Abstract: A hydrogen boiloff capture system. The hydrogen boiloff capture system having a cryogenic tank for storing liquid hydrogen. The hydrogen boiloff capture system also includes an intermediate tank fluidically coupled with the cryogenic tank. The intermediate tank is configured to receive hydrogen gas boiloff from the cryogenic tank. The intermediate tank is further configured to provide the hydrogen gas boiloff to a lighter-than-air craft to regulate buoyancy of the lighter-than-air craft. The intermediate tank is also configured to provide the hydrogen gas boiloff to a hydrogen fuel cell coupled to the lighter-than-air craft.

Abstract: An altitude control system for an unmanned aerial vehicle includes a compressor assembly defining a plenum therein, a passive valve assembly coupled to a first portion of the compressor assembly and in fluid communication with the plenum, and an active valve assembly coupled to a second portion of the compressor assembly and in fluid communication with the plenum. A method of controlling an altitude of an unmanned aerial vehicle and an unmanned aerial vehicle are also provided.

Abstract: A sunshade device and management system for mitigating the effects of climate change and direct and prolonged exposure to the sun, the sunshade device including a reflective canopy attached to a collapsible web or frame structure. The sunshade device is positioned above the ground by a combination of lifting balloons and positioning machines for managing the elevation, shape and geolocation of the sunshade device. A sunshade management system controls the status of the sunshade device, and can collapse and ground the sunshade in the evening, or during rainy weather, or cloudy days, or when severe weather-related events, such as thunderstorms, tornados, hurricane, etc. are anticipated, and can relaunch the sunshade device when such conditions have passed.

Abstract: An airship comprises an envelope accommodating hydrogen further comprising a flame arrester arrangement distributed along the envelope. The flame arrester arrangement comprises a plurality of cells made of mesh panels. The cells are adjoined the envelope and mounted end-to-end to each other.

Abstract: A system for an unmanned aerial vehicle can include an altitude control system, which further includes a compressor assembly, a valve assembly, and an electronics assembly. The compressor assembly may include a driveshaft and a bearing assembly configured to rotate the driveshaft. The driveshaft may be formed from a first material and a compressor housing may be formed from a second material. The first and second materials may have different rates of thermal expansion. A dynamic preloading mechanism, such as a flexible plate, may be provided within the compressor assembly to exert a preloading force on the bearing assembly. Throughout the duration of the flight of the unmanned aerial vehicle, the preloading mechanism can continually compensate for differences in rates of thermal expansion between the first and second materials throughout.

Abstract: A lighter-than-air craft including an envelope. A mixture of helium and hydrogen disposed within the envelope. The mixture having a ratio of helium to hydrogen such that the mixture is nonflammable during operating conditions for the lighter-than-air craft. The mixture provides buoyancy for the lighter-than-air craft. A hydrogen fuel cell fluidically coupled with the mixture and configured to utilize the mixture to generate electricity. A propulsion system is coupled to the envelope, and the propulsion system is configured to provide propulsion for the lighter-than-air craft. The propulsion system is electrically coupled with the hydrogen fuel cell and receives electricity generated by the hydrogen fuel cell. The propulsion system is configured to utilize the electricity in providing the propulsion to the lighter-than-air craft.

Abstract: Provided is an aerial vehicle having a structure in which a rotating body has been excluded from a portion that can be touched by a user during flight. An aerial vehicle includes: a balloon unit; a control unit provided at the bottom of the balloon unit; and a plurality of micro-mechanisms (micro blowers), each of which blows out air. The micro blowers have a structure in which a vibrating member is vibrated in a space in communication with a plurality of openings, thereby blowing out, through a second opening, the air that has flowed into the space through a first opening. The control unit controls the micro blowers to change the position or the attitude of the aerial vehicle.

Abstract: A system for an unmanned aerial vehicle can include an altitude control system, which further includes a compressor assembly, a valve assembly, and an electronics assembly. The compressor assembly may include a driveshaft and a bearing assembly configured to rotate the driveshaft. The driveshaft may be formed from a first material and a compressor housing may be formed from a second material. The first and second materials may have different rates of thermal expansion. A dynamic preloading mechanism, such as a flexible plate, may be provided within the compressor assembly to exert a preloading force on the bearing assembly. Throughout the duration of the flight of the unmanned aerial vehicle, the preloading mechanism can continually compensate for differences in rates of thermal expansion between the first and second materials throughout.

Abstract: The present invention is realized by apparatus and methods for harvesting, storing, and generating energy by permanently placing a large rigid buoyant platform high in the earth's atmosphere, above clouds, moisture, dust, and wind. Long, strong and light tethers can connect the buoyant structure to the ground which can hold it in position against wind forces. Weights suspended from the buoyant platform with cables are raised and lowered by electric winches to store and release gravitational potential energy. High voltage transmission lines electrically connect the platform to the earth's surface. Electrical energy from the high voltage transmission lines or from photovoltaic arrays on the platform can be stored as gravitational potential energy and subsequently released as electricity from generators driven from the stored gravitational potential energy and used on the platform or transmitted via the high voltage transmission lines.

Abstract: A lighter-than-air aircraft is provided including a deballasting system, the deballasting system including: at least one tank containing a liquid; a system for pressurizing the liquid of the at least one tank; and at least one sprayer arranged so as to eject the liquid from the pressurization system.

Abstract: A method of repairing an airship hull of an airship during flight and while the airship is untethered from the ground comprises detecting a breach in a gas barrier bordering an interior volume of the airship, the airship containing a lifting gas wherein the hull of the airship comprises an electrically conductive material and wherein the breach in the gas barrier is detected by detecting changes in an electrical conductivity of the electrically conductive material.

Abstract: A system for elevation control. The system comprises a substantially gastight envelope containing lifting gas wherein the envelope further comprises a plurality of envelope segments in fluid communication with one another. At least one tension cable connects at least two of the envelope segments. A control device including a motor adjusts the length of the tension cable to change the pressure within the envelope to thereby facilitate ascent and descent of the system. The control device causes the system to operate in ascent, descent, or vertically stationary modes.

Abstract: An airship (1) comprising a flexible envelope (2), a wall (3) located inside the envelope, and a pumping device. The wall (3) extends longitudinally between the nose and the tail, thus separating the inside space of the envelope into a first space (E1) and a second space (E2), said second space being located on the periphery of the envelope between a first point (P1) and a second point (P2). The pumping device is adapted to inflate the second space so that the envelope assumes a second shape, and to deflate the second space so that the envelope assumes a first shape which is different from the second shape.

Abstract: This disclosure relates to the use of an optimal altitude controller for super pressure aerostatic balloon in connection with a balloon network. The aerostatic balloon includes a bladder containing a gas that is lighter than the air present in the environment of the balloon. Additionally, the aerostatic balloon includes an envelope filled with air. A mass-changing unit configured to selectively add or remove air may control the amount of air in the envelope. Further, the balloon has a communication module configured to transmit data relating to a current balloon state, and receives data relating to a desired balloon state. Additionally, the balloon includes a processor configured to control the mass-changing unit based on the desired balloon state. The mass-changing unit of the aerostatic balloon may be powered by a renewable energy source, such as solar power. The mass-changing unit adds or removes air with an impeller.

Abstract: A conduit protection system, comprising: a conduit for carrying a fluid; a sealed vessel surrounding the conduit along a protected zone of the conduit; and a valve moveable between a first position for obstructing fluid flow through the protected zone of the conduit and a second position for enabling fluid flow through the protected zone of the conduit, wherein the valve is biased to the first position, and wherein the valve is fluidically coupled to the sealed vessel such that a positive pressure within the sealed vessel is operable to move the valve to the second position against the bias. Also, a method for protecting a fluid carrying conduit.

Abstract: An airship system having a flexible envelope and at least one bladder positioned therein is described. The bladder(s) provide an impervious barrier between the gas within the bladder(s) and the air exterior to the bladder(s). The envelope includes longitudinal and hoops straps weaved together in a criss-cross manner. The envelope also includes rings positioned thereon that include truss members for receiving struts for removably coupling the airship to another airship. A tri-hull delta dirigible system is also described, comprising three airships coupled together using struts and arranged in an equilateral triangle formation. The tri-hull delta dirigible system has a similar lift capacity (volume) as a conventional large mono-hull dirigible, while minimizing the detrimental bending in the center of the conventional mono-hull dirigible.

Abstract: A balloon having a bladder positioned within a balloon envelope, a plate having a port, a housing secured to the plate, an impeller positioned within the housing, the port providing a passageway from an inside of the housing to an inside of the bladder, wherein a passive valve having a periphery is positioned over the port, a control system configured, upon receiving a signal to increase the amount of air within the bladder, to cause the passive valve to move from a first, closed position where a seal is provided by the engagement of the periphery of the passive valve and a periphery of the port to a second, open position where the periphery of the passive valve is disengaged from the periphery of the port to open the passageway between the housing and the bladder and to allow air to be forced into the bladder.

Abstract: Innovative new methods in connection with lighter-than-air (LTA) free floating platforms, of facilitating legal transmitter operation, platform flight termination when appropriate, environmentally acceptable landing, and recovery of these devices are provided. The new systems and methods relate to rise rate control, geo-location from a LTA platform including landed payload and ground-based vehicle locations, and steerable recovery systems.

Abstract: A controllable buoyant system (10) includes a support structure having a sealed hollow enclosure (12) containing a first gas and surrounded by a second gas, either the first gas or the second gas being lighter than ambient air. The hollow enclosure is pre-filled with the first gas via a one-way valve that prevents the first gas escaping and an altitude sensor (14) generates an altitude signal indicative of a height of the support structure. A height transducer (17, 21, 61, 66, 67, 68) coupled to the hollow enclosure is responsive to the altitude signal for varying the buoyancy of the support structure. A controller (15) is coupled to the altitude sensor and to the height transducer and is responsive to the altitude signal and to at least one reference altitude signal for automatically controlling the height transducer in order to maintain the support structure buoyant at the preset altitude.

Abstract: A lighter than air emergency beacon platform as part of a hydrogen generation and filtration apparatus includes at least one power source having at least one activation switch. At least one reaction chamber is electrically connected to the at least one reaction chamber by at least one low-resistance electrical conductor. The reaction chamber is configured to house a hydrogen generating material. At least one flow disruption chamber is in fluid communication with the reaction chamber. The flow disruption chamber(s) are configured to provide fluid communication with the next flow disruption chamber in the direction of fluid flow. At least one inflatable housing is configured to carry payload and is in fluid communication with the flow disruption chambers. The inflatable housing is detached from a fill tube to lift the payload above terrain blocking line-of-sight signal communication.

Abstract: The invention relates to an airship comprising a flexible envelope having at least one adjustment region provided with two longitudinal adjustment elements mounted in opposition and mobile in relation to each other between a maximum distancing position and a minimum distancing position, the two longitudinal adjustment elements being connected to each other by a group comprising a plurality of cables crossing the inner space of the envelope, each of the cables cooperating with a plurality or tightening points provided along each longitudinal element. The cables are connected to at least one tightening module that can exert a tightening or loosening action on the cables and thereby bring the longitudinal adjustment elements closer together or move them further away.

Abstract: A method and apparatus for manufacturing a composite structure. A filler material with a barrier material for a channel in the filler material is formed. A composite material and the filler material with the barrier material are laid up onto a tool in a shape of the composite structure. The composite material and the filler material in the shape of the composite structure are cured.

Abstract: A system for controlling the lift of an airship for carrying a cargo and a supply of fuel has a self supporting hull made of a flexible gas impermeable material. Air which is located in the hull is at an internal pressure which is greater than the atmospheric pressure of the air on the outside of the hull, and a bag filled with helium is located within the hull and is surrounded by the air in the hull. A heating means is provided to heat both the air and the helium. The bag located within the hull and surrounded by the air in the hull has enough helium in it at ambient temperature to lift all but the cargo and fuel in the airship, and the air and helium, when heated, provides increased buoyancy due to the increase of expansion of both heated gases to lift the airship with its fuel and cargo.

Abstract: An airship system, including an inflatable airship of predetermined volume adapted to be filled with gas and to rise to a predetermined altitude, said airship having a hull formed from an inflated flexible gas containment primary envelope, at least one lifting envelope located within the primary envelope for containing the lifting gas, where the lifting envelope will expand to substantially occupy the space of the primary envelope when the airship is at its predetermined high altitude, at least one secondary envelope located within the primary envelope, which can be inflated when said lifting envelope is at lower altitudes to fill the balance of the space of the primary envelope, and air handling means external to the primary envelope and communicating with the secondary envelope for filling and emptying the secondary envelope.

Abstract: An airship is disclosed in the form of a spherical hull having a venting duct extending diagonally therethrough from an entrance end at the forward facing surface of the hull to an exit end at the rearward facing surface of the hull. A propeller is disposed in the duct to direct an air flow through the duct for expulsion at the exit end and the exiting flow is vectored by a set of controllable louvers at the exit end. The expulsed airflow reduces drag normally associated with a spherical airship by disturbing the wake at the trailing surface of the airship. A mooring method and apparatus also is disclosed for minimizing wind induced loads on the airship, or indeed on any body such as a gas storage tank, by supporting the airship or other body a predetermined distance above the ground.

Abstract: A suspended load-bearing structure that is formed by pneumatic structural load-bearing elements comprising an elongate hollow body, compression bars, and traction elements. The hollow body is impinged upon by gases that are lighter than air. In a first embodiment, an individual suspended structural load-bearing element is used as a ridge beam of a large tent hall whose interior has no pillars. The roof is formed by a waterproof cover, the sides of which are stretched on pillars. The cover and the structural load-bearing element are anchored to the ground by means of anchoring ropes.

Abstract: An airship system having a flexible envelope and at least one bladder positioned therein is described. The bladder(s) provide an impervious barrier between the gas within the bladder(s) and the air exterior to the bladder(s). The envelope includes longitudinal and hoops straps weaved together in a criss-cross manner. The envelope also includes rings positioned thereon that include truss members for receiving struts for removably coupling the airship to another airship. A tri-hull delta dirigible system is also described, comprising three airships coupled together using struts and arranged in an equilateral triangle formation. The tri-hull delta dirigible system has a similar lift capacity (volume) as a conventional large mono-hull dirigible, while minimizing the detrimental bending in the center of the conventional mono-hull dirigible.

Abstract: The invention relates to a segmented aerial vehicle with gasbags filled with an energy medium. It refers in particular to an aerial vehicle having interlinked gasbags and/or one big gasbag. This one gasbag or these interlinked gasbags are filled with an energy medium the specific weight of which is approximately the one of air. The energy medium of the gasbags provides energy to the eccentrically placed controllable engines fixed at the segments. The vector thrust produced by the engines and by the vehicle's envelope under excess compression provide sufficient dynamic lift to have the proposed invention fly in a stable and controllable way all in carrying a defined payload, Inside segmented interconnected airbags are placed interconnected segmented gasbags.

Abstract: A system and method for equalizing internal and external pressure on an enclosed vessel moving through a gas or fluid is described, thereby reducing hoop stresses imposed on the vessel by pressure differentials. The vessel is divided into multiple chambers, and the internal pressure of a chamber may be equalized with an external pressure proximate the chamber through the use of a valve or controllable vent.

Abstract: An envelope is disclosed for holding gas in a lighter-than-air aircraft. The envelope includes a shell having a leading edge, a trailing edge, an upper surface and a lower surface. The upper surface and the lower surface each extend between the leading edge and the trailing edge. The shell has an airfoil-shaped cross-section having a reflex camber quality.

Abstract: This invention relates to the field of buoyant aircraft and operation thereof, in particular, airships with improved stability. The present invention is directed to non-rigid, non-spherical airships having an envelope contained within the airship and at least one further envelope contained therein for holding a volume of lifting gas.

Abstract: This invention relates to the field of buoyant aircraft and operation thereof, in particular, airships with improved stability. The present invention is directed to non-rigid, non-spherical airships having an envelop contained within the airship and at least one further envelop contained therein for holding a volume of lifting gas.

Abstract: An airship with a lifting gas cell system comprises an airship that contains a plurality of partitions and a plurality of diaphragms, wherein the partitions and diaphragms are configured to form a number of gas cells that contain a lifting gas such as helium, and a single air cell that contains air. As a result, during the ascent and descent of the airship the number of gas cells ensures that the lifting gas is uniformly distributed over the entire length of the airship, whereas the air cell allows a large amount of air to be retained during a descent.

Abstract: One embodiment of the invention provides an airship having an outer tube formed in the shape of a toroid and defining a central opening, a first compartment positioned within the outer tube and containing a first gas, and a second compartment positioned within the outer tube and containing a second gas. The airship may also include top and bottom covers further defining and enclosing the central opening, the central opening containing the second gas, and a controller that controls the flow of the first gas into and out of the first compartment to actively control the ascent and descent of the airship.

Abstract: An airship (100) for conveyance through a fluid medium in a selected direction of travel. The airship includes a hull adapted to contain a lifting medium therein, wherein the hull (108) includes a first section having a width which varies along the selected direction of travel, the width increasing from a bow of the hull to a maximum width and decreasing from the maximum width to a tail section of the first section; and a second section coupled to the first section and having a width which varies along the selected direction of travel, the width increasing from a leading edge of the second section to a maximum width and decreasing from the maximum width to a stern of the hull.

Abstract: A method for applying pressure to the area of a composite part masked by a secondary feature comprises the steps of positioning a pressure augmentation strip in contact with the masked area, securing a pressure transfer wedge on each of two sides of the secondary feature, such that pressure is transferred to the pressure augmentation strip during co-curing/co-bonding, and co-curing/co-bonding the composite part and the secondary feature. When the area between the composite part and the secondary feature is fairly large, the method can comprise the further steps of positioning a sine wave spring between the pressure augmentation strip and the secondary feature, injecting a structural paste adhesive into the voids around the sine wave spring, and curing the structural paste.

Abstract: The invention concerns a lighter-than-air craft for transporting by air equipment and passengers, more particularly, it concerns an aircraft whereof the frame (1) made of light metal and erected vertically, contains and protects the passenger compartment (4) of the invention, and all the components of the invention which, by a mass-reducing assembly (2-8-9-11-19), uses light gas power for neutralizing the earth's gravitational pull. Electric motors actuating propellers (6-7) with multiple blades and powered by a mini-electric power unit (5) enable to counter the force of mean winds, so to lift the neutralized mass and control the aircraft movements. The aircraft wide external surfaces (11-12) are used as wing system, a sailboat keel being replaced by a gyroscope (10) stabilizing effect and by the thrust of the lateral propellers (6).

Abstract: An airship (100) for conveyance through a fluid medium in a selected direction of travel. The airship includes a hull adapted to contain a lifting medium therein, wherein the hull (108) includes a first section having a width which varies along the selected direction of travel, the width increasing from a bow of the hull to a maximum width and decreasing from the maximum width to a tail section of the first section; and a second section coupled to the first section and having a width which varies along the selected direction of travel, the width increasing from a leading edge of the second section to a maximum width and decreasing from the maximum width to a stern of the hull.

Abstract: A method comprises: launching observation means configured to observe upper air environment immediately before launching an airship to acquire ambient air data on the actual conditions of the upper ambient air including altitude, pressure, wind direction, wind speed and temperature; determining an ascension profile for the airship by simulation using the ambient air data on the actual conditions of the ambient air; determining an initial quantity of Helium gas conforming to the actual conditions of the ambient air; and adjusting the quantity of Helium gas in the Helium room to the initial quantity of Helium gas to set an initial buoyancy. The method sets hull parameters for the hull of the airship to provide an ascension profile conforming to the actual conditions of the ambient air.

Abstract: The invention seeks to provide a dirigible balloon with an internal enclosure (V2) having a flexible wall (4) contained in an outer rigid enclosure (15) which is of aerodynamic shape. The internal enclosure (V2) contains helium and is provided with means (5, 6, 7, 8) enabling its volume to be modified. Thus, depending on the volume given to the internal enclosure (V2) of the dirigible balloon, landing, take-off, and altitude variation are easy to perform. The means for modifying the volume of the internal enclosure (V2) comprise a cable (8) connected to the internal enclosure (V2) by means of a set of pulleys (5, 6), and a winch (7) for reducing the length of the cable (8).

Abstract: A system and method for constructing an airship hull is described, comprising a plurality of flexible members disposed lengthwise about the perimeter of the airship skin. The flexible members can be held in place in sleeves on the skin of the airship. The ends of the flexible members are drawn toward one another by tensioning means, causing the members to bow outwardly from a central axis and providing a rigid structure for the skin.

Abstract: A lighter-than-air ship using hydrogen or other gas as a lift gas with at least one hydrogen fuel cell aboard. The fuel cell can draw hydrogen fuel from the lift gas reservoir to produce electricity both for the ship's use and optionally for propulsion. The waste product of the fuel cell is water which can be used for the needs of a crew on the ship. The hydrogen lift gas chamber, which can be compartmentalized for lift control, can be surrounded by a safety jacket filled with an inert gas and contain optional hydrogen and/or oxygen sensors.

Abstract: A variable-lift device using a helium to fly. The device comprises a balloon (1) composed of an outer flexible envelope (3) supported by a rigid structure. The rigid structure comprises a plurality of hollow toruses (4) of inside volume that acts as a tank for storing helium under pressure.

Abstract: A membrane structure includes an airtight pressure-resistant gasbag and a shape maintaining mechanism which maintains the gasbag in a predetermined shape when the gasbag is in a fully inflated state. The gasbag includes a plurality of spindle-shaped gores of an airtight membrane material, adjacent gores joined together at edges, and a plurality of reinforcing ropes attached to joined sections of the edges, the reinforcing ropes extending along the edges, respectively. Each of the gores outwardly protrudes between two adjacent reinforcing ropes extending along the edges of the gore, respectively, without elongation of the airtight membrane material, when the gasbag is in the fully inflated state. Each protruding gore has a radius of curvature in a direction intersecting the two adjacent reinforcing ropes. The radius of curvature is smaller than a radius of the gasbag.

Abstract: To respond to internal threats to the aircraft, an incapacitating aerosol can be released into the cabin of the aircraft. The incapacitating aerosol prevents the hijackers or terrorists from accomplishing their goals. While the hijackers or terrorists are incapacitated, the pilot can land the aircraft at the first opportunity and let trained security forces, such as the police, board the aircraft and deal with the hijackers/terrorists.

Abstract: An improved airship that is uniquely constructed so as to be inexpensive yet easy to pilot and highly maneuverable includes an outer skin that defines a nose portion and a tail portion of the airship and an internal envelope. At least one gas bag is contained within the envelope. A gondola is secured to and positioned beneath the outer skin. Most advantageously, a propulsion mechanism is positioned proximate to the tail portion and is constructed and arranged to create propulsive thrust that is vectored so as to be substantially colinear with a centerline of the airship that extends through the nose portion and the tail portion of the airship. The airship also may include a ballonet-free internal pressurizing system that introduces outside air into a location between the outer skin and the gas bag when pressure at that location has reached a predetermined minimum pressure. As a result, the envelope is sufficiently pressurized to maintain its outer shape without use of a ballonet.

Abstract: A stratospheric airship capable of substantially and smoothly varying the volume of a buoyant gas is provided so as to allow the airship to stably ascend into the stratosphere and keep a station therein. A stratospheric airship includes a gas envelope defined by a ship hull, the gas envelope being divided by a diaphragm into a buoyant gas compartment containing a buoyant gas and an air compartment containing air, the stratospheric airship being allowed to ascend by varying the volume ratio between the buoyant gas and the air, wherein the periphery of the diaphragm is coupled to the ship hull generally at the midpoint along the vertical dimension thereof, and a central portion of the diaphragm is coupled to a suspension chord whose upper and lower ends are coupled respectively to the upper and lower surfaces of the ship hull. The sloshing phenomenon of the diaphragm is suppressed, whereby the change in the shape thereof is balanced, and thus there is no asymmetric distribution of the buoyant gas.

Abstract: A stratospheric balloon comprising on the one hand an external flexible envelope (1) having a natural shape and made of transparent synthetic material and presenting an air inlet and, on the other hand, an internal screen (2) made of visible and infrared energy collecting material and having the shape of a surface generated by a mobile generatrix parallel to the longitudinal symmetry axis of the external envelope. The internal shield is connected to the envelope (1) by attachments arranged at the upper part of the envelope at a distance from the longitudinal axis of the latter, and extending longitudinally freely inside the envelope (1) without contacting it.

Abstract: A neutral buoyancy fuel bladder uses hydrogen and oxygen to power an airship. The neutral buoyancy fuel bladder includes a fuel cell, electrolyzer, and means for storing hydrogen, oxygen and water. The fuel cell uses the hydrogen and oxygen to create heat, water and current flow. An energy source transmits a beam to an energy receiving unit on the airship, and the energy from said beam is used to (1) power said airship, and (2) replenish the supply of hydrogen and oxygen.

Abstract: An airship capable of vertical and horizontal flight and able to make right angle turns is preferably of nearly neutral buoyancy and comprises two gas bags, the lower of which is toroidal in shape and surrounds a centrally located engine that has a downwardly facing inlet. Upwardly directed thrust from the engine is redirected by a gate valve arrangement into a manifold of ducts, each of which passes between the upper and lower gas bags to a respective outlet or nozzle adjacent the periphery of the aircraft. To fly the aircraft, a pilot uses the cable-operated valve arrangement to manage the distribution of thrust from the engine into selected ones of the ducts to provide thrust in a desired direction. Preferred pilot operated controls comprise a foot pedal and a rotatable steering wheel mounted on a pedestal hingedly attached to the gondola of the aircraft for fore and aft pivoting motion.