Communication coverage constraint-oriented earth-moon balance point task orbit rapid determination method

Abstract

The invention discloses a communication coverage constraint-oriented earth-moon balance point task orbit rapid determination method, and belongs to the technical field of aerospace. The implementationmethod comprises the steps of establishing an earth-moon rotating coordinate system, determining an approximate analytical solution of a Halo orbit, obtaining an accurate solution by utilizing a differential correction method, and generating a plurality of Halo orbits for communication constraint amplitude calculation; conducting meshing on a back area of the moon, and calculating the geometricalrelationship between feature sample points and the Halo orbits; selecting characteristic geometric parameters according to communication constraint indexes, constructing a regression equation for thecommunication coverage constraint, and determining a quantitative relation between the communication constraint and the orbit amplitude as well as the landing point through the regression equation; and according to the task constraints, rapidly evaluating communication conditions by utilizing the regression equation, and realizing relay task orbit determination. The method can achieve the quick determination of task orbits with different communication constraints, guarantees the communication coverage of a landing point at the far side of the moon, and has the advantage of high orbit determination efficiency.

Description

technical field [0001] The invention relates to a method for quickly determining the mission orbit of the Earth-Moon balance point facing communication coverage constraints, in particular to a method for determining the mission orbit of a relay satellite under different communication constraints, and belongs to the field of aerospace technology. Background technique [0002] The moon is the natural satellite of the earth, which has important scientific research and engineering value. However, affected by the tidal force, the rotation period and revolution of the moon are synchronized, so the back of the moon is always invisible. In order to realize the detection of the back of the moon, it is necessary to be near the L2 point of the earth and the moon Deploy relay stars to realize relay communication. The choice of the relay satellite mission orbit is a problem that needs to be studied in depth. Mission trajectory selection is limited by various constraints, including fuel ...

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Problems solved by technology

[0004] Prior Technology [2] (Refer to: Liang Weiguang, Liu Lei, Liu Yong, et al. Research on the influence of the shadow of the relay star at the Earth-Moon L2 point [J]. Journal of Deep Space Exploration, 2019, 6(1):52-56.) The shadow coverage of the relay satellite orbit was studied, but the research did not involve the communication constraints between the orbit and the lunar surface, and it is not applicable to the mission orbit design considering the communication constraints

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