Matthew F Hendricks

US Patent:

20130270415, Oct 17, 2013

Filed:

Jan 8, 2013

Appl. No.:

13/736687

Inventors:

BELL HELICOPTER TEXTRON INC. - , US
Matthew W. Hendricks - Bedford TX, US
Maurice Griffin - Euless TX, US
Michael R. Smith - Colleyville TX, US

Assignee:

BELL HELICOPTER TEXTRON INC. - FORT WORTH TX

International Classification:

F16F 7/00

US Classification:

248638

Abstract:

The vibration suppression system includes a vibration isolator located in each corner in a four corner pylon mount structural assembly. The combination of four vibration isolators, two being forward of the transmission, and two being aft of the transmission, collectively are effective at isolating main rotor vertical shear, pitch moment, as well as roll moment induced vibrations. Each opposing pair of vibration isolators can efficiently react against the moment oscillations because the moment can be decomposed into two antagonistic vertical oscillations at each vibration isolator. A pylon structure extends between a pair of vibration isolators thereby allowing the vibration isolators to be spaced a away from a vibrating body to provide increased control.

US Patent:

20200140074, May 7, 2020

Filed:

Nov 6, 2018

Appl. No.:

16/181694

Inventors:

- Providence RI, US
Matthew Hendricks - Grand Prairie TX, US

International Classification:

B64C 27/51
B64C 27/00
B64C 27/08
G06F 17/14
G06F 17/16

Abstract:

A for providing control input adjustment for an aircraft, including one or more mode sensors disposed on an aircraft, a mode analysis system, the mode analysis system operable to receive mode sensor data from the one or more mode sensors, and operable to decompose the mode sensor data into decomposed mode data associated with fundamental modes of structural elements of the aircraft associated with the one or more mode sensors, and a flight control computer (FCC) disposed on the aircraft and connected to one or more actuators, the FCC operable to provide a control signal to the one or more actuators according to an association between the decomposed mode data and one or more rotorcraft parameters associated with the one or more actuators.

US Patent:

20180329430, Nov 15, 2018

Filed:

May 12, 2017

Appl. No.:

15/594393

Inventors:

- Fort Worth TX, US
Jillian Samantha Alfred - Ft. Worth TX, US
Sung Kyun Kim - Bedford TX, US
Marko Vuga - Arlington TX, US
Matthew Hendricks - Grand Prairie TX, US
Mark Wasikowski - Keller TX, US
Thomas Parham - Colleyville TX, US
Michael Reaugh Smith - Colleyville TX, US

International Classification:

G05D 1/08
B64C 27/82
B64C 27/04
B64C 27/57

Abstract:

In accordance with an embodiment of the present invention, a method of operating a rotorcraft includes receiving a measured yaw rate from a yaw rate sensor or a measured lateral acceleration from a lateral acceleration sensor of the rotorcraft, filtering the measured yaw rate or the measured lateral acceleration using a filter to form a filtered measured yaw rate or a filtered measured lateral acceleration, and regulating a yaw rate or a lateral acceleration of the rotorcraft based on the measured yaw rate or the measured lateral acceleration. The filter includes a bandpass characteristic or a notch characteristic, and the filtering is configured to reduce lateral vibrations caused by airflow in a tail section of the rotorcraft

US Patent:

20180038439, Feb 8, 2018

Filed:

Oct 3, 2017

Appl. No.:

15/723510

Inventors:

- Fort Worth TX, US
Matthew W. Hendricks - Bedford TX, US
Maurice Griffin - Euless TX, US
Michael R. Smith - Colleyville TX, US

Assignee:

BELL HELICOPTER TEXTRON INC. - Fort Worth TX

International Classification:

F16F 7/00
B64C 27/00
F16F 13/24

Abstract:

The vibration suppression system includes a vibration isolator located in each corner in a four corner pylon mount structural assembly. The combination of four vibration isolators, two being forward of the transmission, and two being aft of the transmission, collectively are effective at isolating main rotor vertical shear, pitch moment, as well as roll moment induced vibrations. Each opposing pair of vibration isolators can efficiently react against the moment oscillations because the moment can be decomposed into two antagonistic vertical oscillations at each vibration isolator. A pylon structure extends between a pair of vibration isolators thereby allowing the vibration isolators to be spaced a away from a vibrating body to provide increased control.

US Patent:

20150136900, May 21, 2015

Filed:

Nov 21, 2013

Appl. No.:

14/086372

Inventors:

- Fort Worth TX, US
Matthew W. Hendricks - Grand Prairie TX, US

Assignee:

BELL HELICOPTER TEXTRON INC. - Fort Worth TX

International Classification:

B64D 27/26
B64D 35/00

US Classification:

244 54

Abstract:

A mount system for supporting a transmission in an aircraft can include a first link coupled between a structure of the aircraft and the transmission, the first link having a first axis; a second link coupled between the structure of the aircraft and the transmission, the second link having second axis; a third link coupled between the structure of the aircraft and the transmission, the third link having a third axis; and a fourth link coupled between the structure of the aircraft and the transmission, the fourth link having fourth axis. A forward focal point of the first axis and the second axis has a different waterline component compared to an aft focal point of the third axis and the fourth axis.