Double-walled pipe with integrated heating capability for an aircraft or spacecraft
AssigneeAirbus Operations GmbH
InventorsRobertino Kolarski, Magnus Koehler, Alexander Scheidt
Life of this patent
Estimating the term…
Abstract
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.
Claims14
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.
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.
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.
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.
Dependencies are inferred from the claim text.