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Method for rapidly evaluating navigation performance of planetary approach segment

A technology approaching segments and planets, which is applied in the field of deep space exploration to achieve the effects of improving evaluation efficiency, reducing the amount of calculation, and reducing the amount of calculation

Inactive Publication Date: 2019-02-15
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

The invention can provide technical support and reference for the design of the navigation scheme of the approaching section of the planetary exploration mission, and solve related engineering problems

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  • Method for rapidly evaluating navigation performance of planetary approach segment
  • Method for rapidly evaluating navigation performance of planetary approach segment
  • Method for rapidly evaluating navigation performance of planetary approach segment

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Embodiment Construction

[0033] In order to better illustrate the purpose and advantages of the present invention, the content of the invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0034] Such as figure 1 As shown, this example is aimed at the Mars approach section, combined with the state equation of the probe under the B plane and the optical measurement equation, the linear covariance analysis method is used to quickly evaluate the navigation performance. The specific implementation method of this example is as follows:

[0035] Step 1: Establish the state equation of the detector in the B-plane coordinate system.

[0036] The B-plane coordinate system is a commonly used reference coordinate system in the process of planetary approach in deep space exploration. Its origin is located at the center of the target celestial body, and consists of three coordinate axes: S, T, and R. The orbit of the probe approaching the planet is a hyperboli...

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Abstract

The invention discloses a method for rapidly evaluating navigation performance of a planetary approach segment, and belongs to the technical field of deep space exploration. The implementation methodprovided by the invention comprises the following steps: establishing a simplified state equation of a detector in a B-plane coordinate system and an observation equation for observing a state of a relative detector in the B-plane coordinate system; rapidly calculating an error covariance of a navigation system by linear error covariance analysis; and evaluating accuracy of the navigation system with the error covariance, so as to rapidly evaluate the navigation performance of the planetary approach segment. The method provided by the invention can rapidly evaluate the navigation performance of the planetary approach segment, can intuitively evaluate a navigation error, has an advantage of high evaluation efficiency, can provide technical support and reference for design of a navigation scheme of a planetary exploration task approach segment, and solves related engineering problems.

Description

technical field [0001] The invention relates to a method for quickly evaluating the navigation performance of a planet approaching segment, and belongs to the technical field of deep space exploration. Background technique [0002] The planetary approach phase is a critical period of planetary exploration flight, and the navigation performance of the probe at this stage has a decisive impact on the success or failure of the mission. There are two main methods to evaluate the navigation performance of the approach segment. The first method evaluates the navigation system performance through the navigation system observability analysis. For a specific navigation system, this method has an explicit expression and is efficient in calculation, but it cannot directly reflect the navigation accuracy. . The second method is the Monte Carlo simulation method, which needs to establish a high-precision complex dynamic model and measurement model, and consider various uncertainties in ...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C25/00
CPCG01C25/00
Inventor 崔平远王硕秦同朱圣英徐瑞
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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