-
1.发明授权Onboard aircraft landing system, based on a GNSS system, with redundant and dissimilar architecture for high integrity level 有权基于GNSS系统的机载飞机着陆系统，具有用于高完整性级别的冗余和不同的架构公开(公告)号：US09395446B2
公开(公告)日：2016-07-19
申请号：US13855430
申请日：2013-04-02
Applicant: THALES
Inventor： Stephane Rollet , Jean-Pierre Arethens
Abstract: Device for receiving radio-navigation signals, for aiding the piloting of an aircraft, comprising a first master GNSS module and a second slave GNSS module which are dissimilar, the first master GNSS module comprising a first means for processing radio-navigation signals and a first means for computing guidance data (Xg), the second slave GNSS module comprising a second means for processing radio-navigation signals and a second means for computing guidance data (Xg) on the basis of the measurements provided by the said second means for processing signals, each GNSS module furthermore comprising a comparison means for comparing between the outputs Xg1,Xg2 of the said first and second means for computing guidance data, suitable for executing the following integrity test: |Xg1−Xg2|>Kg·√{square root over (Variance(Xg1−Xg2))} and for inferring an integrity defect if the said integrity test is satisfied.
Abstract translation: 用于接收无线电导航信号的装置，用于辅助飞行员的驾驶，包括不相似的第一主GNSS模块和第二从属GNSS模块，所述第一主GNSS模块包括用于处理无线电导航信号的第一装置和第一 用于计算引导数据（Xg）的装置，所述第二从属GNSS模块包括用于处理无线电导航信号的第二装置和用于根据由所述第二装置处理信号提供的测量来计算引导数据（Xg）的第二装置 每个GNSS模块还包括比较装置，用于比较用于计算引导数据的所述第一和第二装置的输出Xg1，Xg2，适用于执行以下完整性测试：| Xg1-Xg2 |> Kg·√{平方根 （方差（Xg1-Xg2））}，并且如果满足所述完整性测试则推断完整性缺陷。
-
公开(公告)号：US11385073B2
公开(公告)日：2022-07-12
申请号：US16675726
申请日：2019-11-06
Applicant: THALES
Inventor： Marc Riedinger , Jean-Pierre Arethens , Philippe Chaix
Abstract: The invention relates to a method and a system for aircraft navigation along a predetermined airway, including an on-board navigation system supplying a positioning integrity of the aircraft during flight relative to said airway respecting an expected position precision performance level, and at least one on-board radio receiver on the aircraft suitable for communicating with at least one land-based radio beacon suitable for supplying a distance of the aircraft relative to said radio beacon. The system includes a module configured to obtain, from a current position of the aircraft and stored data, a tuple of radio beacons to be used, a module configured to obtain a distance measurement of the aircraft relative to each of the N radio beacons of said tuple, a module configured to compute an integrity position from distance measurements obtained by a predetermined computing method, and a module configured to use the computed integrity position as current integrity position.
-
Patent Agency Ranking
公开(公告)号：US20180197422A1
公开(公告)日：2018-07-12
申请号：US15863739
申请日：2018-01-05
Applicant: THALES
Inventor： Jean-Pierre Arethens
Abstract: An electronic monitoring device for monitoring at least one radionavigation signal during an approach phase to a landing runway, related monitoring method and computer program are disclosed. In one aspect, the each radionavigation signal is obtained from a reception chain on board an aircraft. The device includes a calculation module configured to calculate an angular displacement value in a reference plane, a comparison module configured to compare the angular displacement value with the corresponding radionavigation signal, and a warning module to generate a warning signal based on the comparison between the angular displacement value and the corresponding radionavigation signal. The calculation module is configured to calculate the angular displacement value as a function of a magnitude relating to the aircraft course and glide path according to the monitored radionavigation signal, from avionics equipment independent from the reception chain.
-
公开(公告)号：US10580313B2
公开(公告)日：2020-03-03
申请号：US15863739
申请日：2018-01-05
Applicant: THALES
Inventor： Jean-Pierre Arethens
Abstract: An electronic monitoring device for monitoring at least one radionavigation signal during an approach phase to a landing runway, related monitoring method and computer program are disclosed. In one aspect, the each radionavigation signal is obtained from a reception chain on board an aircraft. The device includes a calculation module configured to calculate an angular displacement value in a reference plane, a comparison module configured to compare the angular displacement value with the corresponding radionavigation signal, and a warning module to generate a warning signal based on the comparison between the angular displacement value and the corresponding radionavigation signal. The calculation module is configured to calculate the angular displacement value as a function of a magnitude relating to the aircraft course and glide path according to the monitored radionavigation signal, from avionics equipment independent from the reception chain.
-
5.发明申请ONBOARD AIRCRAFT LANDING SYSTEM, BASED ON A GNSS SYSTEM, WITH REDUNDANT AND DISSIMILAR ARCHITECTURE FOR HIGH INTEGRITY LEVEL 有权基于全球导航卫星系统的ONBOARD飞机着陆系统，具有高度一致性的冗余和分辨率结构公开(公告)号：US20150362598A1
公开(公告)日：2015-12-17
申请号：US13855430
申请日：2013-04-02
Applicant: THALES
Inventor： Stephane Rollet , Jean-Pierre Arethens
Abstract: Device for receiving radio-navigation signals, for aiding the piloting of an aircraft, comprising a first master GNSS module and a second slave GNSS module which are dissimilar, the first master GNSS module comprising a first means for processing radio-navigation signals and a first means for computing guidance data (Xg), the second slave GNSS module comprising a second means for processing radio-navigation signals and a second means for computing guidance data (Xg) on the basis of the measurements provided by the said second means for processing signals, each GNSS module furthermore comprising a comparison means for comparing between the outputs Xg1,Xg2 of the said first and second means for computing guidance data, suitable for executing the following integrity test: |Xg1−Xg2|>Kg·√{square root over (Variance(Xg1−Xg2))} and for inferring an integrity defect if the said integrity test is satisfied.
Abstract translation: 用于接收无线电导航信号的装置，用于辅助飞行员的驾驶，包括不相似的第一主GNSS模块和第二从属GNSS模块，所述第一主GNSS模块包括用于处理无线电导航信号的第一装置和第一 用于计算引导数据（Xg）的装置，所述第二从属GNSS模块包括用于处理无线电导航信号的第二装置和用于根据由所述第二装置处理信号提供的测量来计算引导数据（Xg）的第二装置 每个GNSS模块还包括比较装置，用于比较用于计算引导数据的所述第一和第二装置的输出Xg1，Xg2，适用于执行以下完整性测试：| Xg1-Xg2 |> Kg·√{平方根 （方差（Xg1-Xg2））}，并且如果满足所述完整性测试则推断完整性缺陷。
-
6.发明授权Device for determining location information and inertial primary references for an aircraft 有权用于确定飞机的位置信息和惯性主参考的装置公开(公告)号：US09151620B2
公开(公告)日：2015-10-06
申请号：US13857673
申请日：2013-04-05
Applicant: THALES
Inventor： Jean-Pierre Arethens , Dominique Bouard
IPC: G01S19/45 , G01C21/00 , G01S19/47 , G06F11/16 , G06F11/18 , G01C21/10 , G01C21/20 , G01C23/00 , G06F11/14
CPC classification number: G01C21/005 , G01C21/10 , G01C21/20 , G01C23/005 , G01S19/45 , G01S19/47 , G06F11/1487 , G06F11/1645 , G06F11/185
Abstract: Device for determining location information, primary references consolidated for an aircraft, comprising a chain for determining location information comprising means for measuring radionavigation data, suitable means for consolidating, suitable means for computing parameters and suitable means for consolidating the parameters. The device also comprises a chain for determining inertial primary references comprising means for measuring inertial data, suitable means for consolidating, suitable means for computing parameters and suitable means for consolidating the parameters. The device finally comprises a chain for determining anemo-barometric data comprising means for measuring anemo-barometric data, suitable means for consolidating the measured anemo-barometric data, suitable means for computing parameters, and suitable means for consolidating the reference parameters.
Abstract translation: 用于确定位置信息的设备，用于航空器的主要参考信息，包括用于确定位置信息的链，包括用于测量无线电导航数据的装置，用于合并用于计算参数的合适装置的合适装置以及用于整合参数的合适装置。 该装置还包括用于确定惯性主要参考的链，其包括用于测量惯性数据的装置，用于整合用于计算参数的合适装置的合适装置和用于整合参数的合适装置。 该装置最终包括用于确定气压 - 气压数据的链，包括用于测量气压数据的装置，用于整合所测量的气压 - 气压数据的合适装置，用于计算参数的合适装置以及用于整合参考参数的合适装置。
-
7.发明申请DEVICE FOR DETERMINING LOCATION INFORMATION AND INERTIAL PRIMARY REFERENCES FOR AN AIRCRAFT 有权用于确定航空器位置信息和惯性参考的装置公开(公告)号：US20150032300A1
公开(公告)日：2015-01-29
申请号：US13857673
申请日：2013-04-05
Applicant: THALES
Inventor： Jean-Pierre Arethens , Dominique Bouard
CPC classification number: G01C21/005 , G01C21/10 , G01C21/20 , G01C23/005 , G01S19/45 , G01S19/47 , G06F11/1487 , G06F11/1645 , G06F11/185
Abstract: Device for determining location information, primary references consolidated for an aircraft, comprising a chain for determining location information comprising means for measuring radionavigation data, suitable means for consolidating, suitable means for computing parameters and suitable means for consolidating the parameters. The device also comprises a chain for determining inertial primary references comprising means for measuring inertial data, suitable means for consolidating, suitable means for computing parameters and suitable means for consolidating the parameters. The device finally comprises a chain for determining anemo-barometric data comprising means for measuring anemo-barometric data, suitable means for consolidating the measured anemo-barometric data, suitable means for computing parameters, and suitable means for consolidating the reference parameters.
Abstract translation: 用于确定位置信息的设备，用于航空器的主要参考信息，包括用于确定位置信息的链，包括用于测量无线电导航数据的装置，用于合并用于计算参数的合适装置的合适装置以及用于整合参数的合适装置。 该装置还包括用于确定惯性主要参考的链，其包括用于测量惯性数据的装置，用于整合用于计算参数的合适装置的合适装置和用于整合参数的合适装置。 该装置最终包括用于确定气压 - 气压数据的链，包括用于测量气压数据的装置，用于整合所测量的气压 - 气压数据的合适装置，用于计算参数的合适装置以及用于整合参考参数的合适装置。
-
-
-
-
-
-
Search Results
7
records
(took 0.013 seconds)
