公开(公告)号：US07714536B1

公开(公告)日：2010-05-11

申请号：US11789128

申请日：2007-04-05

申请人： Eric J. Silberg ,  Judah H. Milgram

发明人： Eric J. Silberg ,  Judah H. Milgram

IPC分类号： H02J7/00

CPC分类号： B64C39/024 ,  B60L11/002 ,  B60L11/1801 ,  B60L11/182 ,  B60L2200/10 ,  B60L2200/20 ,  B60L2260/32 ,  B64C2201/042 ,  B64C2201/063 ,  Y02T10/7005 ,  Y02T10/7072 ,  Y02T90/122 ,  Y02T90/14

摘要： A method and apparatus for charging energy supplies in an unmanned aerial vehicle (UAV). The present invention relates to a UAV that comprises an inductive charging device that utilizes the electromagnetic field emanated by overhead/utility power lines, to charge the energy supplies. The UAV also includes a releasable latch for holding power lines to allow for the perching of the UAV on power lines during the charging process. The latch and the inductive charging device may be provided on a single device, a battery augmentation trap (BAT). The UAV may be perched in an upright orientation to allow for takeoff after the charging of energy supplies on the power line.

摘要翻译： 一种在无人机（UAV）中为能量供给充电的方法和装置。 本发明涉及一种UAV，其包括利用由架空/公用电力线发出的电磁场来对能量供应充电的感应充电装置。 无人机还包括可释放的闩锁，用于保持电力线以允许充电过程中的电力线上的UAV的栖息。 闩锁和感应充电装置可以设置在单个装置，电池增压阱（BAT）上。 无人机可以处于垂直方向，以允许在电力线上的能量供应充电之后起飞。

公开(公告)号：US07324016B1

公开(公告)日：2008-01-29

申请号：US11288070

申请日：2005-11-22

申请人： Judah H. Milgram

发明人： Judah H. Milgram

IPC分类号： G08B21/00 ,  B64D47/02 ,  B64D47/06 ,  B64C27/00 ,  G06F7/70 ,  G01C17/00

CPC分类号： B64C27/46 ,  B64C27/023 ,  B64D47/06 ,  B64D2203/00

摘要： Red, green and white colored lights are emitted from navigation orientation indicating light emitting devices mounted within a helicopter rotor blade near its tip. The light emissions from such devices are under control to respectively indicate passage of the rotor blade through limited arcuate portions of the travel path of the rotor blade end tip. Operational control over the light emitting devices is effected by data processing of outputs from air-speed responsive sensors on the blade end tip.

摘要翻译： 导航方向发出红色，绿色和白色的指示灯，指示安装在其尖端附近的直升机转子叶片内的发光装置。 来自这种装置的光发射受到控制，以分别指示转子叶片通过转子叶片末端的行进路径的有限弓形部分的通过。 对发光装置的操作控制是通过对来自叶片末端的空速响应传感器的输出的数据处理来实现的。

公开(公告)号：USH2206H1

公开(公告)日：2007-12-04

申请号：US10975112

申请日：2004-10-28

申请人： Judah H. Milgram

发明人： Judah H. Milgram

IPC分类号： B64C13/24

摘要： Side-slip of an aircraft during flight is detected through a pair of pressure sensors fixedly mounted on opposite lateral sides of the aircraft fuselage. Pressure measurement signals at said sensors are fed to electronic circuitry within the aircraft for generating magnitude and frequency signals reflective of the side-slip that are applied to a pair of vibrators respectively mounted on the undersides of a pair of pilot foot pedals located within the cockpit. The foot pedals are connected by linkage to the tail rudder on the aircraft fuselage. The varying magnitude and frequency of vibrations applied to the rudder foot pedals by the vibrators enables the pilot to immediately sense side-slip through the feet on the pedals. In response to such side-slip sensing, one of the pedals may be timely depressed for side-slip corrective angular displacement of the rudder.

公开(公告)号：US07059566B2

公开(公告)日：2006-06-13

申请号：US10856360

申请日：2004-05-27

申请人： David W. Byers ,  Gary A. Hall ,  Graham D. Hunter ,  Colen G. Kennell ,  Aleksander B. Macander ,  Judah H. Milgram ,  Jason D. Strickland

发明人： David W. Byers ,  Gary A. Hall ,  Graham D. Hunter ,  Colen G. Kennell ,  Aleksander B. Macander ,  Judah H. Milgram ,  Jason D. Strickland

IPC分类号： B64C1/00

CPC分类号： B64C1/068 ,  B64C1/061 ,  B64C1/22 ,  B64C3/58 ,  B64C29/02 ,  B64C31/02 ,  B64C39/024 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/105 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/185 ,  B64C2201/187 ,  B64D5/00

摘要： A hollow elliptical-cylindrical hull conformingly houses a hollow rectangular-prismatic cabin whereby the four longitudinal parallel outside edges of the latter make contact with the inside surface of the former. The fully constructed aircraft (either non-powered or powered) includes the integral hull-plus-cabin structure along with nose, tail and airfoil structures that are coupled therewith. The cabin conformingly accommodates hollow rectangular-prismatic modules useful for cargo storage. While the nose and/or tail structure is uncoupled from the integral hull-plus-cabin structure, the modules are inserted into the cabin and the cabin is sealed. The aircraft is lifted (e.g., via airplane, helicopter, rocket or balloon) to a particular elevation and released, whereupon the two wings fully emerge and the aircraft effects controlled flight until reaching its destination. After landing, the nose and/or tail structure is uncoupled from the integral hull-plus-cabin structure, the cabin is unsealed, and the modules are removed from the cabin.

摘要翻译： 中空的椭圆柱形船体适合地容纳中空矩形棱柱舱，由此四个纵向平行的外边缘与前者的内表面接触。 完全构造的飞机（非动力或动力）包括一体的船体加舱结构以及与其结合的鼻，尾和翼型结构。 机舱适合容纳用于货物存储的中空矩形模块。 当鼻部和/或尾部结构与整体的船体 - 舱室结构脱离时，模块被插入到舱室中，舱室被密封。 飞机被提升（例如，通过飞机，直升机，火箭或气球）到特定的高度并被释放，于是两翼完全出现，并且飞机实现控制的飞行直到到达其目的地。 在着陆后，鼻部和/或尾部结构与整体式的船体 - 舱室结构脱离，舱室被开封，模块从舱室中取出。