Abstract: A load transport system having a load carrier and at least one load receiving device which for receiving the load is fastened to the load carrier, and at least three positioning cables and at least three suspension devices, each suspension device has at least one positioning cable winch for winding and unwinding one of the positioning cables. The load carrier is suspended from the suspension devices by the positioning cables. The load carrier and the load receiving device fastened thereto are relocatable by activating the positioning cable winches, and the load carrier has at least one multi-cable suspension to which at least two of the positioning cables are connected via cable connectors. Each of the cable connectors is mounted on the multi-cable suspension to be pivotable about at least two pivot axes aligned to be mutually orthogonal, and all pivot axes of the cable connectors intersect in a common intersection point of this multi-cable suspension.

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: Described are systems and methods for adjusting a takeoff platform for a vertical takeoff and landing (VTOL) aerial vehicle. The described systems and methods allow a VTOL aerial vehicle to be oriented prior to takeoff to reduce the effects that a VTOL aerial vehicle may experience due to weather conditions at takeoff. In view of the aerodynamic characteristics of a VTOL aerial vehicle and certain weather conditions, a heading, pitch, and/or roll of the VTOL can be provided to counteract the effects the VTOL may experience from the weather conditions at takeoff.

Abstract: Systems and methods for receiving a descending rocket, which may be at sea. The rocket may descend vertically with the nose higher than the nozzle. The rocket body may be angled as it descends. A boom arm with hooks may extend at an angle to the rocket body to engage a cable suspended by a semisubmersible platform at sea. The platform may include a dampened cable and lateral straps for securing and rotating the rocket into a horizontal orientation. The platform may receive a ship and purge water to elevate the platform for placing the horizontal rocket onto the ship.

Abstract: One variation of a tram system includes: a chassis; a latch configured to selectively engage a latch receiver mounted to an aircraft; an alignment feature adjacent the latch and configured to engage an alignment receiver mounted to the aircraft and to communicate acceleration and braking forces from the chassis into the aircraft; an optical sensor facing upwardly from the chassis; a drivetrain configured to accelerate and decelerate the chassis along a runway; and a controller configured to detect an optical fiducial arranged on the aircraft in optical images recorded by the optical sensor adjust a speed of the drivetrain to longitudinally align the alignment feature with the alignment receiver based on positions of the optical fiducial detected in the optical images, trigger the latch to engage the latch receiver once the aircraft has descended onto the chassis, and trigger the drivetrain to actively decelerate the chassis during a landing routine.

Abstract: System for multiple use of space rockets equipped with spreadable arms and sliding engines covers, and for said space rockets a vertical landing method on two movable gantries situated on a specific sea ship or on a solid ground. Said space rockets comprise steering flaps and a dividable sectional load cover. The specific sea ship comprises specific joined hulls, two horizontally movable decks and tunnels with ballasting wagons. The specific sea ship has installed a landing station for the space rockets. The landing station comprises hangers, grasping wagons and two movable ship gantries. The hangers comprise rotating wedges. The gantries comprise damping wagons. The system comprises also two movable ground gantries and a specific movable ground crane all situated on a solid ground that together create a multi-task station for the space rockets hanging up, reloading, launching, and landing.

Abstract: In various embodiments, specialized vehicle launch systems and methods are provided to enable personnel to launch and operate one or more UAVs from the safety of a vehicle or other mobile location. In various embodiments, a launch system comprises a launch device and an operator terminal. The launch device is adapted to be mounted on an exterior surface of a vehicle and is communicably coupled to the operator terminal, which is operable from the interior of the vehicle. The vehicle launch system allows an operator to control one or more UAVs from inside the vehicle, without requiring the operator to step outside of the vehicle to interact with the UAV or launch device.

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: Systems and methods for minimizing an aircraft turn radius are disclosed. For example, a method to minimize an aircraft turn radius may include receiving an activation signal from an activation switch. The activation switch may be configured allow a selected turn. The method may also include receiving a turn command in a direction of the selected turn. The method may also include transmitting a turn signal to an actuator operatively coupled to a nosewheel assembly. The actuator may rotate a shaft in the direction of the selected turn to move at least one nosewheel from a first angle to a second angle with reference to a longitudinal axis of the aircraft. The method may also include transmitting a thrust signal to at least one of a plurality of thrust-producing devices operatively coupled to a first wing and a second wing operatively coupled to the aircraft.

Abstract: Methods and apparatus to recover unmanned aerial vehicles with kites are disclosed. A disclosed example apparatus includes a tether line to be supported by a kite at a distal end thereof, and a release to deploy and expand a parafoil from at least one of the tether line or the kite in response to the aircraft contacting the tether line.

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. A disclosed example apparatus to recover an aircraft includes a mast extending from a base, a boom extending from the mast at a first end of the boom to a second end of the boom opposite the first end, a tether line extending between the mast to the base and guided by the boom, a portion of the tether line extending between the second end of the boom and the base, and a mount to operatively coupled the a kite to the tether line, the kite to support the tether line as the aircraft contacts the portion for recovery thereof.

Abstract: The present invention relates to the field of the unmanned aerial vehicles, in particular to a suspended landing and take-off and management base.

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: In-flight recovery of an unmanned aerial vehicle (UAV). A towline may be deployed by a host aircraft in-flight in order to recover a target UAV that is also in-flight. A reel on the host aircraft may pay out the towline having a fitting thereon. A catch on the target UAV may engage with the fitting on the towline, and the reel may then retract the towline to thereby pull in the target UAV to the host aircraft. The target UAV may then securely attach with the host aircraft.

Abstract: A hybrid airship-aerostat includes a hull, a motor, a fin, a controller, and a bridle system. The motor is coupled to the hull and is configured to rotate between a thrust configuration and a lift configuration. The motor is configured to generate a lift force, a thrust force, or a combination thereof. The fin is coupled to a tail of the hull and is configured to provide directional control of the hull. The controller is configured to operate the motor and the fin to pilot the hull. The bridle system is configured to removably couple to a first end of a tether.

Abstract: A payload elevator system and method are disclosed, configured for providing a plurality of alternative payload elevator configurations, each payload elevator configuration being configured for transporting a payload module. A composite air vehicle configuration is also provided, including a respective payload elevator configuration, the payload elevator configuration being defined by and provided by the payload elevator system, and also including at least one payload module reversibly engaged to the payload elevator configuration via a corresponding engagement and release system.

Abstract: One variation of a tram system includes: a chassis; a latch configured to selectively engage a latch receiver mounted to an aircraft; an alignment feature adjacent the latch and configured to engage an alignment receiver mounted to the aircraft and to communicate acceleration and braking forces from the chassis into the aircraft; an optical sensor facing upwardly from the chassis; a drivetrain configured to accelerate and decelerate the chassis along a runway; and a controller configured to detect an optical fiducial arranged on the aircraft in optical images recorded by the optical sensor adjust a speed of the drivetrain to longitudinally align the alignment feature with the alignment receiver based on positions of the optical fiducial detected in the optical images, trigger the latch to engage the latch receiver once the aircraft has descended onto the chassis, and trigger the drivetrain to actively decelerate the chassis during a landing routine.

Abstract: Systems and methods for multi-armed robotic capture devices are disclosed. The systems and methods for multi-armed robotic capture devices include a base that is configured to attach to a robotic arm or a servicer and having a tether. The systems and methods for multi-armed robotic capture devices include a body that is coupled to the base via the tether. Additionally, the systems and methods for multi-armed robotic capture devices include a plurality of tentacles coupled to the body and configured to grip a target object. The systems and methods for multi-armed robotic capture devices also include a plurality of tiles positioned on each tentacle of the plurality of tentacles and configured to apply a shear force on the target object to grip the target object using an adhesive force.

Abstract: An anchoring platform is disclosed for captive aircraft that addresses problems when handling captive aerostats, including excessive workload required to switch between flying and anchored states. The anchoring platform includes an anchoring device. Cords, together with a confluence point, are wound into the anchoring device, by the winch. The structure for anchoring the captive aircraft is the cradle which bears the aerostat, while the winch exerts tension to hold same static in the structure.

Abstract: Launch and/or recovery for unmanned aircraft and/or other payloads, including via parachute-assist, and associated systems and methods are disclosed. An example unmanned aerial vehicle (UAV) system includes a lift device, a parachute, and a capture line. The lift device includes a canister. The parachute is stowed in and deployable from the canister. The capture line is attached to the parachute and to a line control device. The capture line is configured to be engaged by a capture device located at an end of a wing of a UAV.

Abstract: An airborne delivery system employs unmanned aerial vehicles (UAVs) released from an airborne platform, such as a Joint Precision Airdrop System (JPAD), to more accurately deliver supplies. The airborne delivery system is configured to be mounted on a JPAD, or similar airborne platform. As with a conventional JPAD, the JPAD is then released from an airborne vehicle. After a certain amount of flight time, one or more UAVs are released mid-flight from the airborne delivery system.

Abstract: A tethered aerial system includes an on-board fuel cell for powering on-board electronics and a tether cable which is less conductive than air. The tether cable includes a pipe for carrying a flow of gas to the fuel cell and/or maintain the gas level in a lighter-than-air platform, so that the tethered aerial system can remain operational for an extended period of time. The system is particularly applicable for maintaining communication links in remote areas, agriculture and applications in the IoT (Internet of Things), event coverage, interactive marketing, for post-disaster situations in rural areas and at mining sites or construction sites in remote environments. The system also is immune to rays.

Abstract: A barge for recovery of a rocket launch vehicle is proposed, which can recover a launch vehicle from the sea onto the land in safety during launch vehicle recovering work. The barge can recover the launch vehicle in safety by effectively preventing a slope of the structure which supports the launch vehicle.

Abstract: One variation of a tram system includes: a chassis; a latch configured to selectively engage a latch receiver mounted to an aircraft; an alignment feature adjacent the latch and configured to engage an alignment receiver mounted to the aircraft and to communicate acceleration and braking forces from the chassis into the aircraft; an optical sensor facing upwardly from the chassis; a drivetrain configured to accelerate and decelerate the chassis along a runway; and a controller configured to detect an optical fiducial arranged on the aircraft in optical images recorded by the optical sensor adjust a speed of the drivetrain to longitudinally align the alignment feature with the alignment receiver based on positions of the optical fiducial detected in the optical images, trigger the latch to engage the latch receiver once the aircraft has descended onto the chassis, and trigger the drivetrain to actively decelerate the chassis during a landing routine.

Abstract: The presently disclosed subject matter is directed to a device that can be used to lift and/or position a remote-controlled (RC) aircraft as needed by a user (e.g., into/out of a transport vehicle). The device includes a handle that allows the user to grip and hold the device. The handle is operably connected to an arm that comprises an angled portion and a connector portion. The angled portion is angled to accommodate the canopy of an associated aircraft. The connector portion allows joining of the arm to an extender. The extender passes through the central portion of the aircraft to allow the user to lift and/or position the aircraft as desired.

Abstract: A naval platform has a zone for the deck landing/take-off of an aircraft and an aircraft handler, to move the aircraft over the deck landing/take-off zone. The aircraft handler includes a body in the form of a bar for gripping and securing the main landing gear of the aircraft, provided with an anchoring hook mounted to slide in at least one rail, guiding the the aircraft on the deck landing/take-off zone. The hook is retractable, allowing the release of the body in the form of a gripping and securing bar from the rail, the body gripping the landing gear of the aircraft. The movement of the aircraft brings the body into position on the rail, and the hook into a position in which it faces the rail, and the hook back into an anchoring position in the rail in order to secure the aircraft.

Abstract: A wind-driveable wing construction (30) which comprises a tether line (40), which is designed to connect the wing construction to a ground station (10) during operation, and one end of the tether line (40) being attached to the wing construction; and a bridle line system comprising a multiplicity of bridle lines (70, 71). At least two bridle lines having an end connected to the wing construction and at least one bridle line has an end connected to the tether line (40). The bridle line system is detachably connected to the tether line, during operation. The tether line (40) has a first sleeve (130) which is attached to the tether line, the bridle line system has a second sleeve (120), to which the at least one bridle line (70, 71) is connected. A capture cable is passed through the second sleeve, and the sleeves are designed to form a detachable connection.

Abstract: An anchoring vehicle for anchoring an airship at the tail while coupled to a mooring mast at the bow. Airships are generally coupled at the bow to a mooring-mast after landing on the ground. However, vertical gusts can result to a considerable amount of damage to the airship with this mechanism. To avoid such damage, the proposed anchoring mechanism designed as an anchoring vehicle, is coupled via an anchor-mast to the tail of the airship near the height of its middle axis. Thus, the vehicle stabilizes the airship vertically and can independently maneuver horizontally without considerable rolling resistance to a predefined airship position, thus preventing a tilting moment. The all-terrain, autonomous anchoring vehicle captures direction and strength data of horizontal deflection caused by wind power via sensors on the anchoring-mast. A control unit regulates the drive systems for navigation and wheel drive.

Abstract: A system for handling an aircraft on a nautical vessel includes a plurality of winches each associated with a corresponding one of a plurality of electromotors and a plurality of cables associated with the plurality of winches. Each of the plurality of cables is configured to attach to an aircraft positioned on a deck of the nautical vessel. A control system is configured to receive a target aircraft hauling speed and direction and operate the winches to achieve the target speed in the selected direction while maintaining load on the aircraft to below a maximum limit and also maintaining the cables in tension.

Abstract: An underwater docking system for an autonomous underwater vehicle, the underwater docking system including: an underwater station including a base mount fixed to a seabed and a circular frame member supported by the base mount and parallel to a horizontal plane; and an autonomous underwater vehicle configured to dock with the underwater station while sailing through an upper side of the frame member, wherein: the autonomous underwater vehicle includes an underwater vehicle main body.

Abstract: A portable launch rig (PLR) may include a support structure including two side supports defining an interior space for lifting and filling a balloon envelope of a balloon. Wheels on each of the side supports enable the PLR to be moved in various directions in order to prepare the PLR for launching the balloon. The side supports are connected by a lateral support beam having a pair of cranes arranged thereon. Each crane has an arm arranged over the interior space that is connected to a spreader beam. The spreader beam includes a lift assembly configured to lift and inflate the balloon envelope within the interior space. The PLR includes a platform and perch for supporting and moving the balloon envelope. A door assembly of the PLR includes a plurality of hangar doors configured to block wind from a respective direction of each hangar door entering the interior space.

Abstract: A flight device includes at least one propelling unit and a controller unit for flying in the air, and the flight device is thrown by a user. The controller unit drives the propelling unit after throwing is performed by the user, such that the flight device flies based on a state of the flight device at a moment when the throwing is performed.

Abstract: An aerial platform receives power in the form of light, for example laser light, transmitted via an optical fiber from a remote optical power source. The platform comprises a receiver which converts at least a portion of the light to a different form of power, for example electric power. The platform also comprises a propulsion element which consumes the different form of power to generate propulsive thrust. Supplying power to the aerial platform from a remote source enables the platform to remain aloft longer than a battery or fuel tank carried by the platform would allow. Transmitting the power in the form of light is preferable in many cases to transmitting electric power, because electrical conductors are generally heavier than optical fibers, and are hazardous in the presence of lightning or a high-voltage power line.

Abstract: An apparatus and method of charging and housing of an unmanned vertical take-off and landing (VTOL) aircraft is disclosed. The apparatus can accommodate an aircraft, and the apparatus includes a landing platform on which the aircraft lands, a housing portion to monitor state data by housing or charging the aircraft, and a sensor to assist in landing of the aircraft by allowing the aircraft to communicate with the apparatus. The apparatus enhances operational efficiency by reducing a travel time of the aircraft.

Abstract: A self transportable aerostat system comprising: a first motorized mooring truck; a mooring tower removable attached to a base assembly of the first mooring truck, generally vertically arranged in relation to the bed of the first mooring truck; a proximal and distal boom deck removably attached to the base assembly; a flying sheave for redirecting a tether carried by the base assembly and attachable to an aerostat; a second motorized mooring truck attachable to the outer edge of the distal boom; and, an aerostat truck having an electrical connection for connecting to the first mooring truck and having an aerostat storage compartment for storing the aerostat is a retracted configuration.

Abstract: The present invention is directed to methods of determining a vessel-relative off-deck waypoint (VRODW) location comprising the steps of providing an aircraft in flight; determining vessel range and vessel bearing relative the aircraft; and determining the VRODW location using the range and bearing measurements of the vessel. The present invention is further directed to methods of landing an aircraft on a vessel.

Abstract: A method and system of controlling a rotorcraft for sea-based operations includes receiving sensed information indicative of an operation of the rotorcraft; receiving operator commands, ship models and system constraints; and determining a solution to an optimization function that avoids violating the system constraints, the solution being representative of control command signals for augmenting a flight response of the rotorcraft to a ship.

Abstract: A self transportable aerostat system comprising: a first motorized mooring truck; a mooring tower removably attached to a base assembly of the first mooring truck, generally vertically arranged in relation to the bed of the first mooring truck; a proximal and distal boom deck removably attached to the base assembly; a flying sheave for redirecting a tether carried by the base assembly and attachable to an aerostat; a second motorized mooring truck attachable to the outer edge of the distal boom; and, an aerostat truck having an electrical connection for connecting to the first mooring truck and having an aerostat storage compartment for storing the aerostat is a retracted configuration.

Abstract: Provided is a method of providing a smart helipad configured to support landing of a vertical takeoff and landing aircraft, the method including adaptively displaying an imaged marker recognizable by a camera mounted to the vertical takeoff and landing aircraft; obtaining tilting information about a ground surface and a sea surface using a gyro sensor; and adjusting a landing pad connected to a display unit on which the marker is displayed to be in parallel with a horizontal line based on the tilting information, using a motion platform having change responsiveness to all of the directions.

Abstract: A retrieval device for an unmanned aircraft. The retrieval device may include a frame that supports a flexible material. The flexible material may form a receptacle portion shaped to receive the unmanned aircraft. The flexible material may absorb at least a portion of the energy exerted by the aircraft landing within the receptacle portion. Wheels may be connected to the frame to further control and absorb energy from the landing.

Abstract: An aircraft capable of thrust-borne flight can be automatically retrieved, serviced, and launched using equipment suitable for a small vessel. For retrieval, the aircraft hovers over a base apparatus having one or more rails which bound a space into which the aircraft can safely descend. When the aircraft's measured position and velocity are appropriate, the aircraft descends promptly such that a spanwise component on the aircraft engages the rails. The teeth restrain the aircraft in position and orientation, while the rails bring the aircraft to rest. Articulation of the rails is used to park the aircraft in a servicing station. Connections for refueling, recharging, and/or functional checks are made in preparation for launch. Launch is effected by removing connections and restraints and articulating the rails to put the aircraft in an appropriate position and orientation. The aircraft uses its own thrust to climb out of the apparatus into free flight.

Abstract: An anchoring element (2) intended to be fixed on at least one external anchor point (4) of an aircraft's fuselage, comprising a fixing area (5) for ensuring the fixing of the anchoring element (2) on the external anchor point (4) and said anchoring element (2) comprising an anchor means for the connection to attaching means, characterized in that the fixing area (5) comprises means for fixing the anchoring element (2) also to a additional external anchor point (6) of the aircraft's fuselage and said fixing area (5) comprising an extension area (7) on which is located the anchor means.

Abstract: A flying air purifier includes a flying unit configured to fly within a space at a first elevation. The flying unit is also configured to fly within the space at a second elevation. The flying air purifier also includes an air purifier mounted to the flying unit and configured to remove particles from air within the space at the first elevation and at the second elevation. The air purifier includes an air inlet having a first charge and an air outlet having a second charge, wherein the second charge is opposite of the first charge.

Abstract: An anchoring device in a helicopter deck, where a housing that is provided with an open top and lowered into the helicopter deck, contains a fastener which is vertically displaceable between a withdrawn, inactive position and an active position where an upper fastener portion extends at least partly up from the helicopter deck. The upper fastener portion is arranged to be detachably connected to an anchoring means. The housing is provided with a detachable lid arranged to be able to close tightly against the housing.

Abstract: Liquid dispensing assemblies including adhesive anchoring assemblies configured to adhere to a support surface external to a device such as a vehicle. An air vehicle includes (a) a fluid adhesive container assembly detachably attached to the air vehicle, wherein the fluid adhesive container assembly comprises: (i) an adhesive container comprising fluid adhesive; and (ii) one or more fibers, wherein the one or more fibers are configured, or a brush of fibers, or a fabric of fibers, is configured to conduct the fluid adhesive and to structurally support an adhesive bond between the one or more fibers and a surface; and (b) means for dispensing the fluid adhesive from the fluid adhesive container, to the one or more fibers.

Abstract: An infrared laser landing marker system provides a capability to mark a boundary line of varying lengths with near infrared lasers, e.g., of the order 8xx nm. This system can be either directly operated or remotely operated via satellite communications and is compatible with currently fielded night vision goggles. Two modules, placed at either end of boundary, self align to each other and then proceed to mark a boundary edge of a landing zone with an infrared laser line.

Abstract: A self transportable aerostat system comprising: a first motorized mooring truck; a mooring tower removably attached to a base assembly of the first mooring truck, generally vertically arranged in relation to the bed of the first mooring truck; a proximal and distal boom deck removably attached to the base assembly; a flying sheave for redirecting a tether carried by the base assembly and attachable to an aerostat; a second motorized mooring truck attachable to the outer edge of the distal boom; and, an aerostat truck having an electrical connection for connecting to the first mooring truck and having an aerostat storage compartment for storing the aerostat is a retracted configuration.

Abstract: A system may include a sensor for coupling with a vehicle configured for atmospheric flight. The sensor may be configured for detecting a turbulence event, where the turbulence event is at least one of experienced by the vehicle or occurs proximal to the vehicle during atmospheric flight. The system may also include a transmitter coupled with the sensor. The transmitter may be configured for automatically remotely transmitting data regarding the turbulence event to a ground based entity.

Abstract: A system that includes a ground unit that includes: a takeoff and landing platform; a landing and takeoff assisting module; and a housing. The takeoff and landing platform is arranged to hold and support an aerial unit during a first part of a landing process of the aerial unit and a first part of takeoff process of the aerial unit. The aerial unit is coupled to the ground unit via a connecting element. The effective length of the connecting element increases during the takeoff process and decreases during the landing process. The landing and takeoff assisting module is coupled to the takeoff and landing platform and is arranged to (a) lower the takeoff and landing platform into the housing during a second part of the landing process and (b) elevate the takeoff and landing platform during a second part of the takeoff process.

Abstract: Airship handling devices and associated systems and methods are disclosed herein. An airship handling device in accordance with one embodiment of the disclosure, for example, can include a first support member mountable to a ground vehicle. The device can also include a second support member operably coupled to the first support member and configured to rotatably move relative to the first support member about a support member axis. The second support member is out of contact with the ground vehicle. The device can further include a line attachment portion carried by the second support member and positioned to releasably couple a flexible handling line from an airship to the second support member. The handling line is not coupled to a winch.