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Uncertainty Analysis Method of Planetary Atmosphere Entering Lander Landing Point

An analysis method and lander technology, which can be applied to instruments, special data processing applications, electrical digital data processing, etc., and can solve problems such as low computational efficiency

Inactive Publication Date: 2015-08-05
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

[0004] The present invention aims at the low calculation efficiency of existing planetary atmosphere entering lander landing point uncertainty analysis technology, and proposes a planetary atmosphere entering lander landing point uncertainty analysis method, which can accurately estimate the statistics of the system state characteristics, and the computational efficiency is significantly improved

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  • Uncertainty Analysis Method of Planetary Atmosphere Entering Lander Landing Point

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Embodiment Construction

[0014] In order to make the object, technical solution and advantages of the present invention clearer, the following are detailed descriptions of the embodiments of the present invention: this embodiment is implemented on the premise of the technical solution of the present invention, and detailed implementation methods and specific instructions are provided. Operation process, but the scope of protection of the present invention is not limited to the following examples.

[0015] This part takes the uncertainty analysis of the Mars landing point deviation as an example, and gives a specific implementation method.

[0016] The dynamics of the Mars landing system are:

[0017] h · = v sin γ v · ...

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Abstract

The invention belongs to the technical field of spacecraft landing and returning, and relates to a method for analyzing the uncertainty of a drop point of planetary atmosphere entering into a lander. The method comprises the steps of: carrying out Askey orthogonal polynomial approximation on the system state based on the uncertainty distribution of an initial state of the system; then taking the state into the system dynamics; transforming a stochastic differential equation for representing the original system into an equivalent high dimensional certainty differential equation based on a Galerkin projection rule; and finally acquiring an orthogonal polynomial coefficient of each state for representing the system state by a Runge-Kutta equivalent numerical integration method so as to obtain a statistical property of the system state. In the whole process, an orthogonal polynomial basement is self-adaptively adjusted according to the statistical property of the lander state to overcome influences caused by truncation errors. According to the method, the statistical property of the system state can be accurately estimated and the calculating efficiency is effectively improved.

Description

technical field [0001] The invention belongs to the technical field of spacecraft landing and return, and relates to a method for analyzing the uncertainty of a landing point of a planetary atmosphere entering a lander. Background technique [0002] To complete the landing mission on a planet with an atmosphere, it is necessary to select a predetermined landing point before the mission, but the navigation control error of the probe at the entry point of the Martian atmosphere, the aerodynamic parameters of the probe, and the uncertainty of the Martian atmospheric model will all affect the Seriously affect the final landing accuracy of the lander, and even the success or failure of the mission. Therefore, it is an essential work to analyze the impact of these deviations and uncertainties on the landing point; for planetary landing missions with atmospheres, the development of a fast landing point uncertainty analysis method will be of great help in reducing the future Mars L...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F19/00
Inventor 徐瑞崔平远朱圣英崔祜涛任高峰
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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