With Safety Lowering Device Patents (Class 244/17.15)
  • Patent number: 10464671
    Abstract: A personal flight vehicle including a platform base assembly that provides a surface upon which the feet of an otherwise free-standing person are positionable, and including a plurality of axial flow propulsion systems positioned about a periphery of the platform base assembly. The propulsion systems generate a thrust flow in a direction substantially perpendicular to the surface of the platform base assembly, where the thrust flow is unobstructed by the platform base assembly. The thrust flow has a sufficient intensity to provide vertical takeoff and landing, flight, hovering and locomotion maneuvers. The vehicle allows the pilot to control the spatial orientation of the platform base assembly by the movement, preferably direct, of at least part of his or her body, and the spatial movement of the vehicle is thus controlled.
    Type: Grant
    Filed: January 28, 2019
    Date of Patent: November 5, 2019
    Assignee: 4525612 CANADA INC.
    Inventor: Catalin Alexandru Duru
  • Patent number: 10239615
    Abstract: A personal flight vehicle including a platform base assembly that provides a surface upon which the feet of an otherwise free-standing person are positionable, and including a plurality of axial flow propulsion systems positioned about a periphery of the platform base assembly. The propulsion systems generate a thrust flow in a direction substantially perpendicular to the surface of the platform base assembly, where the thrust flow is unobstructed by the platform base assembly. The thrust flow has a sufficient intensity to provide vertical takeoff and landing, flight, hovering and locomotion maneuvers. The vehicle allows the pilot to control the spatial orientation of the platform base assembly by the movement, preferably direct, of at least part of his or her body, and the spatial movement of the vehicle is thus controlled.
    Type: Grant
    Filed: January 6, 2015
    Date of Patent: March 26, 2019
    Assignee: 4525612 CANADA INC.
    Inventor: Catalin Alexandru Duru
  • Patent number: 10124880
    Abstract: A control surface assembly for an unmanned aerial vehicle (UAV) is disclosed. The control surface assembly has a fin configured to be rotatably coupled to a fuselage of the UAV, with a control surface member rotatably coupled to the fin. A control surface linkage is configured to be coupled between the control surface member and an actuator disposed in the fuselage. The fin is rotatable with respect to the fuselage between a stowed configuration and a deployed configuration. In the deployed configuration, the control surface linkage is configured to rotate the control surface member with respect to the fin, when the actuator actuates the control surface linkage. In the stowed configuration, however, the control surface linkage is configured to move with respect to the fin without rotating the control surface member, when the actuator actuates the control surface linkage.
    Type: Grant
    Filed: February 3, 2016
    Date of Patent: November 13, 2018
    Assignee: Lockheed Martin Corporation
    Inventors: Steven J. Ellzey, James C. Copp
  • Patent number: 9975624
    Abstract: The embodiments relate to an apparatus for controlling the angular position of propeller guards of a multicopter. The apparatus includes a chassis having at least three sides, including first and second sides meeting at a first vertex and second and third sides meeting at a second vertex. Each side is in communication with at least one propeller. At least one guard is in communication with the chassis. Each guard corresponds to a respective side, and each guard has oppositely disposed first and second terminals. The apparatus further includes a rotation mechanism in communication with the at least one guard to control an angular position of at least one guard relative to the chassis. The angular position is controlled in real time to mitigate damage with regard to an approaching or potential obstacle.
    Type: Grant
    Filed: June 7, 2016
    Date of Patent: May 22, 2018
    Inventor: William B. Harvey
  • Publication number: 20120068006
    Abstract: An autogyro plane (10) having a fuselage (12) with a cockpit with a pilot position (22), a tractor propeller (18) mounted at the front of the fuselage, a mast (14) projecting upwardly from the fuselage for supporting rotor blades (16), the pilot position being in front of the mast.
    Type: Application
    Filed: August 18, 2009
    Publication date: March 22, 2012
    Applicant: GYROJET LIMITED
    Inventor: Barry Jones
  • Patent number: 8074919
    Abstract: A parachute support system for supporting a helicopter emergency parachute is provided, comprising a parachute support shaft located within a main rotor shaft, said parachute support shaft being rotationally separated from the rest of the helicopter through the use of bearing supports or enclosures. As the parachute support shaft is connected to the main rotor shaft at multiple distinct and distant points, the system described also provides a preferable load path transfer route, such that parachute system malfunction is minimized.
    Type: Grant
    Filed: October 7, 2009
    Date of Patent: December 13, 2011
    Assignee: The Boeing Company
    Inventor: Richard L. Kulesha
  • Patent number: 8041471
    Abstract: A vertical take-off and landing aircraft that includes AC motors, which drive fans that propel the aircraft, and a control device for controlling the AC motors adaptively based on a thrust control amount from an attitude controller. In particular, the drive controller performs switching to convert DC from a power source to three-phase AC at a predetermined frequency to be supplied to the AC motors. The drive controller reduces the control frequency of the three-phase AC to be applied to the AC motor to reduce the control resolution when the flight mode is switched from a vertical flight control mode to a horizontal flight control mode, in which the control amount to correct the external forces is smaller. Therefore, it is possible to reduce the power loss in the controller and thus the power consumption compared to conventional vertical take-off and landing aircrafts, in which the control resolution is always constant.
    Type: Grant
    Filed: November 13, 2007
    Date of Patent: October 18, 2011
    Assignee: Toyota Jidosha Kabushiki Kaisha
    Inventor: Masatsugu Ishiba
  • Publication number: 20110147511
    Abstract: A helicopter includes a main rotor guided and protected in minor impacts by a guide-ring. In selected embodiments, the rotor is powered by an electric motor employing a magnetic field generator carried by the main rotor and stator coils installed on the guide-ring. The helicopter's main rotor thus effectively functions as the rotor of the electric power plant of the helicopter. In selected embodiments, the rotor's blades are arranged so as to create an opening in the center of the rotor, allowing pilot ejection or deployment of a parachute capable of safely lowering the helicopter in case of an emergency.
    Type: Application
    Filed: January 18, 2010
    Publication date: June 23, 2011
    Inventor: Alexander I. POLTORAK
  • Publication number: 20110101157
    Abstract: Disclosed is a rotary winged aircraft. More specifically, this invention relates to an aircraft wherein lift is generated by two discs which rotate about a central axis. The discs generate equal and opposite forces such that the central axis remains fixed, thereby allowing it to be used for a crew compartment. In one embodiment, the two discs are concentrically located.
    Type: Application
    Filed: July 13, 2009
    Publication date: May 5, 2011
    Inventor: Waldemar F. Kissel, JR.
  • Patent number: 7559506
    Abstract: Disclosed is a rotary winged aircraft. More specifically, this invention relates to an aircraft wherein lift is generated by two discs which rotate about a central axis. The discs generate equal and opposite forces such that the central axis remains fixed, thereby allowing it to be used for a crew compartment. In one embodiment, the two discs are concentrically located.
    Type: Grant
    Filed: September 14, 2006
    Date of Patent: July 14, 2009
    Inventor: Waldemar F. Kissel, Jr.
  • Patent number: 7546976
    Abstract: A dual power helicopter without a tail rotor. The dual power helicopter of present invention primarily uses two power devices which can be rotated in opposite directions to control the flight of the helicopter. The two power devices are rotated in the opposite directions by steering gears from a same engine, such that the engine power can be completely transmitted to the two power devices, enabling the engine power to be completely developed, thereby improving performance of the helicopter.
    Type: Grant
    Filed: September 25, 2006
    Date of Patent: June 16, 2009
    Inventor: Hong-Fu Li
  • Patent number: 7032860
    Abstract: An anti-torque thruster system implemented onboard an aircraft comprising a propulsion means coupled to the aircraft, wherein the propulsion means is capable of providing a measure of anti-torque thrust to the aircraft, a fuel storage container coupled to the propulsion means via a fuel delivery conduit, wherein the fuel storage container is capable of storing an appropriate fuel for the propulsion means, a valve means disposed between the fuel storage container and the propulsion means, wherein the valve means may be useable to regulate the flow of fuel from the fuel storage container to the propulsion means, and a controller for controlling the valve means to regulate the flow of fuel from the fuel storage container to the propulsion means, wherein the controller is capable of receiving input from at least one input device.
    Type: Grant
    Filed: November 5, 2004
    Date of Patent: April 25, 2006
    Assignee: EATTS, LLC
    Inventors: Charles T. Kirk, Virginia L. Hodder, legal representative, Grover L. Moore, deceased
  • Patent number: 6390413
    Abstract: A safety system is provided on a helicopter by mounting a parachute within a cylinder located in a hollow drive shaft of the propeller or in an external container. Four auxiliary parachutes are located in front and behind, and to the left and right of the propeller. The propeller may be locked in a predetermined angular position by a braking system of the drive shaft when the helicopter is disabled in an air accident such that the auxiliary parachutes are located in the spaces between the propeller blades for their safe deployment for suspending the helicopter in air. Speed reducing jets are provided for reducing the falling speed of the helicopter and for landing it safely on the ground. Inflatable bags are provided for maintaining the helicopter afloat when it falls on to a body of water or to cushion its landing impact on the ground.
    Type: Grant
    Filed: August 21, 2001
    Date of Patent: May 21, 2002
    Inventor: Chui-Wen Chiu
  • Patent number: 6382558
    Abstract: A safety system is provided on a helicopter by mounting a parachute within a cylinder located in a hollow drive shaft of the propeller or in an external container. Four auxiliary parachutes are located in front and behind, and to the left and right of the propeller. The propeller may be locked in a predetermined angular position by a braking system of the drive shaft when the helicopter is disabled in an air accident such that the auxiliary parachutes are located in the spaces between the propeller blades for their safe deployment for suspending the helicopter in air. Speed reducing jets are provided for reducing the falling speed of the helicopter and for landing it safely on the ground. Inflatable bags are provided for maintaining the helicopter afloat when it falls on to a body of water or to cushion its landing impact on the ground.
    Type: Grant
    Filed: June 2, 2000
    Date of Patent: May 7, 2002
    Inventor: Chui-Wen Chiu
  • Patent number: 6373521
    Abstract: The invention is of an aviation incident surveillance system which is to be carried on-board aircraft and stand ready at any time for deployment to visually record the final seconds of the downed aircraft. The system of the present invention centers on a rotocraft capsule which suspends itself approximately at an altitude at which the capsule is deployed from the distress aircraft while on-board video cameras and data recording systems record the environment surrounding the capsule which, of course, will include the aircraft from which the capsule was deployed. The capsule is provided with a self deploying, ballistic parachute system for gently landing the School upon expiration of the capsule's internal power sources for driving the rotocraft components.
    Type: Grant
    Filed: July 19, 2000
    Date of Patent: April 16, 2002
    Inventor: Kevin D. Carter
  • Patent number: 6371410
    Abstract: Inflation of impact absorbing bags is effected on a portable platform positioned on an emergency landing zone after jettisoning of damaged landing gear from a helicopter fuselage. The impact absorbing bags when inflated form a cradle shape conforming to the bottom of the helicopter fuselage.
    Type: Grant
    Filed: November 22, 2000
    Date of Patent: April 16, 2002
    Assignee: The United States of America represented by the Secretary of the Navy
    Inventors: Renee Cairo-Iocco, Thomas E. Wenzel, Eugene C. Fischer
  • Publication number: 20020030136
    Abstract: Three methods of deploying safety parachutes from a helicopter for landing it in case of an accident are shown. They solve the problem of the parachutes becoming tangled with the large propeller of a helicopter in such circumstances. Additionally, speed reduction jets are provided to reduce the falling speed of the helicopter to achieve its safe landing. Inflatable air bags are provided on both sides of its belly and inflatable tubular gaskets are provided around the door joints for sealing these joints such that when falling onto water, the helicopter would float safely to await for rescue. Inflatable air bags are also provided to reduce the impact of the helicopter upon landing on the ground.
    Type: Application
    Filed: August 21, 2001
    Publication date: March 14, 2002
    Inventor: Chui-Wen Chiu
  • Patent number: 6199799
    Abstract: A parachute device for a helicopter includes a canopy confining case having a stationary casing part, and a removable casing part mounted removably on the stationary casing part. The stationary and removable casing parts cooperatively form a compartment to receive a parachute canopy that has a release cord connected to the removable casing part, and a suspension line unit. An anchoring line has one end that extends into the canopy confining case and that is coupled to the suspension line unit of the parachute canopy. A rocket member includes a launch tube mounted on the stationary casing part externally of the compartment, and a rocket disposed in the launch tube and connected to the removable casing part. The rocket is capable of propelling from the launch tube when ignited. An ignition control line has a first end connected to the rocket member, and a second end provided with an ignition unit that is operable so as to ignite the rocket.
    Type: Grant
    Filed: September 21, 1999
    Date of Patent: March 13, 2001
    Assignee: Light's American Sportscopter Inc.
    Inventor: Hsing-Hsiung Lai
  • Patent number: RE42446
    Abstract: An anti-torque thruster system implemented onboard an aircraft comprising a propulsion means coupled to the aircraft, wherein the propulsion means is capable of providing a measure of anti-torque thrust to the aircraft, a fuel storage container coupled to the propulsion means via a fuel delivery conduit, wherein the fuel storage container is capable of storing an appropriate fuel for the propulsion means, a valve means disposed between the fuel storage container and the propulsion means, wherein the valve means may be useable to regulate the flow of fuel from the fuel storage container to the propulsion means, and a controller for controlling the valve means to regulate the flow of fuel from the fuel storage container to the propulsion means, wherein the controller is capable of receiving input from at least one input device.
    Type: Grant
    Filed: June 26, 2007
    Date of Patent: June 14, 2011
    Inventors: Charles T. Kirk, Grover L. Moore, Virginia L. Hodder, legal representative