Abstract of the Disclosure
Title: ENVIRONMENT CONTROL SYSTEM FOR AIRCRAFT HAVING INTERIOR CONDENSATION PROBLEM REDUCTION, CABIN AIR QUALITY IMPROVEMENT, FIRE SUPPRESSION AND FIRE VENTING FUNCTIONS
Note: The diagrams have not been included as part of the Web Site because of their complexity. However, those interested can download the PDF file below to obtain the entire document. Read Patent Description in PDF Format. (45 pages, 1.2M)
An environment control system for a body of an aircraft that provides controlled ventilation of the interior space of an aircraft body (1), its interior (3) and its envelope (5), air flow blockers within its envelope (5) to reduce pressure differences between the envelope (5) and the interior space (3), sealing means adapted to at least partially seal the liner (7) against leakage of air between the interior space and the envelope, facilitating reduction of volatile organic compounds (VOCs) within cabin air, inhibiting moist cabin air from contacting cold envelope (5) surfaces, dehumidifying and reducing moisture condensation and thus corrosion and other moisture related problems within the envelope (5), allowing increased humidification of cabin air, and allowing suppression of fires within and venting of smoke directly outdoors from the envelope (5).
The environment control system includes at least a cabin (3) and an envelope (5). It includes supply means (23, 23a) for supplying a flow of dry air to the aircraft body (1). An airflow control device (13) is capable of dividing a flow of dry ventilation air (e.g. engine bleed air) into an envelope air stream (25) and a cabin air stream (26). An envelope duct system (14, 16, 27, 29) directs the envelope air stream (25) into the envelope (5), and a cabin duct system (20, 21) directs the cabin air stream (26) into the cabin (3). Envelope air flow blockers (28) restrict the circulation of air within the envelope and, together with sealing measures for the liner (7) and an envelope air distribution system (16, 27, 29), minimize air requirements to achieve the benefits for all or any portion of the aircraft body (e.g. within the crown of the envelope). An anti-corrosion/sorption treatment (41) is applied to surfaces subject to condensation in the envelope (5). A return air control unit (17) is provided for selectively drawing return air from one of the envelope (5) and the cabin (3). The environment control system can be incorporated into new aircraft construction, or can be installed as a retro-fit into existing aircraft.
[ Previous ] [ Top of Page ] [ Next ]