公开(公告)号：US09540101B2

公开(公告)日：2017-01-10

申请号：US14507198

申请日：2014-10-06

Applicant: Aurora Flight Sciences Corporation

Inventor： James Donald Paduano ,  Paul Nils Dahlstrand ,  John Brooke Wissler ,  Adam Woodworth

IPC: B64C27/52 ,  B64C29/04 ,  B64C29/02 ,  B64C39/02 ,  B64C29/00 ,  B64C3/42 ,  B64C5/02 ,  B64C9/00 ,  B64C25/10 ,  B64D27/02 ,  B64D43/00

CPC classification number: B64C27/52 ,  B64C3/42 ,  B64C5/02 ,  B64C9/00 ,  B64C13/16 ,  B64C25/10 ,  B64C29/00 ,  B64C29/0033 ,  B64C29/0091 ,  B64C29/02 ,  B64C29/04 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/162 ,  B64C2201/187 ,  B64D27/02 ,  B64D43/00

Abstract: A vertical take-off and landing (VTOL) aircraft according to an aspect of the present invention comprises a fuselage, an empennage having an all-moving horizontal stabilizer located at a tail end of the fuselage, a wing having the fuselage positioned approximately halfway between the distal ends of the wing, wherein the wing is configured to transform between a substantially straight wing configuration and a canted wing configuration using a canted hinge located on each side of the fuselage. The VTOL aircraft may further includes one or more retractable pogo supports, wherein a retractable pogo support is configured to deploy from each of the wing's distal ends.

Abstract translation: 根据本发明的一个方面的垂直起飞（VTOL）飞机包括机身，具有位于机身尾端的全移动水平稳定器的尾翼，机身具有位于机身的大致中间位置 翼的远端​​，其中翼被配置成使用位于机身的每一侧上的倾斜铰链在基本上直的机翼构型和倾斜翼结构之间转换。 垂直起落飞行器还可以包括一个或多个可伸缩的弹簧支撑件，其中可伸缩的弹簧支撑构造成从翼的远端中的每一个展开。

公开(公告)号：US20160311530A1

公开(公告)日：2016-10-27

申请号：US15204547

申请日：2016-07-07

Applicant: Frick A. Smith

Inventor： Frick A. Smith

IPC: B64C29/00 ,  B64C27/28 ,  B64D31/00 ,  B64C39/02 ,  B64C27/82 ,  B64D17/64 ,  B64D17/80 ,  B64D27/02 ,  B64C1/14 ,  B64C27/52 ,  B64C27/26 ,  B64D17/24

CPC classification number: B64C29/0033 ,  B64C1/1415 ,  B64C1/1476 ,  B64C27/22 ,  B64C27/26 ,  B64C27/28 ,  B64C27/52 ,  B64C27/82 ,  B64C29/00 ,  B64C29/0016 ,  B64C39/02 ,  B64C39/024 ,  B64C2201/04 ,  B64C2201/088 ,  B64C2201/10 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162 ,  B64D17/24 ,  B64D17/34 ,  B64D17/62 ,  B64D17/64 ,  B64D17/80 ,  B64D27/02 ,  B64D31/00 ,  B64D35/04

Abstract: An aircraft may have a fuselage, a left wing extending from the fuselage, a right wing extending from the fuselage, a tail section extending from a rear portion of the fuselage, and a first engine and a second engine operably connected by a common driveshaft, wherein the first and second engines are configured for freewheeling such that if one of the first and second engines loses power the other of the first and second engines continues to power the aircraft.

Abstract translation: 飞机可以具有机身，从机身延伸的左翼，从机身延伸的右翼，从机身的后部延伸的尾部，以及通过共同的驱动轴可操作地连接的第一发动机和第二发动机， 其中所述第一和第二发动机被配置为自由转动，使得如果所述第一和第二发动机中的一个发动机失去动力，则所述第一和第二发动机中的另一个继续为所述飞行器供电。

公开(公告)号：US09475579B2

公开(公告)日：2016-10-25

申请号：US14121001

申请日：2014-08-13

Applicant: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration

Inventor： William J. Fredericks ,  Mark D. Moore ,  Ronald C. Busan ,  Paul M. Rothhaar ,  David D. North ,  William M. Langford ,  Christopher T. Laws ,  William T. Hodges ,  Zachary R. Johns ,  Sandy R. Webb

IPC: B64D27/24 ,  B64D27/26 ,  B64C29/00 ,  B64C3/40 ,  B64C9/14 ,  B64C11/50 ,  B64C25/32 ,  B64C3/38 ,  B64C39/02 ,  B64D27/02

CPC classification number: B64C29/0033 ,  B64C3/385 ,  B64C3/40 ,  B64C5/02 ,  B64C9/14 ,  B64C11/28 ,  B64C11/50 ,  B64C25/32 ,  B64C25/52 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165 ,  B64D27/24 ,  B64D27/26 ,  B64D2027/026 ,  Y02T50/44 ,  Y02T50/64 ,  Y10S903/903

Abstract: Systems, methods, and devices are provided that combine an advance vehicle configuration, such as an advanced aircraft configuration, with the infusion of electric propulsion, thereby enabling a four times increase in range and endurance while maintaining a full vertical takeoff and landing (“VTOL”) and hover capability for the vehicle. Embodiments may provide vehicles with both VTOL and cruise efficient capabilities without the use of ground infrastructure. An embodiment vehicle may comprise a wing configured to tilt through a range of motion, a first series of electric motors coupled to the wing and each configured to drive an associated wing propeller, a tail configured to tilt through the range of motion, a second series of electric motors coupled to the tail and each configured to drive an associated tail propeller, and an electric propulsion system connected to the first series of electric motors and the second series of electric motors.

Abstract translation: 提供了系统，方法和装置，其将先进的车辆配置（例如先进的飞行器配置）与电力推进的输注结合在一起，从而能够在保持完全垂直起飞和着陆的同时保持四倍的范围和耐力增加（“VTOL “）和车辆的悬停能力。 实施例可以提供具有垂直起落架和巡航高效能力的车辆，而不使用地面基础设施。 一种实施方式的车辆可以包括被配置为倾斜运动范围的翼，连接到翼的第一系列电动马达，并且每个被配置成驱动相关翼翼推进器，构造成在所述运动范围内倾斜的尾部，第二系列 耦合到尾部并且每个被配置为驱动相关联的尾部螺旋桨的电动马达以及连接到第一系列电动机和第二系列电动机的电推进系统。

公开(公告)号：US09457900B1

公开(公告)日：2016-10-04

申请号：US15073831

申请日：2016-03-18

Applicant: The United States of America, as represented by the Secretary of the Navy

Inventor： Kevin D. Jones ,  Vladmir N. Dobrokhodov

IPC: B64G1/00 ,  B64C39/02 ,  B64C27/08 ,  B64C25/54 ,  B63B22/00

CPC classification number: B64C39/02 ,  B63B22/00 ,  B64C25/54 ,  B64C27/08 ,  B64C37/00 ,  B64C39/022 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/12 ,  B64C2201/122 ,  B64C2201/143 ,  B64C2201/18

Abstract: A multirotor mobile buoy combining MR-VTOL capability with environmentally hardened electronics, exchangeable sensor suites, and a solar recharge system and providing sensing in aquatic environments. The multirotor mobile buoy provides for the detection, classification and location of underwater objects using self-contained electronics, and repositions with aerial means using a plurality of rotors. The multirotor mobile buoy additionally incorporates solar panels for recharging of on-board batteries enabling the flight and other functions, and comprises a buoyant assembly and extended tether in order to promote stability in dynamic, open ocean environments. The multirotor mobile buoy may be employed singly or as a swarm of underwater detection platforms, and may utilize its positioning ability to optimize the effectiveness of sonobuoy systems arrayed as a distributed sensor field.

Abstract translation: 将MR-VTOL功能与环境恶化的电子设备，可更换传感器套件和太阳能充电系统相结合的多旋转移动浮标，并在水环境中提供感测。 多转轮移动浮标提供使用独立电子设备的水下物体的检测，分类和定位，以及使用多个转子重新定位与天线装置。 多转轮移动浮标还包括用于为板载电池充电以实现飞行和其他功能的太阳能电池板，并且包括浮力组件和延伸系绳，以促进在动态，开阔的海洋环境中的稳定性。 多旋转移动浮标可以单独使用或作为一群水下检测平台使用，并且可以利用其定位能力来优化作为分布式传感器场排列的声波系统的有效性。

公开(公告)号：US20160090179A1

公开(公告)日：2016-03-31

申请号：US14500691

申请日：2014-09-29

Applicant: The Boeing Company

Inventor： Jamie J. Childress ,  Daniel J. Perron

IPC: B64C29/00 ,  B64C39/02

CPC classification number: B64C29/0091 ,  B64C39/024 ,  B64C2201/088

Abstract: Described herein is an aircraft launch system that includes a riser coupleable to an aircraft. The riser includes an actuator and a tether coupled to the actuator. The aircraft launch system further includes a sky anchor coupled to the tether. The actuator is operable to retract the tether and draw together the sky anchor and the aircraft.

Abstract translation: 这里描述的是包括可与飞机相连的提升板的飞行器发射系统。 提升管包括联接到致动器的致动器和系绳。 飞机发射系统还包括耦合到系绳的天空锚。 致动器可操作以缩回系绳并将天空锚和飞机拉在一起。

公开(公告)号：US20150336666A1

公开(公告)日：2015-11-26

申请号：US14507198

申请日：2014-10-06

Applicant: Aurora Flight Sciences Corporation

Inventor： JAMES DONALD PADUANO ,  PAUL NILS DAHLSTRAND ,  JOHN BROOKE WISSLER ,  ADAM WOODWORTH

IPC: B64C29/04

CPC classification number: B64C27/52 ,  B64C3/42 ,  B64C5/02 ,  B64C9/00 ,  B64C13/16 ,  B64C25/10 ,  B64C29/00 ,  B64C29/0033 ,  B64C29/0091 ,  B64C29/02 ,  B64C29/04 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/162 ,  B64C2201/187 ,  B64D27/02 ,  B64D43/00

Abstract: A vertical take-off and landing (VTOL) aircraft according to an aspect of the present invention comprises a fuselage, an empennage having an all-moving horizontal stabilizer located at a tail end of the fuselage, a wing having the fuselage positioned approximately halfway between the distal ends of the wing, wherein the wing is configured to transform between a substantially straight wing configuration and a canted wing configuration using a canted hinge located on each side of the fuselage. The VTOL aircraft may further includes one or more retractable pogo supports, wherein a retractable pogo support is configured to deploy from each of the wing's distal ends.

公开(公告)号：US20150285165A1

公开(公告)日：2015-10-08

申请号：US14439502

申请日：2013-10-22

Applicant: EADS DEUTSCHLAND GMBH

Inventor： Juergen Steinwandel ,  Florian Stagliano ,  Jan Van Toor

IPC: F02D29/02 ,  B64D27/02 ,  B64C39/02 ,  B64D31/00 ,  B64D41/00

CPC classification number: F02D29/02 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/066 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/16 ,  B64D27/02 ,  B64D27/24 ,  B64D31/00 ,  B64D41/00 ,  B64D2027/026 ,  Y02T50/44 ,  Y02T50/64

Abstract: An unmanned aircraft includes a propulsion system having a diesel or kerosene internal combustion engine and a charger device for engine charging. The propulsion system can be a hybrid propulsion system or a parallel hybrid propulsion system.

Abstract translation: 无人机包括具有柴油或煤油内燃机的推进系统和用于发动机充气的充电装置。 推进系统可以是混合推进系统或并联混合推进系统。

公开(公告)号：US09145207B2

公开(公告)日：2015-09-29

申请号：US14008707

申请日：2012-03-27

Applicant: Jean-Marc Moschetta ,  Chinnapat Thipyopas

Inventor： Jean-Marc Moschetta ,  Chinnapat Thipyopas

IPC: B64C39/02 ,  B64C25/36 ,  B64D45/06

CPC classification number: B64C39/028 ,  B64C25/36 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/126 ,  B64C2201/165 ,  B64C2201/18 ,  B64D45/06

Abstract: An aerial micro-drone having a fixed wing supporting a propulsion device. The micro-drone has wheels for traveling on the ground, which are attached to the side ends of a section of the wing. The rotational axis Y1 of the wheels is located in front of the center of gravity of the micro-drone. The center of gravity of the micro-drone is located in front of the aerodynamic center of the micro-drone. The rotational axis Y1 of the wheels being aligned with the thrust axis of the propulsion device and the wheels are sized such that the radius D/2 thereof is greater than the distance between the rotational axis Y1 of the wheels and the trailing edge of the wing.

Abstract translation: 一种具有支撑推进装置的固定翼的空中微型无人机。 微型无人机具有用于在地面上行进的轮子，其附接到机翼的一部分的侧端。 车轮的旋转轴线Y1位于微型无人机的重心的前方。 微型无人机的重心位于微型无人机的空气动力学中心前方。 车轮的旋转轴线Y1与推进装置的推力轴线对准，车轮的尺寸使其半径D / 2大于车轮的旋转轴线Y1和机翼的后缘之间的距离 。

公开(公告)号：US20150266575A1

公开(公告)日：2015-09-24

申请号：US14222158

申请日：2014-03-21

Applicant: Brandon Borko

Inventor： Brandon Borko

IPC: B64C39/02 ,  B64F1/12 ,  G05D1/10 ,  B64F1/02

CPC classification number: B64C39/024 ,  B64C2201/024 ,  B64C2201/088 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/182 ,  B64C2201/20 ,  B64C2201/205 ,  B64F1/02 ,  B64F1/06 ,  B64F1/12 ,  B64F1/222 ,  G05D1/101

Abstract: A system for facilitating automated landing and takeoff of an autonomous or pilot controlled hovering air vehicle with a cooperative underbody at a stationary or mobile landing place and an automated storage system used in conjunction with the landing and takeoff mechanism that stores and services a plurality of UAVs is described. The system is primarily characterized in that the landing mechanism is settable with 6 axes in roll, pitch, yaw, and x, y and z and becomes aligned with and intercepts the air vehicle in flight and decelerates the vehicle with respect to vehicle's inertial limits. The air vehicle and capture mechanism are provided with a transmitter and receiver to coordinate vehicle priority and distance and angles between landing mechanism and air vehicle. The landing and takeoff system has means of tracking the position and orientation of the UAV in real time. The landing mechanism will be substantially aligned to the base of the air vehicle. With small UAVs, their lifting capacity is limited. Reducing sensing and computation requirements by having the landing plate perform the precision adjustments for the landing operation allows for increased flight time and/or payload capacity.

Abstract translation: 一种用于促进自主着陆和起飞的自动着陆和起飞的系统，其具有在固定或移动着陆地点的协作车身，以及与着陆和起飞机构结合使用的自动存储系统，其存储和服务多个UAV 被描述。 该系统的主要特征在于，着陆机构可设置为具有卷轴，俯仰，偏航以及x，y和z的6个轴线，并与飞行中的空中车辆对准并截取，并相对于车辆的惯性极限使车辆减速。 飞行器和捕获机构设置有发射器和接收器，以协调车辆优先级，着陆机构和机动车辆之间的距离和角度。 着陆和起飞系统具有实时跟踪无人机的位置和方向的方法。 着陆机构将基本上与机动车辆的底座对准。 对于小型无人机，起重能力有限。 通过使着陆板执行着陆操作的精确调整来减少感测和计算要求，可以增加飞行时间和/或有效载荷。

公开(公告)号：US20150225071A1

公开(公告)日：2015-08-13

申请号：US14176960

申请日：2014-02-10

Applicant: Northrop Grumman Systems Corporation

Inventor： Thomas S. Tighe

IPC: B64C3/32 ,  B64C3/38 ,  B64C29/00

CPC classification number: B64C39/024 ,  B64C29/02 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162

Abstract: A multi-engine aircraft is disclosed which is convertible from horizontal flight mode to a vertical flight mode. The aircraft comprises an aircraft fuselage defining a fuselage longitudinal axis, and the first and second wing attached to the fuselage. Each wing defines first and second wing segments. The first segments are translatable about the fuselage longitudinal axis, from a horizontal mode position adjacent the second wing segments to vertical fight mode wherein the first wing segment are substantially offset from the second wing segments. An aircraft propulsion unit is attached to each of the first and second wing segments. The propulsion units attached to a common wing being disposed in substantial axial alignment when the aircraft operates in a horizontal flight mode, and being substantially offset when the aircraft operates in a vertical flight mode. A senor unit is connected to a forward portion of the fuselage.

Abstract translation: 公开了一种可从水平飞行模式转换为垂直飞行模式的多引擎飞机。 该飞机包括一个定义机身纵向轴线的飞机机身，以及连接到机身的第一和第二翼。 每个翼限定第一和第二翼段。 第一段可绕机身纵向轴线平移，从邻近第二翼段的水平模式位置到垂直起搏模式，其中第一翼段基本上偏离第二翼段。 飞机推进单元附接到第一和第二翼段中的每一个。 当飞机以水平飞行模式操作时，连接到共同翼的推进单元被布置成基本上轴向对准，并且当飞机以垂直飞行模式操作时基本上偏移。 传感器单元连接到机身的前部。