United Technologies Corporation

US Government As Represented by the Secretary of the Army

Sikorsky Aircraft Corporation

United Technology Corporation

Michael P Bradford

Gerald W Parkinson

Joseph R Maciolek

Ross M Grant

Thomas Perrotta

Anthony F Sodoski

Bruce S Hamilton

A vehicle power system includes a multiple of electrical generators which provide power for vehicle electrical systems or loads through an electrical load management center which communicates with a general purpose processor set such that the power supplied to each electrical load may be individually controlled. A display communicates with the GPPS to present an electrical system status screen to the vehicle crew such that the crew is constantly made aware of the prevailing electrical power conditions in a rapid and efficient manner. During a drastically reduced generator situation, the GPPS automatically disconnects loads via a predefined load shed priority list. Once electrical loads are disconnected via the predefined load shed priority list the crew can reactivate and deactivate selected systems for the current mission circumstances through a load recovery screen accessible through the display.

Power management under limited power conditions

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. During start-up at low film temperature, film temperature error is filtered (315) to gradually heat up the film at a rate dependent upon the magnitude of the error. After a warm-up delay (307), film temperature error is compared to a fixed temperature error limit (385), the exceedance of which will cause termination of film heating (390) to thereby prevent over temperature of the windshield.

Windshield temperature control system

A helicopter rotor control system (13) including a stop azimuth controller (32) for establishing the value of a deceleration command (15') to a deceleration controller (23), a transition azimuth predictor (41) and a position reference generator (55), which are effective during the last revolution of said rotor (14) to establish a correction indication (38) to adjust the deceleration command (15') to ensure that one of the rotor blades (27) stops at a predetermined angular position.

Rotor control system

A power distribution system includes a plurality of power sources and load transfer units including transistors and diodes connected in series and leading to a common power output, each of the transistors being controller switchable subject to voltage levels of the respective input and output sides of said transistors, and the voltage and current level of said common power output. The system is part of an interconnection scheme in which all but one of the power sources is connected to a single load transfer unit, enabling the survival of at least a single power source with the failure of one of the load transfer units.

Electric power distribution and load transfer system

Frequently, particularly in the case of old machines such as engines, traissions, and gear boxes, particles, or 'chips', are produced as the internal parts wear out. When these chips are present they indicate equipment damage and must be removed since they can cause additional damage to the equipment. For over a decade such electric chip detectors have been installed in helicopter transmissions and engines, as well as in propulsion and drive systems of many military fixed wing aircraft. Detectors usually have a pair of permanently magnetized electrodes that are insulated from each other and positioned to form a magnetic field in the small gap therebetween. One of the underlying problems of monitoring wear particles is that detectors can be triggered by an accumulation of metallic dust, causing a false chip detection warning. The wear particle detector system herein, of the type having a pair of electrically actuated electrodes, is constructed to discriminate between harmless dust and harmful chips while monitoring the rate of wear particle accumulation as a machine runs.

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Orange, CT, United States of America

Michael P Bradford