Patents Examined by Justin M Benedik
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Patent number: 12043393Abstract: Systems and methods to cut a closing loop to deploy a parachute. The system includes a cutter with a body with a cutter opening that extends through the body and a blade that is movable across the cutter opening. Processing circuitry is configured to signal the cutter to move the blade across the cutter opening. A mount includes a base, a retainer with a channel sized to receive the cutter, and a mount opening that extends through the mount and across the channel. The cutter is configured to fit within the channel with the cutter opening aligned with the mount opening to form a through-opening such that the closing loop extends through the cutter and the mount.Type: GrantFiled: August 9, 2023Date of Patent: July 23, 2024Assignee: SUN PATH PRODUCTS, INC.Inventors: Thomas Parker, Jesse Sparling, Justin Beaurivage
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Patent number: 12043380Abstract: A panel assembly is disclosed having a panel, a beam attached to the panel, and a plurality of stiffeners attached to the panel. Each stiffener includes a respective bridge which crosses over the beam at an intersection from a first side of the beam to a second side of the beam. Each bridge has an outer surface facing away from the panel and an inner surface facing towards the panel. The inner surface of each bridge deviates away from the panel to form a recess at the intersection, and the outer surface of each bridge deviates away from the panel to form a protrusion at the intersection.Type: GrantFiled: November 7, 2022Date of Patent: July 23, 2024Assignee: AIRBUS OPERATIONS LIMITEDInventors: John Martin Gaitonde, Chris Heaysman
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Patent number: 12037123Abstract: An ejection handle separation system is disclosed herein. The ejection handle separation system includes an ejection seat handle, a rotatable component, a cable connected to the handle and coupled to the rotatable component, wherein the rotatable component rotates in response to pulling the ejection seat handle, and an anchor inserted into the rotatable component and configured to releasably connect the cable to the rotatable component.Type: GrantFiled: June 15, 2022Date of Patent: July 16, 2024Assignee: ROCKWELL COLLINS, INC.Inventors: Steve A. Holstine, Mayur K. Vadhwana
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Patent number: 12037129Abstract: An apparatus comprising: a port cap operable to be coupled to a hydraulic motor/pump, the port cap comprising a first fluid port, a second fluid port and an access port; a first transducer coupled to the port cap through the first fluid port; a second transducer coupled to the port cap through the second fluid port; and a resolver coupled to the port cap through the access port, the resolver comprising a splined shaft to couple to an output shaft of the hydraulic motor/pump when the port cap is coupled to the hydraulic motor/pump. A system including a hydraulic motor/pump, a drive system controller and a port cap and a method of determining hose velocity, hose position, motor/pump torque and hose tension using data gathered at port cap.Type: GrantFiled: February 2, 2022Date of Patent: July 16, 2024Assignee: Federal Industries, Inc.Inventor: Asher Bartov
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Patent number: 12037098Abstract: In summary, the present application relates to an aircraft interior paneling (10) comprising: —a planar replaceable surface element (40); —a structural element (20); —at least one connection element (30); wherein the replaceable surface element (40) is detachably fastened to the structural element (20) by means of the at least one connection element (30), and wherein the replaceable surface element (40) comprises: —a support element (42), wherein, in the thickness direction of the support element (42), the support element (42) comprises a plurality of successive layers which comprise woven fabrics; —a decorative element (50) which is attached to a decorative connection surface (52) of the support element (42), wherein the support element (42) is dimensionally stable; and a replaceable surface element (40) for an aircraft interior paneling (10); the use of a replaceable surface element (40) for an aircraft interior paneling (10); a method for producing a replaceable surface element (40) for an aircraft interioType: GrantFiled: August 6, 2020Date of Patent: July 16, 2024Inventor: Siegbert Rauch
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Patent number: 12031802Abstract: A guided projectile having a nose portion, a body portion, a tail portion, and a central axis. In various embodiments the projectile includes a control support portion and a collar assembly pivotally mounted to the control support portion. In various embodiments the collar assembly includes a collar having an exterior sidewall with a plurality of fixed aerodynamic surfaces thereon for spinning the collar and a plurality of variable sweep wings for directional control of the projectile. In various embodiments the plurality of variable sweep wings each have a first end coupled to a wing actuator configured to rotate a second end portion between and including a first position, where the wings are oriented generally parallel to the central axis of the projectile to a second position, where the lengthwise wing axis of the plurality of wings are oriented generally perpendicular to the central axis of the projectile.Type: GrantFiled: February 9, 2023Date of Patent: July 9, 2024Assignee: Northrop Grumman Systems CorporationInventor: Michael J. Wilson
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Patent number: 12030642Abstract: The present invention relates essentially to a double-door module for aircraft seats, characterized in that it comprises: a first door that is mobile in translation between a stowed position and a deployed position, a second door that is mobile in translation between a stowed position and a deployed position, the first door and the second door overlapping completely when the first door and the second door are simultaneously in the stowed position, and a control system comprising a device for locking and unlocking the first door and/or the second door.Type: GrantFiled: July 11, 2019Date of Patent: July 9, 2024Assignee: Safran SeatsInventors: Franck Jasny, Daniele Guerra, Denys Lavergne, Bruno Lopez, Christian Verny
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Patent number: 12030649Abstract: Parachutes which have a generally circular skirt or hem, such as semi-hemispherical, extended gore, or any variant of axisymmetric parachutes and cruciform parachutes with arms attached are disclosed with a plurality of vertical slits located in a circumferential band adjacent the skirt or hem of the parachute to prevent canopy inversion. During deployment, when the outer portion of the canopy is exposed to air flow, the slits open up and the drag of the skirt of the canopy is reduced, thus limiting the potential for hem migration. The slits are positioned to allow airflow therethrough in order for the pressure on the outside of the canopy to be transferred through the slit openings and released or transferred to inside of the lower section of the canopy. Instead of slits, elongated narrow openings can be utilized.Type: GrantFiled: November 22, 2022Date of Patent: July 9, 2024Assignee: AIRBORNE SYSTEMS NA INC.Inventor: William Louis Bruce Gargano
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Patent number: 12024311Abstract: A boom cover for covering a refueling boom, particularly a flying boom, of a refueling aircraft. The boom has a closure which has a shield sized to cover the open end of the refueling boom, to prevent intrusion of debris, animals, etc. The closure has a hoop for circumscribing the boom and drawing the shield taut for remaining on the boom and flaccid for attachment to and removal from the boom. The closure may be attached to and removed from the boom by a longitudinally rotatable handle which is manipulated by a ground operator. Optionally the handle may be removable from the closure for use on subsequent aircraft or storage.Type: GrantFiled: August 15, 2022Date of Patent: July 2, 2024Assignee: United States of America as represented by the Secretary of the Air ForceInventor: Jacob Helzer
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Patent number: 12017780Abstract: A shock absorber assembly, particularly for attenuating shocks transmitted to a person's body, especially to reduce shock to a paratrooper's body during a tethered cargo tandem jump. Specialized elastic absorber units are disposed in series in connection with a tether or strap to maintain the series configuration. A chain reactive shock absorption can be predetermined, and adjusted based on the expected shock(s) of a given jump. The adjustment is accomplished by selecting the number and type of absorber unit(s) provided an any of two (or more) series chains of the assembly. In use, the complete shock absorber assembly is deployed between a cargo tether and a cargo harness.Type: GrantFiled: December 7, 2022Date of Patent: June 25, 2024Inventor: Ishmael Antonio
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Patent number: 12017795Abstract: Unmanned aerial vehicle (UAV) launch and recovery is disclosed. A disclosed example apparatus for recovering a UAV includes a base to be mounted to a recovery vehicle, a flexible arm extending from the base to pivot therefrom, the arm having a first end at the base and a second end opposite the first end, the arm to move to counteract a movement of the recovery vehicle, and a coupler mounted on or proximate the second end of the arm, the coupler to be releasably coupled to the UAV.Type: GrantFiled: April 14, 2022Date of Patent: June 25, 2024Assignee: The Boeing CompanyInventor: John Wong
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Patent number: 12012206Abstract: The aircraft can include: an airframe, a tilt mechanism, a payload housing, and can optionally include an impact attenuator, a set of ground support members (e.g., struts), a set of power sources, and a set of control elements. The airframe can include: a set of rotors and a set of support members. By utilizing a larger rotor blade area (and/or larger rotor disc area) and adjusting the blade pitch and RPM, the rotors can augment the lift generated by the aerodynamic profile of the aircraft in the forward flight mode in addition to providing forward thrust. Variants generating lift with the rotors can reduce or eliminate additional control surfaces (e.g., wing flaps, ailerons, ruddervators, elevators, rudder, etc.) on the aircraft since the thrust and motor torque is controllable (thereby indirectly controlling lift) at each rotor, thereby enabling pitch, yaw, and/or roll control during forward flight.Type: GrantFiled: July 28, 2023Date of Patent: June 18, 2024Inventors: Gregor Veble Mikic, Alex Stoll, JoeBen Bevirt
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Patent number: 12006855Abstract: A muffler (40) devised particularly for use with an engine of the type used on unmanned aerial vehicles (UAVs), and a UAV (10) having an engine (30) fitted with the muffler (40). The muffler (40) comprises a body (51) having an interior chamber (60). The muffler body (51) has a first end section (53) and a second end section (55). The first end section (51) is adapted for mounting onto the engine (31) by way of a first mount (81), with the interior chamber (60) in communication with an exhaust outlet of the engine (31) to receive exhaust flow therefrom. The second end section (53) is adapted to be mounted by way of a second mount (82) in a manner resisting movement with respect to the engine (31). In one arrangement, the second mount (82) is configured to yieldingly resist movement with respect to the engine (30). In another arrangement, the second mount (82) is configured to mount the second end section (55) under a preload resisting movement of the second end section with respect to the engine (30).Type: GrantFiled: June 29, 2020Date of Patent: June 11, 2024Assignee: ORBITAL AUSTRALIA PTY LTDInventors: John Howard Tubb, Geoffrey Paul Cathcart, Pouria Mehrani, Mario Charles Muscat
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Patent number: 12006019Abstract: An internal structural reinforcement element for fuselages, where the internal structural reinforcement element has a longitudinal direction adapted for its placement in the longitudinal direction of the fuselage and a transversal direction perpendicular to the longitudinal direction, comprising: an external reinforcement element, an internal reinforcement element, located internally to the external reinforcement element in the transversal direction of the structural element, where both reinforcement elements are manufactured from resin-impregnated fibre, and an intermediate element, located between the external reinforcement element and the internal reinforcement element in the transversal direction of the structural element, the intermediate element being manufactured from pre-impregnated composite material.Type: GrantFiled: July 9, 2020Date of Patent: June 11, 2024Assignee: MUELLES Y BALLESTAS HISPANO-ALEMANAS PROJECTS, S.L.Inventors: Miguel Ruiz Dealbert, Juan Salamero Laorden, Roberto Estal Vera, María del Mar Cuetos Gómez
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Patent number: 12007212Abstract: In accordance with at least one aspect of this disclosure, an actuation system for a guided munition, includes a reservoir disposed in a guided munition body housing a compressible fluid in a compressed state, a fluid path connecting the reservoir in fluid communication with a heat exchange volume, a throttling orifice disposed in the fluid path configured to expand the compressible fluid, and an actuation path connecting the heat exchange volume in fluid communication with a moveable component. The actuation path can be configured to supply pneumatic pressure to the moveable components.Type: GrantFiled: October 8, 2021Date of Patent: June 11, 2024Assignee: Simmonds Precision Products, Inc.Inventors: Jason Graham, Craig R. Bibeau
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Patent number: 11993364Abstract: A pin assembly for insertion into a pin joint of an aircraft landing gear is disclosed. The pin assembly includes a reservoir for storing a lubricating agent and a piston mounted for reciprocal movement within the reservoir, the piston dividing the reservoir into a first chamber and a second chamber. A bi-directional flow path between the first and second chambers via the surface to be lubricated is provided by means of a first bi-directional flow path between the first chamber and the exterior of the pin assembly and a second bi-directional flow path between the second chamber and the exterior of the pin assembly. A pin assembly including an indicator system, and a pin insert in the form of a replaceable cartridge is also disclosed along with associated methods.Type: GrantFiled: February 25, 2021Date of Patent: May 28, 2024Assignee: AIRBUS OPERATIONS LIMITEDInventor: Richard Holt
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Patent number: 11993359Abstract: The system 100 can include a balloon system 110 and a set of spools 120. The system can optionally include a set of actuators 130. However, the system 100 can additionally or alternatively include any other suitable set of components. The system can function to facilitate balloon launch preparation and/or launch of a balloon vehicle system. The system can additionally function to facilitate controlled stand-up of a balloon.Type: GrantFiled: November 13, 2023Date of Patent: May 28, 2024Assignee: Space Perspective Inc.Inventors: Jacquie Prescott, Ryan Nascimento, Taber MacCallum, Manasi Palwankar
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Patent number: 11987353Abstract: Stiffened skin panels comprise alternating truss core portions and solid laminate portions sandwiched between inner and outer facesheets, all formed from a fiber reinforced thermoplastic. The components of the panels are co-consolidated using induction heating. The panels are stiffened with spars fastened to the solid laminate portions.Type: GrantFiled: April 19, 2022Date of Patent: May 21, 2024Assignee: The Boeing CompanyInventors: Jeffery Lee Marcoe, Marc R. Matsen, Waeil M. Ashmawi, Sahrudine Apdalhaliem
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Patent number: 11981453Abstract: A system for aerial vehicle landing is provided. The system includes a displacement compensation unit and a traction control module. The displacement compensation unit includes a top portion, a bottom portion, and at least one actuators connected to the top portion and the bottom portion, configured to provide a displacement compensated top portion to engage with an aerial vehicle. The traction control module includes a traction generator connected to a tether. Through the tether the aerial vehicle is tractioning toward the top portion of the displacement compensation unit. A method for controlling a system for aerial vehicle landing is also provided.Type: GrantFiled: September 22, 2023Date of Patent: May 14, 2024Assignee: FAIRTECH CORPORATIONInventor: Jui-Pao Pan
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Patent number: 11975867Abstract: In one possible embodiment, a UAV payload module retraction mechanism is provided including a payload pivotally attached to a housing. A biasing member is mounted to bias the payload out of the housing and a winch is attached to the payload. An elongated flexible drawing member is coupled between the housing and the winch, the elongated drawing flexible member being capable of being drawn by the winch to retract the payload within the housing.Type: GrantFiled: January 10, 2023Date of Patent: May 7, 2024Assignee: AeroVironment, Inc.Inventors: John Peter Zwaan, Pavel Belik, Manolis Dimotakis, Christopher J. D'Aquila