专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明申请

US20140195210A1 Simulation method for determining aerodynamic coefficients of an aircraft 有权
标题翻译：用于确定飞机空气动力学系数的模拟方法
公开(公告)号：US20140195210A1
公开(公告)日：2014-07-10
申请号：US13882446
申请日：2011-11-02
申请人： Benoit Calmels
发明人： Benoit Calmels
IPC分类号： G06F17/50
CPC分类号： G06F17/5009 , G01M9/08 , G05D1/0808 , G06F17/5095 , G06F2217/16
摘要： A computer method of simulating a fluid flow in an aircraft environment to determine at least one aerodynamic coefficient, comprising obtaining a first series of values of the aerodynamic coefficient. The method also includes defining a criterion for convergence of said aerodynamic coefficient, selecting a determined set of terms belonging to said first series, defining a monotonic function configured to make a relatively expanding transformation in said determined set relative to the complement of said set, applying said monotonic function on said first series to form a second series of values of the aerodynamic coefficient, determining said aerodynamic coefficient by plotting a variation curve representative of said second series of values of the aerodynamic coefficient, and displaying said variation curve including an intrinsic zoom of the convergence zone of said aerodynamic coefficient.
摘要翻译：一种在飞行器环境中模拟流体流动以确定至少一个空气动力学系数的计算机方法，包括获得所述空气动力学系数的第一系列值。该方法还包括定义用于所述空气动力学系数的收敛的标准，选择属于所述第一系列的确定的一组项，定义单调函数，其被配置为相对于所述组的互补进行相对扩大的变换，应用所述第一系列的所述单调功能形成第二系列的空气动力系数值，通过绘制表示所述第二系列气动系数值的变化曲线来确定所述空气动力学系数，并显示所述变化曲线，所述变化曲线包括：所述空气动力系数的会聚区。

2. 发明申请

US20090314076A1 HYBRID METHOD FOR ESTIMATING THE GROUND EFFECT ON AN AIRCRAFT 有权
标题翻译：估计航空器接地效应的混合方法
公开(公告)号：US20090314076A1
公开(公告)日：2009-12-24
申请号：US12485140
申请日：2009-06-16
申请人： Benoit Calmels
发明人： Benoit Calmels
IPC分类号： G01M9/06
CPC分类号： G01M9/02 , G01M9/06
摘要： A method for assessing the aerodynamic ground effects on an aircraft. The method includes determining the variation of at least one aerodynamic coefficient of the aircraft as a function of the height for a range of heights extending from an aerodynamically infinite height to a zero height. In the method, (i) the range of heights is subdivided into at least two consecutive sets of heights; (ii) for one of the sets of heights, the variation of said aerodynamic coefficient is determined by wind tunnel tests using a model of the aircraft; and (iii) for the other of the sets of heights, the variation of said aerodynamic coefficient is determined by digital simulation reproducing by computation the physical reality of the air flow around said aircraft.
摘要翻译：一种用于评估飞机上的空气动力学地面效应的方法。该方法包括根据从空气动力学无限高度到零高度的高度范围的高度来确定飞机的至少一个空气动力学系数的变化。在该方法中，（i）高度范围被细分为至少两个连续的高度组; （ii）对于一组高度，所述空气动力系数的变化通过使用飞机模型的风洞测试来确定; 和（iii）对于另一组高度，所述空气动力学系数的变化通过计算所述飞行器周围的空气流的物理现实的数字模拟来确定。

3. 发明申请

US20080195262A1 Method and Device for Determining the Width of a Safety Corridor for an Aircraft and Method and System fo Securing the Automatic Low-Altitude Flight of an Aircraft 有权
标题翻译：用于确定飞机安全走廊宽度的方法和装置以及确保飞机自动低空飞行的方法和系统
公开(公告)号：US20080195262A1
公开(公告)日：2008-08-14
申请号：US11813967
申请日：2006-01-30
申请人： Franck Artini , Benoit Calmels
发明人： Franck Artini , Benoit Calmels
IPC分类号： G05D1/02 , G06F17/11 , G01C21/00
CPC分类号： G05D1/0202 , G05D1/0646
摘要： The invention relates to a method and device for determining the width of a safety corridor for an aircraft and to a method and system for securing the automatic low-altitude flight of an aircraft. The inventive device (1) comprises: means (3) which can be used by an operator in order to enter a plurality of errors which each have an impact on the automatic low-altitude flight of the aircraft; means (4) for determining an excursion probability of a safety corridor that is not to be crossed; and means (5) for determining the width of said safety corridor form the aforementioned errors and excursion probability, taking account of at least one mathematical expression linking at least the errors, the excursion probability and the width.
摘要翻译：本发明涉及一种用于确定飞机安全走廊宽度的方法和装置以及用于确保飞机的自动低空飞行的方法和系统。本发明的装置（1）包括：装置（3），其可由操作者使用以输入各自对飞行器的自动低空飞行有影响的多个错误; 指（4）确定安全走廊不偏离的偏移概率; 以及用于确定所述安全走廊的宽度形成上述错误和偏移概率的装置（5），考虑至少一个至少连接错误，偏移概率和宽度的数学表达式。

4. 发明授权

US08386217B2 Method of determining a stiff value of an aerodynamic coefficient 有权
标题翻译：确定空气动力系数刚度值的方法
公开(公告)号：US08386217B2
公开(公告)日：2013-02-26
申请号：US12685924
申请日：2010-01-12
申请人： Benoit Calmels
发明人： Benoit Calmels
IPC分类号： G06F7/60 , G06F17/10
CPC分类号： G01M9/06
摘要： Method for determination of a rigid value of an aerodynamic coefficient of an aircraft, in which measurements are made in a wind tunnel on a model of the said aircraft and, on the basis of these measurements, at least one value, known as flexible model value, of this aerodynamic coefficient is determined, characterized in that a rigid value of the aerodynamic coefficient is calculated on the basis of the said flexible model value(s) and a correction taking into account the flexibility of the model. A plurality of flexible model values is determined on the basis of measurements made by varying the parameter q/E and maintaining the angle of incidence at a constant value, and the correction consists in an extrapolation operation providing a value of the aerodynamic coefficient corresponding to q/E=0. As a variant, a single flexible model is determined and the correction consists in adjusting the said value with the aid of a correction factor.
摘要翻译：用于确定飞机的空气动力系数的刚性值的方法，其中在所述飞行器的模型上的风洞中进行测量，并且在这些测量的基础上，至少一个称为柔性模型值的值确定该空气动力学系数，其特征在于，基于所述柔性模型值和考虑到模型的灵活性的校正来计算空气动力学系数的刚性值。基于通过改变参数q / E并将入射角保持在恒定值进行的测量来确定多个柔性模型值，并且校正包括提供与q相对应的空气动力系数的值的外插操作 / E = 0。作为变型，确定单个柔性模型，并且校正包括借助于校正因子来调整所述值。

5. 发明申请

US20100280802A1 METHOD OF PREDICTING THE AERODYNAMIC BEHAVIOR OF AN AIRCRAFT ELEMENT 有权
标题翻译：预测飞机元素的航空行为的方法
公开(公告)号：US20100280802A1
公开(公告)日：2010-11-04
申请号：US12766465
申请日：2010-04-23
申请人： Benoit CALMELS
发明人： Benoit CALMELS
IPC分类号： G06F7/60 , G06G7/70
CPC分类号： G06F17/5018 , B64F5/00 , G06F17/5095 , G06F2217/16
摘要： The invention relates to a method for predicting the aerodynamic performance of an aircraft element under predetermined conditions, the said aircraft element having at least one break (5) at least partially separating two parts (1, 2) that cannot or should not be modeled with a common envelope form, in which: a digital form representative of the form that the aircraft element assumes under the predetermined conditions studied and in which each break (5) is represented, is created, for each break (5), a totally non-coincident boundary surface (7) at the joining of the two parts (1 and 2) is created, and a partial structured meshing around each part (1, 2) is generated, the two partial meshings made in this way being independent of one another, digital aerodynamic simulation computations using this meshing are carried out with the aid of an aerodynamic computation code capable of processing a totally non-coincident join.
摘要翻译：本发明涉及一种用于在预定条件下预测飞行器元件的空气动力学性能的方法，所述飞行器元件具有至少一个断裂（5），至少部分地分离两个部分（1,2），所述两个部分（1,2）不能或不应该被建模一种常见的信封形式，其中：对于每个断点（5），创建代表在飞机元件根据研究的预定条件下所代表并且其中表示每个断点（5）的形式的数字形式，产生在两部分（1和2）的连接处的重合边界面（7），并且产生围绕每个部分（1,2）的部分结构化网格，这样制成的两个局部网格彼此无关利用这种啮合的数字空气动力学模拟计算借助于能够处理完全不重合的连接的空气动力学计算代码进行。

6. 发明授权

US09317633B2 Simulation method for determining aerodynamic coefficients of an aircraft 有权
标题翻译：用于确定飞机空气动力学系数的模拟方法
公开(公告)号：US09317633B2
公开(公告)日：2016-04-19
申请号：US13882446
申请日：2011-11-02
申请人： Benoit Calmels
发明人： Benoit Calmels
IPC分类号： G01M9/08 , G06F17/50 , G05D1/08
CPC分类号： G06F17/5009 , G01M9/08 , G05D1/0808 , G06F17/5095 , G06F2217/16
摘要： A computer method of simulating a fluid flow in an aircraft environment to determine at least one aerodynamic coefficient, comprising obtaining a first series of values of the aerodynamic coefficient. The method also includes defining a criterion for convergence of said aerodynamic coefficient, selecting a determined set of terms belonging to said first series, defining a monotonic function configured to make a relatively expanding transformation in said determined set relative to the complement of said set, applying said monotonic function on said first series to form a second series of values of the aerodynamic coefficient, determining said aerodynamic coefficient by plotting a variation curve representative of said second series of values of the aerodynamic coefficient, and displaying said variation curve including an intrinsic zoom of the convergence zone of said aerodynamic coefficient.
摘要翻译：一种在飞行器环境中模拟流体流动以确定至少一个空气动力学系数的计算机方法，包括获得所述空气动力学系数的第一系列值。该方法还包括定义用于所述空气动力学系数的收敛的标准，选择属于所述第一系列的确定的一组项，定义单调函数，其被配置为相对于所述组的互补进行相对扩大的变换，应用所述第一系列的所述单调功能形成第二系列的空气动力系数值，通过绘制表示所述第二系列气动系数值的变化曲线来确定所述空气动力学系数，并显示所述变化曲线，所述变化曲线包括：所述空气动力系数的会聚区。

7. 发明申请

US20100256962A1 AERODYNAMIC MODEL IDENTIFICATION PROCESS FOR AIRCRAFT SIMULATION PROCESS 有权
标题翻译：航空模拟过程的航空模型识别过程
公开(公告)号：US20100256962A1
公开(公告)日：2010-10-07
申请号：US12753633
申请日：2010-04-02
申请人： Benoit CALMELS
发明人： Benoit CALMELS
IPC分类号： G06G7/70 , G06F15/18 , G01M9/08
CPC分类号： G06F17/5009 , G06F17/5095
摘要： A method is disclosed of identifying or fixing the value of the parameters (aerodynamic data) of a pre-determined set of equations forming the aerodynamic models of an aircraft in various configurations, so as to minimize the variance between the values anticipated by using these aerodynamic data, and reference data in cases of known configurations, includes the use of learning or optimization methods to determine at least one portion of the parameters' values. The method includes storing database data, choosing an optimization method or a neural network method, breaking the identification down into several partial identifications, carrying out successive partial identifications, validating the values found for the aerodynamic model's parameters or iterating the method according to a threshold criterion determined on the value of variances between the reference data and the values measured by the identified model.
摘要翻译：公开了一种识别或确定形成各种配置的飞行器的空气动力学模型的预定的一组方程的参数值（空气动力学数据）的方法，以便通过使用这些空气动力学来最小化预期值之间的差异数据和参考数据包括使用学习或优化方法来确定参数值的至少一部分。该方法包括存储数据库数据，选择优化方法或神经网络方法，将识别分解成若干部分识别，执行连续的部分识别，验证空气动力学模型参数的值或根据阈值标准迭代该方法确定参考数据与由所识别的模型测量的值之间的差异的值。

8. 发明申请

US20050130627A1 Authentication between a cellular phone and an access point of a short-range network 失效
标题翻译：蜂窝电话与短距离网络接入点之间的认证
公开(公告)号：US20050130627A1
公开(公告)日：2005-06-16
申请号：US10996614
申请日：2004-11-26
申请人： Benoit Calmels , Christophe Maguy , Sebastien Trillaud
发明人： Benoit Calmels , Christophe Maguy , Sebastien Trillaud
IPC分类号： H04L12/56 , H04W12/00 , H04B7/00 , H04M1/66
CPC分类号： H04W12/06 , H04L63/0869 , H04L63/18 , H04L2463/061 , H04W12/04 , H04W84/18 , H04W88/06
摘要： To render secure a connection between an access point of a short-range network and a mobile terminal within a cellular network while precluding acquisition of a PIN code, a platform transmits a confirming message, including a secret code and the access point address retrieved from a terminal request, to the terminal through the cellular network and a connection request message including the secret code and the mobile terminal address to the access point. The access point authenticates the terminal, or the terminals authenticate each other as a function of a session key determined as a function of the secret code retrieved from the connection request message and from the confirming message.
摘要翻译：为了在短距离网络的接入点和蜂窝网络内的移动终端之间建立安全连接，同时阻止获取PIN码，平台发送包括秘密码的确认消息和从一个通过蜂窝网络向终端请求终端，以及向接入点发送包括密码和移动终端地址的连接请求消息。接入点认证终端，或者终端根据从连接请求消息中检索的密码确定的会话密钥和确认消息来进行认证。

9. 发明授权

US08676544B2 Method of predicting the aerodynamic behavior of an aircraft element 有权
标题翻译：预测飞机元件空气动力学行为的方法
公开(公告)号：US08676544B2
公开(公告)日：2014-03-18
申请号：US12766465
申请日：2010-04-23
申请人： Benoit Calmels
发明人： Benoit Calmels
IPC分类号： G06F17/50
CPC分类号： G06F17/5018 , B64F5/00 , G06F17/5095 , G06F2217/16
摘要： A method for predicting the aerodynamic performance of an aircraft element under predetermined conditions, the aircraft element having at least one break at least partially separating two parts that cannot or should not be modeled with a common envelope form, in which: a digital form representative of the form that the aircraft element assumes under the predetermined conditions studied and in which each break is represented, is created, for each break, a totally non-coincident boundary surface at the joining of the two parts is created, and a partial structured meshing around each part is generated, the two partial meshings made in this way being independent of one another, and digital aerodynamic simulation computations using this meshing are carried out with the aid of an aerodynamic computation code capable of processing a totally non-coincident join.
摘要翻译：一种用于在预定条件下预测飞行器元件的空气动力学性能的方法，所述飞行器元件具有至少一个断裂，至少部分地分离两个不能或不应以公共信封形式建模的部分，其中：代表创建了在所研究的预定条件下并且其中表示每个断点的飞行器元件所采取的形式，对于每个断裂，在两个部分的接合处产生完全不重合的边界表面，并且部分结构化地啮合每个部分都被生成，以这种方式制造的两个部分网格彼此独立，并且借助于能够处理完全非重合连接的空气动力学计算代码来执行使用该啮合的数字空气动力学模拟计算。

10. 发明授权

US08504331B2 Aerodynamic model identification process for aircraft simulation process 有权
标题翻译：飞机模拟过程的空气动力学模型识别过程
公开(公告)号：US08504331B2
公开(公告)日：2013-08-06
申请号：US12753633
申请日：2010-04-02
申请人： Benoit Calmels
发明人： Benoit Calmels
IPC分类号： G06F7/60 , G06F17/10 , G06F17/50 , G06G7/48 , G05B13/02
CPC分类号： G06F17/5009 , G06F17/5095
摘要： A method is disclosed of identifying or fixing the value of the parameters (aerodynamic data) of a pre-determined set of equations forming the aerodynamic models of an aircraft in various configurations, so as to minimize the variance between the values anticipated by using these aerodynamic data, and reference data in cases of known configurations, includes the use of learning or optimization methods to determine at least one portion of the parameters' values. The method includes storing database data, choosing an optimization method or a neural network method, breaking the identification down into several partial identifications, carrying out successive partial identifications, validating the values found for the aerodynamic model's parameters or iterating the method according to a threshold criterion determined on the value of variances between the reference data and the values measured by the identified model.
摘要翻译：公开了一种识别或确定形成各种配置的飞行器的空气动力学模型的预定的一组方程的参数值（空气动力学数据）的方法，以便通过使用这些空气动力学来最小化预期值之间的差异数据和参考数据包括使用学习或优化方法来确定参数值的至少一部分。该方法包括存储数据库数据，选择优化方法或神经网络方法，将识别分解成若干部分识别，执行连续的部分识别，验证空气动力学模型参数的值或根据阈值标准迭代该方法确定参考数据与由所识别的模型测量的值之间的差异的值。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式