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Asteroid attachment trajectory robust optimization method

An optimization method, asteroid technology, applied in the direction of non-electric variable control, instrument, height or depth control, etc., can solve the problems of reduced landing accuracy and uncertain parameters

Inactive Publication Date: 2016-09-07
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

[0005] The purpose of the present invention is to solve the problem of parameter uncertainty in the asteroid attachment process, which leads to the reduction of landing accuracy, and propose a robust optimization method for asteroid attachment trajectory to reduce the influence of parameter uncertainty on the landing trajectory

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Embodiment Construction

[0057] In order to better illustrate the purpose and advantages of the present invention, the content of the present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0058] The specific process of a robust optimization method for asteroid attachment trajectory is as follows: figure 1 shown, including the following steps:

[0059] Step 1. Landing Dynamics Modeling

[0060] In the fixed coordinate system of small celestial bodies, the landing dynamic equation of the probe is expressed as:

[0061] x ·· = ω 2 x + 2 ω y · + ...

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Abstract

The present invention relates to an asteroid attachment trajectory robust optimization method, belonging to the technical field of planetary landing. The method comprises a step of using a linear covariance method to deduce the error spreading equation of an asteroid attachment process according to the mathematical model of uncertain factors of an initial state, thrust direction and size, a target celestial parameter and the like, a step of achieving the purposes of suppressing error spreading and improving landing trajectory robustness are achieved through introducing a tracking guide strategy in the trajectory optimization process. According to the method, the fuel consumption in a lander attaching process can be saved, at the same time, the influence of parameter uncertainties on trajectory can be reduced. According to the asteroid attachment robust optimization method, the linear covariance method is used to quantitatively describe the influence of random variables on a landing process, a tracking guide strategy is considered in the trajectory optimization process, thus the spread of various errors can be inhibited in the tracking process, and the purpose of improving the landing precision is achieved.

Description

technical field [0001] The invention relates to an anti-difference optimization method for an asteroid attachment trajectory, which belongs to the technical field of planetary landing. Background technique [0002] Planetary landing detection and sample return are one of the main forms of deep space exploration activities. All major aerospace countries are also fully aware of the importance of planetary landing detection and sample return missions for exploring the origin and evolution of life and improving their own aerospace technology capabilities, and are actively carrying out related tasks. Among them, safe and precise landing on the surface of the planet is the basis for successful planetary landing detection and sampling return missions, and planetary landing trajectory planning is the basis for achieving safe and precise landing. [0003] In the existing mission, the Philae lander of the Rosetta mission attaches to the surface of the comet at a speed of about 1m / s d...

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Application Information

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IPC IPC(8): G05D1/06G05D1/08
CPCG05D1/0676G16Z99/00
Inventor 朱圣英崔平远胡海静高艾徐瑞于正湜
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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