Barge for transport of silt comprises central receptacle compartment with flat bottom and side and transverse walls and removable lateral float compartment either side central compartment

Le compartiment réceptacle (2) est un compartiment de forme sensiblement rectangulaire à fond (7) sensiblement plat et à parois latérales (8, 9) et transversales (10, 11) sensiblement perpendiculaires audit fond (7). Chacun des compartiments flotteurs (3, 4; 5, 6) est amovible. Le compartiment réceptacle (2) et les compartiments flotteurs (3, 4; 5, 6) comprennent des moyens respectifs complémentaires permettant une solidarisation ou une désolidarisation rapide entre lesdits compartiments flotteurs (3, 4; 5, 6), d'une part, et le compartiment réceptacle (2), d'autre part. Chacun des compartiments réceptacle (2) ou flotteurs (3, 4; 5, 6) est dimensionné et conformé de manière à être transportable par la route.

Remotely guided aircraft engine

The engine has a flight direction finding unit (1-8) and guide units (9) for defining a trajectory from a reference point. This direction finding unit includes an on-board radio-navigation receiver, which operates by multi-channel correlation on the codes to be correlated included in the radio-navigation signal (such as GPS). One of the treatment channels (97) of the receiver works on the auxiliary signal, distinct from the radio-navigation signal, and which is used to bring the remote control information, to the aircraft

HIGH FREQUENCY SIGNAL RECEIVER FOR THE SIMULTANEOUS RECEIPT OF SEVERAL OF SUCH SIGNALS

DISTRIBUTED ARCHITECTURE FOR ALL RADIO NAVIGATION AIDS

La présente invention est relative à une architecture distribuée pour l'ensemble des aides à la navigation aérienne. Pour que cette architecture permette de réduire le poids et/ou l'encombrement des câbles reliant les antennes aux équipements correspondants, ainsi que le poids et/ou l'encombrement d'au moins une partie desdits équipements, on déporte une partie au moins des récepteurs à proximité des antennes correspondantes, et une partie au moins de l'alimentation de puissance des équipements de l'aéronef est centralisée, et cette alimentation centralisée distribue aux équipements déportés une alimentation en énergie continue stabilisée.

RECETPEUR OF SIGNALS HIGH FREQUENCY RECEIVING SEVERAL SUCH SIGNALS SIMULTANEOUSLY

La présente invention est relative à un récepteur de signaux haute fréquence recevant simultanément plusieurs tels signaux reçus par au moins une antenne et comportant des circuits de conversion analogique/ numérique (13, 14) convertissant ces signaux sous forme numérique, et ce récepteur est caractérisé en ce qu'il comporte des circuits numériques de filtrage individuel filtrant respectivement chacune des fréquences porteuses de ces signaux (16.1 à 16. 3) et des circuits de traitement numérique (17.1 à 17.3). The present invention relates to a receiver of high frequency signals simultaneously receiving several such signals received by at least one antenna and comprising analog / digital conversion circuits (13, 14) converting these signals in digital form, and this receiver is characterized in it comprises digital individual filtering circuits respectively filtering each of the carrier frequencies of these signals (16.1 to 16. 3) and digital processing circuits (17.1 to 17.3).

FLOATING STRUCTURE SUCH AS A PONTOON, INTENDED TO SUPPORT A MACHINE DETERRASSEMENT OR ANALOGUE

Pontoon for carrying earth moving equipment comprises platform fixed to two floats and stabilizer legs operated by hydraulic actuators

The pontoon comprises a platform to which two floats (1) are fixed. The platform is fixed to the floats by removable fixings so that when loaded it is slightly above the water surface. The platform has two stabilizer legs (6,9) connected to it by articulations which are operated by hydraulic actuators (46). The stabilizer legs comprise sealed caissons (4,5) which constitute the platform floatation means.

HIGH-FREQUENCY SIGNAL RECEIVER SIMULTANEOUSLY RECEIVING SEVERAL SUCH SIGNALS

La présente invention est relative à un récepteur de signaux haute fréquence recevant simultanément plusieurs tels signaux reçus par au moins une antenne et comportant des circuits de conversion analogique/ numérique (13, 14) convertissant ces signaux sous forme numérique, et ce récepteur est caractérisé en ce qu'il comporte des circuits numériques de filtrage individuel filtrant respectivement chacune des fréquences porteuses de ces signaux (16.1 à 16.3) et des circuits de traitement numérique (17.1 à 17.3).

MACHINE STEALING GUIDE WITH RADIONAVIGATION GPS AND ASSOCIATED REMOTE CONTROL

METHOD AND SYSTEM FOR DETERMINING NAVIGATION PARAMETERS OF AN AIRCRAFT

Method for determining navigation parameters of an aircraft, characterized in that it consists at least in determining the geographic speed ~, expressed in a given local fixed coordinate system {~,~,~,}, based on the measurements m i of carrier phase increments .DELTA. .phi. i of the radio navigation signals originating from a plurality of radio navigation satellites in sight of said aircraft, each of said measurements m i constituting an estimate of the relative speed of said aircraft relative to said satellite projected onto the sight axis linking the aircraft to the satellite, each of said measurements m i being compensated by the apparent radial speed of the satellite.

METHOD AND SYSTEM FOR DETERMINING THE ATTITUDE OF AN AIRCRAFT BY MULIT-AXIS ACCELEROMETRIC MEASUREMENTS

Method of determination, by an inertial system, of a measurement of the attitude of an aircraft consisting at least in determining the angle of pitch .theta. and/or the angle of heading .PSI. and/or the angle of roll .phi. of the said aircraft, each of the said angles of attitude being determined by successive double integration of their second derivative, the said second derivative being determined as the difference between the acceleration measurements delivered by two matched accelerometers, divided by the sum of the respective distances between the said accelerometers and the centre of gravity G of the said inertial system, the pair of accelerometers used for the determination of the angle of pitch .theta. being disposed on either side of the centre of gravity G along an axis x substantially merged with the longitudinal axis of the aircraft, the pair of accelerometers used for the determination of the angle of heading .PSI. being disposed on either side of the centre of gravity G along an axis y substantially merged with the transverse axis of the aircraft, the pair of accelerometers used for the determination of the angle of roll .phi. being disposed on either side of the centre of gravity G along a vertical axis z perpendicular to the plane formed by the x and y axes.

BARGE ADAPTEE WITH THE TRANSPORT OF MUDS

Method and system for determining the attitude of an aircraft by multi-axis accelerometric measurements

An inertial system measures the attitude of an aircraft consisting at least in determining the angle of pitch and/or the angle of heading and/or the angle of roll of the aircraft, each of the said angles of attitude being determined by successive double integration of their second derivative. A pair of accelerometers to determine the angle of pitch being are disposed on either side of the centre of gravity along an axis substantially merged with the longitudinal axis of the aircraft. A pair of accelerometers to determine the angle of heading are disposed on either side of the centre of gravity along an axis substantially merged with the transverse axis of the aircraft. A pair of accelerometers to determine the angle of roll are disposed on either side of the centre of gravity along a vertical axis perpendicular to the plane formed by the other axes.

STRUCTURE DISTRIBUEE FOR the WHOLE OF the ASSISTANCES TO the RADIONAVIGATION

La présente invention est relative à une architecture distribuée pour l'ensemble des aides à la navigation aérienne. Pour que cette architecture permette de réduire le poids et/ou l'encombrement des câbles reliant les antennes aux équipements correspondants, ainsi que le poids et/ou l'encombrement d'au moins une partie desdits équipements, on déporte une partie au moins des récepteurs à proximité des antennes correspondantes, et une partie au moins de l'alimentation de puissance des équipements de l'aéronef est centralisée, et cette alimentation centralisée distribue aux équipements déportés une alimentation en énergie continue stabilisée.

METHOD AND SYSTEM FOR DETERMINING NAVIGATION PARAMETERS OF AN AIRCRAFT

Method for determining navigation parameters of an aircraft, characterized in that it consists at least in determining the geographic speed {right arrow over (V)}, expressed in a given local fixed coordinate system {{right arrow over (i)}, {right arrow over (j)}, {right arrow over (k)}}, based on the measurements m, of carrier phase increments i of the radio navigation signals originating from a plurality of radio navigation satellites in sight of said aircraft, each of said measurements mi constituting an estimate of the relative speed of said aircraft relative to said satellite projected onto the sight axis linking the aircraft to the satellite, each of said measurements m, being compensated by the apparent radial speed of the satellite.

High-Frequency Signal Receiver Simultaneously Receiving Several Such Signals

The present invention relates to a high-frequency signal receiver simultaneously receiving several such signals received by at least one antenna and comprising analog/digital conversion circuits converting these signals into digital form, and this receiver is characterized in that it comprises individual filtering digital circuits respectively filtering each of the carrier frequencies of these signals and digital processing circuits.

Distributed architecture for all radionavigation aids

The present invention relates to a distributed architecture for all aerial navigation aids. So that this architecture makes it possible to reduce the weight and/or the bulk of the cables linking the antennas to the corresponding equipment, as well as the weight and/or the bulk of at least part of said equipment, a part at least of the receivers is sited remotely in proximity to the corresponding antennas, and a part at least of the power supply for the equipment of the aircraft is centralized, and this centralized supply distributes a stabilized DC power supply to the remotely sited equipment.

Method and system for determining navigation parameters of an aircraft

Method for determining navigation parameters of an aircraft, characterized in that it consists at least in determining the geographic speed {right arrow over (V)}, expressed in a given local fixed coordinate system {{right arrow over (i)}, {right arrow over (j)}, {right arrow over (k)}}, based on the measurements m, of carrier phase increments i of the radio navigation signals originating from a plurality of radio navigation satellites in sight of said aircraft, each of said measurements mi constituting an estimate of the relative speed of said aircraft relative to said satellite projected onto the sight axis linking the aircraft to the satellite, each of said measurements m, being compensated by the apparent radial speed of the satellite.

METHOD AND SYSTEM FOR DETERMINING THE ATTITUDE OF AN AIRCRAFT BY MULTI-AXIS ACCELEROMETRIC MEASUREMENTS

An inertial system measures the attitude of an aircraft consisting at least in determining the angle of pitch and/or the angle of heading and/or the angle of roll of the aircraft, each of the said angles of attitude being determined by successive double integration of their second derivative. A pair of accelerometers to determine the angle of pitch being are disposed on either side of the centre of gravity along an axis substantially merged with the longitudinal axis of the aircraft. A pair of accelerometers to determine the angle of heading are disposed on either side of the centre of gravity along an axis substantially merged with the transverse axis of the aircraft. A pair of accelerometers to determine the angle of roll are disposed on either side of the centre of gravity along a vertical axis perpendicular to the plane formed by the other axes. 1. Method of determination , by an inertial system , of a measurement of the attitude of an aircraft consisting at least in determining the angle of pitch θ and/or the angle of heading ψ and/or the angle of roll φ of the said aircraft , each of the said angles of attitude being determined by successive double integration of their second derivative , the said second derivative being determined as the difference between the acceleration measurements delivered by two matched accelerometers , divided by the sum of the respective distances between the said accelerometers and the centre of gravity G of the said inertial system , the pair of accelerometers used for the determination of the angle of pitch θ being disposed on either side of the centre of gravity G along an axis x substantially merged with the longitudinal axis of the aircraft , the pair of accelerometers used for the determination of the angle of heading ψ being disposed on either side of the centre of gravity G along an axis y substantially merged with the transverse axis of the aircraft , the pair of accelerometers used for the determination of the angle of ...

Electronic system comprising of a plurality of electronic equipment units, electronic equipment for such a system and method for management and maintenance of such a system

The electronic system includes of a plurality of electronic equipment and devices () and a network for communication () between equipment units, each equipment unit () having the ability to be integrated into the electronic system or removed from the electronic system, each equipment unit () being provided with a radio tag () having an electronic circuit () containing a memory () capable of storing data in electronic form, including identification data for the equipment unit () and a radio antenna () for exchanging data with the electronic circuit (). Each equipment unit () includes an internal communication device () integrated into the equipment unit () and configured in order to communicate with the radio tag (). The system is applicable in particular to electronic systems for aircraft, railway vehicles, motor vehicles, boats, medical facilities, etc. 16868106620222462622632620. An electronic system comprising of a plurality of electronic equipment units () and a network for communication () between equipment units , each equipment unit () being connected to the communication network () through an interface () , each equipment unit () having the ability to be integrated into the electronic system or removed from the electronic system , each equipment unit () being provided with a radio tag () having an electronic circuit () containing a memory () capable of storing data in electronic form , including identification data for the equipment unit () and a radio antenna () for exchanging data with the electronic circuit () , characterised in that each equipment unit () includes an internal communication device () integrated into the equipment unit () and configured in order to communicate with the radio tag ().23486. An electronic system according to claim 1 , comprising of a centralised maintenance system () connected to the communication network () in order to exchange data with each equipment unit ().338343840206. An electronic system according to claim 2 , ...

ELECTRONIC SYSTEM COMPRISING A PLURALITY OF ELECTRONIC EQUIPMENT, ELECTRONIC EQUIPMENT OF SUCH A SYSTEM AND METHOD OF MANAGING AND MAINTAINING SUCH A SYSTEM

METHOD AND SYSTEM FOR DETERMINING THE ATTITUDE OF AN AIRCRAFT BY MULTI-AXIS ACCELEROMETRIC MEASUREMENTS

The method involves determining an angle of pitch and/or an angle of heading and/or an angle of roll of an aircraft (100). A first pair of accelerometers (A5, A6) used for determination of the angle of heading is arranged on a side of a center of gravity (G) along an axis merged with a transverse axis of the aircraft. A second pair of accelerometers (A3, A4) used for determination of the angle of roll is arranged on a side of the center of gravity along a vertical axis (z) perpendicular to a plane formed by other axes (x, y). An independent claim is also included for an inertial navigation system.

METHOD AND SYSTEM FOR DETERMINING THE NAVIGATION PARAMETERS OF AN AIRCRAFT

Procédé de détermination de paramètres de navigation d'un aéronef (100) caractérisé en ce qu'il consiste au moins à déterminer la vitesse géographique (110), exprimée dans un repère fixe local donné , à partir des mesures mi d'incréments Δφi de phase de porteuse des signaux de radio-navigation provenant d'une pluralité de satellites de radio-navigation en vue dudit aéronef (100), chacune desdites mesures mi constituant une estimée (111) de la vitesse relative dudit aéronef (100) par rapport audit satellite (121) projetée sur l'axe à vue (101) reliant l'aéronef (100) au satellite (121), chacune desdites mesures mi étant compensée de la vitesse radiale apparente du satellite (121). A method for determining navigation parameters of an aircraft (100) characterized in that it consists at least in determining the geographical speed (110), expressed in a given local fixed coordinate system, from the measurements mi of increments Δφi of carrier phase of the radio navigation signals from a plurality of radio navigation satellites in view of said aircraft (100), each of said mi measurements constituting an estimate (111) of the relative speed of said aircraft (100) with respect to said satellite (121) projected on the line of sight (101) connecting the aircraft (100) to the satellite (121), each of said mi measurements being compensated for the apparent radial velocity of the satellite (121).

METHOD AND SYSTEM FOR DETERMINING THE ATTITUDE OF AN AIRCRAFT BY MULTI-AXIS ACCELEROMETRIC MEASUREMENTS

Procédé de détermination, par un système inertiel, d'une mesure de l'attitude d'un aéronef (100) caractérisé en ce qu'il consiste au moins à déterminer l'angle de tangage θ et/ou l'angle de cap ψ et/ou l'angle de roulis Φ dudit aéronef (100), chacun desdits angles d'attitude étant déterminé par double intégration successive de leur dérivée seconde, ladite dérivée seconde étant déterminée comme la différence entre les mesures d'accélérations délivrées par deux accéléromètres appariés ((A1,A2),(A3,A4),(A5,A6)) divisée par la somme des distances respectives ((x ,x ),(z ,z ),(y ,y )) entre lesdits accéléromètres et le centre de gravité G dudit système inertiel, le couple d'accéléromètres (A1,A2) utilisé pour la détermination de l'angle de tangage θ étant disposé de part et d'autre du centre de gravité G le long d'un axe x sensiblement confondu avec l'axe longitudinal de l'aéronef (100), le couple d'accéléromètres (A5,A6) utilisé pour la détermination de l'angle de cap ψ étant disposé de part et d'autre du centre de gravité G le long d'un axe y sensiblement confondu avec l'axe transversal de l'aéronef (100), le couple d'accéléromètres (A3,A4) utilisé pour la détermination de l'angle de roulis Φ étant disposé de part et d'autre du centre de gravité G le long d'un axe z vertical perpendiculaire au plan formé par les axes x et y. Method for determining, by an inertial system, a measurement of the attitude of an aircraft (100) characterized in that it consists at least in determining the pitch angle θ and / or the heading angle ψ and / or the roll angle Φ of said aircraft (100), each of said attitude angles being determined by double successive integration of their second derivative, said second derivative being determined as the difference between the acceleration measurements delivered by two accelerometers pair ((A1, A2), (A3, A4), (A5, A6)) divided by the sum of the ...

Sediment lifting device

Le dispositif de relevage (5) de boues comporte une structure allongée (52) sur laquelle est enroulée une chaine de transport (55), une goulotte (51) s'étendant en regard et parallèlement à la structure allongée et une série de palettes (53) montées uniformément le long de la chaine de transport et agencées de sorte à glisser le long de la goulotte.

HIGH FREQUENCY SIGNAL RECEIVER RECEIVING SIMULTANEOUSLY MULTIPLE SIGNALS

Hochfrequenzsignalempfänger zum gleichzeitigen empfang mehrerer solcher signale