241results about "Non-rigid airships" patented technology

The MULTIBODY AIRCRANE performs relative positioning, predictive control, and ballast control to achieve very heavy-lifting tasks on land or sea. Such tasks allow station keeping and precise transfer of very heavy payloads between ships underway. This scalable multibody system features three subcomponents: AIRSHIP, SKYCRANE and LOADFRAME. This semi-autonomous system combines aerodynamic (kinetic) and aerostatic (buoyancy force) lift with efficient power and propulsion. During low-speed flight, the Airship and Skycrane are decoupled but linked via a reelable Tether Control Line. Beneath the Skycrane, centered on its hull, a patented NIST (National Institute of Standards and Technology) RoboCrane (featuring a computer controlled six degrees of freedom (DoF) cabling system,) is attached, to precisely suspend and control a Loadframe, with or without payload. During subsonic forward flight, these Airship and Skycrane are coupled as a single airframe (fuselage and delta wing.)

A wind harnessing system using a plurality of self supporting airfoil kites 50 for production of useful power. The system comprising multiple airfoil kites 50 in tandem attached to a pivotal control housing 32 by control lines 58L and 58R and support lines 60L and 60R. Control lines 58L and 58R can change length with respect to the length of support lines 60L and 60R to control the airfoil kites' 50 angle-of-attack, pitch angle, direction of flight, and flight speed. The length of control lines 58L and 58R are controlled from ground station 30 by a movable pulley system in control housing 32 to adjust the airfoils' direction to follow a specific flight path 140. Control lines 58R and 58L and support lines 60R and 60L are also wound on a power shaft and pulley system in control housing 32. As the airfoil kites are propelled by the wind at very-high speed, the airfoils generate a powerful AXIAL force. The control lines 58L and 58R and support lines 60L and 60R are then reeled-out under this AXIAL tension causing the power shaft and pulley system in control housing 32 to turn a generator to generate electricity. After airfoil kites 50 have finished their reel-out power stroke 140a, the airfoil's pitch angle is made negative so they can be reeled-in by their control and support lines using a minimum of force along path 140b. Once the airfoils have been rewound to the proper distance, the airfoils are again angled for high-speed operation to generate powerful AXIAL force and reeled-out along 140c to provide another power stroke. The airfoil kites are then reeled-in again along path 140d and the entire process repeats starting with power stroke 140a. Since the force to rewind the airfoils is much less than the force generated during reel-out, there is net power generated.

Various embodiments of the invention relate generally to systems for providing active vertical control of an airship. More particularly, at least one embodiment of the invention relates to a system for actively controlling the aerostatic lift of an airship by manipulating the ratio of air to lifting gas contained within the airship, and thus the overall mass of the airship. This manipulation is accomplished by actively compressing and / or decompressing the lifting gas or internal air, with the resulting pressure differential borne primarily by the hull and / or an internal pressure tank depending upon the configuration.

An aerostat assembly, specifically an aerostat assembly including one or more cameras for aerial photography and surveillance. The aerostat assembly includes a frame assembly having a pivot assembly joined to a balloon tether line. Thrusters on the frame allow an operator to maneuver the assembly to desired positions as well as rotate the frame assembly about the pivot assembly.

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.

A structural panel component, such as an aircraft fuselage shell component, includes a single integral part having longitudinal and crosswise stiffening elements integrally arranged on a skin sheet. This integral component has been formed by a high speed milling chip removal process applied to a solid plate-shaped semi-finished starting material. The skin sheet has areas of differing thicknesses, and the height, thickness, and spacing of the stiffening elements varies as needed, depending on the local loading conditions that will prevail on the finished structural component. The configuration of the component can be optimized to minimize the weight while satisfying all load strength requirements. The manufacturing method is very simple and economical.

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.

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 solar-powered airship with a hull configured to contain a gas and at least one propulsion assembly with a propulsion device and electric motors configured to drive the propulsion device. The airship may also include a power supply system including solar panels operatively coupled to the electric motors and configured to supply power to the electric motors. The power supply system may also include batteries operatively coupled to the solar panels and configured to receive and store electrical energy supplied by the solar panels, the batteries being further operatively coupled to the electric motors and configured to supply power to the electric motors. The batteries may each be located within an outer envelope of the airship defined by the hull of the airship in a position selected to provide ballast. The solar-powered airship may also include a cargo system configured to contain passengers or freight.

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.

This invention performs relative positioning, predictive control, and ballast control to achieve very heavy-lifting tasks on land or sea. Such tasks allow station keeping and precise transfer of very heavy payloads between ships underway. This scalable multibody system features three subcomponents: Airship, Skycrane and Loadframe. This semi-autonomous system combines aerodynamic (kinetic) and aerostatic (buoyancy force) lift with efficient power and propulsion. During low-speed flight, the Airship and Skycrane are decoupled but linked via a reelable Tether Control Line. Beneath the Skycrane, centered on its hull, a patented NIST (National Institute of Standards and Technology) RoboCrane, featuring a computer controlled six degrees of freedom (DoF) cabling system, is attached, to precisely suspend and control a Loadframe, with or without payload. During subsonic forward flight, these Airship and Skycrane are coupled as a single airframe: fuselage and delta wing.

Multi-Mission Frameless Airship Platform (MFAP) leverages composite material science to achieve a frameless lightweight airframe design enabling increased speed, lift and cargo capacity. Deployable / retrievable high-value modules provide enhanced operational and mission flexibility. Unified power electronics enable hybrid integration of propulsion, power generation (e.g. diesel generator, photovoltaic solar, etc.), energy storage and tethered wind-power generation for both on-grid and off-grid electrical power delivery for airborne operations and ground operations. Onboard antenna systems serve as cell phone towers.

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. The airship can have a pusher propeller that assists in driving the airship and also moves the point of flow separation of the spherical airship further aft. In one embodiment the airship can be refuelled at altitude to permit extended loitering.

An apparatus and method to control the attitude, heading course, altitude and position of a lighter-than-air airship. In one aspect, a hybrid airship including a lighter-than-air gas filled envelope, a thrust vectored front propulsion system, a back rotary wing system and a onboard control system. In one aspect, at least one system to modify the on board mass, a system to control the internal pressure, at least a power battery pack and a radio link communications for unmanned piloting. Said hybrid airship has improved maneuverability, safely flights and is capable to fly as Lighter-than-air airship and Heavy-than-air aircraft.

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.

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.

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.

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.

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.

A hybrid air vehicle having a gas-filled contoured flattened hull including a pair of longitudinally extending side lobes defining, on the underside of the hull, a longitudinally extending central recess, a payload module received in the central recess and air cushion landing gear units on the underside of the side lobes of the hull. The landing gear units are spaced apart on either side of the payload module. The hybrid air vehicle has characteristics of an airplane, a lighter-than-air airship and a hovercraft.

Unmanned aircraft for telecommunicative or other scientific purposes, which is stationed at a determined height, in particular in the stratosphere. The aircraft includes a gas-filled balloon carrying a platform and equipment that maintains the platform in a position relative to the ground. The balloon carrying the platform is disposed in the interior of an external balloon of aerodynamical shape, particularly in the stratosphere. At least one low or high pressure insulation chamber filled with a medium is arranged between them and encircles the inner balloon. The medium used in the insulation chamber is a gas having a low thermal conductivity. The negative effects of the temperature differences are largely compensated so that the inner balloon can be produced from a lighter and cheaper material, thereby increasing durably its longevity.

A hovering surveillance device. An electronic imaging device is disposed on a housing having a primary lift element, at least one compressed lighter-than-air gas element, a pitch adjustment element, and, a steering element. The compressed lighter-than-air gas is channeled to the primary lift element and the pitch adjustment element to selectively vary the altitude and angle for the housing such that scene of interest may be imaged. The lighter-than-air gas may be selected from the group of helium, hydrogen, heated air, neon, ammonia, and methane.

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. The airship can have a pusher propeller that assists in driving the airship and also moves the point of flow separation of the spherical airship further aft. In one embodiment the airship can be refuelled at altitude to permit extended loitering.