring model and an X-ray pulsar navigation sub system measuring model are built; then, the startlight angle and the X-ray pulsar quantity measurements are respectively obtained; filtering estimation is performed to obtain the position and the speed of a detector in a heliocentric inertia coordinate system and a target object center inertia coordinate system; on the basis, a state model and a measuring model of target object ephemeris error are built; the quantity measurement about the target object ephemeris error is obtained through estimation state vectors of the startlight angle navigation sub system and the X-ray pulsar navigation sub system; a Kalman filtering method is used for estimating the target object ephemeris error; the target object ephemeris error is fed back into a navigation system model; the position of a target object in the navigation model is corrected. The deep space explorer acquisition phase celestial navigation method belongs to the technical field of aerospace navigation, can be used for estimating the object ephemeris error and correcting the model error of the navigation system on line, and is applicable to the explorer acquisition phase.

Description

technical field [0001] The present invention relates to when the deep space probe is in the capture phase, and in particular to a method for astronomical navigation of the deep space probe capture phase based on target celestial ephemeris correction, specifically, it corrects the target based on the target celestial body image and X pulsar signal The astronomical navigation method of celestial ephemeris error is a navigation method very suitable for the capture segment of deep space probes. 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. A new round of competition for deep space exploration has kicked off. At the beginning of the 21st century, all major aerospace powers focused their attention on the deep space universe 380,000 kilometers away from the earth. The ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/02G01C21/20
CPCG01C21/02G01C21/20
Inventor 宁晓琳李卓房建成刘刚
Owner BEIHANG UNIV
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