A flow path duct system for a propulsion system of an aircraft includes a base defining a flow surface. The base has an internal surface and an external surface. A plurality of perforations are formed through the base between the internal surface and the external surface. A plurality of supports define a plurality of cavities. The plurality of supports extend outwardly from the external surface of the of the base. One or more of the plurality of cavities are in fluid communication with the one or more of the plurality of perforations. A backing surface is secured to the plurality of supports. The plurality of supports are disposed between the base and the backing surface. The one or more of the plurality of cavities are in fluid communication with an internal volume defined by the internal surface of the base through the one or more of the plurality of perforations. The base, the plurality of supports, and the backing surface can be integrally formed together as a monolithic, load-bearing structure.

A system comprises a non-transitory machine readable storage medium storing instructions and a database identifying a plurality of assets and a state of each asset. The instructions configure a processor for receiving updates to a distributed electronic ledger managed by plural peer processors. Each update includes an event or change affecting one of the assets. The peer processors verify portions of the ledger describing each event or change. At least one of the updates has not yet been recorded in the ledger at a time of the receiving. The processor computes a state of each asset, based on the updates, receives a request for a state of one of the assets; and responds to the request, reflecting each event and change affecting that asset. The response is performed without waiting for the peer processors to verify an update that has not yet been recorded in the ledger.

The invention relates to an aircraft power architecture comprising a power transmission gearbox (12), located in a first compartment (30), a gas turbine (14), located in a second compartment (32) comprising a gas generator (18) and a free turbine (22) connected to the power transmission gearbox (12) by a power shaft (26) of the gas turbine (14), and an accessory gearbox (16), the gas turbine (14) being set into the main transmission gearbox (12), characterized in that the gas turbine (14) comprises a first electric machine (38), and in that the accessory gearbox (16) is placed in the first compartment (30) and comprises a second electric machine (42) configured to supply energy to the accessory equipment and to receive electrical energy transmitted via the first electric machine (38).

An airplane has main propulsion engines and a first fuel supply for the main propulsion engines. The airplane further has an auxiliary propulsion engine and a second fuel supply for the auxiliary propulsion engine, this second fuel supply being separate from the first fuel supply. The auxiliary propulsion engine can be switched on independently from the main propulsion engines. Such airplane has increased safety, since it will be possible to maintain flight, particularly when at high altitude, even if all main propulsion engines have failed.

An airplane has main propulsion engines and a first fuel supply for the main propulsion engines. The airplane further has an auxiliary propulsion engine and a second fuel supply for the auxiliary propulsion engine, this second fuel supply being separate from the first fuel supply. The auxiliary propulsion engine can be switched on independently from the main propulsion engines. Such airplane has increased safety, since it will be possible to maintain flight, particularly when at high altitude, even if all main propulsion engines have failed.

Ground support equipment for powering an aircraft on the ground, the ground support equipment including: a solid state converter configured to power an aircraft on the ground from an airport power source having a pre-determined maximum power, and a battery charging unit configured to charge an external battery from the airport power source. The solid state converter is configured to measure an instantaneous power drawn by the aircraft. The solid state converter is configured to generate, for controlling the battery charging unit, a control signal indicative of a maximum power available for the battery charging unit based on the difference between the pre-determined maximum power of the airport power source and the instantaneous power drawn by the aircraft.

The aircraft engine can have an air-oil separator having an air-oil mixture inlet, an oil outlet, an air outlet, and a pressure relief path provided fluidly in parallel with the air-oil separator, between the air-oil mixture inlet and the air outlet, the pressure relief path can have a pressure relief valve for evacuating air-oil mixture to the exhaust duct in the event of excess pressure in the auxiliary gearbox.

The aircraft engine can have an air-oil separator having an air-oil mixture inlet, an oil outlet, an air outlet, and a pressure relief path provided fluidly in parallel with the air-oil separator, between the air-oil mixture inlet and the air outlet, the pressure relief path can have a pressure relief valve for evacuating air-oil mixture to the exhaust duct in the event of excess pressure in the auxiliary gearbox.

The present invention relates to an apparatus and a method for configuring a control message in a broadcasting system for supporting a multimedia service based on an internet protocol. To this end, control information to be recorded in a payload of a control message to be configured is generated based on a table selected from among a plurality of tables for defining the information related to the generation and consumption of a hybrid content when a message type of the control message to be configured is determined to be a type for providing information related to the generation and consumption of a hybrid content. In addition, the information related to the type of the selected table is recorded in an optional field of the control message to be configured.

The present invention relates to an apparatus and a method for configuring a control message in a broadcasting system for supporting a multimedia service based on an internet protocol. To this end, control information to be recorded in a payload of a control message to be configured is generated based on a table selected from among a plurality of tables for defining the information related to the generation and consumption of a hybrid content when a message type of the control message to be configured is determined to be a type for providing information related to the generation and consumption of a hybrid content. In addition, the information related to the type of the selected table is recorded in an optional field of the control message to be configured.