子分类：
| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 101 | Aircraft having buoyancy gas balloon | EP82305838.3 | 1982-11-03 | EP0078713B1 | 1989-01-18 | Ferguson, Frederick |
| 102 | Conteneur à structure symétrique lobée | EP80401236.7 | 1980-08-28 | EP0025384B1 | 1988-11-17 | Rougeron, Michel; Simon, Jacques |
| 103 | AN AERIAL MACHINE | EP83903393.0 | 1983-10-21 | EP0138817A1 | 1985-05-02 | CRAMP, Leonard, George |
| Une machine plus lourde que l'air comprend un fuselage (10) portant une pluralité de soufflantes à moteur qui fonctionnent pour diriger l'air vers le bas. Deux enveloppes gonfflées (25 et 26) sont fixées au fuselage, leurs centres volumétriques au-dessus du centre de gravité de la machine. La présence des enveloppes gonfflées (25 et 26) confère à la machine une stabilité aérodynamique inhérente lorsqu'elle à recours à l'effet de sol, au décolage et à l'atterrissage verticaux, au vol stationnaire, au vol transitionnel et au vol vers l'avant, et même lors de modes de descentes verticales libres sans moteur. | ||||||
| 104 | Aircraft having buoyancy gas balloon | EP82305838.3 | 1982-11-03 | EP0078713A2 | 1983-05-11 | Ferguson, Frederick |
An airship having a spherical balloon filled with buoyant gas such as helium at a pressure substantially greater than atmospheric and which is mounted for rotation about a normally horizontal axis, the airship including a rigid load supporting yoke having two support arms extending upwardly from a central gondola and each with an upper end rotatably connected to the balloon, is characterized by the gondola and support arms having surfaces close to and conforming to the shape of the balloon so as to inhibit air flow between the gondola and the bottom of the balloon and to redirect this air to the sides and back of the balloon. |
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| 105 | Conteneur à structure symétrique lobée | EP80401236.7 | 1980-08-28 | EP0025384A2 | 1981-03-18 | Rougeron, Michel; Simon, Jacques |
L'invention concerne un conteneur à structure sphéroidale aplatie aux pôles. La structure est formée de fuseaux (1) assemblés selon leurs bords. Des renforts méridiens monodirectionnels (4) sont fixés ponctuellement sur les lignes d'assemblage des fuseaux. Les fuseaux sont en un matériau à faible module élastique et à grande capacité d'allongement plastique et les renforts méridiens en un matériau à haut module élastique. Une surpression à l'intérieur de la structure lui fait prendre la forme d'une sphéroïde aplatie aux pôles. Application aux ballons fermés et aux réservoirs pressurisés. |
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| 106 | Aircraft having buoyant gas balloon | EP80302686.3 | 1980-08-06 | EP0023843A2 | 1981-02-11 | Ferguson, Frederick |
An aircraft is provided utilizing a spherical balloon filled with buoyant gas such as helium at a pressure substantially greater than atmospheric so that its dimensions are substantially unaffected by changes in atmospheric pressure or temperature. The aircraft may take the form of a self-propelled and self-contained airship, or may be merely a passive device for providing lift and intended to be towed by and controlled from a helicopter. The spherical balloon is mounted on a normally horizontal axle having end portions projecting from opposite sides of the balloon, and includes a rigid load supporting yoke including two arms extending upwardly from a central load supporting structure and each with an upper end suspended from the axle. |
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| 107 | 空中楼阁 | CN94211753.0 | 1994-05-07 | CN2196153Y | 1995-05-03 | 卢杲 |
| 本实用新型涉及一种由骨架(1)、气舱(2)、推进系统(3)、生活娱乐设施(4)、花园(5)组成的空中楼阁。楼阁重量由气舱(2)产生的静浮力支承，推进系统(3)控制楼阁的悬浮和移动；生活娱乐设施(4)在楼阁底部，以稳定重心，空中花园(5)在花园区顶部，通过配平水箱(6)的移动来控制楼阁的平衡。空中楼阁用于旅游、娱乐、居住。 | ||||||
| 108 | AIRSHIP INCLUDING AERODYNAMIC, FLOATATION, AND DEPLOYABLE STRUCTURES | PCT/US2012030562 | 2012-03-26 | WO2012135117A2 | 2012-10-04 | GOELET JOHN |
| 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. | ||||||
| 109 | LENTICULAR AIRSHIP AND ASSOCIATED CONTROLS | PCT/US2008009453 | 2008-08-07 | WO2009023114A8 | 2009-05-22 | BALASKOVIC PIERRE |
| A system for controlling yaw associated with an airship may include one or more vertical control surfaces associated with the airship, a first power source and a second power source, each configured to provide a thrust associated with the airship, and a yaw control configured to receive an input indicative of a desired yaw angle. The system may further include a controller communicatively connected to the yaw control, the one or more vertical control surfaces, and the first and second power sources. The controller may be configured to receive an output signal from the yaw control corresponding to the desired yaw angle and to generate a control signal configured to modify a state associated with at least one of the one or more vertical control surfaces, the first power source, and the second power source, such that the airship substantially attains the desired yaw angle. | ||||||
| 110 | LENTICULAR AIRSHIP AND ASSOCIATED CONTROLS | PCT/US2008009453 | 2008-08-07 | WO2009023114A2 | 2009-02-19 | BALASKOVIC PIERRE |
| A system for controlling yaw associated with an airship may include one or more vertical control surfaces associated with the airship, a first power source and a second power source, each configured to provide a thrust associated with the airship, and a yaw control configured to receive an input indicative of a desired yaw angle. The system may further include a controller communicatively connected to the yaw control, the one or more vertical control surfaces, and the first and second power sources. The controller may be configured to receive an output signal from the yaw control corresponding to the desired yaw angle and to generate a control signal configured to modify a state associated with at least one of the one or more vertical control surfaces, the first power source, and the second power source, such that the airship substantially attains the desired yaw angle. | ||||||
| 111 | AIRCRAFT | PCT/DE0102357 | 2001-06-29 | WO0202400A3 | 2004-02-26 | BRODA HANS-JOERG |
| The invention relates to an aircraft which has a hull (1) that is fill with a lifting gas and a passenger holding compartment (5) which traverses said hull (1). The passenger holding compartment (5) is made up of a top holding compartment (6) which protrudes beyond the top of the hull (1) and a bottom holding compartment (7) which protrudes beyond the bottom of the hull (1). Said top and bottom holding compartments (6, 7) are interconnected by a connecting compartment (8) which traverses the hull and are surrounded by an outer shell (6a) or (7b), this outer shell having transparent window areas (6c) or (7c). An outwardly free platform (6e) is provided in front of a door (6d) in the area of the top holding compartment (6). This particular embodiment of the passenger holding compartment (5), comprising a top holding compartment (6), a bottom holding compartment (7), a connecting compartment (8) and a free platform results in advantages for passenger use. | ||||||
| 112 | SYSTEMS AND METHODS FOR ATTITUDE CONTROL OF TETHERED AEROSTATS | PCT/US2012055898 | 2012-09-18 | WO2013043586A3 | 2013-05-16 | VERMILLION CHRISTOPHER R; GLASS BENJAMIN W; GOESSLING ANDREW D |
| A control system for a tethered aerostat is provided, where up to two rotational and at least one translational degree of freedom are controlled to setpoints through the variation of tether lengths by an actuator system. The term tether includes a single tether, a tether group or a sub section of tether controlled by an individual actuator. Accurate rotational and translational control is essential for the successful operation of an aerostat under several applications, including surveillance, weather monitoring, and power generation. For a given use case, the controller can be constructed and arranged to manage the tradeoff between several key performance characteristics, such as transient performance, steady-state pointing accuracy, tether tension regulation, and power generation. | ||||||
| 113 | SUPER -RIGID HYBRID AIRSHIP AND METHOD OF PRODUCING | PCT/IB2011001216 | 2011-06-03 | WO2011154797A3 | 2012-04-12 | KRAUS HANS GEORG |
| The invention relates to a super-rigid hybrid airship having a modular structure, which comprises a central tube (1) having a diameter of between 5 to 10% of the diameter of the airship, structural rings (2) surrounding and preferably concentric with the central tube and connected to the tube by bolts (3), an external cover (4) made from thin metal sheets, interspersed with composite resins and fibbers which is pressurized and prestressed by light gases and which is rigid, conductive, non- combustible and impermeable to gases, balloons (6) filed with hydrogen and disposed in structural sections defined by neighbouring structural rings (2), at least two interconnected cuffs (7) inflated by atmospheric air serving as operational ballast and ensuring weight, pressure and volume balance of the airship, wherein the dimensions and quantity of airship components depend on the size of the airship of such a modular design. The modular structure of the airship allows vertical construction by assembling modularly consecutive airship modules defined by sections of a central tube (1 ) and structural rings (2) substantially vertically along the length of the airship to form the front end part and the back end part of the airship, filing the front end part and the back end part of the airship with light gases to make them float, and connecting the front end part and the back end part of the airship together. Preferably the airship comprises among others a blower system (12) for dispersing air, arranged on the centreline of the top layer so that the air is blasted from centreline to right and left of the airship, as well as wings (18) arranged at each side of the fixed sections (13) and optionally comprising at its ends thrust means (19) such as engines and propellers or turbo-propellers. | ||||||
| 114 | CHANGING A POSITION OF A STRUCTURE (4) | PCT/GB2008002693 | 2008-08-07 | WO2009019487A2 | 2009-02-12 | GOODALL PETER ROBERT |
| A structure where the free rotation of the blade can be slowed or stopped so that the wind or some of it passes through the blade and less or no wind energy is absorbed by the rotation of the blade and therefore makes contact with a structure behind the blade, exerting pressure on this part of the structure and causing anything attached to it to move as in figure 29. | ||||||
| 115 | SPHERICAL LTA CARGO TRANSPORT SYSTEM | PCT/IB0102816 | 2001-11-20 | WO0242149A9 | 2003-05-01 | BEACH GLENN RICHARD; LUFFMAN CHARLES RAYMOND; GOTTLIEB GREGORY CHARLES ROSS |
| A system and mechanism for the movement of large, outsized and heavy cargo includes a tow cable (30) connectable at a first end to a towing vehicle (35) , a buoyant lift vehicle (10) comprising an inflatable member (10), a tether cable (15) linked to the buoyant lift vehicle (10) and having a connection (20) with the tow cable (30), and a payload connector linked to at least one of said payload tether cable (15) and said tow cable (30). The tow cable (30) has a tow vehicle connector at a first end. A connector (20) links the tether cable and the tow cable. | ||||||
| 116 | SPHERICAL LTA CARGO TRANSPORT SYSTEM | PCT/IB0102816 | 2001-11-20 | WO0242149A2 | 2002-05-30 | BEACH GLENN RICHARD; LUFFMAN CHARLES RAYMOND; GOTTLIEB GREGORY CHARLES ROSS |
| A system and mechanism for the movement of large, outsized and heavy cargo includes a tow cable (30) connectable at a first end to a towing vehicle (35) , a buoyant lift vehicle (10) comprising an inflatable member (10), a tether cable (15) linked to the buoyant lift vehicle (10) and having a connection (20) with the tow cable (30), and a payload connector linked to at least one of said payload tether cable (15) and said tow cable (30). The tow cable (30) has a tow vehicle connector at a first end. A connector (20) links the tether cable and the tow cable. | ||||||
| 117 | BALLOON TRAJECTORY CONTROL SYSTEM | PCT/US9914430 | 1999-06-25 | WO0000387A3 | 2001-12-13 | AARON KIM MAYNARD |
| A device to provide control of the trajectory of a lighter than air vehicle, such as a balloon, is provided. A lifting device, such as a wing (1) on end, is suspended on a tether well below the balloon to take advantage of the natural variation in winds at different altitudes. The wing (1) can generate a horizontal lift force that can be directed over a wide range of angles. This force is transmitted to the balloon by the tether (23). Due to this force, the balloon's path is altered depending on the relative sizes of the balloon and the wing (1). A relatively small amount of power is needed to control the system, possibly with a rudder (15). As the energy of the wind provides most of the force, the wind's energy does most of the work. The balloon is able to avoid hazards, to reach desired targets, to select convenient landing zones, and to provide other operational advantages. As a result, fewer flights must be terminated early due to an inability to control the trajectory, and it is easier to obtain permission to launch since a planned flight path can be achieved within a greater range of conditions. | ||||||
| 118 | Anti gravity system | PCT/IN0000066 | 2000-07-12 | WO0109509A3 | 2001-08-23 | NAGARJUNA RAO K |
| An anti gravity system with a hallow metal sphere (7) placed inside a very strong hallow outer metal sphere (1) with a clearance in between the two and the outer sphere having a sump at bottom, the clearance (8) between the spheres filled with mercury or lead, the sump (2) having an electric resistance coil (3) connected to a generating unit (4) via a transformer generates high temperature in the matter in between the spheres and a force is applied on the inner face of the outer sphere by the inner hallow sphere and the system looses its weight depending on the temperature. | ||||||
| 119 | AIRSHIP LAUNCH FROM A CARGO AIRSHIP WITH A PAYLOAD RETURN VEHICLE | US15955007 | 2018-04-17 | US20180237141A1 | 2018-08-23 | Stephen B. Heppe |
| A method for launch of an airship includes connecting a cargo airship to a second airship that is not positively buoyant at the launch site, launching the cargo airship, transferring lifting gas from the cargo airship to the second airship where said lifting gas is carried by the cargo airship while aloft; and releasing the second airship from the cargo airship. A releasable payload return vehicle is also provided, wherein the payload return vehicle generates aerodynamic forces while it is mated to the cargo airship. | ||||||
| 120 | Airborne fulfillment center utilizing unmanned aerial vehicles for item delivery | US15059197 | 2016-03-02 | US10032125B1 | 2018-07-24 | Paul William Berg; Scott Isaacs; Kelsey Lynn Blodgett |
| Described is an airborne fulfillment center (“AFC”) and the use of unmanned aerial vehicles (“UAV”) to deliver items from the AFC to users. For example, the AFC may be an airship that remains at a high altitude (e.g., 45,000 feet) and UAVs with ordered items may be deployed from the AFC to deliver ordered items to user designated delivery locations. As the UAVs descend, they can navigate horizontally toward a user specified delivery location using little to no power, other than to stabilize the UAV and/or guide the direction of descent. Shuttles (smaller airships) may be used to replenish the AFC with inventory, UAVs, supplies, fuel, etc. Likewise, the shuttles may be utilized to transport workers to and from the AFC. | ||||||
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