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1. 发明申请

US20170103661A1 AIRCRAFT TRAFFIC COLLISION AVOIDANCE 审中-公开
公开(公告)号：US20170103661A1
公开(公告)日：2017-04-13
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： G08G5/04 , G08G5/00
CPC分类号： G08G5/0021 , G08G5/0008 , G08G5/0052 , G08G5/0078 , G08G5/045
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. 发明申请

US20160159494A1 DEFLARE PITCH COMMAND 有权
标题翻译： DEFLARE PITCH命令
公开(公告)号：US20160159494A1
公开(公告)日：2016-06-09
申请号：US14213967
申请日：2014-03-14
申请人： Safe Flight Instrument Corporation
发明人： Randall A. GREENE , Shawn P. BEYER
IPC分类号： B64D45/08 , G01C23/00
CPC分类号： B64D45/00 , B64C13/00 , B64C17/00 , B64C19/00 , B64D43/00 , B64D45/0005 , B64D45/04 , B64D45/08 , B64D2045/008 , G02B27/01 , G05D1/0676 , G05D1/0808 , G05D1/0816 , G08G5/0021 , G08G5/0047 , G08G5/02 , G08G5/025
摘要： A pitch command display method includes identifying touchdown of an aircraft, identifying a first value representing an actual pitch reduction rate of the aircraft, identifying a second value representing a target pitch reduction rate of the aircraft, determining a difference between the first value and the second value, and displaying a pitch command when the difference between the first value and second value is greater than a threshold amount and the aircraft has touched down.
摘要翻译：俯仰指示显示方法包括识别飞行器的触地，识别表示飞行器的实际俯仰减速率的第一值，识别表示飞机的目标俯仰减速率的第二值，确定第一值与第二值之间的差值，并且当第一值和第二值之间的差大于阈值量并且飞机已经触及时，显示音调指令。

4. 发明申请

US20170057657A1 HELICOPTER TACTILE STALL WARNING 有权
标题翻译：直升机战术警告
公开(公告)号：US20170057657A1
公开(公告)日：2017-03-02
申请号：US15005998
申请日：2016-01-25
申请人： Safe Flight Instrument Corporation
发明人： Randall A. GREENE
IPC分类号： B64D43/02
CPC分类号： B64D43/02 , B64C27/006 , B64C27/56
摘要： A helicopter stall warning method includes receiving an airspeed of the helicopter, determining a stall airspeed based on multiple factors associated with the helicopter, the multiple factors comprising ambient temperature near the helicopter, the helicopter's altitude, and the helicopter's gross weight, determining a stall warning threshold derived from the stall airspeed, and providing a tactile warning through a collective helicopter control when the helicopter's airspeed meets or exceeds the stall warning threshold.
摘要翻译：直升机失速警告方法包括接收直升机的空速，基于与直升机相关的多个因素确定失速空速，包括直升机附近的环境温度，直升机高度和直升机总重量的多个因素，确定失速警告来自失速空速的门槛，并且当直升机的空速达到或超过失速警告阈值时，通过集体直升机控制提供触觉警报。

5. 发明申请

US20170008642A1 AIRCRAFT TURBULENCE DETECTION 有权
标题翻译：飞机湍流检测
公开(公告)号：US20170008642A1
公开(公告)日：2017-01-12
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： B64D45/04 , G07C5/08
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.
摘要翻译：一种用于飞行器的警告方法包括：接收指示飞行器飞行路径的第一参数，基于第一参数计算稳定逼近值，接收指示飞机湍流的第二参数，基于第二参数计算湍流因子;计算基于稳定逼近值和湍流因子的安全着陆值，将安全着陆值与阈值进行比较，并在安全着陆值不能达到阈值时提供飞机警告。

6. 发明申请

US20150291287A1 AUTOTHROTTLE RETARD CONTROL 有权
标题翻译：自动后退控制
公开(公告)号：US20150291287A1
公开(公告)日：2015-10-15
申请号：US14251533
申请日：2014-04-11
申请人： SAFE FLIGHT INSTRUMENT CORPORATION
发明人： Randall A. GREENE , Shawn P. BEYER
IPC分类号： B64D31/06 , G05D1/00
CPC分类号： B64D31/06 , G01C5/005 , G01S13/882 , G05D1/0055 , G05D1/0676 , G05D1/101
摘要： An autothrottle retard initiation method includes receiving an aircraft's ground speed, receiving the aircraft's vertical speed, determining autothrottle retard initiation height based on the aircraft's ground speed, the aircraft's vertical speed, and an aircraft vertical landing speed factor, receiving the aircraft's height above ground, and initiating autothrottle retard when the aircraft's height above ground and the autothrottle retard initiation height are equal.
摘要翻译：自动油门延迟启动方法包括接收飞机的地面速度，接收飞机的垂直速度，基于飞机的地面速度，飞行器的垂直速度和飞机垂直着陆速度因子确定自动油门延迟启动高度，接收飞机的地面高度，并且当飞机高于地面高度和自动油门延迟启动高度相等时启动自动油门延迟。

7. 发明申请

US20190176997A1 AIRCRAFT TORQUE CONTROL DEVICE 审中-公开
公开(公告)号：US20190176997A1
公开(公告)日：2019-06-13
申请号：US16219775
申请日：2018-12-13
申请人： Safe Flight Instrument Corporation
发明人： Michael J. LAMBTON , Louis C. SIMONS , Randall A. GREENE
IPC分类号： B64D31/04 , B64D31/06 , B64D31/14
摘要： An electronic aircraft control system and an electronic aircraft control method are provided. In some embodiments, the aircraft control system includes a motor including a rotating shaft, a lever including an axis of rotation, the lever connected to the rotating shaft, wherein the position of the lever is not maintained by a mechanical clutch during normal operations. In some embodiments, the aircraft control system includes a fail-safe system for maintaining mechanical friction of the lever in an event of a failure, a sensor identifying a position of the lever, and a transmitter transmitting the lever position to a controller, the controller adjusting an aircraft performance device based on the received lever position. In some embodiments, the motor provides a torque on the lever. In some embodiments, the fail-safe system includes shear pins configured to break when a sufficient amount of manual torque is applied to the lever.

8. 发明申请

US20170008639A1 AIRCRAFT TURBULENCE DETECTION 审中-公开
公开(公告)号：US20170008639A1
公开(公告)日：2017-01-12
申请号：US15056989
申请日：2016-02-29
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
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.

9. 发明申请

US20160033300A1 ARINC 429 DATA SUBSTITUTION 审中-公开
标题翻译： ARINC 429数据替代
公开(公告)号：US20160033300A1
公开(公告)日：2016-02-04
申请号：US14450165
申请日：2014-08-01
申请人： Safe Flight Instrument Corporation
发明人： Randall A. GREENE , Robert D. TETER , Louis SIMONS
IPC分类号： G01C23/00 , B64D43/00
CPC分类号： G01C23/005
摘要： In one embodiment, an aircraft display system includes a first module that identifies a label in an ARINC 429 communication between a flight director and a display, a second module that removes flight director data from the ARINC 429 communication, the flight director data associated with the label, and a third module that inserts substitute data in the ARINC 429 communication. The display receives the substitute data before an error is detected.
摘要翻译：在一个实施例中，飞行器显示系统包括识别飞行指导员和显示器之间的ARINC 429通信中的标签的第一模块，从ARINC 429通信中移除飞行指导者数据的第二模块，与标签，以及在ARINC 429通信中插入替代数据的第三个模块。在检测到错误之前，显示屏接收到替代数据。

10. 发明申请

US20150175270A1 AIRCRAFT LIFT TRANSDUCER 有权
标题翻译：飞机提升传感器
公开(公告)号：US20150175270A1
公开(公告)日：2015-06-25
申请号：US14139566
申请日：2013-12-23
申请人： Safe Flight Instrument Corporation
发明人： Joseph S. TISEO , Randall A. GREENE
IPC分类号： B64D45/00
CPC分类号： B64D45/00 , B64C11/001 , B64C13/50 , B64C15/02 , G01D5/2006 , G01L1/14 , G01M9/06
摘要： An aircraft lift transducer may include a vane, actuator, an LC circuit, and a processor. The vane may be positioned on the leading edge of a wing of the aircraft, where the angle defined by the chord of the wing and the vane changes when the aircraft angle of attack changes. The actuator may be associated with the vane and change position when the angle defined by the vane and the chord changes. The LC circuit may include an induction coil spaced from the actuator and an oscillator. The oscillation frequency of the LC circuit may change when the position of the actuator changes. The processor may receive the change in the oscillation frequency and may determine a corresponding change in an available lift of the aircraft.
摘要翻译：飞机升降传感器可以包括叶片，致动器，LC电路和处理器。叶片可以定位在飞行器的翼的前缘上，当飞行器的迎角发生变化时，由翼的翼和叶片限定的角度改变。当由叶片和弦限定的角度改变时，致动器可以与叶片相关联并且改变位置。 LC电路可以包括与致动器间隔开的感应线圈和振荡器。当执行器的位置改变时，LC电路的振荡频率可能会改变。处理器可以接收振荡频率的变化，并且可以确定飞行器的可用升力的相应变化。

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