Cooling assembly for cooling a thermal body for an aircraft

1. A cooling assembly for cooling an aircraft apparatus generating heat, the cooling assembly comprising:

a feed pipe;

a thermal body having a fluid channel, wherein a fluid with a first temperature is provided by the feed pipe from the aircraft apparatus to the fluid channel; the fluid channel being adapted to dissipate thermal energy from the fluid to the thermal body,

a Peltier element having a hot side and a cold side;

wherein the thermal body is arranged in heat-conductive contact with the cold side of the Peltier element; and

a cooling device having at least one first cooling element and at least one second cooling element;

wherein the second cooling element is arranged in heat-conductive contact with the hot side of the Peltier element and is arranged without direct heat-conductive contact with an aircraft structure, the second cooling element absorbs thermal energy from the hot side of the Peltier element and dissipates thermal energy to an air flow, when the cooling assembly is mounted to cool the aircraft apparatus;

wherein the first cooling element is arranged in heat-conductive contact with the aircraft structure and is arranged without direct heat-conductive contact with the Peltier element, the first cooling element absorbs thermal energy from the air flow and dissipates thermal energy to the aircraft structure, when the cooling assembly is mounted to cool the aircraft apparatus; and

wherein the first cooling element and the second cooling element are structurally spaced apart from one another.

2. The cooling assembly according to claim 1 ,

wherein the cooling device has air deflector plates for controlling the air flow.

3. The cooling assembly according to claim 1 ,

further comprising a condensate precipitator;

wherein the condensate precipitator is connected to the drain pipe;

wherein the fluid is cathode exhaust air of a fuel-cell system;

wherein the cathode exhaust air is fed to the condensate precipitator via the drain pipe; and

wherein the condensate precipitator is adapted to precipitate a condensed water component of the cathode exhaust air.

4. The cooling assembly according to claim 3 ,

further comprising a condensate storage tank; and

wherein the condensed water component is fed to the condensate storage tank.

5. The cooling assembly according to claim 1 ,

wherein the drain pipe is adapted to provide the fluid with the second temperature to the aircraft apparatus.

6. The cooling assembly according to claim 5 ,

wherein the aircraft apparatus is a fuel-cell system.

7. The cooling assembly according to claim 1 ,

wherein the cooling device and the thermal body are implemented integrally.

8. The cooling assembly according to claim 1 ,

wherein the cooling device has a plurality of Peltier elements.

9. The cooling assembly according to claim 1 ,

further comprising wherein the cooling assembly includes more than one first cooling element, second cooling element, or cooling device.

10. The cooling assembly according to claim 1 ,

wherein the aircraft structure is selected from the group consisting of cylindrical aircraft fuselages, stringers, frames, and a combination thereof.

11. The cooling assembly of claim 1 , wherein the first cooling element and the second cooling element comprise a first and a second distinct structural elements, respectively.

12. An aircraft having a cooling assembly, the cooling assembly comprising:

a feed pipe;

a thermal body having a fluid channel, wherein a fluid with a first temperature is provided by the feed pipe from the aircraft apparatus to the fluid channel; the fluid channel being adapted to dissipate thermal energy from the fluid to the thermal body,

a Peltier element having a hot side and a cold side;

wherein the thermal body is arranged in heat-conductive contact with the cold side of the Peltier element; and

a cooling device having at least one first cooling element and at least one second cooling element;

wherein the second cooling element is arranged in heat-conductive contact with the hot side of the Peltier element and is arranged without direct heat-conductive contact with an aircraft structure, the second cooling element absorbs thermal energy from the hot side of the Peltier element and dissipates thermal energy to an air flow, when the cooling assembly is mounted to cool the aircraft apparatus;

wherein the first cooling element is arranged in heat-conductive contact with the aircraft structure and is arranged without direct heat-conductive contact with the Peltier element, the first cooling element being absorbs thermal energy from the air flow and dissipates thermal energy to the aircraft structure, when the cooling assembly is mounted to cool the aircraft apparatus, and

wherein the first cooling element and the second cooling element are structurally spaced apart from one another.

13. A method of cooling an aircraft apparatus generating heat, comprising:

a) providing a Peltier element having a hot side and a cold side;

b) arranging a thermal body in heat-conductive contact with the cold side of the Peltier element so as to absorb heat generated by the aircraft apparatus;

c) providing a cooling device having at least one first cooling element and at least one second cooling element,

wherein the second cooling element is arranged in heat-conductive contact with the hot side of the Peltier element absorbing thermal energy from the hot side of the Peltier element and dissipating thermal energy to an air flow, the second cooling element being arranged without direct heat-conductive contact with an aircraft structure; and

wherein the first cooling element is arranged in heat-conductive contact with an aircraft structure and is arranged without direct heat-conductive contact with the Peltier element, the first cooling element absorbing thermal energy from the air flow and dissipating thermal energy to the aircraft structure, and

wherein the first cooling element and the second cooling element are structurally spaced apart from one another.