|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||364/434023 ; 364/432 ; 244/164 ; 244/165|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 20 인용 특허 : 10|
A zero-momentum spacecraft\s attitude is controlled by determining the torque required about a control axis to maintain the desired attitude, and, during each of recurrent control cycles, enabling a magnetic torquer if the torque demand exceeds a threshold. During each of the control cycles, thruster(s) are enabled to make up the difference between the torque demand and the estimated torque produced by the magnetic torquer. In determining the torque demand, the attitude rate signal is low-pass filtered to reduce noise, and the control loop bandwidth is m...
An attitude control system for a zero-momentum spacecraft which includes a body, for maintaining said body in a particular attitude, said system comprising: magnetic torquing means mounted on said body, for, when enabled, torquing said body about a particular axis; thrusters mounted on said body, for, when enabled, producing torque about said particular axis; a source of attitude command signals representing said particular attitude; attitude sensing means, for sensing the attitude of said spacecraft body about said particular axis, and for generating at...