Method for designing fixed-point landing orbit in lunar sampling return task

Abstract

The invention discloses a method for designing a fixed-point landing orbit in a lunar sampling return task, which comprises the steps of aiming at the longitude of a predetermined lunar surface drop point by introducing an orbit surface normal speed increment component in a near-moon braking maneuver in combination with the optimization of a near-moon inclination angle of an earth-moon transfer section of the lunar sampling return task, aiming at the latitude of the predetermined lunar surface drop point and the height of a power drop starting point through a lunar orbit drop and orbit transfer latitude argument and an orbit plane internal speed increment component, and enabling the lunar surface drop point to be located in a target orbit plane at a predetermined lunar surface rising moment; and furthermore, eliminating the longitudinal voyage error by introducing a lunar orbit descending speed increment normal component to correct the longitude of the drop point and adjusting the power descending moment. According to the method, the problem that the correction speed increment of the moon orbit rendezvous and docking orbit surface is large due to the fact that the influence of orbit design on subsequent moon orbit rendezvous and docking is not considered in the existing fixed-point landing technology is solved.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a method for designing a fixed-point landing track in a lunar sampling return mission. Background technique [0002] In the lunar sample return mission or the manned lunar landing mission, the probe may start to descend from the orbit around the moon, enter the lunar surface powered descent trajectory through orbit change maneuvering, and achieve a soft landing at the predetermined lunar surface landing point. The fixed-point landing orbit design on the lunar surface is a key orbit design technology that our country must break through to realize lunar sampling return and manned lunar landing. [0003] The full flight process of the lunar sampling return mission orbit includes carrier launch, earth-moon transfer, near-moon braking, orbiting the moon, lunar surface power descent, lunar surface work, lunar surface power rise, rendezvous and docking, moon-ground transfer, reentry ...

AI Technical Summary

Problems solved by technology

However, the adjustment of the inclination involves changes in the orbital surface, which will affect the position of the landing point on the lunar surface

On the other hand, the existing fixed-point landing technology does not consider the influence of inclination optimization, and cannot guarantee that the landing point of the lunar surface is within the orbital plane of the orbiter when the lunar surface rises, so it may lead to a large increase in the correction speed of the lunar orbital rendezvous and docking orbital surface

Moreover, the existing method does not consider two longitude aimings, and only uses one control of orbiting around the moon to aim at the predetermined longitude of the landing point, which cannot achieve a large longitude adjustment of the landing point.

Therefore, the existing technology cannot be simply applied to the fixed-point landing on the lunar surface in the sampling return mission. How to ensure that the ascender is located in the orbital plane of the orbiter when the lunar surface takes off is a big problem

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