Abstract: A system for improving the air quality in a pressure cabin of an aircraft comprises a recirculation air circuit by means of which a portion of the cabin air, referred to as recirculation air, is withdrawn from the pressure cabin, filtered and then recirculated into the pressure cabin. To increase the oxygen partial pressure of the air fed back into the pressure cabin, the quantity of recirculation air is passed wholly or partially through a nitrogen generator (52) which generates nitrogen and an oxygen-containing waste gas from the recirculation air supplied. The oxygen-containing waste gas of the nitrogen generator (52), together with any remaining quantity of recirculation air untreated by the nitrogen generator (52), is recirculated into the pressure cabin. The nitrogen generator (52), to which only recirculation air is supplied, utilises a pressure gradient existing in flight between the pressure cabin and the outside of the aircraft for nitrogen generation.

Abstract: With a method for controlling the temperature of feed air which is injected into the cabin zone of a passenger aircraft, the cabin of which is sub-divided into several cabin zones supplied respectively with specially temperature-controlled feed air, the temperature of the injected feed air is controlled for each cabin zone, dependent upon the deviation of an injection temperature actual value for the feed air injected into the cabin zone in question, measured by sensors, in relation to an injection temperature optimum value. If there is no, or at least no usable reading of the ambient temperature of this cabin zone for a cabin zone, an optimum value for the injection temperature of this cabin zone can be established in accordance with a variation, whereby it is determined upon the basis of the injection temperature optimum values and/or the injection temperature actual values of other cabin zones, whereby the measurement by sensors of the cabin temperature works reliably.

Abstract: With a method for controlling the temperature of feed air supplied to a cabin area of a passenger aircraft (10), a measurement value for the ambient temperature in the cabin area is determined by means of a temperature sensor system (24). The temperature of the feed air is controlled, dependent upon a deviation of the ambient temperature measurement value in relation to an ambient temperature optimum value. In accordance with the invention, the ambient temperature measurement value is deduced from a number of individual temperature values for different points in the cabin area. In accordance with an example, the temperature sensor system used to establish individual temperature values for a cabin zone includes a number of discreet temperature sensors (24) positioned in this cabin zone, each of which provides an individual temperature value. Preferably, the temperature sensors (24) are distributed evenly over the whole length of the cabin zone in question.

Abstract: A method and a line system for the air-conditioning of a freight compartment or a cabin of an aircraft envisage that at sites (A, B, C, D) remote from passengers air that is at a temperature different from that at sites (E, F, G, H) closer to passengers is introduced into the freight compartment (12, 14) or into the cabin.

Abstract: With a cooling system for expelling heat from a heat source (30) located in the interior of an aircraft to a heat reducer (32), with a piping system (10) sealed against the surrounding atmosphere which is thermally coupled to a heat intake section (14) with the heat source (38) and to a heat output section (22) with the heat reducer (32), and which preferably has an essentially adiabate transport section (21), it is proposed that the piping system (10) is filled with a heat conveyance medium (12) which, when taking in heat from the heat source (38) in the heat intake section (14) undergoes a transition from the liquid phase to the gaseous phase, then flows into the heat output section (22), and here, when discharging heat to the heat reducer (32) condenses once again, and flows back into the heat intake section (14).

Abstract: The present application describes an arrangement and a method for utilizing the heat of waste air for heating the bilge area of aircraft, wherein the bilge area is connected to a heat transfer unit via a first air supply pipe, through which a bilge air flow drawn in from the bilge area flows into the heat transfer unit, wherein the heat transfer unit comprises a second air supply pipe, through which a waste air heat flow to be cooled that is created at another location in the aircraft flows into the heat transfer unit in order to heat the drawn-in bilge air flow, wherein the heat transfer unit comprises a first air discharge pipe, through which the cooled waste air heat flow is discharged, and a second air discharge pipe with a bilge inlet section, and wherein at least a portion of the heated bilge flow is returned to the bilge area via the air discharge pipe and the bilge inlet section.

Abstract: An air dispersion system has a main supply line, a plurality of air outlets, which are connected via respective air exhaust routes to the main supply line, and at least one heating element, which is associated with at least one of the air outlets and can temper the air in the exhaust route of this air outlet.

Abstract: An aircraft air-conditioning system provides ventilation, air-conditioning and fire protection for a below-deck stairwell and cargo hold that may be equipped with passenger sleeping compartment containers. An air mixing unit mixes fresh air and recycled air to supply mixed air through a first supply air main line (31) and a supply air unit (21) into the freight hold (4), and through a second supply air main line (32) into the stairwell (5). A trimming air unit (7A) provides hot bleed air from the aircraft engines into the mixed air supplied through the first and second supply air main lines (31, 32). An exhaust air line (11) extracts exhaust air from the freight hold (4), while an exhaust air supplemental line (15) extracts exhaust air from the stairwell (5), both of which are connected to an exhaust air main line with an exhaust air ventilator (16) that blows the exhaust air overboard. A bypass line (8) provides bypass air if needed for the demands of the ventilator (16).

Abstract: The below-deck space of an aircraft may be selectively configured as a freight hold or alternatively as a passenger sleeping cabin space by arranging a sleeping cabin container therein. An air conditioning system for this below-deck space provides air in a supply air main line (31), which branches off to at least one supply air delivery line (19). A first flange (23) is provided at the end of the supply air delivery line (19), and a seal collar (25) seals the end relative to the freight hold wall (29). When a sleeping cabin container is to be arranged in the below-deck space, a flap door (24) is pivoted into an open position, and the flange (28) at the end of a ventilation duct (27) of the sleeping cabin is connected directly to the flange (23).

Abstract: An air supply system for an aircraft cabin reduces the concentration of contaminations of the air in the cabin by a flexibly controllable valve system that comprises pairs of valves which on the one hand are ganged to respective air openings. One valve of a pair is connected to a fresh air or mixed air supply line. The other valve of a pair is connected to a suction or exhaust duct. Thus, depending on which valve in a pair is open and which is closed, the respective air opening can function as an air outlet for supply of mixed or fresh air into the cabin or as a suction port. Such a system permits a flexible volume control of the supply of fresh air into selectable cabin sections as well as a flexible volume control for the removal of used air from respective cabin sections. Additionally, it is now possible to increase the size of the non-smoking section at the expense of the smoking section or vice versa simply by a respective valve control.

Abstract: A method and apparatus is provided for air conditioning two passenger decks in an aircraft, especially a high capacity aircraft. The engine tap air stream is provided for air conditioning the upper deck passenger cabin and the lower deck passenger cabin. The air stream is cooled in at least one air conditioning plant, mixed with recirculated air from the lower cabin in at least one premix chamber, and then mixed with recirculated air from the upper cabin in local mixing chambers. The finished air streams are directed to the upper deck and the lower deck passenger cabins. The upper deck exhaust air is essentially completely used as recirculation air being mixed with the conditioning air in the local mixing chambers. The lower deck exhaust air is partially used as recirculation air being mixed with the conditioning air in the premix chambers, and is partially exhausted overboard.