Abstract: A mobility vehicle hub configured to function as a terminal for an air mobility vehicle, a ground mobility vehicle, or a water mobility vehicle, includes a plurality of layers through a combination of: a water layer connected to the surface of water and having an entrance for a water mobility vehicle; a port layer having a take-off and landing pad for an air mobility vehicle; or a ground layer configured to be connected to a ground and having an entrance for a ground mobility vehicle, wherein an elevation passage is provided between the layers, the elevation passage has an internal space extending in an up-down direction of the mobility vehicle hub, the internal space is connected to each of the water, port and ground layers, and the air mobility vehicle, the ground mobility vehicle, or the water mobility vehicle is lifted or lowered through the internal space.

Abstract: This specification describes systems for unmanned aerial vehicle carrying and deployment. In some examples, an unmanned vehicle includes a drive system and a chassis. The chassis includes a platform for carrying an unmanned aerial vehicle and a retainer configured to secure the unmanned aerial vehicle to the platform while the drive system drives the unmanned vehicle. The clamping system includes at least a first rotating bar and a protrusion from the first rotating bar.

Abstract: A landing zone arrangement is disclosed for aircraft capable of vertical take-off. The arrangement includes a plurality of segments that form a landing zone in an operating state, a storage space for at least partially storing the segments in a stored state, and a base with a rotatable rotor element in order to rotate the segments for transfer between the operating state and the stored state. The landing zone arrangement allows a lighter technical design as the individual segments are removably secured to the rotor element, and a securing unit of the arrangement is designed to fasten the removable segments to the rotor element for transfer into the operating state and to release this fastening for transfer into the stored state. A lifting unit is provided in order to move the removable segments in the direction of the rotor element when transferring into the operating state.

Abstract: A hybrid aircraft system uses a combination of direct propeller driven gas engine and electric motor power to provide vertical thrust and control for hover of the aircraft. Furthermore, a portable launch/recovery system is configured for use with an aircraft such as a Vertical Takeoff and Landing (VTOL) Unmanned Air Vehicle (UAV). The system is configured to enable ships with limited available deck space to become UAV-compatible.

Abstract: An unmanned aerial signal relay includes an unmanned aerial vehicle, including a communication relay unit and at least one antenna, communicatively connected to the communication relay unit; a tether comprising at least two wires and at least one fiber optic cable, the wires and cable communicatively connected to the unmanned aerial vehicle; and a surface support system comprising a spool physically connected to the tether and a ground-based receiver communicatively connected to the at least one fiber optic cable, wherein the unmanned aerial vehicle is powered by electrical energy provided by the at least two wires, and wherein the communication relay unit is configured to relay signals received from the at least one antenna via the fiber optic cable to the ground-based receiver. Various systems and methods related to an unmanned aerial signal relay are also described.

Abstract: A mooring latch includes a passive foundation portion and a latching portion. The latching portion includes a mechanism, a conical surface shaped to mate with a conical surface of the passive portion, a connector for connection to a mooring structure and permitting rotation about a horizontal axis. The mechanism has a latched configuration that mates the conical surfaces and permits rotations about a shared vertical axis of the conical surfaces. A mooring line threaded through the passive and latching portions and equipped with one or more stops may be used to guide the latching portion to or from the passive portion and to actuate latching or unlatching or the mooring latch.

Abstract: Apparatus and methods for marine capture of an unmanned aerial vehicle (UAV) using water for braking and damping are described. An example capture device is for capturing a UAV aboard a marine vessel located in a body of water. The capture device includes a mounting frame and a capture frame. The mounting frame is configured to be coupled to the marine vessel. The capture frame is configured to be rotatably coupled to the mounting frame. The capture frame is rotatable relative to the mounting frame about an axis of rotation. The capture frame includes a braking member configured to be submerged in the body of water. The braking member is configured to oppose rotation of the capture frame relative to the mounting frame based on a braking force to be applied to the braking member by the body of water.

Abstract: An example UAV landing structure includes a landing platform for a UAV, a cavity within the landing platform, and a track that runs along the landing platform and at least a part of the cavity. The UAV may include a winch system that includes a tether that may be coupled to a payload. Furthermore, the cavity may be aligned over a predetermined target location. The cavity may be sized to allow the winch system to pass a tethered payload through the cavity. The track may guide the UAV to a docked position over the cavity as the UAV moves along the landing platform. When the UAV is in the docked position, a payload may be loaded to or unloaded from the UAV through the cavity.

Abstract: An aircraft platform includes a base, a landing pad, a level sensor, and at least one actuator. The landing pad is supported on the base. The level sensor is configured to detect an inclination angle of at least one of the landing pad and the base with respect to a level ground. The at least one actuator is connected to change an inclination of the landing pad.

Abstract: An example UAV landing structure includes a landing platform for a UAV, a cavity within the landing platform, and a track that runs along the landing platform and at least a part of the cavity. The UAV may include a winch system that includes a tether that may be coupled to a payload. Furthermore, the cavity may be aligned over a predetermined target location. The cavity may be sized to allow the winch system to pass a tethered payload through the cavity. The track may guide the UAV to a docked position over the cavity as the UAV moves along the landing platform. When the UAV is in the docked position, a payload may be loaded to or unloaded from the UAV through the cavity.

Abstract: A landing device for landing an aircraft thereon. The landing device comprises a first group of supporting elements arranged next to each other in a first direction, each supporting element configured to support a portion of a body or a portion of a wing of the aircraft. Each supporting element is further configured to bow when loaded by the mass of the body portion or the wing portion supported by the respective supporting element.

Abstract: A sleep system comprises an air posturizing module having a case, the case comprising a first case section extending medially along a length of the case to define a movable first section, a second case section adjacent to the first case section and extending along a length of the case to define a movable second section, a third case section defining a third posturing section, a fourth case section extending medially along a length of the case to define a movable third section, and a fifth case section extending medially along a length of the case to define a movable fourth section. One or more first air chambers are carried in the first, third and fourth case sections to provide a first sleep area, and one or more second air chambers are carried in the second, third, and fifth module sections to provide a second sleep area.

Abstract: A construction device for an offshore wind turbine foundation with piling performed later. The construction device comprises an offshore wind turbine foundation (1), a pile casing (2) and a sleeve (3). The pile casing (2) is used for the installation of a steel pile (4) and arranged at the bottom of the offshore wind turbine foundation (1). The lower end of the sleeve (3) is detachably connected with the upper end of the pile casing (2). A construction method for an offshore wind turbine foundation with piling performed later is also provided.

Abstract: A rocket landing stabilization system can include one or more upright support structures such as posts, columns, or walls, from which one or more stabilizing elements can be supported. The stabilizing elements can be used to stabilize a rocket as it lands at a landing site. The rocket landing stabilization system can also include a cradle, funnel, or cone to catch or otherwise support a rocket as it lands at the landing site. The rocket landing stabilization system can be located on land or at sea.

Abstract: A surface travel system for military aircraft is provided that enables efficient, quiet, and safe ground operations of one or more aircraft in a wide range of military missions and operations. The surface travel system includes controllable onboard drive means that effectively drives one or more of the aircraft's wheels to move the aircraft autonomously, efficiently, quietly, and safely on any travel surface required for a military mission. The present invention allows the rapid safe deployment of multiple aircraft from tight spaces and enhances the readiness and availability of aircraft for a wide range of military operations.

Abstract: Disclosed are various embodiments for flight guidance of an aircraft or other aerial vehicle using one or more lenticular arrays. An aircraft control application may be employed to determine whether a location of an aircraft is within a predefined distance of a lenticular array that defines an optimal flight corridor. If the aircraft is at a location within the predefined distance, the aircraft control application may attempt to visually locate the lenticular array using an imaging device. A position of the aircraft relative to the optimal flight corridor may be determined based at least in part on a visual identifier identified in a digital image of the lenticular array. A flight of the aircraft may be controlled to follow a flight path falling within the optimal flight corridor based at least in part on the visual identifier.

Abstract: The invention is a watercraft to aircraft refueling system (“WARS”). A WARS is a refueling system based from a watercraft, such as a surface ship or submarine. A WARS would typically include an elevation apparatus to lift a refueling hose above the water. The elevation apparatus can compose a lifting or swiveling mechanism. In some embodiments both a lifting and swiveling mechanism is used. The WARS lifts the refueling hose above the water, allowing an aircraft to engage with the WARS. The refueling hose may also include a telescoping mechanism or a rotor apparatus or a pressurized water nozzle system to elevate the refueling hose and assist in engaging a WARS with an aircraft.

Abstract: A platform (1) for the landing of an aircraft on a boat (B), comprising at least one lower base (2) fixed on the boat (B), and at least one upper base (21), fixed on an aircraft landing footboard (3), wherein a plurality of first curved tubular sections (4), parallel one to each other, are welded inside the frame of the lower base (2), while a plurality of second curved tubular sections (5), parallel one to each other and placed orthogonally with respect to said first tubular sections (4), are welded inside the frame of the upper base (21); said tubular sections (4, 5) are bounded together by means of sliding shaped structures, which are driven through actuating and control means.

Abstract: A rocket landing stabilization system can include one or more upright support structures such as posts, columns, or walls, from which one or more stabilizing elements can be supported. The stabilizing elements can be used to stabilize a rocket as it lands at a landing site. The rocket landing stabilization system can also include a cradle, funnel, or cone to catch or otherwise support a rocket as it lands at the landing site. The rocket landing stabilization system can be located on land or at sea.

Abstract: Examples of the present disclosure are related systems and methods for lead-ins for anti-fatigue floor mats. More particularly, embodiments disclose lead-ins with tapered ends with variable heights that transition from a floor level to a mat surface level to enable drop stitch-mats to be used in residential and commercial areas.

Abstract: An oil containment system aboard a vessel includes a pneumatic system to provide power to a winch and reel assembly containing boom whereby the pneumatic supply is capable of simultaneously powering the winch-reel assembly for boom deployment through inflatable gas fed to a pneumatic motor while also inflating the boom. The inflation of the boom is accomplished by diverting, all or any portion thereof, the inflatable gas from a pneumatic supply through a hose that runs concurrently on the outside of the boom. The pneumatic supply originates from a single pneumatic system powering both the winch and reel assembly as well as associated brake and feeding inflatable gas pressure to the inflation hose running concurrently with the boom. The system can be utilized to confine a discharge of a floating material such as hydrocarbons floating on the surface from a vessel or structure.

Abstract: A mechanical connecting link for tow straps and pintle hitches configured to quickly and easily disassemble even during complex pulling scenarios. The mechanical connecting link also is configured to retain its structural integrity even during heavy loads. The mechanical connecting link has at least two modular “wide body” connector components on which looped tow straps may engage. The modular “wide body” connector component configured to keep the bend radius of any engaged tow strap large enough to prevent abrasion and to resist damage to the tow strap loop during pulling scenarios.

Abstract: Aspects of the disclosure provide a flex connection for high altitude balloon applications. During operation flex connection allows a payload of a high-altitude balloon to remain level when an envelope of the balloon is tilted, in order to change the direction of the balloon. As an example, a system may include a balloon envelope, a payload, a cable between the balloon envelope and the payload, and a flex connection on the cable. The flex connection enables the payload to remain level relative to the ground when the balloon is in flight and the balloon envelope is tilted relative to the payload. The flex connection includes a top portion, a plurality of discs, and a bottom portion.

Abstract: An overflow prevention dispensing container comprising a portable container having at least one handle means, a nozzle, at least one air vent, at least one liquid fill aperture, and fill aperture cover; a dispensing handle having a valve mechanism; and at least one release; an automatic shutoff sensing means for sensing the level of fluid in a receiving tank and stopping the flow of liquid into the receiving tank when it is full, whereby the container is placed in a position to dispense liquid to the receiving tank, the operator activates the dispensing handle allowing liquid to freely flow into the receiving tank until the apparatus senses the level of the liquid in the receiving tank to be desired level at which time the flow will automatically be stopped.

Abstract: The present invention relates broadly to a floating structure and more particular to a floating structure formed by a plurality of modular floating units, a method for forming a floating structure, and a method for stabilising a plurality of modular floating units lined abreast.

Abstract: Disclosed is an autonomous landing system for landing a vertical take-off and landing (VTOL) aircraft. The autonomous landing system may include a flight control system having radar sensors, altimeters, and/or velocity sensors. The flight control system can include a processor to provide pitch, roll, and yaw commands to the VTOL aircraft based at least in part on data from the radar sensors, the altimeters, and/or the velocity sensors. The flight control system can be used to navigate and land the VTOL aircraft on a movable object, such as a ship.

Abstract: The invention is a watercraft to aircraft refueling system (“WARS”). A WARS is a refueling system based from a watercraft, such as a surface ship or submarine. A WARS would typically include an elevation apparatus to lift a refueling hose above the water. The elevation apparatus can compose a lifting or swiveling mechanism. In some embodiments both a lifting and swiveling mechanism is used. The WARS lifts the refueling hose above the water, allowing an aircraft to engage with the WARS. The refueling hose may also include a telescoping mechanism or a rotor apparatus or a pressurized water nozzle system to elevate the refueling hose and assist in engaging a WARS with an aircraft.

Abstract: An aircraft guidance system includes a reviewing and video synchronization device connected to a display panel. The display panel receives and displays guidance status of an aircraft. The reviewing and video synchronization device includes an operator panel, a video recording unit and a built-in recording unit. The operator panel includes a display screen and a plurality of keys. The display screen and the display panel synchronizedly display information. The video recording unit records the information displayed on the display screen. The built-in recording unit records the scanning signals and time stamps received by the display panel.

Abstract: A procedure and system are provided for automatically landing an aircraft, particularly an unmanned aircraft on a moving, particularly floating landing platform, for example, on an aircraft carrier, the aircraft being equipped with an automatic navigation device and an automatic landing control device. The procedure includes detecting the position of an intended landing spot, detecting motion data of the landing platform, determining at least one imminent point in time at which the landing spot takes up a reference position, transmitting the point in time and the reference position of the landing spot to the landing control device of the aircraft, and controlling the aircraft such that it reaches the landing spot at the point in time.

Abstract: A cold water piping system including a floating platform having horizontal and vertical surfaces, the platform including a moon pool generally in the middle of the horizontal surface in the form of a vertical cylinder with four recesses having a rectangular shape, an articulating interface suspended directly from the platform, the interface including a tubular shape made of fabric and a bellows assembly disposed at a bottom portion thereof. The system also includes at least two suspension cable assemblies secured to the platform, where the at least two suspension cables cross the moon pool, vertically mounted modular elements, where ends of the suspension cable assemblies are fastened to a top modular element at four diametrically opposed points, and a strainer having sea water intakes including a counterweight connected to the lowest modular element. The system also includes winches disposed on the horizontal surface of the platform and deployment cables connected to the strainer and winches.

Abstract: The present invention discloses a take-off and landing system for carrier aircraft, which comprises a takeoff device and a landing device; said takeoff device is a bow side launch deck which is located at the front part of the aircraft carrier and extends from a track groove provided with a track guider; said landing device is a stern side rear bridge which is located at the rear part of the aircraft carrier and extends from a treadmill belt-type runway. The invention also discloses a take-off and landing method corresponding to the take-off and landing system. The take-off and landing system and the method thereof enhances advantages and avoids weaknesses with regard to the existing take-off technologies, reduces the difficulty and risk in the existing landing technology. The present invention is suitable for the take-off and landing of all kinds of carrier aircrafts and also makes a design to build a “pocket-sized aircraft carrier” become possible.

Abstract: Launch vehicle systems and methods for landing and recovering a booster stage and/or other portions thereof on a platform at sea or on another body of water are disclosed. In one embodiment, a reusable space launch vehicle is launched from a coastal launch site in a trajectory over water. After booster engine cutoff and upper stage separation, the booster stage reenters the earth's atmosphere in a tail-first orientation. The booster engines are then restarted and the booster stage performs a vertical powered landing on the deck of a pre-positioned sea-going platform. In one embodiment, bidirectional aerodynamic control surfaces control the trajectory of the booster stage as it glides through the earth's atmosphere toward the sea-going platform. The sea-going platform can broadcast its real-time position to the booster stage so that the booster stage can compensate for errors in the position of the sea-going platform due to current drift and/or other factors.

Abstract: A system for automatic or auto pilot controlled landing of air vehicle (2) with an undercarriage (10) with a substantially plane lower side, at a stationary or mobile landing place is described. The system is primarily characterized in that the landing plate is settable after two axes in roll and pitch, by a set mean controlled in relationship to the air vehicle and the horizontal plane. The air vehicle (2) and the landing plate (3) are provided with transmitter and receiver which define and communicate the mutual distance and the relative angles between the landing plate (3) and the undercarriage (10). Said set means is arranged to set said two axes such that the landing plate (3) will be substantially parallel to the lower side of the undercarriage (10).

Abstract: The density of “ready for take-off” aircraft on a flight deck of a ship is increased by orienting the aircraft at orientation angles between 20° and 180° from dead ahead. Preferred ships are modified from, or utilize a design derived from an existing ship, especially a large containership or other commercial ship. One or more payload staging decks can be advantageously located under the flight deck. All suitable types of aircraft are contemplated, including especially helicopters, tilt-rotors, and other rotorcraft. In preferred embodiments at least three, five, or ten aircraft are vertical take-off and landing (VTOL) aircraft. Also in preferred embodiments, at least five of the first plurality of the aircraft are capable of carrying a payload greater than 20,000 pounds.

Abstract: An offshore marine port including a plurality of individual modules of the same dimensions and alike size and shape, being attached to form a singular large platform and having apparatus either fixed or mobile, robotic or manned, pertaining to the handling and efficient movement of bulk; break bulk; liquids or cargo containers while being off-loaded or on-loaded to either bulk or break bulk vessels or barges; liquids vessels or barges; or cargo container vessels or barges. The ‘modules’ are constructed in a way as to most effectively provide for the movement of bulk; break bulk; liquids or cargo containers while transiting through the intended structure. The mono semi-submersible sections of each module, serves to allow for more usable arrears for below main deck operations, while still providing for ample research and development spaces and supporting laboratories.

Abstract: A portable aircraft landing system comprises an inflatable mat provided with gas outlets, in cooperation with inflation apparatus.

Abstract: The density of “ready for take-off” aircraft on a flight deck of a ship is increased by orienting the aircraft at orientation angles between 20° and 180° from dead ahead. Preferred ships are modified from, or utilize a design derived from an existing ship, especially a large containership or other commercial ship. One or more payload staging decks can be advantageously located under the flight deck. All suitable types of aircraft are contemplated, including especially helicopters, tilt-rotors, and other rotorcraft. In preferred embodiments at least three, five, or ten aircraft are vertical take-off and landing (VTOL) aircraft. Also in preferred embodiments, at least five of the first plurality of the aircraft are capable of carrying a payload greater than 20,000 pounds.

Abstract: An offshore depot having a vertically symmetric hull, an upper inwardly-tapered wall and a lower outwardly-tapered wall that produce significant heave damping in response to heavy wave action. Ballast is added to the lower and outermost portions of the hull to lower the center of gravity below the center of buoyancy. The offshore depot includes a tunnel formed within or through the hull at the waterline that provides a sheltered area inside the hull for safe and easy launching/docking of boats and embarkation/debarkation of personnel. When the watertight tunnel doors are all shut, the tunnel may be drained to create a dry dock environment within the hull. The offshore depot includes berthing and dinning accommodations, medical facilities, workshops, machine shops, a heliport, and the like.

Abstract: An amphibious aircraft trailer includes a frame supported on a wheel/suspension bearing axle for movements over a roadway surface. Incorporated into the trailer is a cradle configured to engage a hull of the amphibious aircraft when it is loaded and unloaded in water conditions. A lift mechanism interposed between and coupled to the frame and the cradle is operable to displace the cradle vertically with respect to the frame such that landing gear associated with the amphibious aircraft can be extended or retracted while on the trailer. The trailer may also include a plurality of wheel tracks aligned with the landing gear to facilitate the aircraft's loading and unloading in its ground based mode of operation.

Abstract: A carrier frame on a vessel for local water motion includes a carrier frame (2); an actuator system (4, 5, 6) adapted for translating the carrier frame (2) along a z-axis and rotating the carrier frame around an x-axis and an y-axis; a sensor system (8) for sensing z-axis translational movement and x-axis and y-axis rotational movements of the vessel; and a control system (9) generating control signals for driving the actuator system in response to the sensor signals. The actuator system includes at least three cylinder-piston-units each having a longitudinal axis (14), which longitudinal axes are mutually parallel in a rest position. Each cylinder-piston unit has an upper support (15) for supporting the carrier frame on said cylinder-piston-unit and a lower support (16) for supporting the cylinder-piston-unit on a base. The upper support and/or lower support allows for rotational movement.

Abstract: A motion compensation system for a helipad on a vessel includes a sensor for measuring a parameter related to at least one or pitch and roll of the vessel. The system includes a first actuator functionally coupled to the helipad to move the helipad translationally with respect to the vessel in response to the measured at least one of pitch and roll of the vessel.

Abstract: A system to launch and recover an Unmanned Aerial Vehicle (UAV) aircraft has a pole member attached to a deck of a ship. An arm member is attached to the pole member and extends away from the pole member in an approximately horizontal direction. The arm member is able to move rotationally and vertically on the pole member. An attachment mechanism is attached to a distal end of the arm member for holding and capturing the UAV aircraft. Momentum of the UAV aircraft causes the arm member to move rotationally around and vertically on the pole member when the UAV aircraft is coupled to the attachment mechanism.

Abstract: A double level flight deck type aircraft carrier is disclosed to include a second level of flight deck so that aircraft launching and landing operations can be separately performed on the decks. The double deck design doubles the operation capacity and capability.

Abstract: A drill ship is provided for conducting subsea operations, including intervention, maintenance and workover operations. The ship includes a hull having a substantially wide beam-to-length ratio and a deckspace. An automated system for handling tubulars and risers is mounted to the deck space, along with a pipe racking system. The deckspace includes a heavy-lift heave crane for handling seafloor operations and a medium duty crane mounted over the deckspace. The ship is configured to provide heavy lift subsea construction operations including 16-inch riser well intervention and workover programs, connected riser completion operations, and riserless tophole drilling and casing operations. The ship is also able to perform connected riser remedial drilling and slim hole well construction. The ship maximizes environmental efficiency in both construction and use, and provides a stable and safe work and living environment for operations personnel.

Abstract: Methods and apparatus for marine deployment according to various aspects of the present invention may operate in conjunction with a floatable housing adapted to be deployed by a marine vehicle. The floatable housing may be adapted to be launched from a marine vehicle and rise to the surface. Assets, such as an unmanned aerial vehicle, may be deployed from the surfaced floatable housing.

Abstract: A floatable vessel is associated with an excavated area or foundation such that the floatable vessel rises and falls with changes in the water level of the surrounding environment. The foundation comprises a plurality of stabilizing posts that include telescopic sections where an upper telescopic section is connected to the floatable vessel. As the water level in the foundation rises or falls, the telescopic sections extend or retract as the buoyant floatable vessel moves with the water level. This action maintains the floatable vessel's connection with the foundation at various water levels. When there is no water within the foundation, or when the water level is sufficiently low, the floatable vessel rests on a plurality of pillars within the foundation. A tether cable is provided within the stabilizing posts as a back-up securing structure. Pivoting grates bridge the gap between the floatable vessel and the surrounding land.

Abstract: A double level flight deck type aircraft carrier is disclosed to include a second level of flight deck so that aircraft launching and landing operations can be separately performed on the decks. The double deck design doubles the operation capacity and capability.

Abstract: A motion compensation system for a helipad on a vessel includes a sensor for measuring a parameter related to at least one or pitch and roll of the vessel. The system includes a first actuator functionally coupled to the helipad to move the helipad translationally with respect to the vessel in response to the measured at least one of pitch and roll of the vessel.

Abstract: Systems and methods for a stable maritime helicopter platform are disclosed. In one embodiment, a ship that may be converted into a spar buoy includes a flipping mechanism to convert the ship to the spar buoy, a takeoff and landing platform for helicopters and other VTOL vehicles, and an actuation and balance system to deploy the platform.

Abstract: An unmanned floating platform is provided for continual surveillance at a station-keeping position at sea. The platform is equipped to dispatch an unmanned vehicle to conduct at least one of observation and rendezvous. The platform includes a hull, first and second hangers, and a liquid storage compartment. The hull has a submerged portion and a floating portion. The first hanger is equipped for stowing, deploying and retrieving a self-propelled unmanned vehicle and is substantially disposed in the floating portion. The second hanger houses equipment for electrical power and on-board functions. The liquid storage compartment supplies fuel to the on-board equipment and to the unmanned vehicle. For static stability, the compartment is disposed in the submerged portion. The platform may also include a superstructure for housing sensor equipment. The superstructure can be disposed above at least one of the first and second hangers. The second hanger may additionally house a tetherable observation aerial post.