Covariant initial value determination method for optimal landing track design

Abstract

The invention discloses a covariant initial value determination method for the optimal landing track design and belongs to the field of deep space exploration. The covariant initial value determination method includes building a small body fixing coordinate system and corresponding detector landing kinetic equations; converting the optimal design problem of the small body landing track into the optimal control problem and the corresponding two-point boundary value problem, and defining the problems as the problem 1; approximating the problem 1, and defining the approximated problem 1 as the problem 2; solving the covariant initial values lambda<r2(t0)> and lambda<v2(t0)> of the problem 2, setting the the covariant initial values lambda<r2(t0)> and lambda<v2(t0)> of the problem 2 as iterative initial values of the covariant initial values lambda<r1(t0)> and lambda<v1(t0)> of the problem 1, determining the iterative initial value of the covariant initial value lambda<m1(t0)> of the problem 1 according to the setting of the iterative initial values, namely lambda<r2(t0)> and lambda<v2(t0)>, of the covariant initial values lambda<r1(t0)> and lambda<v1(t0)> of the problem 1, thereby achieving the iterative initial value setting of the covariant initial values for the optima landing track design. The defect that it is difficult to solve the two-point boundary value problem due to improper initial value setting can be avoided by application of the method.

Description

technical field [0001] The invention relates to a method for designing an optimal landing trajectory, in particular to a method for determining an initial value of a covariate for optimal landing trajectory design, and belongs to the field of deep space exploration. Background technique [0002] Small celestial body detection is an important means for people to understand and study the origin and evolution of the solar system, and it is an important content of deep space exploration activities in the 21st century. Small celestial body landing and sampling return are the main forms of small celestial body detection at present. Among them, descent and landing are the key stages of small celestial body landing and sampling return, and play a decisive role in whether it can reach the preset target area safely and accurately. The optimal landing trajectory design for small celestial bodies needs to make the detector reach the designated landing area safely and accurately, satisf...

AI Technical Summary

Problems solved by technology

[0004] In order to solve the problem that the initial value of the covariate is difficult to determine and the corresponding two-point boundary value problem is difficult to solve in the optimal landing trajectory design problem of small celestial bodies

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