Abstract: A base station is disclosed for an unmanned aerial vehicle (UAV). The base station includes: an enclosure; a slide mechanism that is connected to the enclosure and which is repositionable between a retracted position and an extended position; and a cradle that is connected to the slide mechanism and which defines a chamber that is configured to receive the UAV such that the UAV is movable into and out of the enclosure during repositioning of the slide mechanism between the retracted position and the extended position. The cradle includes: an upper shell; a lower shell that is connected to the upper shell; and at least one thermal insulator that is located between the upper shell and the lower shell.

Abstract: A system for deploying and retrieving an unmanned aerial vehicle (UAV) with a UAV carrier including a UAV bay, where the system includes a UAV pad including a UAV pad base and a UAV pad coupler to couple the UAV to the UAV pad base; a mechanical arm including a first end configured to couple to the UAV carrier, and a second end configured to couple to the UAV pad; and a controller configured to determine a deployment position for the UAV pad, determine a retrieval position for the UAV pad, control the UAV pad, and control the mechanical arm.

Abstract: A flying umbrella assembly includes a flying drone that can fly through the air. An umbrella is removably attachable to the flying drone such that the umbrella can be flown above the ground. A tracking unit is carried by a user and the tracking unit broadcasts a tracking signal to the flying drone thereby facilitating the flying drone to fly within a pre-determined distance of the tracking unit. In this way the flying drone positions the umbrella over the user regardless if the user is stationary or in motion. A personal electronic device is in wireless communication with the flying drone. The flying drone receives the sun tracking data from the personal electronic device to optimally position the umbrella for shading the user.

Abstract: A system for docking an aerostat on a receiving structure, including an unmanned aerial vehicle that can be controlled so as to move between the aerostat and the receiving structure, carrying a first end of a cable that has a second end fixed to the aerostat or the receiving structure, and to attach said first end to the receiving structure or to the aerostat such that the cable connects the aerostat to the receiving structure.

Abstract: An underwater liquid supply unit includes a first bladder containing a first liquid, a second bladder containing a second liquid, and a third bladder containing a third liquid. The combined volume of the first liquid, second liquid, and third liquid is neutrally buoyant relative to a surrounding medium the liquid supply unit is disposed in (e.g., in seawater). As the first liquid, second liquid, and third liquid are dispensed from the bladders, the bladders may reduce in size in at least one dimension. As the liquids are dispensed, the liquids may be dispensed in a predetermined volumetric ratio based on the density of the liquids to maintain neutral buoyancy of the combined volume of liquid. The underwater liquid supply unit may also include an integrated generator such as a fuel cell, as well as a propeller.

Abstract: A base module may be used to receive and house one or more unmanned aerial vehicles (UAVs) via one or more cavities. The base module receives commands from a manager device and identifies a flight plan that allows a UAV to execute the received commands. The base module transfers the flight plan to the UAV and frees the UAV. Once the UAV returns, the base module once again receives it. The base module then receives sensor data from the UAV from one or more sensors onboard the UAV, and optionally receives additional information describing its flight and identifying success or failure of the flight plan. The base module transmits the sensor data and optionally the additional information to a storage medium locally or remotely accessible by the manager device.

Abstract: A method for controlling palm landing of an unmanned aerial vehicle (“UAV”) includes detecting a flight status of the UAV under a predetermined condition. The method also includes controlling the UAV to land on a palm of a user when the flight status is a hover state and when the palm is located under the UAV.

Abstract: A base module may be used to receive and house one or more unmanned aerial vehicles (UAVs) via one or more cavities. The base module receives commands from a manager device and identifies a flight plan that allows a UAV to execute the received commands. The base module transfers the flight plan to the UAV and frees the UAV. Once the UAV returns, the base module once again receives it. The base module then receives sensor data from the UAV from one or more sensors onboard the UAV, and optionally receives additional information describing its flight and identifying success or failure of the flight plan. The base module transmits the sensor data and optionally the additional information to a storage medium locally or remotely accessible by the manager device.

Abstract: A base module may be used to receive and house one or more unmanned aerial vehicles (UAVs) via one or more cavities. The base module receives commands from a manager device and identifies a flight plan that allows a UAV to execute the received commands. The base module transfers the flight plan to the UAV and frees the UAV. Once the UAV returns, the base module once again receives it. The base module then receives sensor data from the UAV from one or more sensors onboard the UAV, and optionally receives additional information describing its flight and identifying success or failure of the flight plan. The base module transmits the sensor data and optionally the additional information to a storage medium locally or remotely accessible by the manager device.

Abstract: A method for sheltering a balloon, a blimp, or airship. The method includes obtaining a first guideway by detachably attaching a first plurality of detachable rings to a first side of an outer surface of the balloon, placing a first rope into the first guideway by passing the first rope through the first plurality of detachable rings, attaching a first end of the first rope to a first point of a blanket, and pulling the blanket over the balloon by pulling a second end of the first rope in a first direction pulling the blanket over the balloon by pulling a second end of the first rope in a first direction.

Abstract: Disclosed is a naval platform equipped with a deck-landing/takeoff zone for at least one aircraft and dolly-type mechanism for handling the aircraft to move it over the deck-landing/takeoff zone. The dolly-type mechanism includes a vacuum disc for immobilizing the dolly and thereby securing the aircraft in position on the deck-landing/takeoff zone, the operation of which is triggered by an analyzer of the behavior of the platform in order to avoid any risk of uncontrolled movement of the aircraft.

Abstract: Provided is a flight vehicle operating method including: mooring a flight vehicle to a mooring unit by a cable; reducing a weight of the flight vehicle, increasing the flotage of the flight vehicle, or increasing the flotage of the flight vehicle while reducing the weight of the flight vehicle, by using a first flotation adjuster; floating the flight vehicle at a suitable altitude in the air; increasing the weight of the flight vehicle, reducing the flotage of the flight vehicle, or reducing the flotage of the flight vehicle while increasing the weight of the flight vehicle, by using a second flotation adjuster or a propelling unit of the flight vehicle; and releasing the connection between the flight vehicle and the mooring unit and withdrawing the cable.

Abstract: A flying object with a landing gear module serving as a floating weight that can be used simultaneously with an airship and an aerial mooring type aerostat, and more particularly, a flying object capable of simultaneously allowing a landing gear to serve as a floating weight, thereby stably simplifying a mooring process of the flying object and manufacturing the flying object at low cost.

Abstract: An apparatus and method for securing a landed aerospace vehicle/object onto a landing pad include a use of the magnetic force to couple the landed aerospace vehicle/object with the landing pad. A magnetized base captures and is anchored onto the landing pad. The use of a rocket booster in a high-gravity environment with the ensuring extreme heat exhaust emission considers the use of an exhaust ventilation system.

Abstract: The Guideless Resilient Androgynous Serial Port (GRASP) mechanism provides an androgynous mechanical and electrical interface that can be tailored to the meet the requirements of a given application. Each mechanism is equipped with physical connections (spring pins) for both power and data transmission between modules.

Abstract: A link device comprising a first object and a second object comprises a first strip, capable of passing from a configuration wound about an axis Z about a support fixed to the first object to a configuration deployed along an axis X substantially at right angles to the axis Z, the strip having an end intended to come into contact with the second object, so as to link the first object to the second object.

Abstract: An unmanned aerial vehicle (UAV), a stand for launching, landing, testing, refueling and recharging a UAV, and methods for testing, landing and launching the UAV are disclosed. Further, embodiments may include transferring a payload onto or off of the UAV, and loading flight planning and diagnostic maintenance information to the UAV.

Abstract: An apparatus and system for launching and/or capturing an unmanned aerial vehicle (UAV). The apparatus includes a moving substrate having an electromagnetic end effector and a UAV with a metallic strike plate to be attracted to the end effector when the electromagnet is activated. The system includes a movable robotic arm having a free end and a secured end; an electromagnetic end effector connected proximate to the free end of the robotic arm; a UAV with a metallic strike to be attracted and held to the electromagnetic end effector when the electromagnetic end effector is active; trajectory software configured to control a location of the free end of the robotic arm; and a control module for receiving input data, analyzing the data and using the trajectory software to control the location of and activate or deactivate the electromagnetic end effector. Also described are methods for launching and capturing the UAV.

Abstract: A connecting device for supporting an apparatus configured to couple to a pipeline and having a coupling mechanism, which has a first portion configured to couple integrally to the apparatus, and a second portion, configured to be connected to a hoisting device, and selectively releasable from the first portion in a designated or given direction as a function of the relative position of, and the force exchanged between, the apparatus and the hoisting device.

Abstract: The invention relates to an air freight container and/or air freight pallet with a flat bottom wall and/or side wall, at least two guide devices arranged on the bottom wall and/or side wall, two connecting elements, wherein a fastening region assigned to a first end of the connecting element in each case extends over part of the connecting element, and a fixing element for fixing an item to be transported transportable by means of the air freight container and/or air freight pallet, wherein the fixing element is connected at the first end thereof to the fastening region of one connecting element and at the second end thereof, which is opposite the first end, is connected to the fastening region of the other connecting element, the connecting elements each have, at a second end arranged opposite the first end, a latching device designed for latching into the corresponding guide device, and at least one guide device is formed in such a way that the latching device can be latched into the guide device at differe

Abstract: A base module may be used to receive and house one or more unmanned aerial vehicles (UAVs) via one or more cavities. The base module receives commands from a manager device and identifies a flight plan that allows a UAV to execute the received commands. The base module transfers the flight plan to the UAV and frees the UAV. Once the UAV returns, the base module once again receives it. The base module then receives sensor data from the UAV from one or more sensors onboard the UAV, and optionally receives additional information describing its flight and identifying success or failure of the flight plan. The base module transmits the sensor data and optionally the additional information to a storage medium locally or remotely accessible by the manager device.

Abstract: An unmanned aerial vehicle docking system can include a docking arm and a docking station. The docking arm can be mounted on the UAV and include a rod with an interface element positioned on top of the rod. The interface element can have charging contacts that are attached to wires that extend down to a charging circuit on the UAV. The docking station can be located separate from the docking arm and have a guidance cone to direct the docking arm to a capture mechanism. Once the interface element is in the capture mechanism, a charging dome is then lowered down onto the top of the interface element to form a circuit between a power source at the docking station and the UAV's battery. Upon completion of the charging process, the charging dome is raised and the capture mechanism releases the interface element of the UAV.

Abstract: A debris removal device includes: an end mass adapted to approach debris to be removed; a debris capture device separably-mounted on the end mass; and a tether connecting the debris capture device and the end mass to each other. The debris capture device includes a harpoon adapted to penetrate into the debris, a shooting device adapted to shoot the harpoon, a guide member positioned to come into contact with the surface of the debris to adjust the shooting angle of the harpoon with respect to the surface of the debris, and a switch that sends the shooting signal to the shooting device. When the harpoon is penetrated into the debris, the end mass is separated from the debris capture device, and the tether is released into outer space.

Abstract: Systems and methods to launch an aircraft are disclosed. In one embodiment, a system to launch an aircraft comprises a launch arm comprising at least one load cell, an aircraft coupled to the launch arm, and a release mechanism in communication with the at least one load cell, wherein the release mechanism releases the aircraft when the at least one load cell indicates that a load on the launch arm is below a predetermined threshold. Other embodiments may be described.

Abstract: Described herein are apparatuses that provided various features related to unmanned aerial vehicles (UAVs). An example apparatus may include, among other features, (i) a launch system for a UAV, (ii) a landing feature that is arranged on the apparatus so as to receive the UAV when the UAV returns from a flight, and (iii) a mechanical battery-replacement system that is configured to (a) remove a first battery from the UAV, and (b) after removal of the first battery, install a second battery in the UAV.

Abstract: A tie down apparatus that may be utilized for securing an item, such as a safety chain, wherein the tie down apparatus may be used with a hitch mounting system. In one embodiment, the tie down apparatus may include a receiving member, a tie down member, and a clocking member. The receiving member may include an opening located there through. The tie down member may include at least one aperture, wherein the tie down member may be capable of being located and rotated within the receiving member. The tie down member may be rotated either clockwise or counterclockwise. The locking member may include at least one leg capable of being housed within the aperture. The locking member may engage the receiving member once the tie down member is rotated, thereby trapping the item within the tie down apparatus.

Abstract: A self-contained mobile surveillance apparatus has applicability in a variety of short or long term settings where security and documentation of activities are needed. Integral to the apparatus is a gas shock assisted swing arm lift assembly and a removable quick connect pod platform system for use in acquiring, recording, storing, and transmitting data to one or more receive locations.

Abstract: A hoisting system, including: a hoisting crane including a hoisting cable, a craft, and a connector catch assembly for interconnecting the hoisting crane and the craft or a load/cargo on the craft. The connector catch assembly includes: a connector body, and a connector catch having a funnel-shaped trap-cage, whereby one of the connector body and the connector catch is attached to the hoisting cable and the other of the connector body and the connector catch is attached to the craft or the load on the craft. A wide side of the funnel shaped trap-cage is directed toward the connector body on approaching one another, whereas an opposite narrow side of the funnel shaped trap-cage has the connector catch mounted therein for releasably holding the connector body.

Abstract: A reconfigurable unmanned aircraft system is disclosed. A system and method for configuring a reconfigurable unmanned aircraft and system and method for operation and management of a reconfigurable unmanned aircraft in an airspace are also disclosed. The aircraft is selectively reconfigurable to modify flight characteristics. The aircraft comprises a set of rotors. The position of at least one rotor relative to the base can be modified by at least one of translation of the rotor relative to the boom, pivoting of the boom relative to the base, and translation of the boom relative to the base; so that flight characteristics can be modified by configuration of position of at least one rotor relative to the base.

Abstract: The present invention extends to methods, systems, devices, apparatus, and computer program products for aligning a target with and/or over and/or into a specific position and orientation. Embodiments include one or more capture components, such as, engagement lines, spars, or struts, that can be actuated together or independently to position a vehicle in a capture area defined by a ring or other geometry. A vehicle can include a sloped surface feature configured to engage with the capture components. When actuated, the capture components draw the sloped surface feature towards and down into the center of the defined capture area. Variations allow a vehicle to be rotated in place, repositioned in place, or clamped securely in place. Positioning and rotation allows alignment with replenishment devices for resupplying and refueling. In this way, a vehicle is relieved from having to have precision terminal guidance for landing and recharging.

Abstract: The present invention extends to methods, systems, devices, and apparatus for replenishing vehicle resources. Vehicles can be aligned with and docked to replenishment devices. In one aspect, a flying vehicle (e.g., an unmanned aerial vehicle (UAV)) is aligned onto electrical recharging contacts. The flying vehicles fuel level or battery charge can be replenished with minimal, if any, human intervention. Vehicle docking (e.g., landing), alignment, and replenishment can be performed automatically. A circular ring or shaped surface of a vehicle can engage with a conical sloping surface of a docking apparatus as a vehicle moves towards and/or into the docking apparatus. The conical sloping surface shape aligns the vehicle with recharge contacts or a refueling probe at the base of the docking apparatus.

Abstract: Various embodiments of the present disclosure provide an apparatus and method for launch and retrieval of a hovering aircraft. Generally, the apparatus of the present disclosure is configured to capture a hovering aircraft between two or more fingers of an aircraft capturer, guide the captured aircraft into a docking station for servicing and/or storage, and launch the aircraft from the docking station. The apparatus of the present disclosure is thus configured to bring the aircraft from an imprecise, irregular hover into a secure and well-controlled rest state. The tolerance of imprecision provided by the apparatus makes it particularly suited for use under a practical conditions such as aboard a small boat in a rough sea.

Abstract: Wind energy is converted into electrical or mechanical energy through the flight of at least one power wing profile tethered via one or more cables to a ground unit moved by the power wing profile along a path of alternating displacement for driving a generator, where the path of alternating displacement is orientable so as to set itself in a direction substantially orthogonal to the direction of the wind. During the phases of flight of the power wing profile in conditions of generation of energy the length of the cables is kept constant.

Abstract: The harpoon comprises a bistable actuator (34) having a rod (56) for actuating the finger (32) the rod being movable between a retracted resting position and an extended position of deployment of the finger (32). The bistable actuator (34) comprises a tappet (52) that is movable during a first impulse comprising a stroke (34) in a first direction and then a stroke in a second direction opposite to the first direction in order to cause the switch of the rod (56) from its retracted position to its extended position. The tappet (52) is movable during a second impulse comprising a stroke in the first direction and then a stroke in the second direction in order to cause the switch of the rod (56) from its extended position to its retracted position. The actuator (34) is configured so as to allow the return of the rod (56) to its retracted position when the tappet (52) moves along the first stroke in the first direction during the second impulse.

Abstract: A method for landing an airship on a landing device placed on the ground by: aligning, in particular horizontally aligning, the airship relative to the landing device with the aid of driving mechanisms arranged on the airship; lowering the airship onto a landing platform element of the landing device; arresting the airship on the landing platform element, wherein at least one electric magnet arranged in the landing device magnetically pulls the airship towards the landing device; and fastening the airship to the ground.

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: The present invention regards an aerial vehicle harpoon device for securing an aerial vehicle (31, 55) to a grid (9) of a landing site, the aerial vehicle (31, 55) comprises an undercarriage (11) having a supporting surface (13) for supporting the aerial vehicle (31, 55) when being in contact with the ground (15), the harpoon device (1) further comprises a securing element (4) arranged adjacent the supporting surface (13). The harpoon device (1) further comprises a resilient actuating device (23) which is adapted to extend the securing element (4) beyond the supporting surface (13) in an unloaded state, and which in a loaded state is compressed by the weight of the aerial vehicle (31, 55) when contacting the ground (15) so that the securing element (4) retracts and the supporting surface (13) contacts the ground (15).

Abstract: An airship docking station includes one or more sources of relatively high speed airflow to facilitate landing an airship in turbulent or gusting air conditions. The sources of airflow are arranged to produce an envelope of airflow over the surface of the airship to stabilize the airship as it lands and is moved into a docked position where it can be secured. The docking station allows an airship to land with reduced or eliminated risk of damage to the airship, payload or ground personnel injury compared to current methods in use. The docking station and method thus ensure more consistent wind conditions adjacent the docking station. Protection from buffeting by gusting winds also facilitates automated or semi-automated airship landing with fewer or no ground personnel.

Abstract: The invention relates to an anchoring harpoon intended in particular for an aircraft, capable of cooperating with an anchoring grate (2) of a platform, comprising jack means (3) including cylinder means (4) containing mobile piston means (5) provided with a rod (6) that extends beyond the cylinder means, the free end of which includes a harpoon head (7) that is hooked in the grate (2) and comprises retaining fingers (8, 13, 14) that can be moved between a retracted position and an active position by control means (9). The invention is characterised in that the cylinder means (4) include at least two telescopic cylinder portions (10, 11) which can move between a position in which one portion is retracted inside the other and an active position in which one portion projects out from the other.

Abstract: Method for identifying an airplane in connection to parking of the airplane at a gate or a stand, for possible connection of a passenger bridge (1) or a loading bridge to a door of an airplane, where the airplane is positioned and stopped at a predetermined position using a touchless measurement of the distance between the airplane and a fixed point, where the distance is indicated on a display (6) mounted in front of the pilot of the airplane on for instance an airport building (7), which display (6) shows the position of the airplane (5) in relation to a stop point for the airplane and shows the current airplane type, where the distance measurement and display are caused to be activated by a computer system (20) belonging to the airport or manually, and wherein an antenna (16) is caused to receive information (17) transmitted by an airplane.

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 harpoon head (6) for a system for anchoring an aircraft on a grating (4) is characterized in that a distal end of the harpoon head has an interchangeable insert (20).

Abstract: The present invention regards an aerial vehicle harpoon device for securing an aerial vehicle (31, 55) to a grid (9) of a landing site, the aerial vehicle (31, 55) comprises an undercarriage (11) having a supporting surface (13) for supporting the aerial vehicle (31, 55) when being in contact with the ground (15), the harpoon device (1) further comprises a securing element (4) arranged adjacent the supporting surface (13). The harpoon device (1) further comprises a resilient actuating device (23) which is adapted to extend the securing element (4) beyond the supporting surface (13) in an unloaded state, and which in a loaded state is compressed by the weight of the aerial vehicle (31, 55) when contacting the ground (15) so that the securing element (4) retracts and the supporting surface (13) contacts the ground (15).

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: A hydrogen airship for efficiently transporting hydrogen from where it can be economically made to where it is most needed using specially designed airships. Hydrogen can be delivered from the place where it is produced to the place where it is needed using an airship in which the hydrogen gas can also be used for generating lift, providing propulsion energy and serving ancillary needs. A unique docking system can use a remotely piloted unmanned aircraft flown from the mother craft to carry a guide line into a receiving attachment point.

Abstract: An anchoring harpoon (1) intended in particular for an aircraft, capable of cooperating with an anchoring grate (2) of a platform, includes a jack member (3) including a cylinder element (4) containing a mobile piston element (5) provided with a rod (6) that extends beyond the cylinder element, the free end of which includes a harpoon head (7) that is hooked in the grate and includes retaining fingers (8, 13, 14) that can be moved between a retracted position and an active position by control elements (9). The jack member is connected to a pressurized fluid source (30) by the control elements (31) and the pressurized fluid source includes a consumable gas cartridge (30).

Abstract: The design and refinement of a tethered hovering platform into a feasible working system is presented. To determine a starting point for the design, a detailed historical search was conducted to find the history and the current state of such technology. Real world current needs are analyzed to produce a mission specification and to drive the preliminary vehicle design. Analysis of environmental conditions and decisions about an initial payload package are made in conjunction with motor and propeller sizing. Initial concept testing to discover feasibility and operational issues was performed; from this, instability issues were discovered. Analyzing these instability issues using known rotorcraft and momentum effects, in conjunction with flight testing, yields possible solutions to the problem. The use of constrained layer dampers as a means of passive stabilization is addressed and suggested as the preferred solution. Testing of passive constrained layer damping verifies the stability of the solution.

Abstract: The invention relates to an aerodynamic wind propulsion device, particularly for watercrafts, comprising an aerodynamic wing being connected to a steering unit located below the aerodynamic wing via a plurality of tractive lines, a tractive cable, a first end of the tractive cable being connected to the steering unit and a second end of the tractive cable being connected to a base platform, the aerodynamic wing having an aerodynamic profile which generates an uplift force in the direction of the tractive cable when the airflow direction is about perpendicular to the tractive cable. According to the invention, an aerodynamic wing is provided being coupled to a steering unit located close below the wing via a plurality of tractive lines of different elasticity.

Abstract: An anchoring harpoon intended in particular for an aircraft, capable of cooperating with an anchoring grate of a platform, includes jack elements including a cylinder element containing mobile piston elements provided with a rod that extends beyond the cylinder element, the free end of which includes a harpoon head (7) that is hooked in the grate and includes retaining fingers (8, 13, 14) that can be moved between a retracted position and an active position by control elements (9). The control element (9) for controlling the movements of the fingers include a control piston (18) which can slide inside the rod of the jack and which is associated with a bistable actuator (19) of the fingers, capable of moving between a retracted position and an active position in which the fingers are deployed with the application of successive pressure pulses in the jack elements.

Abstract: An airship docking station includes one or more sources of relatively high speed airflow to facilitate landing an airship in turbulent or gusting air conditions. The sources of airflow are arranged to produce an envelope of airflow over the surface of the airship to stabilize the airship as it lands and is moved into a docked position where it can be secured. The docking station allows an airship to land with reduced or eliminated risk of damage to the airship, payload or ground personnel injury compared to current methods in use. The docking station and method thus ensure more consistent wind conditions adjacent the docking station. Protection from buffeting by gusting winds also facilitates automated or semi-automated airship landing with fewer or no ground personnel.