Prediction correcting guidance method of deep space exploration returning process

Abstract

A prediction correcting guidance method of a deep space exploration returning process comprises the steps that (1) a heeling angle section used for deep space exploration returning process track prediction is determined; (2) the amplitude value | sigma 0 | of the heeling angle of a current point is computed in an iterative mode; (3) a salutatory reentry flight track of a returning device is divided into an initial reentry stage, a primary reentry descending stage, a primary reentry ascending stage, a Kepler stage and a final reentry stage, a final guidance rule of the returning device is determined, and the final guidance rule is that when the returning device is in the initial reentry stage or the primary reentry descending stage or the primary reentry ascending stage or the final reentry stage, the amplitude value | sigma 0 | determined in the step (2) of the heeling angle sigma 0 of the current point is used for guidance; and when the returning device is in the Kepler stage, | sigma 0 | = 180 degrees is used for guidance, and accordingly prediction correcting guidance of the deep space exploration returning process is completed. The guidance rule is designed at the Kepler stage of the track for achieving overload restrain on the deep space exploration returning process, and safe and accurate landing of the returning device is guaranteed.

Description

technical field [0001] The invention relates to a predictive correction guidance method for the return process of deep space exploration, belonging to the guidance field of spacecraft deep space exploration return process. Background technique [0002] The deep space exploration return vehicle re-enters the boundary of the earth's atmosphere, the speed is about 11km / s at a height of about 120km from the ground, and the initial kinetic energy is about twice that of the low-earth orbit spacecraft when it re-enters, which brings a series of new re-entry guidance. Difficulties and challenges, such as the voyage deviation is more sensitive to the initial state deviation, the heat flux peak value increases during the reentry process, the overload peak value increases, etc., these will seriously affect the accuracy, safety and reliability of the landing of the returner. [0003] The return device generally adopts a small lift body configuration, and the angle of attack is generated...

AI Technical Summary

Problems solved by technology

However, when the returner with limited lift re-enters at the second cosmic velocity, reducing the initial re-entry angle may cause the returner to fly out of the atmosphere because the first reentry is not deep enough, which shows that a new overload suppression algorithm is urgently needed

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