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31. 发明授权

EP1353185B1 Capteur inertiel à sonde de température intégrée 有权
标题翻译：具有集成温度探头Ineritalsensor
公开(公告)号：EP1353185B1
公开(公告)日：2012-09-26
申请号：EP03290775.0
申请日：2003-03-27
申请人： Sagem Défense Sécurité
发明人： Featonby, Paul , Renault, Alain , Vandebeuque, Paul
IPC分类号： G01P15/097 , G01P15/10 , G01P1/00 , G01C19/56 , B81B7/00
CPC分类号： G01P15/097 , G01P1/006

32. 发明公开

EP2485943A1 DISPOSITIF DE COMMANDE DES GAZ D'UN AERONEF, INCORPORANT UNE LIAISON PAR CAMES 有权转让
标题翻译：与CAM和功率AIRPLANE节气门控制
公开(公告)号：EP2485943A1
公开(公告)日：2012-08-15
申请号：EP10765384.2
申请日：2010-10-05
申请人： SAGEM Défense Sécurité
发明人： ELABELLAOUI, Hafid , BESOLD, Jean-Eric , PAUTARD, Sébastien , CARTRY, Thierry , ENGLER, David , MERLET, Etienne
IPC分类号： B64D31/04 , G05G1/04 , B63H21/22
CPC分类号： B64D31/04
摘要： The invention relates to an aircraft engine control device comprising a frame (1) having the following elements pivotally mounted thereon, namely: a thumb wheel (2), and a main lever (4) and a secondary lever (5) for rotating the thumb wheel, whereby each lever can move between a rest position and a maximum actuation position, said secondary lever being mounted to pivot on the main lever. Cam channels (7) are provided on the thumb wheel and the frame, such that the main lever can drive the thumb wheel when the main lever is moved from the rest position of the secondary lever, and the secondary lever can drive the thumb wheel when the secondary lever is moved from the rest position of the main lever, the movement of one lever being prevented when the other lever is not in the rest position.

33. 发明授权

EP2347521B1 SYSTEME AVIONIQUE COMPRENANT UN CONTROLEUR ET AU MOINS UN PERIPHERIQUE RELIES PAR UNE LIGNE MUTUALISEE POUR LA PUISSANCE ET LES DONNEES 有权
标题翻译：与控制航空电子设备和至少一个的设备通过一个用于电源和数据管理MUTUALISIERTE连
公开(公告)号：EP2347521B1
公开(公告)日：2012-08-15
申请号：EP09783977.3
申请日：2009-10-13
申请人： SAGEM Défense Sécurité
发明人： GUILLOT, François , COURTEILLE, Jean-Marie
IPC分类号： H04B3/54 , H04B3/56 , H04L25/02
CPC分类号： H04B3/54 , H04B3/56 , H04B2203/5491
摘要： According to a first aspect the invention relates to a device forming a central controller (C) intended to be linked to a remote peripheral (P
1 ‑P
N ) by way an electrical power line (L), comprising a power transmitter (1) and a low-pass filter (C
C_BF ) arranged between the power transmitter and the electrical line, as well as means for transmitting/receiving data (3) in baseband and a high-pass filter (C
C_HF ) arranged between the data transmission/reception means and the electrical line, the electrical line being of the kind mutualized for the transmission of power at low frequency from the central controller to the remote peripheral and for the simultaneous bidirectional transmission of data in baseband at high frequency between the central controller and the remote peripheral. The invention also relates to a remote peripheral (P
1 -P
N ) as well as to the system comprising a central control linked to one or more remote peripherals by an electrical line mutualized for the transmission of power and of bidirectional data simultaneously.

34. 发明公开

EP2475961A1 PROCEDE ET SYSTEME DE DETERMINATION DE LIMITES DE PROTECTION AVEC EXTRAPOLATION INTEGRE SUR UN HORIZON TEMPOREL DONNE 有权转让
标题翻译：方法和系统保护的边界具有集成外推关于特定时间HORIZON测定
公开(公告)号：EP2475961A1
公开(公告)日：2012-07-18
申请号：EP10752778.0
申请日：2010-09-06
申请人： SAGEM Défense Sécurité
发明人： SZELEWA, Stanislas
IPC分类号： G01C21/16
CPC分类号： G01C21/165 , G01S19/20
摘要： The invention relates to a method for determining protection limits at a future moment associated with navigation states of a bearer, including the steps of: estimating the navigation states of the bearer at the present moment, developing a statistic model of the estimation errors of navigation states of the bearer at the present moment in the form of a covariance matrix, extrapolating, for a future moment, the statistical model of the estimation errors, calculating protection limits at the future moment from the extrapolated statistical model, wherein the extrapolation of the statistical model of the estimation errors implements the application of a constant and positive transition matrix to a standard deviation vector constructed from the square root of the elements of the diagonal of the covariance matrix, in order to propagate, up to the future moment, the standard deviations of the navigation states developed at the present moment. The invention also relates to a navigation system configured to implement the method.

35. 发明授权

EP1445581B1 Résonateur hémisphérique à électrode de garde divisée 有权转让
标题翻译：半球形共振器与两件式保护电极
公开(公告)号：EP1445581B1
公开(公告)日：2012-05-23
申请号：EP04290138.9
申请日：2004-01-20
申请人： Sagem Défense Sécurité
发明人： Renault, Alain , Vandebeuque, Paul
IPC分类号： G01C19/56
CPC分类号： G01C19/5691

36. 发明公开

EP2440453A1 DEVICE FOR ACTUATING A CONTROL SURFACE OF AN AIRCRAFT 有权转让
标题翻译：设备技术操作控制面飞机
公开(公告)号：EP2440453A1
公开(公告)日：2012-04-18
申请号：EP10725122.5
申请日：2010-06-10
申请人： SAGEM Défense Sécurité
发明人： RODRIGUES, Fernand
IPC分类号： B64C13/30 , B64C13/28
CPC分类号： B64C13/30 , B64C13/28 , Y02T50/44
摘要： The invention relates to a device (4) for actuating a control surface (2) of an aircraft, comprising: - a frame intended to be mounted fixed in relation to a structure of an aircraft, - a bell crank part (7) mobile in rotation in relation to the frame around an axis of rotation (X, X') and adapted in order to be connected to a mechanical unit (1) for displacement of the control surface (2), - a slider (6) intended to be connected to a drive member (5), the slider (6) being mobile in translation in relation to the frame according to a direction of translation, parallel to the axis of rotation (X, X') of the bell crank part (7), - first connecting means (61) between the slider (6) and the bell crank part (7) in order to convert a displacement in translation of the slider (6) generated by the drive member (5) into a displacement in rotation of the bell crank part (7), in order to actuate the mechanical unit (1) for displacement of the control surface (2),an input part (53, 16) able to be driven in rotation by the motor, - a control rod mounted fixed in relation to the frame and extending parallel to the axis of rotation (X) of the input part and at a distance from the latter, in order to block in rotation the slider in relation to the frame and authorize a translation of the slider in relation to the frame, the control rod extends through the slider (6). Application specific to the actuating of control surfaces incorporated into a thin airfoil.

37. 发明公开

EP2438400A1 CIRCUIT ÉLECTRONIQUE, GYRO-VIBRANT ET PROCÉDÉ DE TRAITEMENT ASSOCIÉ 有权转让
标题翻译：电子电路，振动陀螺仪及相关的处理
公开(公告)号：EP2438400A1
公开(公告)日：2012-04-11
申请号：EP10734206.5
申请日：2010-06-01
申请人： SAGEM Défense Sécurité
发明人： RENAULT, Alain
IPC分类号： G01C19/56
CPC分类号： G01C19/567
摘要： The invention relates to an electronic circuit for a vibrating gyroscope that comprises a resonator, wherein the electronic circuit includes: an input for receiving a detection signal representing the vibration of the resonator, the detection signal including a specific vibration mode and a parasitic vibration mode; and a demodulation unit for demodulating the detection signal in order to generate a phase-demodulated detection signal and a quadrature-demodulated detection signal. The electronic circuit of the invention is characterized in that the same further comprises a processing unit (64) and a subtractor (70) for removing a portion of the detection signal that represents the parasitic vibration mode from the phase-demodulated detection signal and from the quadrature-demodulated detection signal.

38. 发明授权

EP1672874B1 Procédé de transmission securisée, système, pare-feu et routeur le mettant en oeuvre 有权转让
标题翻译：一种用于安全传输和系统，防火墙和路由器用于执行该方法的方法
公开(公告)号：EP1672874B1
公开(公告)日：2012-03-28
申请号：EP05292683.9
申请日：2005-12-14
申请人： SAGEM Défense Sécurité
发明人： Colas, Gilles
IPC分类号： H04L29/06
CPC分类号： H04L63/0227

39. 发明公开

EP2427724A1 A VIBRATING SENSOR HAVING TWO CHANNELS ACTIVATED IN SEQUENCE 有权转让
标题翻译：与两个顺序激活通道VIBRANT SENSOR
公开(公告)号：EP2427724A1
公开(公告)日：2012-03-14
申请号：EP10721414.0
申请日：2010-05-07
申请人： Sagem Défense Sécurité
发明人： ROSELLINI, Lionel
IPC分类号： G01C19/56
CPC分类号： G01C19/5691
摘要： A vibrating sensor comprising a base (1) and an axisymmetrical resonator (2) secured to the base, the base and the resonator being associated with electrodes (3, 4) connected to a control circuit (5) via at least a first connection channel (6.1) and a second connection channel (6.2) with the electrodes being connected to one or other of the channels, the control circuit comprising excitation electronics (7) and detection electronics (8) and being arranged to control an excitation stage and a detection stage on each of the connection channels, the excitation stages and the detection stages having substantially identical respective durations, the sensor being characterized in that the control circuit is arranged to perform the following sequence: excitation stage on the second connection channel; detection stage on the first connection channel; excitation stage on the first connection channel; detection stage on the second connection channel.

40. 发明公开

EP2411832A1 PROCÉDÉ ET DISPOSITIF DE DÉTECTION ET D'EXCLUSION DE PANNES SATELLITE DANS UN SYSTÈME HYBRIDE INS/GNSS 有权
标题翻译：方法和设备用于在混合INS / GNSS系统检测与卫星进行了故障的排除
公开(公告)号：EP2411832A1
公开(公告)日：2012-02-01
申请号：EP10709757.8
申请日：2010-03-24
申请人： Sagem Défense Sécurité
发明人： VOURC'H, Sébastien , MAUGER, Victor
IPC分类号： G01S5/14 , G01S1/00
CPC分类号： G01S19/47 , G01S19/20
摘要： According to a first form, the invention relates to a method for monitoring the integrity of position information outputted by a hybridization device that includes a bank (3) of Kalman filters, each filter developing a hybrid navigation solution from inertial measurements calculated by a virtual platform (2) and from raw measurements of signals transmitted by a satellite constellation which are outputted by a global navigation satellite system (GNSS), characterized in that the method consists of the steps, for each satellite of the constellation, of: calculating a cross-innovation of the satellite that reflects the deviation between an observation, corresponding to a raw measurement from the satellite, and an a posteriori estimation of said observation that is developed through a Kalman filter and does not use the raw measurement from the satellite; carrying out a statistical test of the cross-innovation to ascertain whether or not the satellite is malfunctioning.

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