|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||701/013 ; 701/221 ; 701/226 ; 244/164 ; 244/165 ; 342/352 ; 342/354|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 26 인용 특허 : 6|
Real time correction to ground generated satellite ephemeris implements a reference trajectory management module (334), an error estimation module (336), an parameter calculation module (338) and a position information management module (340). The reference trajectory management module (334) accesses reference trajectory data such as ground generated ephemeris data which is uplinked to a spacecraft through a communications unit (312). The position information management module (340) accesses and interprets position information such as Global Positioning ...
[ We claim:] [1.] In a system including a processor and a memory a method for real time on-board determination of corrected spacecraft orbital parameters, said method comprising:obtaining a reference trajectory for the spacecraft based upon reference trajectory data provided from a source external to the spacecraft:obtaining a measured position of the spacecraft corresponding to a first time:calculating a position of the spacecraft along the reference trajectory which corresponds to the first time:comparing the measured position and the calculated positi...