Dual redundant cold plate

A cooling system for cooling avionics, the cooling system comprising:

• a cold plate having a first end, a second end, and a top face configured to engage one or more avionic components;
• a first cooling loop including a first pump and a first set of conduits extending through the cold plate;
• and
• a second cooling loop including a second pump and a second set of conduits extending through the cold plate;
• wherein fluid in the first cooling loop travels through the cold plate in a first direction and fluid in the second cooling loop travels through the cold plate in a second direction, opposite the first direction.

A method for cooling an avionic component, the method comprising:

• mounting the avionic component to a top face of a cold plate;
• circulating a first cooling fluid through a first loop, including
• activating a first pump to circulate the first cooling fluid, and
• circulating the first cooling fluid through a set of first conduits in the cold plate to transfer heat from the avionic component through the top face to the first cooling fluid;
• circulating a second cooling fluid through a second loop, including
• activating a second pump to circulate the second cooling fluid, and
• circulating the second cooling fluid through a set of second conduits in the cold plate to transfer heat from the avionic component through the top face to the second cooling fluid;
• wherein the second loop is fluidly isolated from the first loop.