公开(公告)号：US06409122B1

公开(公告)日：2002-06-25

申请号：US09761076

申请日：2001-01-17

Applicant: Leland M. Nicolai

Inventor： Leland M. Nicolai

IPC: B64C3500

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 “sea-sitting” 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。

公开(公告)号：US06264140B1

公开(公告)日：2001-07-24

申请号：US09426042

申请日：1999-10-25

Applicant: Brian T. McGeer ,  Andreas H. von Flotow ,  Cory Roeseler ,  Clifford Jackson

Inventor： Brian T. McGeer ,  Andreas H. von Flotow ,  Cory Roeseler ,  Clifford Jackson

IPC: B64C2568

CPC classification number: B64C39/024 ,  B64C25/68 ,  B64C2201/104 ,  B64C2201/148 ,  B64C2201/182 ,  B64C2201/205 ,  B64F1/02

Abstract: A method and apparatus for retrieving an aircraft in a confined space involves hanging a cable, for example from a kite or mast, across the aircraft's flight path. The aircraft approaches the cable in steady forward flight, and may strike the cable at any point on the wing, fuselage, or other leading surface. The cable then slides along the airframe as the aircraft moves forward, until it is intercepted by a hook attached to the wing tip or other convenient location. The hook captures the cable, and prevents further sliding; the cable then pulls the aircraft to a stop. Compliance of the cable, optionally combined with compliance of the cable suspension, provides acceptably gradual deceleration. The aircraft is left suspended in mid-air, and is then winched or slid to the base of the cable or other convenient retrieval point. The cable suspension and other fixed objects can be kept well clear of the flight path, so that the aircraft can continue safely in the event that it misses the cable, and make another approach.

Abstract translation: 用于在密闭空间中检索飞行器的方法和装置涉及将诸如风筝或桅杆的电缆悬挂在飞机的飞行路径上。 飞机在稳定的前进飞行中接近电缆，并可能在机翼，机身或其他前导表面上的任何一点撞击电缆。 随着飞机向前移动，电缆随着机身滑动，直到被挂在翼尖或其他便利位置的钩子拦截。 钩子捕获电缆，并防止进一步滑动; 电缆然后拉飞机停下来。 电缆的符合性，可选地与电缆悬架的顺应性相结合，提供可接受的逐渐减速。 飞机悬挂在半空中，然后被绞盘或滑动到电缆的基座或其他方便的检索点。 电缆悬架和其他固定物体可以保持远离飞行路径，使飞机在错过电缆的情况下可以安全地继续，并进行另一种方法。

公开(公告)号：US5918832A

公开(公告)日：1999-07-06

申请号：US818582

申请日：1997-03-14

Applicant: Siegfried Hermann Zerweckh

Inventor： Siegfried Hermann Zerweckh

IPC: B64C3/38 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C3/38 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/187 ,  Y02T50/145

Abstract: An air vehicle defining a plane of symmetry includes a pair of outboard panels which are rotatably mounted on the lifting body of the vehicle and respectively extend in opposite directions from the plane of symmetry. A control system collectively rotates the outboard panels to selectively contribute forces from the panels to the lift on the air vehicle. The control system also differentially rotates the outboard panels to control roll of the air vehicle. A pair of empennage panels are also rotatably mounted on the lifting body to establish a dihedral angle centered on the plane of symmetry. The control system collectively rotates these empennage panels to control pitch, and differentially rotates the empennage panels to control yaw, of the air vehicle. In a high speed flight regime the lifting body alone is sufficient and the outboard panels are collectively rotated to reduce drag and contribute substantially zero lift. In a slow speed flight regime, the outboard panels are collectively rotated to contribute to the lift on the air vehicle.

Abstract translation: 限定对称平面的空中车辆包括一对舷外面板，其可旋转地安装在车辆的提升体上并且分别沿着对称平面的相反方向延伸。 控制系统共同地旋转外侧面板，以选择性地贡献从面板到机动车辆上的电梯的力。 控制系统还将外侧面板差分地旋转以控制空中车辆的滚动。 一对尾翼也可旋转地安装在提升体上，以建立以对称平面为中心的二面角。 控制系统将这些尾翼面板共同旋转以控制俯仰，并差速旋转尾翼面板以控制飞行器的偏航。 在高速飞行状态下，单独的提升体就足够了，并且外侧面板共同旋转以减少阻力并大体上提供零升力。 在慢速飞行状态下，外侧面板被集体旋转以对飞行器上的电梯做出贡献。

公开(公告)号：US5340057A

公开(公告)日：1994-08-23

申请号：US850913

申请日：1992-03-13

Applicant: Hugh Schmittle

Inventor： Hugh Schmittle

IPC: B64C3/38 ,  B64C29/00 ,  B64C29/02 ,  B64C39/02 ,  B64C39/04

CPC classification number: B64C39/024 ,  B64C29/0033 ,  B64C29/02 ,  B64C3/385 ,  B64C39/04 ,  B64C2201/044 ,  B64C2201/046 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64D2201/00

Abstract: The VTOL aircraft includes a free wing having wings on opposite sides of the fuselage connected to one another for joint free rotation and for differential pitch settings under pilot, computer or remote control. On vertical launch, pitch, yaw and roll control is effected by the elevators, rudder and the differential pitch settings of the wings, respectively. At launch, the elevator pitches the fuselage nose downwardly to alter the thrust vector and provide horizontal speed to the aircraft whereby the free wing freely rotates relative to the fuselage into a generally horizontal orientation to provide lift during horizontal flight. Transition from horizontal to vertical flight is achieved by the reverse process and tile aircraft may be gently recovered in or on a resilient surface such as a net.

Abstract translation: 垂直起落架飞机包括一个自由翼，在机身的相对两侧具有彼此连接的翼，用于联合自由旋转，并在飞行员，计算机或遥控器下进行差距俯仰设置。 在垂直发射时，俯仰，偏航和侧倾控制分别由电梯，方向舵和翼的差距俯仰设置来实现。 在发射时，升降机将机身鼻部向下倾斜以改变推力矢量并向飞行器提供水平速度，由此自由翼相对于机身自由旋转成大致水平的方向以在水平飞行期间提供升力。 从水平飞行到垂直飞行的过渡是通过相反的过程实现的，瓦片飞机可以在诸如网络的弹性表面中或其上轻轻地回收。

公开(公告)号：US4120468A

公开(公告)日：1978-10-17

申请号：US876576

申请日：1978-02-10

Applicant: Hans-Otto Fischer

Inventor： Hans-Otto Fischer

IPC: B64C39/02 ,  B64C39/06 ,  F41G7/20 ,  F42B15/00 ,  B64C3/12

CPC classification number: F41G7/20 ,  B64C39/024 ,  B64C39/06 ,  F42B15/00 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162

Abstract: The vehicle is constructed from a flat disc recessed in a slot in a thin, pencil-like fuselage having aft and front propulsion engines and mounted for rotating about the center of the disc and about an axis extending transversely to the disc and to the direction of extension of the fuselage.

Abstract translation: 该车辆由凹陷在具有尾部和前推进发动机的薄铅笔状机身的狭槽中的平盘构成，并且安装成围绕盘的中心旋转并围绕横向于盘延伸的轴线和 机身延伸。

公开(公告)号：US4032088A

公开(公告)日：1977-06-28

申请号：US675004

申请日：1976-04-08

Applicant: John Jerome McAvoy

Inventor： John Jerome McAvoy

IPC: B60V3/08 ,  B64C39/02 ,  B64C25/56

CPC classification number: B60V3/08 ,  B64C39/024 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/167 ,  B64C2201/187 ,  B64D2201/00

Abstract: An air bag landing system for an aircraft. The landing system has an air bag assembly which is stored in the fuselage of the aircraft during cruise and which extends for landing. The assembly consists of a rigid arm with either two or three folding portions and an inflatable bag attached to the underside of the arm. The inflatable bag cushions the impact of the aircraft at landing. Actuators are provided to extend and retract the assembly.

Abstract translation: 飞机的气囊着陆系统。 着陆系统具有气囊组件，其在巡航期间存储在飞行器的机身中并且延伸以着陆。 该组件包括具有两个或三个折叠部分的刚性臂和附接到臂的下侧的可充气袋。 充气袋缓冲飞机在着陆时的冲击。 提供致动器以延伸和缩回组件。

公开(公告)号：US20230339602A1

公开(公告)日：2023-10-26

申请号：US17727531

申请日：2022-04-22

Applicant: Baxter Aerospace LLC.

Inventor： Jeffrey Baxter ,  Michael Baxter

IPC: B64C11/44 ,  B64C39/02 ,  B64C29/02

CPC classification number: B64C11/44 ,  B64C39/024 ,  B64C29/02 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/104 ,  B64C2201/021

Abstract: An aircraft may include a body structure and a propulsion system coupled to the body structure and including a mounting shaft and a rotor. The rotor may include a rotor hub and a set of rotor blades, wherein the rotor is configured to orient the set of rotor blades at a first collective blade angle during a first flight mode and orient the set of rotor blades at a second collective blade angle during a second flight mode. The propulsion system may further include a motor coupled to the rotor and configured to rotate the rotor in a first rotational direction in the first flight mode to produce thrust in a first thrust direction and rotate the rotor in a second rotational direction opposite the first rotational direction in the second flight mode to produce thrust in a second thrust direction opposite the first thrust direction.

公开(公告)号：US20230192290A1

公开(公告)日：2023-06-22

申请号：US17554371

申请日：2021-12-17

Applicant: WING Aviation LLC

Inventor： Adam Woodworth ,  Giulia B. Pantalone ,  Luis Prado ,  Michelle Suen

IPC: B64C39/02 ,  B64C27/26 ,  B64C27/32 ,  B64C11/00 ,  B64C27/30 ,  B64C27/80 ,  G05D1/10

CPC classification number: B64C39/024 ,  B64C27/26 ,  B64C27/325 ,  B64C11/00 ,  B64C27/30 ,  B64C27/80 ,  G05D1/102 ,  B64C2201/02 ,  B64C2201/108 ,  B64C2201/104 ,  B64C2201/165

Abstract: An unmanned aerial vehicle (UAV) includes lift rotors and control rotors. The lift rotors are mounted to the UAV and oriented to provide a first vertical thrust to the UAV. The control rotors are mounted to the UAV outboard of the lift rotors and oriented to provide a second vertical thrust to the UAV. The control rotors are each smaller than any of the lift rotors.

公开(公告)号：US20230141493A1

公开(公告)日：2023-05-11

申请号：US17983384

申请日：2022-11-08

Applicant: Autoflight (Kunshan) Co., Ltd.

Inventor： Yu Tian

IPC: B64C39/02

CPC classification number: B64C39/024 ,  B64C2201/121 ,  B64C2201/104

Abstract: A device for unmanned aerial vehicle to deploy a rainfall catalytic bomb deploy which comprises an unmanned aerial vehicle, a cannonball for artificial precipitation and a cylinder, wherein the unmanned aerial vehicle is connected with the cannonball for artificial precipitation through a soft lock, the cannonball for artificial precipitation are multiple and are wrapped in the cylinder, a second sensor is arranged in the cylinder wing surfaces are arranged on the other side of the cylinder, the wing surfaces are multiple and are arranged at one end of the cylinder in the long shaft direction, and one end of the soft lock is connected to the other end of the cylinder in the long shaft direction.

公开(公告)号：US20190112045A1

公开(公告)日：2019-04-18

申请号：US15851672

申请日：2017-12-21

Applicant: Hanhui ZHANG

Inventor： Hanhui ZHANG

IPC: B64C39/02

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/12 ,  B64C2201/182

Abstract: A drone capture aerial vehicle includes a fuselage and a drone capture device. The drone capture device includes a middle post and a plurality of foldable frame arms; the middle post includes a first end and a second end; and each foldable frame arm includes a plurality of ribs and a plurality of links. A method of capturing a drone includes providing a drone capture aerial vehicle, the drone capture aerial vehicle having a drone capture device and the drone capture device having a foldable capture net; flying the drone capture aerial vehicle toward the drone; activating the drone capture device to deploy the foldable capture net; and capturing the drone with the capture net.