Abstract: A method for automatic generation of integrated test procedures using system test procedures includes generating a system test case for each system model of a plurality of system models. The method also includes automatically generating an integrated test harness including a group of interacting system models of the plurality of system models. An output signal from one or more of the interacting system models is an input signal to one or more other interacting system models. The method additionally includes automatically generating an integrated test case for each system model in the integrated test harness and automatically running the integrated test case using an integrated test procedure. The method further includes generating an integrated test procedure coverage report in response to running the integrated test case.

Abstract: Methods of determining a recommended cruise altitude for a flight plan of an aircraft, flight management systems that perform the methods, and/or aircraft that include the flight management systems are disclosed herein. The methods are computer-implemented methods and include receiving flight plan information regarding the flight plan with a flight management system of the aircraft and electronically determining the recommended cruise altitude for the aircraft utilizing the flight management system and based, at least in part, on the flight plan information and a cruise altitude regulation database that regulates cruise altitude within the flight plan of the aircraft. The flight management system includes a logic unit programmed to perform the methods and a display unit configured to display the recommended cruise altitude for the aircraft to a crew member of the aircraft. The aircraft include a fuselage, a wing, an engine, and the flight management system.

Abstract: A method for automatic generation of integrated test procedures using system test procedures includes generating a system test case for each system model of a plurality of system models. The method also includes automatically generating an integrated test harness including a group of interacting system models of the plurality of system models. An output signal from one or more of the interacting system models is an input signal to one or more other interacting system models. The method additionally includes automatically generating an integrated test case for each system model in the integrated test harness and automatically running the integrated test case using an integrated test procedure. The method further includes generating an integrated test procedure coverage report in response to running the integrated test case.

Abstract: A method for air separation module management includes determining an amount of nitrogen-enriched-air to be supplied to each fuel tank of a plurality of fuel tanks of an aircraft. The method also includes evaluating a status and usage of each air separation module of a plurality of air separation modules onboard the aircraft. The method additionally includes determining an optimal distribution of workload among the plurality of air separation modules based on the amount of the nitrogen-enriched-air to be supplied to each fuel tank and the status and usage of each air separation module. The method further includes regulating a valve associated with each air separation module or a group of air separation modules based on the optimal distribution of workload to each air separation module.

Abstract: A method for automatic generation of integration tests from unit tests includes automatically running, by a processor, a unit test for each model of a plurality of models making-up a system. The method also includes automatically determining, by the processor, integration of unit test cases of interfacing models for one or more groups of interfacing models of the plurality of models. The method additionally includes automatically running, by the processor, an integration test for each group of interfacing models using the unit tests for each model of the interfacing models. The method further includes automatically detecting, by the processor, at least one of inconsistent, incomplete or incorrect data transmitted between the interfacing models for each group of interfacing models.

Abstract: A method for automatic generation of integration tests from unit tests includes automatically running, by a processor, a unit test for each model of a plurality of models making-up a system. The method also includes automatically determining, by the processor, integration of unit test cases of interfacing models for one or more groups of interfacing models of the plurality of models. The method additionally includes automatically running, by the processor, an integration test for each group of interfacing models using the unit tests for each model of the interfacing models. The method further includes automatically detecting, by the processor, at least one of inconsistent, incomplete or incorrect data transmitted between the interfacing models for each group of interfacing models.

Abstract: Aircrafts and methods for reusing oxygen enriched air. In one embodiment, an aircraft includes an oxygen supply subsystem configured to supply oxygen to a cabin of the aircraft, and an air separator configured to receive a pressurized air stream, to separate the pressurized air stream into oxygen enriched air and an inert gas, and to feed the oxygen enriched air to the oxygen supply subsystem.

Abstract: A method and electronic device for providing an optimal quantity of aircraft fuel. The method comprises collecting recorded flight data from past flights of an aircraft; determining aircraft specific performance correction parameters per flight phase, using the recorded flight data; collecting a flight plan of the aircraft; determining the total fuel required for the given flight plan, using the aircraft specific performance correction parameters; determining a single synthetic drag factor (?DFMS) and a single synthetic fuel factor (?FFFMS) that, when used by the aircraft FMS, yield the said total fuel required for the given flight plan; receiving an estimated total fuel required determined by the aircraft FMS based on the flight plan, the single synthetic drag factor (?DFMS) and the single synthetic fuel factor (?FFFMS). The method allows reducing the fuel weight and total flight cost, and is particularly advantageous for FMS which only admit one single drag factor and one single fuel factor.

Abstract: A method and electronic device for providing an optimal quantity of aircraft fuel. The method comprises collecting recorded flight data from past flights of an aircraft; determining aircraft specific performance correction parameters per flight phase, using the recorded flight data; collecting a flight plan of the aircraft; determining the total fuel required for the given flight plan, using the aircraft specific performance correction parameters; determining a single synthetic drag factor (?DFMS) and a single synthetic fuel factor (?FFFMS) that, when used by the aircraft FMS, yield the said total fuel required for the given flight plan; receiving an estimated total fuel required determined by the aircraft FMS based on the flight plan, the single synthetic drag factor (?DFMS) and the single synthetic fuel factor (?FFFMS). The method allows reducing the fuel weight and total flight cost, and is particularly advantageous for FMS which only admit one single drag factor and one single fuel factor.

Abstract: A cabin pressure assessment system for an aircraft includes a plurality of polling devices within an internal cabin of the aircraft. The plurality of polling devices are associated with passenger seats onboard the aircraft. A cabin pressure assessment control unit is communicatively coupled to the plurality of polling devices. The cabin pressure assessment control unit is configured to receive cabin pressure comfort data from the plurality of polling devices.