Aeronautics and astronautics – Aircraft structure – Details
Utility Patent
1999-02-12
2001-01-02
Swiatek, Robert P. (Department: 3643)
Aeronautics and astronautics
Aircraft structure
Details
C052S786100
Utility Patent
active
06168112
ABSTRACT:
PRIORITY CLAIM
This application is based on and claims the priority under 35 U.S.C. §119 of German Patent Applications 198 06 106.4 and 198 06 107.2, both filed on Feb. 14, 1998, the entire disclosures of which are incorporated herein by reference.
FIELD OF THE INVENTION
The invention relates to the construction of aircraft cabin windows having double panes with a spacing between the panes. The construction shall avoid fogging of the pane surfaces facing the space between the panes.
BACKGROUND INFORMATION
Efforts to defog the space between double window panes have been made over a long period of time. For example, German Patent 647,347 (Kruckenberg), published in 1937, suggests to hermetically seal the space between the panes in an airtight manner and to compensate for pressure differentials between the space and the outside by connecting the space to a flexible rubber bag, the volume of which is elastically variable to compensate for such pressure differentials to prevent breakage of the window panes.
U.S. Pat. No. 2,189,388 (Zand), published Feb. 6, 1940, discloses an aircraft double pane window construction in which the space between the panes is vented to the atmosphere outside the aircraft. The air between the panes is dried by causing the air to flow through a moisture absorbing material such as calcium chloride or silica gel contained in a canister (
11
).
U.S. Pat. No. 2,302,740 (Boicey), Published on Nov. 24, 1942, discloses double pane aircraft windows with a venting fitting specially placed to avoid damage to the inner glass pane. The fitting connects the vent to a suction device for withdrawing air from the space between the panes or for causing dehydrated air or heated air to circulate through the space between the window panes.
German Patent 933,371 (Götz), published Sep. 22, 1955, discloses double pane windows with an air dryer cartridge reaching into the space between the panes. Additionally, a pipe passing through the cartridge vents the space between the panes to the space inside the cabin.
The above prior art leaves room for improvement, especially with regard to economically dehumidifying the air entering from the cabin into the space between the panes. Even if the cabin air itself is relatively dry, fogging may occur nevertheless because the temperature on the inner surface of the outer pane may, for example, be about −20° C. while the temperature on the outside of the aircraft may, for example, be −30° C. or colder at high altitudes.
OBJECTS OF THE INVENTION
In view of the foregoing it is the aim of the invention to achieve the following objects singly or in combination:
to condition the air entering into the space between the panes from the cabin space without any additional structural components outside the window itself and without the use of an active power operated pressure control system;
to prevent fogging and icing of the window panes by a passive air conditioning device that substantially does not require window components in addition to those presently forming aircraft cabin windows except for an auxiliary seal, if necessary;
to modify present window components in such a way that air entering into the space between the panes is dehumidified by using the cold temperatures outside an aircraft for the dehumidifying; and
to guide air flowing from the cabin into the space between the panes into contact with a cold window frame component before the air enters into the space between the panes.
SUMMARY OF THE INVENTION
An aircraft cabin window with double panes having a space between the panes is characterized according to the invention by a metal frame that has a flange section for securing the metal frame to a fuselage wall, more specifically to the outer fuselage wall for heat exchange contact with the fuselage wall and thus with the atmosphere outside the aircraft. The metal frame further includes a mounting section in heat exchange contact with the flange section. The mounting section extends away from the flange section inwardly toward the space inside the cabin. At least one main sealing section secures the window panes to the metal frame so that the above mentioned space is provided between the panes. An air dehumidifying channel is positioned in heat exchange contact with the metal frame. A first air flow port communicates the air dehumidifying channel with the cabin space and a second air flow port communicates the air dehumidifying channel with the space between the window panes.
When humid air flows from the cabin through the first air flow port and then along the dehumidifying channel, humidity will be condensed along the dehumidifying channel due to its low temperature resulting from the heat exchange with the metal frame that in turn is in heat exchange with the exterior of the aircraft. Any condensation water is collected in the channel which is so positioned that the condensation water must flow by gravity through and out of the first air flow port into a collection container.
Advantages of the invention are seen in that an active power consuming pressure control system or air conditioning system is not required. Further, the space between the panes is reliably supplied with dried air. Currently existing double pane aircraft windows can be easily modified for the present purposes with insignificant efforts and expense. Merely the sealing strip or the window frame need to be changed for the present purposes. These changes do not increase the aircraft weight and the air conditioning does not require any extra energy. Even the passenger comfort is increased when the passenger's view through the window is not hampered by fogging.
REFERENCES:
patent: 2117581 (1938-05-01), Stoneback
patent: 2189388 (1940-02-01), Zand
patent: 2302740 (1942-11-01), Boicey
patent: 2320069 (1943-05-01), Cresswell et al.
patent: 5884865 (1999-03-01), Scherer et al.
patent: 647307 (1937-07-01), None
patent: 933371 (1955-09-01), None
Luetjens Heiko
Mueller Rainer
Scherer Thomas
Uhlemann Sven
DaimlerChrysler Aerospace Airbus GmbH
Fasse W. F.
Fasse W. G.
Swiatek Robert P.
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