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1. 发明申请

US20040245378A1 Autonomous control method for a small, unmanned helicopter 审中-公开
公开(公告)号：US20040245378A1
公开(公告)日：2004-12-09
申请号：US10786051
申请日：2004-02-26
发明人： Kenzo Nonami , Jin Ok Shin , Daigo Fujiwara , Kensaku Hazawa , Keitaro Matsusaka
IPC分类号： B64C015/02
CPC分类号： G05D1/0033 , A63H27/12 , A63H30/04 , G05D1/0858
摘要： An objective of the present invention is to provide an autonomous control method that autonomously controls a small unmanned helicopter toward target values, such as a set position and velocity, by deriving model formulas that are well suited for the autonomous control of small unmanned helicopters, by designing an autonomous control algorithm based on the model formulas, and by calculating the autonomous control algorithm. The autonomous control system for a small unmanned helicopter of the present invention comprises: sensors that detect the current position, the attitude angle, the altitude relative to the ground, and the absolute azimuth of the nose of the aforementioned small unmanned helicopter; a primary computational unit that calculates optimal control reference values for driving the servo motors that move five rudders on the helicopter from target position or velocity values that are set by the ground station and the aforementioned current position and attitude angle of the small unmanned helicopter that are detected by the aforementioned sensors; an autonomous control system equipped with a secondary computational unit that converts the data collected by said sensors and the computational results as numeric values that are output by said primary computational unit into pulse signals that can be accepted by the servo motors, such that these components are assembled into a small frame box, thereby achieving both size and weight reductions; a ground station host computer that can also be used as the aforementioned computational unit for the aforementioned autonomous control system; if the aforementioned ground station host computer is used as the aforementioned computational unit for the aforementioned autonomous control system, in the process of directing the computational results that are output from said ground station host computer to said servo motors through a manual operation transmitter, a radio control generator that converts said computational results as numerical values into pulse signals that said manual operation transmitter can accept; a servo pulse mixing/switching apparatus, on all said servo motors for said small unmanned helicopter, that permits the switching of manual operation signals and said control signals that are output from said autonomous control system or mixing thereof in any ratio; an autonomous control algorithm wherein the mathematical model for transfer function representation encompassing pitching operation input through pitch axis attitude angles in the tri-axis orientation control for said small unmanned helicopter is defined as 1 G null null ( s ) = null - Ls null K null null null n null null null s 2 ( s 2 + 2 null null null  s null null s null s + null n null null null s 2 ) null ( T null null s + 1 ) null s such that the aforementioned small unmanned helicopter is controlled autonomously based on the aforementioned mathematical model;

2. 发明申请

US20030085319A1 VTOL personal aircraft 失效
标题翻译： VTOL个人飞机
公开(公告)号：US20030085319A1
公开(公告)日：2003-05-08
申请号：US10242036
申请日：2002-09-11
发明人： Joseph Wagner , Anthony Pruszenski JR. , Karl F. Milde JR.
IPC分类号： B64C015/02 , B64C029/00
CPC分类号： B64C3/56 , B64C27/20 , B64C29/0025 , Y02T50/14
摘要： A personal aircraft (PAC) capable of vertical take-off and landing (VTOL) comprises a fixed wing and a fuselage with a passenger compartment having a front, a rear and two sides, and a plurality of independently powered thrusters, preferably integrated into the wing, on each side of the fuselage. The aircraft has a lift to drag ratio equal to or greater than 2. The thrusters, which are ducted fan units capable of providing a vertically upward force to the aircraft, are provided with such redundancy that the aircraft can hover with at one thruster inoperative on each side of the fuselage. At least one thruster on each side of the fuselage preferably comprises a nulllevitatornull which creates lift from the airfoil-like air inlet as well as from the acceleration of air from inlet to outlet.
摘要翻译：能够垂直起飞和着陆（VTOL）的个人飞机（PAC）包括一个固定翼和一个具有前，后和两侧的乘客舱的机身，以及多个独立动力的推进器，最好集成到机翼，在机身的每一侧。飞机具有等于或大于2的提升阻力比。作为能够向飞行器提供垂直向上的力的导风扇单元的推进器具有这样的冗余度，即飞行器可以在一个推进器上无法操作机身的每一边。机体每一侧至少有一个推进器最好包括一个“升降机”，它从翼型空气入口以及空气从入口到出口的加速度产生升力。

3. 发明申请

US20040065772A1 High-lift, low-drag, stall-resistant airfoil 失效
标题翻译：高升力，低阻力，失速翼型
公开(公告)号：US20040065772A1
公开(公告)日：2004-04-08
申请号：US10370740
申请日：2003-02-21
发明人： Frank S. Malvestuto JR.
IPC分类号： B64C015/02 , B64C029/00
CPC分类号： B64C23/08 , B64C21/04 , B64C29/0025 , Y02T50/166
摘要： Method and apparatus embodiments of the present invention are disclosed wherein wing-rotor configurations provide aerodynamically high lift-low drag capabilities and improvements over the prior art including increasing effective stall angles. In addition, wing-rotor-propeller configurations provide aerodynamically high lift-low drag and forward thrust capabilities and improvements over the prior art for all vehicles moving through gaseous fluids and particular including application for air vehicles and watercraft. Also, wing leading edge air blowing systems augment the example configurations for enhanced performance including substantially vertical take-off and landing of air vehicles.
摘要翻译：公开了本发明的方法和装置实施例，其中翼 - 转子构造提供了空气动力学上的高提升 - 低牵引能力和相对于现有技术的改进，包括增加有效的失速角度。此外，机翼转子 - 螺旋桨配置提供了空气动力学上的高升降低阻力和向前推力能力，并且改进了现有技术对于所有移动通过气态流体的车辆，特别是包括用于空中车辆和船舶的应用。此外，机翼前缘吹风系统增加了用于增强性能的示例配置，包括基本垂直起飞和降落的空中客车。

4. 发明申请

US20040011923A1 Efficient wings 审中-公开
标题翻译：高效的翅膀
公开(公告)号：US20040011923A1
公开(公告)日：2004-01-22
申请号：US10156205
申请日：2002-07-22
发明人： John Daniel Romo
IPC分类号： B64C015/02 , B64C029/00
CPC分类号： B64C11/001 , B64C3/00 , B64C21/00 , B64C29/0025 , Y02T50/166
摘要： To obtain an augmented lift coefficient for a given airfoil set at a maximum angle of attack (null), in a steady state airflow system, a shrouded motorized propeller is installed normal to its upper side, creating additional airflow. An outlet for the additional airflow is provided including a horizontal motorized propeller placed at the trailing edge of the airfoil. The motorized propeller converts the additional air flow into a down-wash generating additional lift. Neither the first nor the second installation alone will produce the augmented lift efficiently. Therefore, the combination of the first and the second installation is needed. The propeller-wing arrangement is implement in the airfoils.
摘要翻译：为了获得在最大迎角（α）下的给定翼型组的增强升力系数，在稳态气流系统中，被覆盖的电动螺旋桨安装在其上侧，产生额外的气流。提供了用于附加气流的出口，包括放置在翼型的后缘处的水平电动螺旋桨。电动螺旋桨将额外的空气流转换成下洗生成附加升降机。单独的第一和第二安装不能有效地产生增强升力。因此，需要第一和第二安装的组合。螺旋桨翼结构在机翼中实现。

5. 发明申请

US20030062442A1 VTOL personal aircraft 审中-公开
标题翻译： VTOL个人飞机
公开(公告)号：US20030062442A1
公开(公告)日：2003-04-03
申请号：US09968934
申请日：2001-10-02
发明人： Karl F. Milde JR.
IPC分类号： B64C015/02 , B64C029/00
CPC分类号： B64C27/20 , B64C3/56 , B64C29/0025 , Y02T50/14
摘要： A personal aircraft (PAC) capable of vertical take-off and landing (VTOL) comprises a passenger compartment having a front, a rear and two sides, and a plurality of independently powered thrusters attached to the outer periphery of the compartment. At least three thrusters are disposed on each side of the compartment. The thrusters, which are preferably ducted fan units, are capable of providing a vertically upward force to the compartment.
摘要翻译：能够垂直起飞和着陆（VTOL）的个人飞机（PAC）包括具有前，后和两侧的乘客舱，以及附接到隔室的外周的多个独立动力的推进器。至少三个推进器设置在隔室的每一侧。推进器（其优选地是风扇式风扇单元）能够向隔室提供垂直向上的力。

6. 发明申请

US20040245374A1 VERTICAL TAKE-OFF AND LANDING AIRCRAFT 有权
标题翻译：垂直起落架和飞机
公开(公告)号：US20040245374A1
公开(公告)日：2004-12-09
申请号：US10746082
申请日：2003-12-26
发明人： Brian H. Morgan
IPC分类号： B64C015/02
CPC分类号： B64C29/0025 , B64C5/02
摘要： A vertical take-off and landing aircraft includes a fuselage, a left wing, a right wing, at least one forward thruster, a horizontal stabilizer and a vertical stabilizer. The left and right wings extend from substantially a middle of the fuselage on left and right sides, respectively. The at least one forward thruster is preferably mounted to the fuselage, substantially behind the left and right wings. The horizontal stabilizer extends from a rear of the fuselage. The vertical stabilizer extends from a top of the fuselage at a rear thereof. At least two left lift rotors are retained in the left wing and at least two right lift rotors are retained in the right wing. A second embodiment of the VTOL aircraft includes a fuselage truncated behind the left and right wings with a twin tail empennage.
摘要翻译：垂直起飞和着陆飞机包括机身，左翼，右翼，至少一个前推进器，水平稳定器和垂直稳定器。左翼和右翼分别从左侧和右侧的机身的大致中部延伸。至少一个前推进器优选地安装到机身，基本上在左翼和右翼后面。水平稳定器从机身后部延伸。垂直稳定器在机身的后部从机身的顶部延伸。至少两个左升降转子保留在左翼，至少两个右升降转子保持在右翼。垂直起落架飞机的第二个实施例包括在左翼和右翼后面截尾的机身，具有双尾尾翼。

7. 发明申请

US20030062443A1 VTOL personal aircraft 审中-公开
标题翻译： VTOL个人飞机
公开(公告)号：US20030062443A1
公开(公告)日：2003-04-03
申请号：US10114754
申请日：2002-04-02
发明人： Joseph Wagner , Anthony Pruszenski JR. , Karl F. Milde JR.
IPC分类号： B64C015/02 , B64C029/00
CPC分类号： B64C27/20 , B64C3/56 , B64C29/0025 , Y02T50/14
摘要： A personal aircraft (PAC) capable of vertical take-off and landing (VTOL) comprises a passenger compartment having a front, a rear and two sides, and a plurality of independently powered thrusters attached to the outer periphery of the compartment. At least two thrusters are disposed on each side of the compartment. The thrusters, which are preferably ducted fan units, are capable of providing a vertically upward force to the compartment. The thrusters preferably comprise a nullLevitatornull which creates lift from the airfoil-like air inlet as well as from the acceleration of air from inlet to outlet.
摘要翻译：能够垂直起飞和着陆（VTOL）的个人飞机（PAC）包括具有前，后和两侧的乘客舱，以及附接到隔室的外周的多个独立动力的推进器。至少两个推进器设置在隔室的每一侧。推进器（其优选地是风扇式风扇单元）能够向隔室提供垂直向上的力。推进器优选地包括“升液器”，其从翼型空气入口以及从入口到出口的空气加速度产生升力。

8. 发明申请

US20030006340A1 Aircraft 失效
标题翻译：飞机
公开(公告)号：US20030006340A1
公开(公告)日：2003-01-09
申请号：US10186665
申请日：2002-07-02
申请人： BAE SYSTEMS plc
发明人： Richard George Harrison , Terry Prendergast , Geoffrey Salkeld , Darren Holdcroft
IPC分类号： B64C015/02 , B64C029/00
CPC分类号： B64C39/024 , B64C29/0075 , B64C2201/086 , B64C2201/088 , B64C2201/102 , B64C2201/104 , B64C2201/121 , B64C2201/127 , B64C2201/128 , B64C2201/165 , B64C2201/187
摘要： An aircraft 1 comprising interchangeable wings 5 detachedly connected to a fuselage 3, each wing 5 containing the fuel and flight systems 13, 15 for engines 7 mounted to the wings 5, so that the fuselage 3 need contain no flight systems, simply a nullbusnull 23 for communication and the transfer of data between the wings.
摘要翻译：飞机1包括分离地连接到机身3的可互换翼5，每个翼5包含用于安装到翼5上的发动机7的燃料和飞行系统13,15，使得机身3不需要包含飞行系统，简单地是“总线 “23”用于沟通和传递数据之间的翅膀。

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