Abstract: A transaxle system for a golf car, wherein the system comprises a transaxle and a matting interface. The transaxle comprises a plurality of mounting flanges fixedly mountable to at least one axle tube of the golf car, wherein the at least one axle tube houses at least one wheel axle, and the transaxle is operably couplable to the at least one wheel axle. The transaxle additionally comprising a transaxle mounting collar that is fixedly mounted to or integrally formed with a housing of the transaxle. The mating interface is mountable to the transaxle mounting collar, and is structured and operable to have an integrated internal combustion engine-transmission unit of the golf car mounted thereto.
Type:
Grant
Filed:
May 14, 2019
Date of Patent:
January 12, 2021
Assignee:
Textron Inc.
Inventors:
Zekarias W. Yohannes, Matthew Wilson, David A. Smith, Chris L. Normand
Abstract: An all-terrain vehicle is provided comprising a chassis, four wheels and a passenger compartment that includes a passenger seating structure. The vehicle additionally comprises a drivetrain operatively connected to at least one of the wheels comprising at least one drive shaft and at least one torque transfer device. Furthermore the vehicle includes a prime mover that is mounted to the chassis entirely forward of a front edge of the seating structure and operatively connected to the drivetrain. The prime mover is structured and operable to provide motive force to at least one of the wheels.
Type:
Grant
Filed:
February 4, 2020
Date of Patent:
January 12, 2021
Assignee:
Textron Inc.
Inventors:
John C. Dunne, Jr., Jon C. Charland, Jared Trauernicht, Hayden Barr, Eric Anderfaas
Abstract: A vibration control system for a rotor hub provides vibration attenuation in an aircraft by reducing the magnitude of rotor induced vibratory. The system can include a force generating device attached to a rotor hub which rotates along with the rotor at the rotational speed of the rotor. Vibratory shear force is generated by rotating unbalanced weights each about an axis non-concentric with the rotor hub axis at high speed to create large centrifugal forces. The rotational speed of the weights can be a multiple of the rotor rotational speed to create shear forces for canceling rotor induced vibrations. The amplitude of the generated shear force is controlled by indexing the positions of the unbalanced weights relative to each other, while the phase of the shear force is adjusted by equally phasing each weight relative to the rotor.
Type:
Application
Filed:
September 21, 2020
Publication date:
January 7, 2021
Applicant:
Bell Textron Inc.
Inventors:
David E. Heverly, II, Jeremy DeWaters, Frank B. Stamps
Abstract: A pitot-static array system for a tail-sitting aircraft has a disk with a plurality of edge ports arrayed about an edge of the disk. Each of a plurality of pressure transducers is configured to measure air pressure at one of the edge ports. The edge ports are arrayed about an axis parallel to a pitch axis of the aircraft.
Type:
Grant
Filed:
May 1, 2019
Date of Patent:
January 5, 2021
Assignee:
Bell Textron Inc.
Inventors:
Andrew Vincent Louis, Daniel Bryan Robertson, Matthew Edward Louis
Abstract: Embodiments are directed to systems and methods for a sliding door in a pressurized aircraft. In one embodiment, an aircraft comprises a fuselage having a door opening, and a door configured to slide into the door opening from within the fuselage, the door held in a closed position in the door opening by excess air pressure within the fuselage during operation of the aircraft.
Type:
Grant
Filed:
April 12, 2018
Date of Patent:
January 5, 2021
Assignee:
Bell Textron Inc.
Inventors:
Jeremy Robert Chavez, Brent Chadwick Ross
Abstract: An auxiliary storage compartment for a golf car, wherein the auxiliary storage compartment comprises a storage receptacle disposed on a rear deck of a body of a golf car behind and accessible from a seating structure of the golf car. In various instances, the storage receptacle comprising at least one sidewall that defines an interior storage space of the storage receptacle.
Abstract: A rotor blade control system and methods therefor including a hub assembly pivotally attached to a rotor blade; a mast attached to the hub assembly; a swashplate assembly engaged with the mast and including a swashplate actuation mechanism pivotally coupled with the non-rotating ring at a plurality of coupling locations for moving the non-rotating ring and pivotally coupled with the base at a plurality of base locations, the swashplate actuation mechanism comprises a plurality of substantially triangular dual actuator assemblies that are independently and concurrently operable to move the respective coupling location so as to impart movement on the non-rotating ring. The swashplate actuation mechanism is configured to move the swashplate assembly about a longitudinal axis and a lateral axis in response to a cyclic input. The swashplate actuation mechanism is configured to move the swashplate assembly along the mast in response to a collective input.
Type:
Application
Filed:
June 26, 2019
Publication date:
December 31, 2020
Applicant:
Bell Helicopter Textron Inc.
Inventors:
Robert P. Reynolds, Glenn A. Shimek, Brady G. Atkins, William D. Girard
Abstract: In one embodiment of the present disclosure, there is provided an aircraft that includes a cowling having a j-track mounted on the inwardly facing surface and a rod pivotally connected to a stationary part of the aircraft at a first end and moveable within the j-track at a second end, so that, when the cowling is opened, the second end moves to lock into the j-shaped portion and hold the cowling open. In various embodiments, the first end may be pivotally connected to the aircraft by a quick release pin, and the second end may be connected to the j-track by a torsion spring. In another embodiment of the present disclosure, the cowling is a bi-folding cowl having an upper portion and a lower portion, where the rod and the lower portion may include structures for retaining the lower portion in an opened position.
Abstract: An aircraft, including a fixed nacelle disposed on a wing of the aircraft, the fixed nacelle including a nacelle opening; a proprotor pylon disposed on the wing and rotatable relative to the fixed nacelle between a substantially horizontal position and a non-horizontal position, wherein rotation of the proprotor pylon to a non-horizontal position exposes the nacelle opening; and a movable cover disposed on at least one of the wing and fixed nacelle, said movable cover including a plurality of cover members that are movable between a closed position where at least a portion of the cover members collectively form a protective cover in front of the nacelle opening when the proprotor pylon is positioned in the non-horizontal position and a stowed position where at least a portion of the plurality of cover members are stowed. In other aspects, there is provide a method of covering a nacelle opening.
Abstract: In one embodiment of the present disclosure, there is provided an aircraft having a bi-folding cowl for providing full access to equipment without completely removing the cowl. The bi-folding cowl has an upper portion and a lower portion mechanically connected along the adjacent edges, where the upper and lower portions fold so that the inner surfaces face each other when opened. In another embodiment, the bi-folding cowl has at least three maintenance positions, including partially-opened, fully-opened, and fully-opened, lying flat on the surface of the aircraft.
Abstract: An aspect provides a skid landing gear assembly including a cross member disposed between a first skid tube and a second skid tube, and a tension cable member configured to be disposed in the cross member; wherein the tension cable member resists outward deflection of at least a portion of the skid landing gear assembly when a downward load is applied to the skid landing gear assembly. In other aspects, there are methods of avoiding ground resonance in a skid landing gear assembly, methods of assembling a skid landing gear assembly, methods of operating a helicopter with a skid landing gear assembly, and methods of improving the service life of a skid landing gear assembly.
Abstract: An aircraft that is convertible between a helicopter mode and an airplane mode. The aircraft includes a fuselage with a longitudinal axis and a vertical axis and distributed propulsion array that surrounds the vertical axis when the aircraft is operating the helicopter mode and surrounds the longitudinal axis when the aircraft is operating in the airplane mode.
Type:
Application
Filed:
June 18, 2019
Publication date:
December 24, 2020
Applicant:
Bell Helicopter Textron Inc.
Inventors:
Carlos Alexander Fenny, Nicholas Brodeur, Rohn Lee Olson, Kevin Morris
Abstract: A rotorcraft includes a main rotor system coupled to a mast and a rotor assembly. The rotor assembly includes a yoke comprising a rotor coupling, a first damper mount attached to the rotor coupling, a rotor extension configured to couple to the rotor coupling and comprising a second damper mount, a damper coupled to the first and second damper mounts, and a fairing enclosing the damper and the yoke.
Type:
Application
Filed:
June 20, 2019
Publication date:
December 24, 2020
Applicant:
Bell Textron Inc.
Inventors:
Glenn Alan SHIMEK, Jared Mark PAULSON, Tom DONOVAN, Michael Christopher BURNETT
Abstract: A component alignment system for an aircraft includes a first component having a first surface including first shaped projections that repeat in at least two directions along the first surface. The component alignment system also includes a second component having a second surface including second shaped projections that repeat in at least two directions along the second surface. The first shaped projections are complementary to the second shaped projections such that the first surface is translationally and rotationally constrained relative to the second surface when the first and second shaped projections are in an interlocked position.
Abstract: A method of repairing a composite structure includes providing an assembled composite structure comprising a substantially rigid outer component, wherein the composite structure comprises a void space at least partially bounded by the outer component. The method further includes forming an injection hole through the outer component to provide a path between the void space and space external to the composite structure. The method further includes injecting foam into the void space through the injection hole while the foam is in a substantially unexpanded state and expanding the foam within the void space.
Type:
Application
Filed:
June 24, 2019
Publication date:
December 24, 2020
Applicant:
Bell Helicopter Textron Inc.
Inventors:
Suvankar Mishra, Vance Newton Cribb, III
Abstract: A mount system for tiltably supporting a pylon assembly of a rotorcraft. First, second, third and fourth pylon links are each coupled between the pylon assembly and the airframe of the rotorcraft. The first pylon link has a first axis, the second pylon link has a second axis, the third pylon link has a third axis and the fourth pylon link has a fourth axis. Each of the axes intersects at a focal point located proximate a coaxial rotor system having counter-rotating upper and lower rotor assemblies such that the focal point provides a virtual pivot point about which the pylon assembly tilts to generate a control moment about a center of gravity of the rotorcraft that counteracts lateral and fore/aft moments generated by the upper and lower rotor assemblies during rotorcraft maneuvers.
Type:
Application
Filed:
December 17, 2019
Publication date:
December 24, 2020
Applicant:
Bell Textron Inc.
Inventors:
Frank Bradley Stamps, Michael Reaugh Smith, Michael Scott Seifert