Double-walled pipe with integrated heating capability for an aircraft or spacecraft
A double-walled pipe with integrated heating capability for an aircraft or spacecraft includes a pipe body rigidly formed from plastic in one piece with an inner wall, with an outer wall and with a plurality of wall supports, the wall supports connecting the inner wall to the outer wall, the inner wall and the outer wall defining an intermediate space. The double-walled pipe further includes an electrically conductive coating surrounding the inner wall within the intermediate space and configured to heat up under application of an electric current such that heat is transferred to the inner wall.
1. A double-walled pipe with integrated heating capability for an aircraft or spacecraft, comprising:
a pipe body rigidly formed in one piece from plastic with an inner wall, with an outer wall and with a plurality of wall supports, the wall supports connecting the inner wall to the outer wall, the inner wall and the outer wall defining an intermediate space; and
an electrically conductive coating surrounding the inner wall within the intermediate space and configured to heat up under application of an electric current such that heat is transferred to the inner wall, wherein the electrically conductive coating fills up the intermediate space from the inner wall to the outer wall.
2. The double-walled pipe of claim 1 wherein the pipe body and the electrically conductive coating are integrally formed.
3. The double-walled pipe of claim 1 wherein the electrically conductive coating has a positive temperature coefficient (PTC).
4. The double-walled pipe of claim 1 wherein the electrically conductive coating is an admixture of a synthetic resin and carbon particles.
5. The double-walled pipe of claim 1 wherein the intermediate space defines a circumferential gap in between the inner wall and the outer wall having a substantially constant diameter along the pipe body.
6. The double-walled pipe of claim 1 wherein the outer wall has an outer diameter in between 5 mm and 50 mm and the electrically conductive coating has a radial thickness of less than 300 μm.
7. The double-walled pipe of claim 1 , further comprising:
a conductor channel formed along the pipe body within the intermediate space; and
a conductor arranged within the conductor channel and being connected to the electrically conductive coating to lead an electric current into the electrically conductive coating to transfer heat into the inner wall.
8. The double-walled pipe of claim 1 , further comprising a thermal insulation layer surrounding the outer wall.
9. An aircraft or a spacecraft comprising a double-walled pipe with integrated heating capability, the double-walled pipe comprising:
a pipe body rigidly formed in one piece from plastic with an inner wall, with an outer wall and with a plurality of wall supports, the wall supports connecting the inner wall to the outer wall, the inner wall and the outer wall defining an intermediate space; and
an electrically conductive coating surrounding the inner wall within the intermediate space and configured to heat up under application of an electric current such that heat is transferred to the inner wall, wherein the electrically conductive coating fills up the intermediate space from the inner wall to the outer wall.
10. A method for forming a double-walled pipe with integrated heating capability for an aircraft or spacecraft, the method comprising:
manufacturing a rigid pipe body in one piece from plastic with an inner wall, an outer wall and a plurality of wall supports, the wall supports connecting the inner wall to the outer wall, the inner wall and the outer wall defining an intermediate space, and an electrically conductive coating surrounding the inner wall within the intermediate space, wherein the electrically conductive coating fills up the intermediate space from the inner wall to the outer wall and is configured to heat up under application of an electric current such that heat is transferred to the inner wall, using an additive manufacturing or 3D printing technique.
11. The method of claim 10 , wherein the 3D printing technique comprises stereolithography.
12. The method of claim 10 , wherein manufacturing the pipe body comprises forming a conductor channel along the pipe body in between the inner wall and the outer wall; and wherein the method further comprises inserting a conductor into the conductor channel and connecting the conductor to the electrically conductive coating.
13. The method of claim 10 , further comprising surrounding the outer wall with a thermal insulation layer.
14. A computer-readable medium comprising computer-executable instructions which, when executed on a data processing apparatus, cause the data processing apparatus to perform a method for forming a double-walled pipe with integrated heating capability for an aircraft or spacecraft, the method comprising:
manufacturing a rigid pipe body in one piece from plastic with an inner wall, an outer wall and a plurality of wall supports, the wall supports connecting the inner wall to the outer wall, the inner wall and the outer wall defining an intermediate space, and an electrically conductive coating surrounding the inner wall within the intermediate space, wherein the electrically conductive coating fills up the intermediate space from the inner wall to the outer wall and is configured to heat up under application of an electric current such that heat is transferred to the inner wall, using an additive manufacturing or 3D printing technique.