Daniel Robertson

US Patent:

20190061925, Feb 28, 2019

Filed:

Aug 28, 2017

Appl. No.:

15/688165

Inventors:

- Fort Worth TX, US
Daniel Bryan Robertson - Fort Worth TX, US
Brett Rodney Zimmerman - Fort Worth TX, US

Assignee:

Bell Helicopter Textron Inc. - Fort Worth TX

International Classification:

B64C 27/20
B64C 39/00
B64C 11/00
B64D 27/02
B64C 39/02

Abstract:

A cargo transportation system includes a cargo platform having an upper surface and a perimeter. A propulsion system is disposed about the perimeter of the cargo platform. The propulsion system includes a plurality of propulsion assemblies, each including a propulsion unit disposed within a housing defining an airflow channel having an air inlet for incoming air and an air outlet for outgoing air such that the outgoing air is operable to generate at least vertical lift. A power system disposed within the cargo platform provides energy to drive the propulsion system. A flight control system operably associated with the propulsion system and the power system controls flight operations of the cargo transportation system.

US Patent:

20190055016, Feb 21, 2019

Filed:

Aug 18, 2017

Appl. No.:

15/680501

Inventors:

- Fort Worth TX, US
Daniel Bryan Robertson - Fort Worth TX, US

Assignee:

Bell Helicopter Textron Inc. - Fort Worth TX

International Classification:

B64C 39/02
B64C 27/18
B64C 27/82
B64C 27/02
B64D 47/08

Abstract:

An unmanned aircraft system has a vertical takeoff and landing flight mode and a forward flight mode. The unmanned aircraft system includes an airframe, a rotor assembly rotatably coupled to the airframe and a propeller rotatably coupled to the airframe. The rotor assembly including at least two rotor blades having tip jets that are operably associated with a compressed gas power system. The propeller is operably associated with an electric power system. In the vertical takeoff and landing flight mode, compressed gas from the compressed gas power system is discharged through the tip jets to rotate the rotor assembly and generate vertical lift. In the forward flight mode, the electric power system drives the propeller to generate forward thrust and autorotation of the rotor assembly generates vertical lift.

US Patent:

20190031333, Jan 31, 2019

Filed:

Jul 27, 2017

Appl. No.:

15/662257

Inventors:

- Fort Worth TX, US
Daniel Bryan Robertson - Fort Worth TX, US

Assignee:

Bell Helicopter Textron Inc. - Fort Worth TX

International Classification:

B64C 29/00
B64D 27/24
B64C 39/08

Abstract:

An aircraft having a vertical takeoff and landing flight mode and a forward flight mode. The aircraft includes a fuselage and a dual tiltwing assembly having a vertical lift orientation and a forward thrust orientation relative to the fuselage. The dual tiltwing assembly includes a forward wing and an aft wing coupled together and to the fuselage by a quadrilateral linkage. A distributed propulsion system is coupled to the dual tiltwing assembly and includes a plurality of forward propulsion assemblies coupled to the forward wing and a plurality of aft propulsion assemblies coupled to the aft wing. A flight control system is operably associated with the distributed propulsion system and the dual tiltwing assembly. The flight control system is operable to independently control each of the propulsion assemblies and is operable to transition the dual tiltwing assembly between the vertical lift orientation and the forward thrust orientation.

US Patent:

20180354615, Dec 13, 2018

Filed:

Jun 12, 2017

Appl. No.:

15/619765

Inventors:

- Fort Worth TX, US
Daniel Bryan Robertson - Fort Worth TX, US

Assignee:

Bell Helicopter Textron Inc. - Fort Worth TX

International Classification:

B64C 29/00
B64C 39/08
B64D 27/24
B64C 15/12

Abstract:

An aircraft having a vertical takeoff and landing fight mode and a forward flight mode. The aircraft includes a fuselage and an X-tiltwing that is rotatable relative to the fuselage between a vertical lift orientation and a forward thrust orientation. The X-tiltwing has oppositely disposed V-wing members each having first and second wing sections. In the vertical lift orientation, the first and second wing sections of each V-wing member are generally in the same horizontal plane. In the forward thrust orientation, the first and second wing sections of each V-wing member are generally in the same vertical plane. A distributed propulsion system is attached to the X-tiltwing such that a plurality of propulsion assemblies is attached to each wing section. A flight control system is operably associated with the distributed propulsion system to independently control each of the propulsion assemblies.

US Patent:

20180354619, Dec 13, 2018

Filed:

Jun 12, 2017

Appl. No.:

15/620310

Inventors:

- Fort Worth TX, US
Danielle Lynn Moore - Fort Worth TX, US
Andrea Chavez - Colleyville TX, US
Kirk Landon Groninga - Keller TX, US
John Lloyd - Arlington TX, US
Daniel Bryan Robertson - Southlake TX, US

Assignee:

Bell Helicopter Textron Inc. - Fort Worth TX

International Classification:

B64C 39/02
B64C 29/02

Abstract:

An Unmanned Aerial Vehicle (UAV) has a fuselage, a rotor system, and a wing configured for selective positioning during flight of the UAV to a fully deployed position, a fully stowed position, and to positions between the fully deployed position and the fully stowed position.

US Patent:

20180273167, Sep 27, 2018

Filed:

Mar 23, 2017

Appl. No.:

15/468069

Inventors:

- Fort Worth TX, US
Matthew E. Louis - Fort Worth TX, US
Kirk L. Groninga - Keller TX, US
Daniel B. Robertson - Southlake TX, US
Frank B. Stamps - Colleyville TX, US
Albert G. Brand - N. Richland Hills TX, US
Eric A. Sinusas - Euless TX, US

International Classification:

B64C 27/82
F04D 17/16
F04D 29/46

Abstract:

In one embodiment, a rotorcraft comprises a fuselage, a tail boom, a rotor system, and a centrifugal blower system. The centrifugal blower system comprises a centrifugal blower configured to generate thrust using an airflow, wherein the centrifugal blower is located within the tail boom. The centrifugal blower system also comprises a plurality of ducts configured to control the thrust generated by the centrifugal blower, wherein the plurality of ducts is located on a portion of the tail boom surrounding the centrifugal blower, and wherein the plurality of ducts comprises one or more adjustable ducts configured to vary a size of an associated duct opening.

US Patent:

20180237136, Aug 23, 2018

Filed:

Feb 22, 2017

Appl. No.:

15/438972

Inventors:

- Fort Worth TX, US
Daniel Bryan Robertson - Fort Worth TX, US
Kirk Landon Groninga - Fort Worth TX, US
Frank Bradley Stamps - Fort Worth TX, US
Matthew Edward Louis - Fort Worth TX, US

Assignee:

Bell Helicopter Textron Inc. - Fort Worth TX

International Classification:

B64C 39/00
B64C 3/32
B64C 3/14
B64D 27/12
B64D 27/26
B64C 29/00
B64C 27/26
B64C 27/28
B64C 27/52

Abstract:

A tiltrotor aircraft has a fuselage and a wing having upper and lower surfaces with a plurality of channels extending therebetween, each with a cycloidal rotor mounted therein. At least two pylon assemblies are rotatably coupled to the wing to selectively operate the tiltrotor aircraft between helicopter and airplane flight modes. Each pylon assembly includes a mast and a proprotor assembly operable to rotate with the mast to generate thrust. At least one engine provides torque and rotational energy to the proprotor assemblies and the propulsion assemblies. Each of the cycloidal rotors has a plurality of blades that travels in a generally circular path and has a plurality of pitch angle configurations such that each cycloidal rotor is operable to generate a variable thrust and a variable thrust vector, thereby providing vertical lift augmentation, roll control, yaw control and/or pitch control in the helicopter flight mode.

US Patent:

20180057157, Mar 1, 2018

Filed:

Aug 31, 2016

Appl. No.:

15/252916

Inventors:

- Fort Worth TX, US
Daniel Bryan Robertson - Fort Worth TX, US

Assignee:

Bell Helicopter Textron Inc. - Fort Worth TX

International Classification:

B64C 27/82
B64C 29/00

Abstract:

In some embodiments, an aircraft includes a fuselage having a forward portion and an aft portion. First and second ducted fans are supported by the forward portion of the fuselage. The first and second ducted fans are tiltable relative to the fuselage between a generally horizontal orientation, in a vertical takeoff and landing mode, and a generally vertical orientation, in a forward flight mode. A tailboom having an aft station extends from the aft portion of the fuselage. A cross-flow fan is disposed in the aft station of the tailboom and is operable to generate a pitch control moment.