Thomas M Perrotta

US Patent:

54969891, Mar 5, 1996

Filed:

May 5, 1994

Appl. No.:

8/238553

Inventors:

Michael P. Bradford - Orange CT
Thomas Perrotta - Brookfield CT

Assignee:

United Technology Corporation - Hartford CT

International Classification:

H05B 102
B60L 102

US Classification:

219497

Abstract:

A windshield temperature control system (200) monitors aircraft operating (240) and environmental (246) conditions, and determines, based on the fixed physical properties of the windshield (250,251 ), a required film temperature necessary to produce a heat output to maintain the internal and/or external temperature of the windshield at a desired temperature. The heat output is based on a total heat loss including internal heat loss and external convective, evaporative, sensible and radiation heat loss, and a film temperature error defined as the difference (340) between required film temperature and actual film temperature is applied via proportional (355) and integral (350) control paths to produce zero steady state film temperature error. The desired external temperature is selected to be sufficiently above freezing, i. e. , 0. degree. C. , to prevent ice formation on the windshield, and the desired internal temperature is selected to be sufficiently above the cockpit air dew point to prevent condensation on the internal surfaces of the windshield.

US Patent:

53277449, Jul 12, 1994

Filed:

Dec 18, 1992

Appl. No.:

7/992392

Inventors:

Robert C. Frawley - Shelton CT
Thomas Perrotta - Brookfield CT
Richard S. Barnard - Monroe CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F25D 900

US Classification:

62401

Abstract:

A compact, lightweight integrated environmental control (IEC) system for a helicopter incorporates in operative combination an environmental control system (ECS) and a nuclear/biological/chemical life support system (NBC LSS). The IEC system includes a refrigerant subsystem, a regenerative heat exchange apparatus, a decontamination subsystem, and an airflow distribution network, and is operative to provide super-cooled, super-dry, decontaminated airflow, in seriatim, directly to left and right mission equipment package bays and the cockpit for cooling of avionics/electronic modules and crew comfort. The IEC system is further operative to directly provide cooled, super-dry, decontaminated airflow for cooling of avionics/electronic modules of the mid mission equipment package bay and for over pressurizing the left and right mission equipment package bays to preclude contaminant infiltration thereof.