Abstract: An aircraft system for an aircraft, the aircraft system including a controller configured, during a take-off procedure, to receive a first signal indicative of a climb rate of the aircraft and, when the controller determines, on the basis of the first signal, that the climb rate of the aircraft is positive, cause a retraction alert to be issued to a flight crew of the aircraft, the retraction alert indicative that a landing gear of the aircraft is retractable.

Abstract: A radio beacon system configured to assist autonomous flight of one or more unmanned aerial vehicles (UAVs), wherein the radio beacon system comprises: —a drone device (200), configured to be installed on an UAV and including a radio transceiver, and —a radio beacon device (100), configured to be installed on ground and including N antenna arrays (110, 120) with N?2, one or more radio transceivers configured to communicate with the radio transceiver of the drone device (200), and at least one processing unit (130), wherein each antenna array (110, 120) has M antenna elements (115, 125) with M?2 associated to respective beamforming electronic weights w(n, m), with n ranging from 1 to N and m ranging from 1 to M, wherein said at least one processing unit (130) is configured to perform an adaptive beamforming method for assisting autonomous flight of the UAV.

Abstract: The system for aiding the landing of an aircraft on a landing runway of an airport equipped with an Instrument Landing System (“ILS”) corresponding to an axis of a predetermined approach, includes: an ILS signals receiver and a processing unit. The processing unit is configured to, when the ILS signals receiver) has not yet captured a Glide signal corresponding to a Glide axis of the approach as a function of items of information relating to the predetermined approach, acquired from a database, determine a protection volume in which there is no risk of the ILS signals receiver detecting a replica of the Glide signal; and when a current position of the aircraft is above the protection volume, inhibit the capture of the Glide signal by the ILS signals receiver and instruct the emission of an alert item of information in the cockpit of the aircraft.

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.

Abstract: A method for securing a ground speed used for guiding landing of an aircraft by determining a ground speed of the aircraft and determining a landing guidance instruction based on the determined ground speed. Next, estimate the vertical speed of the aircraft and limit, during guidance along a glide path having a descent angle, the determined ground speed as a function of the estimated vertical speed. The guidance instruction is based on the limited ground speed. Further, measure the height of the aircraft and compare it with a threshold height. If the measured height is greater than the threshold height, limit the ground speed as a function of acceleration measurements. If the measured height is below the threshold height, limiting the ground speed as a function of the estimated vertical speed and as a function of acceleration measurements of the aircraft taken once threshold height has been crossed.

Abstract: A system for tracking balls in sports in which players kick, pass, bounce, strike or carry a ball. The ball is equipped with two beacons pulsing in the 5-10 Hz range at a frequency which is not attenuated by the body of the players. one beacon has a very short range of 40-120 cm and the other has a range of 1-5 meters. A data logger worn by the players includes a clock, location and speed sensors, a receiver for the beacon signals and a micro controller to record the data from all the sensors. The micro controller is able to record whether the player is in possession of the ball or is contesting the ball. The path of the ball from player to player is tracked relative to the playing field. An impact or pressure sensor may be fitted to the players footwear, glove or a bat stick, club or racquet to register a kick or ball strike.

Abstract: A method and a device for an aircraft for detecting noise in a signal of LOC type. A first step includes estimating a first lateral speed of the aircraft according to a first set of parameters. Concurrently, at least one second lateral speed of the aircraft is estimated according to at least one second set of parameters, among which at least one parameter is of different nature from each parameter of the first set of parameters. A second step includes comparing the first lateral speed and the at least one second lateral speed according to a threshold. If the difference between the first lateral speed and the at least one second lateral speed is greater than the threshold, the presence of noise in the signal of LOC type is detected.

Abstract: A distribution device for a glide guidance component, the distribution device including an array of antenna elements installed on a pylon. The distribution device includes: a first and a second input for receiving a CSB (carrier plus sideband) input signal and an SBO (sideband only) input signal respectively, a plurality of outputs connectable to the array and including a first and a second output for the first and second output signals, respectively; each of said output signals including a CSB component and an SBO component. The array of antenna elements is such as to irradiate an image-less type pattern and the distribution device is such that the outputs have an substantially equal amplitude value for each pair arranged symmetrically around a central point of the array and a phase difference which is identical for the two CSB and SBO components.

Abstract: A method of removing undesired signals in an aviation guidance system may include receiving at least one first desired signal having a first frequency of amplitude modulation, receiving at least one second desired signal having a second frequency of amplitude modulation, and receiving at least one undesired signal having any frequency including a frequency that is substantially the same as or a subharmonic of at least one of the first and second desired signals. The first and second frequencies of amplitude modulation are phase synchronous, and the undesired signals are non-synchronous with at least one of the first and second desired signals. The method may also include identifying the undesired signals and removing the undesired signals.

Abstract: A satellite navigational receiver landing system having retrofit compatibility with integrated landing system (ILS) receivers, in accordance with the invention, includes radio frequency circuitry which converts satellite signals into intermediate signals. A first processing channel coupled to the radio frequency circuitry generates a first position, velocity and time (PVT) solution as a function of the intermediate signals, and provides a PVT data output. A second processing channel coupled to the radio frequency circuitry generates a second PVT solution as a function of the intermediate signals. Monitor circuitry provides monitor output signals as a function of the first and second PVT solutions. Shutdown circuitry provides the first PVT solution to the PVT data output under the control of a shutdown signal from the monitor circuitry.

Abstract: In a far field monitor apparatus, each of first and second ILS localizers includes a receiving antenna, a plurality of couplers, a combiner, a receiver, and a first detector. The receiving antenna is formed from a plurality of antenna elements symmetrically arranged in a direction perpendicular to the longitudinal direction of a runway. The receiving antennas of the first and second ILS localizers oppose each other. The couplers are arranged in units of antenna elements to pick up some of signals obtained by the antenna elements in a predetermined amplitude and phase. The combiner combines output signals from the couplers. The receiver receives a combined signal output from the combiner. The first detector detects, on the basis of a receiving signal output from the receiver, a predetermined monitor parameter representing the radiation state of a radio wave radiated from the opposing-side ILS localizer.

Abstract: Disclosed are a global navigation satellite system (GNSS) landing system (GLS) and methods of using the same to calculate a vertical deviation from the glide slope of the aircraft. A GNSS antenna and position determining circuitry are used to determine the position of the aircraft as a function of received GNSS positioning signals. Vertical deviation computation circuitry coupled to the position determining circuitry calculates an angular vertical deviation &agr;v from the glide slope of the aircraft as a function of the total horizontal distance between the aircraft and a GLS elevation reference point (GERP).

Abstract: A surface guidance system for guiding aircraft equipped with Instrument Landing Systems along taxiways which utilizes two inductive loops (14,16) installed around the right half and the left half of the taxiways. Audio amplifiers (18,20) drive one loop (14) with an 90 Hz signal and the other loop (16) at 150 Hz. A sensor (22) mounted on the aircraft detects the composite magnetic field induced by the surface loops (14,16). The detected signal is conditioned and supplied to the ILS system to provide left/right lateral guidance to the pilot. Longitudinal aircraft position is determined by using dipole marker antennas (52) embedded near the taxiway center line. Each marker antenna (52) has a unique code identifier. Existing ILS equipped aircraft can sense the marker signal and transmit the aircraft position to the ATC facility. Additional pairs of loops (14,16) and marker antennas (52) are used for different taxiway or runway sections.

Abstract: An instrument verification system which causes the instrument needles to "bob" periodically--a sharp momentary deflection from center. If desired, the flags can also be "dipped" at the same time, verifying their operation as well. The pilot can easily distinguish the momentary deflection of the needles from the more gradual changes caused by deviation from true course, and is assured that the centered needles mean perfect flying and not instrument failure.

Abstract: The invention relates to an instrument landing system (ILS) signal analysis device including an analog/digital converter receiving the composite signal to be analyzed and delivering a succession of values which can be processed in digital form, the signal to be analyzed being furthermore applied to a phase-locking unit which delivers for the analog/digital converter a sampling signal of frequency greater than the largest frequency of the components of the signal to be analyzed, the digital processing of the values from the converter, carried out in real time between two sampling instants, allowing determination of the parameters for modulation of the ILS signal.The phase-lock loop is synchronized with the frequency of the signal to be analyzed, which frequency is extracted from a sub-harmonic of the 90 Hz and the 150 Hz components constituting this signal.

Abstract: The Instrument Landing System Calibrator employs a combined analog radio frequency downconverter with a digital control system for analysis of difference in depth of modulation of tones generated by an instrument landing system localizer and glide slope transmitters. Signal sensitivity and accuracy is increased by elimination of system and phase noise present in purely analog designs and hybrid analog digital designs where digital signal processing is conducted at audio frequencies. Digital signal processing is conducted at video frequency with a single heterodyne from VHF and UHF frequency through selectable crystals. Selection of ILS channels is extended by the use of high speed video digital processing in conjunction with the use of selectable filters and selectable crystals to include all ILS channels.

Abstract: Airborne navigation receivers are designed to derive navigation information with accuracy immune to beam asymmetry errors. Scanned navigation beams of the Microwave Landing System are subject to asymmetry causing beam center measurement errors at power levels other than a standard level 3dB down from peak. Dwell gate and split gate type receivers achieve error immunity through offsetting of errors at power levels above and below a standard power level.

Abstract: A guidance system for landing an aircraft is described which uses a source of signals identifiable with the aircraft and a ground station which is linked to the aircraft. Specifically, the ground station includes a receiver which is connected to one or more pairs of antennas having a fixed, overlapping, directional sensitive pattern symmetically located relative to the center of the landing path, a receiver and a processor for measuring the relative sensitivity of the signals received at the antennas and for using the relative signal intensity to determine the location of the aircraft relative to the center of the landing path.

Abstract: The object of this invention is to reduce the adverse effects of reflected electromagnetic radiation on the measurement threshold of a scanning beam. It has particular application to the time reference scanning beam of the international microwave landing system (MLS). In the present MLS configuration, the reflection induced errors during the "TO" scan are additive to those of the "FRO" scan. This invention describes a method and apparatus for compensating errors by reversing the phase of the reflections during the "FRO" scan, by displacing the phase center of the transmitantenna during that scan. System performance is enhanced by the errors compensation.

Abstract: Received scanning signals radiated by a MLS ground system are used to determine and evaluate the approach angle of the aircraft. The difference between the angle for a particular scanning signal and the angle for a previous scanning signal is compared to a predetermined difference. A flag or alarm is indicated when the difference is greater than the predetermined difference for one second.