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Planet entering section navigation filtering method based on layered atmosphere model

A technology of atmospheric model and entry section, which is applied in the field of deep space exploration, can solve the problems of limited radio beacons, and achieve the effect of ensuring accuracy and real-time performance

Inactive Publication Date: 2013-12-18
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

However, due to the "black barrier" of communication and the limited availability of radio beacons, radio navigation has not yet been applied in engineering applications in the Martian atmosphere entry stage.

Method used

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  • Planet entering section navigation filtering method based on layered atmosphere model
  • Planet entering section navigation filtering method based on layered atmosphere model
  • Planet entering section navigation filtering method based on layered atmosphere model

Examples

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Embodiment Construction

[0037] 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.

[0038] This example is aimed at the navigation method based on the IMU measurement output in the Martian atmosphere entry section. The acceleration in the IMU output is regarded as an external measurement value, and the extended Kalman filter (EKF) method is used to filter and estimate the state of the lander to achieve high-precision real-time autonomous navigation. . The specific implementation method of this example is as follows:

[0039] Step 1: The equation of state of the Martian atmosphere entry section is established

[0040] The state model of Mars entering the stage is established in the fixed coordinate system of Mars. The state vector x of the navigation system includes the detector's position, velocity, azimuth, track angle, and latitude and longitu...

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Abstract

The invention relates to a planet entering section navigation filtering method based on a layered atmosphere model and belongs to the technical field of deep space detection. The method provided by the invention takes an output of an inertial measurement unit (IMU) as an external measuring value on the basis of a dead reckoning navigation method and simultaneously introduces a multilayered atmosphere model to establish a planet entering section measurement equation and construct a state estimating device; filtering estimation is carried out on positions, speeds and direction information of a landing device; resolving time of navigation data is short and real-time requirements of self navigation are met; compared with a single dead reckoning navigation method, the influences on the state of the landing device by initial deviation can be corrected and the navigation precision is improved.

Description

technical field [0001] The invention relates to a navigation filtering method for a planetary entry segment based on a layered atmospheric model, and belongs to the technical field of deep space exploration. Background technique [0002] Mars fixed-point landing detection is an important means to obtain more valuable scientific discoveries, and the acquisition of navigation information during the Martian atmosphere entry stage is one of the necessary conditions for accurate landing detection. During the entry into the Martian atmosphere, in order to prevent the probe from being damaged by aerodynamic heat, the entire lander was encapsulated in a heat shield, which caused the optical sensor to fail to work normally. delay, it is difficult to perform real-time control. Inertial navigation has become the main navigation method currently relied on for the Mars atmosphere entry phase. [0003] In the past, the exploration missions that successfully landed on Mars only used the ...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/24
Inventor 高艾邓剑峰崔平远徐瑞朱圣英
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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