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81. 发明申请

US20060124800A1 Powered aircraft including inflatable and rotatable bodies exhibiting a circular cross-section perpendicular to its rotation axis and in order to generate a lift force 有权
标题翻译：动力飞机包括可旋转和可旋转的主体，其呈现垂直于其旋转轴线的圆形横截面并且产生升力
公开(公告)号：US20060124800A1
公开(公告)日：2006-06-15
申请号：US11138130
申请日：2005-05-26
申请人： Omid Tehrani
发明人： Omid Tehrani
IPC分类号： B64C39/00 , B64C27/00
CPC分类号： B64C39/005 , B64C3/30 , B64C3/56 , B64C23/02 , Y02T50/14
摘要： A lift force generating aircraft having an engine and a thrust force producing device. A pair of elongated and rotating bodies, an axial centerline through the bodies extending in a direction substantially perpendicular to a fore to aft axis extending between the engine and thrust-producing device and at a location above a center of gravity associated with the engine and thrust-producing device. The rotating bodies being constructed of a material inflatable to a desired pressure. A rotary output associated with the engine rotating the bodies, causing them to deflect to angles lesser than the perpendicular with the fore to aft axis, and in response to air stream forces acting upon the bodies in order to reduce drag forces experienced on a rear side of the rotating bodies.
摘要翻译：具有发动机和推力生成装置的升力生成机。一对细长的旋转体，穿过主体的轴向中心线，其沿着基本上垂直于发动机和推力产生装置之间的前后轴线的方向延伸，并且在与发动机和推力相关联的重心上方的位置生产设备。旋转体由可充气至期望压力的材料构成。与发动机相关联的旋转输出使主体旋转，使得它们偏转到小于垂直于前轴到后轴的角度，并且响应于作用在车体上的气流力，以减少后侧所经受的阻力的旋转体。

82. 发明申请

US20050258304A1 Reduced visibility rotorcraft and method of controlling flight of reduced visibility rotorcraft 有权
标题翻译：降低视力旋翼航空器的可视性旋翼航空器和控制飞行的方法
公开(公告)号：US20050258304A1
公开(公告)日：2005-11-24
申请号：US11189605
申请日：2005-07-26
申请人： Michael Dammar
发明人： Michael Dammar
IPC分类号： B64C27/00 , B64C39/00 , B64C39/02 , B64C27/22
CPC分类号： B64C39/00 , B64C27/00 , B64C39/024 , B64C2201/027 , B64C2201/042 , B64C2201/046 , B64C2201/048 , B64C2201/104 , B64C2201/108 , B64C2201/123 , B64C2201/127 , B64C2201/146 , B64C2201/22
摘要： A rotary aircraft (rotorcraft) in which the entire aircraft rotates about its center of mass as it flies, and in which the center of mass is located external to the aircraft in the generally triangular region formed by the aircraft's single wing and two propellers. As the aircraft flies, the two propellers provide torque about the center of mass and rotate the wing, which provides lift for the aircraft. The aircraft is controllable via a stationary radio transmitter that sends commands for pitch, roll, yaw and altitude. A receiver in the aircraft uses the transmitted signal to establish the aircraft's instantaneous orientation in combination with the sent commands to generate control signals that drive the propeller motors that affect the aircraft's attitude. Pitch and roll are controlled by pulse width modulation of the propeller motor voltages in order to affect the thrust at specific portions of the aircraft's rotation cycle.
摘要翻译：旋转飞机（旋翼飞机），其中整个飞机在其飞行时绕其质心旋转，并且其中质心位于由飞机的单翼和两个螺旋桨形成的大致三角形区域中的飞机外部。当飞机飞行时，两个螺旋桨提供关于质心的扭矩，并旋转机翼，为飞机提供升降机。飞机可以通过固定的无线电发射机进行控制，该发射机发出俯仰，滚转，偏航和高度的指令。飞机中的接收机使用传输的信号来结合发送的命令来建立飞机的瞬时定向，以产生驱动影响飞机姿态的螺旋桨马达的控制信号。俯仰和倾斜是通过螺旋桨电机电压的脉宽调制来控制的，以便影响飞机旋转周期特定部分的推力。

83. 发明申请

US20050118952A1 AIRCRAFT CONTROL METHOD 有权
标题翻译：飞机控制方法
公开(公告)号：US20050118952A1
公开(公告)日：2005-06-02
申请号：US09789450
申请日：2001-02-20
申请人： Earl Cox , Kyle Swanson
发明人： Earl Cox , Kyle Swanson
IPC分类号： B64C39/00 , B64C3/42 , B64C3/52 , B64C15/02 , B64C39/02 , B64C39/10 , B64D27/24 , B64D31/06 , G05D1/00 , H04B7/185 , H04Q7/20
CPC分类号： B64C3/42 , B64C3/52 , B64C15/02 , B64C39/024 , B64C39/10 , B64C2201/028 , B64C2201/042 , B64C2201/102 , B64C2201/122 , B64C2201/126 , B64C2201/127 , B64C2201/146 , B64C2201/165 , B64D27/24 , B64D31/06 , B64D2211/00 , G05D1/0022 , G05D1/0077 , H04B7/18504 , Y02T50/12 , Y02T50/14 , Y02T50/44 , Y02T50/55 , Y02T50/62
摘要： This disclosure provides a solar rechargeable aircraft that is inexpensive to produce, is steerable, and can remain airborne almost indefinitely. The preferred aircraft is a span-loaded flying wing, having no fuselage or rudder. Traveling at relatively slow speeds, and having a two-hundred foot wingspan that mounts photovoltaic cells on most all of the wing's top surface, the aircraft uses only differential thrust of its eight propellers to turn. Each of five segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other segments, to avoid loading them. Five two-sided photovoltaic arrays, in all, are mounted on the wing, and receive photovoltaic energy both incident on top of the wing, and which is incident also from below, through a bottom, transparent surface. The aircraft includes hinges and actuators capable of providing an adjustable dihedral for the wing. The actuators can be motors or control surfaces. Alternately, the actuators can be movable masses within the wing, which may be capable of deforming the wing to alter the aerodynamics of the wing, and thereby actuate the hinges. Because of wing dihedral, the aircraft includes motors both above and below the center of drag, and the aircraft uses differential thrust to control aircraft pitch. The aircraft has a wide variety of applications, which include serving as a long term high altitude platform that serves to link a ground station using radio wave signals and a satellite using optical signals.
摘要翻译：本公开提供了一种太阳能可再充电飞机，其生产便宜，是可操纵的，并且几乎可以无限期地保持空中飞行。首选飞机是一个装有跨距的飞翼，没有机身或方向舵。以相对较慢的速度行驶，并且拥有两百英尺的翼展，将光伏电池安装在大部分机翼的顶部表面上，飞机只使用其八个螺旋桨的差动推力来转动。翼的五个部分中的每一个具有一个或多个电动机和光伏阵列，并且独立于其它部分产生其自身的升降机，以避免加载它们。五个双面光伏阵列总体上安装在机翼上，并且接收能量入射到机翼的顶部并且从下方入射的光能通过底部的透明表面。飞机包括铰链和致动器，能够为机翼提供可调节的二面体。执行器可以是电机或控制面。或者，致动器可以是机翼内的可移动质量块，其可以使机翼变形以改变机翼的空气动力学，从而致动铰链。由于机翼二面体，飞机包括在阻力中心上方和下方的电机，飞机使用差速推力来控制飞机俯仰。该飞机具有广泛的应用，其中包括作为长期高空平台，用于使用无线电波信号连接地面站和使用光信号的卫星。

84. 发明申请

US20050001090A1 Wing driving apparatus 有权
标题翻译：翼驱动装置
公开(公告)号：US20050001090A1
公开(公告)日：2005-01-06
申请号：US10720927
申请日：2003-11-24
申请人： Teruaki Tanaka , Toshio Kamimura
发明人： Teruaki Tanaka , Toshio Kamimura
IPC分类号： B64C13/42 , F15B18/00 , B64C27/22 , B64C39/00
CPC分类号： F15B18/00 , B64C13/42
摘要： A wing driving apparatus is made up of a flight controller part for generating a drive signal, first and second servo actuators, a first controller unit having a first drive circuit, and a second controller unit having a second drive circuit. The first controller unit includes a follower signal generator circuit for generating a follower signal. The second servo actuator includes a solenoid valve for invalidating a control to the second serve actuator based on the drive signal from the second drive circuit in response to the follower signal, whereby the second second servo actuator follows the steering wing when the first drive circuit is able to operate the first servo actuator to drive the steering wing.
摘要翻译：机翼驱动装置由用于产生驱动信号的飞行控制器部分，第一和第二伺服致动器，具有第一驱动电路的第一控制器单元和具有第二驱动电路的第二控制器单元组成。第一控制器单元包括用于产生跟随信号的随动信号发生器电路。第二伺服致动器包括电磁阀，用于响应于从动信号，基于来自第二驱动电路的驱动信号使对第二伺服致动器的控制无效，由此当第一驱动电路是第二驱动电路时，第二伺服驱动器跟随转向翼能够操作第一伺服致动器来驱动转向翼。

85. 发明授权

US6148609A Turbo-rocket thruster 失效
标题翻译：涡轮火箭推进器
公开(公告)号：US6148609A
公开(公告)日：2000-11-21
申请号：US321796
申请日：1999-05-27
申请人： Anthony Italo Provitola
发明人： Anthony Italo Provitola
IPC分类号： B64B1/08 , B64B1/58 , B64C39/00 , B64G1/00 , B64G1/40 , F02K5/00
CPC分类号： B64G1/401 , B64B1/08 , B64B1/58 , B64C29/005 , B64C39/001 , B64G1/402 , F02K9/42 , B64G1/002
摘要： A turbo-rocket thruster is disclosed in which the turbine compressor is used to intake and compress a gaseous fuel for combustion with a stored oxidizer injected into the compressed gaseous fuel stream. The compressor stage is driven by the turbine stage, which is driven by burning gaseous fuel passing across the turbine blades. The burned gases are then expanded through an exhaust nozzle and thereby ejected to produce reaction thrust.
摘要翻译：公开了一种涡轮火箭推进器，其中涡轮压缩机用于吸入和压缩用于燃烧的气体燃料，其中储存的氧化剂被注入到压缩气体燃料流中。压缩机级由涡轮机级驱动，涡轮级通过燃烧通过涡轮叶片的气体燃料驱动。然后将燃烧的气体通过排气喷嘴膨胀，从而喷射以产生反作用力。

86. 发明授权

US6016991A Evacuated rotating envelope aircraft 失效
标题翻译：撤离旋转信封飞机
公开(公告)号：US6016991A
公开(公告)日：2000-01-25
申请号：US788535
申请日：1997-01-24
申请人： Charles S. Lowe, Jr.
发明人： Charles S. Lowe, Jr.
IPC分类号： B64B1/00 , B64C39/00 , B64B1/02
CPC分类号： B64C39/001 , B64B1/00 , B64C29/0025
摘要： An aircraft utilizes a buoyant evacuated rotating envelope to provide at least a portion of the lift required. The rotating envelope may be in the form of a disk, cylinder or other suitable shape. In one embodiment, an evacuated rotating envelope in the form of a disk is utilized. The disk is provided with a central core tube with at least one jet engine mounted therein. The deflection of the exhaust causes rotation of the envelope. A non-rotating payload compartment is mounted to the rotating envelope by bearings. Structures are provided for deflecting the exhaust to be utilized for lateral propulsion as well as for stabilizing the payload compartment to prevent rotation. Two other embodiments utilize rotating cylinders which may be rotated either by a jet engine mounted within a core tube or by an off center jet engine which drives the cylinder. In all of the embodiments, the envelope is evacuated by pumps and the centrifugal force of rotation reduces the amount of necessary mechanical structure to maintain the envelope shape. Accordingly, an evacuated envelope may be utilized with a minimum of weight required to maintain its structural rigidity.
摘要翻译：一架飞机使用浮力抽空的旋转外壳，以提供所需电梯的至少一部分。旋转的外壳可以是圆盘，圆筒或其他合适形状的形式。在一个实施例中，利用盘形式的抽真空的旋转外壳。该盘具有中心芯管，其中安装有至少一个喷气发动机。排气的偏转导致外壳旋转。非旋转有效负载舱通过轴承安装到旋转的外壳。提供了用于偏转用于横向推进的排气以及用于稳定有效载荷舱以防旋转的结构。另外两个实施例利用可以由安装在芯管内的喷气发动机或驱动气缸的偏心喷气发动机旋转的旋转气缸。在所有实施例中，通过泵将外壳抽真空，并且旋转离心力减小了维持外壳形状所需的机械结构的数量。因此，可以以维持其结构刚度所需的最小重量来使用抽真空的外壳。

87. 发明授权

US5839690A Inertial acceleration aircraft 失效
标题翻译：惯性加速飞机
公开(公告)号：US5839690A
公开(公告)日：1998-11-24
申请号：US697354
申请日：1996-02-22
申请人： David John Blanchette
发明人： David John Blanchette
IPC分类号： B64C39/00 , B64C27/00 , B64C39/06
CPC分类号： B64C39/001 , B64C29/0075
摘要： An aircraft structured particularly, as a whole to improve its capacity for accelerating by the means of transforming stored motion of mass into translocational motion of the aircraft; the aircraft is structured particularly, as a whole, to improve its capacities for storing motion of mass and for transforming stored motion of mass into translocational motion of itself; motion preferrably in stored as orbital motion of the aircraft's parts; the stored orbital motion preferrably is transformed by aerodynamic action into translocational motion of the aircraft; the means for storing orbital motion preferrably consists of a rotor, within the periphery of which are situated the aircraft's sustaining, propelling, motion transformation, fuel containment, and landing means; situated within said appended to a generally nonrotating fuselage are, respectively, a pilot area and a means for controlling the source of translocational flight; the preferred motion transforming means comprises a plurality of rotor blades, each of which has a longitudinal axis aligned generally with a radius of the rotor axis and of which is tiltable about a longitudinal axis, and effects the transformation with an appropriate rate collective alteration of the blade lateral axes from coincident with the blade orbital planer to the perpendiculars thereto, which alternation aerodynamically transforms the rotation of the rotor into axial motion thereof; the spin axes of the spinning mechanisms of the propulsion means parallel the rotor axis; appended to each propulsion means is a thrust redirecting means which enables the former to propel the rotor both rotationally and axially.
摘要翻译：特别是作为一个整体，通过将存储的质量运动转变为飞机的易位运动来提高其加速能力的飞机，飞机的整体结构特别是提高其存储质量运动和将储存的质量运动变为自身运动的能力; 运动优先存储为飞机零件的轨道运动; 存储的轨道运动优选地通过空气动力学作用转化为飞行器的易位运动; 用于存储轨道运动的装置优选地由转子组成，其外围位于飞机的持续，推进，运动变换，燃料封闭和着陆装置中; 位于所述附加到大体上不旋转的机身内的分别是导向区域和用于控制易位飞行源的装置; 优选的运动变换装置包括多个转子叶片，每个转子叶片具有大致与转子轴线的半径对准的纵向轴线，并且其可绕纵向轴线倾斜，并以适当的速率集中改变叶片横向轴线与叶片轨道平面重合到垂直于其的垂直方向，这种交替空气动力学地将转子的旋转变换成其轴向运动; 推进装置的旋转机构的旋转轴平行于转子轴线; 附加到每个推进装置的是推力重定向装置，其使得前者能够旋转地和轴向地推进转子。

88. 发明授权

US5413465A Propulsion device having circular array of inclined airfoil elements with radially-outwardly directed vacuum-inducing surfaces 失效
标题翻译：具有具有径向向外定向的真空诱导表面的倾斜翼型件圆形阵列的推进装置
公开(公告)号：US5413465A
公开(公告)日：1995-05-09
申请号：US196477
申请日：1994-02-15
申请人： William H. Daniel
发明人： William H. Daniel
IPC分类号： B63H1/12 , B64C11/00 , B64C39/00 , F04D29/28 , F04D29/38
CPC分类号： B64C11/007 , B63H1/12 , B64C29/0025 , B64C39/001 , F04D29/281
摘要： A propulsion device comprises a circular series of inclined airfoil elements. Each airfoil element is connected along its upper side to a rigid plate member, which is adapted to be rotated at high speed via a motor output shaft. The airfoil elements are oriented on the plate such that their vacuum-inducing surfaces face upwardly and outwardly of the circular series, and their pressure surfaces face downwardly and inwardly of the circular series.
摘要翻译：推进装置包括圆形系列的倾斜翼型元件。每个翼型元件沿其上侧连接到刚性板构件，该刚性板构件适于经由马达输出轴以高速旋转。翼型元件定位在板上，使得它们的真空诱导表面面对圆形系列的上方和外侧，并且它们的压力表面面向圆形系列的向下和向内。

89. 发明授权

US5259571A Aircraft with gyroscopic stabilization system 失效
标题翻译：具有陀螺稳定系统的飞机
公开(公告)号：US5259571A
公开(公告)日：1993-11-09
申请号：US844499
申请日：1992-03-03
申请人： Jose M. R. Blazquez
发明人： Jose M. R. Blazquez
IPC分类号： B64C39/00 , B64C39/06 , B64C15/00
CPC分类号： B64C39/001 , B64C39/06 , Y10T74/1296
摘要： An aircraft of the heavier-than-air type driven by reactors includes a fuselage of a lenticular configuration, a central shaft, and two rotary discs rotating in opposite directions and provided with large masses of inertia displaced or diplaceable toward the periphery thereof. The discs rotate about the central shaft driven by the reactors and turbines associated thereto, determining a gyroscopic effect which renders the aircraft stable. The base of the fuselage has a middle longitudinal hollow where the reactors are located. Two vertical rudders are positioned in front of and behind the fuselage and a horizontal depth aileron extends from the rear extension of the fuselage body.
摘要翻译：由反应堆驱动的重空气型飞机包括透镜状结构的机身，中心轴和沿相反方向旋转的两个旋转盘，并且具有朝向其周边移位或可置换的大质量的惯性。圆盘围绕由与其相关联的反应器和涡轮驱动的中心轴旋转，确定使飞机稳定的陀螺效应。机身的底座有反应器所在的中间纵向中空部分。两个垂直方向舵位于机身前方和后方，水平深度副翼从机身后部延伸。

90. 发明授权

US5094638A Water vehicle 失效
标题翻译：水车
公开(公告)号：US5094638A
公开(公告)日：1992-03-10
申请号：US512755
申请日：1990-04-20
申请人： Noboru Kobayashi
发明人： Noboru Kobayashi
IPC分类号： B63B1/16 , B63B35/81 , B64C31/02 , B64C31/032 , B64C31/06 , B64C39/00
CPC分类号： B63B35/815 , B62B15/003
摘要： A water vehicle comprised of a tow unit having only an internal combustion engine and a propulsion unit for propelling the watercraft and which cannot accommodate a rider. A towed unit is towed by the tow unit and includes a control device for controlling the tow unit from the towed unit. The towed unit has a kite so that it can operate either on the water or in the air.
摘要翻译：一种水车，其包括仅具有内燃机的牵引单元和用于推进船只并且不能容纳乘客的推进单元。牵引单元由牵引单元牵引并且包括用于从拖曳单元控制拖曳单元的控制装置。拖曳单元有风筝，可以在水面或空中操作。

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