Abstract: A duct includes a rigid air-permeable tube of composite material. The duct also includes a layer of insulation coupled to an exterior surface of the rigid air-permeable tube. The duct further includes a non-rigid insulation layer in contact with the layer of insulation. The non-rigid insulation layer forms an air-impermeable duct wall.

Abstract: A duct includes a rigid air-permeable tube of composite material. The duct also includes a layer of insulation coupled to an exterior surface of the rigid air-permeable tube. The duct further includes a non-rigid insulation layer in contact with the layer of insulation. The non-rigid insulation layer forms an air-impermeable duct wall.

Abstract: A duct includes a foam-filled honeycomb core structure having a tubular shape. The duct further includes an air-impermeable duct wall coupled to an exterior surface of the foam-filled honeycomb core structure.

Abstract: Described herein are noise attenuating ducts and vehicles using these ducts for environmental control systems. A duct comprises an exoskeleton structure and a sound-absorbing structure, disposed within and conforming to the exoskeleton structure. The exoskeleton structure provides external mechanical support to the sound-absorbing structure thereby helping to maintain the tubular shape of the sound-absorbing structure. This external support does not interfere with the airflow inside the sound-absorbing structure. Furthermore, the external positioning of the exoskeleton structure allows the integration of various support mounting features for the installation of the duct in a vehicle. In some examples, the exoskeleton structure comprises a plurality of enclosed openings to reduce the weight of the exoskeleton structure and provide additional flexibility.

Abstract: A cap for closing an open end of a duct tube has a cylindrical side wall having a length between a closed end and an open end of the side wall. An end wall extends across the closed end of the side wall. A conical section of the side wall extends outwardly from the open end of the side wall and has an interior surface configured to guide an end of a duct tube into a hollow interior volume of the side wall. A groove in an interior surface of the side wall is configured to receive a bead around an end of a duct tube inserted through the conical section and into the hollow interior of the side wall. A plurality of pull tabs extend outwardly from the conical section and are configured to be manually pulled, pulling the cap over the end of the duct tube.

Abstract: An aircraft includes an interior and an environmental system configured to circulate air through the interior. The aircraft also includes at least one disinfectant dispenser configured to dispense a disinfectant in the air circulated through the interior.

Abstract: Methods and apparatus to direct ventilation of vehicle occupants are disclosed. A disclosed example apparatus includes an air supply duct of a cabin of a vehicle, a manifold fluidly coupled to the air supply duct, the manifold to extend to occupant seats of the cabin, and nozzles fluidly coupled to the manifold, the nozzles to be positioned to face toward a front of a face of an occupant when the occupant occupies one of the occupant seats.

Abstract: A fluid flow restrictor device for controlling fluid flow at a connection between ducts may include a restrictor device body that is partially or fully inserted into and disposed within one of the ducts and an outboard restrictor device flange extending radially outward at an outboard end of the restrictor device body and having an outboard flange outer diameter that is greater than an inner diameter of the ducts so that the restrictor device body or the outboard restrictor device flange is engaged by an open end surface of the duct to prevent full insertion of the fluid flow restrictor device into the duct. A body inner surface defines a restrictor opening through the restrictor device body that can be varied to achieve desired fluid flow characteristics at the connection.

Abstract: A cap for closing an open end of a duct tube has a cylindrical side wall having a length between a closed end and an open end of the side wall. An end wall extends across the closed end of the side wall. A conical section of the side wall extends outwardly from the open end of the side wall and has an interior surface configured to guide an end of a duct tube into a hollow interior volume of the side wall. A groove in an interior surface of the side wall is configured to receive a bead around an end of a duct tube inserted through the conical section and into the hollow interior of the side wall. A plurality of pull tabs extend outwardly from the conical section and are configured to be manually pulled, pulling the cap over the end of the duct tube.

Abstract: A fluid flow restrictor device for controlling fluid flow at a connection between ducts may include a restrictor device body that is partially or fully inserted into and disposed within one of the ducts and an outboard restrictor device flange extending radially outward at an outboard end of the restrictor device body and having an outboard flange outer diameter that is greater than an inner diameter of the ducts so that the restrictor device body or the outboard restrictor device flange is engaged by an open end surface of the duct to prevent full insertion of the fluid flow restrictor device into the duct. A body inner surface defines a restrictor opening through the restrictor device body that can be varied to achieve desired fluid flow characteristics at the connection.

Abstract: According to an embodiment, an aircraft comprises a fuselage including composite skin; an enclosure located inside the fuselage; a rechargeable battery disposed inside the enclosure; and a ventilation conduit extending from the enclosure to an opening in the composite skin, the ventilation conduit including: a first portion having a first end coupled to the enclosure and a second end spaced from the composite skin, and a second portion extending between the composite skin and the second end of the first portion, the second portion comprising an electrically non-conductive material.

Abstract: A duct includes a rigid air-permeable tube of composite material. The duct also includes a layer of insulation coupled to an exterior surface of the rigid air-permeable tube. The duct further includes a non-rigid insulation layer in contact with the layer of insulation. The non-rigid insulation layer forms an air-impermeable duct wall.

Abstract: A duct includes a foam-filled honeycomb core structure having a tubular shape. The duct further includes an air-impermeable duct wall coupled to an exterior surface of the foam-filled honeycomb core structure.

Abstract: According to an embodiment, an aircraft comprises a fuselage including composite skin; an enclosure located inside the fuselage; a rechargeable battery disposed inside the enclosure; and a ventilation conduit extending from the enclosure to an opening in the composite skin, the ventilation conduit including: a first portion having a first end coupled to the enclosure and a second end spaced from the composite skin, and a second portion extending between the composite skin and the second end of the first portion, the second portion comprising an electrically non-conductive material.

Abstract: An aircraft comprises composite skin having an opening, and a ventilation conduit having an end portion that extends to the opening in the composite skin. The conduit is made of metal except for the end portion, which functions as an electrical insulator.

Abstract: A rechargeable battery is externally heated to induce thermal runaway, and material expelled from the battery is analyzed.

Abstract: An aircraft comprises a rechargeable battery including an array of battery cells, and means for mitigating consequences of failure of the rechargeable battery due to aircraft operating cycles.

Abstract: An apparatus comprises a rechargeable battery susceptible to thermal runaway, and a metal enclosure for the battery. The enclosure is configured to mitigate battery failure consequences resulting from thermal runaway.

Abstract: An aircraft comprises composite skin having an opening, and a ventilation conduit having an end portion that extends to the opening in the composite skin. The conduit is made of metal except for the end portion, which functions as an electrical insulator.

Abstract: Apparatus and methods for providing airflow within an aircraft are disclosed. In one embodiment, a method includes forming a clamshell component, including: providing first and second spaced-apart mold members; forming first and second half-body portions, including forming at least one sheet of formable material between the first and second mold members; and coupling the first and second half-body portions to form the clamshell component. The method also includes coupling the clamshell component to a source of air; and operating the source of air to provide an airflow through the clamshell component.