公开(公告)号：US06976653B2

公开(公告)日：2005-12-20

申请号：US10626697

申请日：2003-07-25

Applicant: Piero Perlo ,  Denis Bollea ,  Roberto Finizio ,  Cosimo Carvignese ,  Elena Balocco

Inventor： Piero Perlo ,  Denis Bollea ,  Roberto Finizio ,  Cosimo Carvignese ,  Elena Balocco

IPC: B64C27/20 ,  B64C29/02 ,  B64C39/02 ,  B64C27/26

CPC classification number: B64C29/02 ,  B64C27/20 ,  B64C39/024 ,  B64C39/028 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/165

Abstract: VTOL micro-aircraft comprising a first and a second ducted rotor mutually aligned and distanced according to a common axis and whose propellers are driven in rotation in mutually opposite directions. Between the two ducted rotors are positioned a fuselage and a wing system formed by wing profiles forming an X or an H configuration and provided with control flaps.

Abstract translation: VTOL微型飞机包括第一和第二导管转子，该第一和第二导管转子根据共同的轴线相互对准和间隔，并且其螺旋桨沿彼此相反的方向旋转驱动。 在两个管状转子之间设置有由机翼轮廓形成的机身和机翼系统，所述机翼轮廓形成X或H构造并设置有控制翼片。

公开(公告)号：US06857601B2

公开(公告)日：2005-02-22

申请号：US10189796

申请日：2002-07-03

Applicant: Yutaka Akahori

Inventor： Yutaka Akahori

IPC: B64B1/06 ,  B64C39/02 ,  B64F1/18 ,  G01S5/20 ,  G01S5/22 ,  G05D1/02 ,  G08G5/00 ,  B64B1/00

CPC classification number: G08G5/0052 ,  B64B1/06 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/042 ,  B64C2201/048 ,  B64C2201/101 ,  B64C2201/122 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/167 ,  B64F1/18 ,  G01S5/20 ,  G01S5/22 ,  G05D1/0202 ,  G08G5/00 ,  G08G5/0013

Abstract: An airship system according to the invention has an airship (110), a base station (120), and at least three measurement points. The airship (110) emits ultrasonic waves upon receiving an instruction from the base station (120). Measurement point units (S1-S3) receive the ultrasonic waves, and thereby measure distances from the airship (110) to the respective measurement points. An MPU that is incorporated in the base station (120) calculates a position of the airship (110). The base station (120) controls a route of the airship (110) based on the calculated position by sending a flight instruction to the airship (110). In this manner, an airship system can be provided that makes it unnecessary for an operator to pilot the airship and that can reduce the load weight and the power consumption of the airship.

Abstract translation: 根据本发明的飞艇系统具有飞艇（110），基站（120）和至少三个测量点。 飞艇（110）在接收到来自基站（120）的指令时发射超声波。 测量点单元（S1-S3）接收超声波，从而测量从飞艇（110）到相应测量点的距离。 并入基站（120）的MPU计算飞艇（110）的位置。 基站（120）通过向飞艇（110）发送飞行指令，基于计算出的位置来控制飞艇（110）的路线。 以这种方式，可以提供一种飞艇系统，使得飞行员不需要飞行飞艇，并且可以减少飞艇的负载重量和功率消耗。

公开(公告)号：US20040251377A1

公开(公告)日：2004-12-16

申请号：US10855275

申请日：2004-05-26

Inventor： Michael A. Dammar

IPC: B64C027/22

CPC classification number: 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

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20040232285A1

公开(公告)日：2004-11-25

申请号：US10877082

申请日：2004-06-25

Inventor： Yutaka Akahori

IPC: F41J009/08

CPC classification number: G08G5/0052 ,  B64B1/06 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/042 ,  B64C2201/048 ,  B64C2201/101 ,  B64C2201/122 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/167 ,  B64F1/18 ,  G01S5/20 ,  G01S5/22 ,  G05D1/0202 ,  G08G5/00 ,  G08G5/0013

Abstract: An airship system according to the invention has an airship (110), a base station (120), and at least three measurement points. The airship (110) emits ultrasonic waves upon receiving an instruction from the base station (120). Measurement point units (S1-S3) receive the ultrasonic waves, and thereby measure distances from the airship (110) to the respective measurement points. An MPU that is incorporated in the base station (120) calculates a position of the airship (110). The base station (120) controls a route of the airship (110) based on the calculated position by sending a flight instruction to the airship (110). In this manner, an airship system can be provided that makes it unnecessary for an operator to pilot the airship and that can reduce the load weight and the power consumption of the airship.

Abstract translation: 根据本发明的飞艇系统具有飞艇（110），基站（120）和至少三个测量点。 飞艇（110）在接收到来自基站（120）的指令时发射超声波。 测量点单元（S1-S3）接收超声波，从而测量从飞艇（110）到相应测量点的距离。 并入基站（120）的MPU计算飞艇（110）的位置。 基站（120）通过向飞艇（110）发送飞行指令，基于计算出的位置来控制飞艇（110）的路线。 以这种方式，可以提供一种飞艇系统，使得飞行员不需要飞行飞艇，并且可以降低飞艇的负载重量和功率消耗。

公开(公告)号：US20040135031A1

公开(公告)日：2004-07-15

申请号：US10341206

申请日：2003-01-13

Applicant: BoXaiR Engineering LLC.

Inventor： John S. Stupakis

IPC: B64C001/00

CPC classification number: B64C39/024 ,  B64C39/02 ,  B64C2201/048 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/165 ,  B64C2201/187 ,  B64C2211/00 ,  B64D2011/0046 ,  Y10S244/903

Abstract: A modular automated air transport system comprising an unmanned autonomous aircraft having a selectively detachable control systems portion and a structural air frame portion, wherein the structural air frame portion contains an interior cargo hold, aerodynamic members having control surfaces and at least one propulsion device attached to the structural air frame portion; and wherein the control system portion includes a control computer for autonomously controlling the flight of said air transport system from one known location to a second known location.

Abstract translation: 一种模块化的自动航空运输系统，包括具有可选择地可拆卸的控制系统部分和结构空气框架部分的无人自主飞行器，其中结构空气框架部分包含内部货舱，具有控制表面的空气动力部件和至少一个推进装置 结构空气框架部分; 并且其中所述控制系统部分包括用于自主地控制所述空中运输系统从一个已知位置到第二已知位置的飞行的控制计算机。

公开(公告)号：US06568635B2

公开(公告)日：2003-05-27

申请号：US09898631

申请日：2001-07-02

Applicant: Billy R. Carpenter

Inventor： Billy R. Carpenter

IPC: B64C2900

CPC classification number: B64C15/02 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/048 ,  B64C2201/22 ,  B64D27/02 ,  Y02T50/12 ,  Y02T50/44

Abstract: An apparatus and method for flight control of an aircraft provides a body with adjustable intake ports ducting air into an internal intake manifold. Adjusting the openings of the intake ports changes the amount of air flowing over the surfaces surrounding the intakes, changing the amount of lift created by those surfaces. The intake manifold feeds air to at least one engine, and an exhaust manifold communicates the exhaust of the engine to exhaust exit ports. The exhaust manifold contains a plurality of moveable components that direct exhaust within the exhaust manifold and to particular exhaust exit ports for producing various levels of force imbalance among the exit ports. A compressor powered by the engine provides air to bleed-air ports on the wings. Varying lift on the forward surfaces with the intake ports, vectored exhaust, and bleed air are used to control and stabilize the aircraft during flight, obviating the need for aerodynamic control surfaces.

Abstract translation: 用于飞机飞行控制的装置和方法为身体提供了将空气引导到内部进气歧管中的可调节进气口。 调整进气口的开口可改变在进气口周围的表面上流动的空气量，从而改变由这些表面产生的升力量。 进气歧管将空气供给至少一个发动机，并且排气歧管将发动机的排气与排气出口连通。 排气歧管包含多个可移动部件，其将排气歧管内的排气引导到特定排气出口，用于在出口之间产生不同程度的力不平衡。 由发动机供电的压缩机为机翼上的排气口提供空气。 使用进气口，向外排气和放气的前表面上的不同升力来控制和稳定飞行中的飞机，避免了空气动力学控制面的需要。

公开(公告)号：US06502787B1

公开(公告)日：2003-01-07

申请号：US10082814

申请日：2002-02-22

Applicant: Ronald Martin Barrett

Inventor： Ronald Martin Barrett

IPC: B64C2720

CPC classification number: B64C39/024 ,  A63H27/12 ,  B64C29/02 ,  B64C39/028 ,  B64C39/062 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/162

Abstract: A vertical take-off and landing miniature aerial vehicle includes an upper fuselage segment and a lower fuselage segment that extend in opposite directions from a rotor guard assembly. A rotor rotates within the rotor guard assembly between the fuselage segments. Plural turning vanes extend from the rotor guard assembly beneath the rotor. Moreover, plural grid fins extend radially from the lower fuselage segment below the turning vanes. The aerial vehicle is capable of taking off and landing vertically. During flight, the aerial vehicle can hover and transition between a horizontal flight mode and a vertical flight mode using the grid fins.

Abstract translation: 垂直起飞和着陆的微型飞行器包括从转子保护组件沿相反方向延伸的上部机身段和下部机身段。 转子保护组件内的转子在机身段之间旋转。 多个转向叶片从转子下方的转子保护组件延伸。 而且，多个格栅翅片从转向叶片下方的下部机身段径向延伸。 飞行器能够垂直起飞和着陆。 在飞行中，飞行器可以使用网格散热片在水平飞行模式和垂直飞行模式之间悬停和转换。

公开(公告)号：US20030001046A1

公开(公告)日：2003-01-02

申请号：US09898631

申请日：2001-07-02

Inventor： Billy R. Carpenter

IPC: B64C013/16

CPC classification number: B64C15/02 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/048 ,  B64C2201/22 ,  B64D27/02 ,  Y02T50/12 ,  Y02T50/44

Abstract: An apparatus and method for flight control of an aircraft provides a body with adjustable intake ports ducting air into an internal intake manifold. Adjusting the openings of the intake ports changes the amount of air flowing over the surfaces surrounding the intakes, changing the amount of lift created by those surfaces. The intake manifold feeds air to at least one engine, and an exhaust manifold communicates the exhaust of the engine to exhaust exit ports. The exhaust manifold contains a plurality of moveable components that direct exhaust within the exhaust manifold and to particular exhaust exit ports for producing various levels of force imbalance among the exit ports. A compressor powered by the engine provides air to bleed-air ports on the wings. Varying lift on the forward surfaces with the intake ports, vectored exhaust, and bleed air are used to control and stabilize the aircraft during flight, obviating the need for aerodynamic control surfaces

Abstract translation: 用于飞机飞行控制的装置和方法为身体提供了将空气引导到内部进气歧管中的可调节进气口。 调整进气口的开口可改变在进气口周围的表面上流动的空气量，从而改变由这些表面产生的升力量。 进气歧管将空气供给至少一个发动机，并且排气歧管将发动机的排气与排气出口连通。 排气歧管包含多个可移动部件，其将排气歧管内的排气引导到特定排气出口，用于在出口之间产生不同程度的力不平衡。 由发动机供电的压缩机为机翼上的排气口提供空气。 前进表面上带有进气口，向导排气和排气的不同升降机用于在飞行过程中控制和稳定飞机，避免了空气动力学控制面的需要

公开(公告)号：US20030001045A1

公开(公告)日：2003-01-02

申请号：US09895332

申请日：2001-07-02

Applicant: ELSE Ltd.

Inventor： Aharon Yifrach

IPC: B64C003/00

CPC classification number: B64C39/024 ,  B64C3/56 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/102 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/167 ,  B64C2201/201 ,  B64D5/00 ,  Y10S244/90 ,  Y10S244/901

Abstract: An unmanned flying vehicle comprises an autonomous flying wing having at least two wing portions arranged substantially symmetrically about a center portion. Each wing portion is pivotally attached to each adjoining portion such that the wing portions are foldable for storage and openable for deployment. A preferred form is the so-called seagull wing having four wing portions. The vehicles may be programmable from a mother aircraft whilst being borne to a deployment zone using a data link which may be wireless.

公开(公告)号：US20020092949A1

公开(公告)日：2002-07-18

申请号：US09761076

申请日：2001-01-17

Applicant: Lockheed Martin Corporation

Inventor： Leland M. Nicolai

IPC: B64C037/02 ,  B64D005/00 ,  B64C035/00

CPC classification number: B64C35/005 ,  B60V1/08 ,  B64C39/024 ,  B64C2201/048 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/167 ,  B64C2201/187

Abstract: An anti-submarine warfare system includes an unmanned nullsea-sittingnull aircraft housing submarine detecting equipment, the aircraft including a body portion having a catamaran configuration adapted for stably supporting the body portion when sitting in water, the body portion including a fuselage and laterally disposed sponsons connected to the fuselage via platforms, and submarine detecting equipment housed within the fuselage and adapted to be electronically linked to sonobuoys disposed in adjacent water locations.

Abstract translation: 一种反潜战系统包括一个无人“海坐”飞机舱潜艇检测设备，该飞机包括一个主体部分，该主体部分具有适于在坐在水中时稳定地支撑主体部分的双体船结构，该主体部分包括机身和横向 通过平台连接到机身的安装支架，以及容纳在机身内的潜艇检测设备，并且适于与设置在相邻水位的声波电子电子连接。