Wind correction method for multiple working modes in deceleration landing phase of spacecraft

Abstract

The invention relates to a wind correction method for multiple working modes in the deceleration landing phase of a spacecraft. Through the method, landing point deviation caused by drifting of a re-entry capsule descending by taking a parachute due to a wind field can be acquired, a deviation value is injected into a manned spacecraft in a parameter form, and landing accuracy of the spacecraft is unaffected by the wind field. According to the method, an algorithm solving process is divided by taking the working modes as bases, the process is composed of multiple feature calculation modules, all the modules use a resistance feature parameter and working phase matching method, and solving control of working modules is detailed. By execution of the solving process integrated with the multiple feature calculation modules, accurate wind drift deviation of the deceleration landing phase is acquired, and the problem of deviation in landing accuracy due to wind field changes, the working modes and the like after the spacecraft opens the parachute is solved. The method can be applied to wind correction control on the landing accuracy in the working phase of a spacecraft deceleration landing system.

Description

Technical field [0001] The patent belongs to the field of spacecraft system design, and relates to a wind correction method for multiple working modes of a spacecraft deceleration landing section, and is suitable for accurate calculation of wind correction of a spacecraft deceleration landing system. Background technique [0002] For manned spacecraft, the requirements for the landing point of the return capsule are higher than that of other unmanned spacecraft. The precision control of the landing point involves a series of issues such as the choice of landing zone, the search and rescue of astronauts, and the ground support after landing. [0003] The use of a parachute flexible structure as a deceleration device is greatly affected by the local wind field during its working phase. This requires wind corrections to be applied to the working section of the parachute system when the manned spacecraft returns to the cabin. Moreover, due to the diverse working modes of the manned spa...

AI Technical Summary

Problems solved by technology

[0005] The technical problem solved by the present invention is: to overcome the deficiencies in the prior art, to provide a wind correction method for multi-working modes in the deceleration and landing section of the spacecraft, to solve the wind correction technology for the multi-working modes in the deceleration and landing section of the spacecraft, that is, to improve the multi-working mode. The multi-working stages of the working mode lead to the accuracy requirements of wind correction and improve the control of the accuracy of the landing point

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