|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||B64G-001/26 B64G-001/28 B64G-001/40|
|미국특허분류(USC)||244/164 ; 244/165 ; 244/171 ; 244/176|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 75 인용 특허 : 0|
A method and system (12) for controlling the attitude of a spacecraft during its transfer orbit using an on-board, stand-alone, three-axes attitude determination and control system. The system utilizes a set of on-board sensors to define two independent angular measurements, which will initially identify the z-axis orientation of the spacecraft from an arbitrary attitude after launch vehicle separation. A set of three-axis gyros are then bias calibrated in order to measure the transverse rates of the spacecraft. The three-axis attitude of the spacecraft ...
An on-board method of autonomously determining and controlling the attitude of a spacecraft after separation from a launch vehicle, comprising the steps of: determining the spin axis orientation of said spacecraft relative to a first planetary reference; determining the three-axis attitude of said spacecraft once a second planetary reference is in view; bias calibrating at least one of a set of three-axis gyros; repeatedly integrating the outputs from said gyros in a state estimator model of said spacecraft for continously updating an estimate of the thr...