Colton J Gilliland

20210253233, Aug 19, 2021

Feb 18, 2020

16/792997

- Fort Worth TX, US
Colton Gilliland - Northlake TX, US

Bell Textron Inc. - Fort Worth TX

B64C 29/00
B64C 11/28

Embodiments are directed to a selectable drive system that allows a rotor gearbox to send torque to a proprotor assembly and/or through a multiplier planetary gear set to a pylon-mounted ducted fan thrust unit. The rotor drive system may be a stop-fold system in which rotor blades can be folded when not rotating. This allows a normally idle lift engine to provide additional aircraft thrust during cruise where an aircraft is typically using only a dedicated thrust engine for high speed flight. An inline engage/disengage actuator or “shift fork” on the rotor gearbox is used to select the torque-output direction. The multiplier planetary gear set increases the output RPM that is received from the rotor gearbox and that is applied to the thrust fan unit.

20200172260, Jun 4, 2020

Dec 3, 2018

16/208048

- Fort Worth TX, US
Tyson Henry - Arlington TX, US
Colton Gilliland - Northlake TX, US

B64D 35/00
B64C 29/00
F16H 57/032
F16H 57/04

Briefly, the disclosure relates to apparatuses and methods to form a gearbox enclosure comprising an external liner, an internal liner, and a variable porosity region disposed between the external liner and the internal liner. The variable porosity region may be configured to accommodate flow of the lubricant, thereby providing a capability to cool, for example, a lubricating fluid at an elevated temperature.

20200166119, May 28, 2020

Nov 27, 2018

16/201748

- Forth Worth TX, US
Colton Gilliland - Northlake TX, US

F16H 57/04

Various implementations described herein are directed to an emergency lubrication system for a tiltrotor aircraft. The emergency lubrication system includes a pressurized material chamber, a lubrication chamber, a first valve between the pressurized material chamber and the lubrication chamber, a gearbox, and a second valve between the lubrication chamber and the gearbox. The first valve is configured to operate in a first mode when the emergency lubrication system is in a first configuration and a second mode when the emergency lubrication system is in a second configuration.

20190277392, Sep 12, 2019

Mar 8, 2018

15/915699

- Fort Worth TX, US
Colton Gilliland - Northlake TX, US

Bell Helicopter Textron Inc. - Fort Worth TX

F16H 57/022
B64D 35/00

A cam-locking system for use with a retractable driveshaft that includes a housing, a cam carrier located at least partially the housing, and a cam rotatably coupled to the cam carrier. Translation of the cam carrier along a central axis allows the cam to rotate into cooperative engagement with a catch recess on an interior surface of the housing, preventing the cam carrier from translating backwards, and thereby maintaining the retractable driveshaft in an engaged position. Further advancement of the cam carrier allows that cam to rotate into and unlocking gap in the interior surface of the housing, which enables the cam carrier to translate backwards along the central axis below the locked position, thereby disengaging the retractable driveshaft.

20190257425, Aug 22, 2019

Feb 17, 2018

15/898541

- Fort Worth TX, US
Colton Gilliland - Northlake TX, US

Bell Helicopter Textron Inc. - Fort Worth TX

F16J 15/04
B64C 3/56

Systems and methods include providing an aircraft with a fuselage and a wing assembly rotatable relative to the fuselage about a stow axis between a flight position and a stowed position. The aircraft includes a drive component having a retractable driveshaft that selectively engages the mid-wing gearbox via axially translatable motion along a rotation axis when the wing assembly is in the flight position. The mid-wing gearbox is misaligned with the retractable driveshaft when the wing assembly is in the stowed position. A seal is coupled to the drive component at a first end and the mid-wing gearbox at a second end and deploys in order to maintain a sealed connection between the drive component and the mid-wing gearbox when the wing assembly is transitioned between the flight position and the stowed position.