GROEN BROTHERS AVIATION, INC Patent applications |
Patent application number | Title | Published |
20150142219 | LOW SPEED AUTOGYRO YAW CONTROL APPARATUS AND METHOD - Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion device, such as an air jet or a fan may be used. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use. Apparatus for generating horizontal lift imbalance induced a tail boom positioned within the downwash of a rotor may also be used, including compressed air vents or lateral or trailing edge flaps. | 05-21-2015 |
20130168491 | MISSION-ADAPTIVE ROTOR BLADE WITH CIRCULATION CONTROL - A rotorcraft may include an airframe and a rotor connected to the airframe. The rotor may include a plurality of blades defining ducts along the length thereof and vents in fluid communication with the ducts. Flow from through the vents may be controlled by valves with piezoelectric actuators. The valves may be adjusted to achieve a lift profile suited for an operational mode such as vertical, autorotative, or unloaded flight. The lift profile may vary along the length of the blade and may vary cyclically with rotation of the blade. The lift profile may be chosen to approximate a figure of merit for the rotor suitable for a given operational mode. | 07-04-2013 |
20130037653 | ROTORCRAFT EMPENNAGE MOUNTING SYSTEM - An aircraft is disclosed having an engine and a propeller mounted to a fuselage. An empennage mounts to the aircraft and includes first and second horizontal stabilizers separated by a distance greater than the diameter of a stream tube of the propeller at the horizontal stabilizers. A rudder extends between the horizontal stabilizers and is positioned within the stream tube of the propeller. A bulkhead is positioned rearwardly from the cockpit and oriented perpendicular to a longitudinal axis of the airframe. A tailboom and engine are mounted to the airframe by means of the bulkhead having the engine mounted between the tailboom and a lower edge of the bulkhead. Landing gear may mount to the bulkhead proximate a lower edge thereof. | 02-14-2013 |
20130037652 | ROTORCRAFT, DYNAMIC, CG MANAGEMENT APPARATUS AND METHOD - An aircraft is disclosed having an engine and a propeller mounted to a fuselage. An empennage mounts to the aircraft and includes first and second horizontal stabilizers separated by a distance greater than the diameter of a stream tube of the propeller at the horizontal stabilizers. A rudder extends between the horizontal stabilizers and is positioned within the stream tube of the propeller. A bulkhead is positioned rearward from the cockpit and oriented perpendicular to a longitudinal axis of the airframe. A tailboom and engine are mounted to the airframe by means of the bulkhead having the engine mounted between the tailboom and a lower edge of the bulkhead. Landing gear may mount to the bulkhead proximate a lower edge thereof. Systems and methods redistribute fuel among laterally, vertically, and longitudinally opposed fuel tanks to maintain a center of gravity in a dynamically stable position. | 02-14-2013 |
20120312915 | LOW SPEED AUTOGYRO YAW CONTROL APPARATUS AND METHOD - Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion device, such as an air jet or a fan may be used. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use. Apparatus for generating horizontal lift imbalance induced a tail boom positioned within the downwash of a rotor may also be used, including compressed air vents or lateral or trailing edge flaps. | 12-13-2012 |
20120199692 | REACTIVE DRIVE ROTOR HEAD WITH EXTERNAL SWASHPLATE - A rotorcraft is disclosed. The rotorcraft may include an airframe comprising a mast defining an interior cavity, at least one compressor connected to the airframe, and a rotor. The rotor may include a hub and a rotor blade. The hub may connect to the mast to rotate with respect thereto. The hub may also define an interior cavity. The rotor blade may form a radial conduit extending radially therewithin. A flow of compressed air generated by the at least one compressor may pass from the at least one compressor, through the interior cavity defined by the mast, through the interior cavity defined by the hub, and into the radial conduit. A swashplate assembly controlling pitch of the rotor blade may be located exterior to the hub and mast. Accordingly, the swashplate assembly may not be heated by the flow of compressed air. | 08-09-2012 |
20120175461 | ROTOR HUB AND BLADE ROOT FAIRING APPARATUS AND METHOD - A fairing system may be assembled about a rotor of a rotorcraft to present an aerodynamically quasi-static region that rotates in an airstream, as well as certain extensions that sweep through the airstream as the rotor hub passes through the air. A spherical interface between the extensions on the rotor hub fairing and the base or root portion of each blade fairing provides three degrees of freedom permitting lead-lag, flapping, and blade pitch pivoting in the blade, while still maintaining an aerodynamic profile that will minimize drag. | 07-12-2012 |
20120156050 | DETACHABLE ROTOR BLADE FAIRING APPARATUS AND METHOD - A rotor blade having a detachable fairing is disclosed. The rotor blade includes leading and trailing edge fairings secured to the blade spar and one or more control lines extending between of the fairings and the blade spar. A detachable fairing extends from one or both of the leading and trailing edge fairings toward one of the distal and proximal ends of the blade spar. The detachable fairing and blade spar form an airfoil contour. The detachable fairing may secure to a tip jet attachment fitting at a distal end of the blade spar. A mounting structure including upper and lower plates may secure near a proximal end of the blade spar and the detachable fairing may secure to both the upper and lower plates to form all or part of an airfoil contour. The mounting structure may include a spherical seat engaging a spherical surface of a hub shroud. | 06-21-2012 |
20120153073 | MISSION-ADAPTIVE ROTOR BLADE - A rotorcraft may include an airframe and a rotor connected to the airframe. The rotor may include a hub and a rotor blade connected to the hub to extend radially away therefrom. The rotor blade may include biasing fibers, oriented to increase the twist of the rotor blade in response to an increase in the speed of rotation of the rotor corresponding to a mission, task, or maneuver. | 06-21-2012 |
20120111997 | ROTORCRAFT EMPENNAGE - An aircraft is disclosed having an engine and a propeller mounted to a fuselage. An empennage mounts to the aircraft and includes first and second horizontal stabilizers separated by a distance greater than the diameter of a stream tube of the propeller at the horizontal stabilizers. A rudder extends between the horizontal stabilizers and is positioned within the stream tube of the propeller. The rudder may mount to a first vertical stabilizer extending between the horizontal stabilizers. The horizontal stabilizers may be secured to second and third vertical stabilizers to form a duct having the rudder positioned within the duct. Additional rudders may mount to the second and third vertical stabilizers. | 05-10-2012 |
20120104157 | ROTOR DRIVEN AUXILIARY POWER APPARATUS AND METHOD - Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion provides a yaw moment at low speeds. The yaw propulsion device may be an air jet or a fan. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. The fan may be driven by hydraulic power. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use. | 05-03-2012 |
20120104156 | USE OF AUXILIARY RUDDERS FOR YAW CONTROL AT LOW SPEED - Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion provides a yaw moment at low speeds. The yaw propulsion device may be an air jet or a fan. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. The fan may be driven by hydraulic power. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use. | 05-03-2012 |
20120104155 | TAIL JET APPARATUS AND METHOD FOR LOW SPEED YAW CONTROL OF A ROTORCRAFT - Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion provides a yaw moment at low speeds. The yaw propulsion device may be an air jet or a fan. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. The fan may be driven by hydraulic power. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use. | 05-03-2012 |
20120104154 | TAIL FAN APPARATUS AND METHODS FOR LOW SPEED YAW CONTROL OF A ROTORCRAFT - Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion provides a yaw moment at low speeds. The yaw propulsion device may be an air jet or a fan. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. The fan may be driven by hydraulic power. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use. | 05-03-2012 |
20120104153 | GYROPLANE PREROTATION BY COMPRESSED AIR - A rotorcraft is disclosed. The rotorcraft may include a rotor having at least one tip nozzle, a compressor having an outlet for compressed air, and a network of conduits connecting the outlet of the compressor with the tip nozzle. In operation, the compressor may deliver a flow of compressed air to the tip nozzle. As the flow of compressed air exits the at least one tip nozzle, it may cause rotation of the rotor. This rotation may prerotate the rotor and shorten the take off distance required by the rotorcraft. Take off of the rotorcraft may be accomplished without ever adding fuel to the flow of compressed air to the tip nozzle. | 05-03-2012 |