Patents Examined by Justin M Benedik
  • Patent number: 11904998
    Abstract: The system can include: a vehicle 100 and a stabilizer 200. However, the system can additionally or alternatively include any other suitable set of components. The system functions to facilitate vehicular transport (e.g., via a cabin). Additionally, the system can provide impact attenuation and/or mitigate rebound of the vehicle during a water landing. Additionally or alternatively, the system can function to provide aquatic stabilization of the vehicle and/or cabin thereof. However, the system 100 can provide any other suitable functionalities.
    Type: Grant
    Filed: July 19, 2023
    Date of Patent: February 20, 2024
    Assignee: Space Perspective Inc.
    Inventors: Royce Fernandes, John Zaniel Maccagnano, Taber MacCallum, Ryon Warren, Daniel James Window, Rodger Farley
  • Patent number: 11898757
    Abstract: A propulsion system includes at least one rotating detonation actuator comprising: a flow path extending from an inlet end to an outlet end; an inner wall defining a radially inner boundary of the flow path; an outer wall defining a radially outer boundary of the flow path; and at least one aircraft wing. The rotating detonation actuator is disposed in the aircraft wing. At least one rotating detonation wave travels through the flow path from the inlet end to the outlet end.
    Type: Grant
    Filed: August 3, 2021
    Date of Patent: February 13, 2024
    Inventors: Nicholas William Rathay, Narendra Digamber Joshi, Venkat Eswarlu Tangirala
  • Patent number: 11897621
    Abstract: A device that detects deployment of a parachute. The device is configured to be operatively connected to the parachute, such as through a container that holds the parachute. The device includes a cable with one or more connectors. The device also includes a controller that monitors a status of the cable. The cable is operatively connected to the container such as through a line. The container opens during deployment of the parachute. This opening causes one or more of the connectors to disengage thus causing an open circuit in the cable that is detected by the controller.
    Type: Grant
    Filed: February 1, 2022
    Date of Patent: February 13, 2024
    Inventor: Justin Beaurivage
  • Patent number: 11884421
    Abstract: A UAV launch system including a launch rack mounted at altitude, and housing one or more UAVs, and a ground station. The ground station may activate the UAVs for a high-altitude launch. In a further aspect, the UAVs are configured for a stationary, high-altitude launch, without low altitude launch features. Launching a UAV from a high-altitude (greater than about 30 meters or 100 feet) fixed location like an Aerostat or tall building allows the designer to eliminate much of the functionality required for launching the UAV from low altitude as well as ignore the aerodynamics required to support launch (e.g. near-stall) flight conditions.
    Type: Grant
    Filed: July 28, 2022
    Date of Patent: January 30, 2024
    Assignee: Thunderbolt Software LLC
    Inventor: Andrew Winkler
  • Patent number: 11878789
    Abstract: An aircraft brake control system for controlling antiskid braking of an aircraft wheel is disclosed including a control assembly having a mode controller which sets the mode of operation of an antiskid brake calculator, configured to set a first mode, when an input of the indication of a brake energy supply configuration indicates a first brake energy supply being used, in which the antiskid brake calculator applies a first restriction level on a rise rate of the antiskid brake command, and a second mode, when the input 305 indicates a second brake energy supply being used, in which the antiskid brake calculator applies a second, lower, restriction level on a rise rate of the antiskid brake command.
    Type: Grant
    Filed: March 7, 2022
    Date of Patent: January 23, 2024
    Inventors: Alexander Hayes, Ashley Bidmead, Andrew Hebborn
  • Patent number: 11873089
    Abstract: A powered paragliding harness includes a harness with a pilot's back rest and an engine mount carrying a power unit with propeller. The back rest and engine mount are connected via at least first and second levers. Hinged connections connect one end of each to the back rest and the other end to the engine mount. The first lever is shorter than the second. In the harness operational state, the first lever is above the second. The levers enable the transition between an upright position, where the back rest—propeller angle is small, especially back rest and propeller are or close to parallel, for an upright pilot position during take-off/landing, and a reclined position, where the back rest—propeller angle is larger, for a reclined pilot position. The second lever—engine mount connection is nearer to the power unit center of gravity than the first lever—engine mount connection.
    Type: Grant
    Filed: July 14, 2022
    Date of Patent: January 16, 2024
    Inventor: Miroslav Svec
  • Patent number: 11866188
    Abstract: An electric motor nacelle for a vertical take-off and landing (VTOL) aircraft includes a fairing wherein an electric motor is housed equipped with at least one propeller extending outwards from a top face of the fairing, and a cooling device designed to cool the electric motor when the aircraft is in take-off, cruise and landing phases and including a reversible coolant fluid supply and exhaust manifold, designed, alternately: in the cruise phase, to receive a stream of cold fluid generated by the movement of the aircraft and to convey this stream of fluid, through the motor, towards an outlet situated opposite the propeller, and in take-off or landing phase, to receive a stream of hot fluid transmitted by the propeller and having passed through the motor.
    Type: Grant
    Filed: October 7, 2020
    Date of Patent: January 9, 2024
    Inventors: Christophe Castelli, Valentin Antoine Maxime Mesnil, Abdoulahad Thiam
  • Patent number: 11840352
    Abstract: An air intake includes a substantially cylindrical inner wall, a substantially cylindrical outer wall, a front lip connecting the inner wall and the outer wall, a front mounting flange, and a support structure. The front mounting flange is configured to cooperate with a rear flange of a wall of an aircraft engine. The support structure is configured to be secured to the wall of the aircraft engine at a location longitudinally downstream of the mounting flange. The outer wall includes a downstream end configured to be positioned in a junction area flush with a front end of a fan external cowl. A portion of the outer wall being configured to bear at least against the support structure. The support structure is configured to be secured to the wall of the aircraft engine so that a load path passes directly from the outer wall towards the fan casing.
    Type: Grant
    Filed: October 26, 2021
    Date of Patent: December 12, 2023
    Assignee: Safran Nacelles
    Inventors: Gina Ferrier, Patrick Boileau, Pierre Caruel
  • Patent number: 11834160
    Abstract: An aircraft brake control system accommodates desired yaw for steering, while substantially eliminating undesired yaw. The system assesses brake command signals from the pilot, signals corresponding to aircraft parameters, and signals based on brake control parameters, and determines therefrom an amount of yaw desired by the pilot. The instantaneous yaw rate is monitored and compared to the desired yaw rate. An error signal corresponding to the difference between instantaneous and actual yaw rates is calculated and that error signal is employed to modify a braking differential between right and left brakes to eliminate or substantially reduce the undesired yaw.
    Type: Grant
    Filed: December 18, 2020
    Date of Patent: December 5, 2023
    Assignee: Meggitt Aircraft Braking Systems Corporation
    Inventors: James L. Hill, David N. Roe, Kurt Burkhalter, Benjamin Robert Piercy Quickfall
  • Patent number: 11834151
    Abstract: A configuration system (80) arranged to configure an aircraft in a single-pilot mode and a two-pilot mode, comprising: acquisition means (84) and authentication means (83) arranged to acquire and authenticate a configuration order that defines the selected mode and controls the configuration system (80) to configure the aircraft in the selected mode; first activation means (85) arranged to activate equipment dedicated to piloting by a single-pilot on board when the aircraft is configured in single-pilot mode, and to deactivate dedicated equipment when the aircraft is configured in two-pilot mode; verification means (87) arranged to, when the aircraft is configured in the single-pilot mode, verify that single-pilot flight conditions are met and inform the sole pilot on board and a ground station of the results of these checks.
    Type: Grant
    Filed: December 19, 2019
    Date of Patent: December 5, 2023
    Inventors: Eric Walter, Loïc Fougeres, Mikaël Diaz, Philippe Tranie, Ng Kwee Chye, Tay Siew Liong
  • Patent number: 11834148
    Abstract: A cargo aircraft is disclosed, and may include a fuselage defining a longitudinally-extending cargo compartment and including: an elongate cylindrical portion, longitudinally-opposed forward and rearward ends, and laterally-opposed first and second sides, and a forward portion engaged with the forward end of the cylindrical portion, the fuselage defining a continuous cargo opening to the cargo compartment along the first side, the cargo opening having a first portion extending along the cylindrical portion to a rearward edge and a second portion extending along the forward portion to a forward edge, wherein an increased distance of the forward edge from the forward end of the cylindrical portion allows an elongate cargo item to be obliquely inserted lengthwise through the cargo opening from the forward edge at a decreased acute loading angle between the elongate cargo item and the lateral centerline.
    Type: Grant
    Filed: November 17, 2021
    Date of Patent: December 5, 2023
    Assignee: The Boeing Company
    Inventors: Sergey Barmichev, Zarir Pastakia, Mithra Sankrithi
  • Patent number: 11827354
    Abstract: An unmanned aerial robotic vehicle (UARV) that can fly to an object such as a palm tree, hover in place adjacent to the object, mount itself securely and releasably to a mounting location on the object using a mounting mechanism, and which uses an incorporated utility system for performing one or more utilitarian functions, such as use of a cutting tool to trim palm tree branches and foliage.
    Type: Grant
    Filed: January 26, 2023
    Date of Patent: November 28, 2023
    Inventor: Lucio Volpi
  • Patent number: 11820521
    Abstract: An apparatus and an article of manufacture providing a parachute ripcord pull force reducer device, method and system offering mechanical gain such that the pull force required to pull the main parachute closing pin is reduced. Further disclosed is a parachute container using the novel parachute ripcord pull force reducer, and methods for manufacturing and/or modifying a parachute to operate with various embodiments of the ripcord pull force reducer in accordance with the instant disclosure.
    Type: Grant
    Filed: December 9, 2020
    Date of Patent: November 21, 2023
    Assignee: uninsured United Parachute Technologies, LLC
    Inventor: Ty Philip Bowen
  • Patent number: 11820532
    Abstract: Provided is a system for releasing an Unmanned Aerial Vehicle (UAV), including: a capsule including: a UAV including a controller; and a release actuator configured to release the UAV from the capsule; wherein the capsule is configured to be at least one of launched and deployed; the system further includes: at least one sensor; a release condition evaluation module, connected with the at least one sensor; and a release command module, connected with the release condition evaluation module, and configured to activate the release actuator upon at least one release condition being met; wherein the process of deploying the capsule and/or launching the capsule is a separate process from the process of releasing the UAV from the capsule.
    Type: Grant
    Filed: January 9, 2020
    Date of Patent: November 21, 2023
    Assignee: SPEAR U.A.V LTD
    Inventor: Gedalia Kuperman
  • Patent number: 11820531
    Abstract: Features for in-flight recovery of an unmanned aerial vehicle (UAV). A towline may be deployed by a host aircraft in-flight to recover an in-flight target UAV. The towline or portion thereof may be oriented nearly vertical. The towline may have a fitting thereon. A capture mechanism on the target UAV may have one or more deployable flaps that engage with the near vertical towline and fitting. The flaps may stow to secure the target aircraft to the towline and fitting. The host aircraft may then retract the towline to pull in the target UAV to the host aircraft using a hoist system having a winch. A latching system located in a pylon of the host aircraft, which may be under a wing, may have a towline connector that engages with and secures the target UAV. The host aircraft may have multiple hoist systems for deployment and/or recovery of multiple target UAV's.
    Type: Grant
    Filed: November 17, 2021
    Date of Patent: November 21, 2023
    Assignee: General Atomics Aeronautical Systems, Inc.
    Inventors: Michael Joseph Allwein, James William Groves, Kevin David Koller, Ryan Bylard, Roy Hultenius
  • Patent number: 11814183
    Abstract: A strap that may be used to secure equipment (e.g., a bag) to the parachute harness of a parachutist. The strap may provide adjustability of an effective strap length to assist in positioning the suspended equipment relative to the parachutist. The strap may include quick-release features that allow the suspended equipment to be quickly and easily disengaged (e.g., once the parachutist has landed). In turn, a transition to ground operations in which the equipment is in use may occur quickly and without heavy rigging or additional containers for stowing the equipment during the jump. In turn, the strap may be carried with the parachutist during ground operations without significant additional weight.
    Type: Grant
    Filed: November 12, 2021
    Date of Patent: November 14, 2023
    Assignee: IDIS CORP.
    Inventor: Brian Parker
  • Patent number: 11801930
    Abstract: A wing for an aircraft including a fixed wing and a high-lift device movable between a retracted position and an extended position. The high-lift device includes a movable fence. The fence is movable between a first position in which the fence does not protrude beyond an outer surface of the high-lift device and a second position in which the fence protrudes beyond the outer surface of the high-lift device. The fence is in the first position when the high-lift device is in the retracted position and in the second position when the high-lift device is in the extended position. Further, an aircraft with such a wing, a high-lift device and a fence as well as use of a high-lift device and a fence are provided.
    Type: Grant
    Filed: March 22, 2021
    Date of Patent: October 31, 2023
    Inventors: Luc Andreani, Tobias Schreck, Igor Stab
  • Patent number: 11794878
    Abstract: An assembly comprising a first part and a second part, the assembly comprising a disconnectable coupling system provided with a mechanical fuse for securing the first part and the second part according to an axis of movement up to a breaking threshold. The assembly comprises at least one single-use friction brake interposed between the first part and the second part, the friction brake braking a movement of the first part with respect to the second part after the mechanical fuse has broken.
    Type: Grant
    Filed: April 27, 2022
    Date of Patent: October 24, 2023
    Inventor: Laurent Ruet
  • Patent number: 11794929
    Abstract: An ejection method (100) for ejecting at least one payload such as a satellite. The ejection method includes a step (108) of ejecting the payload from a spacecraft that is driven by a continuous propulsion force when the satellite is ejected.
    Type: Grant
    Filed: January 11, 2019
    Date of Patent: October 24, 2023
    Inventors: Isabelle Quinquis, Siegfrid Chavy, Jean-Michel Sannino
  • Patent number: 11794908
    Abstract: A flow body for an aircraft with an integrated de-icing system. The flow body includes a front skin, an internal structural component, a lever having first and second ends, with an attachment point in-between, and an actuator. The actuator is spaced inside the front skin. The lever extends from the actuator to a front skin inner surface, the first end coupling with the front skin, and the second end coupling with the actuator. The attachment point is swivably supported on the internal structural component. The attachment joint is closer to the first end than the second end. The lever and the actuator apply an impulsive force in a transverse direction to the lever, such that the lever rotates around the attachment point, and such the first end urges the front skin to locally elastically deform for removing ice accretion from an outer side of the front skin.
    Type: Grant
    Filed: August 27, 2020
    Date of Patent: October 24, 2023
    Inventor: Stefan Bensmann