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公开(公告)号：US11814151B2
公开(公告)日：2023-11-14
申请号：US17828455
申请日：2022-05-31
Applicant: URBAN SKY
Inventor： Jared Leidich , Andrew F. Antonio , Mitch Sweeney , Daniel W. McFatter , Maxmillion James West McLaughlin
Abstract: An example reusable high-altitude balloon system includes a balloon with a first end supporting a payload and a second end with an aperture and an apex fitting that is positioned within the aperture. A clamp applies a pressure to a plurality of pleated folds formed in the perimeter of the aperture around the apex fitting to form an air-tight seal against the balloon at the perimeter of the aperture. The reusable high-altitude balloon system further includes control circuitry that controllably releases the apex fitting from the balloon to initiate a descent sequence.
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公开(公告)号：US20180067499A1
公开(公告)日：2018-03-08
申请号：US15802869
申请日：2017-11-03
Applicant: X Development LLC
Inventor： Keith Allen Bonawitz , Johan Mathe
CPC classification number: B64B1/40 , B64B1/44 , B64B1/60 , G01W1/00 , G01W1/08 , G05D1/104 , G05D1/105 , G08G5/0013 , G08G5/0026 , G08G5/0039 , G08G5/0069 , G08G5/0082 , G08G5/0091
Abstract: Example implementations may relate to selection between a first mode and a second mode. The first mode may involve (i) directing an aerial vehicle (e.g., in an aerial network including a plurality of aerial vehicles) to navigate to each of a plurality of altitudes and (ii) determining respective wind-related data at each respective altitude. Whereas, the second mode may involve (i) selecting at least one altitude based on the determined wind-related data and (ii) directing the aerial vehicle to reposition to the at least one selected altitude. As such, a control system may determine flight data for the aerial vehicle. Based on the flight data, the control system may make a selection between the first mode and the second mode. And based on the selection, the control system may then operate the aerial vehicle according to the first mode or may operate the aerial vehicle according to the second mode.
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公开(公告)号：US20170369160A1
公开(公告)日：2017-12-28
申请号：US15629377
申请日：2017-06-21
Applicant: Sikorsky Aircraft Corporation
Inventor： Matthew A. White , Matthew T. Luszcz , Kevin L. Bredenbeck , William C. Fell, JR.
CPC classification number: B64C27/025 , B64C27/006 , B64C27/12 , B64C27/57 , B64D45/00 , B64D45/06 , B64D2045/0085 , G05D1/0858 , G05D1/105
Abstract: A method of automating entry of an aircraft into autorotation includes detecting a loss of engine power, analyzing a sensed height and sensed airspeed of the aircraft, determining an adjusted position of one or more control surfaces of the aircraft in response to the sensed height and sensed airspeed, and automatically moving the one or more control surfaces to the adjusted position.
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公开(公告)号：US09639087B1
公开(公告)日：2017-05-02
申请号：US15371045
申请日：2016-12-06
Applicant: Kitty Hawk Corporation
Inventor： Mark Johnson Cutler
CPC classification number: G08G5/025 , B64C27/08 , B64C27/12 , B64C39/028 , B64C2201/141 , B64C2201/18 , B64D25/00 , B64D45/04 , B64D2045/008 , G05D1/0055 , G05D1/0088 , G05D1/0676 , G05D1/105 , G08G5/0039 , G08G5/0056 , G08G5/0069 , G08G5/0086 , G08G5/02
Abstract: An emergency landing procedure that includes a sequence of control settings is continuously generated. An aircraft is landed, including by using the sequence of control settings and a set of one or more inertial sensors to control an actuator.
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公开(公告)号：US09551990B2
公开(公告)日：2017-01-24
申请号：US14660145
申请日：2015-03-17
Applicant: Sharper Shape Oy
Inventor： Tero Heinonen
CPC classification number: G05D1/0011 , B64C39/024 , B64C2201/128 , B64D1/08 , B64D17/80 , G05D1/101 , G05D1/105 , G08G5/0056
Abstract: The present disclosure provides an unmanned flying vehicle (UAV) operable in a plurality of operating modes including a normal operations mode, a safe landing mode and an emergency landing mode. The normal operations mode is initiated when no errors are detected in the system. The safe landing mode is initiated when one or more non-critical components of the UAV are in non-responsive mode or do not work as desired. The emergency landing mode is initiated when one or more critical components are in non-responsive mode or do not work as desired. Further, the safe landing mode overrides the normal operations mode and the emergency landing mode overrides both the normal operations mode and the safe landing mode.
Abstract translation: 本公开提供了一种可操作于包括正常操作模式，安全着陆模式和紧急着陆模式的多种操作模式的无人驾驶飞行器（UAV）。 当系统中没有检测到错误时，启动正常操作模式。 当UAV的一个或多个非关键部件处于非响应模式或不按需要工作时，开始安全着陆模式。 当一个或多个关键组件处于非响应模式或不按需要工作时，启动紧急着陆模式。 此外，安全着陆模式覆盖正常操作模式，并且紧急着陆模式覆盖正常操作模式和安全着陆模式。
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公开(公告)号：US20160378121A1
公开(公告)日：2016-12-29
申请号：US14750746
申请日：2015-06-25
Applicant: Bell Helicopter Textron Inc.
Inventor： ShyhPyng Jack Shue
CPC classification number: G05D1/105 , G05D1/0072 , G05D1/0676 , G05D1/102 , G08G5/0013 , G08G5/0034 , G08G5/025
Abstract: Methods, systems, and apparatus, including computer programs encoded on a computer storage medium, for landing aircrafts with optimal landing spot selection. In one aspect, a method includes initiating an autorotation of an aircraft in response to detecting all engine failure, determining a plurality of flight characteristics and conditions of the aircraft at a time of initiating the autorotation, the plurality of flight characteristics and conditions comprising an aircraft altitude, an aircraft velocity, and wind direction, determining total air-time for glideslope and flare control, and a geographic area within which to land the aircraft by autorotation based on the plurality of flight characteristics and conditions, and controlling the aircraft to land the aircraft by autorotation within the geographic area.
Abstract translation: 方法，系统和装置，包括在计算机存储介质上编码的计算机程序，用于着陆具有最佳着陆点选择的飞机。 在一个方面，一种方法包括响应于检测到所有发动机故障，确定在启动自转时的飞行器的多个飞行特性和状况，启动航空器的自动转换，所述飞行特征和条件包括飞行器 高度，飞机速度和风向，确定滑坡和火炬控制的总时间，以及基于多个飞行特征和条件通过自转落地飞机的地理区域，并且控制飞机着陆 飞机在地理区域内自转。
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7.发明授权
公开(公告)号：US09508265B2
公开(公告)日：2016-11-29
申请号：US14340018
申请日：2014-07-24
Applicant: THE CHARLES STARK DRAPER LABORATORY, INC.
Inventor： Benjamin S. Chiel , Christopher Walden Dever
CPC classification number: G08G5/0091 , B64D17/025 , B64D17/34 , G01C21/20 , G05D1/105 , G08G5/0021 , G08G5/0069 , G08G5/025
Abstract: According to one aspect, a flight controller constructed to control a parafoil in flight from a starting location to a target location is provided. The flight controller includes an interface constructed to connect to one or more actuators and one or more wind sensors, a memory, a processor coupled to the memory, the interface, and a flight manager component executable by the processor. The flight manager component is configured to identify the target location and the starting location, receive wind data, determine a relationship between a ground reference frame (GRF) and a wind fixed frame (WFF) based on the wind data, generate a trajectory between the starting location and the target location in the WFF, determine a desired heading based on the trajectory and the relationship between the GRF and the WFF, and generate an actuator control signal based on the desired heading to adjust a heading of the parafoil.
Abstract translation: 根据一个方面，提供一种飞行控制器，其被构造成控制从起始位置到目标位置的飞行中的翼型飞行器。 飞行控制器包括被构造成连接到一个或多个致动器和一个或多个风传感器，存储器，耦合到存储器的处理器，接口和由处理器可执行的飞行管理器部件的接口。 飞行管理器组件被配置为基于风数据来识别目标位置和起始位置，接收风数据，确定地面参考帧（GRF）和风固定帧（WFF）之间的关系， 开始位置和WFF中的目标位置，基于轨迹和GRF和WFF之间的关系来确定期望的航向，并且基于期望的航向产生致动器控制信号，以调节翼型石油的航向。
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8.发明申请
公开(公告)号：US20160266582A1
公开(公告)日：2016-09-15
申请号：US14989033
申请日：2016-01-06
Applicant: The Charles Stark Draper Laboratory, Inc.
Inventor： David W. Carter , Scott A. Rasmussen
CPC classification number: G05D1/12 , G01C23/00 , G05D1/0676 , G05D1/105
Abstract: A guidance, navigation and control (GNC) system guides an aircraft based on a special partial differential equation (PDE). The system does not depend on a predetermined desired flight path. To overcome effects of unpredictable wind speed and direction, systems and methods effectively repeatedly determine the worst landing the wind can cause and issue flight control commands that minimize among these worst outcomes. A function C that satisfies the PDE calculates smallest miss distance a guidance system can bring about by appropriately steering an aircraft, given the aircraft's current heading, current location relative to a target and current remaining amount of time to fly. The system repeatedly determines at least a component of a current gradient of the function C. A value of the gradient component is used to select an appropriate flight control command, such as turn left or turn right.
Abstract translation: 指导，导航和控制（GNC）系统基于特殊偏微分方程（PDE）来指导飞机。 系统不依赖于预定的期望飞行路径。 为了克服不可预测的风速和方向的影响，系统和方法有效反复地确定了风能导致的最差降落，并发出了最差的最终结果。 满足PDE的功能C通过适当地指导飞机，给定飞机的当前航向，相对于目标的当前位置和当前剩余飞行时间，计算引导系统可以带来的最小未命中距离。 系统重复地确定功能C的当前梯度的至少一个分量。梯度分量的值用于选择适当的飞行控制命令，例如左转或右转。
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9.发明申请
公开(公告)号：US20160023757A1
公开(公告)日：2016-01-28
申请号：US14872600
申请日：2015-10-01
Applicant: Bell Helicopter Textron Inc.
IPC: B64C27/57 , B64C27/605 , B64C27/32
CPC classification number: B64C27/57 , B64C27/006 , B64C27/04 , B64C27/32 , B64C27/605 , G05D1/0858 , G05D1/105
Abstract: The system is configured for automation of rotorcraft entry into autorotation. The system can provide a means to assist the flight crew of a rotorcraft in maintaining rotor speed following loss of engine power. The system can automatically adjust control positions, actuator positions or both to prevent excessive loss of rotor speed upon initial loss of engine power before the flight crew is able to react. The system uses model matching to provide axis decoupling and yaw anticipation; it includes pitch control initially to assist in preventing rotor deceleration; and it makes use of collective, pitch, roll and yaw trim functions to provide tactile cueing to the pilot to assist when the pilot is in the loop. The system can reduce workload by assisting the crew with controlling rotor speed and forward speed during stabilized autorotation.
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10.发明授权
公开(公告)号：US09195938B1
公开(公告)日：2015-11-24
申请号：US13727688
申请日：2012-12-27
Applicant: Keith Allen Bonawitz , Bradley Rhodes , Adrien Treuille
Inventor： Keith Allen Bonawitz , Bradley Rhodes , Adrien Treuille
IPC: G08G1/0967 , G08G1/0968 , G06N5/02 , G08G1/00 , G08G1/123 , G06Q10/04 , G08G1/01
CPC classification number: G08G5/0095 , B64B1/00 , G05D1/104 , G05D1/105 , G06N5/02 , G06Q10/04 , G06Q10/047 , G06Q50/30 , G08G1/00 , G08G1/0104 , G08G1/0967 , G08G1/0968 , G08G1/096855 , G08G1/123 , G08G1/20 , G08G5/0008 , G08G5/0013
Abstract: Example methods and systems for determining when to launch vehicles into a fleet of autonomous vehicles are described. A method comprises receiving a sequence of coverage requirements for a region over a period of time. The region may be characterized by landmarks and the period of time can be divided into time intervals. The method also includes defining a landmark as a launch site representative of a landmark at which a given vehicle can be added to a plurality of operating vehicles, and determining for a respective landmark, estimated landmarks that can be reached by a vehicle starting from the respective landmark by an end of a time interval. The method also includes based on the sequence of coverage requirements and the estimated landmarks, determining a given launch site and corresponding time interval at which to add the given vehicle to the plurality of operating vehicles.
Abstract translation: 描述了用于确定何时将车辆运送到自主车辆的车队中的示例性方法和系统。 一种方法包括在一段时间内接收一个区域的覆盖要求序列。 该地区可能以地标为特征，时间段可分为时间间隔。 该方法还包括将地标定义为代表能够将给定车辆添加到多个操作车辆的地标的发射场地，以及针对相应地标确定车辆可以从相应的地面开始达到的估计地标 时间间隔结束时的地标。 该方法还包括基于覆盖要求的顺序和估计的地标，确定给定的发射地点和将给定车辆添加到多个操作车辆的相应时间间隔。
