This paper describes the guidance and navigation technique used by Hayabusa2 for the asteroid rendezvous operation to reach Ryugu.The operation results,including the achieved guidance and navigation performance,are al...This paper describes the guidance and navigation technique used by Hayabusa2 for the asteroid rendezvous operation to reach Ryugu.The operation results,including the achieved guidance and navigation performance,are also summarized.Multiple assessment and navigation teams worked closely to provide reliable navigation solutions with a short solution delivery cycle.Although the uncertainty of the Ryugu’s ephemeris was considerable before Hayabusa2’s arrival,a combination of radiometric-optical hybrid navigation and a stochastic-constrained optimum guidance method was able to achieve an accuracy of less than 100 m and 1 cm/s,and the arrival was precisely timed.展开更多
This paper describes attitude dynamics properties of spinning,momentum-biased and zero-momentum solar sail spacecraft.The model called“Generalized Sail Dynamics Model”(GSDM)is introduced,which can deal with general ...This paper describes attitude dynamics properties of spinning,momentum-biased and zero-momentum solar sail spacecraft.The model called“Generalized Sail Dynamics Model”(GSDM)is introduced,which can deal with general and practical sail configurations,such as arbitrary optical property distribution,shape and surface wrinkles.Attitude stability criteria and other key dynamical characteristics are derived and compared by compact analytical equations induced from the GSDM.The newly derived zero-momentum sail dynamics is compared with that of spinning and momentum-biased sails.It is shown that the spinning and momentum sails have an advantage in terms of dynamical stability whereas zero-momentum sails are only statically stable.With this special property,angular momentum-stabilized sails can realize a sun-pointing stable attitude with almost zero-fuel,which are discussed with actual space flight experience of the JAXA’s two interplanetary missions,IKAROS and Hayabusa2.展开更多
基金JSPS KAKENHI Grant No.18H01628 also supported this work.
文摘This paper describes the guidance and navigation technique used by Hayabusa2 for the asteroid rendezvous operation to reach Ryugu.The operation results,including the achieved guidance and navigation performance,are also summarized.Multiple assessment and navigation teams worked closely to provide reliable navigation solutions with a short solution delivery cycle.Although the uncertainty of the Ryugu’s ephemeris was considerable before Hayabusa2’s arrival,a combination of radiometric-optical hybrid navigation and a stochastic-constrained optimum guidance method was able to achieve an accuracy of less than 100 m and 1 cm/s,and the arrival was precisely timed.
基金This work was partially supported by JSPS KAKENHI(Grant Nos JP26289325,JP18H01628).
文摘This paper describes attitude dynamics properties of spinning,momentum-biased and zero-momentum solar sail spacecraft.The model called“Generalized Sail Dynamics Model”(GSDM)is introduced,which can deal with general and practical sail configurations,such as arbitrary optical property distribution,shape and surface wrinkles.Attitude stability criteria and other key dynamical characteristics are derived and compared by compact analytical equations induced from the GSDM.The newly derived zero-momentum sail dynamics is compared with that of spinning and momentum-biased sails.It is shown that the spinning and momentum sails have an advantage in terms of dynamical stability whereas zero-momentum sails are only statically stable.With this special property,angular momentum-stabilized sails can realize a sun-pointing stable attitude with almost zero-fuel,which are discussed with actual space flight experience of the JAXA’s two interplanetary missions,IKAROS and Hayabusa2.
