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11. 发明申请

US20150123821A1 TAILSTRIKE WARNING SYSTEM 有权
标题翻译： TAILSTRIKE警告系统
公开(公告)号：US20150123821A1
公开(公告)日：2015-05-07
申请号：US14072732
申请日：2013-11-05
申请人： Safe Flight Instrument Corporation
发明人： Randall A. GREENE , Shawn BEYER
IPC分类号： B64D45/04
CPC分类号： B64D45/04 , B64D43/00 , G01C23/005 , G08G5/0021 , G08G5/025
摘要： An aircraft tailstrike warning method includes identifying a first value representing an aircraft angle of attack, identifying a second value representing a maximum aircraft angle of attack, identifying a difference between the first value and the second value, and providing a tailstrike warning when the difference between the first value and the second value is less than a threshold amount.
摘要翻译：飞机尾注警报方法包括识别表示飞机迎角的第一值，识别表示最大飞机迎角的第二值，识别第一值与第二值之间的差值，以及当第一值与第二值之间的差值第一值和第二值小于阈值量。

12. 发明申请

US20150084792A1 ANGLE OF ATTACK DISPLAY 有权
标题翻译：攻击角度
公开(公告)号：US20150084792A1
公开(公告)日：2015-03-26
申请号：US14032840
申请日：2013-09-20
申请人： Safe Flight Instrument Corporation
发明人： Arthur C. BARTH , Randall A. GREENE , Louis SIMONS , Darren TAILLIE
IPC分类号： B64D43/02
CPC分类号： B64D43/02 , G01D1/00 , G01D7/02
摘要： An aircraft safety system includes a Stall/Spin Warning & Recovery Computer, an angle of attack sensor, a side slip sensor and an angle of attack display. The Stall/Spin Warning and Recovery Computer detects whether the aircraft is in a safe condition or an unsafe condition. The angle of attack display includes a first configuration that displays information indicative of safe aircraft condition when the orientation detector detects a safe condition and a second configuration that displays information indicative of unsafe aircraft condition when the computer detects an unsafe condition. The display may transition from the first configuration to the second configuration when the orientation detector detects an unsafe condition and then to a third configuration, which may include visual control-input instructions that enable recovery to a safe condition.
摘要翻译：飞机安全系统包括失速/旋转警告和恢复计算机，攻角传感器，侧滑传感器和迎角显示。失速/旋转警告和恢复计算机检测飞机是否处于安全状态或不安全状态。所述迎角显示包括当所述方向检测器检测到安全状态时显示指示安全飞行器状况的信息的第一配置和当所述计算机检测到不安全状态时显示指示不安全飞行器状况的信息的第二配置。当定向检测器检测到不安全状况，然后到第三配置时，显示器可以从第一配置转变到第二配置，其中可以包括能够恢复到安全状态的视觉控制输入指令。

13. 发明申请

US20140172202A1 SYSTEMS AND METHODS FOR SAFELY LANDING AN AIRCRAFT 有权
标题翻译：用于安全飞机的系统和方法
公开(公告)号：US20140172202A1
公开(公告)日：2014-06-19
申请号：US13715866
申请日：2012-12-14
申请人： SAFE FLIGHT INSTRUMENT CORPORATION
发明人： Randall A. GREENE
IPC分类号： B64D45/04 , B64D31/06 , G01C5/00 , G01S13/88
CPC分类号： B64D45/04 , B64D31/06 , G01C5/005 , G01C5/06 , G01S13/882 , G05D1/0676
摘要： A system for safely landing an aircraft including a low range radio altimeter, a barometric altimeter, and an autothrottle control. The low range radio altimeter calculates a first height of the aircraft above ground-level, the barometric altimeter calculates a second height of the aircraft above ground-level, and the autothrottle control determines if the first height and the second height do not correlate. If the first and second heights are determined to lack correlation, then automatic thrust-control of the aircraft is stopped. In some embodiments, the second height is partially calculated by accessing a ground elevation database to obtain an elevation of the ground above sea level and determining a difference between the elevation of the ground above sea level and an elevation of the aircraft above sea level.
摘要翻译：一种用于安全着陆飞机的系统，包括低范围无线电高度计，气压高度计和自动油门控制。低范围无线电高度计计算地面以上的飞机的第一高度，气压高度计计算地面以上的飞机的第二高度，自动油门控制确定第一高度和第二高度是否不相关。如果第一和第二高度被确定为缺乏相关性，则停止飞机的自动推力控制。在一些实施例中，通过进入地面高程数据库部分地计算第二高度，以获得海拔高度的地面高程，并且确定海拔以上的地面高程与海拔高度之间的差异。

14. 发明申请

US20140166813A1 DETECTION OF ICING CONDITIONS ON AN AIRCRAFT 有权
标题翻译：检测飞机上的条件
公开(公告)号：US20140166813A1
公开(公告)日：2014-06-19
申请号：US13715911
申请日：2012-12-14
申请人： SAFE FLIGHT INSTRUMENT CORPORATION
发明人： Randall A. GREENE , Peter R. CORDES , Robert D. TETER
IPC分类号： B64D15/20
CPC分类号： B64D15/20
摘要： A controller for determining when icing conditions are present on an outside surface of an aircraft may include a first input receiving a moisture condition on a windshield of the aircraft, a second input receiving an outside temperature, and an output that provides an icing condition determined as a function of the first input and the second input. The moisture condition can be provided by a moisture sensor positioned on an interior surface of the windshield and the windshield may include a heating system.
摘要翻译：用于确定结冰条件何时存在于飞行器的外表面上的控制器可以包括在飞行器的挡风玻璃上接收湿气条件的第一输入，接收外部温度的第二输入和提供结冰条件的输出，所述结冰条件被确定为第一输入和第二输入的功能。湿度条件可以由位于挡风玻璃的内表面上的湿度传感器提供，并且挡风玻璃可以包括加热系统。

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