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81. 发明申请

WO2017210595A2 VERTICAL TAKE-OFF AND LANDING (VTOL) WINGED AIR VEHICLE WITH COMPLEMENTARY ANGLED ROTORS 审中-公开
标题翻译：垂直起飞和着陆（垂直起降）带有互补斜齿轮的翼形气动汽车
公开(公告)号：WO2017210595A2
公开(公告)日：2017-12-07
申请号：PCT/US2017/035742
申请日：2017-06-02
申请人： AEROVIRONMENT, INC.
发明人： WON, Henry Thome , LINDSEY, Quentin
IPC分类号： B64C27/26 , B64C39/02
摘要： Systems, devices, and methods for an aircraft having a fuselage (110); a wing (120) extending from both sides of the fuselage; a first pair of motors (132b, 133b) disposed at a first end of the wing; and a second pair of motors (142b, 143b) disposed at a second end of the wing; where each motor is angled (381, 382, 391, 392) to provide a component of thrust by a propeller (134, 135, 144, 145) attached thereto that for a desired aircraft movement applies a resulting torque additive to the resulting torque created by rotating the propellers.
摘要翻译：用于具有机身（110）的飞行器的系统，设备和方法; 机身（120），从机身的两侧延伸; 设置在所述机翼的第一端处的第一对马达（132b，133b）和布置在所述机翼的第二端处的第二对马达（142b，143b）其中每个马达成角度（381,382,391,392）以通过附接到其上的螺旋桨（134,135,144,145）提供推力分量，所述螺旋桨（134,135,144,145）为了期望的飞机运动而将合成的转矩添加剂施加到所产生的转矩通过旋转螺旋桨。

82. 发明申请

WO2017030638A2 ROTATING LIDAR 审中-公开
标题翻译：旋转激光雷达
公开(公告)号：WO2017030638A2
公开(公告)日：2017-02-23
申请号：PCT/US2016/037275
申请日：2016-06-13
申请人： AEROVIRONMENT, INC.
发明人： MIREMADI, Reza
CPC分类号： G01S7/4817 , G01S7/4813 , G01S17/42 , G01S17/66
摘要： A lidar system, including a base, a sensor body, and a motor having a shaft. The motor is affixed to the base, and can drive the sensor body in rotation with respect to the base. An LED device and a light sensor are each mounted upon the sensor body. A data processing device is also mounted upon the sensor body, and is programmed to produce range information based upon the sensor data. The shaft carries two slip rings. The LED, the sensor and the data processing device all receive electrical power via the two slip rings. The data processing device is configured to transmit the range information via the two slip rings using pulse width modulation.
摘要翻译：激光雷达系统包括基座，传感器主体和具有轴的电机。电机固定在底座上，可以驱动传感器体相对于底座旋转。 LED装置和光传感器分别安装在传感器主体上。数据处理设备也安装在传感器主体上，并且被编程为基于传感器数据产生范围信息。轴带有两个滑环。 LED，传感器和数据处理设备都通过两个滑环接收电源。数据处理设备配置为使用脉宽调制通过两个滑环传输距离信息。

83. 发明申请

WO2016154281A1 SYSTEM MONITORING POWER CONNECTOR AND CABLE HEALTH 审中-公开
标题翻译：系统监控电源连接器和电缆健康
公开(公告)号：WO2016154281A1
公开(公告)日：2016-09-29
申请号：PCT/US2016/023733
申请日：2016-03-23
申请人： AEROVIRONMENT, INC.
发明人： DICKINSON, Blake Edward , HORI, Bradford M. , DRESSELHAUS, Daniel D.
IPC分类号： G01R27/08 , H03F3/45
CPC分类号： B60L11/187 , B60L3/04 , B60L11/1809 , B60L11/1818 , B60L2200/42 , B60L2230/12 , B60L2240/36 , G08B21/182 , H02H3/085 , H02H5/042 , H02J7/0026 , Y02T10/7005 , Y02T10/7088 , Y02T90/121 , Y02T90/14
摘要： A method of protecting an electric vehicle (EV) charger connector 200 from excessive heat includes monitoring the internal temperature of an electrical connector (block 1500), the electrical connector 200 having pilot and pilot return signal lines (235, 240), reducing a voltage between the pilot and pilot return signal lines (block 1515) in response to the internal temperature exceeding a first threshold (block 1505), and reducing charging current provided through the electrical connector in response to the change in voltage (block 1520) so that the internal temperature exceeding the first threshold will result in a reduction of charging current through the connector.
摘要翻译：一种保护电动车辆（EV）充电器连接器200免于过热的方法包括监测电连接器（块1500）的内部温度，电连接器200具有导频和导频返回信号线（235,240），降低电压响应于内部温度超过第一阈值而在导频和导频返回信号线（方框1515）之间（块1505），并且响应于电压变化减小通过电连接器提供的充电电流（方框1520），使得内部温度超过第一阈值将导致通过连接器的充电电流减少。

84. 发明申请

WO2016153990A1 BATTERY WATERING EVENT DETECTION USING A TEMPERATURE SENSOR 审中-公开
标题翻译：使用温度传感器进行电池水处理事件检测
公开(公告)号：WO2016153990A1
公开(公告)日：2016-09-29
申请号：PCT/US2016/023115
申请日：2016-03-18
申请人： AEROVIRONMENT, INC. , DICKINSON, Blake Edward
发明人： DICKINSON, Blake Edward
IPC分类号： G01R31/36 , H01M2/36 , H01M10/48
CPC分类号： H01M10/484 , G01R31/36 , H01M10/4257 , H01M10/443 , H01M10/486 , H01M2220/20
摘要： A method of battery cell monitoring includes measuring a temperature of an electrolyte (block 700) in a battery cell using a temperature sensor, outputting from the temperature sensor a plurality of electrolyte temperature signals (block 710) indicative of the temperature of the electrolyte over time, providing the plurality of electrolyte temperature signals to a system controller (block 710), determining by the system controller a sudden transition in the electrolyte temperature signals (block 720), and logging a watering event data indication (block 725) in a memory in response to calculating the sudden transition.
摘要翻译：电池单元监视的方法包括使用温度传感器测量电池单元中的电解质（块700）的温度，从温度传感器输出指示电解质温度随时间变化的多个电解质温度信号（框710），向系统控制器提供多个电解质温度信号（方框710），由系统控制器确定电解质温度信号中的突然转变（方框720），并将浇水事件数据指示（框725）记录在存储器中响应计算突然过渡。

85. 发明申请

WO2016130716A2 GEOGRAPHIC SURVEY SYSTEM FOR VERTICAL TAKE-OFF AND LANDING (VTOL) UNMANNED AERIAL VEHICLES (UAVS) 审中-公开
标题翻译：垂直起降（垂直起降）无人机（UAVS）的地理测量系统
公开(公告)号：WO2016130716A2
公开(公告)日：2016-08-18
申请号：PCT/US2016/017407
申请日：2016-02-10
申请人： AEROVIRONMENT, INC.
发明人： FISHER, Christopher Eugene , MUKHERJEE, Jason Sidharthadev , LOTT, William Arden
IPC分类号： G06Q10/08 , B64D43/00
CPC分类号： G05D1/102 , B64C29/02 , B64C39/024 , B64C2201/021 , B64C2201/088 , B64C2201/123 , B64C2201/141 , B64C2201/201 , B64D47/08 , B64F1/005 , G06F17/30241 , G06Q30/016 , G08G5/0021 , G08G5/0034 , G08G5/0039 , G08G5/0056 , G08G5/0065 , G08G5/0069 , G08G5/0078 , G08G5/0091 , G08G5/025
摘要： A method of unmanned aerial vehicle (UAV) operation, including: receiving from a customer a first data request (400), the first data request (400) having: a first geographic coverage area, and a refresh rate for the first geographic coverage area, planning a first plurality of flight missions to accomplish the first data request, uploading flight missions data representing the first plurality of flight missions into a UAV pod (404), and deploying the UAV pod (802).
摘要翻译：一种无人飞行器（UAV）操作的方法，包括：从客户接收第一数据请求（400），所述第一数据请求（400）具有：第一地理覆盖区域和第二地理覆盖区域计划第一多个飞行任务以完成第一数据请求，将表示第一多个飞行任务的飞行任务数据上传到UAV舱（404），以及部署UAV舱（802）

86. 发明申请

WO2015012935A3 VERTICAL TAKEOFF AND LANDING (VTOL) AIR VEHICLE 审中-公开
标题翻译：垂直起飞和着陆（垂直起降）空气车辆
公开(公告)号：WO2015012935A3
公开(公告)日：2015-05-14
申请号：PCT/US2014036863
申请日：2014-05-05
申请人： AEROVIRONMENT INC , TAYLOR DANA J , TOKUMARU PHILLIP T , HIBBS BART DEAN , PARKS WILLIAM MARTIN , GANZER DAVID WAYNE , FISHER CHRISTOPHER EUGENE , MUKHERJEE JASON SIDHARTHADEV , KING JOSEPH FREDERICK
发明人： TAYLOR DANA J , TOKUMARU PHILLIP T , HIBBS BART DEAN , PARKS WILLIAM MARTIN , GANZER DAVID WAYNE , FISHER CHRISTOPHER EUGENE , MUKHERJEE JASON SIDHARTHADEV , KING JOSEPH FREDERICK
IPC分类号： B64C29/02
CPC分类号： B64C29/0025 , B64C11/32 , B64C27/26 , B64C27/54 , B64C27/605 , B64C29/00 , B64C29/02 , B64C39/024 , B64C2201/021 , B64C2201/042 , B64C2201/088 , B64C2201/104 , B64C2201/108 , B64C2201/165 , B64D27/24 , G05D1/0858
摘要： A flight control apparatus for fixed-wing aircraft includes a first port wing (115) and first starboard wing (120), a first port swash plate (145) coupled between a first port rotor 155) and first port electric motor (135), the first port electric 5 motor (135) coupled to the first port wing (115), and a first starboard swash plate (150) coupled between a first starboard rotor (130) and first starboard electric motor (140), the first starboard electric motor (140) coupled to the first starboard wing (120).
摘要翻译：一种用于固定翼飞机的飞行控制装置，包括：第一端口翼（115）和第一右舷翼（120），联接在第一端口转子（155）与第一端口电动机（135）之间的第一端口斜板（145）联接到第一端口机翼（115）的第一端口电动机（135）以及联接在第一右舷转子（130）和第一右舷电动机（140）之间的第一右舷斜盘（150），第一右舷电动机马达（140）联接到第一右舷翼（120）。

87. 发明申请

WO2013074177A3 TILT-BALL TURRET WITH GIMBAL LOCK AVOIDANCE 审中-公开
标题翻译： TILT-BALL TURRET与GIMBAL LOCK AVOIDANCE
公开(公告)号：WO2013074177A3
公开(公告)日：2014-05-15
申请号：PCT/US2012052729
申请日：2012-08-28
申请人： AEROVIRONMENT INC , OMER THOMAS , SZAREK THOMAS , DIMOTAKIS MANOLIS PAVLOS , MCBRIDE JEFFERSON C
发明人： OMER THOMAS , SZAREK THOMAS , DIMOTAKIS MANOLIS PAVLOS , MCBRIDE JEFFERSON C
IPC分类号： B64D47/08
CPC分类号： B64D47/08 , B64C39/024 , B64C2201/021 , B64C2201/123 , B64C2201/127 , F16M11/123 , F16M11/126 , F16M11/18 , H04N7/183
摘要： A turret assembly for attachment on the undersurface of an aircraft that reduces performance limitations due to gimbal lock and reduces the cross section profile of the assembly. The assembly includes a roll actuator including a drive shaft. A yoke having a cross member is coupled to the drive shaft and a pair of prongs. The yoke is rotated via the roll actuator and drive shaft along a roll axis oriented substantially parallel to the body of the aircraft. A turret is mounted on the prongs of the yoke. A tilt actuator is contained within the turret. The tilt actuator tilts the turret on a tilt axis relative to the yoke. The tilt axis is perpendicular to the roll axis.
摘要翻译：一种用于附接在飞行器下表面上的转塔组件，其减小由于万向节锁定而导致的性能限制并减小组件的横截面轮廓。组件包括具有驱动轴的辊致动器。具有横向构件的轭联接到驱动轴和一对插脚。轭架通过辊子致动器和驱动轴沿着基本平行于飞行器主体的辊轴线旋转。一个转塔安装在轭的叉子上。转塔内装有一个倾斜致动器。倾斜致动器相对于轭架在倾斜轴上倾斜转台。倾斜轴垂直于辊轴。

88. 发明申请

WO2012106372A3 QUICK CHARGER CONNECTOR FOR LOW AND ZERO VOLTAGE TESTING OF AN ELECTRIC VEHICLE DIRECT CHARGE DEVICE 审中-公开
标题翻译：快速充电器连接器，用于电动车辆直接充电装置的低和零电压测试
公开(公告)号：WO2012106372A3
公开(公告)日：2014-04-17
申请号：PCT/US2012023391
申请日：2012-01-31
申请人： AEROVIRONMENT INC , LOTFY NADER , DUNN ERIC ALLEN
发明人： LOTFY NADER , DUNN ERIC ALLEN
IPC分类号： G01R15/00
CPC分类号： B60L3/00 , B60L11/1816 , B60L11/1818 , B60L11/185 , B60L2210/10 , B60L2210/30 , B60L2210/40 , B60L2240/547 , G01R31/40 , Y02T10/7005 , Y02T10/7072 , Y02T10/7216 , Y02T10/7241 , Y02T90/121 , Y02T90/127 , Y02T90/128 , Y02T90/14
摘要： Methods and devices for testing an electric vehicle direct charge device (110) via a quick (direct) charger connector (410) for low and zero voltage testing (640) according to a direct charge protocol of an electric vehicle (EV) or an EV simulator. A first jumper pin (471) is disposed between the ground terminal (450) and the charging permission terminal (440) of a direct charger connector (410). A second jumper pin (472) is disposed between the positive power supply terminal (420) and the negative power supply terminal (430) of the direct charger connector (410).
摘要翻译：用于根据电动车辆（EV）或EV的直接充电协议通过用于低和零电压测试（640）的快速（直接）充电器连接器（410）测试电动车辆直接充电装置（110）的方法和装置模拟器。第一跨接销（471）设置在直接充电器连接器（410）的接地端子（450）和充电允许端子（440）之间。第二跨接销（472）设置在直接充电器连接器（410）的正电源端子（420）和负电源端子（430）之间。

89. 发明申请

WO2014036013A3 PORTABLE ELECTRIC VEHICLE SUPPLY EQUIPMENT 审中-公开
公开(公告)号：WO2014036013A3
公开(公告)日：2014-03-06
申请号：PCT/US2013/056871
申请日：2013-08-27
申请人： AEROVIRONMENT, INC.
发明人： STEINBUCHEL IV, Herman Joseph , FLACK, Albert Joseph , ZANTESON, Richard Elliott
IPC分类号： H05K5/03
摘要： An electric vehicle service equipment (EVSE) system includes an EVSE case having a front plug face, a rear face, and left and right gripping sides that collectively define a trapezoidal prism cross section, the left and right gripping sides further having left and right convex gripping portions, respectively, a relay positioned within the EVSE case, and a controller positioned within the EVSE case and in communication with the relay, the controller responsive to a pilot duty signal, when a pilot duty signal is present.

90. 发明申请

WO2013062608A3 INVERTED-LANDING AIRCRAFT 审中-公开
标题翻译：反转式飞机
公开(公告)号：WO2013062608A3
公开(公告)日：2013-06-27
申请号：PCT/US2012000356
申请日：2012-08-16
申请人： AEROVIRONMENT INC , FISHER CHRISTOPHER E , SZAREK THOMAS ROBERT , MCALLISTER JUSTIN B , BELIK PAVEL
发明人： FISHER CHRISTOPHER E , SZAREK THOMAS ROBERT , MCALLISTER JUSTIN B , BELIK PAVEL
IPC分类号： B64C39/02 , G05D1/08
CPC分类号： G01C5/005 , B64C39/024 , B64C2201/021 , B64C2201/104 , B64C2201/127 , B64C2201/146 , B64C2201/165 , B64C2201/18 , B64D47/08 , G05D1/0011 , G05D1/0676 , G05D1/0808 , G05D1/0816
摘要： An aircraft defining an upright orientation and an inverted orientation, a ground station; and a control system for remotely controlling the flight of the aircraft. The ground station has an auto-land function that causes the aircraft to invert, stall, and controllably land in the inverted orientation to protect a payload and a rudder extending down from the aircraft. In the upright orientation, the ground station depicts the view from a first aircraft camera. When switching to the inverted orientation: (1 ) the ground station depicts the view from a second aircraft camera, (2) the aircraft switches the colors of red and green wing lights, extends the ailerons to act as inverted flaps, and (3) the control system adapts a ground station controller for the inverted orientation. The aircraft landing gear is an expanded polypropylene pad located above the wing when the aircraft is in the upright orientation.
摘要翻译：一台定义垂直方向和倒置方向的飞机，一个地面站; 以及用于远程控制飞机飞行的控制系统。地面站具有自动地面功能，使飞机以反方向反转，失速和可控地着陆，以保护从飞机向下延伸的有效载荷和舵。在直立方向，地面站描绘从第一架飞机相机的视图。当切换到反向方向时：（1）地面站描绘第二架飞机相机的视野，（2）飞机切换红色和绿色翼灯的颜色，延伸副翼作为倒转襟翼，（3）控制系统使地面站控制器适应倒置方向。当飞机处于直立方向时，飞机起落架是位于机翼上方的扩展的聚丙烯垫。

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