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公开(公告)号：US10435181B2
公开(公告)日：2019-10-08
申请号：US15383267
申请日：2016-12-19
申请人： EMBRAER S.A.
发明人： Rogério Scafutto Scotton , Natália Vianna Correia , Luiz Fernando Dos Santos , Thomas Waring , Richard Waring
IPC分类号： B64F5/40 , B64C1/14 , B05B15/60 , B05B13/06 , B05D7/22 , B64C1/18 , B64C1/22 , B64C1/34 , B05D1/02 , B05B13/04 , B05B12/32 , B25J5/00 , B25J11/00
摘要： Methods are provided by which a treatment fluid (e.g., a liquid corrosion inhibitor) may be applied onto the interior surfaces of an aircraft fuselage. The methods include (a) deploying an automated guided vehicle (AGV) comprising a carriage assembly and a robotic spray system carried by the carriage assembly within the interior of the fuselage, (b) closing the cabin door opening of the fuselage with the AGV positioned therewithin, and (c) operating the AGV so as to move within the fuselage along a longitudinal axis thereof to spray the treatment fluid onto the surfaces thereof.
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公开(公告)号：US20170008609A1
公开(公告)日：2017-01-12
申请号：US15270922
申请日：2016-09-20
申请人： Kevin Arash Peyman , Nazmi Peyman
发明人： Kevin Arash Peyman , Nazmi Peyman
CPC分类号： B64G1/002 , B64B1/40 , B64B1/62 , B64C1/34 , B64C37/02 , B64G1/005 , B64G1/22 , B64G1/401 , B64G2001/224
摘要： The present invention relates to an aerospace vehicle comprising an airplane or spacecraft, operatively coupled to an airship balloon containing lighter than air gas adapted to elevate the vehicle. A control system adapted to deflate the balloon upon reaching a predetermined altitude by directing the gas for powering the vehicle at greater speed. The balloon can be re-inflated for decreasing the speed of the vehicle upon reaching a destination and deflated in a controlled manner for landing the vehicle or disengaged from the vehicle upon transferring the gas from the balloon to a propulsion system of the vehicle.
摘要翻译： 本发明涉及一种航空航天车辆，其包括飞行器或航天器，其可操作地耦合到包含比适于提升车辆的空气气体更轻的飞艇气球。 一种控制系统，其适于通过引导用于以更高速度为车辆供电的气体达到预定高度而使气囊放气。 气囊可以被重新充气，以便在到达目的地时降低车辆的速度并且以可控的方式放气，以便在将气体从气囊转移到车辆的推进系统时将车辆着陆或脱离车辆。
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公开(公告)号：US09162761B2
公开(公告)日：2015-10-20
申请号：US13925797
申请日：2013-06-24
IPC分类号： B64C31/02 , B64C1/34 , B64C3/30 , B64C31/028
CPC分类号： B64C31/02 , B64C1/34 , B64C3/30 , B64C31/028 , B64D2211/00
摘要： A partially-inflated rigid-structure glider is a portable or collapsible gliding apparatus that a user can transport in a carrying case. The gliding apparatus includes a rigid yet collapsible frame, tension membranes over both on the wings and tail, and inflatable bladder, a pair of drogue brakes, and a left and right steering mechanism. The pair of drogue brakes is located on opposing sides of the gliding apparatus and create drag on its respective side in order to turn the gliding apparatus either left or right. The user can activate either drogue brake with the left and right steering mechanism, which are control lines attached to each drogue brake. The tension membranes are fitted over the frame so that the gliding apparatus has an airfoil shape in order to create lift with the wings and tail while the gliding apparatus is in flight.
摘要翻译： 部分充气的刚性结构滑翔机是用户可以在手提箱中运输的便携式或可折叠的滑翔装置。 滑翔装置包括刚性且可折叠的框架，在翼和尾部上方均设有张力膜，以及可膨胀的气囊，一对锥形制动器以及左右转向机构。 一对锥形制动器位于滑翔装置的相对侧上并且在其相应侧上产生拖动以便使滑翔装置左或右转动。 使用者可以用左右转向机构来启动两个制动器，左右转向机构是连接到每个棘轮式制动器的控制线。 张紧膜安装在框架上，使得滑翔装置具有翼型形状，以便在滑翔装置处于飞行状态时产生具有翼和尾部的升力。
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公开(公告)号：US09067668B2
公开(公告)日：2015-06-30
申请号：US14091969
申请日：2013-11-27
CPC分类号： B64C1/0009 , B64C1/34 , B64C3/46 , B64C39/024 , B64C2201/105 , B64D2211/00 , G01S3/7861 , Y02T50/14
摘要： Methods and apparatus for an adaptable solar airframe are provided herein. In some embodiments, an adaptable solar airframe includes an expandable body having an aerodynamic cross-section that reduces parasitic air drag at any given thickness of the body, further being able to change its shape in flight in response to changes in the relative position of the sun; and a flexible solar PV system attached to the surface of the expandable body.
摘要翻译： 本文提供了适用于太阳能机身的方法和装置。 在一些实施例中，可适应的太阳能机身包括具有空气动力学横截面的可膨胀体，该横截面减小了任何给定厚度的身体的寄生空气阻力，并且还能够响应于相对位置的变化而改变其在飞行中的形状 太阳; 以及附接到可膨胀体表面的柔性太阳能光伏系统。
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公开(公告)号：US20150102159A1
公开(公告)日：2015-04-16
申请号：US14513753
申请日：2014-10-14
申请人： Russ Hegarty
发明人： Russ Hegarty
CPC分类号： B64F5/00 , B64C39/024 , B64C2201/024 , B64C2201/027 , B64C2201/042 , B64C2201/108 , B64F5/10
摘要： Disclosed is an invention related to a waterproof unmanned flying apparatus, which is waterproof or water resistant and can perform in inclement weather conditions. The flying apparatus comprises of a main frame covering the outer structure of the flying apparatus that is constructed out of a single piece or multiple pieces which are fused together or mechanically attached to create a watertight seal. A centralized frame can be configured in numerous layouts to include the size and number of rotor blades. The flying apparatus can be used in various applications such as a training device, an aerial photography, and any other event for which the flying apparatus would be required to fly in or around water. The flying apparatus protects expensive internal electrical components that would normally be destroyed by water and moisture. Furthermore, the flying apparatus can be attached with devices for providing features intended for user's consumption.
摘要翻译： 公开了一种防水无人驾驶装置的发明，其防水或防水，可在恶劣天气条件下进行。 飞行装置包括覆盖飞行装置的外部结构的主框架，其由单件或多个构件组成，其被熔合在一起或机械地附接以形成防水密封。 可以在多个布局中配置集中式框架，以包括转子叶片的尺寸和数量。 飞行装置可以用于各种应用中，例如训练装置，航空摄影以及需要飞行装置在水中或周围飞行的任何其它事件。 飞行装置保护昂贵的内部电气部件，通常会被水和水分破坏。 此外，飞行装置可以附接有用于提供旨在用于消费的特征的装置。
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6.发明授权Mechanism for arming, disarming and activating airplane emergency slide evacuation systems 失效布防，解除和激活飞机紧急滑行疏散系统的机制
公开(公告)号：US5738303A
公开(公告)日：1998-04-14
申请号：US441283
申请日：1995-05-15
申请人： Tomio Hamatani , David Brockmeyer , Katsuya Ikeda , Hisao Kondo
发明人： Tomio Hamatani , David Brockmeyer , Katsuya Ikeda , Hisao Kondo
CPC分类号： B64D25/14 , Y10S244/905
摘要： A mechanism(10) arms, disarms, and activates an airplane emergency evacuation system having a slide with one end connected to a girt bar (16). The mechanism includes floor fittings (18) mountable below and at each edge of the airplane door (14). Each floor fitting includes a base (32) defining a notch (40) for receiving the girt bar and a pawl (42) mounted to the base. The pawl rotates relative to the base from a locked position preventing removal of the girt bar from the notch, and to an unlocked position permitting removal of the girt bar. Support fittings (20) mountable to the door, engages the floor fittings when the door is closed and locked. A first jaw (58) extends downwardly to one side of the notch, and faces generally towards the notch from the support fitting. First and second linkage members (60) and (70) connect to one another and rotatably mount to the support fitting. A second jaw (94) extends from the second linkage member and faces generally towards the first jaw. The mechanism operates to rotate the second jaw towards the first jaw to capture the girt bar therebetween, and to rotate the pawl to the unlocked position to disarm the system and allow normal use of the door. To arm the system, the second jaw is rotated in the opposite direction which releases the girt bar and causes the pawl to securely lock the girt bar to the floor of the airplane.
摘要翻译： 一种机构（10）臂，分离和激活具有滑动件的飞机紧急撤离系统，其一端连接到密封条（16）。 该机构包括安装在飞机门（14）的每个边缘下方和下方的地板配件（18）。 每个地板配件包括限定用于接收衬垫条的凹口（40）的底座（32）和安装到基座的棘爪（42）。 棘爪相对于基座从锁定位置旋转，从而防止将缝线从凹口移除，并且到解锁位置，从而能够移除棉条。 当门关闭并锁定时，可安装到门上的支撑配件（20）与地板配件接合。 第一钳口（58）向下延伸到凹口的一侧，并且大致朝向来自支撑配件的凹口面对。 第一和第二连杆构件（60）和（70）彼此连接并可旋转地安装到支撑配件。 第二钳口（94）从第二连杆构件延伸并且大致面向第一钳口。 该机构用于使第二钳口朝向第一钳口旋转，以在其间捕获间隙棒，并且将棘爪旋转到解锁位置以解除系统并允许门的正常使用。 为了操纵系统，第二钳口沿相反的方向旋转，释放出细条，并使棘爪牢牢地锁定到飞机的地板上。
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公开(公告)号：US5005783A
公开(公告)日：1991-04-09
申请号：US466888
申请日：1990-01-18
申请人： James D. Taylor
发明人： James D. Taylor
CPC分类号： B64C1/34 , B64B1/02 , B64C37/00 , B64B2201/00
摘要： A variable geometry lighter-than-air craft which can change from a buoyant airship to a heavier-than-air craft by changing shape. The craft has a flexible envelope filled with helium or other lifting gas. Releasing or tightening the adjusting lines changes the envelope shape by adjusting the internal dimensions and extending or withdrawing wing expansion sections. The craft's shape can change from an ovoid shape for lighter-than-air flight to a winged shape for heavier-than-air flight. Controlling the craft's speed and trim regulates the aerodynamic lift.
摘要翻译： 一种可变的几何式轻型飞行器，可以通过改变形状从浮力飞艇变成更重的飞机。 该工艺具有填充有氦气或其他提升气体的柔性信封。 释放或拧紧调节线通过调节内部尺寸和延伸或抽出翼展开部来改变包络线形状。 工艺的形状可以从轻于空中飞行的卵形形状转变为空中飞行的有翼形状。 控制工艺的速度和调整调节空气动力升力。
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公开(公告)号：US4261534A
公开(公告)日：1981-04-14
申请号：US951080
申请日：1978-10-13
申请人： Auro Roselli
发明人： Auro Roselli
CPC分类号： B64C3/30 , B64C1/34 , B64C39/00 , B64B2201/00
摘要： An aircraft is constructed of an airfoil shaped inflated involucrum of lightweight gas-impervious plastic film. The airfoil is maneuverable to attain forward self-propulsion upon ascent as well as descent. The gases contained in the involucrum are heated by solar radiation to reduce craft density with the upper surface of the airfoil being translucent and the lower surface of the airfoil interior mirrored for concentration of the radiant energy upon an interior cylindrical black spar. A honeycomb reradiation barrier is provided beneath the translucent surface. In one embodiment a large volume involucrum is changeable in camber to maximize forward propulsion. The craft may be utilized to suspend a large fog broom for the purpose of condensation of water vapor. In a further embodiment a manpowered inflatable craft is formed with a flexible longitudinal medial fold which separates the airfoil into wing segments. Each segment includes a passive trailing zone. When the wing segments are oscillated about the medial fold, the craft is propelled by ciliary thrust.
摘要翻译： 一架飞机是由一个轻型不透气塑料薄膜的翼型充气基座构成的。 机翼可以在上升和下降时获得自主推进。 包含在叶片中的气体被太阳辐射加热以降低机翼密度，翼型件的上表面是半透明的，并且翼型件内部的下表面被镜像以将辐射能集中在内部圆柱形黑色翼梁上。 在半透明表面之下提供蜂窝再辐射屏障。 在一个实施例中，大的体积内壁可以在外倾角变化以最大化向前推进。 为了冷凝水蒸气，该工艺可用于悬挂大型扫帚。 在另一个实施例中，人力充气的可飞行艇形成有将翼型件分成翼段的柔性纵向内侧折叠。 每个段包括一个被动尾随区。 当翼段围绕内侧折叠振荡时，飞行物被睫毛推动推动。
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