Abstract: A lighter than air airship (1) comprising a gas-filled flexible hull (2) which is elongate with a longitudinal axis (1?) and with a front end (4) and a rear end (5), wherein a harness-structure (3) is abutting an outer side of the hull (2) and not perturbing the hull and not extending through the hull, the harness-structure (3) is made of a bendable material and carries a propeller engine (10) for forward thrust of the airship (1), rechargeable batteries (11) for providing electrical power to the propeller engine (10), and a solar panel for providing electrical power to recharge the batteries (11).

Abstract: An air duct system comprising an air duct having a main body, a visible light source, an emitter configured to emit radio frequency waves, and one or more antennas. The main body of the air duct defines a passageway having a reflective inner surface. The visible light source is configured to generate visible light. The visible light source directs the visible light along the reflective inner surface of the air duct. The emitter directs the radio frequency waves along the reflective inner surface of the air duct. The one or more antennas are each connected to a corresponding power harvesting circuit, where the radio frequency waves are received by the one or more antennas and are converted into electrical power by the corresponding power harvesting circuit.

Abstract: An unmanned aerial vehicle (UAV) has: a body for carrying an article; at least one rotor; and a light source for generating a light beam to indicate the landing zone for the UAV. The UAV, in use, is flown to a desired location, that might be a site of an emergency with no defined landing zone. The UAV descends, and, while descending the light source is operated to illuminate and to define a landing zone. The UAV can be provided with lights and an audio source to warn and advise bystanders that the UAV is landing and to stand clear of the landing zone.

Abstract: A method for controlling an aerial system with a rotor enclosed by a housing, including: operating the rotor in a flight mode, detecting a grab event indicative of the aerial system being grabbed, and automatically operating the rotor in a standby mode. A method for controlling an aerial system including a central axis extending normal to a lateral plane of the aerial system, including: generating a first aerodynamic force with a set of rotors enclosed by a housing, detecting that an acute angle between the central axis and a gravity vector is greater than a threshold angle, and operating each rotor of the set of rotors to cooperatively generate a second aerodynamic force less than the first aerodynamic force with the set of rotors.

Abstract: A method for controlling an aerial system with a rotor enclosed by a housing, including: operating the rotor in a flight mode, detecting a grab event indicative of the aerial system being grabbed, and automatically operating the rotor in a standby mode. A method for controlling an aerial system including a central axis extending normal to a lateral plane of the aerial system, including: generating a first aerodynamic force with a set of rotors enclosed by a housing, detecting that an acute angle between the central axis and a gravity vector is greater than a threshold angle, and operating each rotor of the set of rotors to cooperatively generate a second aerodynamic force less than the first aerodynamic force with the set of rotors.

Abstract: A method for controlling an aerial system with a rotor enclosed by a housing, including: operating the rotor in a flight mode, detecting a grab event indicative of the aerial system being grabbed, and automatically operating the rotor in a standby mode. A method for controlling an aerial system including a central axis extending normal to a lateral plane of the aerial system, including: generating a first aerodynamic force with a set of rotors enclosed by a housing, detecting that an acute angle between the central axis and a gravity vector is greater than a threshold angle, and operating each rotor of the set of rotors to cooperatively generate a second aerodynamic force less than the first aerodynamic force with the set of rotors.

Abstract: A power distribution system includes at least a ground power unit, an aerial vehicle, and a power station. The ground power unit is configured to convert an input AC power into DC power output, wherein the ground power unit includes at least a first bus, second bus, and a third bus, wherein the first bus is configured to operate at a first voltage level referenced to the third bus, and wherein the second bus is configured to operate at a second voltage level referenced to the third bus that is different from the first voltage level. The aerial vehicle may include a plurality of motor-generators coupled to a respective plurality of turbines, wherein the plurality of motor-generators may be configured to be energized by power received from a tether.

Abstract: A system may include a tether, a slip ring, a tether gimbal assembly, a drive mechanism, a control system. The tether may include a distal tether end coupled to an aerial vehicle, a proximate tether end, and at least one insulated electrical conductor coupled to the aerial vehicle. The slip ring may include a fixed portion and a rotatable portion, where the rotatable portion is coupled to the tether. The tether gimbal assembly may be rotatable about at least one axis and is coupled to the fixed portion of the slip ring. The drive mechanism may be coupled to the slip ring and configured to rotate the rotatable portion of the slip ring. And the control system may be configured to operate the drive mechanism to control twist in the tether.

Abstract: A method for controlling an aerial system with a rotor enclosed by a housing, including: operating the rotor in a flight mode, detecting a grab event indicative of the aerial system being grabbed, and automatically operating the rotor in a standby mode. A method for controlling an aerial system including a central axis extending normal to a lateral plane of the aerial system, including: generating a first aerodynamic force with a set of rotors enclosed by a housing, detecting that an acute angle between the central axis and a gravity vector is greater than a threshold angle, and operating each rotor of the set of rotors to cooperatively generate a second aerodynamic force less than the first aerodynamic force with the set of rotors.

Abstract: A balloon may include an optical-communication component, which may have a pointing axis. A pointing mechanism could be configured to adjust the pointing axis. The optical-communication component could be operable to communicate with a correspondent balloon via a free-space optical link. For example, the optical-communication component could include an optical receiver, transmitter, or transceiver. A controller could be configured to determine a predicted relative location of the correspondent balloon. The controller may control the pointing mechanism to adjust the pointing axis of the optical-communication component based on the predicted relative location so as to maintain the free-space optical link with the correspondent balloon.

Abstract: Methods and apparatus are disclosed for receiving and transmitting signals at a balloon. Received signals can be received at the balloon, which can include a payload and an envelope. The envelope can include at least a first antenna section and a second antenna section. Both the first and second antenna sections are configured at least to receive the received signals and convey at least the received signals to the payload. The first antenna section can include a first metallization pattern to receive a first type of signal. The second antenna section can include a second metallization pattern to receive a second type of signal, with the first metallization pattern being different from the second metallization pattern.

Abstract: A balloon envelope with a plate secured thereto having an outlet port that provides a passageway from an inside of a balloon envelope to the atmosphere, a bracket extending from the plate, a first linear actuator having a first end attached to the bracket, where a passive valve having a periphery is positioned over the outlet port, where the second end of the linear actuator is attached to the passive valve which is movable 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 outlet port to a second, open position where the periphery of the passive valve is disengaged from the periphery of the outlet port by movement of the second end of the linear actuator to open the passageway between the inside of the balloon envelope and the atmosphere.

Abstract: Methods and apparatus are disclosed for receiving and transmitting signals at a balloon. Received signals can be received at the balloon, which can include a payload and an envelope. The envelope can include at least a first antenna section and a second antenna section. Both the first and second antenna sections are configured at least to receive the received signals and convey at least the received signals to the payload. The first antenna section can include a first metallization pattern to receive a first type of signal. The second antenna section can include a second metallization pattern to receive a second type of signal, with the first metallization pattern being different from the second metallization pattern.

Abstract: The invention relates to an airship including a flexible envelope having no rigid inner structure containing a gas that is lighter than air, and a gondola. The balloon also includes three legs for setting the balloon on the surface and a landing structure. The landing structure is located on the outside of the envelope, and provides a connection between the legs, the gondola and the envelope while surrounding the envelope.

Abstract: Here invented are efficient road vehicles having special aerodynamic shapes, with stabilizing provisions that enable aerodynamic efficiency. It is a vehicle that is configured to include a carriage part that encloses a driver and passenger riding in tandem. This car width is for persons seated in single file, enabling a narrow width that makes a body shaped like an airship practical, where that shape is characterized by a very low drag coefficient in free flow conditions. This body is elevated on struts above a wheel system to enable such free flow aerodynamic conditions, thus, the drag coefficient of the airship is made applicable to this road vehicle. The wheel system includes wheels on each side of the vehicle that are arranged in horizontal columns, to which the struts are attached. The horizontal columns act as individual aerodynamic entities that function independently of the carriage aerodynamic operation.

Abstract: Embodiments according to the methods and systems provide for the selection, assembly, deployment, exploitation of data collected, redeployment, retrieval and stowage of a remotely operated lighter than air (LTA) network of vehicles. From modular components stowed with a mobile platform, one or more LTA vehicles can be assembled, deployed and retrieved. Determining the desirable number of LTA vehicles and the modular components to be assembled for each vehicle can be performed through a computer recommending modular components based on mission parameters. A remote controller device can be used for pre-deployment setup, in-flight mission management and analysis of data gathered by a plurality of possible sensing devise operably attached to the one or more LTA vehicles.

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

Abstract: Lighter-than-air systems, methods, and kits for obtaining aerial images are described. For example, various methods for determining planned ascent, drift, and/or descent of a lighter-than-air system are described. In addition, various structural arrangements of lighter-than-air systems for accomplishing planned ascent, drift, and/or descent and obtaining aerial images are described.

Abstract: Lighter-than-air systems, methods, and kits for obtaining aerial images are described. For example, various methods for determining planned ascent, drift, and/or descent of a lighter-than-air system are described. In addition, various structural arrangements of lighter-than-air systems for accomplishing planned ascent, drift, and/or descent and obtaining aerial images are described.

Abstract: Apparatus and method for a continuous replenishing of the lift gas and maintaining the proper pressure and lift of a tethered medium altitude aerostat utilizing a novel feed tube running the entire length of the tether. A first end of the feed tube is connected to the aerostat while a second end is connected through a novel slip ring means to a pressure controlled helium ballast chamber and scrubber on the ground to maintain pressure and lift by a reversible compressing pump. A plurality of pressure and temperature sensors and tension gauges strategically placed inside and around the airship continuously monitor the temperature and pressure changes in the aerostat. A data retrieval and communication unit mounted on the aerostat collects measurement data from the pressure, temperature and tension sensors which is relayed to the ground station and the data is used to regulate lifting gas pressure inside the aerostat.

Abstract: The mobile aerial sustained solar power-plant (MASP) provides an improved method and device for the highly efficient collection, storage, transport, and wireless delivery of renewable energy from an airborne platform. This energy can be used to supply electrical power to clients or be used to power directed energy weapons.

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 neutrally buoyant flying toy has a tail fin assembly and a movable weight element that are configured such that the toy moves forward and can be steered left and right by controlled motion of the tail fin, and such that the toy ascends or descends by controlled motion of the weight element. Most preferably, the toy is configured as a fish and is remote controlled.

Abstract: Provided is a flight device which can utilize headwind and following wind, respond flexibly to changes of wind directions and travel stably. The flight device includes a main body with an air sac. It also includes a forward air resistance changing unit and a backward air resistance changing unit that lies anterior and posterior to the main body in traveling direction, respectively. They are controlled by a controller to change air resistance. As a result, the flight device can travel stably despite wind direction. The flight device further includes a wing tilted vertically which provides driving force without gasoline engine. The driving force is gained from vertical wind caused by changing altitude using air sac. Further, the flight device can select the route toward the destination based on the prediction of changes of winds by prediction device.

Abstract: The present invention is generally directed to tapes or laminates designed for use in conjunction with lighter-than-air vehicles, platforms or other inflated structures. In one embodiment, the present invention is directed to tapes or laminates designed for use in logos and/or identification numbers that can be, for example, used on a lighter-than-air vehicle, platform or other inflated structure. In another embodiment, the present invention is directed to tapes or laminates that include, among other layers, at least one dichroic layer designed to produce a logo, letter and/or number that can be, for example, used on a lighter-than-air vehicle, platform or other inflated.

Abstract: The present invention is generally directed to tapes designed for use in conjunction with lighter-than-air vehicles, platforms or other inflated structures. In one embodiment, the present invention is directed to conductive seam cover tape that can be, for example, used to protect and/or cover one or more seams in a lighter-than-air vehicle, platform or other inflated structure. In another embodiment, the present invention is directed to a conductive seam cover tape that can be, for example, used to protect and/or cover fabric panels or sections that are used to form lighter-than-air vehicles, platforms or other inflated structures that are in, one instance, designed for deployment at high altitudes.

Abstract: This invention relates to an aerial transporter comprising rigid cell structures which are covered with light materials as a skin, composed of modules. The invention aerial transporter represents some type of airship without a tail unit as well as an approximate balloon construction comprising a rigid structure and an independent drive unit. Said aerial transporter can transport loads in the range of about 20 t and more over short to medium distances using lighter-than-air technology while meeting air traffic regulations. Furthermore, the disclosed aerial transporter can be used as an air crane in the tied state.

Abstract: An installation platform for deploying an earth-based sensor network utilizing a projected pattern from a height. The installation platform includes an aerostatic aircraft, at least one sensor-location projector, and a projector stabilizer. The sensor-location projector is coupled with the aerostatic aircraft, and is configurable to project the projected pattern including at least one sensor-location marker associated with a location for a sensor in the sensor network. The projector stabilizer is configurable for maintaining the sensor-location projector in a sufficiently static orientation relative to the location for the sensor to allow deployment of the sensor within a specified distance of the location on a surface of the earth from the sensor-location marker. A sensor-network-deployment system along with a method for deploying the sensor-network are also provided.

Abstract: Apparatus and method for a continuous replenishing of the lift gas and maintaining the proper pressure and lift of a tethered medium altitude aerostat utilizing a novel feed tube running the entire length of the tether. A first end of the feed tube is connected to the aerostat while a second end is connected through a novel slip ring means to a pressure controlled helium ballast chamber and scrubber on the ground to maintain pressure and lift by a reversible compressing pump. A plurality of pressure and temperature sensors and tension gauges strategically placed inside and around the airship continuously monitor the temperature and pressure changes in the aerostat. A data retrieval and communication unit mounted on the aerostat collects measurement data from the pressure, temperature and tension sensors which is relayed to the ground station and the data is used to regulate lifting gas pressure inside the aerostat.

Abstract: Embodiments of the present invention relate to concentrating solar radiation using an assembly of at least one clear and one reflective film that inflates into a shape reflecting parallel rays of light to a concentrated focus in the interior or immediate proximity of the assembly. Embodiments of the present invention can be assembled in a substantially flat stack with bonds or welds between the films, compatible with conventional high-throughput film manufacturing processes. Embodiments in accordance with the present invention may employ external circumferential rings or a “harness” assembly to support and point the balloon against wind forces and the like without severe stress localization. Embodiments in accordance with the present invention may also employ film attachments to facilitate feedthroughs, reduce stress concentrations, and modify the inflated shape. Embodiments in accordance with the present invention may also employ film modifiers, including laminated films, adhesives, printing, etc.

Abstract: An optimized lighter-than-air vehicle or airship incorporating a frame 104, internal propulsion 124, perforated covering 102 and lifting-gas cells 110 is disclosed. Optimization features include variations on a Stratford Ramp, means to control the boundary layer 210, absence of unnecessary protuberances and means to reduce the bow wave. A transportable version utilizing a flexible frame 310 and keels 314 is also disclosed along with a means for rapid descent and landing. The operating concept reduces velocity requirements which, in turn, reduce weight and size requirements.

Abstract: Systems and methods for anti-collision lights on a UAV. A method for passive anti-collision lights on a Micro-Aerial Vehicle (“MAV”) including determining a location of the MAV using a flight management computer configured to fly the MAV on a programmed path using data from a global positioning system and an inertial navigation system. The flight management system transmits light activation data and selectively activates at least one navigation light located on a visible surface of the MAV using the light activation data from the flight management computer.

Abstract: Here is invented an efficient road vehicles having special aerodynamic shapes, with stabilizing devices that enable aerodynamic efficiency. It is an articulated vehicle that is tall and narrow. It includes a carriage part that encloses a driver and passenger riding in tandem. This car is only wide enough for persons seated in single file, so it has very low projected frontal area compared with typical cars. Further, the narrow width makes a body shaped like an airship practical, where that shape is characterized by a very low drag coefficient in free flow conditions. The carriage is elevated on struts to enable such free flow aerodynamic conditions, thus the drag coefficient of the airship is made applicable to this road vehicle. Because this car has both low frontal area and low drag coefficient it will require minimal energy for high speed operation.

Abstract: An apparatus for sealing and illuminating a balloon includes a housing for sealing insertion into a neck of a balloon. A flow path within the housing conducts an inflation gas from an inlet to an outlet of the housing, and a flow control system disposed in the flow path allows the inflation gas to flow from the inlet to the outlet. The apparatus includes a light source mounted in conjunction with the housing and a power source disposed within the housing providing power for the light source. A switch mounted in conjunction with the housing is operable to selectively connect the power source to the light source by completing a circuit between the power source and the light source. The apparatus also includes a switch activating member annularly disposable around the housing to operate the switch.

Abstract: The structure provided multi-Levels of the center fuselage, two front wings, Extended mid-two wings and two rear wings with two vertical winglets. The fuselage has a cross section of half circle shaped fuselage. The first level comprises multi-fuel tanks, water tanks, Helium gas tanks, hydraulic, Pneumatic systems and plurality of the multi-landing gear bays and multi-cargo Compartments. The first level comprises a top cockpit and the plurality of the multi-passenger Cabins. The second level is comprises multi-central posts, multi-guy wires on the top center Beams, mid level, lower level center beams, leak proof sealed floor gates for the Multi-gas envelopes structure, under belly multi-pontoon air bags. The first level further comprises multi-jet power plants with multi-chute flaps. The second level may comprises, carbon fiber honey comb sandwich composite Multi-envelopes and multi-level soft gas envelopes.

Abstract: An apparatus for removing harmful gas components out of the earth's atmosphere is a free-flying autonomous lightweight aircraft with an onboard gas processing system including gas separation or extraction devices, and inlets and outlets connected to the devices. Solar cells and/or thermoelectric generators provided on the craft produce electrical energy to operate the individual devices. The system may include a cryogenic closed-loop circulation system that participates in liquefying the extracted gas components. The apparatus is preferably a lighter-than-air craft like a dirigible. A method of extracting harmful gas components from the atmosphere involves flying the apparatus at a prescribed altitude level and operating the gas processing system to remove the harmful gas component from the atmosphere, then returning the apparatus to earth to offload the liquefied stored harmful gas component.

Abstract: A Wind energy conversion apparatus comprising a wind turbine supported by, or integral with, a lighter-than-air structure, the part of the turbine that rotates being rotated by the wind whilst at the same time absorbing substantially all of the force of the wind so that the position of the apparatus can be maintained.

Abstract: An apparatus for launching and recovering a lighter-than-air aircraft is provided. The aircraft includes an envelope that is substantially filled before launch with a lift gas and a second gas. The lift gas and second gas are substantially separated in the envelope by a boundary layer of mixed gas, formed by the lift and second gases. The aircraft is supported by one or more masts as the lift gas is injected to achieve the required buoyancy for launch. The aircraft is then released and rises, for example, in an inclined orientation. As the aircraft climbs, the lift gas expands in the envelope, and the second gas is vented therefrom. During horizontal descent, air can be pumped into the envelope to maintain the envelope in a substantially filled configuration. The air and lift gas can be mixed to avoid sloshing and pooling.

Abstract: An energy management system for lighter-than-air vehicles which includes a reactor means for generating energy, storage means for storing the reactants used in the reactor means, and an integrated pipeless reactant and power distribution means.

Abstract: An apparatus for sealing and illuminating a balloon includes a housing for sealing insertion into a neck of a balloon. A flow path within the housing conducts an inflation gas from an inlet to an outlet of the housing, and a flow control system disposed in the flow path allows the inflation gas to flow from the inlet to the outlet. The apparatus includes a light source mounted in conjunction with the housing and a power source disposed within the housing providing power for the light source. A switch mounted in conjunction with the housing is operable to selectively connect the power source to the light source by completing a circuit between the power source and the light source. The apparatus also includes a switch activating member annularly disposable around the housing to operate the switch.

Abstract: A system for controlling lift of an aircraft comprises an inflatable compartment for containing a gas which is lighter than air. A receiver receives and stores the gas in a compressed condition. Means are provided for compressing the gas and transferring it from the inflatable compartment into the receiver thus reducing the lift force on the aircraft.

Abstract: A laminate material for lighter-than-air vehicles includes at least one monofilament yarn layer, a polymeric film layer adjacent to the at least one monofilament layer, and a metallized coating adjacent to said polymeric film layer. A clear film cover layer may be adhered to the metallized coating, and one or more fluorescent dyes may be incorporated into the clear film layer.

Abstract: An apparatus for sealing and illuminating a balloon includes a housing for sealing insertion into a neck of a balloon. A flow path within the housing conducts an inflation gas from an inlet to an outlet of the housing, and a flow control system disposed in the flow path allows the inflation gas to flow from the inlet to the outlet. The apparatus includes a light source mounted in conjunction with the housing and a power source disposed within the housing providing power for the light source. A switch mounted in conjunction with the housing is operable to selectively connect the power source to the light source by completing a circuit between the power source and the light source. The apparatus also includes a switch activating member annularly disposable around the housing to operate the switch.

Abstract: A propulsion assembly for attachment to the enclosing material of an airship which includes a base which is positioned proximate to the enclosing material. An extension member having opposed ends projects away from the base and includes opposed ends. A motor assembly is attached to the end of the extension member opposed to the base. A mounting assembly is attached to the enclosing material and a plurality of pre-tensioned guy cables connect the mounting assembly to the extension member.

Abstract: A system and method is described generally for providing a high altitude conduit the high altitude conduit includes a first material layer forming an elongated duct. The high altitude conduit also includes a second material layer outside the first material layer. The second material layer defines a space between the second material layer and the first material layer. A gas has a density that is less dense than that of the atmosphere outside of the second material layer. The gas is disposed in the space between the first and the second layer. An introducer is configured to provide the gas into the space between the first material layer and the second material layer. The gas causes the conduit to extend in an approximately upright orientation.

Abstract: A gimbaled truss assembly is disclosed including a frame rotatably mounted in a gimbal mount, and a truss rotatably mounted within the frame. The truss is configured to retain a propulsion system. The frame and the truss rotate independently of one another. A fastening system for mounting the propulsion system to the truss includes vibration isolators. A plurality of braces are coupled to the gimbal mount. The braces conform to the external surface of an air vehicle on which the assembly is to be attached.

Abstract: An apparatus and associated method for launching and recovering a lighter-than-air aircraft are provided. The aircraft includes an envelope that is substantially filled before launch with a lift gas and a second gas. The lift gas and second gas are substantially separated in the envelope by a boundary layer of mixed gas, formed by the lift and second gases. The aircraft is supported by one or more masts as the lift gas is injected to achieve the required buoyancy for launch. The aircraft is then released and rises, for example, in an inclined orientation. As the aircraft climbs, the lift gas expands in the envelope, and the second gas is vented therefrom. During horizontal descent, air can be pumped into the envelope to maintain the envelope in a substantially filled configuration. The air and lift gas can be mixed to avoid sloshing and pooling.

Abstract: A hybrid aerial vehicle is optimized, for example, and not by way of limitation, to operate above 100,000 feet in altitude and provide persistent and maneuverable flight while carrying a wide array of communications and sensing payloads. The hybrid vehicle may use the high altitude winds to gain altitude by pitching up with the center of gravity (CG) control and using its propulsion drive to thrust into the wind to create aerodynamic lift to rise above the neutral buoyancy altitude. The hybrid vehicle will pitch down with the CG control so as to use gravity and propulsion to accelerate. Yaw control directs the flight towards any compass direction by rotating the gondola. This maneuvering capability permits the vehicle to station operate persistently, even in high winds. The lighter-than-air inflatable saucer shape is optimized for maintaining an aerodynamic cross-section to the prevailing wind from any direction in the vehicle horizontal plane.

Abstract: Power generating apparatus (10) including a cable (12) which rotatably mounts a plurality of power units (14). The power units (14) include wind power turbines (46) for producing power from the wind as the power units (14) fly in the sky whilst connected to the cable (12).

Abstract: A large heavy lift airship of lenticular shape is described making use of multiple temperature controlled buoyant cells for smooth control of buoyancy and trim.