An airplane is provided. The airplane includes a pressurized medium, a turbine, and a valve. The turbine includes at least one nozzle. The valve is located upstream of the turbine. The valve provides the pressurized medium to the at least one nozzle of the turbine according to an operational mode.

An airplane is provided. The airplane includes a pressurized medium, a turbine, and a valve. The turbine includes at least one nozzle. The valve is located upstream of the turbine. The valve provides the pressurized medium to the at least one nozzle of the turbine according to an operational mode.

In an aspect, a test platform for testing an embedded control system having a plurality of interconnected components is operable to: receive, at run time, configuration data for configuring a system under test (“SUT”) representing the embedded control system, the configuration data specifying: which of the components shall be simulated versus hardware-in-the-loop (HIL) components in the SUT; and an inter-component signal mapping that maps input signals to output signals of the specified simulated or HIL components of the SUT; for each of the simulated or HIL components, automatically activate, at run time, a corresponding object code portion for simulating the embedded system component in the test platform or a corresponding object code portion for facilitating communication with the HIL component connected to the test platform, respectively; and automatically map input signals of the activated object code portions to output signals of the activated code portions according to the signal mapping.

In an aspect, a test platform for testing an embedded control system having a plurality of interconnected components is operable to: receive, at run time, configuration data for configuring a system under test (“SUT”) representing the embedded control system, the configuration data specifying: which of the components shall be simulated versus hardware-in-the-loop (HIL) components in the SUT; and an inter-component signal mapping that maps input signals to output signals of the specified simulated or HIL components of the SUT; for each of the simulated or HIL components, automatically activate, at run time, a corresponding object code portion for simulating the embedded system component in the test platform or a corresponding object code portion for facilitating communication with the HIL component connected to the test platform, respectively; and automatically map input signals of the activated object code portions to output signals of the activated code portions according to the signal mapping.

Heat exchanger assembly comprising a ram air flow channel (14) extending in a longitudinal direction, and characterized in that said assembly comprises: at least two separate heat exchangers (12a, 12b) that are adjacent in a transverse direction perpendicular to the longitudinal direction, are arranged in the ram air flow channel (14), and are configured such that the ram air passing through said channel (14) forms a cold pass of each heat exchanger (12a, 12b) by passing through said heat exchanger (12a, 12b) in said longitudinal direction, each heat exchanger (12a, 12b) also being configured for the passage therethrough of a fluid that is intended to be cooled and that forms a hot pass (20a, 20b); and an air passage which is provided between the heat exchangers and forms a thermally insulating air gap (18) between said exchangers (12a, 12b), and through which the ram air flows, said air passage extending in said longitudinal direction of said ram air flow channel (14).

Heat exchanger assembly comprising a ram air flow channel (14) extending in a longitudinal direction, and characterized in that said assembly comprises: at least two separate heat exchangers (12a, 12b) that are adjacent in a transverse direction perpendicular to the longitudinal direction, are arranged in the ram air flow channel (14), and are configured such that the ram air passing through said channel (14) forms a cold pass of each heat exchanger (12a, 12b) by passing through said heat exchanger (12a, 12b) in said longitudinal direction, each heat exchanger (12a, 12b) also being configured for the passage therethrough of a fluid that is intended to be cooled and that forms a hot pass (20a, 20b); and an air passage which is provided between the heat exchangers and forms a thermally insulating air gap (18) between said exchangers (12a, 12b), and through which the ram air flows, said air passage extending in said longitudinal direction of said ram air flow channel (14).

A mixer assembly for mixing two air streams in a ventilation system. The mixer assembly comprises a mixing chamber, which comprises an inlet and an outlet and a mixing chamber wall delimiting the mixing chamber, and also a shroud, which surrounds the mixing chamber wall, at least in certain portions. The shroud forms and delimits an intermediate space between the mixing chamber wall and the shroud. The mixer assembly also comprises a filter element, which fluidically connects the intermediate space to a surrounding area of the mixer assembly, the intermediate space being fluidically connected to the mixing chamber. Fluid can thus flow through the filter element into the intermediate space and further into the mixing chamber. A stowage space with a mixer assembly, an aircraft with such a stowage space and a method for producing a mixer assembly in an aircraft are also described.

Lightning-dissipative A/C assemblies are provided, as are valve frames utilized within lightning-dissipative A/C assemblies. In embodiments, the lightning-dissipative A/C assembly includes a base dielectric component having a mount interface, a strike-susceptible metallic component coupled to the base dielectric component, and mounting hardware configured to engage the mount interface to attach the base dielectric component to an A/C. An electrically-conductive coating overlies or is formed over at least a portion of the base dielectric component to complete a lightning strike dissipation path. The lightning strike dissipation path extends from the strike-susceptible metallic component, through the electrically-conductive coating, through the mounting hardware, and to an A/C electrical ground plane when the lightning-dissipative A/C assembly is installed on the A/C. In one implementation, the base dielectric component assumes the form of a valve frame, while the strike-susceptible metallic component assumes the form of a valve door movably mounted to the valve frame.

Lightning-dissipative A/C assemblies are provided, as are valve frames utilized within lightning-dissipative A/C assemblies. In embodiments, the lightning-dissipative A/C assembly includes a base dielectric component having a mount interface, a strike-susceptible metallic component coupled to the base dielectric component, and mounting hardware configured to engage the mount interface to attach the base dielectric component to an A/C. An electrically-conductive coating overlies or is formed over at least a portion of the base dielectric component to complete a lightning strike dissipation path. The lightning strike dissipation path extends from the strike-susceptible metallic component, through the electrically-conductive coating, through the mounting hardware, and to an A/C electrical ground plane when the lightning-dissipative A/C assembly is installed on the A/C. In one implementation, the base dielectric component assumes the form of a valve frame, while the strike-susceptible metallic component assumes the form of a valve door movably mounted to the valve frame.

A bleed air supply system has a sensor monitoring the system, an operating condition monitor detecting an operating condition value of the aircraft (other than the bleed air supply system), and independent monitoring modules evaluating a part of the bleed air supply system. The monitoring modules each have an individual monitoring function and individual activation and deactivation parameters based on sensor data and the operating condition value. The method includes: detecting the condition of the bleed air supply system via sensor data and the operating condition value; activating a monitoring module, which has activation parameters met by the sensor data and the operating condition value; monitoring the condition of the bleed air supply system by the activated monitoring module by a monitoring function of the activated monitoring module; and deactivating the activated monitoring module, deactivation parameters of which are met by the sensor data and the operating condition value.