Amphibian Patents (Class 244/101)
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Patent number: 11820499Abstract: A system includes a first frame for mounting to the aircraft; a second frame for mounting the proprotor, the second frame being rotatably mounted to the first frame; a first gear located along the rotation axis of the second frame and fixed in position relative to the first frame; a pinion that moves with the second frame and engages the first gear such that the pinion revolves around the first gear, causing the pinion to rotate; a cam that is fixedly connected to the pinion such that the cam rotates with the pinion; and a control rod operatively coupled at a first end with the cam such that rotation of the cam can cause translation of the control rod, wherein the control rod can be coupled at a second end to the blades of the proprotor such that translation of the control rod alters the pitch of the blades.Type: GrantFiled: January 18, 2023Date of Patent: November 21, 2023Assignee: Archer Aviation, Inc.Inventors: Jonathan Anthony Beno, Guy Bernard, Benjamin Scott Dyer, Nathan Daniel Storrs
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Patent number: 11498674Abstract: Disclosed is a system for an amphibious aircraft where floats on each side of the aircraft include aerodynamic structures. The structures are configured to compensate for aerodynamic imbalances (e.g., in yaw and pitch) created by the incorporation of the floats onto the aircraft.Type: GrantFiled: February 11, 2020Date of Patent: November 15, 2022Assignee: Textron Aviation Inc.Inventor: Neal Herbert Willford
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Patent number: 11338634Abstract: The present invention presents a vehicle that is capable of utilizing different methods of movement by rotating its propellers to accommodate air, ground, or water locomotion. The present invention includes being able to change the direction of the thrust mechanism, so that it creates thrust in the direction of flight, but it is hinged to provide full protection to the blades in the ground modality. In the case of the water implementation, these propellers are also used to provide horizontal thrust to the vessel.Type: GrantFiled: September 10, 2019Date of Patent: May 24, 2022Assignee: Robotic Research OpCo, LLCInventors: Alberto Daniel Lacaze, Karl Nicholas Murphy, Katrina Corley, Chris Jones
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Patent number: 11279496Abstract: A landing assembly and method of landing an aircraft. The landing assembly includes a landing gear, a charging circuit, a sampling circuit and a processor. The charging circuit applies a charge to the landing gear and the sampling circuit measures a discharge rate of the electrical charge from the landing gear. The processor determines a contact between the landing gear and a surface from the discharge rate.Type: GrantFiled: December 7, 2018Date of Patent: March 22, 2022Assignee: Sikorsky Aircraft CorporationInventor: Igor Cherepinsky
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Patent number: 11173766Abstract: A suspension component includes a suspension spring, a screw actuator that is operable to compress and decompress the suspension spring upon supply of electrical power to the screw actuator, and locking structure that engages a portion of the screw actuator to restrain motion of the screw actuator to maintain a current degree of compression of the suspension spring.Type: GrantFiled: August 21, 2018Date of Patent: November 16, 2021Assignee: Apple Inc.Inventors: Jonathan L. Hall, Neal M. Lackritz, Troy A. Carter
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Patent number: 11104433Abstract: An aircraft float includes a float body configured to provide buoyancy to an aircraft, and a lower portion of the float body is configured to contact water. The lower portion of the float body includes a turbulator.Type: GrantFiled: July 18, 2019Date of Patent: August 31, 2021Inventor: David Bangle
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Patent number: 10988035Abstract: An alternating current type electric propulsion system is described that includes an AC generator and a plurality of propulsors electrically coupled to the AC generator. A first propulsor from the plurality of propulsors includes a first motor that drives a first fan of the first propulsor at a first speed. A second propulsor from the plurality of propulsors comprises a second motor that drives a second fan of the second propulsor at a second speed that is different than the first speed.Type: GrantFiled: October 11, 2019Date of Patent: April 27, 2021Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc., Rolls-Royce PLCInventors: Michael James Armstrong, Mark Jon Blackwelder, David John Howard Eames, Ellis Fui Hen Chong
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Patent number: 10759523Abstract: An aircraft assembly having landing gear with a known deployment value, apparatus for permitting landing gear deployment, down-lock sensing apparatus, a navigation system, a landing gear control system, a flight control system, and a deployment controller. The deployment controller is configured to: calculate a touch down value using the aircraft position and speed information provided by the aircraft navigation system; command the landing gear control system to provide the deploy signal when the touch down value reaches a deployment threshold value which is greater than the landing gear deployment value; and command the flight control system to execute a landing abort sequence if the controller does not receive the down-lock signal from the landing gear sensing apparatus within a deployment value window which is greater than or equal to the known deployment value for the landing gear but less than the touch down value.Type: GrantFiled: December 7, 2017Date of Patent: September 1, 2020Assignee: Safran Landing Systems UK LTDInventor: Robert Kyle Schmidt
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Patent number: 10730612Abstract: An amphibious aircraft has a tricycle landing gear that is movable between a retracted, or up, position and an extended, or down, position. Each member of the landing gear is protected in the forward direction by a hydrodynamic protector, or vane, or shoe, such as may tend to create lift when brought into engagement with water, as during landing. The landing gear protector vanes may be mounted to move with extension and retraction of the landing gear. The landing gear wheels may protrude to extend partially downwardly proud of the sole of the shoe. The landing gear actuator and transmission may operate all gear in concert. The shoes may include sacrificial wear members for ground engagement in the event of an inadvertent gear-up landing on terrain.Type: GrantFiled: October 24, 2018Date of Patent: August 4, 2020Assignee: E.B. Robinson Ltd.Inventor: Eric Brian Robinson
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Patent number: 10556643Abstract: A boat pontoon having a concave V-shape on a bottom portion thereof, generally straight vertical sides, a flat top panel member, and a removable and replaceable skid pad running longitudinally along the bottom of the pontoon. Vertically oriented gussets are positioned on an interior of the pontoon, to provide structural integrity and additional strength. In a preferred embodiment, a buoyant foam is provided within the interior cavity of the pontoon.Type: GrantFiled: November 17, 2017Date of Patent: February 11, 2020Inventor: James Carlisle
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Patent number: 10549848Abstract: A shock strut for a vehicle includes a housing with a through channel and a motor mount, and a motor fixed to the housing. The cylinder of a shock strut is configured to define a lead screw on its outer surface. The cylinder extends through the housing. The piston of the shock strut is attached to a ground engaging assembly. A gear nut rotatably mounted in the housing threadably engages the threaded cylinder, and is configured to be driven by the motor. The housing is attached to the vehicle, and the gear nut is controllably rotated to extend and retract the shock strut. A sensor provided on the assembly monitors the position of the shock strut. A torsion link assembly reacts rotational forces on the cylinder.Type: GrantFiled: April 26, 2017Date of Patent: February 4, 2020Assignee: SAFRAN LANDING SYSTEMS CANADA INC.Inventors: Graeme Peter Arthur Klim, Steven Kevin Amberg, Clément Rodrigues De Souza Meireles, Min Prasad Adhikari, Mohammad Moeid Elahikahouker, Seyed Mohammad Hashemi
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Patent number: 10526074Abstract: A system for the control of the door assemblies of a bay of a landing gear of an aircraft, that is retractile and is able to be deployed, the opening of the bay for the landing gear being able to be closed by a forward door assembly and an aft door assembly, comprises a coupling mechanism of the forward door assembly and the aft door assembly, that is configured such that the aft door assembly is not completely closed, but is ajar, as soon as the forward door assembly is opened during the deployment of the landing gear and the aft door assembly is completely closed at the complete closing of the forward door assembly when the landing gear is retracted.Type: GrantFiled: December 9, 2016Date of Patent: January 7, 2020Assignee: Airbus Operations (S.A.S.)Inventors: Christian Cros, Jérôme Phalippou, Christophe Mialhe, Jacques Peres
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Patent number: 10442542Abstract: An alternating current type electric propulsion system is described that includes an AC generator and a plurality of propulsors electrically coupled to the AC generator. A first propulsor from the plurality of propulsors includes a first motor that drives a first fan of the first propulsor at a first speed. A second propulsor from the plurality of propulsors comprises a second motor that drives a second fan of the second propulsor at a second speed that is different than the first speed.Type: GrantFiled: June 8, 2016Date of Patent: October 15, 2019Assignees: Rolls-Royce North American Technologies, Inc., Rolls-Royce Corporation, Rolls-Royce PLCInventors: Michael James Armstrong, Mark Jon Blackwelder, David John Howard Eames, Ellis Fui Hen Chong
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Patent number: 10112705Abstract: Off-board gyrocopter take-off systems and associated methods are disclosed. A representative method includes restraining a gyrocopter from vertical and lateral movement, pre-rotating a fixed-pitch lift rotor of the gyrocopter via a power source located off the gyrocopter, and releasing the gyrocopter for vertical movement to allow the gyrocopter to lift under a force provided by the lift rotor. Optionally, the method can further include interrupting or reducing power from the power source to the gyrocopter as a way to release the gyrocopter for vertical movement.Type: GrantFiled: September 8, 2017Date of Patent: October 30, 2018Inventor: Jaime G. Sada-Salinas
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Patent number: 10081422Abstract: An aircraft includes a fuselage which includes an unenclosed cockpit, a left arm where the proximal end is attached to the fuselage, a right arm where the proximal end is attached to the fuselage, a left float which is attached to the left arm between the proximal and distal ends, a right float which is attached to the right arm between the proximal and distal ends, and a plurality of rotors which includes a left inner rotor that is attached at a fixed angle to a top surface of the left float, a right inner rotor that is attached at a fixed angle to a top surface of the right float, a left outer rotor that is attached at a fixed angle to a top surface of the distal end of the left arm, and a right outer rotor that is attached at a fixed angle to a top surface of the distal end of the right arm.Type: GrantFiled: March 8, 2018Date of Patent: September 25, 2018Assignee: Kitty Hawk CorporationInventors: Todd Reichert, Cameron Robertson, Mark Johnson Cutler
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Patent number: 10059436Abstract: A float has a front-to-back length, a width, and a height where the front-to-back length of the float is strictly greater than the height of the float which in turn is strictly greater than the width of the float. At least a bottom portion of the float is watertight. The float includes an access panel to access the inside of the float. A battery is inside the float and is accessible via the access panel.Type: GrantFiled: October 13, 2017Date of Patent: August 28, 2018Assignee: Kitty Hawk CorporationInventors: Cameron Robertson, Todd Reichert
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Water-inflow prevention device of aircraft, air pressure regulating valve for aircraft, and aircraft
Patent number: 9969498Abstract: A water-inflow prevention device is provided by installing a closing lid 6 for blocking a duct 2 of an air pressure regulating valve 1, which regulates air pressure inside a cabin 101. A buoyant body 9 is attached to the disc-shaped closing lid 6 installed to the duct 2 so as to be rotatable around a rotation shaft 7. The buoyant body 9 receives a buoyant force from water when immersed in the water. Since the side of the closing lid 6 in which the buoyant body 9 is attached is thereby floated in the water, the closing lid 6 automatically rotates around the rotation shaft 7 so as to close a ventilation port 2a.Type: GrantFiled: November 21, 2016Date of Patent: May 15, 2018Assignee: MITSUBISHI AIRCRAFT CORPORATIONInventors: Shingo Kawano, Tomoka Mashio, Akitaka Urano, Shuichi Hagino -
Patent number: 9821906Abstract: A rotor with an elongated nosecone structure to provide stability when boarding or deplaning and to prevent damage to rotor blades is disclosed. A rotor as disclosed herein may include a plurality of rotor blades affixed to the hub structure; and an elongated nose structure extending away from the hub in a direction substantially orthogonal to a deployed direction of said rotor blades, the elongated nose structure having a length greater than a diameter of the elongated nose structure.Type: GrantFiled: February 8, 2017Date of Patent: November 21, 2017Assignee: Kitty Hawk CorporationInventor: Joseph Roop
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Patent number: 9452827Abstract: The present disclosure includes landing gear components, such as an outer cylinder of a shock strut assembly. The outer cylinder includes one or more structural attachment pins configured to engage with other components of the landing gear including pintle frames, drag braces, and torque links. The pins include a cobalt alloy mated to a receptacle having a cobalt-containing coating on an inner surface, which eliminates the need for a bushing between the pin and the receptacle of the corresponding landing gear component.Type: GrantFiled: September 26, 2014Date of Patent: September 27, 2016Assignee: Goodrich CorporationInventors: Noel C. Haynes, Marilea Manzini
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Patent number: 9169008Abstract: A buoyancy system (10) for an aircraft (1), said buoyancy system (10) comprises an inflatable float (15) and a cover (20). Said buoyancy system (10) includes at least one extensible connection means (25) fastened to the cover (20) to connect the cover (20) to a compartment (3) of an aircraft (1), while enabling the cover (20) to be retained and to be moved transversely during inflation of the float (15).Type: GrantFiled: November 21, 2013Date of Patent: October 27, 2015Assignee: Airbus HelicoptersInventor: Alexandre Bardy
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Patent number: 9096106Abstract: An unmanned vehicle may include a vehicle body that comprises an enclosed hull. The unmanned vehicle may include a propulsion, a ballast control system, a center of gravity system, a pressurization system, a control surface system, a navigation control system, and an on board master control system. The on board master control system may execute local control over operation of the various systems of the unmanned vehicle. The unmanned vehicle may also include a power supply carried by a portion of the vehicle body to provide power to the various systems. The various systems of the unmanned vehicle may be independently operable to support selective operation of the unmanned vehicle in the air, on the surface of the water, and below the surface of the water.Type: GrantFiled: May 14, 2012Date of Patent: August 4, 2015Assignee: UNMANNED INNOVATIONS, INCInventors: Bruce Hanson, Mark Everly
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Patent number: 9051046Abstract: A vertical support system includes a first articulated leg assembly configured to carry a first load, the first articulated leg assembly being selectively movable between a first retracted configuration and a first loaded configuration and a second articulated leg assembly configured to carry a second load substantially kinematically identical to the first articulated leg assembly, the second articulated leg assembly being selectively movable between a second retracted configuration and a second loaded configuration. The arrangement of axis of rotations and offset angles of the first and/or second lees of each articulated leg assembly may produce a lateral width ratio. A first vertical footprint of the first articulated leg assembly overlaps a second vertical footprint of the second articulated leg assembly when the leg assemblies are retracted.Type: GrantFiled: September 18, 2012Date of Patent: June 9, 2015Assignee: Bell Helicopter Textron Inc.Inventor: Steven Ivans
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Patent number: 8919691Abstract: The invention concerns a life-saving vehicle (10) designed as a hollow body with the form of a sphere or disk essentially flattened along a vertical axis (16) that demonstrates its greatest width in a horizontal plane (15) and which body, composed of an upper part (11) and a lower part (13), limits an internal passenger compartment (25), whereby the body comprises a stabilizing arrangement (12) that stabilizes the vehicle when it is in water, a telescopic arrangement (40), a stabilization means (14) arranged at the lower part, which stabilization means can be displaced in a vertical direction downwards from the lower part through activation of the telescopic arrangement (40). The vehicle, in order for it to travel not only in the air but also in water, comprises: a first and second rotor (52, 17), a motor (55) with an associated transmission (54), a pair of propulsion units (60) and a stabilizing fin (65).Type: GrantFiled: June 7, 2011Date of Patent: December 30, 2014Assignee: Well-Head Rescue ABInventors: Jan-Evert Lindmark, Juhani Niinivaara
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Publication number: 20140339359Abstract: A float for an aircraft, the float comprising: two buoyant side parts, a buoyant central part between the side parts, non-retractable main wheels, having their top part (a), that comprises at least 80% of the diameter (D) of the wheels, contained inside the float when viewed from the front, wherein the buoyant central part forms together with the buoyant side parts the furthermost frontal leading edge of the float and a trailing edge between the side parts, the trailing edge being offset from the rear end of the side parts towards the leading edge by a distance (b) which is at least one third of the length (L) of the side parts.Type: ApplicationFiled: May 15, 2014Publication date: November 20, 2014Inventor: Piotr JEUTÉ
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Patent number: 8864068Abstract: A landing system for an air vehicle with vertical takeoff and landing capability is provided that comprises a set of selectively pressurizeable upper and lower air chambers surrounded by a connecting curtain assembly. The upper and lower air chambers are each continuous having elongated right and left cylindrical center sections interconnected by semicircular sections at each end. The landing system is connected to the air vehicle by a catenary system connected to the upper air chamber. The landing system can adjust pressure in each individual set of landing chambers such that the attitude of the vehicle can be adjusted to clear uneven ground or assist with loading and offloading. The system is capable of absorbing energy during vertical landings. After landing, the system is capable of providing suction between the air vehicle and the ground to stabilize the air vehicle.Type: GrantFiled: April 2, 2012Date of Patent: October 21, 2014Assignee: Worldwide Aeros CorporationInventor: Igor Pasternak
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Patent number: 8807478Abstract: Described are aircraft with at least one fuselage, a wing, and at least one float coupled to the wing. As examples, each float may include a step that is located forward of or at an intersection of a bottom surface and a line that extends from an aircraft aft-most center of gravity at an angle of less than ten degrees rearward from a vertical direction. As further examples, each float may include a forward portion located forward of the step, the forward portion including a ski surface that is planar in a left to right horizontal direction, and an aft portion that is located rearward of the step.Type: GrantFiled: November 2, 2012Date of Patent: August 19, 2014Assignee: Leader Industries, Inc.Inventors: John A. Meekins, William Husa
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Publication number: 20140048647Abstract: Described are aircraft with at least one fuselage, a wing, and at least one float coupled to the wing. As examples, each float may include a step that is located forward of or at an intersection of a bottom surface and a line that extends from an aircraft aft-most center of gravity at an angle of less than ten degrees rearward from a vertical direction As further examples, each float may include a forward portion located forward of the step, the forward portion including a ski surface that is slanar in a left to right horizontal direction, and an aft portion that is located rearward of the step.Type: ApplicationFiled: November 2, 2012Publication date: February 20, 2014Applicant: Leader Industries, Inc.Inventors: John A. Meekins, Leader Industries, Inc.
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Patent number: 8480443Abstract: An all season air propelled watercraft has an elongated cabin structure adapted to accommodate at least one person therein. An elongated central pontoon member adjustably mounted to a bottom portion of the cabin structure and extending in a parallel direction thereto for at least the length thereof. Two stabilizer connector assemblies adjustably attached to a bottom portion of the cabin structure and extending horizontally in opposite directions therefrom. Two lateral stabilizer pontoons respectively and adjustably attached to a distal end portion of each the stabilizer connector assembly.Type: GrantFiled: April 23, 2011Date of Patent: July 9, 2013Inventor: Teofil Talos
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Patent number: 8430356Abstract: Described are aircraft with at least one fuselage, a wing, a power plant coupled to the at least one fuselage, a shroud surrounding a propeller, and at least two floats coupled to the wing. As examples, each float may include a step that is forward of the location at which the bottom surface of the float intersects a line that passes through a center of gravity of the aircraft and is oriented at an angle of six degrees rearward from vertical. As further examples, each float may include a forward portion located forward of the step, the forward portion including a ski surface that is planar in a left to right horizontal direction, and an aft portion that is located rearward of the step.Type: GrantFiled: August 20, 2012Date of Patent: April 30, 2013Assignee: Leader Industries, Inc.Inventors: John A. Meekins, William Husa
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Patent number: 8430355Abstract: Described are aircraft with at least one fuselage, a wing, a power plant coupled to the at least one fuselage, a shroud surrounding a propeller, and at least two floats coupled to the wing. As examples, each float may include a step that is forward of the location at which the bottom surface of the float intersects a line that passes through a center of gravity of the aircraft and is oriented at an angle of six degrees rearward from vertical. As further examples, each float may include a forward portion located forward of the step, the forward portion including a ski surface that is planar in a left to right horizontal direction, and an aft portion that is located rearward of the step.Type: GrantFiled: August 20, 2012Date of Patent: April 30, 2013Assignee: Leader Industries, Inc.Inventors: John A. Meekins, William Husa
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Publication number: 20130032666Abstract: Described are aircraft with at least one fuselage, a wing, a power plant coupled to the at least one fuselage, a shroud surrounding a propeller, and at least two floats coupled to the wing. As examples, each float may include a step that is forward of the location at which the bottom surface of the float intersects a line that passes through a center of gravity of the aircraft and is oriented at an angle of six degrees rearward from vertical. As further examples, each float may include a forward portion located forward of the step, the forward portion including a ski surface that is planar in a left to right horizontal direction, and an aft portion that is located rearward of the step.Type: ApplicationFiled: August 20, 2012Publication date: February 7, 2013Applicant: LEADER INDUSTRIES, INC.Inventors: John A. Meekins, William Husa
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Publication number: 20130026290Abstract: Described are aircraft with at least one fuselage, a wing, a power plant coupled to the at least one fuselage, a shroud surrounding a propeller, and at least two floats coupled to the wing. As examples, each float may include a step that is forward of the location at which the bottom surface of the float intersects a line that passes through a center of gravity of the aircraft and is oriented at an angle of six degrees rearward from vertical. As further examples, each float may include a forward portion located forward of the step, the forward portion including a ski surface that is planar in a left to right horizontal direction, and an aft portion that is located rearward of the step.Type: ApplicationFiled: August 20, 2012Publication date: January 31, 2013Applicant: LEADER INDUSTRIES, INC.Inventors: John A. Meekins, William Husa
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Publication number: 20120305702Abstract: The invention relates to a device (32) for rotationally coupling a wheel (10) with a ring (31) for driving the wheel (10) mounted so as to rotate coaxially with the wheel (10). According to the invention the device (32) comprises a plurality of connecting members (60) each extending in a direction contained in a plane perpendicular to the axis of rotation and forming an angle with a radial direction, the connecting members (60) being pivotably mounted on the one hand on the wheel (10) and on the other hand on the ring (31).Type: ApplicationFiled: May 18, 2012Publication date: December 6, 2012Applicant: MESSIER-BUGATTI-DOWTYInventors: Daniel BUCHETON, Sébastien REMOND, Gilles ELUARD
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Patent number: 8272596Abstract: Embodiments of the present invention include an aircraft with at least one fuselage, a wing, a power plant coupled to the at least one fuselage, a shroud surrounding a propeller of the power plant, and at least two floats coupled to the wing. In some embodiments, each float may further comprise a step positioned forward of a line that is at least 5 degrees rearward of a vertical line passing through a most aft empty weight center of gravity. In some embodiments, each float comprises a forward portion that is positioned forward of the step, wherein a ski surface is coupled to the forward portion, and an aft portion that is located aft of the step, wherein the aft portion of each float is configured to be wetted at taxiing speed. A rudder may be coupled to the aft portion. Each float may also include a retractable wheel and landing gear, wherein the wheel is preferably positioned on the line that is at least 5 degrees rearward of a vertical line passing through a most aft empty weight center of gravity.Type: GrantFiled: April 8, 2010Date of Patent: September 25, 2012Assignee: Leader Industries, Inc.Inventors: John A. Meekins, William Husa
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Publication number: 20120104164Abstract: This invention relates to an improved float for use with an aircraft having water landing capabilities comprising at least one float capable of increasing/decreasing its volume arranged to at least substantially support said aircraft in a floating on water status so that the fuselage of the aircraft is substantially above the water.Type: ApplicationFiled: May 20, 2010Publication date: May 3, 2012Inventors: Saxon Grenfell Rudduck, Alan John Smith, Matthew Robert Tetlow
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Patent number: 8131406Abstract: One embodiment is directed to a method for testing an aircraft prior to flight. The method includes receiving a user signal from a pre-flight test input source, the user signal indicating that a pilot of the aircraft has directed engine control circuitry, which is arranged to electronically control operation of a set of piston engines of the aircraft during flight, to begin testing the aircraft in an automated manner. The method includes, in response to the user signal, conducting a pre-flight test of the aircraft from the engine control circuitry. The method includes, upon completion of the pre-flight test, outputting a result of the pre-flight test from the engine control circuitry.Type: GrantFiled: April 9, 2008Date of Patent: March 6, 2012Assignee: Lycoming Engines, a division of Avco CorporationInventors: James Paul Morris, Charles Schneider
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Patent number: 8038095Abstract: A motorized airplane includes a landing gear with at least two legs capable of retracting into the fuselage via hatches. A pair of hydrofoils is fitted to the base of the fuselage in conformance with the ailerons used for lift and hydrodynamic stability, directed towards the base like a reverse V shape. The legs of the landing gear are each articulated around the pivot axes, fitted onto the hydrofoils. The landing gear is dual-function, using wheels or skis suspended on legs. Applications: airplane for landing on water, ground and snow.Type: GrantFiled: June 7, 2007Date of Patent: October 18, 2011Assignee: Lisa AirplanesInventors: Erick Herzberger, Jean-Francois Clavreul
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Publication number: 20110248118Abstract: Embodiments of the present invention include an aircraft with at least one fuselage, a wing, a power plant coupled to the at least one fuselage, a shroud surrounding a propeller of the power plant, and at least two floats coupled to the wing. In some embodiments, each float may further comprise a step positioned forward of a line that is at least 5 degrees rearward of a vertical line passing through a most aft empty weight center of gravity. In some embodiments, each float comprises a forward portion that is positioned forward of the step, wherein a ski surface is coupled to the forward portion, and an aft portion that is located aft of the step, wherein the aft portion of each float is configured to be wetted at taxiing speed. A rudder may be coupled to the aft portion. Each float may also include a retractable wheel and landing gear, wherein the wheel is preferably positioned on the line that is at least 5 degrees rearward of a vertical line passing through a most aft empty weight center of gravity.Type: ApplicationFiled: April 8, 2010Publication date: October 13, 2011Inventors: John A. Meekins, William Husa
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Patent number: 7874514Abstract: A multi-wing, multi-engine, multi-hull amphibious aircraft is disclosed. In the illustrative embodiment, the aircraft has an open frame structure without a fuselage.Type: GrantFiled: June 5, 2007Date of Patent: January 25, 2011Assignee: Lockheed Martin CorporationInventor: Brian R. Said
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Patent number: 7699262Abstract: A hydrofoil trim tab for use with each of a pair of seaplane floats, each tab including a substantially planar shaped body secured to an inside facing location of each float such that a pair of tab bodies are arrayed in opposing and inwardly directed fashion relative to the floats. Each tab is further constructed as a two piece article, a first portion being either mechanically secured or welded to the surface of the float, with a second portion being releasably/breakaway attached to the first portion, such as by frangible fasteners engaging a slidably connection location between the portions. In this fashion, inadvertent breakage of a trim tab at the frangible location will prevent damage to the float.Type: GrantFiled: November 20, 2007Date of Patent: April 20, 2010Inventor: Gerald Filipek
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Publication number: 20100044506Abstract: A method of retrofitting retractable floats to an aircraft such as a floatplane. The aircraft considered have existing landing gear such as wheeled landing gear to equip said aircraft to optionally takeoff or land on a solid surface such as a beach or landing strip, the method including the steps of: a) mounting at least one float retraction arm to the aircraft; and b) attaching the floats to the float retraction arm. Each float includes an air travel position in which it is secured close to the float retraction arm mounting location and/or the fuselage, and a deployed position in which the float is lower than the existing landing gear. In following the float retraction paths of travel of the float retraction arm and the floats between the air travel and deployed positions, the floats do not interfere with the existing landing gear or its operation.Type: ApplicationFiled: January 24, 2008Publication date: February 25, 2010Inventors: Alan John Smith, Grenfell Saxon Ruddock, Matthew Tetlow
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Patent number: 7552895Abstract: The aerodynamics of a floatplane can be improved by providing a wing suitable for mounting on a spreader bar between floats of the floatplane, mounting said wing on the spreader bar between the floats of a floatplane, and preventing the wing from rotating around the spreader bar during flight operations. In one apparatus embodiment, the invention comprises a wing mountable on a spreader bar between floats of the floatplane, a plurality of ribs spaced along the wing's axis, each rib having a recess suitable for accepting the spreader bar, and torque-restraining means to prevent the wing from rotating around the spreader bar.Type: GrantFiled: October 7, 2005Date of Patent: June 30, 2009Inventor: Dave From
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Publication number: 20090127388Abstract: A motorised airplane includes a landing gear with at least two legs capable of retracting into the fuselage via hatches. A pair of hydrofoils is fitted to the base of the fuselage in conformance with the ailerons used for lift and hydrodynamic stability, directed towards the base like a reverse V shape. The legs of the landing gear are each articulated around the pivot axes, fitted onto the hydrofoils. The landing gear is dual-function, using wheels or skis suspended on legs. Applications: airplane for landing on water, ground and snow.Type: ApplicationFiled: June 7, 2007Publication date: May 21, 2009Applicant: Lisa AirplanesInventors: Erick Herzberger, Jean-Francois Clavreul
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Patent number: 7350751Abstract: A system for controlling landing gear of an aircraft is disclosed. The apparatus includes a sensor for sensing water, wherein the sensor is coupled to the landing gear and a retracting device for retracting the landing gear when the sensor senses a body of water. In one alternative, the aircraft is an amphibious aircraft and the sensor senses electrical conductivity. In another alternative, the retracting device comprises a hydraulic system for deploying and retracting the landing gear, wherein the hydraulic system retracts the landing gear when the sensor senses a body of water. In yet another alternative, the retracting device comprises a locking mechanism that locks the landing gear to the aircraft, wherein the locking mechanism unlocks the landing gear so as to detach it from the aircraft when the sensor senses a body of water.Type: GrantFiled: April 7, 2006Date of Patent: April 1, 2008Assignee: Icon Aviation, Inc.Inventor: Thomas Hawkins
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Publication number: 20070272797Abstract: A method for modifying a target includes directing exhaust from multiple engines, preferably jet engines, towards the target. The target being modified can be, for example, a fire, an atmospheric system, a storm, snow, a gathering, a spill, an emission, a discharge, a mud slide, or a dust. The operation and/or deployment of the engines can be by remote control or robotics. In one example, a system for modifying a target includes a support for securing multiple jet engines and a fuel source. Preferably, the jet engines are mounted on turrets that are capable of being rotated.Type: ApplicationFiled: May 23, 2006Publication date: November 29, 2007Inventors: Boris Skurkovich, Melvin A. Millstein, Simon Skurkovich
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Patent number: 7188804Abstract: A float retractable landing gear. The float retractable landing gear incorporates a wheel support, a side gear door, a bottom gear door, and one or more hinges and strut ears attached to a spine. At least one hinge is rotatably attached to a float. The float incorporates a float side cutout communicating with a float bottom cutout. A spring-loaded strut incorporating on over center toggle down lock feature is attached between the float retractable landing gear and the float. A float side wall skin is attached to an upper portion of the float side wall cutout. The side gear door is sized to cover the lower portion of the float side wall cutout, and the bottom gear door is sized to cover the float bottom cutout. The float retractable landing gear may be specified to default into the extended or retracted position depending on the strut spring constant selected.Type: GrantFiled: June 25, 2004Date of Patent: March 13, 2007Inventor: Steven C. Boetto
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Patent number: 7156033Abstract: A flotation device for maintaining an aircraft in a floating and stable condition is provided. The flotation device comprises at least one flotation bladder mounted to the aircraft and an inflation mechanism for inflating the flotation bladder. A method for maintaining an aircraft in a floating condition is also provided.Type: GrantFiled: February 27, 2004Date of Patent: January 2, 2007Assignee: FloatLogic, Inc.Inventors: Tony W. Mears, David G. Walder, Thomas Edward Berg
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Patent number: 7063291Abstract: An amphibian delta wing jet aircraft, which has a plurality of triangular folding wing panels, two of which are hingedly attached to a lifting shape body, which incorporates a W-shaped hull in it's cross section of a fuselage so that the craft operates efficiently as an aircraft when flying through the air with the wings in a fully unfolded extended position. The craft also performs well as a watercraft capable of relatively high speeds on the water surface when the wing are folded-up in a non extended position. The W-shape hull transverse cross section also provides excellent characteristics so that the craft can hydroplane over marshlands or waterlogged soil which may be covered with emersed rushes, or snow, cattails and other tall grasses. The craft is also provided with four retractably mounted mechanically extendable wheels, to be utilized when configured as a land vehicle.Type: GrantFiled: May 25, 2004Date of Patent: June 20, 2006Inventor: Kenneth S. Rado
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Patent number: 7040573Abstract: An aerodynamically efficient fiberglass hull consisting of a pointed bow, a step amidships, and aft section coming to a point which will be attached to the hull of land aircraft and convert them to water operations. In addition, one wing float will be securely attached to the outboard section of each wing. The main and nose landing gear will be removed enabling the propellers to have adequate clearance from water. Landing gear removal procedures will not be used for amphibious aircraft.Type: GrantFiled: June 4, 2004Date of Patent: May 9, 2006Inventor: Richard Selman
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Patent number: 6974107Abstract: A thrust reverser system actuator assembly is provided that includes a torque limiter to limit the number of torque that may be applied to the actuator assembly. The actuator assembly includes an actuator and a torque limiter assembly. The actuator is adapted to receive a drive force and is configured, in response to receipt of the drive force, to move between a stowed position and a deployed position. The torque limiter assembly is coupled to an end of the actuator and is configured to limit torque applied to the actuator assembly upon a torque magnitude being reached in at least the actuator.Type: GrantFiled: June 18, 2003Date of Patent: December 13, 2005Assignee: Honeywell International, Inc.Inventors: Donald J. Christensen, Casey Hanlon, Douglas T. Hopper, Andrew Johnson, Robert D. Kortum