|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||364/459 ; 244/164 ; 244/170|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 11 인용 특허 : 17|
A method for controlling transition from thruster control to momentum wheel control to minimize nutation angle and transition time in a three-axis stabilized spacecraft employing an internal body fixed-momentum wheel as an attitude stabilizer. The method employs direct, substantially real-time measurement of momentum components and angular rates and generates paired roll thrust impluses and paired yaw thrust impulses in synchronization with the nutation period of the spacecraft to drive the spacecraft to a state of substantially zero nutation. The contro...
In a three-axis stabilized spacecraft employing an internal body-fixed momentum wheel as an attitude stabilization means and characterized by a nutation period, an apparatus for controlling transition from thruster control to momentum wheel control to minimize nutation angle and transition time, said apparatus comprising: sensor means for obtaining values representative of spacecraft roll angle, spacecraft yaw angle, spacecraft roll rate and spacecraft yaw rate; and means coupled to said sensor means for controlling firing of spacecraft roll and yaw atti...