Patents by Inventor Mark P. Eisenhauer
Mark P. Eisenhauer has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Publication number: 20240060425Abstract: A hybrid propulsion system extracts electrical power using a combined heat engine and electrical generator. The propulsion system includes a gas generator, an electrical power generator disposed upstream of the gas generator and configured to be driven by a power turbine, an output power shaft mated to the power turbine and extending through a central axis of the gas generator and power generator unit, an engine enclosure circumferentially surrounding the power generator, and a shroud disposed between the power generator and the engine enclosure. The electrical power generator includes at least one rotating member and a stationary conductive member, wherein the at least one rotating member includes a magnetic portion, and rotation of the at least one rotating member relative to stationary conductive member generates a current transmissible by one or more coupled power output cables.Type: ApplicationFiled: October 16, 2023Publication date: February 22, 2024Applicant: Lockheed Martin CorporationInventors: Joseph Lawrence Simonetti, Mark P. Eisenhauer, Michael Strauss
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Patent number: 11788428Abstract: A hybrid propulsion system extracts electrical power using a combined heat engine and electrical generator. The propulsion system includes a gas generator, an electrical power generator disposed upstream of the gas generator and configured to be driven by a power turbine, an output power shaft mated to the power turbine and extending through a central axis of the gas generator and power generator unit, an engine enclosure circumferentially surrounding the power generator, and a shroud disposed between the power generator and the engine enclosure. The electrical power generator includes at least one rotating member and a stationary conductive member. The at least one rotating member includes a magnetic portion, and rotation of the at least one rotating member relative to stationary conductive member generates a current transmissible by one or more coupled power output cables.Type: GrantFiled: January 21, 2021Date of Patent: October 17, 2023Assignee: LOCKHEED MARTIN CORPORATIONInventors: Joseph Lawrence Simonetti, Mark P. Eisenhauer, Michael Strauss
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Publication number: 20220228505Abstract: A hybrid propulsion system extracts electrical power using a combined heat engine and electrical generator. The propulsion system includes a gas generator, an electrical power generator disposed upstream of the gas generator and configured to be driven by a power turbine, an output power shaft mated to the power turbine and extending through a central axis of the gas generator and power generator unit, an engine enclosure circumferentially surrounding the power generator, and a shroud disposed between the power generator and the engine enclosure. The electrical power generator includes at least one rotating member and a stationary conductive member. The at least one rotating member includes a magnetic portion, and rotation of the at least one rotating member relative to stationary conductive member generates a current transmissible by one or more coupled power output cables.Type: ApplicationFiled: January 21, 2021Publication date: July 21, 2022Applicant: Lockheed Martin CorporationInventors: Joseph Lawrence Simonetti, Mark P. Eisenhauer, Michael Strauss
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Patent number: 11344757Abstract: 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.Type: GrantFiled: July 10, 2020Date of Patent: May 31, 2022Assignee: LOCKHEED MARTIN CORPORATIONInventors: Timothy R. Budd, Mark P. Eisenhauer, Thomas B. Priest, Stephen B. Povroznik, III, Lisa A. DeLise, Therese-ann B. Ngaya
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Publication number: 20220008769Abstract: 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.Type: ApplicationFiled: July 10, 2020Publication date: January 13, 2022Inventors: Timothy R. Budd, Mark P. Eisenhauer, Thomas B. Priest, Stephen B. Povroznik, III, Lisa A. DeLise, Therese-ann B. Ngaya
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Patent number: 10457403Abstract: 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.Type: GrantFiled: September 1, 2017Date of Patent: October 29, 2019Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Michael Houlihan, Robert J. Flemming, Jr., Antonio G. Daniele, Timothy R. Budd, Mark P. Eisenhauer
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Patent number: 10087902Abstract: A method of operating an electrical system of an aircraft is provided. The method includes initiating a cross-start action for cross-starting a non-operative engine using a generator of an operative engine, entering a power limiting mode of a generator control unit (GCU) of the operative engine, remaining in the power limiting mode for a duration of the cross-start action and returning to the non-power limiting mode of the GCU of the operative engine upon completion of the cross-start action.Type: GrantFiled: May 11, 2016Date of Patent: October 2, 2018Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Mark P. Eisenhauer, Frederick L. Bourne, Matthew Fogarty
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Patent number: 9909502Abstract: Embodiments are directed to an engine of an aircraft, a starter generator configured to receive power to cause the engine to start and to provide electrical power to at least one load, and a battery system comprising: a battery, and at least one of a controller and a regulator configured to limit an in-rush current to the battery following the starting of the engine.Type: GrantFiled: November 30, 2012Date of Patent: March 6, 2018Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Mark P. Eisenhauer, Frederick L. Bourne
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Publication number: 20180037328Abstract: 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.Type: ApplicationFiled: September 1, 2017Publication date: February 8, 2018Inventors: Michael Houlihan, Robert J. Flemming, JR., Antonio G. Daniele, Timothy R. Budd, Mark P. Eisenhauer
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Patent number: 9849996Abstract: A method of engine electrical load shed control includes receiving an accessory load indicator corresponding to an accessory load of an engine. A request for acceleration of the engine is detected. One or more electrical buses are depowered based on the accessory load indicator exceeding a shedding threshold and detection of the request for acceleration of the engine.Type: GrantFiled: February 11, 2015Date of Patent: December 26, 2017Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: John H. Judge, Nicholas D. Kefalas, Mark P. Eisenhauer, Frederick L. Bourne, Robert J. Andrejczyk, Michael Patrick Wade
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Patent number: 9660435Abstract: A multidirectional electrical power protection system, includes a first power supply and at least a second power supply with each supply being configured for supplying power to a main bus circuit; a first load bus electrically connected to the first power supply and at least the second power supply, at least a second load bus electrically coupled with each of the first power supply and at least the second power supply, the first load bus and the second load bus configured for energizing devices connected to the respective first and second load bus; and at least one smart contactor in coupled with the main bus circuit, the at least one smart contactor being configured for sensing a first current flowing in a first direction through the main bus circuit and for sensing a second current flowing in a second direction through the main bus circuit.Type: GrantFiled: December 21, 2011Date of Patent: May 23, 2017Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Christopher P. Sullivan, Mark P. Eisenhauer, Raymond Andrew Loch
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Publication number: 20160332740Abstract: A method of operating an electrical system of an aircraft is provided. The method includes initiating a cross-start action for cross-starting a non-operative engine using a generator of an operative engine, entering a power limiting mode of a generator control unit (GCU) of the operative engine, remaining in the power limiting mode for a duration of the cross-start action and returning to the non-power limiting mode of the GCU of the operative engine upon completion of the cross-start action.Type: ApplicationFiled: May 11, 2016Publication date: November 17, 2016Inventors: Mark P. Eisenhauer, Frederick L. Bourne, Matthew Fogarty
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Publication number: 20150225089Abstract: A method of engine electrical load shed control includes receiving an accessory load indicator corresponding to an accessory load of an engine. A request for acceleration of the engine is detected. One or more electrical buses are depowered based on the accessory load indicator exceeding a shedding threshold and detection of the request for acceleration of the engine.Type: ApplicationFiled: February 11, 2015Publication date: August 13, 2015Inventors: John H. Judge, Nicholas D. Kefalas, Mark P. Eisenhauer, Frederick L. Bourne, Robert J. Andrejczyk, Michael Patrick Wade
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Publication number: 20140150446Abstract: Embodiments are directed to an engine of an aircraft, a starter generator configured to receive power to cause the engine to start and to provide electrical power to at least one load, and a battery system comprising: a battery, and at least one of a controller and a regulator configured to limit an in-rush current to the battery following the starting of the engine.Type: ApplicationFiled: November 30, 2012Publication date: June 5, 2014Inventors: Mark P. Eisenhauer, Frederick L. Bourne
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Publication number: 20140076882Abstract: 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.Type: ApplicationFiled: September 4, 2013Publication date: March 20, 2014Applicant: Sikorsky Aircraft CorporationInventors: Michael Houlihan, Robert J. Flemming, JR., Antonio G. Daniele, Timothy R. Budd, Mark P. Eisenhauer
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Patent number: 8564914Abstract: An electrical power protection system, includes a generator configured for supplying Direct Current (DC) power to a load bus, the load bus in electrical communication with a bus circuit; a generator control unit being configured for regulating the output voltage supplied by the generator; a bus contactor in serial communication with the bus circuit, the bus contactor including logic circuits configured for detecting an overcurrent in the bus circuit, the overcurrent representative of a ground fault in the bus circuit; and a capacitor bank coupled to the generator for selectively supplying an excitation voltage through a diode switch to the generator during the ground fault in the bus circuit.Type: GrantFiled: February 21, 2012Date of Patent: October 22, 2013Assignee: Sikorsky Aircraft CorporationInventors: Mark P. Eisenhauer, Christopher Patrick Sullivan
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Patent number: 8550402Abstract: 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.Type: GrantFiled: April 6, 2005Date of Patent: October 8, 2013Assignee: Sikorsky Aircraft CorporationInventors: Michael Houlihan, Robert J. Flemming, Jr., Antonio G. Daniele, Timothy R. Budd, Mark P. Eisenhauer
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Publication number: 20130215536Abstract: An electrical power protection system, includes a generator configured for supplying Direct Current (DC) power to a load bus, the load bus in electrical communication with a bus circuit; a generator control unit being configured for regulating the output voltage supplied by the generator; a bus contactor in serial communication with the bus circuit, the bus contactor including logic circuits configured for detecting an overcurrent in the bus circuit, the overcurrent representative of a ground fault in the bus circuit; and a capacitor bank coupled to the generator for selectively supplying an excitation voltage through a diode switch to the generator during the ground fault in the bus circuit.Type: ApplicationFiled: February 21, 2012Publication date: August 22, 2013Applicant: SIKORSKY AIRCRAFT CORPORATIONInventors: Mark P. Eisenhauer, Christopher Patrick Sullivan
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Publication number: 20130162035Abstract: A multidirectional electrical power protection system, includes a first power supply and at least a second power supply with each supply being configured for supplying power to a main bus circuit; a first load bus electrically connected to the first power supply and at least the second power supply, at least a second load bus electrically coupled with each of the first power supply and at least the second power supply, the first load bus and the second load bus configured for energizing devices connected to the respective first and second load bus; and at least one smart contactor in coupled with the main bus circuit, the at least one smart contactor being configured for sensing a first current flowing in a first direction through the main bus circuit and for sensing a second current flowing in a second direction through the main bus circuit.Type: ApplicationFiled: December 21, 2011Publication date: June 27, 2013Applicant: SIKORSKY AIRCRAFT CORPORATIONInventors: Christopher P. Sullivan, Mark P. Eisenhauer, Raymond Andrew Loch
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Patent number: 6227492Abstract: A redundant ice management system and method to de-ice and anti-ice an aircraft member (150) is provided. The system comprising a primary ice management sub-system (154) for providing thermal ice management to the aircraft member and a secondary ice management sub-system (172) for providing back-up thermal ice management to the aircraft member (150) in the event of a failure by the primary ice management sub-system (154). The system provides primary and secondary de-ice and anti-ice capabilities to the aircraft member (150) before and during airborne operation.Type: GrantFiled: August 6, 1999Date of Patent: May 8, 2001Assignee: Bell Helicopter TEXTRON Inc.Inventors: Ernst Calvin Schellhase, Mark P. Eisenhauer, Richard Dean Miller, John Peter Pappas, Gary Scott Froman, Roger Jacques Michel Aubert