Mars entry flight state uncertainty quantification method

Abstract

The invention discloses a Mars entering flight state uncertainty quantification method. Random Mars entering dynamics is converted into an equivalent deterministic dynamics differential equation set through a polynomial chaos theory. The updating of the orthogonal basis in the polynomial chaos is realized by utilizing the spectral decomposition theory when the statistical characteristics of the Mars entering the flight state uncertainty change drastically, so that the uncertainty quantization accuracy is ensured under the condition that the polynomial order is not increased. And violent increase of the equation dimension under the condition of uncertainty of the initial state is inhibited by adopting a random space decomposition theory, so that the calculation efficiency is improved. The method is suitable for instantaneous state uncertainty quantification and state evolution uncertainty quantification of Mars entering flight.

Description

technical field [0001] The invention belongs to the technical field of flight mechanics, and in particular relates to a method for quantifying the uncertainty of Mars entering a flight state. Background technique [0002] The Mars entry phase begins when the vehicle reaches the boundary of the Martian atmosphere and ends when the parachute is successfully deployed. It is one of the most critical stages in the entire Mars exploration mission. The Mars entry flight technology is one of the key technologies for the Mars landing exploration mission. However, the uncertainties in Martian atmospheric density, vehicle aerodynamic parameters and initial state usually lead to large flight trajectory deviation and landing deviation. Therefore, it is an important prerequisite for the design and research of the Mars atmospheric entry flight system to carry out quantitative evaluation of the uncertainty of the Mars entry state trajectory in order to clarify the evolution law of the Mars...

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Problems solved by technology

[0004] Aiming at the deficiencies of the above-mentioned prior art, the purpose of the present invention is to provide a method for quantifying the uncertainty of the Mars entry flight state, so as to solve the problem that the Mars entry dynamics in the prior art have high-dimensional and strong nonlinear characteristics, and it is difficult to directly apply the traditional Uncertainty Quantification Method Realizes the Quick and Accurate Quantitative Evaluation of the Uncertainty of Mars Entering the Flight State

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