Patents by Inventor Nicholas D. Lappos
Nicholas D. Lappos 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).
-
Publication number: 20230382519Abstract: Systems and methods for automatically controlling landing gear responsive to detected aerial vehicle conditions. A system can receive, from one or more sensors of the aerial vehicle, altitude information and speed information of the aerial vehicle. The system can determine to lower landing gear of the aerial vehicle based on a change in a state of the aerial vehicle, and identify a condition corresponding to a type of the aerial vehicle and the state of the aerial vehicle. The system can compare the speed information and the altitude information to the condition to determine that a condition to lower landing gear is satisfied. Responsive to determining that the condition to lower the landing gear is satisfied, the system can provide a signal to lower the landing gear.Type: ApplicationFiled: May 25, 2022Publication date: November 30, 2023Applicant: LOCKHEED MARTIN CORPORATIONInventors: Nicholas D. Lappos, Christopher A. Thornberg
-
Publication number: 20220402600Abstract: A flight control system for a rotary-wing aircraft includes a shape sensor and a controller. The shape sensor is configured to measure a shape of a rotor blade during movement of the rotor blade. The controller is communicably coupled to the shape sensor and is configured to (i) receive, from the shape sensor, a first signal indicative of a first blade shape; (ii) receive a blade characteristic regarding the rotor blade; and (iii) determine at least one of a moment or force associated with the rotor blade based on the first signal and the blade characteristic.Type: ApplicationFiled: June 22, 2021Publication date: December 22, 2022Applicant: LOCKHEED MARTIN CORPORATIONInventors: Nicholas D. Lappos, Navid Dadkhah Tehrani, Mark Daniel Ward
-
Patent number: 10831193Abstract: An aircraft includes an airframe having an aircraft longitudinal axis and a main rotor system supported by the airframe. The main rotor system is rotatable about an axis of rotation. The airframe is tiltable relative to a ground surface to form a non-zero tilt angle between the aircraft longitudinal axis and the ground surface.Type: GrantFiled: November 14, 2017Date of Patent: November 10, 2020Assignee: Sikorsky Aircraft CorporationInventors: Nicholas D. Lappos, Christopher A. Thornberg
-
Patent number: 10745118Abstract: A rotary wing aircraft including a prime mover, a main rotor assembly having a first plurality of rotor blades operatively coupled to a main rotor shaft rotatable at a first speed ratio, a tail rotor assembly including a second plurality of rotor blades operatively coupled to a tail rotor shaft rotatable at a second speed ratio, and a variable ratio gearbox assembly mechanically connected to the tail rotor assembly. The variable ratio gearbox assembly operates to selectively vary the second speed ratio relative to the first speed ratio.Type: GrantFiled: August 17, 2017Date of Patent: August 18, 2020Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Frederick L. Bourne, Timothy F. Lauder, Nicholas D. Lappos
-
Publication number: 20190146490Abstract: An aircraft includes an airframe having an aircraft longitudinal axis and a main rotor system supported by the airframe. The main rotor system is rotatable about an axis of rotation. The airframe is tiltable relative to a ground surface to form a non-zero tilt angle between the aircraft longitudinal axis and the ground surface.Type: ApplicationFiled: November 14, 2017Publication date: May 16, 2019Inventors: Nicholas D. Lappos, Christopher A. Thornberg
-
Patent number: 10131442Abstract: The disclosure herein relates to power leveling mechanisms comprising a high frequency controller. The power leveling mechanism receives a power demand signal indicating a power requirement of a vehicle and determines a high frequency component of the power demand signal. The power leveling mechanism also provides a signal to a primary propulsion system and provides, via the high frequency controller, a high bandwidth signal based on the high frequency component to an auxiliary propulsion system.Type: GrantFiled: October 28, 2016Date of Patent: November 20, 2018Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Peter James Waltner, Joseph Lawrence Simonetti, Nicholas D. Lappos, Jonathan Hartman
-
Publication number: 20180086443Abstract: A rotary wing aircraft including a prime mover, a main rotor assembly having a first plurality of rotor blades operatively coupled to a main rotor shaft rotatable at a first speed ratio, a tail rotor assembly including a second plurality of rotor blades operatively coupled to a tail rotor shaft rotatable at a second speed ratio, and a variable ratio gearbox assembly mechanically connected to the tail rotor assembly. The variable ratio gearbox assembly operates to selectively vary the second speed ratio relative to the first speed ratio.Type: ApplicationFiled: August 17, 2017Publication date: March 29, 2018Inventors: Frederick L. Bourne, Timothy F. Lauder, Nicholas D. Lappos
-
Publication number: 20180065738Abstract: A system and method for controlling an altitude loss of an aircraft in response to a power loss event, includes obtaining at least one aircraft condition from at least one sensor, determining a present aircraft energy state of the aircraft from the at least one aircraft condition via an energy analysis unit, wherein the present aircraft energy state includes an aircraft potential energy and at least one of an aircraft kinetic energy and a rotor rotational kinetic energy, calculating a flight path to partially utilize at least one of the aircraft kinetic energy and the rotor rotational kinetic energy to initiate an autorotation state of the aircraft via a flight path controller, wherein the flight path controller minimizes an aircraft potential energy loss associated with the flight path, and initiating the autorotation state of the aircraft via the flight path.Type: ApplicationFiled: March 29, 2016Publication date: March 8, 2018Inventors: Nicholas D. Lappos, Michael Peter Strauss
-
Publication number: 20170297732Abstract: The disclosure herein relates to power leveling mechanisms comprising a high frequency controller. The power leveling mechanism receives a power demand signal indicating a power requirement of a vehicle and determines a high frequency component of the power demand signal. The power leveling mechanism also provides a signal to a primary propulsion system and provides, via the high frequency controller, a high bandwidth signal based on the high frequency component to an auxiliary propulsion system.Type: ApplicationFiled: October 28, 2016Publication date: October 19, 2017Inventors: Peter James Waltner, Joseph Lawrence Simonetti, Nicholas D. Lappos, Jonathan Hartman
-
Publication number: 20170129597Abstract: An aircraft comprising an airframe; a rotor system mounted to the airframe, the rotor system including a plurality of rotor blades, each of the plurality of rotor blades including a root portion extending to a tip portion through an airfoil portion, the airfoil portion having a leading edge and a trailing edge; at least one control surface mounted within the airfoil portion of at least one of the plurality of rotor blades; at least one actuator configured to actuate the at least one control surface; and at least one actuator configured to pitch at least one of the plurality of rotor blades about a blade pitch axis.Type: ApplicationFiled: November 10, 2016Publication date: May 11, 2017Inventors: Timothy Fred Lauder, Jonathan Hartman, Nicholas D. Lappos
-
Publication number: 20160131765Abstract: A method for providing WAAS infrastructure in conjunction with the sale of a WAAS enabled aircraft includes developing a sales package for a customer. The price of the sales package preferably includes a WAAS enabled aircraft and a WAAS infrastructure. The method further includes assembling a WAAS enabled aircraft and developing the WAAS infrastructure using a computer. The method also includes providing the customer with the WAAS enabled aircraft and the WAAS infrastructure.Type: ApplicationFiled: July 30, 2015Publication date: May 12, 2016Applicant: TEXTRON INNOVATIONS INC.Inventors: William W. Fulton, Nicholas D. Lappos
-
Publication number: 20120316979Abstract: A method for providing WAAS infrastructure in conjunction with the sale of a WAAS enabled aircraft includes developing a sales package for a customer. The price of the sales package preferably includes a WAAS enabled aircraft and a WAAS infrastructure. The method further includes assembling a WAAS enabled aircraft and developing the WAAS infrastructure using a computer. The method also includes providing the customer with the WAAS enabled aircraft and the WAAS infrastructure.Type: ApplicationFiled: May 12, 2010Publication date: December 13, 2012Inventors: William W. Fulton, Nicholas D. Lappos
-
Patent number: 7651050Abstract: A gearbox of a rotary-wing aircraft includes at least one variable speed system which optimizes the main rotor speed for different flight regimes such as a hover flight profile and a high speed cruise flight profile for any rotary wing aircraft while maintaining an independently variable tail rotor speed.Type: GrantFiled: September 3, 2008Date of Patent: January 26, 2010Assignee: Sikorsky Aircraft CorporationInventors: Nicholas D. Lappos, Edward Karedes, Harsh Vinayak, Yuriy Gmirya
-
Publication number: 20080315035Abstract: A gearbox of a rotary-wing aircraft includes at least one variable speed system which optimizes the main rotor speed for different flight regimes such as a hover flight profile and a high speed cruise flight profile for any rotary wing aircraft while maintaining an independently variable tail rotor speed.Type: ApplicationFiled: September 3, 2008Publication date: December 25, 2008Inventors: Nicholas D. Lappos, Edward Karedes, Harsh Vinayak, Yuriy Gmirya
-
Patent number: 7434764Abstract: A gearbox of a rotary-wing aircraft includes at least one variable speed system which optimizes the main rotor speed for different flight regimes such as a hover flight profile and a high speed cruise flight profile for any rotary wing aircraft while maintaining an independently variable tail rotor speed.Type: GrantFiled: December 2, 2005Date of Patent: October 14, 2008Assignee: Sikorsky Aircraft CorporationInventors: Nicholas D. Lappos, Edward Karedes, Harsh Vinayak, Yuriy Gmirya
-
Patent number: 6480763Abstract: A system and method for issuing an aircraft drift advisory. In one embodiment, the system includes a head or eye tracker to monitor the rotational position of the pilot's line of sight with respect to the aircraft axis. The pilot's line of sight is compared to the direction of the aircraft. If the absolute value of the difference is greater than or equal to a predetermined angle, corresponding to the foveal cone of vision, the incremental aircraft drift distance is computed and used to update the cumulative aircraft drift distance. The cumulative aircraft drift distance is compared to the predetermined advisory criterion, which may be a constant, a uniform function of altitude or a function of altitude that is tied to a digital terrain map. When the cumulative aircraft drift distance equals or exceeds the advisory criterion, the pilot is given a drift advisory that the aircraft has drifted so as to prompt the pilot to adjust his line of sight to the direction of the drift.Type: GrantFiled: December 14, 2000Date of Patent: November 12, 2002Assignee: Sikorsky Aircraft CorporationInventor: Nicholas D. Lappos
-
Patent number: 5465212Abstract: An integrated fire and flight control (IFFC) system determines a ballistic firing solution based on the position of targets relative to a helicopter and also based on the type of weapons to be fired. An elevation command is determined based on the required change in helicopter attitude to achieve the ballistic firing solution that, combined with the estimated time required to perform the aim and release of weapons, provides an estimate of deceleration and velocity loss that will occur. A forward acceleration and velocity profile is determined based on the desire to make a symmetrical maneuver sequence involving a nose down acceleration to achieve the acceleration and velocity profile that will be canceled by the subsequent deceleration and velocity loss during the pitch up maneuver to the ballistic firing solution.Type: GrantFiled: December 23, 1993Date of Patent: November 7, 1995Assignee: United Technologies CorporationInventors: Donald W. Fowler, Nicholas D. Lappos, Joan A. Edwards
-
Patent number: 5431084Abstract: A fire control system (55) azimuth command and elevation command provides a flight control system attitude reference in response to operation of the flight control system in a coupled aiming mode. The coupled aiming mode is engaged in response to the continuous operation of a pilot switch (920) the azimuth command and elevation command being below respective threshold magnitudes (940, 941), and the operation of the fire control system (55). During operation in the coupled aiming mode, the azimuth command and elevation command replace the yaw attitude feedback error signal and pitch attitude error signal, respectively, as the aircraft attitude reference.Type: GrantFiled: April 7, 1994Date of Patent: July 11, 1995Assignee: United Technologies CorporationInventors: Donald W. Fowler, Nicholas D. Lappos, James B. Dryfoos, James F. Keller
-
Patent number: 5339244Abstract: An integrated time/limit exceedance cue system including a plurality of dedicated subsystem sensors, a processing unit, and a graphics generating/processing unit that is operative to generate an event dependent, time varying visual cue indicative of the exceedance of an established normal operating limit of a specific aircraft subsystem and operation thereof in a time critical exceedance condition. The time varying visual cue provides a relative indication of the elapsed time of operation of the specific subsystem in the time critical exceedance condition. The time varying visual cue is a symbolic image in the form of an outline, having a predetermined length, that defines a void region. The void region is proportionately opaqued or "filled in" in correspondence with the elapsed time of operation of the specific subsystem in the time critical exceedance condition.Type: GrantFiled: August 13, 1992Date of Patent: August 16, 1994Assignee: United Technologies CorporationInventors: Lorren Stiles, Jr., Nicholas D. Lappos, Gregory P. Wright
-
Patent number: 5331881Abstract: A fire control system (55) azimuth command and elevation command provides a flight control system attitude reference in response to operation of the flight control system in a coupled aiming mode. The coupled aiming mode is engaged in response to the continuous operation of a pilot switch (920) the azimuth command and elevation command being below respective threshold magnitudes (940, 941), and the operation of the fire control system (55). During operation in the coupled aiming mode, the azimuth command and elevation command replace the yaw attitude feedback error signal and pitch attitude error signal, respectively, as the aircraft attitude reference.Type: GrantFiled: May 19, 1992Date of Patent: July 26, 1994Assignee: United Technologies CorporationInventors: Donald W. Fowler, Nicholas D. Lappos, James B. Dryfoos, James F. Keller