公开(公告)号：US20120130564A1

公开(公告)日：2012-05-24

申请号：US13388060

申请日：2010-07-19

Applicant: Veeresh Kumar Masaru Narasimhulu ,  Dinesh Kumar Kushwaha

Inventor： Veeresh Kumar Masaru Narasimhulu ,  Dinesh Kumar Kushwaha

IPC: G05D1/00 ,  G06F19/00

CPC classification number: G01C23/00

Abstract: A system and method for dynamically computing an equi-distance point (EDP) for aircrafts is disclosed. In one embodiment, a method for dynamically computing an EDP for an aircraft includes receiving at least two reference points for landing the aircraft upon an occurrence of an emergency, determining a remaining flight path for the aircraft based on a current location of the aircraft and a flight plan serviced by a flight management system (FMS) of the aircraft, and generating the EDP for the aircraft by locating a point on the remaining flight path which is equidistant from the at least two reference points.

Abstract translation: 公开了一种动态计算飞机等距点（EDP）的系统和方法。 在一个实施例中，用于动态地计算飞行器的EDP的方法包括接收至少两个用于在发生紧急情况时着陆飞行器的参考点，基于飞行器的当前位置确定飞行器的剩余飞行路径，以及 由飞行器的飞行管理系统（FMS）服务的飞行计划，并且通过在与至少两个参考点等距的剩余飞行路径上找到点来生成飞行器的EDP。

公开(公告)号：US20120109428A1

公开(公告)日：2012-05-03

申请号：US13379667

申请日：2010-07-19

Applicant: Veeresh Kumar Masaru Narasimhulu ,  Dinesh Kumar Kushwaha

Inventor： Veeresh Kumar Masaru Narasimhulu ,  Dinesh Kumar Kushwaha

IPC: G05D1/00

CPC classification number: G01S5/0284 ,  G08G5/0052

Abstract: A system and method for computing flight time from an equi-distance point (EDP) to a reference point is disclosed. In one embodiment, a method of a flight management system (FMS) of an aircraft for computing flight time from an EDP to a reference point for an emergency landing of the aircraft includes receiving at least two reference points for landing the aircraft upon an occurrence of an emergency and determining a remaining flight path for the aircraft based on a current location of the aircraft and a flight plan serviced by the FMS. Further, the method includes generating the EDP for the aircraft by locating a point in the remaining flight path, and calculating an expected flight time of the aircraft from the EDP to each of the at least two reference points based on a plurality of factors affecting the flight time of the aircraft.

Abstract translation: 公开了一种用于计算从等距点（EDP）到参考点的飞行时间的系统和方法。 在一个实施例中，用于计算从EDP到用于飞机的紧急着陆的参考点的飞行时间的飞行器的飞行管理系统（FMS）的方法包括：接收至少两个用于在飞行器发生时着陆的参考点 紧急情况并根据飞机的当前位置确定飞机的剩余飞行路线以及由飞行时间表管理系统提供的飞行计划。 此外，该方法包括通过在剩余飞行路径中定位一个点来生成飞行器的EDP，并且基于影响到该飞行器的多个因素来计算飞行器从EDP到每个至少两个参考点的预期飞行时间 飞机的飞行时间。

公开(公告)号：US08463468B2

公开(公告)日：2013-06-11

申请号：US13379667

申请日：2010-07-19

Applicant: Veeresh Kumar Masaru Narasimhulu ,  Dinesh Kumar Kushwaha

Inventor： Veeresh Kumar Masaru Narasimhulu ,  Dinesh Kumar Kushwaha

IPC: G06F19/00

CPC classification number: G01S5/0284 ,  G08G5/0052

Abstract: A method of a flight management system (FMS) of an aircraft for computing flight time from an equi-distance point (EDP to a reference point for an emergency landing of the aircraft includes receiving at least two reference points for landing the aircraft upon an occurrence of an emergency and determining a remaining flight path for the aircraft based on a current location of the aircraft and a flight plan serviced by the FMS. Further, the method includes generating the EDP for the aircraft by locating a point in the remaining flight path, and calculating an expected flight time of the aircraft from the EDP to each of the at least two reference points based on a plurality of factors affecting the flight time of the aircraft.

Abstract translation: 一种飞行器的飞行管理系统（FMS）的方法，用于计算从等距离点（EDP到飞机的紧急着陆的参考点）的飞行时间，包括在发生时接收至少两个用于着陆飞机的参考点 并且根据飞行器的当前位置确定飞行器的剩余飞行路径，以及由飞行器管理系统维护的飞行计划，还包括通过在剩余飞行路径中定位一个点来生成飞机的EDP， 以及基于影响飞行器的飞行时间的多个因素，计算飞行器从EDP到所述至少两个参考点中的每一个的预期飞行时间。

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。

公开(公告)号：US08442704B2

公开(公告)日：2013-05-14

申请号：US13388060

申请日：2010-07-19

Applicant: Veeresh Kumar Masaru Narasimhulu ,  Dinesh Kumar Kushwaha

Inventor： Veeresh Kumar Masaru Narasimhulu ,  Dinesh Kumar Kushwaha

IPC: G06F17/00

CPC classification number: G01C23/00

Abstract: A method for dynamically computing an equi-distance point (EDP) for an aircraft includes receiving at least two reference points for landing the aircraft upon an occurrence of an emergency, determining a remaining flight path for the aircraft based on a current location of the aircraft and a flight plan serviced by a flight management system (FMS) of the aircraft, and generating the EDP for the aircraft by locating a point on the remaining flight path which is equidistant from the at least two reference points.

Abstract translation: 一种用于动态地计算飞行器的等距点（EDP）的方法包括：在发生紧急情况时接收至少两个用于着陆飞行器的参考点，基于飞机的当前位置确定飞行器的剩余飞行路径 以及由所述飞行器的飞行管理系统（FMS）服务的飞行计划，以及通过在与所述至少两个参考点等距的剩余飞行路径上定位点来生成所述飞行器的EDP。

公开(公告)号：US08467916B2

公开(公告)日：2013-06-18

申请号：US13382289

申请日：2010-07-19

Applicant: Veeresh Kumar Masaru Narasimhulu ,  Dinesh Kumar Kushwaha

Inventor： Veeresh Kumar Masaru Narasimhulu ,  Dinesh Kumar Kushwaha

IPC: G06F17/00

CPC classification number: G01C23/00 ,  G08G5/0056

Abstract: A method of a flight management system (FMS) of an aircraft for generating an equi-time point (ETP) for an emergency landing of the aircraft includes receiving at least two reference points for landing the aircraft upon an occurrence of an emergency. The method also includes determining an equi-distance point (EDP) for the aircraft by locating a first point on the remaining flight path of the aircraft which is equidistant from the at least two reference points. The method further includes generating an ETP for the aircraft by locating a second point on the remaining flight path such that time difference between any two of expected flight times of the aircraft from the second point to the at least two reference points is less than a threshold value.

Abstract translation: 用于生成飞机紧急着陆的等时点（ETP）的飞行器的飞行管理系统（FMS）的方法包括在发生紧急情况时接收至少两个用于着陆飞机的参考点。 该方法还包括通过将飞行器的剩余飞行路径上的第一点与至少两个参考点等距来确定飞行器的等距离点（EDP）。 该方法还包括通过在剩余飞行路径上定位第二点来生成用于飞行器的ETP，使得飞机从第二点到至少两个参考点的预期飞行时间的任何两个之间的时间差小于阈值 值。