公开(公告)号：WO2010127966A3

公开(公告)日：2010-11-11

申请号：PCT/EP2010/055652

申请日：2010-04-27

Applicant: AIRBUS ENGINEERING CENTRE INDIA ,  CHEVALIER, Thierry

Inventor： CHEVALIER, Thierry

IPC: G09B9/00

Abstract: A system and method for collaborative building of a shared self-refining surrogate model for engineering simulations are disclosed. In one embodiment, a method includes running a reduced order engineering simulation model on a complex system, and querying a shared self-refining surrogate model upon receiving a request for a higher order simulation for a reduced order simulated item. The method also includes estimating a required higher order simulation result having a desired confidence interval for the reduced order simulated item, and determining whether the required higher order simulation result having the desired confidence interval is in the shared self-refining surrogate model. If not, then the method includes performing the higher order simulation to obtain the required higher order simulation result, enriching the shared self-refining surrogate model with the obtained higher order simulation result, and sending the obtained higher order simulation result to the reduced order engineering simulation model.

Abstract translation: 公开了一种用于工程模拟的共享自精细替代模型的协作构建的系统和方法。 在一个实施例中，一种方法包括在复杂系统上运行降阶工程仿真模型，并且在接收到针对降阶模拟物品的更高阶模拟的请求时查询共享自精细替代模型。 该方法还包括估计具有降阶模拟项目的期望置信区间的所需更高阶模拟结果，以及确定具有期望置信区间的所需更高阶模拟结果是否处于共享自细化替代模型中。 如果不是，那么该方法包括执行高阶模拟以获得所需的高阶模拟结果，利用所获得的高阶模拟结果丰富共享自精细替代模型，并且将获得的高阶模拟结果发送到降阶工程 仿真模型。

公开(公告)号：WO2011027358A2

公开(公告)日：2011-03-10

申请号：PCT/IN2010/000480

申请日：2010-07-19

Applicant: AIRBUS ENGINEERING CENTRE INDIA ,  NARASIMHULU, Veeresh Kumar Masaru ,  KUSHWAHA, Dinesh, Kumar

Inventor： NARASIMHULU, Veeresh Kumar Masaru ,  KUSHWAHA, Dinesh, Kumar

IPC: G06F19/00

CPC classification number: G01C23/00 ,  G08G5/0056

Abstract: A system and method for generating an equi-time point (ETP) for an emergency landing of an aircraft are disclosed. In one aspect, a method of a flight management system (FMS) of an aircraft for generating an 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: 公开了一种用于产生飞机紧急着陆的等时点（ETP）的系统和方法。 一方面，一种用于生成用于飞机的紧急着陆的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。

公开(公告)号：WO2011027357A2

公开(公告)日：2011-03-10

申请号：PCT/IN2010/000478

申请日：2010-07-19

Applicant: AIRBUS ENGINEERING CENTRE INDIA ,  NARASIMHULU, Veeresh Kumar Masaru ,  KUSHWAHA, Dinesh, Kumar

Inventor： NARASIMHULU, Veeresh Kumar Masaru ,  KUSHWAHA, Dinesh, Kumar

IPC: 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: 公开了一种用于动态计算飞机的等距点（EDP）的系统和方法。 在一个实施例中，一种用于动态计算飞机的EDP的方法包括：接收至少两个参考点以在发生紧急情况时着陆飞机;基于飞机的当前位置确定飞机的剩余飞行路径;以及 飞行计划由飞机的飞行管理系统（FMS）提供服务，并且通过在与至少两个参考点等距离的剩余飞行路径上定位一个点来产生飞机的EDP。

公开(公告)号：WO2014054056A2

公开(公告)日：2014-04-10

申请号：PCT/IN2013/000605

申请日：2013-10-04

Applicant: AIRBUS ENGINEERING CENTRE INDIA

Inventor： JAIN, Mayank ,  KUMAR, Ravi Shankar

IPC: G01C21/34

CPC classification number: G08G5/0034 ,  G01C23/00 ,  G01C23/005

Abstract: A system and method for maximizing displaying of trajectory elements in an edit area of a navigational display are disclosed. In one embodiment, navigational display parameters are obtained from a cockpit display system. Further, flight plan information is obtained from a flight management system (FMS). Furthermore, a portion of the flight plan information which lies within the edit area of the navigation display is dynamically determined using the navigational display parameters. In addition, a display buffer is dynamically populated with only the determined portion of the flight plan information. Moreover, any needed data that is in the determined portion of the flight plan information is dynamically refreshed in the display buffer. Also, the flight plan information is dynamically displayed on the edit area of the navigation display using the refreshed and populated flight plan information and the needed data.

Abstract translation: 公开了一种用于使导航显示器的编辑区域中的轨迹元素的显示最大化的系统和方法。 在一个实施例中，从驾驶舱显示系统获得导航显示参数。 此外，从飞行管理系统（FMS）获得飞行计划信息。 此外，使用导航显示参数动态地确定位于导航显示器的编辑区域内的飞行计划信息的一部分。 另外，只有确定的飞行计划信息的部分，动态地填充显示缓冲器。 此外，在显示缓冲器中动态地刷新在飞行计划信息的确定部分中的任何需要的数据。 此外，飞行计划信息使用刷新和填充的飞行计划信息和所需的数据动态显示在导航显示器的编辑区域上。

公开(公告)号：WO2014027366A2

公开(公告)日：2014-02-20

申请号：PCT/IN2013/000488

申请日：2013-08-08

Applicant: AIRBUS ENGINEERING CENTRE INDIA

Inventor： SINGH, Abhay ,  BHASKARAN, Srinivasan ,  NARAYAN, Vishal ,  KATAKAM, Ramakrishna ,  SHANMUGAM, Mahadevan

IPC: G06F19/00

CPC classification number: G06F17/509 ,  G06F2217/36

Abstract: A system and method for analyzing arrangement of vehicle and building wire harnesses for electromagnetic interference (EMI) are disclosed. In one embodiment, at least design data of a first wire harness and a second wire harness and associated electrical structure of the vehicle or building are received. Further, a plurality of cutting planes are applied to intersect at least the first wire harness and the second wire harness and the associated electrical structure based on the design data. Furthermore, a respective set of cutting points are identified for each of the plurality of cutting planes. The respective set of cutting points includes locations where a respective cutting plane intersects at least the first wire harness and the second wire harness and the associated electrical structure. In addition, a segregation distance is measured between each respective set of cutting points.

Abstract translation: 公开了一种用于分析车辆和建筑物线束的电磁干扰（EMI）的布置的系统和方法。 在一个实施例中，至少接收车辆或建筑物的第一线束和第二线束以及相关联的电气结构的设计数据。 此外，基于设计数据，施加多个切割平面以至少交叉第一线束和第二线束以及相关的电气结构。 此外，针对多个切割平面中的每一个识别相应的一组切割点。 各组切割点包括相应的切割平面至少与第一线束和第二线束以及相关的电气结构相交的位置。 另外，在每组相应的切割点之间测量分隔距离。

公开(公告)号：WO2011033525A2

公开(公告)日：2011-03-24

申请号：PCT/IN2010/000550

申请日：2010-08-19

Applicant: SHARMA, H.K., Anurag ,  AIRBUS ENGINEERING CENTRE INDIA

Inventor： SHARMA, H.K., Anurag

IPC: B64D13/04

CPC classification number: B64D10/00 ,  A61M16/0051 ,  A61M16/024 ,  A61M16/12 ,  A61M16/125 ,  A61M16/20 ,  A61M16/207 ,  A61M2016/0027 ,  A61M2202/0208 ,  A61M2205/3358 ,  A61M2230/205 ,  A62B7/14 ,  A62B9/006 ,  B64D2231/02 ,  A61M2230/005

Abstract: A system and method for an adaptable oxygen regulator with an electronic control device is disclosed. In one embodiment, an oxygen regulator system includes an electronic control device which includes a non-volatile memory for storing a first reference point. The electronic control device also includes a pressure sensor configured for generating pressure data of the pressurized aircraft cabin. The electronic control device further includes a logical control unit for generating a control signal by processing the first reference point and the pressure data. Further, the electronic control unit includes a rotary actuator for generating a rotary displacement based on the control signal. Moreover, the oxygen regulator system includes a demand dilution oxygen regulator coupled to the electronic control unit and configured to control the supply of oxygen and the flow of dilution air from the pressurized aircraft cabin based on the control signal.

Abstract translation: 公开了一种用于具有电子控制装置的可适应的氧气调节器的系统和方法。 在一个实施例中，氧气调节器系统包括电子控制装置，该电子控制装置包括用于存储第一参考点的非易失性存储器。 该电子控制装置还包括压力传感器，该压力传感器被配置用于产生加压的飞机机舱的压力数据 电子控制装置还包括逻辑控制单元，用于通过处理第一参考点和压力数据来产生控制信号。 此外，电子控制单元包括用于基于控制信号产生旋转位移的旋转致动器。 此外，氧气调节器系统包括需求稀释氧气调节器，该需求稀释氧气调节器连接到电子控制单元并且被配置为基于控制信号来控制来自加压的飞机机舱的氧气供应和稀释空气的流动。

公开(公告)号：WO2010055017A2

公开(公告)日：2010-05-20

申请号：PCT/EP2009/064861

申请日：2009-11-09

Applicant: AIRBUS ENGINEERING CENTRE INDIA ,  AIRBUS OPERATIONS SAS ,  BHASKARAN, Srinivasan ,  SINGH, Raj Kumar ,  NARAYAN, Vishal ,  KATAKAM, Ramakrishna ,  MANGLOTRA, Sumeet Singh ,  ROY, Aloke ,  MONNERET, Clement

Inventor： BHASKARAN, Srinivasan ,  SINGH, Raj Kumar ,  NARAYAN, Vishal ,  KATAKAM, Ramakrishna ,  MANGLOTRA, Sumeet Singh ,  ROY, Aloke ,  MONNERET, Clement

IPC: G06Q10/00

CPC classification number: G06F17/50 ,  G06Q10/06

公开(公告)号：WO2015097708A1

公开(公告)日：2015-07-02

申请号：PCT/IN2013/000803

申请日：2013-12-26

Applicant: AIRBUS ,  AIRBUS ENGINEERING CENTRE INDIA

Inventor： GOWDA, Netra ,  KRISHNAMOHAN, Ajit ,  LOUBIERE, Vincent

IPC: B64D11/00 ,  B64D45/00

CPC classification number: B25J9/06 ,  B64D11/00 ,  B64D45/00 ,  B64D2045/0075 ,  F16M11/105 ,  F16M11/18 ,  F16M11/2035 ,  F16M13/02

Abstract: An aircraft part, such as a cockpit or cabin, comprising a support structure and a robot arm (7). The robot arm has a proximal end (10) attached to the support structure and a distal end adapted to hold a electronic device (8). An actuation system is arranged to drive the robot arm so that the distal end of the robot arm moves relative to the support structure. A memory contains data, and a controller is programmed to drive the actuation system according to the data in the memory in order to move the distal end of the robot arm to a position determined by the data in the memory. The robot arm comprises a "snake-arm" with three or more links connected by a series of two or more joints, each joint connecting together a respective adjacent pair of the links and permitting relative rotation between the adjacent pair of links. The actuation system is arranged to move the distal end of the robot arm by causing a relative rotation between the links about their joints.

Abstract translation: 包括支撑结构和机器人手臂（7）的飞行器部件，例如驾驶舱或驾驶室。 机器人臂具有附接到支撑结构的近端（10）和适于保持电子设备（8）的远端。 驱动系统被布置成驱动机器人臂，使得机器人臂的远端相对于支撑结构移动。 存储器包含数据，并且控制器被编程为根据存储器中的数据来驱动致动系统，以便将机器人臂的远端移动到由存储器中的数据确定的位置。 机器人臂包括具有三个或更多个连杆的“蛇形臂”，该链条通过一系列两个或更多个接头连接，每个接头连接相应的相邻的一对连杆并允许相邻的一对连杆之间的相对转动。 致动系统被布置成通过使链节围绕其关节相对旋转来移动机器人手臂的远端。

公开(公告)号：WO2014192003A1

公开(公告)日：2014-12-04

申请号：PCT/IN2013/000337

申请日：2013-05-27

Applicant: AIRBUS ENGINEERING CENTRE INDIA ,  PATEL, Soham, Narayan ,  CHAUDHARI, Amit ,  DWIVEDI, Abhishek ,  GONZALEZ, Rubio, Jorge

Inventor： PATEL, Soham, Narayan ,  CHAUDHARI, Amit ,  DWIVEDI, Abhishek ,  GONZALEZ, Rubio, Jorge

IPC: G06F17/10

CPC classification number: G06F17/5018 ,  G06F17/10 ,  G06F17/16

Abstract: System and method of converting geometric entities of 1D elements in a finite element model (FEM) from a source finite element analysis (FEA) tool format to a destination FEA tool format is disclosed. In one embodiment, coordinates of all the geometric entities associated with each 1D element in the FEM are transformed from the source FEA tool format to a global coordinate system. The geometric entities of the 1D elements in the FEM are then converted from the source FEA tool format to the destination FEA tool format using the transformed coordinates of all the geometric entities associated with each 1D element.

Abstract translation: 公开了将有限元模型（FEM）中的1D元素的几何实体从源有限元分析（FEA）工具格式转换为目标FEA工具格式的系统和方法。 在一个实施例中，与FEM中的每个1D元素相关联的所有几何实体的坐标从源FEA工具格式变换为全局坐标系。 然后使用与每个1D元素相关联的所有几何实体的变换坐标，将FEM中的1D元素的几何实体从源FEA工具格式转换为目标FEA工具格式。

公开(公告)号：WO2014027365A1

公开(公告)日：2014-02-20

申请号：PCT/IN2013/000481

申请日：2013-08-05

Applicant: AIRBUS ENGINEERING CENTRE INDIA

Inventor： TIWARI, Punit ,  RAJPUT, Arun ,  REDDY, Madhusudhana

IPC: G06F7/60

CPC classification number: G06F17/50 ,  G06F17/10 ,  G06F17/5095 ,  G06F2217/80

Abstract: A system and method for computing design parameters for a thermally comfortable environment is disclosed. In one embodiment, a surface heat transfer coefficient (hea1) is obtained for each body part of one or more thermal manikins in a uniform thermal environment by performing a 1 D numerical analysis on the uniform thermal environment based on a given set of boundary conditions for the uniform thermal environment. Further, equivalent temperature (teq) limits for each body part corresponding to the thermal comfort limits are obtained from known design standards.

Abstract translation: 公开了一种用于计算热舒适环境的设计参数的系统和方法。 在一个实施例中，在均匀热环境中通过对均匀热环境进行1D数值分析，基于给定的一组边界条件为一个或多个热人体模型的每个身体部分获得表面传热系数（hea1） 均匀的热环境。 此外，从已知的设计标准中获得与热舒适度相对应的每个主体部件的等效温度（teq）极限。