An integrated avionics bay in a floor area can be provided with adequate ventilation. The structure of an aircraft cockpit floor is able to integrate at least one bay, with a walking floor in the cockpit, a structural volume and a bay integrated in a space of the liberated structural volume. The bay as integrated in a horizontal position in this space includes a peripheral frame with at least one protective cover with a direct access to the bay at the floor level and a lower wall with a rear face access. Side openings formed in the frame can couple with vertical walls to allow fresh air blowing from the rear wall of the bay via a flow from rearwards to upwards to reach the top cover and an air extraction by an upper surface extractor.

An integrated avionics bay in a floor area can be provided with adequate ventilation. The structure of an aircraft cockpit floor is able to integrate at least one bay, with a walking floor in the cockpit, a structural volume and a bay integrated in a space of the liberated structural volume. The bay as integrated in a horizontal position in this space includes a peripheral frame with at least one protective cover with a direct access to the bay at the floor level and a lower wall with a rear face access. Side openings formed in the frame can couple with vertical walls to allow fresh air blowing from the rear wall of the bay via a flow from rearwards to upwards to reach the top cover and an air extraction by an upper surface extractor.

Disclosed are methods for determining and classifying aircraft air contaminants comprising one or more of: turbine engine oil, hydraulic fluid and deicing fluid using contaminant analyzers comprising a contaminant collector comprising a membrane and a heater vaporizing the contaminants; a gravimetric sensor generating a response when contaminant mass is added to or removed from the sensor, the sensor receiving contaminants desorbed from the heated membrane; a frequency measurement device, measuring the response generated by the sensor as the contaminant is added to and removed from the sensor; a computer readable medium bearing a contaminant recognition program and calibration data; a processor executing the program, the program including a module classifying contaminants by type, and a module using the data for comparison with magnitude of response generated by the sensor to calculate contaminant concentration; and, a pump, generating flow of air through the collector before and after the membrane is heated.

Disclosed are methods for determining and classifying aircraft air contaminants comprising one or more of: turbine engine oil, hydraulic fluid and deicing fluid using contaminant analyzers comprising a contaminant collector comprising a membrane and a heater vaporizing the contaminants; a gravimetric sensor generating a response when contaminant mass is added to or removed from the sensor, the sensor receiving contaminants desorbed from the heated membrane; a frequency measurement device, measuring the response generated by the sensor as the contaminant is added to and removed from the sensor; a computer readable medium bearing a contaminant recognition program and calibration data; a processor executing the program, the program including a module classifying contaminants by type, and a module using the data for comparison with magnitude of response generated by the sensor to calculate contaminant concentration; and, a pump, generating flow of air through the collector before and after the membrane is heated.

A aircraft cabin partition element and aircraft cabin arrangement, with a wall member having a lower edge and extending upwards from the lower edge provided with a coupling, capable of slidingly engaging a guide rail arrangement, an upper panel member pivotably mounted on the wall member with respect to a horizontal axis which is spaced from the lower edge, the upper panel member pivotable between a first position where the upper panel member extends from the horizontal axis towards the lower edge parallel to the wall member, and a second position where the upper panel member extends away from the wall member, and a support member movably mounted on the wall member and movable between a support position supporting the upper panel member when in the second position to prevent pivoting towards the wall member to the first position, and a storage position extending parallel to the wall member.

An oxygen supply system providing an adequate oxygen supply mode in an aircraft. A preventive oxygen supply system includes an oxygen source, a preventive oxygen dispensing unit connectable to the oxygen source, a cabin altitude detection device, and a preventive oxygen control device provide at least the following modes: a pre-wear mode providing no oxygen of the oxygen source to the preventive oxygen dispensing unit but normal cabin air; a pre-oxygenation mode providing a predetermined rate of oxygen of the oxygen source to the preventive oxygen dispensing unit sufficient for generating a pre-oxygenation condition of the user; and a decompression mode providing high concentrated oxygen of the oxygen source to the preventive oxygen dispensing unit sufficient for ensuring a minimum oxygenation of the user. The preventive oxygen control device automatically switches to the decompression mode in case a predetermined cabin altitude threshold is detected by the cabin altitude detection device.

An oxygen supply system providing an adequate oxygen supply mode in an aircraft. A preventive oxygen supply system includes an oxygen source, a preventive oxygen dispensing unit connectable to the oxygen source, a cabin altitude detection device, and a preventive oxygen control device provide at least the following modes: a pre-wear mode providing no oxygen of the oxygen source to the preventive oxygen dispensing unit but normal cabin air; a pre-oxygenation mode providing a predetermined rate of oxygen of the oxygen source to the preventive oxygen dispensing unit sufficient for generating a pre-oxygenation condition of the user; and a decompression mode providing high concentrated oxygen of the oxygen source to the preventive oxygen dispensing unit sufficient for ensuring a minimum oxygenation of the user. The preventive oxygen control device automatically switches to the decompression mode in case a predetermined cabin altitude threshold is detected by the cabin altitude detection device.

An aircraft cabin blower system is described having a hydraulic circuit comprising a first hydraulic device and a second hydraulic device. The first hydraulic device is mechanically coupled to a cabin blower compressor and the second hydraulic device is arranged in use to be mechanically coupled to a spool of a gas turbine engine. The first hydraulic device is capable of performing as a hydraulic motor and the second hydraulic device is capable of performing as a hydraulic pump. When, in use, the system is operating in a cabin blower configuration, a driving force supplied by the spool of the gas turbine causes the second hydraulic device to pump liquid provided in the hydraulic circuit and thereby to drive the first hydraulic device, which in turn rotates the cabin blower compressor.

An aircraft cabin blower system is described having a hydraulic circuit comprising a first hydraulic device and a second hydraulic device. The first hydraulic device is mechanically coupled to a cabin blower compressor and the second hydraulic device is arranged in use to be mechanically coupled to a spool of a gas turbine engine. The first hydraulic device is capable of performing as a hydraulic motor and the second hydraulic device is capable of performing as a hydraulic pump. When, in use, the system is operating in a cabin blower configuration, a driving force supplied by the spool of the gas turbine causes the second hydraulic device to pump liquid provided in the hydraulic circuit and thereby to drive the first hydraulic device, which in turn rotates the cabin blower compressor.

A thermal management system includes at least one vapor compression system (VCS) that is configured to cool portions of the vehicle. The VCS circulates a fluid therethrough to cool the portions of the vehicle through heat exchange. At least one reverse air cycle machine (RACM) couples to VCS through a first heat exchanger. The RACM is configured to receive ram air. The RACM expands the ram air. Heat from the fluid circulating through the VCS is transferred to the expanded ram air through the first heat exchanger.