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公开(公告)号：US08249792B2
公开(公告)日：2012-08-21
申请号：US12575286
申请日：2009-10-07
IPC分类号： G06F19/00
CPC分类号： B64D31/06 , G05D1/0072
摘要： Disclosed is a method and device for protecting an aircraft comprising at least one wing-mounted engine arranged on each of its wings against at least one of a low-energy situation and a high-energy situation during flight in which at least one engine is a failed engine. A control unit is triggered to activate a protection function, as a function of the number and position of failed engines. The control unit controls at least one non-failed engine, and the protection function is activated when activation conditions are met. The activation conditions indicate that the aircraft is either in the low-energy situation such that the total current power of the aircraft is less than a predetermined minimum power or that the aircraft is in the high-energy situation such that the total current power of the aircraft is greater than a predetermined maximum total power.
摘要翻译： 公开了一种用于保护飞行器的方法和装置，其包括布置在其每个翼上的至少一个机翼安装的发动机，以抵抗飞行中的低能量情况和高能量情况中的至少一个，其中至少一个发动机是 发动机失效 触发控制单元以根据故障发动机的数量和位置来激活保护功能。 控制单元控制至少一个非故障发动机，并且当满足激活条件时激活保护功能。 激活条件表明飞机处于低能量状态，使得飞机的总电流功率小于预定的最小功率，或者飞机处于高能量状态，使得飞行器的总电流功率 飞机大于预定的最大总功率。
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公开(公告)号：US20100100262A1
公开(公告)日：2010-04-22
申请号：US12575286
申请日：2009-10-07
IPC分类号： G06F19/00
CPC分类号： B64D31/06 , G05D1/0072
摘要： According to the invention, an aircraft speed threshold is computed in order to calculate a total power to apply to aircraft engines. When conditions of activation are fulfilled, the current individual power of each aircraft engine in operation controlled by a protection function is gradually modified.
摘要翻译： 根据本发明，计算飞行器速度阈值以计算应用于飞机发动机的总功率。 当满足激活条件时，由保护功能控制的每个飞机发动机的当前单独功率逐渐改变。
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公开(公告)号：US08155866B2
公开(公告)日：2012-04-10
申请号：US12422542
申请日：2009-04-13
IPC分类号： G06F19/00
CPC分类号： G05D1/0202 , G08G5/0039 , G08G5/0052
摘要： Disclosed is a method and device for guiding an aircraft flying along a flight trajectory. The flight trajectory has at least one constrained section, and the aircraft flies at a required speed within the constrained section to comply with a required arrival time at a predetermined waypoint in the constrained section. Auxiliary speed setpoints are determined to guide the aircraft to arrive at an auxiliary arrival tune at an auxiliary waypoint, with the auxiliary speed setpoints being applied by a guidance system to guide the aircraft.
摘要翻译： 公开了一种用于引导飞行器沿飞行轨迹飞行的方法和装置。 飞行轨迹具有至少一个约束部分，并且飞机以受限部分内的所需速度飞行，以符合约束部分中预定航路点处的所需到达时间。 确定辅助转速设定值以引导飞机在辅助通路点处到达辅助到达曲线，辅助转速设定点由引导系统施加以引导飞行器。
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