Abstract: A method for dynamically computing an equi-distance point (EDP) for an aircraft includes receiving at least two reference points for landing the aircraft upon an occurrence of an emergency, determining a remaining flight path for the aircraft based on a current location of the aircraft and a flight plan serviced by a flight management system (FMS) of the aircraft, and generating the EDP for the aircraft by locating a point on the remaining flight path which is equidistant from the at least two reference points.

Abstract: A system and method for assessing thermal comfort in an enclosure is disclosed. In one embodiment, a method includes performing a numerical analysis on a calibration enclosure including a thermal manikin in a uniform thermal environment to obtain a surface heat transfer coefficient (hcal) for each body part of the thermal manikin. The method also includes performing a numerical analysis on an enclosure including one or more thermal manikins in a non-uniform thermal environment to obtain a total heat flux (q?T) for each body part of the one or more thermal manikins. The method further includes computing an equivalent temperature (teq) of each body part of the one or more thermal manikins using the obtained associated hcal, the obtained associated q?T, and an associated surface temperature of the body part. Furthermore, the method includes evaluating thermal comfort in the enclosure based on each computed teq.

Abstract: A method of automatic delivery of appropriate flow rate of oxygen to a person flying in a pressurized aircraft cabin is disclosed. In one embodiment, a first aneroid valve that is responsive to differential gas pressure in a first altitude range is preset to close at a oxygen starting altitude point based on apriori lung capacity test. Further, flow of oxygen is initiated from an oxygen bottle using quarter turn switching regulator connected to the oxygen bottle via a minimum flow area of main valve to output a mixture of the flow of oxygen and aircraft cabin air into a mixing chamber. Furthermore, the first aneroid valve is gradually closed in response to increasing aircraft cabin pressure altitude to stop the pilot flow of oxygen during the first altitude range. Then, main valve is opened upon closing the first aneroid valve to flow pressurized oxygen into the mixing chamber.

Abstract: A system and method of automatic delivery of appropriate flow rate of oxygen to a person flying in a pressurized aircraft cabin is disclosed. In one embodiment, an adaptable demand dilution oxygen regulator for use inside a pressurized aircraft cabin, includes an oxygen initiation and demand regulation system adapted to be responsive to differential gas pressure in a first altitude range based on a pulmonary capacity of a person flying in the pressurized aircraft cabin and to control flow of pressurized oxygen to a breathing outlet during the first altitude range. The adaptable demand dilution oxygen regulator further includes a cabin air dilution and delivery system, coupled to the oxygen initiation and demand regulation system, adapted to be responsive to differential gas pressure in a second altitude range and to output progressively enriched mixture till 100% pressurized oxygen into a breathing apparatus during the second altitude range.

Abstract: A system and method for aircraft taxi gate selection based on passenger connecting flight information are disclosed. In one embodiment, a communication link is established between an aircraft computing system and a ground station system via a communication network provided by the ground station system. Further, aircraft taxi gate selection information and the passenger connecting flight information are substantially simultaneously displayed on a display device to a pilot upon establishing the communication link. Furthermore, the pilot is allowed to select an aircraft taxi gate based on the displayed aircraft taxi gate selection information and passenger connecting flight information.