Identification Of The Whole Star Quality Characteristics Based On Cell Stars And Determination Of Position And Posture Of Cell Star Installation

During the operation of a satellite,its load antenna often has a large manufacturing cost,and the system life is very long,and the control system on the satellite is often prone to failure.If the load can not be reused,it will cause great losses.In recent years,the concept of cell satellites has been proposed.Single cell satellites only assume the sub-system functions of satellites,achieve low cost,modularization and integrability,and cell satellites can be assembled in orbit,and fault modules can also be replaced.For spacecraft whose load has not failed but whose control system has failed,cell satellites can be used to take over the attitude control of the serviced spacecraft to realize the reuse of the load.There are still some unresolved problems in the attitude takeover control of serviced spacecraft based on cell satellites.For example,after the combination of serviced spacecraft and cell satellites,the quality characteristics of spacecraft have changed,and online identification of the quality characteristics of combined spacecraft is required.Cell satellites can not be determined relative to the installation location and installation matrix of the serviced spacecraft.It is necessary to determine the installation location and installation matrix of the cell satellites relative to the serviced spacecraft online.Based on the problem of inter-satellite communication of mass cell satellites,it is necessary to design the topology of cell satellite interaction to reduce the interplanetary communication pressure.In order to solve the above problems,this paper mainly focuses on the following parts of the research.For the case where the serviced spacecraft is a non-cooperative target(such as space debris),we can't obtain its relevant parameters such as shape structure,quality characteristics,or the definition of the body coordinate system of the serviced spacecraft.Quality characteristics can't be identified within the body coordinate system of the serviced spacecraft.For this type of spacecraft,considering that we do not need to repair and repair the spacecraft,we only hope to change its original posture and orbit,or to reduce the orbit of non-cooperative targets so that they can be destroyed in the atmosphere to clean up space debris.purpose.Therefore,a cell satellite reference coordinate system is established,and the measurement and output parameters of the cell satellite are unified,and then the quality characteristics of the spacecraft are identified within the reference coordinate system.For the failure of the serviced spacecraft as a cooperative target for the control system,the spacecraft load,antenna,solar sail,etc.can still work.We hope to be able to use the cell satellite attached to the serviced spacecraft for attitude takeover control,achieve on-orbit maintenance of the serviced spacecraft,extend the working life of the serviced spacecraft,and achieve the reuse of resources.In this case,it is hoped that the cell satellite will be determined relative to the installation position of the serviced spacecraft,and then the quality characteristics of the spacecraft will be identified and controlled within the reference coordinate system of the serviced spacecraft.This article reasonably assumes that the definition of the body coordinate system of the serviced spacecraft,the overall shape structure and quality characteristics of the spacecraft are known.Using the principle of point cloud registration,the installation position of the cell satellite under the reference coordinate system is registered with the structural shape of the serviced spacecraft,and the position and attitude of the serviced spacecraft relative to the reference coordinate system are determined.Then determine the installation matrix and installation location of the cell satellite relative to the serviced spacecraft.Considering the large number of cell satellites,the limited data interface of cell satellites,and the limited computing power of single cell satellites,the method of selecting the central node to receive data and perform identification and registration calculations is no longer applicable.Therefore,a hierarchical topology is designed,an interactive quality characteristic identification method for cell satellites is designed,and a spacecraft position matching method is designed.Reduce the pressure of information transmission and the computational pressure of cell satellites.