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61. 发明申请

US20130068880A1 INFLATABLE FOLDING WINGS FOR A VERY HIGH ALTITUDE AIRCRAFT 有权
公开(公告)号：US20130068880A1
公开(公告)日：2013-03-21
申请号：US13620249
申请日：2012-09-14
申请人： Robert Parks , Adam Woodworth , Peter Lively , Thomas Vaneck , Kimberly Kohlhepp , Justin McClellan
发明人： Robert Parks , Adam Woodworth , Peter Lively , Thomas Vaneck , Kimberly Kohlhepp , Justin McClellan
IPC分类号： B64C3/56
CPC分类号： B64C39/024 , B64C3/56 , B64C2201/021 , B64C2201/102 , B64C2201/127
摘要： A foldable wing for use with a very high altitude aircraft capable of operating at an altitude at or above 85,000 feet is disclosed. The foldable wing may employ a spiral fold deployment, wherein a hinge between each segment of the foldable wing is slightly offset from the perpendicular. Successively positioned wing segments fold over one another. Alternatively, the hinges are substantially perpendicular so that each respective wing segment folds linearly against the next wing segment. An inflatable rib, with inflatable arms, can be inflated to provide a force against two adjacent arms, thereby deploying the wing segments through a full 180° of rotation.

62. 发明授权

US08356770B2 Tail-mounted pointable solar panels for solar-powered aircraft 有权
标题翻译：用于太阳能飞机的尾部可点焊太阳能电池板
公开(公告)号：US08356770B2
公开(公告)日：2013-01-22
申请号：US12904562
申请日：2010-10-14
申请人： Robert Parks
发明人： Robert Parks
IPC分类号： B64C9/06
CPC分类号： B64D27/24 , B64C2201/021 , B64C2201/042 , B64D2211/00 , Y02T50/55
摘要： An aircraft tail section has a first tail component and a second tail component, the first tail component being positioned further forward than the second tail component with respect to a nose of the aircraft. Each tail component has two surfaces, each of the two surfaces of at least one of the first and second tail components comprises a solar panel configured to collect solar energy. Each tail component is rotatable with respect to a centerline of the aircraft such that an offset angle of between zero degrees and 180 degrees is formed between corresponding surfaces of the first and second tail components. Preferably, the tail components are rotated into (i) a takeoff and landing configuration that is substantially horizontal, and (ii) a crosswise configuration during flight such that collection of solar energy is maximized.
摘要翻译：飞机尾部具有第一尾部部件和第二尾部部件，第一尾部部件相对于飞行器的鼻部位于比第二尾部部件更靠前的位置。每个尾部部件具有两个表面，第一和第二尾部部件中的至少一个的两个表面中的每一个包括被配置为收集太阳能的太阳能电池板。每个尾部部件可相对于飞行器的中心线旋转，使得在第一和第二尾部部件的对应表面之间形成零度和180度之间的偏移角。优选地，尾部部件旋转成（i）基本水平的起飞和着陆构造，以及（ii）飞行期间的横向构造，使得太阳能的收集最大化。

63. 发明申请

US20110226174A1 COMBINED SUBMERSIBLE VESSEL AND UNMANNED AERIAL VEHICLE 审中-公开
标题翻译：组合的不合格船只和无人驾驶的航空器
公开(公告)号：US20110226174A1
公开(公告)日：2011-09-22
申请号：US12484557
申请日：2009-06-15
申请人： ROBERT PARKS
发明人： ROBERT PARKS
IPC分类号： B63G8/00 , B63G8/08
CPC分类号： B64C37/00 , B60F5/02 , B63G8/001 , B63G8/08 , B63G2008/005 , B64C39/024 , B64C2201/021 , B64C2201/042 , B64C2201/08 , B64C2201/102 , B64C2201/127 , B64C2201/165 , B64C2201/167 , F42B15/20
摘要： A combined submersible vessel and unmanned aerial vehicle preferably includes a body structure, at least one wing structure coupled to the body structure, at least one vertical stabilizer structure coupled to the body structure, and at least one horizontal stabilizer structure coupled to the body structure. A propulsion system is coupled to the body structure and is configured to propel the flying submarine in both airborne flight and underwater operation. Preferably, the propulsion system includes a motor, a gearbox coupled to the motor and configured to receive power generated by the motor and provide variable output power, a drive shaft coupled to the gearbox and configured to transfer the variable output power provided by the gearbox, and a propeller coupled to the drive shaft and configured to accept power transferred to it from the drive shaft. The propeller is further configured to rotate and propel the flying submarine in both an airborne environment and in an underwater environment.
摘要翻译：组合潜艇和无人驾驶飞行器优选地包括主体结构，联接到主体结构的至少一个翼结构，联接到主体结构的至少一个垂直稳定器结构，以及耦合到主体结构的至少一个水平稳定器结构。推进系统联接到车身结构并且被构造成在空中飞行和水下操作中推进飞行潜艇。优选地，推进系统包括电动机，耦合到电动机并被配置为接收由电动机产生的电力并提供可变输出功率的变速箱;耦合到齿轮箱并被配置为传递由变速箱提供的可变输出功率的驱动轴，以及联接到所述驱动轴并被配置为接受从所述驱动轴传递到其的动力的螺旋桨。螺旋桨进一步构造成在空中环境和水下环境中旋转和推进飞行潜艇。

64. 外观设计

USD640537S1 Line clamp 有权
标题翻译：线夹
公开(公告)号：USD640537S1
公开(公告)日：2011-06-28
申请号：US29368446
申请日：2010-08-24
申请人： Robert Parks , Matthew Cimbala , Joy Cottrill , Steven Day , Ryan Kaintz , Regis J. Nero, Jr. , Jeffrey Allan Gibala
设计人： Robert Parks , Matthew Cimbala , Joy Cottrill , Steven Day , Ryan Kaintz , Regis J. Nero, Jr. , Jeffrey Allan Gibala

65. 外观设计

USD622583S1 Line clamp 有权
标题翻译：线夹
公开(公告)号：USD622583S1
公开(公告)日：2010-08-31
申请号：US29317219
申请日：2008-04-24
申请人： Robert Parks , Matthew G. Cimbala , Joy Cottrill , Steven P. Day , Ryan Kaintz , Regis J. Nero, Jr. , Jeffrey Allan Gibala
设计人： Robert Parks , Matthew G. Cimbala , Joy Cottrill , Steven P. Day , Ryan Kaintz , Regis J. Nero, Jr. , Jeffrey Allan Gibala

66. 发明申请

US20100213309A1 NON-PLANAR ADAPTIVE WING SOLAR AIRCRAFT 审中-公开
标题翻译：非平面自适应太阳能飞机
公开(公告)号：US20100213309A1
公开(公告)日：2010-08-26
申请号：US12211027
申请日：2008-09-15
申请人： Robert Parks
发明人： Robert Parks
IPC分类号： B64C39/00 , B64C3/42 , B64C9/00 , B64C3/00 , B64D27/24
CPC分类号： B64C3/16 , B64D27/24 , Y02T50/12 , Y02T50/44 , Y02T50/62
摘要： A system and method for assembling and operating a solar powered aircraft, composed of one or more modular constituent wing panels. Each wing panel includes at least one hinge interface that is configured to rotationally interface with a complementary hinge interface on another wing panel. When a first and second wing panel are coupled together via the rotational interface, they can rotate with respect to each other within a predetermined angular range. The aircraft further comprises a control system that is configured to acquire aircraft operating information and atmospheric information and use the same alter the angle between the wing panels, even if there are multiple wing panels. One or more of the wing panels can include photovoltaic cells and/or solar thermal cells to convert solar radiation energy or solar heat energy into electricity, that can be used to power electric motors. Further, the control system is configured to alter an angle between a wing panel and the horizon, or the angle between wing panels, to maximize solar radiation energy and solar thermal energy collection. A tail assembly for the aircraft includes a rotational pivot that allows the flight control surfaces to rotate to different orientations to avoid or reduce flutter loads and to increase solar radiation energy and/or solar thermal energy collection from photovoltaic cells and/or solar thermal cells the can be located on the tail structure associated with the flight control surfaces.
摘要翻译：一种用于组装和操作太阳能飞行器的系统和方法，由一个或多个模块化组件翼板组成。每个翼板包括至少一个铰链接口，其被配置为与另一翼板上的互补铰链接口旋转地接合。当第一和第二翼板通过旋转接口联接在一起时，它们可以在预定角度范围内相对于彼此旋转。飞机还包括控制系统，其被配置为获取飞行器操作信息和大气信息，并且使用该控制系统改变翼板之间的角度，即使存在多个翼板。一个或多个翼板可以包括用于将太阳能辐射能量或太阳能热能转换成电的光伏电池和/或太阳能热电池，其可用于为电动机供电。此外，控制系统被配置为改变翼板与地平线之间的角度或翼板之间的角度，以最大化太阳辐射能量和太阳能热能收集。用于飞机的尾部组件包括旋转枢轴，其允许飞行控制表面旋转到不同的取向以避免或减少颤动负载并且增加从光伏电池和/或太阳能热电池收集太阳辐射能量和/或太阳能热能。可以位于与飞行控制表面相关联的尾部结构上。

67. 发明申请

US20090127376A1 WING TIP DOCKING SYSTEM FOR AIRCRAFT 有权
标题翻译：飞机起落架系统
公开(公告)号：US20090127376A1
公开(公告)日：2009-05-21
申请号：US12210711
申请日：2008-09-15
申请人： Martin L. Gomez , Robert Parks , Adam J. Woodworth
发明人： Martin L. Gomez , Robert Parks , Adam J. Woodworth
IPC分类号： B64C37/02
CPC分类号： B64C37/02 , B64C23/076 , B64C39/024 , B64D2211/00 , Y02T50/164 , Y02T50/55
摘要： A system and method for docking various types of aircraft is disclosed. An aerodynamic lifting structure docking mechanism for docking two or more aircraft is provided comprising an aerodynamic lifting structure. The aerodynamic lifting structure includes a first and second airflow adjustment mechanism. The aerodynamic lifting structure further includes a first hard docking mechanism, and a second hard docking mechanism, and still further includes a soft docking mechanism. The first and second airflow adjustment mechanisms are configured to substantially remove any aerodynamic lifting structure vortices around each of the aerodynamic lifting structure tip areas. The soft docking mechanism is configured to soft dock a first aerodynamic lifting structure with a second aerodynamic lifting structure. The first hard docking mechanism is configured to hard dock with the second hard docking mechanism, thereby temporarily attaching the first aerodynamic lifting structure with the second aerodynamic lifting structure.
摘要翻译：公开了用于对接各种类型的飞机的系统和方法。提供了用于对接两个或更多个飞行器的空气动力提升结构对接机构，其包括空气动力提升结构。空气动力提升结构包括第一和第二气流调节机构。空气动力提升结构还包括第一硬对接机构和第二硬对接机构，并且还包括软对接机构。第一和第二气流调节机构构造成基本上去除围绕每个空气动力提升结构尖端区域的任何空气动力学提升结构涡流。柔性对接机构被配置为使第一空气动力提升结构与第二空气动力提升结构软对接。第一硬对接机构构造成与第二硬对接机构硬地对接，从而将第一空气动力提升结构临时附接到第二空气动力提升结构。

68. 发明申请

US20090121074A1 WING LOAD ALLEVIATION STRUCTURE 有权
标题翻译： WOW LOAD ALLEVIATION STRUCTURE
公开(公告)号：US20090121074A1
公开(公告)日：2009-05-14
申请号：US12139363
申请日：2008-06-13
申请人： THOMAS VANECK , ROBERT PARKS
发明人： THOMAS VANECK , ROBERT PARKS
IPC分类号： B64C3/00 , B64C3/18 , B64D41/00
CPC分类号： B64C13/16 , B64C3/185 , B64C2201/021 , Y02T50/44
摘要： A wing load alleviation structure for use on an aircraft, comprising a front spar, wherein the front spar includes a plurality of alternating rigid spar structures and inflatable spar structures; and a rear spar, wherein the rear spar includes a plurality of alternating rigid spar structures and pivot joints, such that when a load is applied to the front and rear spars, deflection of each of the front and rear spars continues at a first rate until a critical load is reached, and then as the loading increases, deflection of each of the front and rear spars continues at a second rate.
摘要翻译：一种用于飞机上的机翼负载减轻结构，包括前翼梁，其中所述前翼梁包括多个交替的刚性翼梁结构和可充气翼梁结构; 和后翼梁，其中后翼梁包括多个交替的刚性翼梁结构和枢转接头，使得当负载施加到前翼梁和后翼梁时，前翼梁和后翼梁中的每一个的偏转以第一速率持续，直到达到临界负载，然后随着载荷的增加，前后翼梁中的每一个的偏转以第二速率继续。

69. 发明授权

US07506837B2 Inbound transition control for a tail-sitting vertical take off and landing aircraft 有权
标题翻译：尾部垂直起飞和着陆飞机的入站过渡控制
公开(公告)号：US07506837B2
公开(公告)日：2009-03-24
申请号：US11228229
申请日：2005-09-19
申请人： Robert Parks
发明人： Robert Parks
IPC分类号： B64C27/22
CPC分类号： B64C3/385 , B64C29/02 , G05D1/0669 , Y02T50/14
摘要： A system for controlling inbound transition of an aircraft includes a fuselage and first and second freewings pivotably mounted on opposing sides thereof. The system includes an airspeed sensor that outputs an airspeed indication signal. The system includes a controller for increasing aircraft engine thrust to substantially maximum for inbound transition, and for generating pitch and freewing control signals. The system includes actuators for actuating aircraft control surfaces in response to the pitch control signal to rapidly increase pitch of the fuselage to decelerate the aircraft, and for actuating freewing control surfaces in response to the freewing control signal to adjust lift produced by the freewings to oppose climbing of the aircraft due to the increase in engine thrust and the increase in the fuselage pitch. The controller is configured to decrease the engine thrust as the aircraft decelerates until the aircraft is in a hover mode.
摘要翻译：一种用于控制飞行器入境过渡的系统包括机身以及可枢转地安装在其相对侧上的第一和第二快门。该系统包括输出空速指示信号的空速传感器。该系统包括一个控制器，用于将飞机发动机推力增加到进入过渡的基本最大值，并产生俯仰和自由控制信号。该系统包括用于响应于俯仰控制信号来致动飞行器控制表面的致动器，以快速增加机身的俯仰以使飞行器减速，以及响应于自由转动控制信号来驱动释放控制表面，以调节由空档产生的升力来抵抗由于发动机推力的增加和机身间距的增加，飞机上升。控制器配置成当飞机减速直到飞机处于悬停模式时，减小发动机推力。

70. 发明申请

US20090065651A1 SAIL WING WITH HIGH SPAN EFFICIENCY AND CONTROLLED PITCHING MOMENT 有权
标题翻译：具有高跨度效率和控制式搅拌动作的SAIL WING
公开(公告)号：US20090065651A1
公开(公告)日：2009-03-12
申请号：US12138900
申请日：2008-06-13
申请人： Robert Parks
发明人： Robert Parks
IPC分类号： B64C3/14
CPC分类号： B64C3/10 , B64C31/028 , Y02T50/12
摘要： An aircraft comprising a fuselage, a sail wing appended to the fuselage, the sail wing having a sail wing root chord length, and wherein the sail wing includes a sail wing leading edge spar, a sail wing membrane attached to the sail wing leading edge spar, and a sail wing trailing edge wire located at a trailing edge of the sail wing membrane, the aircraft further comprising a wing surface extension, located aft and at an inboard area of the sail wing trailing edge wire, the wing surface extension having a wing surface extension root chord length, and wherein the wing surface extension includes a wing surface extension membrane attached to the sail wing trailing edge wire, and a wing surface extension trailing edge, and wherein the wing surface extension trailing edge is reflexed such that the wing surface extension trailing edge is positioned upwards at a first angle with respect to a plane formed along a centerline of the aircraft and along the lower surfaces of the sail wing. The wing surface extension is further configured to affect a reduced nose-up pitching moment, and to produce a more even coefficient of lift along the wing of the aircraft.
摘要翻译：一种飞机，包括机身，附属于机身的帆翼，具有帆翼根弦长的帆翼，并且其中所述帆翼包括帆翼前缘翼梁，附连到帆翼前缘翼梁的帆翼膜以及位于帆翼膜的后缘处的帆翼后缘线，所述飞机还包括机翼表面延伸部，所述机翼表面延伸部位于帆翼后缘线的后部和内侧区域，翼表面延伸部具有翼表面延伸根弦长度，并且其中所述机翼表面延伸部包括附接到所述帆翼后缘线的翼表面延伸膜和翼表面延伸后缘，并且其中所述翼表面延伸后缘被反射，使得所述翼表面延伸膜延伸后缘相对于沿着飞行器的中心线形成的平面并沿着帆翼的下表面以第一角度向上定位。机翼表面延伸部进一步构造成影响减小的俯仰俯仰时刻，并且沿着飞行器的翼部产生更均匀的升力系数。

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