Patent ID: 9238513
Filing Date: 2016-01-19
CPC Classification: B64G,F28D,F28F

Claim Text:
1. A radiator panel for a spacecraft, the radiator panel comprising: two spaced-apart face-sheets including an inside face-sheet and an outside face-sheet; a heat pipe positioned between the two spaced-apart face-sheets and operatively engaged and in thermal communication with the two spaced-apart sheets, wherein the heat pipe includes a side extension with a substantially planar extension surface that is perpendicular to the two spaced-apart face sheets; and an insert positioned adjacent to the heat pipe, wherein the insert includes a substantially planar insert surface that is perpendicular to the two spaced-apart face sheets and that is operatively engaged with the substantially planar extension surface of the heat pipe, wherein the insert is configured with at least one feature useful in the operative securing of a package to the inside face-sheet opposite the heat pipe and the insert so that heat from the package may operatively conduct from the package through the inside face-sheet to the heat pipe, wherein the insert extends from the inside face-sheet to the outside face-sheet, wherein the insert engages the inside face-sheet and the outside face-sheet, wherein the insert includes a positioning structure extending adjacent to the substantially planar insert surface, wherein the positioning structure includes a lip that wraps around a first edge of the side extension of the heat pipe, and wherein the insert includes a retaining structure extending adjacent to the substantially planar insert surface opposite the positioning structure relative to the planar extension surface and that includes a clip that engages a second edge of the side extension of the heat pipe.