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Martian atmosphere entrance interruption allowing estimation method based on multiple models

A multi-model, Martian technology, applied in the field of deep space exploration, can solve problems such as nonlinear time-varying system filter estimation

Inactive Publication Date: 2015-07-22
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

Since the system state equation and measurement model both exhibit strong nonlinear time-varying characteristics, the traditional Kalman filter algorithm cannot filter and estimate the nonlinear time-varying system, so the nonlinear filtering method should be used to estimate the state information of the detector

Method used

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  • Martian atmosphere entrance interruption allowing estimation method based on multiple models
  • Martian atmosphere entrance interruption allowing estimation method based on multiple models
  • Martian atmosphere entrance interruption allowing estimation method based on multiple models

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Embodiment

[0042] This example is aimed at the navigation scheme based on inertial measurement and radio measurement information in the Martian atmosphere entry section, combined with acceleration measurement information, ranging and speed measurement information of the detector and radio beacon, and using the modified EKF filter to estimate the state of the detector, increasing Robustness and two-sided accuracy of system state estimation. The specific implementation method of this example is as follows:

[0043] Step 1: Establish the dynamic equation of the Martian atmosphere entry section.

[0044] In the inertial system of Mars, the state x of the probe includes the position vector r=[x,y,z] T , velocity vector v=[v x ,v y ,v z ] T . Equation of State of Mars Atmospheric Entry Segment Detector As follows:

[0045] r · = v ...

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Abstract

The invention discloses a Martian atmosphere entrance interruption allowing estimation method based on multiple models, relates to the Martian atmosphere entrance interruption allowing estimation method, and belongs to the technical field of deep space exploration. The method includes the implementation steps of (1) building a Martian atmosphere entrance section dynamics equation; (2) building the Martian atmosphere entrance section wireless measurement model and the wireless measurement interruption model so as to be used for modifying the detector position and speed information in the step (3); (3) resolving the detector state in cooperation with the wireless model and the interruption model in the step (2) and a filtering algorithm, and estimating the detector state. By means of the Martian atmosphere entrance interruption allowing estimation method, the problem of estimation divergence of the detector state under wireless measurement interruption can be effectively solved, and the reliability and the state estimation accuracy of an autonomous navigation system of a detector on the Martian atmosphere entrance section are improved. By means of the Martian atmosphere entrance interruption allowing estimation method, technical supports and references can be provided for adopting the wireless navigation scheme design on the atmosphere entrance section in Martian landing detection in future.

Description

technical field [0001] The invention relates to a method for estimating the interruption of Martian atmosphere entry capacity, belonging to the technical field of deep space exploration. Background technique [0002] The Mars fixed-point landing detection is an important means to obtain more scientifically valuable discoveries. In order to realize the future Mars fixed-point landing detection, the probe must be guided and controlled during the atmosphere entry process, so as to ensure that the probe accurately reaches the pre-opening point, and accurately The prerequisite for guidance and control is that the navigation system can provide accurate status information for the detector. Therefore, designing a navigation scheme and an estimation algorithm that can accurately determine the state information of the detector is a prerequisite for fixed-point landing detection. [0003] In previous successful landing missions, the Martian atmosphere entry section used dead-recursion...

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Application Information

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IPC IPC(8): G06F19/00G01C21/20G01C25/00
Inventor 崔平远邓剑峰高艾朱圣英徐瑞
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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