Patent ID: 8157217

Claim:
A radiator system, relating to a generally-cylindrical spacecraft having a longitudinal axis, comprising: a) at least one thermal energy radiator structured and arranged to radiate thermal energy generated by components of at least one spacecraft; b) wherein said at least one thermal energy radiator receives thermal energy through at least one thermal energy transport system when said at least one thermal energy radiator is installed on such at least one spacecraft; and c) at least one spacecraft structural support structured and arranged to structurally support such at least one spacecraft; d) wherein said at least one thermal energy radiator comprises at least one portion of said at least one spacecraft structural support; and e) wherein at least one geometry of said at least one thermal energy radiator substantially augments structural strength of said at least one spacecraft structural support; f) wherein said at least one geometry of said at least one thermal energy radiator comprises at least one surface comprising at least one cylindrical surface portion having a first central longitudinal axis; and g) wherein said first central longitudinal axis is coplanar with a second central longitudinal axis of at least one generally-cylindrical portion of such at least one spacecraft.