Moon-earth transfer orbit correction method based on engineering constraint

The invention discloses a moon-earth transfer orbit correction method based on engineering constraints, and the method comprises a step of determining a correction speed increment according to the orbit state of a moon-earth transfer orbit at a certain moment and a reentry point target requirement; according to the method, a full-target strategy, a bias strategy and a reduced-order strategy are combined, the full-target strategy is adopted for first midway correction, the pre-bias strategy is adopted for second midway correction and the reduced-order strategy is adopted for third midway correction of a moon-earth transfer orbit, and full-target aiming of the reentry point state is achieved through single-time control. And the influence of the separation process, the control residual error and the like on the reentry point is reduced, and stable convergence of the reentry state is realized under the condition that errors exist in actual flight. The technical problem that in the prior art, a transfer track corr