Abstract: A vehicle has a roadable configuration similar to an automobile in which multiple rotors are stowed within the vehicle, and a flying configuration in which the rotors are deployed from the vehicle, allowing it to fly like a VTOL/STOL aircraft or a helicopter.

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: Aircraft systems that are optimized for multiple phases of flight are disclosed. In an aspect, an in-line staged aircraft is disclosed comprising a launch vehicle and a flight vehicle which are configured to join together along a common center line and form a single air foil in the joined configuration. The flight vehicle and the launch vehicle are separable in flight. In an aspect, the flight vehicle is an unmanned aerial vehicle configured for high-altitude, long-endurance operations.

Abstract: An unmanned aircraft system includes a manned aircraft and an unmanned aircraft. The manned aircraft includes a manned aircraft main wing, a manned aircraft fuselage, a manned aircraft landing system, and a manned aircraft joining mechanism provided at a bottom portion of the manned aircraft fuselage. The unmanned aircraft includes an unmanned aircraft main wing, an unmanned aircraft fuselage, an unmanned aircraft landing system, and an unmanned aircraft joining mechanism provided at a roof portion of the unmanned aircraft fuselage. The manned aircraft joining mechanism and the unmanned aircraft joining mechanism are detachably joined. The unmanned aircraft system can take off or land in a state that the unmanned aircraft and the manned aircraft are joined.

Abstract: An orbital launch system and its method of operation use a maneuver to improve the launch condition of a booster rocket and payload. A towed launch aircraft, to which the booster rocket is mounted, is towed to a predetermined elevation and airspeed. The towed launch aircraft begins the maneuver by increasing its lift, thereby increasing the flight path angle, which increases the tension on the towline connecting the towed launch aircraft to a towing aircraft. The increased tension accelerates the towed launch aircraft and booster rocket, while decreasing the speed (and thus the kinetic energy) of the towing aircraft, while increasing kinetic energy of the towed launch aircraft and booster rocket by transferring energy from the towing aircraft. The potential energy of the towed launch aircraft and booster rocket is also increased, due to the increased lift. The booster rocket is released and ignited, completing the launch.

Abstract: A vehicle capable of both aerial and terrestrial locomotion. The terrestrial and aerial vehicle includes a flying device and a rolling cage connected to the flying device by at least one revolute joint. The rolling cage at least partially surrounds the flying device and is free-rolling and not separately powered.

Abstract: A multi-mode vehicle is disclosed that can be used in two or more of land, water and ground effect flight. The vehicle includes a first engine driving the vehicle's wheels and a second engine driving a fan. The vehicle includes removable wings, a removable horizontal stabilizer and a rudder. The second engine and fan, operating alone, provide insufficient thrust for the wings to lift the vehicle off the ground. The first and second engines, operating together, provide sufficient thrust for the wings to lift the vehicle into ground effect flight. The second engine and fan provide sufficient thrust for the vehicle to maintain ground effect flight.

Abstract: An aircraft system incorporates a first aircraft having a grappling device including a first gripper with a first actuator and a second gripper with a second actuator. The first gripper and the second gripper are movable between an open and a closed position to engage a hooking device and pivot together to change a capture angle. A first controller receives a command and operates the actuators in response to open and close the first and second grippers of the grappling device. The controller also receives a second command and operates the first and second actuators to pivot the grippers and provide grappling at a range of capture angles. A second aircraft, which may be a UAV, incorporates the hooking device. The hooking device includes a ring rotatable from the surface and a third actuator to rotate the ring between a stowed and an extended position.

Abstract: An aircraft with a wide fuselage having a longitudinal axis, a left and right forward swept wing mounted well back on the fuselage, a tail section extending from the aft portion of the fuselage, a first and second brushless ducted fan with air accelerator ring stationary and integrated into the left and right lateral fuselage, a third brushless ducted fan with integrated air accelerator ring rotatable mounted to the aft tail portion, a solar turbine based external solar film applied on the fuselage and wing surfaces and lateral fan regenerative drive that powers all ducted electric fans, that powers one internal-mounted central master impeller motor, that powers a brushless electric motor that spins three supercharger impellers via pulley chains to enable all three air accelerator rings with super compressed forced air thrust, that recharges ultracapacitors for aircraft propulsion of persistent flight endurance targeted for 30 to 90 days.

Abstract: In one example, a free-flying tethered airship system includes an upper airship adapted to tailor its lift and drag, a lower airship adapted to tailor its lift and drag, and a tether connecting the upper airship to the lower airship such that the upper airship is at least one kilometer above the lower airship. The upper airship is configured to be equiliberally buoyant, while carrying the tether, in a first altitude range. The lower airship is configured to be equiliberally buoyant in a second altitude range, the first altitude range being higher than the second altitude range. A method for stationkeeping of a free-flying tethered airship system is also provided.

Abstract: A method is provided to measure an aircraft under simulated flight-loads while the aircraft is not in flight. Simulated flight-loads may be applied to the aircraft, while the aircraft is not in flight, in order to substantially simulate flight pressure distribution loads the aircraft would experience during flight. A position of one or more portions of the aircraft may be measured, while the aircraft is under the simulated flight-loads, to determine an effect of the simulated flight-loads on the aircraft.

Abstract: An illustrative airship system for long endurance stratospheric operations includes an upper airship and a first end of a tether attached to the upper airship. A lower airship is attached to a second end of the tether and a payload airship is reversibly mated to the lower airship. The airship system is free flying and configured to maintain long duration station keeping. Illustrative methods for long endurance stratospheric operations are also provided.

Abstract: A combination rotor and wheel assembly for an unmanned vehicle with ground and aerial mobility has a rotor arm adapted to be attached at an inner end thereof to a vehicle body. A rotor is rotatably connected to an outer end of the rotor arm about a rotor axis, and a rotor drive mounted on the rotor arm rotates the rotor such that the rotor exerts an upward lift force on the rotor arm. An open spoked wheel is rotatably connected about the rotor axis independent of the rotor The diameter of the wheel is greater than that of the rotor, and a bottom edge of the wheel is below the rotor. A wheel drive rotates the wheel. Vehicles can have various numbers and orientations of the rotor and wheel assembly to provide aerial and ground mobility.

Abstract: A method of launching a powered unmanned aerial vehicle at an altitude of at least 13,000 m, the method comprising lifting the vehicle by attachment to a lighter-than-air carrier from a substantially ground-level location to an elevated altitude, causing the vehicle to detach from the carrier while the velocity of the vehicle relative to the carrier is substantially zero, the vehicle thereafter decreasing in altitude as it accelerates to a velocity where it is capable of preventing any further descent and can begin independent sustained flight.

Abstract: A roadable vehicle with a single nacelle assembly that contains a pair of inline counter-rotating propellers. Two inline counter-rotating engines are directly connected to the propellers. One engine is shut down in horizontal flight to improve efficiency. Gimbal mounting the nacelle assembly permits thrust to be directed forward to back and left to right to control the vehicle position in the horizontal plane, when hovering. Varying the relative engine speeds controls yaw. The roadable vehicle is adaptable as an unmanned vehicle. The foldable wings equipped with automotive type wheels provide for travel off-road as well as on the highway.

Abstract: A vehicle driving control apparatus is provided at least with: a rudder angle varying device capable of changing a relation between a steering angle, which is a rotation angle of a steering input shaft, and a rudder angle, which is a rotation angle of steered wheels; and a trajectory controlling device for controlling the rudder angle varying device such that a trajectory of a vehicle approaches a target driving route of the vehicle. The vehicle driving control apparatus is further provided with a changing device for changing responsiveness of control by the trajectory controlling device when there is a steering input given to the steering input shaft through a steering wheel by a driver of the vehicle.

Abstract: The proposed advanced multi-level protective system comprises two types of barriers, harmoniously complementing to each other: a portable barrier for the protection of individual houses at the height of the floods up to 0.8-0.9 meters, and more powerful protective quick-installable barriers, suitable for mechanized installation and resistant to higher water flows up to 1.2-2 meters. The proposed advanced protective system comprises a number of additional means capable of weakening against dangerous natural processes that give rise strong water flows, and these means can weaken these flows and increase the efficiency of proposed protective barriers.

Abstract: A vehicle comprises a first stage supersonic aircraft, and a second stage hypersonic aircraft. The second stage aircraft is in tandem with the first stage aircraft.

Abstract: Apparatus indicated generally at 26 is incorporated within an aircraft. The apparatus 26 includes an electric motor 28, a first drive train 30 and a second drive train 32. The first drive train 30 provides drive from the electric motor 28 for one or more of the wheels 20, allowing the electric motor 28 to propel the aircraft when taxiing. The second drive train 32 provides drive from the electric motor 28 for an aircraft system which is operational at least when the aircraft is in flight. In this example, the electric motor 28 is illustrated using the second drive train 32 for driving a compressor 34 of the ECS 24, the compressor 34 being responsible for cabin pressurization during flight. A clutch 36 allows the drive train 30 to be connected or disconnected from the electric motor 28, thereby connecting or disconnecting the drive from the electric motor 28 to the wheels 20. The clutch 36 is controlled to disconnect the first drive train 30 when the aircraft is in flight.

Abstract: A tethered unmanned aerial vehicle (“UAV”) may be outfitted with a sensor payload for data gathering. The tethered UAV may be tethered to a ground station for constricting the flight space of the UAV while also providing the option for power delivery and/or bidirectional communications. The tethered UAV's flight path may be extended by introducing one or more secondary UAVs that cooperate to extend the horizontal flight path of a primary UAV. The ground station, which may be coupled with the tethered aerial vehicle, may comprise a listening switch configured to determine a condition of the tether such that the supply of power to the tether may be terminated when tether damage or a tether severance is detected.

Abstract: A vehicle includes a first sub-vehicle, and a second sub-vehicle which is repeatably moveable between coupled and uncoupled conditions with the first sub-vehicle. The first and second sub-vehicles each include a landing system and propulsion system. The first and second sub-vehicles are in the coupled condition during take-off. The first and second sub-vehicles are separately flyable in the uncoupled condition. Both vehicles are launched horizontally, by a ramp, or vertically, using atmospheric lift to achieve atmospheric flight, orbital, or sub-orbital launch.

Abstract: A vehicle suitable as both a road vehicle and an aircraft, which includes two units that can be coupled to one another; a first unit embodies a road vehicle with least single-file seating, and a second unit is embodied as a flight unit.

Abstract: A roadable aircraft may be registered and driven as a motorcycle on the roadways, does not require that any parts be “left behind” at the airport when configuring to roadable use and does not require removing portions of the aircraft and towing them behind. A foldable and collapsible wing comprises a number of wing ribs, which are hinged to a main forward spar. To fold for road usage, the wing ribs fold about a hinge fitting to collapse against the wing spar. To maintain tension on the wing skin (to prevent flutter) tensioning bladder(s) may be used to keep the fabric taut. Once retracted and folded, the wings align with tail booms to form a compact and aerodynamic package. The ductless fan may be provided with a center-mounted extraction fan ducted to inlets along the fuselage to draw low energy air in toward the fuselage and thus prevent boundary layer separation.

Abstract: An air-to-surface surveillance and/or weapons system includes a base aircraft and an unmanned slave aircraft that can be uncoupled from a base aircraft and coupled back to it again. The base aircraft and slave aircraft are equipped with coupling equipment designed to work together. The base aircraft is equipped with surveillance and monitoring equipment. The slave aircraft is equipped with monitoring equipment and/or weapons. The slave aircraft can be connected to a control station via a data link for data exchange and can be controlled from this control station.

Abstract: At least a first rescue device for receiving rescue is configured on a bottom side of an aircraft and at least a second rescue device for providing rescue is configured on a bottom side of the aircraft. The first and second rescue devices can be optionally configured. For a small aircraft, only the first rescue device for receiving rescue can be configured. For a large aircraft, both the first and second rescue devices for providing and receiving rescue can be simultaneously or optionally configured. When an aircraft with the first rescue device for receiving rescue suffers loss of power, insufficient power, or control difficulty, another aircraft with the second rescue device for providing rescue can fly on top of the former and their first and second rescue devices can be linked together so that the troubled aircraft can be pulled away to land in a safe place.

Abstract: An aircraft comprising a fuselage, a vessel associated with the fuselage, a propulsion system associated with the fuselage, and a lift system. The vessel is capable of storing a pressurized gas compressed to a density that allows the aircraft to operate under water. The lift system is capable of providing the aircraft lift to fly in air.

Abstract: The invention relates to a roadable aircraft vehicle (100) and related systems. An example roadable aircraft vehicle (100) includes a vehicle drive system (262) including an engine (264) and gearbox (206) selectively engageable with an automotive driveline (266) and at least one propeller (270), a user interface including a display (202) for controlling the drive system (262) in an automotive mode including a steering wheel (204) and in a flight mode including a control stick (272), a control system for switching between the flight mode and the automotive mode, and a system (236) for locking the propeller (270) during the automotive mode. The invention also relates to aircraft systems and elements such as an airfoil (106) having a nominal profile, a folding wing (102), and an occupant crash protection system for an aircraft (100).

Abstract: The invention concerns a life-saving vehicle (10) designed as a hollow body with the form of a sphere or disk essentially flattened along a vertical axis (16) that demonstrates its greatest width in a horizontal plane (15) and which body, composed of an upper part (11) and a lower part (13), limits an internal passenger compartment (25), whereby the body comprises a stabilizing arrangement (12) that stabilizes the vehicle when it is in water, a telescopic arrangement (40), a stabilization means (14) arranged at the lower part, which stabilization means can be displaced in a vertical direction downwards from the lower part through activation of the telescopic arrangement (40). The vehicle, in order for it to travel not only in the air but also in water, comprises: a first and second rotor (52, 17), a motor (55) with an associated transmission (54), a pair of propulsion units (60) and a stabilizing fin (65).

Abstract: An aircraft structure is provide, an aircraft structure for an aircraft. including front Wing and rear wing of the Swan-Wing, vertical winglets and the first level Floor body. the fuselage has a cross-section of substantially flat fuselage shape being is Wide enough to provide lifting force. the front wing of the Swan-Wing are Disposed horizontally in front portion of the fuselage. rear wings of the Swan-Wing are disposed horizontally in rear portion of the fuselage. the vertical winglets Are disposed at the top of the rear fuselage. the first level disposed fuel tank storages, a Plurality of landing gear bays, cockpit with control panels, various avionics and Cabin doors. The top of the rear fuselage disposed jet power plants, the fuselage provide lifting force And the wings provides steering force and lifting force the whole structure of an aircraft Comprises carbon fiber honey comb composite molded structure which lighter weight And shear strong structure. the cockpit and cabin disposed.

Abstract: Flying Car, readable aircraft, amphibian, multimode, multifunctional, composite versatile personal transport vehicle with twin, parallel fuselages, hulls, each with inflatable pontoons and/or wheels below and a cabin. Combined, aircraft, airplane, aeroplane, flying, air, aerial, airborne vehicle with variable, folding wings which is convertible via automatic transformation to a land vehicle and to a sea vessel. Two wings are stored between the fuselages. They extend on a system of rails, pivots and counter-rotating, fuselage-mounted arms which then sink flush into the wings' undersides and lock for flight. Upon wing extension and retraction, controls for road transport and flight controls alternately emerge or are stowed inoperably, as needed. Engine power alternately drives a propeller for flight, wheels for road travel and a separate, submersible, marine propeller for water transport.

Abstract: An aircraft includes a fuselage, a first wing, and a second wing. The first wing and the second wing each have at least two wing panels, where the at least two wing panels of each wing are telescopically related to one another for movement between an extended position and a retracted position. The first wing and the second wing are both connected to the fuselage and are positioned with respect to the fuselage such that the first wing is offset with respect to the second wing.

Abstract: A multi-modal vehicle (“MMV”) 20a-20d. The MMV 20a-20d includes a fuselage 22 and a chassis 26 supporting at least three wheels 44 having deployed and stowed states. Extending away from the fuselage 22 is a canard wing system 28 and a main wing system 30. The main wing system 30 includes an inboard portion 134 and an outboard portion 132. The inboard portion 134 is pivotally connected to the fuselage 22; the outboard portion 132 is pivotally connected to the inboard portion 134. The MMV 20a-20d further includes a vertical thrust system 32 comprising a pair of ducted fans 100 that are incorporated into the fuselage 22, and a dual-use thrust system 34 that is configured to transition between a first position for supplying vertical thrust and a second position for supplying a horizontal thrust. A controller 42 is configured to control the MMV operations, reconfigurations, or transitions.

Abstract: An air-ground vehicle (10) has a fuselage body (14), a propulsion system (15), and a landing gear system 16. The body includes a passenger compartment (21) and a pair of wings (22). The body also includes a central air channel (25) formed by a U-shaped channel wall (26) and a pivotal horizontal stabilizer (27). Each wing also has a curved top surface (31), a relatively flat bottom surface (32), and an outboard end wall (33). The U-shaped channel wall, top surface, and end walls form a pair of side air channels (36). Each wing has a set of internal S-shaped louvers (41) positioned within an interior airflow channel (48) and directly adjacent an air opening (40) of the interior airflow channel. Each S-shaped louver has a U-shaped trough (42) extending to or into an inverted U-shaped crest (43). Each adjacent pair of S-shaped louvers are spaced from each other to form an airflow gap (46) therebetween.

Abstract: An aero-assisted pre-stage (10) with a commensurably large wing area having a short-burn rocket propulsion system providing sufficient thrust is used to launch a variety of single-stage and multiple-stage space vehicles (20), such as conventional ballistic rockets and prospective spaceplanes, from conventional runways. This method of launch eliminates the need for dedicated ground launch structures and/or dedicated long runways. The vehicle to be launched (20) is mated to this aero-assisted pre-stage (AP) (10), with their flight directions aligned, using a lock-and-release mechanism (30). The resulting stack takes off like a conventional airplane using the propulsion and aerodynamic lift of the AP. After the desired trajectory of the vehicle is achieved and propulsion system of the AP is shut down, the vehicle is separated from the AP, the propulsion system of the vehicle is ignited, and the vehicle continues its ascent. The AP returns back to the surface for reuse or disposal.

Abstract: A vehicle has a roadable configuration similar to an automobile in which multiple rotors are stowed within the vehicle, and a flying configuration in which the rotors are deployed from the vehicle, allowing it to fly like a VTOL/STOL aircraft or a helicopter.

Abstract: A roadable aircraft and an associated method are disclosed herein. The roadable aircraft includes a body extending along a longitudinal axis and operable to house a human occupant. The roadable aircraft also includes at least first and second wings each being selectively moveable relative to the body between a retracted position for stowing and an extended position for flight. Each of the first and second wings extend a wing cord along the longitudinal axis when in the extended position between a leading edge and a wing trailing-edge vectoring nozzle. The roadable aircraft also includes a system for directing first and second streams of air through the first and second wings, respectively, and out of the first and second wing trailing-edge vectoring nozzles such that thrust for the body is generated. In addition, embodiments of the invention can include a plurality of deployable, vectoring lift fans which are also capable of producing thrust.

Abstract: In one example, a long endurance airship system includes a payload airship and a first logistics airship mechanically joined to the payload airship to form a first combined airship, the payload airship and the logistics airship having design capabilities differing by at least a factor of two with regard to at least one of: power generation capability, propulsion capability, endurance capability, and lift capability, in which the first combined airship is free flying, lighter-than-air, and configured to maintain aloft for greater than 30 days without physical connection to the ground. Illustrative methods for long endurance airship operations are also provided.

Abstract: A hybrid fixed wing aircraft converts into a roadworthy vehicle in a matter of seconds therefore operating efficiently in both air and ground transportation systems. The single piece wing is mounted on a skewed pivot that is on the lower portion of the fuselage and is operated by a pushbutton operating system. The aircraft includes telescopic twin boom tail design that when extended allows good pitch stability and damping. The aircraft's wing area may be increased with additional telescopic wing tip segments. This allows an increase in aspect ratio, hence improving efficiency at high loads. This feature also creates a reduction in induced drag at cruise speed by simply retracting the tips in flight. The vehicle has a unique synchronized control system that switches from flight to ground mode without input from the operator, thereby providing a natural interface for the operator.

Abstract: A system for determining a propellant content and a center of gravity in a three-axis stabilized spacecraft includes a ranging device that is coupled to an interior of a propellant tank of the spacecraft. The ranging device is configured to receive a ranging echo to facilitate determining a location of a membrane within the propellant tank.

Abstract: A Combination Ground Vehicle and Helicopter and Fixed Wing Aircraft. A sideways translating tailsitter aircraft.

Abstract: Miniature robotic vehicles suitable for a variety of tasks including covert surveillance, reconnaissance, and recreation are provided. Embodiments of the invention may include vehicles having a hybrid transportation system that incorporates a rotary-wing flight mode in conjunction with a wheeled ground transport mode. As a result, exemplary vehicles provide efficient ground-mode travel, with the added ability to fly over large obstacles and rough terrain.

Abstract: An aircraft includes a reference system including a longitudinal X axis, a vertical Z axis perpendicular to the X axis, and a lateral Y axis perpendicular to the plane defined by the X and Z axes, a fuselage, a wing affixed to an upper central part of the fuselage, a set of rear airfoils situated behind the wing, and propulsion engines mounted on the wing, where the wing, the set of rear airfoils and the propulsion engines are parts of an aero-propulsive unit forming a structure independent of the fuselage, and where the aero-propulsive unit is connected to the fuselage by a six degrees of freedom connection system using arms with lengths modified to control a position of the aero-propulsive unit relative to the fuselage along the X, Y and Z axes and in rotation about the X, Y and Z axes, during flight.

Abstract: A method for launch of an airship includes connecting a cargo airship to a deflated second airship, launching the cargo airship, inflating the second airship with lifting gas carried by the cargo airship while aloft; and releasing the second airship from the cargo airship. A high-altitude airship launch system is also provided.

Abstract: A device (10) for launching and recovering a drone (5), the device being suitable for being fastened to an aircraft. The device includes docking means (20) for a drone (5), the docking means (20) being provided with securing/releasing means (30) for the drone (5), said docking means (20) being secured to flared guide means (40) for guiding the drone (5) towards said docking means (20).

Abstract: A flying vehicle, comprising a discoidal secondary wing and two airfoil primary wings. The airfoil primary wings provide out-of-surface-effect lift that acts as the main lift force for the vehicle. The discoidal secondary wing provides lift via the surface effect, stabilizes the vehicle, provides a mounting surface for solar panels, and acts as a pontoon for water landings. The vehicle can also include a retractable toroidal or round balloon to provide additional lift. The vehicle is fully scalable, from children's toys to passenger vehicles.

Abstract: A system and method of lifting a cargo container into flight using a plurality of aircraft. A swivel bearing is provided that has a first end and a second end. The two ends of the swivel bearing are free to rotate independently. A cargo container is provided that is streamlined for flight. The second end of the swivel bearing is attached to the cargo container. Aircraft in flight are used to lift the container. The aircraft have tow tether lines. The tow tether lines are attached to the first end of the swivel bearing. The aircraft fly in an ascending circular pattern, therein applying lift to the cargo container that is sufficient to raise the cargo container into flight. The cargo container is streamlined and contains flight controls to enable the cargo container to maintain level and controlled flight while it is being towed.

Abstract: An apparatus for use as a flying entertainment vehicle. The apparatus includes a lift system, such as a parawing, that is inflated by air to generate lift and further includes a vehicle frame attached to the lift system such as by suspension lines that also space the lift system apart from the vehicle frame. The apparatus includes a thrust assembly supported on the vehicle frame that is operable to propel the vehicle at a flight speed at which the lift system is operated, e.g., the parawing is inflated, to generate lift to suspend the vehicle frame above the ground. The apparatus includes show elements that may be supported on or by the vehicle frame and be configured to be lift neutral. The show elements function to distract observers away from the lift system such as by appearing to provide the lift or features that cause the vehicle frame to fly.

Abstract: A system and method for assessing the risk of conjunction of a rocket body with orbiting and non-orbiting platforms. Two-body orbital dynamics are used to initially determine the kinematic access for a ballistic vehicle. The access may be represented in two ways: as a volume relative to its launcher and also as a geographical footprint relative to a target position that encompasses all possible launcher locations.

Abstract: In one example, a long endurance airship system includes a first combined airship with a payload airship and a first logistics airship. The first combined airship is configured for stationkeeping at a predetermined station during meteorological conditions with wind speeds below a predetermined threshold. The airship system also includes a second combined airship which is a reconfiguration of the first combined airship and includes the payload airship and a second logistics airship. The second combined airship is configured for stationkeeping at the predetermined station in all meteorological conditions, including meteorological conditions with wind speeds above the predetermined threshold.

Abstract: An illustrative airship system for long endurance stratospheric operations includes an upper airship and a first end of a tether attached to the upper airship. A lower airship is attached to a second end of the tether and a payload airship is reversibly mated to the lower airship. The airship system is free flying and configured to maintain long duration station keeping. Illustrative methods for long endurance stratospheric operations are also provided.