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公开(公告)号：US08798810B2
公开(公告)日：2014-08-05
申请号：US12066599
申请日：2006-09-12
Applicant: Franck Delaplace , Didier Ronceray , Jean Muller
Inventor： Franck Delaplace , Didier Ronceray , Jean Muller
CPC classification number: B64D31/08 , B64D27/02 , B64D31/06 , B64D31/10 , G05D1/0072
Abstract: An energy protecting device for three and four-engined aircraft includes a detecting unit configured to detect failure of each engine. A control unit is configured to provide a protective function by controlling maximum thrust of each engine. A triggering unit is configured to monitor a plurality of parameters and trigger the control unit to provide maximum thrust at predetermined conditions of the monitored parameters. An inhibiting unit is linked to the triggering unit and is configured to inhibit the protective function, when at least one of the engine on the wings of the aircraft has failed. The control unit is also configured to control the engines that have not failed to minimize thrust imbalance.
Abstract translation: 用于三发射机和四发射机的能量保护装置包括：检测单元，被配置为检测每个发动机的故障。 控制单元被配置为通过控制每个发动机的最大推力来提供保护功能。 触发单元被配置为监视多个参数并且触发控制单元以在所监视的参数的预定条件下提供最大推力。 禁止单元连接到触发单元并且被配置为当飞行器的机翼上的发动机中的至少一个发生故障时禁止保护功能。 控制单元还被配置为控制未失效的发动机以最小化推力不平衡。
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2.发明授权Method and device for piloting an aircraft optimizing the control of the ailerons in an enhanced-lift configuration 有权用于驾驶飞机的方法和装置，其以增强升力配置优化对副翼的控制公开(公告)号：US08083178B2
公开(公告)日：2011-12-27
申请号：US12294588
申请日：2007-05-21
Applicant: Franck Delaplace , Sophie Lambeaux , Frédéric Sauvinet
Inventor： Franck Delaplace , Sophie Lambeaux , Frédéric Sauvinet
CPC classification number: B64C9/06 , B64C13/16 , B64C13/503 , G05D1/0808
Abstract: In conformance with the invention, based on the incident conditions and velocity, the steering of the ailerons is weakly negative (b0) or corresponds either to the maximum sharpness of the aircraft (b1), or the optimal lift of the latter (b2).
Abstract translation: 根据本发明，基于事故状况和速度，副翼的转向是弱负的（b0），或对应于飞行器的最大锋度（b1），或对应于后者的最佳提升（b2）。
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公开(公告)号：US20080208398A1
公开(公告)日：2008-08-28
申请号：US12066599
申请日：2006-09-12
Applicant: Franck Delaplace , Didier Ronceray , Jean Muller
Inventor： Franck Delaplace , Didier Ronceray , Jean Muller
IPC: B64D31/10
CPC classification number: B64D31/08 , B64D27/02 , B64D31/06 , B64D31/10 , G05D1/0072
Abstract: The invention concerns a device (1) comprising control means (3) for activating a protective function which consists in automatically controlling the engines (M1 to M4) so that they supply maximum power when the triggering conditions are fulfilled, and inhibiting means (8) for inhibiting the protective function solely when all the engines which are arranged on a common wing of the aircraft have simultaneously broken down.
Abstract translation: 本发明涉及一种装置（1），包括用于启动保护功能的控制装置（3），该保护功能包括自动控制发动机（M 1至M 4），使得它们在触发条件满足时提供最大功率;以及禁止装置 8）用于仅当布置在飞机的共同翼上的所有发动机已经同时分解时才抑制保护功能。
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4.发明授权Method and device for reducing the wake vortices of an aircraft in the approach/landing phase 有权在接近/着陆阶段减少飞机尾流涡流的方法和装置公开(公告)号：US07850125B2
公开(公告)日：2010-12-14
申请号：US11737438
申请日：2007-04-19
Applicant: Franck Delaplace
Inventor： Franck Delaplace
IPC: G05D1/00
CPC classification number: B64C9/12 , B64C23/06 , Y02T50/162
Abstract: The invention relates to a method and device for reducing the wake vortices of an aircraft during the approach/landing phase. Spoilers are automatically ordered to deploy when lift-augmenting aerodynamic surfaces are ordered to deploy, and are automatically ordered to retract when at least one of the following three conditions holds: the angle of incidence α of the aircraft is equal to or greater than an incidence threshold αs; the speed Vc of the aircraft is equal to or less than a speed threshold Vs; and the aircraft is instigating a go-around maneuver.
Abstract translation: 本发明涉及一种在接近/着陆阶段减少飞机尾流涡流的方法和装置。 当升降增压气动表面被命令部署时，自动命令铲斗，以便在以下三个条件中的至少一个条件成立时被自动命令缩回：飞行器的入射角α等于或大于入射角 阈值αs; 飞行器的速度Vc等于或小于速度阈值Vs; 飞机正在引发复飞机动。
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公开(公告)号：US20080188999A1
公开(公告)日：2008-08-07
申请号：US11913395
申请日：2005-05-04
Applicant: Gerard Mathieu , Franck Delaplace , Xavier Le Tron
Inventor： Gerard Mathieu , Franck Delaplace , Xavier Le Tron
CPC classification number: G05D1/0083 , G05D1/0661
Abstract: A reference value VRef is arbitrarily selected from the range of possible rotation speeds, the position of the trimmable horizontal stabiliser is angled at least in accordance with the centring, for said value VRef, the deviation between said reference value and the accelerating aircraft speed value VC is determined, and the elevators and/or the trimmable horizontal stabiliser of the aircraft are controlled, prior to rotation, in such a way that said deviation is taken into account.
Abstract translation: 参考值VRef可以从可能的转速的范围中任意选择，可调节水平稳定器的位置至少根据所述中心位置成角度，对于所述值VRef，所述参考值和加速飞行器速度值VC之间的偏差 并且在旋转之前控制飞机的电梯和/或可调节的水平稳定器，使得考虑到所述偏差。
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Patent Agency Ranking
6.发明授权Method and device for detecting an overstepping of design loads of the tailplane of an aircraft 有权用于检测飞机尾翼设计负荷超标的方法和装置公开(公告)号：US07382283B2
公开(公告)日：2008-06-03
申请号：US11146105
申请日：2005-06-07
Applicant: Franck Delaplace , Sylvie Marquier , Gérard Mathieu , Gennaro Squeglia
Inventor： Franck Delaplace , Sylvie Marquier , Gérard Mathieu , Gennaro Squeglia
IPC: G08B21/00
Abstract: Detection of the overstepping of design loads of an aircraft tailplane may include determining current bending and twisting moments applied to the aircraft. The determined bending and twisting moments are compared with a safety envelope to determine the risk of developing permanent deformations on the tailplane. A determination is made as to whether a structural inspection of the tailplane should be performed based on the comparison result.
Abstract translation: 检测飞机尾翼的设计负载的超越可以包括确定施加到飞行器的当前弯曲和扭转力矩。 将确定的弯曲和扭矩与安全壳进行比较，以确定在尾翼上发生永久变形的风险。 根据比较结果确定是否应进行尾翼的结构检查。
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7.发明申请公开(公告)号：US20080097728A1
公开(公告)日：2008-04-24
申请号：US11146105
申请日：2005-06-07
Applicant: Franck Delaplace , Sylvie Marquier , Gerard Mathieu , Gennaro Squeglia
Inventor： Franck Delaplace , Sylvie Marquier , Gerard Mathieu , Gennaro Squeglia
Abstract: Detection of the overstepping of design loads of an aircraft tailplane may include determining current bending and twisting moments applied to the aircraft. The determined bending and twisting moments are compared with a safety envelope to determine the risk of developing permanent deformations on the tailplane. A determination is made as to whether a structural inspection of the tailplane should be performed based on the comparison result.
Abstract translation: 检测飞机尾翼的设计负载的超越可以包括确定施加到飞行器的当前弯曲和扭转力矩。 将确定的弯曲和扭矩与安全壳进行比较，以确定在尾翼上发生永久变形的风险。 根据比较结果确定是否应进行尾翼的结构检查。
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公开(公告)号：US08014910B2
公开(公告)日：2011-09-06
申请号：US11913395
申请日：2006-05-04
Applicant: Gerard Mathieu , Franck Delaplace , Xavier Le Tron
Inventor： Gerard Mathieu , Franck Delaplace , Xavier Le Tron
IPC: G05D1/08
CPC classification number: G05D1/0083 , G05D1/0661
Abstract: A reference value is arbitrarily selected from a range of possible aircraft rotation speeds. A position of a trimmable horizontal stabilizer is angled in accordance with a centering of the reference value. A deviation between the reference value and an accelerating speed value of the aircraft is determined. Elevators or the horizontal stabilizer are controlled, prior to rotation, in accordance with the determined deviation.
Abstract translation: 从可能的飞机旋转速度的范围中任意选择参考值。 可调节水平稳定器的位置根据参考值的中心而成角度。 确定飞机的参考值和加速度值之间的偏差。 根据确定的偏差，在旋转之前控制电梯或水平稳定器。
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公开(公告)号：US07281683B2
公开(公告)日：2007-10-16
申请号：US11111927
申请日：2005-04-22
Applicant: Franck Delaplace , Gérard Mathieu , Nicolas Daniel
Inventor： Franck Delaplace , Gérard Mathieu , Nicolas Daniel
IPC: B64C13/00
CPC classification number: G05D1/0083
Abstract: An aircraft takeoff process may include applying a pitch command deflecting an adjustable horizontal tailplane of the aircraft by a predetermined angle. Thereafter, the pitch command is corrected in accordance with the deviation between a takeoff rotation speed and a stall reference speed VRref of the aircraft.
Abstract translation: 飞机起飞过程可以包括应用将飞行器的可调节水平尾翼偏转预定角度的俯仰指令。 此后，根据飞行器的起飞转速和失速基准速度VRref之间的偏差校正俯仰指令。
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10.发明授权Method and device for detecting an overstepping of design loads of the fin of an aircraft 有权用于检测飞行器翅片的设计载荷超标的方法和装置公开(公告)号：US07271741B2
公开(公告)日：2007-09-18
申请号：US11143704
申请日：2005-06-03
Applicant: Franck Delaplace , Sylvie Marquier , Gérard Mathieu , Gennaro Squeglia
Inventor： Franck Delaplace , Sylvie Marquier , Gérard Mathieu , Gennaro Squeglia
IPC: G08B21/00
Abstract: A method and device for detecting an overstepping of design loads of the fin of an aircraft. The device includes a set of information sources and a section for determining, with the aid of information emanating from the set of information sources, a current bending moment. The device further includes a section for determining, with the aid of information emanating from the set of information sources, a current twisting moment, and a section for carrying out a comparison by comparing the pair formed by the current bending moment and the current twisting moment with a safety envelope representing a chart formed in a plane on the basis of pairs of values of bending and twisting moments and defined so that, for any pair which lies outside the safety envelope, there exists a risk of appearance of permanent deformation on the fin. The device further includes a section for determining whether a structural inspection of the fin has to be performed, at least on the basis of a comparison result provided by the comparison section.
Abstract translation: 一种用于检测飞行器翅片的设计载荷超标的方法和装置。 该装置包括一组信息源和一个部分，用于借助于从该组信息源发出的信息确定当前的弯矩。 该装置还包括一个部分，用于借助于从该组信息源发出的信息来确定当前的扭转力矩，以及用于通过比较由当前弯矩和当前扭转力矩形成的对来执行比较的部分 其中安全信封代表基于弯曲和扭转力矩值的平面中形成的图表，并且被定义为使得对于位于安全壳体之外的任何一对，存在在翅片上出现永久变形的风险 。 该装置还包括至少基于由比较部分提供的比较结果来确定是否必须执行散热片的结构检查的部分。
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