Anthony S Litwinowicz

US Patent:

20110137494, Jun 9, 2011

Filed:

Nov 1, 2010

Appl. No.:

12/917091

Inventors:

Anthony Litwinowicz - Derby CT, US

Assignee:

SIKORSKY AIRCRAFT CORPORATION - Stratford CT

International Classification:

G06F 7/00

US Classification:

701 3

Abstract:

A method for velocity profile based approach to point control for an aircraft includes determining a distance from the aircraft to a target point; determining a velocity command based on the distance to the target point and a desired acceleration; and issuing the velocity command. A velocity profile based approach to point control module for an aircraft and a computer program product comprising a computer readable storage medium containing computer code that, when executed by a computer, implements a method for velocity profile based approach to point control are also provided.

US Patent:

20170285660, Oct 5, 2017

Filed:

Jan 11, 2017

Appl. No.:

15/403807

Inventors:

- Stratford CT, US
Anthony Litwinowicz - Derby CT, US

International Classification:

G05D 1/06
B64C 27/04
B64C 13/50
B64C 27/82

Abstract:

A rotary wing aircraft control system includes an airframe, a main rotor assembly supported by the airframe, and a control system arranged in the airframe and operatively connected to the main rotor assembly. The control system includes a flight control computer (FCC), at least one control inceptor device and a touchdown orientation control system. The touchdown orientation control system includes a computer readable program code an FCC to: sense, by a sensor operatively connected to the flight control computer (FCC), an altitude of the rotary wing aircraft relative to a landing surface, determine one of a landing state rearward velocity reference limit value and a landing state lateral velocity reference limit value associated with the altitude, and selectively limit a landing state flight envelope of the rotary wing aircraft to the one of the landing state rearward velocity reference limit value and the landing state lateral velocity reference limit value.

US Patent:

20150050142, Feb 19, 2015

Filed:

Aug 14, 2013

Appl. No.:

13/966951

Inventors:

- Stratford CT, US
Anthony Litwinowicz - Derby CT, US

Assignee:

Sikorsky Aircraft Corporation - Stratford CT

International Classification:

B64C 27/04

US Classification:

416 1, 416 98

Abstract:

Controlling rotor blades of a rotor assembly includes determining an azimuthal position of a rotor assembly and identifying a lateral control command value, a longitudinal control command value and a collective control command value of a rotor assembly control system. A sine value and a cosine value of the azimuthal position are calculated and separate blade commands signals are generated for each separate blade of the rotor assembly to control a position of each blade independent of each other blade. The blade command signals are generated based on combining the sine and cosine values of the azimuthal position with the lateral control command value, the longitudinal control command value and the collective control command value.