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 |
|---|---|---|---|---|---|---|
| 21 | JPS4886298A - | JP878872 | 1972-01-25 | JPS4886298A | 1973-11-14 | |
| 22 | Balloon flight path control system of | JP2000556957 | 1999-06-25 | JP4505139B2 | 2010-07-21 | アーロン、キム・メイナード |
| 23 | Energy generation, storage and transmission system by photocatalytic reaction in lighter-than-aircraft | JP2009030860 | 2009-02-13 | JP2009190730A | 2009-08-27 | SINSABAUGH STEVEN L |
| PROBLEM TO BE SOLVED: To provide a reaction means for generating energy, a storage means for storing reactants used in the reaction means and a means for distributing the reactants and generated electric power without using pipes, in an energy management system for a lighter-than-aircraft. SOLUTION: The energy management system for the lighter-than-aircraft includes the reaction means 22 for generating energy, the storage means for storing the reactants used in the reaction means 22, and the means for integrally distributing the reactants and electric power without using pipes. COPYRIGHT: (C)2009,JPO&INPIT | ||||||
| 24 | Power and imaging system for airship | JP2008115494 | 2008-04-25 | JP2009033954A | 2009-02-12 | QUINN EDWARD W; HARIHARAN JEANETTE |
| <P>PROBLEM TO BE SOLVED: To provide a method for remotely powering an airship and a system for integrating a power transmission/reception function and a radar imaging function into the airship. <P>SOLUTION: A power transmission and imaging system for the airship comprises a transmission antenna array configured to transmit an energy beam to a patch rectenna carried by the airship. Coupled to the patch rectenna is a power distribution and control network that supplies rectified power delivered by the energy beam into the proper format for delivery to a power storage system and a monitor control system. The power storage system comprises one or more batteries to store the transmitted energy, while the motor control system powers various propellers, blowers, and valves maintained by the airship in order to descend the airship to the ground. The rectenna may also function as an imaging system in real-time. The image processing system uses the patch rectenna to transmit and receive signals, and in turn store and process the return signals (images). <P>COPYRIGHT: (C)2009,JPO&INPIT | ||||||
| 25 | Apparatus and method for receiving the accurate accurately or unload the cargo from the aircraft, or the cargo | JP2000555792 | 1999-06-22 | JP2002518254A | 2002-06-25 | シェーファー インゴルフ; ケンプフ ベルンハルト |
| (57)【要約】 本発明は、航空機の着陸や航空機の正確な三次元的位置決めを不要にすることのできる、航空機から貨物を的確に卸すか、または貨物を的確に受け取るための方法に関する。 アンロードされかつ中間プラットホームとの間に貯えられるべき貨物は、グラウンド上方の所定の高度で航空機から引き下ろすことができる。 この引下ろし過程はケーブルシステムにより実施され、このケーブルシステムは貨物に対する航空機の運動を十分に分離する。 中間プラットホームはグラウンドに対して中間高度で、押圧力を吸収する三次元骨組によって支持される。 その後に、貨物が、三次元的に固定されたこの中間プラットホームによって受け取られるか、または卸されるか、あるいは両方法ステップが同時にまたは連続して実施される。 | ||||||
| 26 | JPH07503918A - | JP50753592 | 1992-01-10 | JPH07503918A | 1995-04-27 | |
| 27 | Aircraft | JP10372586 | 1986-05-06 | JPS6218397A | 1987-01-27 | JIYOOJI NINKOBITSUCHI; JIYON EDOWAADO WARINTON; DEIRU KURIFUOODO KUREIMAA |
| 28 | JPS59501946A - | JP50350783 | 1983-10-21 | JPS59501946A | 1984-11-22 | |
| 29 | JPS4919599A - | JP4264073 | 1973-04-14 | JPS4919599A | 1974-02-21 | |
| An aircraft comprises a plurality of wings. Each of the wings has a leading edge and a trailing edge and upper and lower surfaces defining an airfoil portion which produces a lifting force when the wing is moved through the air. At least a portion of the trailing edge of each wing is configured to define a semicircle. A power-driven rotor is mounted for rotation in the semicircle and has generally radial blades extending into close proximity with the semicircular surface portion of the trailing edge of the wing and arranged to produce a downward air flow at the trailing edge. The radial blades rotate in a plane that intersects the semicircular portion of the wing trailing edge, and increase the velocity of air flow across the upper surface of the airfoil portion and decrease the velocity of air flow across the lower surface of the airfoil portion thereby increasing the lifting capability of the airfoil. The tips of the rotor blades are located so that when they are in proximity to the trailing edge of the wing, the upper portion of each tip is below the upper edge of the semicircular portion of the wing trailing edge and above the lower edge thereof. The axis of rotation of the rotor corresponds approximately with the axis of the semicircle and may be canted relative to the forward direction of aircraft movement to provide a component of forward thrust. The wings are supported in a tandem, horizontally spaced relation so that a rotor located along the trailing edge of one of the wings increases the downward flow of air relative thereto and also increases the downward flow of air relative to the other wing, whereby each rotor associated with each wing augments or magnifies the downward flow of air produced by each other rotor so as to further produce additional lift for the aircraft. In addition, lighter-than-air bouyancy units may be connected to the opposite ends of each of the wings so as to further provide a lifting force on the aircraft. | ||||||
| 30 | 해양환경 관측 시스템 및 무인비행체 및 그 운용방법 | KR1020080005438 | 2008-01-17 | KR1020080014104A | 2008-02-13 | 배헌민; 김용환 |
| An observation system of sea circumstances, an unmanned aerial vehicle, and an operating method thereof are provided to promptly and exactly observe environment change of sea in real time in spite of severe weather by using the unmanned aerial vehicle. An observation system of sea circumstances includes an unmanned aerial vehicle(100), a radio network(110), a control station(120), database(130), a web server(140), and an aerial network(150). The unmanned aerial vehicle flies in an unmanned manner to a specified route and transmits sea observing information and information of the detected flying route in real time. The radio network communicates a control signal and the information through radio connection with the unmanned aerial vehicle by a cellular method. The control station receives and manages the information observed by the unmanned aerial vehicle in real time by being connected to the radio network and remotely controls collection of the flying route and the information in real time. The database records the information observed and measured by the unmanned aerial vehicle by being connected to the control station. The web server supplies the information recorded in the database to Internet in real time by control of the control station. The aerial network supplies a communication path with the control station. | ||||||
| 31 | 무인 해양환경 자동측정 장치 및 그 방법 | KR1020080005437 | 2008-01-17 | KR1020080014103A | 2008-02-13 | 배헌민; 김용환 |
| An unmanned system and a method for automatically measuring environment of sea are provided to analyze and use environment information of sea in real time by measuring and supplying the environment information of sea in a specified sea area regardless of rapid change of oceanic climate in real time. A method for automatically measuring environment of sea using an unmanned measuring ship includes the steps of: plying by searching a plying route to load and setting an automatic mode when a control unit of the unmanned measuring ship checks that an operation order of the automatic mode is inputted from a sea center by (S110,S120); storing various plying information to transmit to the sea center with plying to a specified sea area by controlling a propulsion adjustment unit by the control unit(S140); collecting a seawater sample and measuring information of sea in case of surveying the environment of sea in the specified sea area(S170); and storing the collected seawater sample, measuring information of climate, and returning to a port(S190,S200,S210). | ||||||
| 32 | 水を集めるための方法およびデバイス | JP2018544441 | 2015-11-13 | JP2018536602A | 2018-12-13 | ラーソン, ラルフ |
| 本発明は、雨水を集めるための、ならびに、好適な条件において、折り畳み可能なメンブレンおよび水を移送容器まで送り出すホースを使用することにより、夜間の空気から湿気を凝結させるための、方法およびデバイスに関連する。可動性を得るために、設備の支持壁が膨張可能であり、地面に一時的に接続可能であり、さらに浮いているときにはボートまたは類似物にも一時的に接続可能である。 【選択図】図3 |
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| 33 | 熱キャパシタを使用した航空機センサへの電力供給 | JP2016124217 | 2016-06-23 | JP2017063595A | 2017-03-30 | ヒラー, ネイサン ディー. |
| 【課題】輸送体内の既存の熱キャパシタを使用し、補助システムのために電力供給する発電システムの提供。 【解決手段】主システム51の一部分として存在する熱キャパシタから電力を得る熱電発電装置30を使用して、輸送体内の補助システム54のための電力を提供する。熱電発電装置30は、熱キャパシタの温度と外部の冷たい空気若しくは輸送体の他の外部環境の温度との間に存在するポテンシャルエネルギーを使用して、電力を生み出す。 【選択図】図3 |
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| 34 | Method of detecting the image and power supply in the remote to the power and image system as well as the airship for airship | JP2008115494 | 2008-04-25 | JP4510113B2 | 2010-07-21 | ダブリュ クイン エドワード; ハリハラン ジャネット |
| 35 | Stratosphere airframe of despun platform type | JP2002211534 | 2002-07-19 | JP2004050971A | 2004-02-19 | HOTTA TOSHITSUNE; AKINAGA KAZUHISA |
| PROBLEM TO BE SOLVED: To provide a stratosphere platform arranged in the stratosphere and capable of directing a plurality of directional antennas and a telescope for communication mounted on the stratosphere platform in respective predetermined directions always without controlling attitude of individual directional antenna and the telescope for communication. SOLUTION: This stratosphere platform 10 has an airframe main body 11, a despun platform part 13 attached to the airframe main body 11 through a pedestal 12, and a control means controlling in such a way that the despun platform part 13 faces the same direction always in a horizontal face by detecting an azimuth angle in the horizontal face of the despun platform part 13. COPYRIGHT: (C)2004,JPO | ||||||
| 36 | Balloon flight path control system of | JP2000556957 | 1999-06-25 | JP2002519236A | 2002-07-02 | アーロン、キム・メイナード |
| (57)【要約】 【課題】バルーンの飛翔経路制御システム【解決手段】端部に翼を備える浮揚デバイスが、バルーンの充分下方において曳航紐に吊り下げられ、異なる高度における風の変化を利用する。 翼は、広範囲の角度に向けられる水平方向の浮揚力を発生することができ、この力は、曳航紐によってバルーンに伝達され、バルーンの飛翔経路が変更される。 風のエネルギーを利用するので舵の制御に大きな動力は不要である。 | ||||||
| 37 | Stfam light airplane | JP2000341461 | 2000-11-09 | JP2001206293A | 2001-07-31 | GOODEY THOMAS JOHN |
| PROBLEM TO BE SOLVED: To provide a free flying balloon or a light airplane such as an airship, whose envelope is charged with steam floating gas to provide buoyancy. SOLUTION: This light airplane is equipped with a drain valve 3 and a hose 7 for preventing steam from escaping from the envelope 1 and discharging water condensed to stay inside the envelope 1, and the drain water may be released to the atmospheric air or the airplane may be equipped with a boiler for re-boiling the drain water to become steam and returning the same to the envelope 1. The availability factor of the boiler is variable, and equipped with a water storing tank for temporarily storing water. When the light airplane is an airship, a propulsion means is a steam engine SE supplied with pressurized steam from the boiler and returning the drain steam to the envelope 1. The steam is supplied from the boiler directly to the envelope 1, and the quantity and proportion of steam supplied directly to the envelope 1 and steam supplied to the steam engine SE are variable. COPYRIGHT: (C)2001,JPO | ||||||
| 38 | Aircraft having buoyant gas balloon | JP28515289 | 1989-11-02 | JPH02162196A | 1990-06-21 | FUREDERITSUKU FUAAGUSON |
| PURPOSE: To increase lift and decrease drag as the rotation of a balloon is increased by providing a balloon rotating means generating the Magnus lifting force that the static lifting force of a balloon means is increased by the surface characteristic of the balloon means during the rotation in a forward flight. CONSTITUTION: A balloon is provided with peripheral cables 12a and cables 12b forming a series of squares on the surface of the balloon. When the balloon is inflated by floating gas such as helium, the balloon is slightly inflated between the cables 12a, 12b by the pillow effect, the irregularity of the magnitude improves the Magnus effect and decreases drag. An electric motor fitted to the apex of an arm 32 is rotated, the balloon is rotated around the standard horizontal axis 16, the balloon is advanced by a gas turbine engine 40, and the balloon is moved above the center. The Magnus lift quantity depends on the advancing speed of the balloon, the rotating speed of the balloon, and the irregularities on the surface of the balloon. COPYRIGHT: (C)1990,JPO | ||||||
| 39 | Aircraft with floating gas balloon | JP19194882 | 1982-11-02 | JPS5885795A | 1983-05-23 | FUREDERITSUKU FUAAGUSON |
| 40 | JPS5026297A - | JP3310074 | 1974-03-22 | JPS5026297A | 1975-03-19 | |
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