Abstract: An aerial load lifting system features a non-rigid or blimp-type dirigible providing a lighter-than-air envelope that is placed within a structural shell. The system is designed so that the envelope provides essentially neutral buoyancy for the structure, leaving only the cargo weight to be lifted by the rotors. The structural shell supports the engine, fuel tank, rotors, and transmission system that power the lift and vectoring of the aircraft, in addition to supporting the cargo load. The structural shell transfers the weight of the load directly to the location of the rotors, thus avoiding stress on the envelope.

Abstract: A system allowing for the controlled propulsion of aircraft, especially buoyant and semi-buoyant airships designed as a symmetric body of revolution, without the need for or use of aerodynamic control surfaces, comprised of a plurality of ducted fan thrusters placed both fore and aft, designed to ingest air flowing at less than free stream velocity. Fans are arranged such that when at standard orientation, the thrust from each is directed tangentially to an arc drawn along the hull from bow to stem. By defining multiple sets of thrusters based upon their location, differential thrust may be applied based upon set membership in order to affect translational and rotational maneuvering of the aircraft.

Abstract: The present invention describes lighter-than-air vehicles. An exemplary embodiment of the present invention provides a lighter-than-air vehicle having a payload module, the payload module including an engine. Furthermore, the lighter-than-air vehicle includes a non-rigid envelope in communication with the payload module. The lighter-than-air vehicle also provides a propulsion system that includes a plurality of thrusters, the thrusters positioned substantially near the equatorial plane of the non-rigid envelope. In an alternative exemplary embodiment, the present invention provides a lighter-than-air vehicle comprising a payload module and a non-rigid envelope in communication with the payload module. Furthermore, the lighter-than-air vehicle includes a hydraulic propulsion system in communication with the non-rigid envelope and the payload module.

Abstract: An orientation system is disclosed for a lighter-than-air aircraft having a lower stage suspended from an envelope. The orientation system includes cords interconnecting the envelope and the lower stage and means for adjusting the length of at least one of the cords between the lower stage and the envelope. Adjusting the length produces a shift in the angle of attack of the envelope with respect to the lower stage.

Abstract: An airship including a hull having a lenticular shape and a fairing attached to the hull to act as a stall strip and reduce the lift generated by the hull. The hull is symmetrical along a central horizontal plane and the fairing may be positioned along the central horizontal plane. The fairing may have a triangular shape, a semi-circular shape or any other shape capable of disrupting the flow of air over the hull.

Abstract: A dehumidification system for removing water vapor from the within the envelope of an airship comprises a pressurizer valve, a blower and a dehumidifier attached to the airship. The pressurizer valve releases air from the envelope and directs the air to the blower. The blower forces the air through the dehumidifier where the air is dried to a desired dew point. The dried air is then forced back into the envelope of the airship, thus reducing the weight of the airship and reducing the amount of condensate that may form during an ascent.

Abstract: An differential expansion system and method for balloon buoyancy control which includes a zero-pressure envelope and a superpressure envelope. A gas transfer device is positioned between the envelopes to facilitate the transfer of lift gases that are lighter than air between the envelopes. The superpressure envelope and the gas transfer device can be located inside the zero-pressure envelope. Alternatively, the zero-pressure envelope, the superpressure envelope, and the gas transfer device can be located inside a zero-pressure envelope.

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 airship may include a hull substantially shaped as an oblate spheroid, one or more frame members defining a support structure, wherein the support structure forms at least a partial support for the hull, at least one horizontal stabilizing member operably coupled to a lower surface of the airship, and at least one horizontal stabilizing member having a first end and a second end. The at least one horizontal stabilizing member may define an anhedral configuration. The airship may also include a vertical stabilizing member having a first end pivotally coupled to the airship and a second end oriented to remain below an upper surface of the airship. The vertical stabilizing member may be configured to pivot within a vertical plane, and the first end of the vertical stabilizing member and the first end of the at least one horizontal stabilizing member may be operably coupled to one another.

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 device for deploying an aerostat includes a cylindrical shaped container having an open end and a closed end and a center tube axially oriented in the container. A tapered disc is mounted for axial movement on the center tube, and it has a taper of increasing diameter in an axial direction from the closed end toward the open end of the container. In its operation, the tapered disc is held in a first position while a portion of the aerostat is loaded into the container. It is then moved to a second position wherein the tapered disc holds the loaded portion of the aerostat in the container. Thereafter, the disc is moved to a release position wherein the disc directs deployment of the aerostat from the container.

Abstract: The invention relates to a mechanism to control the pitch and/or roll and/or center of gravity of a vehicle. The first embodiment is a track-based mass transfer system in which pathways are positioned along or radially terminate at a central horizontal plane of the vehicle to move one or more mass transfer devices to a desired location to control the pitch and/or roll and/or center of gravity of the vehicle. A second embodiment is a fluid mass distribution system in which one or more conduits selectively distribute a fluid to one or more tanks positioned near a central horizontal plane of the vehicle to control the pitch and/or roll and/or center of gravity of the vehicle.

Abstract: An unmanned, lighter-than-air airship includes three omnidirectional thrust generating units. One unit is mounted at the fore-end of the airship to generate thrust in a plane that is perpendicular to the longitudinal axis of the airship. This unit controls pitch and yaw movements of the airship. The other two units are mounted on the airship equidistant from the first unit, and are located in a same midships plane that is perpendicular to the longitudinal axis. These two units generate thrust vectors that control roll movements of the airship and provide propulsion for the airship.

Abstract: In one aspect, a hybrid airship including an outer shell, a plurality of helium filled gas envelopes, and an all-electric propulsion system may have the shape of a delta-wing. In some embodiments, the hybrid airship may be launched using buoyancy lift alone and aerodynamic lift may be provided by the all-electric propulsion system. In one aspect, a photovoltaic array and a high energy density power storage system may be combined to power the propulsion system making the propulsion system regenerative. The delta-wing shape can provide a surface area large enough to accommodate very large circular or elliptical transmission devices. By continuously recharging the power storage system, the hybrid airship in accordance with some embodiments can stay aloft at an operational altitude of at least about 85,000 ft for months or even years. The hybrid airship may function as an airborne military communications relay platform.

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: An airship has a generally spherical shape and has an internal envelope for containing a lifting gas such as Helium or Hydrogen. The airship has a propulsion and control system that permits it to be flown to a desired loitering location, and to be maintained in that location for a period of time. In one embodiment the airship may achieve neutral buoyancy when the internal envelope is as little as 7% full of lifting gas, and may have a service ceiling of about 60,000 ft. The airship has an equipment module that can include either communications equipment, or monitoring equipment, or both. The airship can be remotely controlled from a ground station. The airship has a solar cell array and electric motors of the propulsion and control system are driven by power obtained from the array. The airship also has an auxiliary power unit that can be used to drive the electric motors.

Abstract: Apparatus and method are provided for detecting and responding to aircraft emergencies and, in particular, thwarting attempts to hijack an aircraft including the storage in aircraft computer memory of a pattern of aircraft flight characteristics assumed to be unique to aircraft controlled by hijackers. The invention also periodically detects real-time flight characteristics from the aircraft automatic sensing apparatus and compares the real-time flight characteristics with the stored patterns of assumed aircraft flight characteristics of a hijacked aircraft. The assumed aircraft flight characteristics includes thresholds such as exceeding given airspeeds or altitudes less than a specific altitude. If an assumed stored pattern is matched by the real-time flight characteristics, automatic control is taken of the autopilot, attempts to manually control the aircraft are overridden and the aircraft is caused to automatically begin flying in an emergency holding pattern.

Abstract: An airship system according to the invention has an airship (110), a base station (120), and at least three measurement points. The airship (110) emits ultrasonic waves upon receiving an instruction from the base station (120). Measurement point units (S1-S3) receive the ultrasonic waves, and thereby measure distances from the airship (110) to the respective measurement points. An MPU that is incorporated in the base station (120) calculates a position of the airship (110). The base station (120) controls a route of the airship (110) based on the calculated position by sending a flight instruction to the airship (110). In this manner, an airship system can be provided that makes it unnecessary for an operator to pilot the airship and that can reduce the load weight and the power consumption of the airship.

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 system according to the invention has an airship (110), a base station (120), and at least three measurement points. The airship (110) emits ultrasonic waves upon receiving an instruction from the base station (120). Measurement point units (S1-S3) receive the ultrasonic waves, and thereby measure distances from the airship (110) to the respective measurement points. An MPU that is incorporated in the base station (120) calculates a position of the airship (110). The base station (120) controls a route of the airship (110) based on the calculated position by sending a flight instruction to the airship (110). In this manner, an airship system can be provided that makes it unnecessary for an operator to pilot the airship and that can reduce the load weight and the power consumption of the airship.

Abstract: An airship is provided including a frame and first and second hulls pivotally connected to said frame. An airship second is provided including a frame, a gondola disposed within said frame, first and second hulls pivotally connected to said frame, and a propulsion system connected to said frame. Methods are provided for landing on water and refueling.

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: An airship comprises a fuselage and a supporting structure positioned within the fuselage. An air passageway extends through the fuselage in an axial direction, with this air passageway having air inlet openings at the forward end of the airship with a first passageway tapering inwardly to provide a venturi in a mid region of the airship. A second passageway downstream of the venturi continues to the rear end of the airship where it flow-connects to a variable pitch rearwardly projecting air nozzle. An air turbine is mounted in the narrowest region of the venturi and is adapted to generate electricity. A plurality of adjustable air wings project outwardly from the surface of the fuselage, these air wings being arranged in circumferential rows. Cargo areas are provided at the bottom of the fuselage. A unique berthing post is used with the airship.

Abstract: An airship comprises a fuselage and a supporting structure positioned within the fuselage. An air passageway extends through the fuselage in an axial direction, with this air passageway having air inlet openings at the forward end of the airship with a first passageway tapering inwardly to provide a venturi in a mid region of the airship. A second passageway downstream of the venturi continues to the rear end of the airship where it flow-connects to a variable pitch rearwardly projecting air nozzle. An air turbine is mounted in the narrowest region of the venturi and is adapted to generate electricity. A plurality of adjustable air wings project outwardly from the surface of the fuselage, these air wings being arranged in circumferential rows. Cargo areas are provided at the bottom of the fuselage. A unique berthing post is used with the airship.

Abstract: A plurality of bulkheads (23a to 23d) are installed in a hull (21) so as to divide the interior space of the hull (21) into a plurality of compartments (&Dgr;S1 to &Dgr;S5) successively arranged along the axis (22) of the hull (21). The compartments (&Dgr;S1 to &Dgr;S5) are divided into upper flotation gas containing spaces (25a to 25e) and lower air containing spaces (26a to 26e) by flexible diaphragms (24a to 24e) impermeable to air and a flotation gas, respectively. The bulkheads (23a to 23d) have upper parts A1a, A1b, A1c and A1d formed of a meshed sheet, extending upward from joints (27a to 27d) of the diaphragms (24a to 24e) and the bulkheads (23a to 23d), exposed to the flotation gas containing spaces (25a to 25e). The upper parts are provided with a plurality of vents through which the flotation gas is allowed to flow.

Abstract: An airship has a generally spherical shape and has an internal envelope for containing a lifting gas such as Helium or Hydrogen. The airship has a propulsion and control system that permits it to be flown to a desired loitering location, and to be maintained in that location for a period of time. In one embodiment the airship may achieve neutral buoyancy when the internal envelope is as little as 7% fall of lifting gas, and may have a service ceiling of about 60,000 ft. The airship has an equipment module that can include either communications equipment, or monitoring equipment, or both. The airship can be remotely controlled from a ground station. The airship has a solar cell array and electric motors of the propulsion and control system are driven by power obtained from the array. The airship also has an auxiliary power unit that can be used to drive the electric motors.

Abstract: An adjustable weight ballast for lighter-than-air balloon with a predetermined lift is disclosed, comprising at least two individual weights. There is a first means on each individual weight for selectively attaching two or more weights to each other to form a composite weight having a total weight at least equal to the predetermined lift of the balloon, and a second means for tethering the lighter-than-air balloon to this composite weight, in which manner a ballast for a balloon can have its weight incrementally adjusted to an amount just greater than the balloon's predetermined lift to thus securely tether the balloon to a surface on which the composite weight is supported without significantly exceeding the lift of the balloon.

Abstract: An adjustable weight ballast for lighter-than-air balloon with a predetermined lift is disclosed, comprising at least two individual weights. There is a first means on each individual weight for selectively attaching two or more weights to each other to form a composite weight having a total weight at least equal to the predetermined lift of the balloon, and a second means for tethering the lighter-than-air balloon to this composite weight, in which manner a ballast for a balloon can have its weight incrementally adjusted to an amount just greater than the balloon's predetermined lift to thus securely tether the balloon to a surface on which the composite weight is supported without significantly exceeding the lift of the balloon.

Abstract: The remote-controlled air, land or water borne toy vehicle comprises: a body; a printed circuit board mounted in or to the body; a receiver connected to the printed circuit board for receiving commands; hardware on the printed circuit board including control circuitry for manipulating the toy vehicle in response to commands received by the receiver; and a motor drive mechanism mounted on or to the toy vehicle for moving or propelling the toy vehicle in response to control signals from the control circuitry. Preferably at least one of several infrared emitting simulated weapons are mounted on the toy vehicle and are selected from the group including a machine gun, a cannon and a missile.

Abstract: A plurality of bulkheads (23a to 23d) are installed in a hull (21) so as to divide the interior space of the hull (21) into a plurality of compartments (&Dgr;S1 to &Dgr;S5) successively arranged along the axis (22) of the hull (21). The compartments (&Dgr;S1 to &Dgr;S5) are divided into upper flotation gas containing spaces (25a to 25e) and lower air containing spaces (26a to 26e) by flexible diaphragms (24a to 24e) impermeable to air and a flotation gas, respectively. The bulkheads (23a to 23d) have upper parts A1a, A1b, A1c and A1d formed of a meshed sheet, extending upward from joints (27a to 27d) of the diaphragms (24a to 24e) and the bulkheads (23a to 23d), exposed to the flotation gas containing spaces (25a to 25e). The upper parts are provided with a plurality of vents through which the flotation gas is allowed to flow.

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: An airship system according to the invention has an airship (110), a base station (120), and at least three measurement points. The airship (110) emits ultrasonic waves upon receiving an instruction from the base station (120). Measurement point units (S1-S3) receive the ultrasonic waves, and thereby measure distances from the airship (110) to the respective measurement points. An MPU that is incorporated in the base station (120) calculates a position of the airship (110). The base station (120) controls a route of the airship (110) based on the calculated position by sending a flight instruction to the airship (110). In this manner, an airship system can be provided that makes it unnecessary for an operator to pilot the airship and that can reduce the load weight and the power consumption of the airship.

Abstract: A submersible water toy comprises a buoyant streamlined body and a pair of wings attached thereto. While the body encourages the vehicle to rise in water, the wings, being formed from thin flat members resist vertical movement while providing little resistance to forward motion. The centerline of the wings is positioned behind the center of gravity of the bode so that the vehicle will rise in a forward direction while the wings resist vertical movement. Upon release, the submerged water toy will glide at relatively high speeds in a forward direction while slowly rising to the surface.

Abstract: A lighter than air airship is disclosed that has an internal weight supporting structure. The weight supporting structure allows the airship to enjoy the advantages of both static and dynamic lift. The airship disclosed herein is lifted by both lighter than air gasses as well as wings attached to the internal weight supporting structure. A cargo container for use with the airship is also disclosed.

Abstract: A lighter than air aircraft has a non-jettisonable ballast comprised of a liquefied lighter than air gas contained within an insulated container. The liquefied gas is vaporized and released into the lift compartment of the aircraft which is at least partially filled with a lifting gas. A heat exchanger, separate from the means delivering the vaporized gas to the lift compartment, increases the temperature of the vaporized gas prior to entry of the vaporized gas into the lift compartment, wherein the vaporized gas becomes mixed together with lifting gas and whereby damage to the compartment by excessive cooling is minimized.

Abstract: A global communications network comprises a plurality of aerial platforms or vehicles deployed at an altitude in or near the stratosphere and permitted to drift in a controlled manner such that each platform adjusts its position relative to other aerial platforms. Each aerial platform has a propulsion system and control surfaces and preferably includes a lighter-than-air component to maintain lift in an economical manner. Each aerial platform also includes a payload, means for communicating with other aerial platforms and a control system including location-finding equipment and a processor adapted for directing the platform's propulsion system and control surfaces to effectuate changes in the aerial platform's position relative to other aerial platforms based on position information, and optionally on other factors such as terrestrial demand for services provided by the payload of the aerial platforms.

Abstract: A cyclical thermal management system is provided for responding to diurnal heating and nocturnal cooling cycles to maintain a high altitude platform in a geostatic position for long periods of time. The novel cyclical thermal management system utilizes solar energy collection devices to collect solar energy which is stored and utilized to operate physical and chemical exothermic processes for heating the lifting gas of the novel high altitude platform at night and to operate physical and chemical processes during the day for transferring the heat of the lifting gas to maintain a particular geostatic position. The cyclical thermal management system utilizes a recyclable energy storage material which is utilized in not only the cyclical thermal management of heat diurnally but also to provide for seasonal and longitudinal variation by increasing or decreasing the volume of lifting gas or by increasing or decreasing the amount of the energy storage material.

Abstract: Airship tail fins (20) deflect under excessive load on axii (108,110) to protect the airship hull (22) and also reduce angles of attack to disturbing airflow. A propulsion engine (24) may be mounted to the tail fin structure. A longitudinally elongated roller (36) may be mounted to the lower tail fin to act as landing gear. Two widely separated lower tail fins may control pitch and roll when moored by providing secure attachment points, as at shaft (38), for ground handling.

Abstract: An aircraft of the present invention has an envelope used in such an air balloon and/or airship. The aircraft can be in flated continuously to the envelope with supplying an air into the envelope without extending the envelope on the ground, and the envelope can be rolled up continuously into the gondola with an inside-out condition, as keeping the inflating condition of the envelope.

Abstract: A method and apparatus for controlling the flight direction of a blimp. The blimp includes an elongate fuselage for containing a lighter-than-air gas, a movable rudder located toward a tail end of the fuselage, and at least one propeller mounted on a side of the fuselage. The propeller is attached to the blimp by a connection that provides two axes of movement. The propeller connection can be rotated or pivoted (1) about a first axis which is a horizontal axis that is perpendicular to a direction of the longitudinal axis of the elongate fuselage, and/or (2) about a second axis which is a vertical axis that is perpendicular to the direction of the longitudinal axis of the fuselage.

Abstract: A sensor mount apparatus includes a loop for carrying a sensor payload. An upper portion of the loop includes at least one upper attachment point for receiving at least one upper tether line. A lower portion of the loop includes at least one lower attachment point to connect the sensor mount apparatus to a lower tether line. The sensor mount apparatus further includes an upper plate mounted to the loop, a lower plate for carrying a sensor payload, and a slide mechanism mounted between the two plates. The slide mechanism operates to slidably move the lower plate relative to the upper plate so that the lower plate and sensor payload attached to the lower plate move to a position where the sensing device of the sensor payload is not obstructed by the loop. Where the sensor payload is an optical sensor, such as a camera, the camera may be positioned to see an unobstructed, three hundred sixty degree field of view.

Abstract: An aerostat, including an aerostat hull and a single ballonet, attached to said aerostat hull, along an attachment line, the attachment line dividing a helium compartment formed by said aerostat hull into a forward helium compartment and an aft helium compartment, wherein a ratio of a volume of the forward helium compartment to volume of the aft helium compartment is equal to a ratio of a volume of the single ballonet forward of the attachment line to a volume of the single ballonet aft of the attachment line.

Abstract: A venting valve in a hot air balloon comprises a valve member for opening and closing on outlet hole in the balloon envelope, the valve member being in the form of a flat panel having an edge portion secured along a line to a portion of the envelope adjacent an edge portion of the outlet hole. There is a cord and pulley arrangement for drawing the valve member to and fro across the outlet hole, moving substantially transversely of the outlet hole, to close and open the outlet hole. The cord and pulley arrangement can be operated both to open and to close the valve, closing movement being possible from any partially or fully open position of the valve, and, in one form, also, from the valve member fully closed position, to obtain re-closable venting without moving the valve member transversely of the outlet hole.

Abstract: A lighter than air apparatus is provided with a gas impermeable sheeting material having a pathway either extending through the apparatus itself or adjacent to the apparatus. One or more control surfaces are provided proximately to an aperture in the pathway for deflecting air passing through the pathway. A propulsion unit with the pathway propels air through pathway. The pathway, the control surfaces, and the control unit allow the lighter than air apparatus to control its bearing and efficiently maintain its position over the Earth.

Abstract: A burner system for a radio-controlled hot air balloon. The frame that is connected to an envelope contains two fuel tanks. One fuel tank is disposed right side up and delivers fuel in vapor form to a pilot burner mechanism. The other fuel tank is inverted and delivers in liquid form to a burner coil means. The flame of the pilot burner mechanism partially heats the liquid fuel in the burner coil means so that when a valve member is opened, fuel in a vaporous mist form is discharged from an outlet orifice of the burner coil means for ignition by the flame of the pilot burner mechanism. A radio-controlled servo is connected to the valve member and operates the same.

Abstract: The invention is a ballonet system for a lighter-than-air-vehicle, the vehicle having a lift producing gas bag and a longitudinal, vertical and lateral axis. In detail, the ballonet system includes a plurality of ballonets located within the gas bag positioned along the longitudinal axis and on each side of the vertical axis of the vehicle. Each of the ballonets include a flexible sheet joined at its periphery thereof to a portion of the wall of the gas bag. A ballonet pressurization system is coupled to each ballonet for pressurizing them with air that includes the portion of the wall of the gas bag forming the ballonet having a plurality of holes therethrough. A manifold having an inlet port is joined to the wall covering the holes therein and is adapted to diffuse the pressurized air entering therein.

Abstract: A novel, high-altitude, solar powered aircraft, capable of staying aloft at high altitudes for many months or even years to conduct around the clock surveillance and/or reconnaisance, includes a forward wing with solar energy capturing cells, a rear wing, inflated pontoons for keeping the aircraft aloft, suspension wires attached to the pontoons, a gondola suspended from and connected to the wires, control apparatus for moving the gondola along the wires, shifting the weight of the aircraft and thereby enabling banking to optimize exposure of the solar cells to the rays of the sun. The gondola preferably contains a sensor suite, power generating and storage apparatus, and synthetic aperture radar imaging apparatus.

Abstract: The invention is a propulsion system for a lighter-than-air vehicle. In detail the propulsion system includes a pylon having a longitudinal axis and first and second ends, the first end of the pylon rotatably mounted to the vehicle and the second end extending outward from the vehicle. The pylon is rotatable about the first end in a plane perpendicular to the longitudinal axis of the vehicle. A thrust producing assembly is mounted on the second end of the pylon and is rotatable about an axis of rotation in a plane perpendicular to the longitudinal axis of the pylon. A powerplant assembly is coupled to the thrust producing assemblies to provide power thereto. An actuation system is provided for rotating the assembly about the axis of rotation. A second actuation system is provided for rotating the pylon about the first end.

Abstract: An airship includes a gas envelope filled with a buoyant gas, a duct equipped with an internal propulsion fan and attached to the aft of the gas bag, a boom projecting aft along an extension of the axis of the propulsion fan and an empennage provided on the distal end of the boom and is constituted to prevent boundary layer separation by causing the propulsion fan to suck air flowing along the hull surface into the duct and jet it aft.