公开(公告)号：US20120277936A1

公开(公告)日：2012-11-01

申请号：US13452967

申请日：2012-04-23

Applicant: Veeresh Kumar MN ,  Dinesh Kumar KUSHWAHA ,  Chaitanya Pavan KUMAR

Inventor： Veeresh Kumar MN ,  Dinesh Kumar KUSHWAHA ,  Chaitanya Pavan KUMAR

IPC: G05D1/06

CPC classification number: G05D1/0676

Abstract: A system and method for aircraft performance predictions for descent and approach phases are disclosed. In one embodiment, cruise computation is stopped substantially around a default distance from a destination. Further, current predicted aircraft state is determined using a total energy of the aircraft starting from the default distance. Furthermore, descent and approach phase profiles are computed using the determined current predicted aircraft state. In addition, the aircraft performance predictions are obtained using the computed descent and approach phase profiles.

Abstract translation: 公开了用于下降和接近阶段的飞机性能预测的系统和方法。 在一个实施例中，巡航计算基本上围绕目的地的默认距离停止。 此外，使用从默认距离开始的飞机的总能量来确定当前预测的飞行器状态。 此外，使用确定的当前预测的飞行器状态来计算下降和进近相位轮廓。 此外，使用计算的下降和进近阶段轮廓获得飞机性能预测。

公开(公告)号：US09442490B2

公开(公告)日：2016-09-13

申请号：US13452967

申请日：2012-04-23

Applicant: Veeresh Kumar Mn ,  Dinesh Kumar Kushwaha ,  Chaitanya Pavan Kumar

Inventor： Veeresh Kumar Mn ,  Dinesh Kumar Kushwaha ,  Chaitanya Pavan Kumar

IPC: G05D1/06

CPC classification number: G05D1/0676

Abstract: A system and method for aircraft performance predictions for descent and approach phases are disclosed. In one embodiment, cruise computation is stopped substantially around a default distance from a destination. Further, current predicted aircraft state is determined using a total energy of the aircraft starting from the default distance. Furthermore, descent and approach phase profiles are computed using the determined current predicted aircraft state. In addition, the aircraft performance predictions are obtained using the computed descent and approach phase profiles.

Abstract translation: 公开了用于下降和接近阶段的飞机性能预测的系统和方法。 在一个实施例中，巡航计算基本上围绕目的地的默认距离停止。 此外，使用从默认距离开始的飞机的总能量来确定当前预测的飞行器状态。 此外，使用确定的当前预测的飞行器状态来计算下降和进近相位轮廓。 此外，使用计算的下降和进近阶段轮廓获得飞机性能预测。

公开(公告)号：US20120277935A1

公开(公告)日：2012-11-01

申请号：US13459092

申请日：2012-04-28

Applicant: Veeresh Kumar MN ,  Dinesh Kumar Kushwaha ,  Chaitanya Pavan Kumar

Inventor： Veeresh Kumar MN ,  Dinesh Kumar Kushwaha ,  Chaitanya Pavan Kumar

IPC: G06F17/00

CPC classification number: G01C23/00 ,  G05D1/0083 ,  G05D1/0661

Abstract: A system and method for aircraft performance predictions for climb flight phase is disclosed. In one embodiment, a method of aircraft performance predictions for climb flight phase in a flight management system (FMS) includes determining current predicted aircraft state using a total energy of the aircraft. Further, excess energy available in an engine of the aircraft is computed. Furthermore, a change of speed of the aircraft is computed at a given point in the climb flight phase. Kinetic energy (KE) change required is then computed for the computed speed change. Remaining energy available is then computed based on the computed KE change. The aircraft performance predictions for the climb flight phase are then computed using the determined current predicted aircraft state.

Abstract translation: 公开了一种用于飞机飞行阶段的飞机性能预测的系统和方法。 在一个实施例中，用于飞行管理系统（FMS）中的爬升飞行阶段的飞机性能预测的方法包括使用飞行器的总能量确定当前预测的飞行器状态。 此外，计算飞机发动机中可用的多余能量。 此外，在爬升飞行阶段的给定点计算飞机的速度变化。 然后计算所计算的速度变化所需的动能（KE）变化。 然后根据计算的KE变化计算剩余剩余能量。 然后使用确定的当前预测飞行器状态来计算爬升飞行阶段的飞机性能预测。

公开(公告)号：US08909395B2

公开(公告)日：2014-12-09

申请号：US13459092

申请日：2012-04-28

Applicant: Veeresh Kumar Mn ,  Dinesh Kumar Kushwaha ,  Chaitanya Pavan Kumar

Inventor： Veeresh Kumar Mn ,  Dinesh Kumar Kushwaha ,  Chaitanya Pavan Kumar

IPC: G06F19/00 ,  G01C23/00 ,  G05D1/06 ,  G05D1/00

CPC classification number: G01C23/00 ,  G05D1/0083 ,  G05D1/0661

Abstract: A system and method for aircraft performance predictions for climb flight phase is disclosed. In one embodiment, a method of aircraft performance predictions for climb flight phase in a flight management system (FMS) includes determining current predicted aircraft state using a total energy of the aircraft. Further, excess energy available in an engine of the aircraft is computed. Furthermore, a change of speed of the aircraft is computed at a given point in the climb flight phase. Kinetic energy (KE) change required is then computed for the computed speed change. Remaining energy available is then computed based on the computed KE change. The aircraft performance predictions for the climb flight phase are then computed using the determined current predicted aircraft state.

Abstract translation: 公开了一种用于飞机飞行阶段的飞机性能预测的系统和方法。 在一个实施例中，用于飞行管理系统（FMS）中的爬升飞行阶段的飞机性能预测的方法包括使用飞行器的总能量确定当前预测的飞行器状态。 此外，计算飞机发动机中可用的多余能量。 此外，在爬升飞行阶段的给定点计算飞机的速度变化。 然后计算所计算的速度变化所需的动能（KE）变化。 然后根据计算的KE变化计算剩余剩余能量。 然后使用确定的当前预测飞行器状态来计算爬升飞行阶段的飞机性能预测。