|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/168 ; 244/158R ; 343/909|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 15 인용 특허 : 7|
A spacecraft having a pair of asymmetrical side-mounted antennas that are designed to control the net angular momentum of the spacecraft over a twenty-four hour period. One of the side-mounted antennas is a dual surface antenna having a front surface that has a reflective sunshield overlay thereon and a rear surface. The rear surface of this side mounted antenna has a reflective blanket attached directly to the rear surface of the antenna that has low-.alpha. properties to control the solar or radiation force acting on the spacecraft.
[ What is claimed is:] [1.] A system for minimizing the net angular momentum of a spacecraft comprising:a spacecraft body;a first antenna mounted to a side of said spacecraft body;a second antenna mounted to an opposing side of said spacecraft body;said first and second antennas being configured such that a larger force acts on said second antenna than on said first antenna during a twenty-four hour period; anda reflective antenna blanket positioned on a back surface of said second antenna, to balance said larger force, said reflective antenna blanket ha...