| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 61 | Bi-convex airship | US12131671 | 2008-06-02 | US08905353B2 | 2014-12-09 | Blaine Knight Rawdon; Christopher K. Droney; John Charles Vassberg |
| An airship comprises a shell having a bi-convex shape, wherein the shell encompasses a volume, and a gas storage system located within the volume. | ||||||
| 62 | UNMANNED AERIAL VEHICLE ANGULAR REORIENTATION | US14016602 | 2013-09-03 | US20140172200A1 | 2014-06-19 | Carlos Miralles |
| A system comprising an unmanned aerial vehicle (UAV) having wing elements and tail elements configured to roll to angularly orient the UAV by rolling so as to align a longitudinal plane of the UAV, in its late terminal phase, with a target. A method of UAV body re-orientation comprising: (a) determining by a processor a boresight angle error correction value bases on distance between a target point and a boresight point of a body-fixed frame; and (b) effecting a UAV maneuver comprising an angular role rate component translating the target point to a re-oriented target point in the body-fixed frame, to maintain the offset angle via the offset angle correction value. | ||||||
| 63 | AIRSHIP, ANCHORING DEVICE, AND LANDING AND MOORING METHOD | US14233293 | 2012-07-19 | US20140158819A1 | 2014-06-12 | Philippe Tixier |
| An air vehicle such as an airship is provided, having a rounded top portion, and the bottom portion of which has a substantially planar shape, including a region having a smaller inclination, which is referred to as a bottom surface, and the surface area of which is larger than that of an intermediate region having a greater inclination, referred to as an intermediate surface. The general shape produces, due to relative wind, a resulting overall downward force near the ground. The vehicle also includes a device for anchoring same to the ground, the anchoring device being stationary or controllable from the vehicle, located at the front portion of the vehicle, and projecting downward, in particular a ram including a portion which can be expanded by applying a bar against a translatably movable shoulder. Also included is a landing method implementing such a vehicle. | ||||||
| 64 | AIR VEHICLE | US13944141 | 2013-07-17 | US20140021298A1 | 2014-01-23 | Michael DURHAM |
| An air vehicle has a gas-filled hull (1) of flexible sheet material. Strakes (7) extend along an exterior of the hull, each strake comprising a gas-filled tube (10) of flexible sheet material. A rigid board (12) may project outwardly from the gas-filled tube (10) and away from the vehicle. A further layer of flexible sheet material (13) may extend from one side of the strake (7) over the board (12) to another side of the strake, to provide a strake (7) generally triangular in cross section. | ||||||
| 65 | Airship including aerodynamic, floatation, and deployable structures | US13430010 | 2012-03-26 | US08596571B2 | 2013-12-03 | John Goelet |
| An airship is provided. The airship includes a hull configured to contain a gas, at least one propulsion assembly coupled to the hull and including a propulsion device, and at least one aerodynamic component including a plurality of fairing structures including one or more slats, wherein the at least one aerodynamic component is associated with the hull and is configured to direct airflow around the airship. | ||||||
| 66 | Aircraft configured for vertically ascending and landing | US12530336 | 2008-03-10 | US08474746B2 | 2013-07-02 | Aalbert Adrianus van Helden |
| An aircraft which is configured for vertically ascending and landing, includes at least two wings (2a, 2b, 4a, 51, 4b, 52), a space (2c, 4c) for the generating during operation of climbing power, and an intermediate portion (3), the intermediate portion (3) being provided with thrust motors (6), and the space (2c, 4c) for the generating during operation of climbing power being provided with a quantity of lifting power units (HV). Each lifting power unit includes a first variable volume (V1) for the storage of an amount of relatively light gas which is lighter than atmospheric air, and is configured for the controllable adjustment of an upward force or lifting power by the variable volume taken up by the amount of relatively light gas. | ||||||
| 67 | Positive-pressure flying aircraft | US12677917 | 2008-08-12 | US08464977B2 | 2013-06-18 | Masahiko Suzuki |
| A positive-pressure floating type airplane comprising an airfoil portion, left-right fuselages, a central fuselage, an elevator and a rudder disposed at the back of the airfoil portion, a thruster disposed at the back of the central fuselage, and a horizontal stabilizer disposed at the rear ends of the left-right fuselages. The individual front ends of the airfoil portion, the left-right fuselages and the central fuselage are formed into arcuate shapes in longitudinal sections. On the lower side of the airfoil portion, a recessed air capture is formed from the front end to the rear end. As a result, the positive-pressure floating type airplane is floated by the reaction from the air at the time when the air to pass the air capture through the airfoil portion is pushed by the thrust of the thruster, and is propelled forward by the component of that thrust. | ||||||
| 68 | HYBRID LIFT AIR VEHICLE | US12999309 | 2009-05-21 | US20120273608A1 | 2012-11-01 | Peter E. Jess; Ken Laubsch |
| A hybrid lift air vehicle for carrying and transporting a load, comprising an envelope having a generally ellipsoidal shape adapted to receive a volume of lighter-than-air gas, at least two variable thrust vertical thrusters in secure engagement with the envelope and at least two variable thrust lateral thrusters in secure engagement with the envelope, means for temporarily securely engaging the load to the envelope wherein the volume of lighter-than-air gas has a buoyancy that offsets at least 25% of the weight of the air vehicle when unloaded, wherein the thrust from the at least two vertical thrusters may be varied to raise and lower the air vehicle and the load when engaged, and wherein the thrust from the at least two lateral thrusters may be varied to maneuver and transport the raised air vehicle and the load when engaged. | ||||||
| 69 | Airship Including Aerodynamic, Floatation, and Deployable Structures | US13430010 | 2012-03-26 | US20120248241A1 | 2012-10-04 | John Goelet |
| An airship is provided. The airship includes a hull configured to contain a gas, at least one propulsion assembly coupled to the hull and including a propulsion device, and at least one aerodynamic component including a plurality of fairing structures including one or more slats, wherein the at least one aerodynamic component is associated with the hull and is configured to direct airflow around the airship. | ||||||
| 70 | Collapsible space shuttle | US11919914 | 2006-11-27 | US20120119035A1 | 2012-05-17 | Issam Sharif |
| The invention relates to an airship which can be unfolded and folded up automatically on the ground and during flight and which can be operated as an aircraft or as a reusable space shuttle, having a combined collapsible gas cell (400), a grid network (600) which provides the shape, an aircraft body (200) comprising a cockpit (210), a cargo bay (220), a machine bay (230) and collapsible wheels (240), components for aircraft navigation control (300), two rocket motors (500L, 500R) which can be rotated, a collapsible control surface (700) and a mechanism for operation of the collapsible control surface (100). The combined collapsible gas cell (400) comprises an envelope (402) which can be folded and a housing (401) which cannot be folded. The housing (401) which cannot be folded is mounted on the inner walls and the bottom of the cargo bay (220). The gas cell (400) is filled with helium or hydrogen in the unfolded state, and is completely empty in the collapsed state. The envelope (402) which can be folded is held by the grid network (600) which provides the shape when in the unfolded state, and is located in the internal area of the housing (401), which cannot be folded, in the collapsed state. | ||||||
| 71 | System and methods for buoyancy management in an airship | US12404241 | 2009-03-13 | US08167240B2 | 2012-05-01 | Douglas H. Greiner |
| An airship comprising a hull configured to be inflated with a first gas; a ballonet in the hull, the ballonet configured to be inflated with a second gas that is heavier than the first gas; a fan configured to draw the second gas into the ballonet; an inflatable landing system; a duct configured in the ballonet to allow access to components in the airship; and a valve coupled to the ballonet. The valve provides a pathway for air to flow between the ballonet and a plenum chamber, the plenum chamber is formed by the airship, a landing surface, and the inflatable landing system when the inflatable landing system is in contact with the landing surface. | ||||||
| 72 | High-security aircraft | US11922506 | 2005-07-07 | US08113459B2 | 2012-02-14 | Alfredo Capuani |
| An aircraft comprising an elongated framework provided with propelling means and direction-control planes. The framework is coupled to a pneumatic chamber suited to be filled with lighter-than-air gas and comprising two tubular branches joined to form a V-shaped profile, with an aerodinamic-lift surface extending therebetween. | ||||||
| 73 | Inflatable wing flight vehicle | US12157600 | 2008-06-11 | US08104718B2 | 2012-01-31 | Donald Orval Shaw |
| 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. | ||||||
| 74 | Lenticular airship | US11907883 | 2007-10-18 | US07866601B2 | 2011-01-11 | Pierre Balaskovic |
| 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. | ||||||
| 75 | Envelope For Lighter-Than-Air Aircraft | US12182827 | 2008-07-30 | US20100025534A1 | 2010-02-04 | Adam N. Chu |
| An envelope is disclosed for holding gas in a lighter-than-air aircraft. The envelope includes a shell having a leading edge, a trailing edge, an upper surface and a lower surface. The upper surface and the lower surface each extend between the leading edge and the trailing edge. The shell has an airfoil-shaped cross-section having a reflex camber quality. | ||||||
| 76 | BI-CONVEX AIRSHIP | US12131671 | 2008-06-02 | US20090314880A1 | 2009-12-24 | Blaine Knight Rawdon; Christopher K. Droney; John Charles Vassberg |
| An airship comprises a shell having a bi-convex shape, wherein the shell encompasses a volume, and a gas storage system located within the volume. | ||||||
| 77 | Inflatable wing flight vehicle | US12157600 | 2008-06-11 | US20090108135A1 | 2009-04-30 | Donald Orval Shaw |
| 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. | ||||||
| 78 | SOLAR-POWERED AIRCRAFT | US11774732 | 2007-07-09 | US20080185475A1 | 2008-08-07 | Howard J. Fuller |
| 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. | ||||||
| 79 | Lighter-than-air gas handling system and method | US11501608 | 2006-08-08 | US20080035787A1 | 2008-02-14 | Mark N. Thompson |
| A lighter-than-air gas handling method and system for an airship capable of operating at a plurality of altitudes each characterized by a plurality of environmental conditions comprises a structure including a first envelope and a flexible volume portion in fluid communication with the first envelope. The first envelope capable of containing a volume of lighter-than-air gas disposed within the first envelope at a pressure in substantial equilibrium with an ambient pressure external to the first envelope when the airship is operating at a first altitude of the plurality of altitudes. A lighter-than-air gas transfer mechanism is coupled with the first envelope and the flexible volume portion and operative to allow the lighter-than-air gas to flow into the flexible volume portion as the lighter-than-air gas expands when the airship ascends to a second altitude higher than the first altitude and before the expanded lighter-than-air gas exceeds the containment capability of the first envelope. The flexible volume portion is operative to expand to accommodate the lighter-than-air gas flowing thereto from the first envelope wherein expansion of the flexible volume portion does not substantially affect the capability of the airship to operate in the plurality of environmental conditions of the second altitude. The lighter-than-air gas is transferred from the flexible volume portion into the first envelope as the airship descends from the second altitude to a third altitude lower than the second altitude. | ||||||
| 80 | Unmanned Urban Aerial Vehicle | US11307461 | 2006-02-08 | US20060284002A1 | 2006-12-21 | Kurt Stephens; David Burns |
| The proposed UUAV provides a small, agile vehicle that leverages the unique principals of remote controlled model aviation. The UUAV also encompasses an aerodynamically shaped, gas filled wing that can be used to provide buoyancy for lift assistance both through the use of the lighter than air gas and by its aerodynamic shape in forward flight. | ||||||
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