A sound-absorbing panel to be used affixed to a jet engine of an aircraft, provided with: a resin core layer having a first surface, a second surface disposed on the side opposite from the first surface, and multiple partitions extending between the first surface and second surface so as to partition multiple cells; a resin first skin layer laminated on the first surface of the core layer; and a resin second skin layer laminated on the second surface of the core layer. The first skin layer is disposed so as to face the external space while in use, and has multiple through-holes for providing communication between internal spaces of the multiple cells and external space faced by the first skin layer. The core layer has openings for providing communication between the internal spaces of the multiple cells and external space of the core layer.

An acoustic panel is provided that includes a perforated first skin, a second skin and a core. The core includes a first wall, a second wall and a stiffener. The core forms a plurality of cavities that extend vertically between the perforated first skin and the second skin and that extend laterally between the first wall and the second wall. The plurality of cavities include a first cavity. The stiffener projects partially into the first cavity and is connect to the first wall and the second wall.

A system for use in an aircraft or other system in an ambient airflow includes a body defining a cavity having an opening exposed to ambient airflow, with a cavity interface defined by body structure surrounding the opening. The cavity interface includes a cavity floor opposite the cavity opening, a leading edge facing away from the ambient airflow, a trailing edge facing the airflow, and a rear wall extending between the trailing edge and the cavity floor. A panel of sound-absorbing material is attached to and covers substantially all of the surface area of the rear wall of the cavity, and minimizes emanation of a predetermined range of audible sound frequencies from the cavity. The system may include an elongated serrated element connected to body and extending along the leading edge and arranged flush with the leading edge.

A system for use in an aircraft or other system in an ambient airflow includes a body defining a cavity having an opening exposed to ambient airflow, with a cavity interface defined by body structure surrounding the opening. The cavity interface includes a cavity floor opposite the cavity opening, a leading edge facing away from the ambient airflow, a trailing edge facing the airflow, and a rear wall extending between the trailing edge and the cavity floor. A panel of sound-absorbing material is attached to and covers substantially all of the surface area of the rear wall of the cavity, and minimizes emanation of a predetermined range of audible sound frequencies from the cavity. The system may include an elongated serrated element connected to body and extending along the leading edge and arranged flush with the leading edge.

An aircraft fairing includes a fairing body having an exterior fairing wall and at least one wheel bin. The at least one wheel bin has a side wall extending from an opening in the exterior fairing wall to an end wall. The side wall and the end wall define a cavity of the at least one wheel bin in fluid communication with the opening in the exterior fairing wall. An acoustic resonator is mounted to an outer surface of the side wall of the at least one wheel bin and is in fluid communication with the cavity. The acoustic resonator has a resonant frequency substantially similar to a cavity modal frequency of the at least one wheel bin at an aircraft flight condition.

An aircraft fairing includes a fairing body having an exterior fairing wall and at least one wheel bin. The at least one wheel bin has a side wall extending from an opening in the exterior fairing wall to an end wall. The side wall and the end wall define a cavity of the at least one wheel bin in fluid communication with the opening in the exterior fairing wall. An acoustic resonator is mounted to an outer surface of the side wall of the at least one wheel bin and is in fluid communication with the cavity. The acoustic resonator has a resonant frequency substantially similar to a cavity modal frequency of the at least one wheel bin at an aircraft flight condition.

An aircraft cabin section includes a door frame, which forms a door opening, a passenger door, which is arranged on the door frame and is configured to close the door opening, and a door insulation arrangement, which is larger in at least one direction than the door opening. The door insulation arrangement is produced from a textile which is heat-insulating and/or airflow-inhibiting. Furthermore, a corresponding door insulation arrangement and an aircraft having such an aircraft cabin section or such a door insulation arrangement are disclosed.

An aircraft cabin section includes a door frame, which forms a door opening, a passenger door, which is arranged on the door frame and is configured to close the door opening, and a door insulation arrangement, which is larger in at least one direction than the door opening. The door insulation arrangement is produced from a textile which is heat-insulating and/or airflow-inhibiting. Furthermore, a corresponding door insulation arrangement and an aircraft having such an aircraft cabin section or such a door insulation arrangement are disclosed.

An acoustic treatment panel includes at least one acoustically resistive layer, a reflective layer and at least one cellular structure interposed between the acoustically resistive layer and the reflective layer. The cellular structure includes cylindrical and identical main tubes which are closed at one end by the acoustically resistive layer and at the other end by the reflective layer, spacer zones between the main tubes, the spacer zones being sealed relative to one another, cutouts made at an end of certain main tubes, in contact with the reflective layer, and/or secondary tubes positioned in the main tubes and/or in the spacer zones, the cutouts and/or the secondary tubes being configured to generate acoustic cells of different dimensions from identical main tubes.

An aircraft line or harness fastening system with a clamp attaching the line or harness to the aircraft. A bobbin within the clamp surrounds the line or harness, wherein the bobbin is smaller than the clamp and is circular in shape to enable rotation of the bobbin within the clamp. The bobbin includes two separate complementary parts that fit together around the line or harness. Each of the two separate complementary parts include a tab and a recess, wherein the tab of one of the complementary parts fits into the recess on the other of the complementary parts.