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1. 发明授权

US10269252B2 Aircraft traffic collision avoidance 有权
公开(公告)号：US10269252B2
公开(公告)日：2019-04-23
申请号：US14881059
申请日：2015-10-12
申请人： Safe Flight Instrument Corporation
发明人： Randall A. Greene
IPC分类号： G08G5/00 , G08G5/04
摘要： A collision warning method includes receiving a collision risk indication from a traffic collision avoidance system of an aircraft, receiving a preset altitude, comparing the preset altitude and an altitude associated with the collision risk indication, and providing a warning in the aircraft when the preset altitude and the altitude associated with the collision risk are within a threshold.

2. 发明申请

US20170305573A1 AIRCRAFT TURBULENCE DETECTION 审中-公开
公开(公告)号：US20170305573A1
公开(公告)日：2017-10-26
申请号：US15647167
申请日：2017-07-11
申请人： Safe Flight Instrument Corporation
发明人： Randall A. GREENE , Shawn P. BEYER , Robert D. TETER
IPC分类号： B64D45/04 , B64D45/00 , G07C5/08 , B64D43/00
CPC分类号： B64D45/04 , B64D43/00 , B64D45/00 , B64D2045/008 , G07C5/0808 , G08G5/0021 , G08G5/0091 , G08G5/025
摘要： A warning method for an aircraft includes receiving a first parameter indicative of an aircraft's flight path, calculating a stable approach value based on the first parameter, receiving a second parameter indicative of the aircraft's turbulence, calculating a turbulence factor based on the second parameter, calculating a safe landing value based on the stable approach value and the turbulence factor, comparing the safe landing value to a threshold value, and providing an aircraft warning when the safe landing value fails to meet the threshold value.

3. 发明授权

US09701422B2 Aircraft turbulence detection 有权
公开(公告)号：US09701422B2
公开(公告)日：2017-07-11
申请号：US15143123
申请日：2016-04-29
申请人： Safe Flight Instrument Corporation
发明人： Randall A. Greene , Shawn P. Beyer , Robert D. Teter
IPC分类号： B64D45/00 , B64D45/04 , G07C5/08 , B64D43/00
CPC分类号： B64D45/04 , B64D43/00 , B64D45/00 , B64D2045/008 , G07C5/0808 , G08G5/0021 , G08G5/0091 , G08G5/025
摘要： A warning method for an aircraft includes receiving a first parameter indicative of an aircraft's flight path, calculating a stable approach value based on the first parameter, receiving a second parameter indicative of the aircraft's turbulence, calculating a turbulence factor based on the second parameter, calculating a safe landing value based on the stable approach value and the turbulence factor, comparing the safe landing value to a threshold value, and providing an aircraft warning when the safe landing value fails to meet the threshold value.

4. 发明申请

US20130120164A1 OBSTACLE DETECTION & NOTIFICATION SYSTEM 有权
标题翻译：障碍物检测和通报系统
公开(公告)号：US20130120164A1
公开(公告)日：2013-05-16
申请号：US13296029
申请日：2011-11-14
申请人： Randall A. GREENE , Paul LEVINE , Louis SIMONS , Robert D. TETER
发明人： Randall A. GREENE , Paul LEVINE , Louis SIMONS , Robert D. TETER
IPC分类号： G08B21/00
CPC分类号： G08G5/0021 , G08G5/0086 , G08G5/045
摘要： A power line warning system for a helicopter, comprising a positioning system operable to determine the coordinates of the helicopter, an obstacle coordinate database comprising the coordinates of at least a portion of a first power line, a sensor operable to detect electromagnetic radiation from the first power line, and a visual display operable to represent a position of the first power line relative to the helicopter is described. When the coordinates of the first power line are within a predetermined distance of the coordinates of the helicopter, wherein the representation of the position of the first power line is modified when the sensor detects electromagnetic radiation from the first power line.
摘要翻译：一种用于直升机的电力线警报系统，包括可操作以确定直升机的坐标的定位系统，包括第一电力线的至少一部分的坐标的障碍物坐标数据库，可操作以检测来自第一电力线的电磁辐射的传感器描述了可操作以表示第一电力线相对于直升机的位置的视觉显示器。当第一电力线的坐标在直升机的坐标的预定距离内时，其中当传感器检测到来自第一电力线的电磁辐射时，修改第一电力线的位置的表示。

5. 发明申请

US20110036948A1 AUTOMATIC RECYCLING ICE DETECTOR 有权
标题翻译：自动回收冰箱检测器
公开(公告)号：US20110036948A1
公开(公告)日：2011-02-17
申请号：US12913531
申请日：2010-10-27
申请人： Leonard M. Greene
发明人： Leonard M. Greene
IPC分类号： B64D15/22 , G06F19/00
CPC分类号： B64D15/20 , B64D15/22 , G08B19/02
摘要： An automatic recycling ice detector includes a sensor for sensing the formation of ice on an aircraft surface and a heater for melting the detected ice. The detector also includes a timing circuit for indicating the time to melt any detected ice and automatically recycling the detector when the ice is melted. A computer including a look up table or the like are provided for measuring and indicating the thickness of the accumulated ice based on a relationship between melting time and thickness.
摘要翻译：自动回收冰检测器包括用于感测飞机表面上的冰的形成的传感器和用于熔化检测到的冰的加热器。检测器还包括定时电路，用于指示熔化任何检测到的冰的时间，并且当冰融化时自动回收检测器。提供包括查看表等的计算机，用于基于熔化时间和厚度之间的关系来测量和指示累积的冰的厚度。

6. 发明授权

US07564373B2 System and method for detecting ice formation on an aircraft 有权
标题翻译：用于检测飞机上冰层形成的系统和方法
公开(公告)号：US07564373B2
公开(公告)日：2009-07-21
申请号：US11564878
申请日：2006-11-30
申请人： Clyde F. Platt
发明人： Clyde F. Platt
IPC分类号： G08B21/00 , B64D15/20
CPC分类号： B64D15/20
摘要： A system and method for detecting ice formation on the surface of an aircraft includes a small rotatable disc disposed on and flush with a surface of a aircraft wing and/or stabilizer and a DC motor for rotating the disc. The disc is rotated periodically and the peak current which is directly proportional to the torque required to break any ice is monitored. When the torque exceeds a pre-selected amount a warning is sounded in the cockpit. If the torque required to rotate the disc increases a second warning is given and the amount of ice accumulation is calculated. In one embodiment of the invention, a stall warning system is automatically modified to increase the margin to accommodate for the increase due to ice accumulation.
摘要翻译：用于检测飞行器表面上的冰层形成的系统和方法包括设置在飞行器机翼和/或稳定器的表面上并与其平齐的小的可旋转盘，以及用于旋转盘的DC马达。盘被周期性地旋转，并且监测与破坏任何冰所需的扭矩成正比的峰值电流。当扭矩超过预选量时，驾驶舱内发出警告。如果旋转盘所需的扭矩增加，则给出第二个警告并计算积冰量。在本发明的一个实施例中，失速警告系统被自动修改以增加余量以适应由于积冰而增加。

7. 发明授权

US07262712B2 Helicopter tactile exceedance warning system 有权
标题翻译：直升机触觉超警预警系统
公开(公告)号：US07262712B2
公开(公告)日：2007-08-28
申请号：US10821974
申请日：2004-04-12
申请人： Randall A. Greene
发明人： Randall A. Greene
IPC分类号： G08B23/00
CPC分类号： F02C9/285 , B64C13/10 , B64C27/04 , B64D43/00 , F05D2270/303 , F05D2270/3032 , F05D2270/44
摘要： A helicopter tactile accedence warning system includes a control stick and a tactile warning device attached to the control stick. A computer or micro processor and a keyboard for entering a safe temperature profile are also provided as well as a thermocouple for measuring the turbine output temperature. The computer compares the actual temperature versus the safe temperature profile and generates a signal to activate the tactile warning device when the actual temperature falls outside of the safe temperature profile to warn a pilot to abort the start. The tactile warning device is also activated during flight operations when an over stress condition occurs to thereby warn the pilot to take corrective action. In addition, the tactile warning may be activated at a first frequency as an early warning and then at a second frequency as an indication of imminent danger.
摘要翻译：直升机触觉入门警告系统包括控制杆和附接到控制棒的触觉警告装置。还提供用于输入安全温度曲线的计算机或微处理器和键盘以及用于测量涡轮机输出温度的热电偶。计算机将实际温度与安全温度曲线进行比较，并在实际温度超出安全温度曲线的情况下产生信号以激活触觉报警装置，以警告飞行员中止启动。触发警告装置在飞行操作期间也会发生过应力状况，从而警告飞行员采取纠正措施。此外，触觉警告可以以第一频率作为早期警告激活，然后以第二频率激活，作为即将发生危险的指示。

8. 发明申请

US20040070521A1 System and method for reducing the speed of an aircraft 失效
公开(公告)号：US20040070521A1
公开(公告)日：2004-04-15
申请号：US10265385
申请日：2002-10-07
申请人： Safe Flight Instrument Corporation
发明人： Randall A. Greene
IPC分类号： G08B023/00
CPC分类号： B64D31/06 , G05D1/063
摘要： An aircraft system for reducing the airspeed of an aircraft as it passes through a preselected altitude includes an automatic throttle system including a computer, a device for inputting a preselected altitude and a preselected airspeed into the computer. An altimeter provides the current altitude of the aircraft and an aircraft instrument provides the current air speed and the vertical speed of the aircraft. The computer in response to the current altitude and vertical speed of the aircraft generates a signal to retard the throttles when the current altitude, the current air speed of the aircraft is equal to 2 times the vertical speed plus a preselected altitude.

9. 发明授权

US5874673A Air speed and direction indicating system for rotary winged aircraft 失效
标题翻译：旋翼飞机的空气速度和方向指示系统
公开(公告)号：US5874673A
公开(公告)日：1999-02-23
申请号：US839394
申请日：1997-04-11
申请人： Leonard M. Greene
发明人： Leonard M. Greene
IPC分类号： G01P13/02 , G01P15/00 , G01C21/12
CPC分类号： G01P13/025 , G01P15/00
摘要： An airspeed and direction indicating system for an aircraft of the rotary wing type includes a vertical accelerometer for monitoring the up and down movement of an outer portion or tip of the rotary wing. The vertical accelerometer produces a generally sinusoidal signal in response to the up and down movement of the wing tip as it rotates about an axis. The amplitude of the signal corresponds to the airspeed and the phase angle indicates direction. Suitable readouts display the information for consideration by a pilot.
摘要翻译：用于旋转翼型飞行器的空速和方向指示系统包括垂直加速度计，用于监测旋转翼的外部或尖端的上下运动。垂直加速度计响应于翼尖围绕轴旋转的上下运动而产生大致正弦信号。信号的幅度对应于空速，相位角指示方向。合适的读数显示信息供飞行员考虑。

10. 发明授权

US5590853A Aircraft control system 失效
标题翻译：飞机控制系统
公开(公告)号：US5590853A
公开(公告)日：1997-01-07
申请号：US829256
申请日：1992-02-03
申请人： Leonard M. Greene
发明人： Leonard M. Greene
IPC分类号： B64C13/10 , B64D43/02 , G01P13/02 , G05D1/08 , B64C9/00 , G05D1/10
CPC分类号： B64D43/02 , B64C13/10 , G01P13/025 , G05D1/0808
摘要： An aircraft control system for computing a yaw compensated angle of attack is disclosed. The system includes an angle of attack sensor for generating a signal which represents an aircraft's angle of attack as determined by an angle of attack vane and a transverse accelerometer for generating a signal in response to the lateral acceleration of the aircraft. A summing device sums the two signals to thereby provide a yaw compensated angle of attack signal. The system may also include a rudder deflection sensor for generating a signal which represents the deflection of an aircraft's rudder. The rudder deflection signal is then subtracted from the yaw compensated angle of attack in the summing device. A stall warning system incorporating the yaw compensation system includes a stall warning computer for comparing the yaw compensated angle of attack signal to a predetermined value. The stall warning computer then triggers a stall warning device when the yaw compensated angle of attack signal exceeds the predetermined value.
摘要翻译：公开了一种用于计算偏航补偿迎角的飞机控制系统。该系统包括一个迎角传感器，用于产生代表飞机的迎角的信号，该角度由迎角和横向加速度计确定，用于响应于飞行器的横向加速度而产生信号。求和装置将两个信号相加，从而提供偏航补偿的迎角信号。该系统还可以包括用于产生代表飞行器方向舵偏转的信号的舵偏转传感器。然后从求和装置中的偏航补偿迎角中减去舵偏转信号。包括偏航补偿系统的失速警报系统包括用于将偏航补偿的迎角信号与预定值进行比较的失速警告计算机。然后，当偏航补偿迎角信号超过预定值时，失速警报计算机触发失速警告装置。

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