公开(公告)号：US06676084B2

公开(公告)日：2004-01-13

申请号：US10168588

申请日：2002-06-24

Applicant: Jean Asseline ,  George De Noni

Inventor： Jean Asseline ,  George De Noni

IPC: B64D1734

CPC classification number: A63H27/08 ,  A63H30/04 ,  B64C2201/086 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/187 ,  Y10S244/902 ,  Y10S244/903

Abstract: A small radio controlled flying device propelled by a thermal engine (20) with pusher type airscrew (19) for remote sensing, the device being capable of short take-off and landing and flying at maximum speed of 35 Km/h. The device includes a pod and wings, the pod (1) being a rigid tricycle carriage dismountable by disengagement of substantially pyramidal jig with rear base (2) and front apex (7), lower plane (3), two lateral planes (4, 5) and an upper plane (6). The base is a welded one-piece element that includes the engine, the airscrew, a tank and the radio control. The apex is a welded one-piece element. The lower plane and the two lateral planes include spars (11, 12) assembled at the base and as the apex. The lower plane includes at its three end angles two rear wheels (8) and a front wheel (9), the front wheel being provided to protrude towards the front in the apex and the wheels being low pressure tires. The wings (13) are a caisson-type supple parachute and are connected to the pod in an adjustable fashion by two front slings (17), two braking slings (18) acting on the two flaps/ailerons.

Abstract translation: 由具有推进式螺旋桨（19）的热力发动机（20）推进的用于遥感的小型无线电控制飞行装置，该装置能够以35Km / h的最大速度短时起飞和着陆并飞行。 该装置包括荚和翼，荚（1）是刚性三轮车，可通过基本上棱锥形的夹具与后基部（2）和前顶点（7），下平面（3），两个侧平面（4， 5）和上平面（6）。 底座是焊接的单件元件，包括发动机，螺旋桨，油箱和无线电控制。 顶点是焊接的单件元件。 下平面和两个横向平面包括组装在基部和顶点的翼梁（11,12）。 下平面在其三个端角处包括两个后轮（8）和前轮（9），前轮设置成朝向顶点的前部突出，并且轮是低压轮胎。 机翼（13）是沉箱式柔软的降落伞，并且通过两个前吊索（17）和作用在两个翼片/副翼上的两个制动吊索（18）以可调节的方式连接到吊舱。

公开(公告)号：US20040004157A1

公开(公告)日：2004-01-08

申请号：US10296137

申请日：2003-06-30

Inventor： Lance A. Liotta

IPC: B64D027/00 ,  B64D029/00

CPC classification number: B64C39/066 ,  A63H27/00 ,  B64C39/028 ,  B64C2201/105 ,  B64C2201/107

Abstract: An aircraft which is designed for remote controlled slow flight, indoor or in a small outdoor yard or field. The aerial lifting body is defined by a series of lightweight planar or thin airfoil surfaces (A1, A2, A3, A4) arranged in a radially symmetrical configuration. Suspended within the cavity (O) formed by the thin airfoil surfaces (A1, A2, A3, A4) is a thrust generating propeller system (C) that is angled upwardly and that can be regulated remotely so as to change the angle of the thrust vector within the cavity (O) for steering. Lifting, stability, turning, and general control of the direction of motion in flight is accomplished without any formal wings, rudder, tail, or control surfaces.

Abstract translation: 一种专为遥控慢速飞行，室内或室外小型场地设计的飞机。 升降体由一系列以径向对称构造布置的轻型平面或薄型翼型表面（A1，A2，A3，A4）限定。 悬挂在由薄翼面（A1，A2，A3，A4）形成的空腔（O）内的是推力发生螺旋桨系统（C），其向上倾斜并且可以远程调节，以便改变推力角 在腔（O）内的向量用于转向。 飞行中的运动方向的提升，稳定性，转向和一般控制是在没有任何正式的机翼，方向舵，尾翼或控制面的情况下完成的。

公开(公告)号：US20140255189A1

公开(公告)日：2014-09-11

申请号：US14250385

申请日：2014-04-11

Applicant: The Boeing Company

Inventor： Kevin Reed Lutke ,  Aaron Jonathan Kutzmann

IPC: B64C3/30

CPC classification number: B64C3/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/105

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.

Abstract translation: 一种用于操作翼型系统的方法和装置。 可能产生气体。 气体可以被送入包括可膨胀的气翼和截面的充气翼型系统中。 可膨胀翼型件可以具有内端和外端，其中可膨胀翼型可以由许多基本上通过电磁波通过可充气翼型的材料构成。 该部分可以具有多个开口，其中可充气翼片的内端可以与该部分相关联。 该部分可以被配置为与机身相关联。 开口的数量可以被配置为提供与可膨胀翼型件的内部的通信。 具有开口数量的部分可以被配置为减少遇到该部分的电磁波的反射。

公开(公告)号：US20120211598A1

公开(公告)日：2012-08-23

申请号：US13445708

申请日：2012-04-12

Applicant: Kevin Reed Lutke ,  Aaron Jonathan Kutzmann

Inventor： Kevin Reed Lutke ,  Aaron Jonathan Kutzmann

IPC: B64C13/00 ,  B64C13/28 ,  B64C3/46

CPC classification number: B64C1/34 ,  B64C3/385 ,  B64C13/28 ,  B64C2201/105 ,  Y02T50/14

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20120109427A1

公开(公告)日：2012-05-03

申请号：US13381197

申请日：2009-10-28

Applicant: Bernard Berthier

Inventor： Bernard Berthier

IPC: G05D1/00 ,  B64C31/036

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：托架提供有控制所述索具线的自动驾驶控制致动器;所述翼型件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，能够限定翼型的位置 相对于地面的参考框架和用于与所述自动驾驶仪通信的装置; - 在起飞时，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，以控制所述致动器。 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。

公开(公告)号：US20110127373A1

公开(公告)日：2011-06-02

申请号：US11217851

申请日：2005-09-01

Applicant: James P. Thomas ,  Jared N. Baucom ,  William R. Pogue, III ,  Muhammad A. Qidwai

Inventor： James P. Thomas ,  Jared N. Baucom ,  William R. Pogue, III ,  Muhammad A. Qidwai

IPC: B64C11/00 ,  H01L35/30 ,  F16L3/01

CPC classification number: 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

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20090045284A1

公开(公告)日：2009-02-19

申请号：US11840607

申请日：2007-08-17

Applicant: Adam N. Chu

Inventor： Adam N. Chu

IPC: B64B1/00

CPC classification number: B64C39/024 ,  B64B1/02 ,  B64C2201/022 ,  B64C2201/101 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/127 ,  B64C2201/165

Abstract: An orientation system is disclosed for a lighter-than-air aircraft having a lower stage suspended from an envelope. The orientation system includes cords interconnecting the envelope and the lower stage and means for adjusting the length of at least one of the cords between the lower stage and the envelope. Adjusting the length produces a shift in the angle of attack of the envelope with respect to the lower stage.

Abstract translation: 公开了一种具有从信封悬挂的较低级的轻型飞机的定向系统。 定向系统包括将信封和下层相互连接的绳索和用于调节下层和包封之间的至少一根帘线长度的装置。 调整长度会导致信封相对于下层的迎角发生偏移。

公开(公告)号：US20070084971A1

公开(公告)日：2007-04-19

申请号：US11252185

申请日：2005-10-18

Applicant: Haru Miyake

Inventor： Haru Miyake

IPC: B64C13/20

CPC classification number: B64C13/20 ,  A63H27/007 ,  A63H27/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/165

Abstract: A wireless-controlled airplane includes a flying unit and an on-ground controller which is connected to the flying unit through a communication section and flies the flying unit. The flying unit includes a body, a drive section installed on the body, a propulsion apparatus which generates a propulsive force when driven by the drive section, a main wing including a plurality of wing elements which are installed so as to be able to move with respect to each other, an opening and closing mechanism which changes the relative positions of the wing elements to change the effective area of the main wing, and a dropping apparatus which selectively holds and drops a load. By changing the effective area of the main wing, the flight speed can be changed, so the capacity and size of the drive section for rotating the propulsion apparatus can be decreased.

Abstract translation: 无线控制飞机包括飞行单元和地面控制器，其通过通信部分连接到飞行单元并飞行飞行单元。 飞行单元包括主体，安装在主体上的驱动部分，当由驱动部驱动时产生推进力的推进装置，包括多个翼元件的主翼，其安装成能够与 相对于彼此相对的改变主翼的有效面积而改变翼元件的相对位置的开闭机构，以及选择性地保持和降低载荷的下落装置。 通过改变主翼的有效面积，可以改变飞行速度，因此可以减小用于旋转推进装置的驱动部的容量和尺寸。

公开(公告)号：US20060060706A1

公开(公告)日：2006-03-23

申请号：US10927579

申请日：2004-08-26

Applicant: Daryl Elam

Inventor： Daryl Elam

IPC: B64B1/58

CPC classification number: B64C3/30 ,  B64C39/024 ,  B64C2201/105

Abstract: An inflatable structure constructed of flexible material that can occupy a minimal volume when in a deflated and stored condition as compared to its fully inflated and deployed configuration, has sufficient structural rigidity to function as a wing when deployed. The wing includes an array of inflatable chambers with generally circular cross-sections. The chambers are spaced a particular distance between their centers and held in that spacing by an outer wing skin. For equal cross-sectional diameter chambers this distance is less than the diameter. When the chambers are inflated the close spacing causes tension in the opposing surfaces to create a rigid structure.

Abstract translation: 与其完全膨胀和展开的构造相比，当处于放气和储存状态时可以占据最小体积的柔性材料构成的充气结构在展开时具有足够的结构刚度用作翼。 机翼包括具有大致圆形横截面的可充气室阵列。 这些室在它们的中心之间隔开特定的距离，并通过外翼皮保持在该间隔中。 对于等截面直径的腔室，该距离小于直径。 当室被充气时，紧密的间隔在相对的表面中产生张力以产生刚性结构。

公开(公告)号：US20020190157A1

公开(公告)日：2002-12-19

申请号：US10168588

申请日：2002-06-24

Inventor： Jean Asseline ,  George De Noni

IPC: B64C001/00 ,  B64C003/00 ,  B64C005/00 ,  B64C007/00

CPC classification number: A63H27/08 ,  A63H30/04 ,  B64C2201/086 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/187 ,  Y10S244/902 ,  Y10S244/903

Abstract: This invention relates to a small-sized radio controlled flying device propelled by a thermal engine (20) with pusher type airscrew (19) for remote sensing, said device enabling short take-off and landing and flying at maximum speed of 35 Km/h. The device comprises a pod and wings, the pod (1) being a rigid tricycle carriage dismountable by disengagement of substantially pyramidal jig with rear base (2) and front apex (7), lower plane (3), two lateral planes (4, 5) and an upper plane (6), the base being a welded one-piece element and comprising the engine, the airscrew, a tank and the radio control, the apex being a welded one-piece element, the lower plane and the two lateral planes comprising spars (11, 12) at least assembled at the base and at the apex, the lower plane comprising at its three end angles two rear wheels (8) and a front wheel (9), the front wheel being provided to protrude towards the front in the apex and the wheels being low pressure tires, the wings (13) being a caisson-type supple parachute, said wings being connected to the pod in an adjustable fashion by two front slings (17), two braking slings (18) acting on the two flaps/ailerons.

Abstract translation: 本发明涉及一种由具有用于遥感的推进式螺旋桨（19）的热引擎（20）推进的小型无线电控制飞行装置，所述装置能够以35Km / h的最大速度进行短时起飞和着陆和飞行 。 该装置包括荚和翼，所述荚（1）是刚性三轮车，通过基本上棱锥形的夹具与后基部（2）和前顶点（7），下平面（3），两个侧平面（4， 5）和上平面（6），底座是焊接的整体元件，包括发动机，螺旋桨，水箱和无线电控制器，顶点是焊接的一体元件，下平面和两个 包括至少在基部和顶点处组装的翼梁（11,12）的横向平面，所述下平面在其三个端角处包括两个后轮（8）和前轮（9），所述前轮设置成突出 朝向顶端的前部并且车轮是低压轮胎，翼（13）是沉箱式柔软的降落伞，所述翼以可调节的方式通过两个前吊索（17），两个制动吊索（ 18）作用于两个翼片/副翼。