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公开(公告)号：US20170320559A1
公开(公告)日：2017-11-09
申请号：US15528109
申请日：2015-11-19
发明人： Amir GAT , Shai ELBAZ , Yoav MATIA
CPC分类号： B64C3/185 , B29L2031/3085 , B64C1/34 , B64C3/38
摘要： A pressurized, fluid-filled channel network embedded in an elastic structure, asymmetrically to the neutral plane, is used to create a deformation field within the structure by the pressurization of the embedded fluidic network, which can be applied in accordance with external forces acting on the structure. The deformation of the structure resulting from the liquid pressure and geometry of the network is related to a continuous deformation-field function. This enables the design of networks creating steady arbitrary deformation fields as well as to eliminate deformation created by external time varying forces, thus increasing the effective rigidity of the beam. By including the effects of the deformation created by the channel network on the beam inertia, the response of the beam to oscillating forces can be modified, enabling the design of channel networks which create pre-defined oscillating deformation patterns in response to external oscillating forces.
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公开(公告)号：US20150217848A1
公开(公告)日：2015-08-06
申请号：US14667068
申请日：2015-03-24
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： 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 specific altitude by directing the gas to a propulsion system and high pressure gas chambers for powering the vehicle at a greater speed or to a greater altitude. The balloon can be retracted into the vehicle to achieve a better aerodynamic shape and further re-inflated for decreasing the speed of the vehicle upon reaching a destination.
摘要翻译： 一种航空航天车辆，其包括飞行器或航天器，其可操作地联接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，其适于通过将气体引导到推进系统达到特定高度而放气，并且高压气体室以更高的速度或更高的高度向车辆供电。 气囊可以缩回到车辆中以获得更好的空气动力学形状，并进一步重新充气以便在到达目的地时降低车辆的速度。
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公开(公告)号：US20120211598A1
公开(公告)日：2012-08-23
申请号：US13445708
申请日：2012-04-12
CPC分类号： B64C1/34 , B64C3/385 , B64C13/28 , B64C2201/105 , Y02T50/14
摘要： An apparatus may comprise an inflatable control surface for an aircraft and an end of the inflatable control surface configured for attachment to a fuselage of the aircraft. The end of the inflatable control surface may be configured to be rotated about an axis to control movement of the aircraft during flight.
摘要翻译： 装置可以包括用于飞行器的可充气控制表面和构造成附接到飞行器的机身的可充气控制表面的一端。 可充气控制表面的端部可以被构造为绕轴线旋转以控制飞行器在飞行过程中的运动。
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公开(公告)号：US20110127373A1
公开(公告)日：2011-06-02
申请号：US11217851
申请日：2005-09-01
CPC分类号： B64C1/34 , B64C3/185 , B64C3/34 , B64C39/024 , B64C2201/042 , B64C2201/105 , B64D27/24 , B64D37/04 , B64D37/06 , B64D37/30 , B64D41/00 , H01L35/30 , Y02T50/44 , Y02T50/53 , Y02T50/62
摘要： A vehicle including at least one bladder for containing a fuel as liquid and gas at a predetermined pressure, with a bladder outlet arranged to releasing fuel from the bladder and to maintain the fuel in the bladder at the predetermined pressure, the fuel provides thrust to the vehicle upon combustion, the fuel-filled bladder providing initial structural integrity of the vehicle. In an exemplary embodiment, the vehicle is an unmanned anal vehicle. A combustion chamber and thermoelectric conversion module can generate electricity for a propellor and battery from the fuel supply. Internal vapor pressure is maintained until the fuel bladder is empty.
摘要翻译： 一种车辆，包括用于将燃料作为液体和气体以预定压力容纳的至少一个气囊，其中气囊出口布置成从气囊释放燃料并将气体中的燃料保持在预定压力，燃料提供推力 燃料填充的气囊提供车辆的初始结构完整性。 在示例性实施例中，车辆是无人驾驶的肛门车辆。 燃烧室和热电转换模块可以从燃料供应器为推进器和电池发电。 保持内部蒸汽压力，直到燃料囊为空。
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公开(公告)号：US5881970A
公开(公告)日：1999-03-16
申请号：US434981
申请日：1995-05-04
摘要： An aircraft with automated means to transport. Spherical or one of its segments, without airfoils for lift or guidance. Means for flight are housed within the aircraft. The outer-most sureface is configured to disrupt the air-flow, over its surfaces, in flight. This, to reduce skin-friction and drag coefficients, and mollify heat build-up on the skins outer surfaces as speeds increase to and beyond mach 1. The weight of gas per unit volume, with temperature variations, is the means to reduce the gross-weight and adjust for temperature and weight changes during flight. Propulsion, within the propulsion component, is provided by turbojet engines. They are secured within an inner compression pod and an outer combustion pod. The compression pod and the attached vertical-air-duct, rotate through three hundred sixty degrees, as the means for directional guidance and direct thrust. Augmented power-thrust-tubes extend outward from the combustion pod to the mid-horizontal circumference of the aircraft. Control baffles, on each thrust-tube, check, deflect and regulate the engines' thrust to control the motivity of the aircraft. Struts retract for flight and are extended for landing. These electro-hydraulic struts, level, raise and lower the aircraft for direct ground level support operations. The aircraft has the means to maintain a horizontal flight attitude. For flight aptness the aircraft has an internal, mechanical and scientific means, for vertical ascent and vertical descent without horizontal motivity, to hover and maintain a position and altitude. And during horizontal flight, climb and descend, and perform heading changes. These flight means are all performed in the aircrafts' horizontal attitude.
摘要翻译： 一架具有自动化装置的飞机。 球形或其中一个段，没有用于升降或引导的翼型。 飞机的方式安置在飞机内。 最外面的表面配置为在飞行中破坏其表面上的空气流。 这是为了减少皮肤摩擦和阻力系数，并且随着速度增加到超过马赫1，在皮肤外表面上的热积累变得虚弱。每单位体积的气体重量与温度变化是减少毛重 重量，并适应飞行过程中的温度和重量变化。 在推进组件内的推进由涡轮喷气发动机提供。 它们固定在内部压缩舱和外部燃烧舱内。 压缩舱和连接的垂直风道，旋转三百六十度，作为定向导向和直接推力的手段。 增强的动力推力管从燃烧舱向外延伸到飞行器的中部水平周边。 控制挡板，在每个推力管上，检查，偏转和调节发动机的推力以控制飞机的动力。 Struts撤回飞行，并延长着陆。 这些电动液压支柱，水平，升高和降低飞机直接地面水平支持操作。 飞机有维持水平飞行姿态的手段。 对于飞行适应性，飞机具有内部，机械和科学的手段，用于垂直上升和垂直下降，没有水平动力，可以悬停并保持位置和高度。 在水平飞行中，爬升和下降，并执行航向变化。 这些飞行手段都是以飞机的横向姿态进行的。
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公开(公告)号：US3913871A
公开(公告)日：1975-10-21
申请号：US46641774
申请日：1974-05-02
申请人： MILLER RALPH H
发明人： MILLER RALPH H
CPC分类号： B64C39/00 , B64B2201/00 , B64C1/34
摘要： Improvement in heavier-than-air passenger aircraft having forward thrust engines, wings, a rear fin and rudder, and a lighter-than-air gas lift mechanism for enhancing the aerodynamic lift provided by the forward thrust engines and wings, such improvement comprising respective forward and rear wings, two equally widthwise spaced apart gas compartments containing lighter-than-air gas disposed vertically above the forward wing, a passenger compartment having a pilot compartment at the front end thereof, the passenger compartment disposed vertically above the forward wing and transversely centrally between the gas compartments, the forward and rear wings and the three compartments joined to each other to provide framing rigidity for said aircraft, the rear fin and rudder mounted upon the passenger compartment so as to upstand vertically therefrom to obtain a clear aerodynamic cut into the air, each compartment of substantially uniform transverse cross-section, each compartment extending axially substantially full length of said aircraft, the rear wing being a substantially full width rear wing disposed vertically above the forward wing so as to have a substantially clear aerodynamic cut into the air.
摘要翻译： 具有向前推力发动机，翼，后翼和方向舵的重型客机的改进，以及用于增强由前推力发动机和机翼提供的空气动力升力的轻于空气的气举升降机构，其改进包括各自的 前翼和后翼，两个等宽度方向间隔开的气室，其包含垂直设置在前翼上方的轻于空气的气室，在其前端具有先导舱的乘客舱，在前翼上方垂直设置的乘客舱 在气室之间的中央，前翼和后翼与三个隔间相互连接，为所述飞机提供框架刚性，后鳍和方向舵安装在乘客舱上，从而垂直向上竖立，以获得清晰的气动切割 空气，每个隔室的横截面基本均匀，每个隔室延伸一个 所述飞行器的基本上全长，后翼是垂直设置在前翼上方的基本上全宽度的后翼，以便具有基本上清楚的空气动力学切入空气。
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公开(公告)号：US10059425B2
公开(公告)日：2018-08-28
申请号：US14706476
申请日：2015-05-07
发明人： Ferdinand Vetter , Stefan Loebel
CPC分类号： B64C1/34 , B64C1/10 , B64C1/40 , B64D11/0023
摘要： An aircraft comprising a fuselage defining a longitudinal axis and an interior compartment. Along the axis, in cross-section perpendicular to the axis, the compartment is enclosed by a floor, sidewall and ceiling structure. The aircraft further comprises an environmental control system comprising a conduit system through which a pressurized fluid is supplied, at least one first terminal disposed inside the compartment and in fluid communication with the conduit system, and a selectively inflatable and deflatable partition element. The partition element comprises at least one second terminal and is constructed such that it is inflatable from a deflated condition into an inflated condition by establishing a fluid communication between the second terminal and the first terminal. In the inflated condition the partition element completely closes the cross-section of the compartment, thereby dividing it into two portions, and in the deflated condition collapses and at least partially unblocks the cross section.
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公开(公告)号：US20170217562A1
公开(公告)日：2017-08-03
申请号：US15013644
申请日：2016-02-02
申请人： James Schalla
发明人： James Schalla
CPC分类号： B64C1/34 , A63H27/12 , A63H29/18 , B64C39/024 , B64C2201/027 , B64C2201/042 , B64C2201/101 , B64C2201/108
摘要： In one embodiment, an unmanned aircraft comprises a housing, an inflatable fuselage, three motors, and three propellers. The housing may comprise an enclosure configured to house one or more electrical components. The inflatable fuselage may comprise a first, a second and a third spindle each extending from the housing. The first motor may be coupled to a first propeller and mounted to the first spindle. The second motor may be coupled to a second propeller and mounted to the second spindle. The third motor may be coupled to a third propeller and mounted to the third spindle.
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公开(公告)号：US08393576B2
公开(公告)日：2013-03-12
申请号：US13445708
申请日：2012-04-12
IPC分类号： B64C3/00
CPC分类号： B64C1/34 , B64C3/385 , B64C13/28 , B64C2201/105 , Y02T50/14
摘要： An apparatus may comprise an inflatable control surface for an aircraft and an end of the inflatable control surface configured for attachment to a fuselage of the aircraft. The end of the inflatable control surface may be configured to be rotated about an axis to control movement of the aircraft during flight.
摘要翻译： 装置可以包括用于飞行器的可充气控制表面和构造成附接到飞行器的机身的可充气控制表面的一端。 可充气控制表面的端部可以被构造为绕轴线旋转以控制飞行器在飞行过程中的运动。
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10.发明授权High strength, lightweight pressurized structure for use as the skin of a spacecraft or other vehicle 失效高强度轻质加压结构，用作航天器或其他车辆的皮肤
公开(公告)号：US6074509A
公开(公告)日：2000-06-13
申请号：US932143
申请日：1997-09-16
申请人： Douglas E. Pittman
发明人： Douglas E. Pittman
CPC分类号： B64C1/34 , B32B3/20 , B32B3/22 , B64C3/30 , E04C2/34 , Y10T156/103 , Y10T428/234 , Y10T428/239 , Y10T428/24661 , Y10T428/24942
摘要： A sandwich skin construction that is comprised of an internal structure comprising a plurality of cones disposed between two outer skins is disclosed. The interior contains a pressurized gas to give the resulting sandwich skin construction added strength over a similarly constructed non-pressurized structure of the same material with an equivalent mass. Various attributes of the cones can be adjusted, for example, size and angle, to optimize the performance of the sandwich skin construction to a variety of external stresses. Moreover, a method is provided for manufacturing the sandwich skin construction. The structure can be placed in a pressurized environment before attaching the outer skins.
摘要翻译： 公开了一种由包括设置在两个外表层之间的多个锥体的内部结构构成的夹心皮肤结构。 内部包含加压气体，以使相同质量的相同材料的类似构造的非加压结构的结果增加了夹层外观结构。 可以调整锥体的各种属性，例如尺寸和角度，以优化夹层表皮结构对各种外部应力的性能。 此外，提供了一种用于制造夹层结构的方法。 在安装外皮之前，该结构可以放置在加压环境中。
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