|국가/구분||United States(US) Patent 등록|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 5 인용 특허 : 2|
A method and apparatus for damping nutation in a spacecraft to essentially zero in less than one nutation period which has a spin axis, first and second transverse axes and a characteristic nutation frequency l1 after the transverse momentum of the spacecraft about one transverse axis, such as the Y axis has crossed zero, a torque of magnitude TY is applied to the spacecraft about its Y transverse axis. After a time interval t2, the application of this torque is terminated. The time t1=1/l-1 (hY0lY) and the time t2=2/l-1 (hY0lY), where hY0 is the peak bo...
A method for reducing nutation of a momentum stabilized spacecraft to essentially zero in less than a single nutation period where said spacecraft has a spin axis, a torquer providing a torque value about a first arbitrary axis transverse to said spin axis and a characteristic nutation frequency comprising the steps of: sensing the peak magnitude of nutation motion about said first axis; starting a timer when the sensed nutational motion on said first axis reaches zero; starting said torquer at said torquer value when said timer has timed out t1 after th...