| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 1 | 飞行器运行系统 | CN201480033716.X | 2014-06-03 | CN105283382A | 2016-01-27 | 章秀宁 |
| 本发明涉及运行处于从地面升起并漂浮在空中的状态的飞行器的系统，本发明的飞行器运行系统包括：飞行器，内部充满气体，从而漂浮在空中；场地单元，设置于地面；金属线单元，用于在上述飞行器和上述场地单元之间进行连接；以及浮力产生单元，设于上述飞行器的一侧，向飞行器传递通过浮力产生单元与空气的摩擦来获得的浮力。如上所述的本发明具有如下优点，即，可借助与飞行器相连接的浮力产生单元产生利用风的额外的浮力，因此，在高空环境下也可通过向飞行器供给充分的浮力来稳定地运行飞行器，并且，通过金属线单元来向地面传递利用风力发电单元所产生的电力，从而上述飞行器可被用作风力发电设备。 | ||||||
| 2 | 氢气再生太阳能动力的飞行器 | CN201380058156.9 | 2013-09-19 | CN104768847A | 2015-07-08 | 塞巴斯蒂安·福尼尔; 杰伊·戈德塞尔 |
| 一种飞行器，包括：容纳氢气的壳层，用于从所述壳层收集水的水收集系统，将使用所述水收集系统收集的水转换成氢气的电解器，以及使用通过所述电解器所产生的氢气再添满所述的壳层的氢气补给系统电解器。在一个实施例中，所产生的氢气也供应给一个用于飞行器推进器的氢燃料推进系统飞行器。 | ||||||
| 3 | 飛行体運用システム | JP2016521186 | 2014-06-03 | JP2016537233A | 2016-12-01 | スヨン チャン |
| 本発明は地上から浮揚された状態の飛行体を運用するためのシステムに関するもので、本発明は内部に気体が満たされて空中に泊まる飛行体と、地上に設置されるグラウンドユニットと、前記飛行体と前記グラウンドユニットとの間を連結するワイヤユニットと、前記飛行体の一側に備えられ、空気との摩擦で浮力を得てこれを飛行体に伝達する浮力発生ユニットとを含んで構成される。このような本発明では、飛行体に連結される浮力発生ユニットにより風を利用した追加的な浮力がさらに発生されるので、高高度の環境でも飛行体に十分な浮力を供給して安定的な飛行体の運用が可能になり、風力発電ユニットを利用して発生された電力をワイヤユニットを通じて地上に伝達することで風力発電設備として活用することができるという長所がある。【選択図】図2a | ||||||
| 4 | JPS4886297A - | JP878972 | 1972-01-25 | JPS4886297A | 1973-11-14 | |
| 5 | Flight system | JP2010260619 | 2010-11-22 | JP2012111298A | 2012-06-14 | MURAKAMI HIDEYO |
| PROBLEM TO BE SOLVED: To provide a flight system which properly responds to changes of wind directions and stably travels despite no wind, headwind or following wind.SOLUTION: The flight system 1 includes a body 3 with an air sac 7 and can stably travel despite wind directions by changing air resistance of a forward air resistance changing unit 9 which lies anterior in a traveling direction and controlled by a control system 5 to change air resistance and a backward air resistance changing unit 11 which lies posterior and controlled to change air resistance. The flight system 1 further includes a wing 13 which is vertically (perpendicularly) installed, and obtains a driving force by vertical wind generated by changes of altitude using the air sac 7 without using mobile power from a gasoline engine or the like. Further, the flight system can select the route toward the destination based on the prediction of changes of winds by a prediction system 6. | ||||||
| 6 | Flight equipment | JP2010260619 | 2010-11-22 | JP4732546B1 | 2011-07-27 | 英世 村上 |
| 【課題】 本願発明は、風が無かろうと、向かい風であろうと、追い風であろうと、風向きの変化にも適切に対処し、安定した航行が可能な飛行装置を提供する。
【解決手段】 飛行装置１は、気嚢７を含む本体部分３を備え、進行方向の前方に位置して制御装置５の制御により空気抵抗が変更される前方空気抵抗変更部９と、後方に位置して空気抵抗が変更される後方空気抵抗変更部１１の空気抵抗を変更することにより、風向によらず安定した航行が可能になる。 さらに、飛行装置１は、上下方向（垂直方向）に設置された翼１３を備え、気嚢７による高度の変更等によって生じた上下方向の風によって、ガソリンエンジン等の機動力を用いずに推進力を得ることができる。 さらに、予測装置６により、風の変化を予測しつつ目的地への経路を知ることができる。 【選択図】 図１ |
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| 7 | JPS4886298A - | JP878872 | 1972-01-25 | JPS4886298A | 1973-11-14 | |
| 8 | 위치제어 기능을 구비한 비행체 운용시스템 | KR1020130090389 | 2013-07-30 | KR101388491B1 | 2014-04-24 | 장수영 |
| The present invention relates to a system for operating a flying object in a state of floating above the ground. The present invention includes the flying object that floats in the air; a ground unit that is disposed on the ground; and a wire unit that connects the ground unit to the flying object with one end fixed to the ground unit and the other end fixed to the flying object. The flying object has a horizontal wing and a vertical wing that are provided to be rotatable relative to the flying object so as to adjust the direction of drag against wind; and a control unit that detects the position of the flying object to control the pivoting of the horizontal wing and the vertical wing according to the detected position. According to the present invention, self-position control is possible, and thus the flying object can be fixed to a mission area with stability using a single wire, which ensures stability in carrying out a mission by the flying object. | ||||||
| 9 | AUTONOMOUS INTELLIGENCE SURVEILLANCE RECONNAISSANCE AND PAYLOAD DELIVERY SYSTEM AND METHOD OF USING SAME | EP12866919 | 2012-08-06 | EP2739527A4 | 2015-06-10 | STIGLER MICHAEL J; SETAR NICHOLAS JAMES |
| An intelligence, surveillance, and reconnaissance system and associated operating method is disclosed including a ground station and one or more autonomous aerial vehicles. Each automomous vehicle is adapted to a) self-monitor a plurality of environment data; b) calculate, based at least in part upon the environment data, a soft wall radius from which it can return to the command and control interface station; c) receive a destination position to which it is commanded to fly; d) determine if the destination position is beyond the soft wall radius; and e) communicate an alert to the command and control interface station if the destination position is beyond the soft wall radius. | ||||||
| 10 | AIRSHIP INCLUDING AERODYNAMIC STRUCTURES | EP12712835.3 | 2012-03-26 | EP2691295B1 | 2015-02-18 | 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. | ||||||
| 11 | LENTICULAR AIRSHIP | EP07873810.1 | 2007-10-15 | EP2076429B1 | 2013-05-15 | BALASKOVIC, Pierre |
| 12 | LENTICULAR AIRSHIP | EP07873810.1 | 2007-10-15 | EP2076429A2 | 2009-07-08 | BALASKOVIC, Pierre |
| An airship (10) may include a hull (22) substantially shaped as an oblate spheroid, one or more frame members (120, 122, 124) defining a support structure (20), wherein the support structure forms at least a partial support for the hull, at least one horizontal stabilizing member (315) operably coupled to a lower surface of the airship, and at least one horizontal stabilizing member (315) having a first end and a second end. The at least one horizontal stabilizing member (315) may define an anhedral configuration. The airship may also include a vertical stabilizing member (310) 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 (310) 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. | ||||||
| 13 | HYBRID-STARRLUFTSCHIFFE VON FILIMONOV | EP96935628.6 | 1996-10-07 | EP0861773B1 | 2000-03-22 | Filimonov, Alexandr Iosifovich |
| The hybrid dirigible craft belongs to the category of flying vehicles which use an air cushion and take off and land at any type of airfield. The aim of the invention is to design an improved dirigible craft capable of taking off from and landing on water and low-load bearing surfaces. To that end the hybrid dirigible craft comprises the following elements: a discoid body (1) with a central passage (2) in which is mounted a flow-permitting body (5) with a rotor (6) on its upper part and secured to the walls by radial partitions (7) which have an aerodynamic profile; the pilot-passenger and cargo compartments (9 and 10 respectively); a propulsion unit with propellers (8), units for landing on an air cushion in the form of an inflatable toroidal bag (11) and wheel-skid supports (12, 13) mounted on the lower surfaces; rotating flaps (3) mounted at the inlet into the central passage (2); control and stabilising elements (4) mounted at the outlet of the central passage (2); outer wing units (14) and a tail assembly with stabiliser (19) and two or more fins (17) mounted on the rear part of the hull; airflow flaps (21) on the rear flaps of the outer wing elements and hull (22); and airflow control surfaces (20) on the stabiliser and outer wing elements. The dirigible craft also has elevons (22) on the stabiliser and a flexible guard element (23) mounted on and underneath the forward part of the toroidal bag (11). It also has gear for taking off from water in the form of gliding surfaces (28) underneath the compartment (9). | ||||||
| 14 | HYBRID-STARRLUFTSCHIFFE VON FILIMONOV | EP96935628.6 | 1996-10-07 | EP0861773A1 | 1998-09-02 | Filimonov, Alexandr Iosifovich |
Ein hybrides lenkbares Luftschiff gehört zu den Luftkissen-Luftfahrzeugen, die auf Flugplätzen beliebiger Art starten und landen. Aufgabe der Erfindung ist die Entwicklung eines lenkbaren Luftschiffs mit verbesserten Eigenschaften, die ein Starten und Landen auf dem Wasser und auf schwachtragenden Flächen ermöglichen. Zur Lösung dieser Aufgabe enthält das hybride lenkbare Luftschiff einen diskusförmigen Rumpf (1) mit einem zentralen Tunnel (2), innerhalb dessen ein leicht zu umströmender, mit den Wänden mittels radialer Zwischenwände (7) aerodynamischen Profils befestigter Körper (5) mit einem Rotor (6) an seinem oberen Teil angeordnet ist, Pilot-Passagier- (9) und Frachtkabinen (10), eine Antriebsanlage mit Schub-Propellern (8), Luftkissen-Landeeinrichtungen in Form eines aufblasbaren torusartigen Ballons (11) und von Rad-Kufe-Stützen (11, 12), die an den unteren Flächen angebracht sind, drehbare Klappen (3), die am Eingang in den zentralen Tunnel (2) angeordnet sind, Steuer- und Stabilisierungsorgane (4), die am Ausgang aus dem zentralen Tunnel angeordnet sind, Flügeltragwerke (14) und ein Heckleitwerk mit einem Stabilisator (19) und zwei oder mehreren Leitflächen (17), die am hinteren Teil des Rumpfes angeordnet sind, Strahlklappen (21), die an den hinteren Kanten der Flügeltragwerke und des Rumpfs (22) angeordnet sind, Strahlruder (20), die am Stabilisator und an den Flügeltragwerken angeordnet sind. Das hybride lenkbare Luftschiff ist auch mit am Stabilisator angeordneten Höhenquerrudern (22) und einer flexiblen, unten am vorderen Teil des torusartigen Ballons (11) angeordneten Schutzumrandung (23) versehen; außerdem ist es zusätzlich mit Organen zum Starten vom Wasser aus in Form einer Gleitfläche (28) unter der Kabine (9) versehen. |
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| 15 | Aerial vehicle and method of flight | US14324306 | 2014-07-07 | US09694894B2 | 2017-07-04 | Nicholas James Deakin |
| An aerial vehicle comprises an elongate envelope within which are at least one first compartment for holding a lighter than air gas and at least one second compartment for holding atmospheric air and said at least one second compartment having an inlet and an outlet and at least one pair of wings extending laterally from the envelope; said wings being planar units with a leading and trailing edge, the width of the wings from their leading edges to their trailing edges being substantially less than the length of the envelope with airfoil portions fitted between the leading and trailing edges of the wing: the top and bottom of the wings are mirror images of one another; in which forward motion of the vehicle is obtainable without trust through alternate diving and climbing motion. | ||||||
| 16 | Hydrogen-regenerating solar-powered aircraft | US14428906 | 2013-09-19 | US09527569B2 | 2016-12-27 | Sebastien Fournier; Jay Godsall |
| An aircraft comprising a hydrogen-containing envelope, a water-collection system for collecting water from the envelope, an electrolyzer to convert the water collected using the water-collection system into hydrogen, and a hydrogen-replenishment system for replenishing the envelope with hydrogen generated using the electrolyzer. In one embodiment, generated hydrogen is also supplied to a hydrogen-fuelled propulsion system for propulsion of the aircraft. | ||||||
| 17 | Airship with internal propulsion system | US13767844 | 2013-02-14 | US09296460B2 | 2016-03-29 | Phillip R. Barber |
| An airship is presented having a plurality of resilient gas bags and gas containers, a straight fuselage tubular hull, with an inner air passageway and propulsion system located therein, and, connecting air inlet, and outlet funnels fore, and aft, with air deflector cones axially positioned therein. The ship also contains propulsion, reverse, and directional rocket thrusters, in addition to typical airship components. | ||||||
| 18 | AERIAL VEHICLE AND METHOD OF FLIGHT | US14324306 | 2014-07-07 | US20140339356A1 | 2014-11-20 | Nicholas James DEAKIN |
| An aerial vehicle comprises an elongate envelope within which are at least one first compartment for holding a lighter than air gas and at least one second compartment for holding atmospheric air and said at least one second compartment having an inlet and an outlet and at least one pair of wings extending laterally from the envelope; said wings being planar units with a leading and trailing edge, the width of the wings from their leading edges to their trailing edges being substantially less than the length of the envelope with airfoil portions fitted between the leading and trailing edges of the wing: the top and bottom of the wings are mirror images of one another; in which forward motion of the vehicle is obtainable without trust through alternate diving and climbing motion. | ||||||
| 19 | Airship Including Aerodynamic, Floatation, and Deployable Structures | US14058410 | 2013-10-21 | US20140231580A1 | 2014-08-21 | 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. | ||||||
| 20 | Airship | US13907320 | 2013-05-31 | US20140224938A1 | 2014-08-14 | Philip Richard Barber |
| An improved airship having a plurality of resilient gasbags & gas containers, a straight fuselage tubular hull with an inner air passageway & propulsion means located therein, connecting air inlet & outlet funnels fore & aft, with air deflector cones axially positioned therein, and a plurality of bifurcated winged air control surfaces axially affixed vertically & horizontally across the air inlet & outlet funnels fore & aft; further, a plurality of vectored air passageways & mechanisms, and propulsion, reverse, & directional rocket thrusters, positioned fore & aft, top, bottom, port & starboard; thereby providing improved speed, maneuverability, efficiency, adverse weather capability, reduced forward air resistance, & rearward drag; furthermore space, outer & inner atmosphere ingress & egress. | ||||||
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