Inflatable airfoil system having reduced radar observability

    公开(公告)号:US09988138B2

    公开(公告)日:2018-06-05

    申请号:US14250385

    申请日:2014-04-11

    Abstract: A method and apparatus for operating an airfoil system. A gas may be generated. The gas may be sent into an inflatable airfoil system comprising an inflatable air foil and a section. The inflatable airfoil may have an inner end and an outer end in which the inflatable airfoil may be comprised of a number of materials that substantially pass electromagnetic waves through the inflatable airfoil. The section may have a number of openings in which the inner end of the inflatable airfoil may be associated with the section. The section may be configured to be associated with a fuselage. The number of openings may be configured to provide communications with an interior of the inflatable airfoil. The section with the number of openings may be configured to reduce reflection of the electromagnetic waves encountering the section.

    Adaptable solar airframe with a flexible photovoltaic system
    25.
    发明授权
    Adaptable solar airframe with a flexible photovoltaic system 有权
    具有柔性光伏系统的适应性太阳能机身

    公开(公告)号:US09067668B2

    公开(公告)日:2015-06-30

    申请号:US14091969

    申请日:2013-11-27

    Abstract: 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.

    Abstract translation: 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。

    Automatic takeoff method for an aircraft with a flexible airfoil, and airfoil and aircraft
    26.
    发明授权
    Automatic takeoff method for an aircraft with a flexible airfoil, and airfoil and aircraft 有权
    具有柔性翼型,翼型和飞机的飞机的自动起飞方法

    公开(公告)号:US08855838B2

    公开(公告)日:2014-10-07

    申请号:US13381197

    申请日:2009-10-28

    Inventor: Bernard Berthier

    CPC classification number: B64C31/036 B64C39/024 B64C2201/105 B64C2201/107

    Abstract: The invention relates to an automatic takeoff method for an aircraft with a flexible airfoil, comprising a carriage suspended by rigging lines from an airfoil. According to said method: —said carriage is provided with an autopilot controlling actuators that control said rigging lines; —said airfoil is provided with an airfoil attitude sensor, comprising a biaxial accelerometer and a biaxial rate gyro, capable of defining the position of an airfoil reference frame in relation to the ground, and means for communicating with said autopilot; —during takeoff, information is received from said airfoil attitude sensor and transmitted to said autopilot for the purpose of controlling said actuators. The invention also relates to an airfoil for the implementation of said method, comprising an airfoil attitude sensor with an inertial unit with a biaxial accelerometer and a biaxial rate gyro, and means for communicating with an autopilot. The invention further relates to an aircraft comprising such an airfoil.

    Abstract translation: 本发明涉及一种具有柔性翼型的飞行器的自动起飞方法,该飞行器包括通过从翼型装配线路悬挂的滑架。 根据所述方法:托架具有控制所述索具线的自动驾驶控制致动器; 翼面设置有翼型姿态传感器,包括双轴加速度计和双轴率陀螺仪,其能够定义相对于地面的翼型参考框架的位置,以及用于与所述自动驾驶仪通信的装置; 在起飞时,为了控制所述致动器,从所述翼型姿态传感器接收信息并传送到所述自动驾驶仪。 本发明还涉及一种用于实现所述方法的翼型件,包括具有带有双轴加速度计和双轴率陀螺仪的​​惯性单元的翼型姿态传感器和用于与自动驾驶仪通信的装置。 本发明还涉及一种包括这种翼型的飞行器。

    ADAPTIVE SOLAR AIRFRAME
    27.
    发明申请
    ADAPTIVE SOLAR AIRFRAME 有权
    自适应太空飞机

    公开(公告)号:US20140203139A1

    公开(公告)日:2014-07-24

    申请号:US14091969

    申请日:2013-11-27

    Abstract: 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.

    Abstract translation: 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。

    Aerial delivery system
    28.
    发明申请
    Aerial delivery system 审中-公开
    空中交付系统

    公开(公告)号:US20090026319A1

    公开(公告)日:2009-01-29

    申请号:US12222485

    申请日:2008-08-11

    Applicant: Edward Strong

    Inventor: Edward Strong

    Abstract: An aerial delivery system including a ram-air parachute, one or more recovery parachutes, a mantle removably attached to a cargo, and a controller operably connected to the mantle, the ram-air parachute, and the one or more recovery parachutes. The controller may be configured to receive location information associated with a target, receive information related to an ambient condition, determine a recovery parachute opening point based on the target information and the ambient condition, and cause a navigation of the aerial delivery system to the determined recovery parachute opening point.

    Abstract translation: 一种空中输送系统,包括冲击空气降落伞,一个或多个回收降落伞,可移除地附接到货物的地幔,以及可操作地连接到地幔,冲击空降落伞和一个或多个恢复降落伞的控制器。 控制器可以被配置为接收与目标相关联的位置信息,接收与环境条件相关的信息,基于目标信息和环境条件来确定恢复降落伞开放点,并且使空中传送系统导航到所确定的 恢复降落伞开放点。

    Deployable, rigidizable wing
    30.
    发明申请
    Deployable, rigidizable wing 审中-公开
    可部署,可固化翼

    公开(公告)号:US20050151007A1

    公开(公告)日:2005-07-14

    申请号:US10770130

    申请日:2004-02-03

    CPC classification number: B64C39/024 B64C3/56 B64C2201/105

    Abstract: A novel design and construction method for an inflatable, rigidizable wing for a terrestrial or planetary flying vehicle. The wing is caused to deploy from an initially packed condition and to assume its functional shape by means of an inflation gas. After inflation, the wing is rigidized by any of several means, such that the inflation gas is no longer required. The composite wing is fabricated from a base reinforcement material, often a fabric, which is coated with a polymer resin that hardens when exposed to a curing mechanism. Several activation mechanisms exist by which to initiate rigidization of such a structure, including elevated temperature, ultraviolet light, and chemical constituents of the inflation gas. The resultant wing has fundamental advantages compared to existing inflatable wings, including improved stiffness, and reduced susceptibility to structural failure in response to puncture.

    Abstract translation: 一种用于陆地或行星飞行器的可充气,可固定翼的新颖设计和施工方法。 使机翼从初始包装状态部署,并通过充气气体承担其功能形状。 在膨胀之后,机翼通过几种手段中的任何一种来固定,使得不再需要膨胀气体。 复合翼片由基底增强材料制成,通常是织物,其涂覆有当暴露于固化机构时硬化的聚合物树脂。 存在几种启动机制,其通过其启动这种结构的刚性化,包括升高的温度,紫外线和膨胀气体的化学成分。 所得到的翼片与现有的充气翼相比具有基本的优点,包括改善的刚度,以及降低响应于穿刺的结构失效的敏感性。

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