Abstract: A communication system for a guideway mounted vehicle includes a control system communication system configured to exchange information between the guideway mounted vehicle and an external control system. The communication system further includes a vehicle-to-vehicle communication system configured to exchange information between the guideway mounted vehicle and another vehicle along the guideway, wherein the vehicle-to-vehicle communication system is separate from the control system communication system, and the vehicle-to-vehicle communication system is configured to exchange information directly between the guideway mounted vehicle and the other vehicle.

Abstract: Estimating the speed of an aircraft estimates three components of the speed vector (TAS, AOA, SSA) of an aircraft relative to the surrounding air. The static pressure is estimated on the basis of measurements of geographical altitude. A first intermediate variation of a linear combination of the three components of the speed vector of the aircraft relative to the surrounding air is estimated using explicitly the fact that the pressure measured by the static probe is falsified by a known quantity under the effect of the three components of this speed vector of the aircraft relative to the surrounding air. The process then estimates the three components of the speed vector of the aircraft relative to the air by likening the latter to the speed vector of the aircraft relative to an inertial reference frame and by using inertial measurements. The various estimates are fused to provide a final result.

Abstract: Space system comprising a structure formed by structure components, an on-board equipment carried by the structure, and a passive device designed to facilitate demise of the space system during re-entry into the Earth's atmosphere. The passive device comprises connecting members designed to stably connect the structure components. The connecting members comprise at least a portion made of a primer material with characteristics such as to decay at re-entry altitudes higher than those at which the current connecting members melt so as to make unstable the connection created by the connecting members to such an extent as to early triggering demise of the structure of the space system during re-entry into the Earth's atmosphere.

Abstract: In the field of satellite communication systems, a method is provided for managing communication resources allocated by central control equipment to the various terminal communication devices within a global satellite communication system. In particular, the management of communication resources by way of the monitoring of the equivalent isotropically radiated power transmitted by a terminal of the satellite communication system is provided.

Abstract: A method of graphical manipulation of the trajectory of an aircraft comprises the steps of receiving an indication of a deformation point associated with the trajectory of the aircraft; determining a zone of local modification of the trajectory of the aircraft as a function of the deformation point; computing a modified trajectory and graphically restoring the modified trajectory. A parameter associated with the indication of the deformation point, notably a speed and/or acceleration value (for example of the contact point on the touch-sensitive interface, or else of a cursor), is received or determined. A modified trajectory is computed by selecting a computation algorithm from among a plurality of faster or slower predefined algorithms; the selection being performed as a function of the parameter. Various other developments are described (configurable selection, trajectory modification bounds, processing of an arbitrary deformation point, i.e. one other than a point of the flight plan, etc.).

Abstract: The general field of the invention is that of passive resonator gyros comprising an injection laser emitting an initial optical beam at a first frequency and a fiber optic cavity. The gyro according to the invention operates with three optical beams at three different optical frequencies. A first beam is injected in a first direction of rotation, the second and the third beam are injected in the contrary direction. The gyro includes three slaving devices maintaining each optical frequency at a specific mode of resonance of the cavity. The gyro includes means for measuring the frequency differences existing between the different frequencies. Combined together, these differences are representative of the length of the cavity and the angular rotational velocity of the cavity along an axis perpendicular to its plane.

Abstract: A method for transmission of a signal simultaneously including a first stream of binary data and one or more other streams of binary data, the method including, in the following order: dynamic distribution of bits of the data streams between coders, with one coder per data stream; coding the distributed bits using the coders; dynamic distribution of the coded bits between hierarchical levels of a modulator; and hierarchical modulation using the modulator.

Abstract: A deployable structure comprises: a mount comprising a first point and a second point opposite and a third point, a storage reel able to rotate about an axis Z, a tape spring able to switch from a configuration in which it is wound about the axis Z in the storage reel into a configuration in which it is deployed along an axis X substantially perpendicular to the axis Z, the first and second points forming a double support with the tape spring to keep the tape spring in the deployed configuration. The third point is able to form a simple support with the tape spring, the storage reel is able to move with respect to the third point and the storage reel is pressed against the third point to guide the deployment of the tape spring.

Abstract: Method of detecting interference in a satellite radio-navigation signal, characterized in that it comprises the following steps: determining a first temporal position for which the correlation between the said signal and a local spreading code, offset by the said position, is maximum; determining a plurality of measurements of correlation between the said signal and a local spreading code offset by a plurality of secondary temporal positions, the said plurality of secondary temporal positions and the said first temporal position being regularly spaced; determining, for a plurality of correlation measurement pairs formed by two measurements at two consecutive temporal positions, the phase difference between the two correlation measurements of the said pair; calculating an item of information representative of the standard deviation of the said phase difference; and comparing the said item of information with a detection threshold configured at least as a function of the ratio of the powers of the signal and

Abstract: The general field of the invention is that of matter-wave gravimeters. The gravimeter according to the invention comprises at least: means for generating, for capturing and for cooling a cloud of ultra-cold atoms; means of transferring the atoms into a superposition, with equal weights, of a first internal electronic state called state |1>) and of a second internal electronic state called state |2> comprising the application of at least a first microwave field and of a radiofrequency field; means for separating the atoms into two wave packets for a given period of time under the effect of at least a second microwave field, the said separation leading to a phase-shift associated with the local gravitational field; calibration means allowing a “magic” magnetostatic field to be determined for which the difference in energy between the first internal electronic state and the second internal electronic state is independent, to a first order, of the fluctuations of the magnetostatic field.

Abstract: This method concerns the protection against humidity of a device including a first and a second electronic components respectively having two opposite surfaces, the surfaces: being separated by a non-zero distance shorter than 10 micrometers; having an area greater than 100 mm2; being connected by an assembly of electrical interconnection elements spaced apart from one another by a space void of matter. This method includes applying a deposit of thin atomic layers onto the device to form a layer of mineral material covering at least the interconnection elements, the layer of mineral material having a permeability to water vapor smaller than or equal to 10?3 g/m2/day.

Abstract: This method for computing a conjugated airport navigation graph, from an initial airport navigation graph, is implemented by a computer. This method involves acquiring the initial graph including a plurality of navigation arcs, each including two end nodes, having at least one authorized navigation direction and being identified by its two end nodes. This method further involves determining a conjugated node for each navigation arc and for each authorized navigation direction of the arc, each conjugated node corresponding to a single authorized direction and representing the arc of the initial graph associated with the authorized direction. The conjugated graph is computed by connecting the conjugated nodes as a function of the connections between the arcs of the initial graph and the authorized directions. Two conjugated nodes connect to one another corresponding to two successive arcs of the initial graph and to a same authorized direction.

Abstract: The general field of the invention is that of Doppler lidars intended to measure the speed of a target. The lidar according to the invention comprises: First means for modulating the optical frequency of the transmission signal, said frequency being the sum of a constant frequency and of a variable frequency of determined amplitude modulated by a periodic temporal function; Second means for computing the spectrum of the measured heterodyne signal and for creating two measurement spectra obtained by shifting the spectrum of the heterodyne signal by a positive and negative frequency value, said realignment frequency equal to the difference between the instantaneous frequency of the transmission signal and the frequency of a signal transmitted at a time shifted by the round-trip travel time between the lidar and the target; Third means for comparing the two measurement spectra, the difference in amplitude between the two spectra at the Doppler frequency determining the direction of the speed of the target.

Abstract: A man-worn power and data harness. The harness is intended to facilitate the supply of power and data around a user's, and in particular a soldier's, person. Furthermore, the harness is intended to be compatible with a tiered structure of soldier load carriage and protection. The harness may comprise: at least one brace for passing over a user's shoulder, each brace comprising at least one cable; and a belt for at least partially encircling a user's waist, the belt comprising at least one cable; wherein each cable comprises power and/or data cabling, each brace is connected at both ends to the belt and each brace comprises at least one release clip, the release clip being for disconnecting and reconnecting the brace; each brace may further comprise at least one attachment device to attach the brace to an item worn underneath the harness. Furthermore, a harness and load carriage may be provided.

Abstract: A frequency converter comprising a frequency transposition block for samples (11Q_1, 11Q_2), a filtering block (12Q_1, 12Q_2), the filtered samples y(n) verifying y(n)=c(0)·x(n)+c(1)·x(n?1)+c(2)·x(n?2)+ . . . +c(p?1)·x(n?p+1)+c(p)·x(n?p)+c(p?1)·x(n?p?1)+ . . . + . . . +c(1)·x(n?2·p+1)+c(0)·x(n?2·p), wherein x( ) are the transposed samples and c(0), . . . c(p) are the real coefficients of the filter; and being adapted for, during a cycle for determining the value of the filtered sample y(n): calculating the first terms c(0)·x(n), c(1)·x(n?1), c(2)·x(n?2), . . . , c(p)·x(n?p) by multiplying the respective coefficients and transposed samples, and storing in memory said first calculated terms; reading the second terms c(p?1)·x(n?p?1), . . . , c(1)·x(n?2·p+1), c(0)·x(n?2·p), calculated and stored in memory during previous cycles for determining the value of filtered samples y(n?m); and determining y(n) by summation of the first and second terms.

Abstract: The general field of the invention is that of methods for representing a rate of turn indicator for an aircraft implemented by an on-board avionics system. The method includes a step of graphically representing on a visualization device a symbol called “aeroplane model”, said graphic representation being a function of the specific speed of the aircraft and of its angle of inclination. In a favored embodiment, said aeroplane model includes two straight arms interlinked by a common point and inclined to the horizontal symmetrically in such a way as to form an inverted V. The angle of inclination of the two arms of the V is proportional to the specific speed of the aircraft, the coefficient of proportionality being determined in such a way that when the specific speed and the angle of inclination correspond to values compatible with the standard rate, said arm is parallel to the horizon line, thus indicating that the aircraft is carrying out its turn at the standard rate.

Abstract: A method and system is provided for determining the compatibility of an approach, to a landing runway, with an angular guidance mode, the approach being compatible with a linear guidance mode, the angular guidance being characterized by a lateral angle of precision, the linear guidance being characterized by a lateral divergence of precision. The method is implemented on a flight management system deployed aboard an aircraft and comprising a first step of determining a first distance representative of a maximum distance of use of the angular guidance, on the basis of the lateral angle of precision and of the lateral divergence of precision.

Abstract: The invention relates to a drive arrangement in a spacecraft, comprising several drive units (TW1,TW2,TW3), several individually controllable drive units that can be continuously applied to a common, constant voltage potential (HV), and a control of the axial thrust in the respective drive units is achieved due to the fact that the production of plasma in the respective drive units is individually controlled. In particular, the time-variable control of the production of plasma occurs by the time-variable control of the flow of neutral working gas (AG) in the ionization chamber (IK).

Abstract: The general field of the invention is that of systems for detecting the posture of a moving object. The system may include a fixed electro-optical device of known orientation comprising an emission source, an image sensor and image analysis means, and an optical assembly comprising an optical retroreflector arranged on the moving object. The optical retroreflector of the system is an optical sphere of variable index comprising a transparent hemisphere and a reflecting hemisphere. It comprises a meshing comprising at least three opaque wires, of small thickness and known geometrical arrangement. The image of the retroreflector lit by the source forms a reflection on the image sensor, said reflection comprising at least the two images of the shadow of one of the three wires. The image analysis means detect the orientation of the leak line given by said images, said orientation being representative of one of the parameters of the posture of the moving object.

Abstract: A compact dual-polarization planar power splitter comprises at least four asymmetric orthomode transducers (OMTs) connected in an array suitable for being coupled in-phase to a dual orthogonal polarization feed source via two power distributors mounted perpendicularly in relation to one another, each power distributor comprising at least two lateral metal waveguides disposed parallel to one another, and a transverse metal waveguide coupled perpendicularly to the two lateral metal waveguides and four ends of the lateral waveguides coupled respectively to the four asymmetric OMTs.