Matthew D White, 30North Haven, CT

7369483, May 6, 2008

Jan 21, 2005

10/588066

W. Dennis Slafer - Arlington MA, US
Matthew White - Cohasset MA, US
Milford Kime - Cambridge MA, US
Timothy Frey - Hudson MA, US

MicroContinuum, Inc. - Cambridge MA

G11B 7/24

3692754, 369283

A pre-formatted optical data storage tape () including an elongated linear polymer layer having at least one pattern of optically readable embossments () on at least one surface of the polymer layer, and an optical recording layer covering the pattern of optically readable embossments () of the elongated linear polymer layer, wherein the optical recording layer is adapted such that recorded marks () may be made in the recording layer by directing a focused source of energy into the recording layer.

2012000, Jan 5, 2012

Jun 29, 2011

13/172342

Vineet Sahasrabudhe - Cheshire CT, US
Stella Jang - Derby CT, US
Matthew A. White - Milford CT, US

SIKORSKY AIRCRAFT CORPORATION - Stratford CT

G05D 1/00
G06G 7/78

701300

A method for directing formation flying of an aircraft includes sensing a relative position of a leader to a follower aircraft by one or more sensors disposed at the follower aircraft. The relative position is compared to a selected relative position, and a follower velocity of the follower aircraft necessary to move the follower aircraft to the selective relative position is determined via a flight control computer of the follower aircraft. The follower velocity is transformed into flight control inputs and the follower aircraft is moved to the selected relative position via the flight control inputs.

2019033, Nov 7, 2019

May 1, 2018

15/967949

- Stratford CT, US
Matthew A. White - Milford CT, US
Mark W. Davis - Southbury CT, US

B64D 45/00
B64C 13/16

A computer-implemented method and system for controlling an aircraft based on detecting control element damage is disclosed. According to one example, a computer-implemented method includes detecting, by a processing system, damage to a control element of the aircraft. The method further includes characterizing, by the processing system, the damage to determine a corrective action to take based at least in part on the detected damage. The method further includes controlling, by the processing system, the aircraft based at least in part on the corrective action.

2018000, Jan 4, 2018

Feb 6, 2017

15/425634

- Stratford CT, US
Matthew A. White - Milford CT, US

G05D 1/08
B64C 27/57
B64C 13/50

A method of controlling rotor moments includes receiving, in a flight control computer (FCC) a rotor moment reference value based on pilot inceptor inputs, sensing rotor moment from one or more sensors, receiving, in the FCC, a rotary wing aircraft condition parameter, and establishing, through the FCC, a rotor blade pitch angle for one or more of a plurality of rotor blades that counteracts external forces acting upon the rotary wing aircraft.

2017029, Oct 19, 2017

Sep 21, 2015

15/513726

- Stratford CT, US
Matthew A. White - Milford CT, US
Kenneth S. Wittmer - Sandy Hook CT, US

Sikorsky Aircraft Corporation - Stratford CT

B64C 27/57
B64C 27/605
B64C 27/10

A system and method for counteracting a rotor moment of one or more rotors of a coaxial rotor helicopter includes receiving signals with a processor indicative of a displacement command from a controller during a flight maneuver; receiving one or more signals with the processor from a sensor indicative of an airspeed and air density for the helicopter; determining a commanded rate of acceleration for the helicopter during the flight maneuver; and adjusting with one or more control servos a cyclic pitch for the one or more rotors to counteract the rotor moment during the flight maneuver.

2017029, Oct 12, 2017

Sep 29, 2015

15/501095

- Stratford CT, US
Matthew A. White - Milford CT, US
Matthew T. Luszcz - Hamden CT, US

B64C 27/82
G05D 1/08
B64C 13/50
G05D 1/02
B64C 27/57
B64C 27/10

An aircraft is provided including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. A horizontal stabilizer with a left elevator and right elevator positioned at the extending tail. A flight control computer to independently control one or more of the main rotor assembly and the elevator through a fly-by-wire control system. The flight control computer is configured to mix a collective pitch of the main rotor assembly and a deflection of the elevator.

2017024, Aug 24, 2017

Jan 9, 2017

15/401644

- Stratford CT, US
Matthew A. White - Milford CT, US
Matthew T. Luszcz - Hamden CT, US

B64D 45/00
B64C 13/04
B64D 31/04

An aircraft is provided and includes an airframe defining a cockpit with first and second control stations configured for co-activation and complementary deactivation, flight control assemblies disposed at multiple locations of the airframe and a flight control computer (FCC). The FCC is configured to control operations of the flight control assemblies in accordance with current flight conditions and commands received at activated ones of the first and second control stations that are inputted by a flight crew. The FCC includes a secondary monitoring system to identify when commands are input at a deactivated one of the first and second control stations, to determine whether the commands are indicative of normal and intentional piloting inputs and to generate control station cues in an event the commands are indicative of normal and intentional piloting inputs to alert the flight crew of a hazardous condition or automatically turn the station back on.

2017023, Aug 17, 2017

Sep 30, 2015

15/504525

- Stratford CT, US
Matthew A. White - Milford CT, US
David H. Hunter - Cheshire CT, US

B64C 27/57
B64C 27/51
B64C 27/82
B64C 27/14
B64C 27/10

An aircraft is provide including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. At least one flight control computer configured to independently control the upper rotor assembly and the lower rotor assembly through a fly-by-wire control system. A plurality of sensors to detect sensor data of at least one environmental condition and at least one aircraft state data, wherein the sensors provide the sensor data to the flight control computer.