A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a thermal energy storage reservoir positioned within the vapor chamber contains a phase change material for absorbing thermal energy.

A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a thermal energy storage reservoir positioned within the vapor chamber contains a phase change material for absorbing thermal energy.

A sensing assembly comprising includes one or more sensing elements formed as a tube. The sensing assembly also includes one or more clamps to secure the one or more sensing elements. Each of the one or more clamps includes a recess in which each of the one or more sensing elements is seated.

A fluid system comprising a surface that is fluid washed in use by a fluid flow travelling substantially parallel to the surface is disclosed. The system has a first port through the surface and a second port through the surface, the first and second ports having respective first and second port inlets that are substantially flush with the fluid washed surface. The first and second port inlets are stacked in a direction parallel to the normal flow of fluid over the fluid washed surface such that the first port is upstream of the second port and fluid travelling closer to the fluid-washed surface entering into the first port tends to entrain fluid travelling further from the fluid-washed surface for entry into the second port.

In an aircraft, a cooling target having a different amount of heat depending on a situation is sufficiently cooled. An aircraft (10) is provided with a cooling facility (40a) having a first cooling circuit (42a) and a second cooling circuit (42b) that are independent of each other. The first cooling circuit (42a) includes a first circulation flow path (44a) that allows a first cooling medium to sequentially and repeatedly pass through a cooling target (34a, 34b). Similarly, the second cooling circuit (42b) includes a second circulation flow path (44b) that allows a second cooling medium to sequentially and repeatedly pass through the cooling target. Here, the first circulation flow path (44a) and the second circulation flow path (44b) do not communicate with each other. Therefore, the first cooling medium and the second cooling medium do not merge or split.

An apparatus for modifying aircraft cabin airflow includes a redirector configured to receive an airflow from an inlet of an aircraft cabin. The redirector is configured to downwardly redirect at least a portion of the airflow. In one embodiment, the redirector includes a dividing portion configured to be oriented generally parallel to the airflow received at the redirector from the cabin inlet, and further includes a redirecting portion configured to be oriented in a generally downward direction. In another embodiment, the redirector includes an elongated protrusion configured to be positioned on a ceiling of the aircraft cabin.

An apparatus for modifying aircraft cabin airflow includes a redirector configured to receive an airflow from an inlet of an aircraft cabin. The redirector is configured to downwardly redirect at least a portion of the airflow. In one embodiment, the redirector includes a dividing portion configured to be oriented generally parallel to the airflow received at the redirector from the cabin inlet, and further includes a redirecting portion configured to be oriented in a generally downward direction. In another embodiment, the redirector includes an elongated protrusion configured to be positioned on a ceiling of the aircraft cabin.

A system has an electric motor having a stator and a rotor. The rotor rotates with a shaft and the shaft drives a fluid rotor. A control senses a fault condition on the electric motor. The control actuates a speed reduction feature when a fault is detected to bring rotation of the motor rotor and the fluid rotor to a stop more rapidly than if the speed reduction feature had not been actuated.

A position sensor for a bleed valve with a piston, a valve disc, and a piston linkage to couple the piston and the valve disc, the position sensor includes a coil, and a core assembly, including a core disposed within the coil, a link retainer coupled to the piston, and a connecting rod coupled to the core and the link retainer.

The invention relates to an emergency oxygen device for passenger of an aircraft, including a chemical oxygen generator including a chemical oxygen source and an activation unit for initiating a chemical reaction of the chemical oxygen source producing oxygen, at least two oxygen masks each connected with the chemical oxygen generator for receiving an oxygen fluid flow from the chemical oxygen generator after the activation unit has initiated the chemical reaction, and a mechanical activation assembly for activating the activation unit. The activation unit is activated by a mechanical force exerted onto an activation element of the activation unit and the mechanical activation assembly includes for each of the at least two oxygen masks a first mechanical connection from the activation element to a fixation element releasably mounted to the emergency oxygen device and a second mechanical connection from the fixation element to the oxygen mask.