100results about "Hybrid airships" patented technology

A method and system for air flight is shown. The blended lifting body system includes a lift module, a propulsion module, a payload module and a control system. A conventional control system morphs the other modules through variable buoyant lift, internal structures and a flexible exterior, and varies bio-inspired oscillation in the propulsion module in order to facilitate takeoff, flight and landing. The hybrid dynamic / morphing shape buoyant, dynamic lift-assisted (hybrid) air vehicle, employing aquatic-like (e.g. fin) propulsion was discussed, with many variations and examples.

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.

An inflatable endurance unmanned vehicle includes an inflatable hull with at least one inflatable wing extending therefrom. The inflatable wing has at least one spar movable between an extended position and a retracted position. Photovoltaic arrays are used to power the vehicle during daytime operation and power an electrolyzer. A fuel cell powers the vehicle during nighttime operation.

In one aspect, a hybrid airship including an outer shell, a plurality of helium filled gas envelopes, and an all-electric propulsion system can have a high-aspect ratio wing shape. 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 high-aspect ratio wing shape provides low drag, and can allow the hybrid airship to fly at an altitude of at least about 100,000 ft. By continuously recharging the power storage system, the hybrid airship in accordance with some embodiments can stay aloft for months or even years. The hybrid airship may function as a military intelligence, surveillance, and reconnaissance and communications relay platform.

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.

A system is disclosed for lifting a rocket into the upper atmosphere and establishing forward flight at several hundred miles per hour, before the rocket engines are ignited and the rocket is released from the lifting system. The main subassemblies of this lifting system comprise:(1) an array of large helium-filled dirigibles, of a size that can provide hundreds or thousands of tons of lifting force;(2) a tank-holding assembly that will be tethered to the dirigibles, and that will contain pumps and high-pressure tanks, to recapture and store the helium for use in subsequent launches; and,(3) a winged platform, with wings that can be rotated vertically during liftoff, and horizontally to establish forward flight after a desired altitude has been reached, and having conventional aircraft engines on each wing.This system enables safer, less expensive, and more efficient launching of rockets and heavy payloads into space, using easily reusable subassemblies.

A solar-powered aircraft uses solar energy to electrolyze on-board water to produce hydrogen. The hydrogen fills various on-board tanks, causing the aircraft to become lighter than air. The hydrogen is also used to operate a fuel cell which provides power for electrical equipment, including a motor for turning a propeller. Water produced as waste by the fuel cell is recycled for use in the production of hydrogen. When hydrogen is removed from the tanks, either because it is consumed by the fuel cell or because it is compressed and pumped out of the tanks, air returns to the tanks, and the aircraft becomes heavier than air. The aircraft can thus be made to climb and descend by making it lighter than air, or heavier than air. The aircraft emits no harmful substances into the environment. The aircraft can remain aloft indefinitely, limited only by an insignificant amount of leakage of hydrogen and water.

A “wing in ground effect” aerial vehicle includes a wing mounted on a fuselage, and two cycloidal propulsion units for providing lift, thrust and longitudinal control. Additional lift is provided by a lighter-than-air gas such as helium contained in the fuselage. Operationally, the two cycloidal propulsion units and the volume of lighter-than-air gas are concertedly regulated to achieve “wing in ground effect” flight. Importantly, the two cycloidal propulsion units may operate in one of several modes, to include a curtate mode, a prolate mode, and a fixed-wing mode. Additionally, the vehicle may hover. Also, a thruster unit is mounted on the fuselage for providing forward thrust in combination with, or in lieu of, the two cycloidal propulsion units.

A rescue aircraft having a rigid body with gas-filled envelopes and propulsion devices located inside rotatable aerodynamic toroidal modules. A longitudinal through passage in the lower part of the aircraft connects a crew cabin, a cargo-and-passenger compartment, fuel tanks, and accessories. The aircraft has exit hatches, mooring devices, and a gangway with railings and a removable cart. The aircraft also has a cross passage with exits onto its wings and a vertical passage with a pulley and other devices for lowering and lifting people and cargo. The lower part of the aircraft and hollow wings are filled with a foamed plastic for buoyancy and strength.

The invention is an aircraft having an inflatable wing connected to a base unit, with the inflatable wing inflated with a lifting gas such as helium. The inflatable wing has a series of cell structures, and may be configured with ballonets to selectively introduce and expel outside air within the inflatable wing to vary the buoyancy and / or airfoil properties of the inflatable wing. The aircraft is particularly useful at low speeds and in thin atmospheres (such as at high Earth altitudes and on Mars), and can be used for interplanetary missions to explore planetary bodies, such as moons and planets, having atmospheres.