The installation accuracy solution design and realization of manned spacecraft

The installation accuracy of the position and attitude measurement sensors directly affects the in-orbit measurement and control accuracy of the manned spacecraft. It is crucial to the in-orbit attitude determination, rendezvous and docking control of the manned spacecraft. Considering the in-orbit calibration difficulties and the complicated design constraints of the position and attitude determination sensors, this paper investigates various elements configurations that need to be considered in the manned spacecraft measurement system design, such as pressure variation, gravity, cargo loading, equipment layout, launch vibration, etc., and proposes a manned spacecraft high accuracy measurement design method based on the fusion of multiple key elements. The objective function of the design method is based on the amount of the accuracy change and the adjustment that has been established. This method solves the problem of multiple constraints and high accuracy measurement quantitative evaluation. All the accuracy error of the sensors meets the requirements of in-orbit measurement and control by using this method. Now, it has been successfully applied to the TianZhou cargo spacecraft and could be used to the other manned spacecraft.