Sikorsky Aircraft Corporation

Lockheed Martin Corporation

United Technologies Corporation

Labinal, LLC

Timothy R Budd

Patrick Wellington Mills

Mark P Eisenhauer

Kevin Francis Hanley

Stephen B Povroznik, Iii

Robert J Flemming, Jr

Michael Houlihan

Antonio G Daniele

Thomas B Priest

Kevin P McGonigle

Darryl A Tetrault

Lisa A DeLise

Therese-ann B Ngaya

James A Monson

James R Malo

Patrick W Mills

Kevin F Hanley

James M Mccormick

Systems and methods for alerting reverse current conditions of vehicle charging systems. One embodiment provides an aircraft power system comprising an aircraft power source and a notification device. The notification device includes a control unit configured to monitor a supply of current from an external power supply to the aircraft power source and detect a reverse current condition of current flowing from the aircraft power source to the external power supply. In response to detecting the reverse current condition, the control unit is configured to provide a notification indicative of the reverse current condition.

External power safety alert for a vehicle

According to an aspect, a fire suppressant system includes a first fire bottle in operable communication with a first cockpit control switch via a first channel, and a first sensor-based switch via a second channel. Additionally, the fire suppressant system includes a second fire bottle in operable communication with a second cockpit control switch via a third channel, and a second sensor-based switch via a fourth channel.

Automatic main engine fire bottle discharge feature&#x2014;dual channel design

A rotary blade includes a blade body, one or more heater elements, and a temperature sensing circuit. The one or more heater elements are connected to the blade body. The temperature sensing circuit is in thermal communication with the blade body and is electrically isolated from the one or more heater elements for determining actual temperature of the rotary blade independent of operation of the one or more heater elements.

Ice protection systems

A dual primary deicing system for a rotary-wing aircraft, according to an exemplary aspect of the present disclosure includes, among other things, an electrothermal heating element system; and a controller in communication with said electrothermal heating element, said controller communicating a heating cycle to said electrothermal heating element system, said heating cycle defining a first electric pulse train associated with a main rotor blade assembly.

Dual-channel deicing system for a rotary wing aircraft

A deicing system includes dual deice system components to provide a redundant deice system. Each redundant portion of the system generally includes a controller, an air data computer, an ice rate controller, and an ice rate probe. The controller communicating a heating cycle which defines a multiple of electric pulse trains to sequentially provides power to a multiple of heating elements in a designated blade set. Each electric pulse train is defined by an element on-time, a null time between the element on-time for this element and the next element, and an off-time between repetition of the heating cycle for the first heater element. The element on-time is a function of outside air temperature (OAT). The off-time is a function of liquid water content. The tail rotor heating cycle is a more straightforward version of the main rotor heating cycle as each of the tail rotor blade are activated simultaneously and there is only a single heating element on each tail rotor blade.

A control system for automatically loading and unloading a vehicle (10) from a cargo compartment comprises a plurality of distance measuring sensors (31,32,33,34) attached to specified locations on the exterior surfaces of the vehicle (54,56,57) and the cargo compartment (55). The sensors provide distance signals, indicative of the distance between each sensor and the nearest obstruction, to a microprocessor which compares each of the distance signals to reference signals indicative of the minimum allowable clearance between each specified location and an obstruction. During activation of an automatic loading/unloading switch (70), a winch (39) is activated to move the vehicle into or out of a cargo compartment if each of the distances is greater than the corresponding minimum allowable clearance. If any clearance is less than the minimum allowable clearance while the vehicle is being moved, movement of the vehicle is automatically stopped and the height of the vehicle is adjusted (800-815) until all of the distances are greater than the corresponding minimum allowable clearances, after which the winch is reactivated to continue moving the vehicle. The cycle is repeated until the helicopter is in its final position or the automatic loading/unloading switch is released.

System for automatic loading of vehicles for transport

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Stratford, CT, United States of America

Timothy R Budd