US 12,263,948 B2
Primary structural assembly for an aircraft outside-skin heat exchanger, aircraft having a primary structural assembly, and method for attaching an aircraft outside-skin heat exchanger
Markus Piesker, Hamburg (DE)
Assigned to AIRBUS OPERATIONS GMBH, Hamburg (DE)
Appl. No. 17/611,381
Filed by Airbus Operations GmbH, Hamburg (DE)
PCT Filed Aug. 5, 2020, PCT No. PCT/EP2020/071953
§ 371(c)(1), (2) Date Nov. 15, 2021,
PCT Pub. No. WO2021/032476, PCT Pub. Date Feb. 25, 2021.
Claims priority of application No. 102019122426.8 (DE), filed on Aug. 21, 2019.
Prior Publication US 2022/0204167 A1, Jun. 30, 2022
Int. Cl. B64D 13/00 (2006.01); B64C 1/00 (2006.01)
CPC B64D 13/006 (2013.01) [B64C 1/00 (2013.01)] 16 Claims
OG exemplary drawing
 
1. A primary structural assembly for an outside-skin heat exchanger for an aircraft, comprising:
an outside skin portion which defines an outer shape of the aircraft and forms a portion of a shell of the aircraft, wherein the outside skin portion has at least one recess;
a heat transfer fluid connection which is adapted to guide a heat transfer fluid into the recess;
a structural element closing the recess; and
at least one holding means arranged in or at the recess, which holding means is configured to hold the structural element closing the recess, in the recess,
at least one heat transfer fluid channel arranged in the structural element closing the recess,
wherein the at least one heat transfer fluid channel is fluidically coupled with the heat transfer fluid connection, so that the heat transfer fluid flows through the heat transfer fluid connection and then through the at least one heat transfer fluid channel,
wherein the structural element comprises a cover which is flush with an outside skin of the aircraft outside the recess,
wherein the at least one heat transfer fluid channel comprises a first heat transfer fluid channel and a second heat transfer fluid channel, the first heat transfer fluid channel separated from the second heat transfer fluid channel by the cover,
wherein the at least one heat transfer fluid channel is fixedly attached directly to a primary structural element of the aircraft, the primary structural element being at least one of a former, a stringer and a gusset plate,
wherein the at least one heat transfer fluid channel forms an outer wall of the aircraft and at least one cooling channel passes between the at least one heat transfer fluid channel and the outside skin portion of the aircraft.