Abstract: Automated control of one or more exterior aircraft lights is presented, for instance exterior aircraft lights that enhance visibility by a pilot and including landing lights, taxi lights, and runway turnoff lights. One aspect of this automated control is that one or more of such exterior aircraft lights may be automatically activated, for instance when the aircraft has at least initiated movement and has not yet reached a certain altitude (e.g., while the aircraft is taxiing on the ground and including during takeoff). Another aspect of this automated control is that a trained image classification model may determine a visibility classification for an image acquired by an exterior aircraft camera, and this visibility classification may be used to automatically control the operation of one of more of such exterior aircraft lights (e.g., an intensity of the light output from such an exterior aircraft light(s)).

Abstract: A method and system for determining a position error of an aircraft. The system comprises a set of collection modules implemented in an iterative manner, including an offset collection module, a position vector collection module, a set of sequentially implemented computation modules, including an angular alignment bias computation module, an observable position bias computation module and a position error computation module. The system thus allows a position error to be determined that is used to perform a landing in good conditions.

Abstract: A method, an apparatus, and a system for recommending a location of a charging station of a robot are disclosed. The method includes obtaining movement path information from one or more robots in a space including a plurality of regions, determining density of each of the plurality of regions based on the obtained movement path information, and determining a recommended location of a charging station for charging the one or more robots from the plurality of regions based on the determined density. In a 5G environment connected for the Internet of things, the method for recommending a location of a charging station is implemented by executing an artificial intelligence algorithm or machine learning algorithm.

Abstract: A surface-based transmitter system for assisting determination of vehicle location is presented. The system comprises a set of radio frequency (RF) transmitter nodes that, when deployed at different respective locations, are configured to output a sequence of respective RF pulses with a predefined inter-pulse delay between each pair of consecutive RF pulses in the sequence, wherein the pre-defined inter-pulse delay is longer than 1 microsecond. The set of RF transmitter nodes include at least a first RF transmitter node, a second RF transmitter node, a third RF transmitter node, and a fourth RF transmitter node, which are configured to output a first RF pulse, a second RF pulse, a third RF pulse, and a fourth RF pulse, respectively, of the sequence of RF pulses.

Abstract: A system for localizing an autonomous vehicle to a target area can include a position indicator adapted for association with the vehicle in a three dimensional configuration, a detection device configured to detect the position indicator, a computation device configured to compute a position of the vehicle based on the detected position indicator and the relationship of the configuration to the vehicle orientation, a transmitter configured to receive information from the computation device and produce a signal carrying the information, a receiver configured to receive the signal from the transmitter and filter the information therefrom, and a control system configured for association with and control of one or more directional control components of the vehicle, the control being based on the information received from the receiver relating to localizing the vehicle to the target area. A method of for localizing a vehicle to a target area is also disclosed.

Abstract: Disclosed is a glide path indicator (2) comprising a light emitter (20) configured to emit a visible light signal that defines a glide path (14) for use by a pilot of an approaching aircraft (10), and a camera (22) configured to capture images of the approaching aircraft (10), the camera (22) being arranged such that at least part of the glide path (14) defined by the light emitter (20) is located within a field of view of the camera (22). The glide path indicator (2) may be mounted to a vehicle (4), for example, an aircraft carrier. The glide path indicator (2) may further comprise a stabilization module (26) configured to stabilize the light emitter (20) and the camera (22) so as to reduce or eliminate the effects of the vehicle's motion on the glide path (14) and the field of view of the camera (22).

Abstract: A method for optimizing a flight speed of a remotely-sensed scan imaging platform. The method comprises: selecting a reference point; obtaining a remotely-sensed scan image in a reference point region, and processing data; and optimizing a flight speed of a remotely-sensed scan platform. By optimizing a movement speed of a remotely-sensed movement platform, the method can prevent a geometric dimension of a target in a remotely-sensed scan image from being distorted, so as to obtain a high-precision remotely-sensed image of a ground target; and the method can be used for airborne and satellite borne remotely-sensed images.

Abstract: Methods, systems, and apparatus for Synthetic Instrument Landing System (SILS) are disclosed. By optimally integrating new SILS capabilities on existing aircraft systems and equipment, the systems, methods, and apparatus of this disclosure affect primarily one system, the MMR, and certain aircraft wiring reconfiguration and leave most of the other airplane systems as well as pilot (flight crew) training substantially unaffected. Unlike existing solutions that are based on a classical approach of new capability integration by providing associated new landing modes that are uniquely identified, the disclosure provides only a single mode to the pilot by moving all mode-specific functionality to onboard computers such as MMRs.

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 for landing an aircraft includes determining the aircraft's deviation from its approach path so as to define a first point of the aircraft's heading. A first straight line passing through the first point and through a second point defining the ground orientation of the approach path is displayed, by a head-up display, on a horizon line with a heading scale. The first straight line represents a ground plot of the approach path. A first assistance gate is displayed such that the first straight line passes through the first assistance gate when the aircraft is aligned on the approach path. A second straight line, parallel with the horizon line and passing through the first point, is displayed and represents a plot on the ground of the origin of the approach path. A second assistance gate is displayed under the horizon line and represents the slope of the approach path.

Abstract: A ground-based, precision aircraft landing system provides CAT I precision approach and landing guidance. The aircraft elevation position is determined by measuring differential carrier phase and time-of-arrival of the aircraft ATCRBS transponder reply. The transponder reply is received at a plurality of sensor antenna locations where it is then conveyed to a sensor, demodulated and digitized. The data is transmitted to a central processor where calibration and multipath corrections are applied. Aircraft transponder diversity antenna switching is isolated from the jitter and colored noise of transponder reply multipath by correlating differential phase jumps measured between separate sensor antennas. An estimate of the diversity antenna separation is maintained by Kalman filter processing; the estimated separation is used to correct the differential phase measurement data of aircraft elevation.

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 programmable digital radio is configured to perform navigation functions. A receiver in the programmable digital radio receives analog signals from a navigation unit and digitizes the analog signals to produce digital navigation signals. The digital navigation signals are processed digitally and valid navigation information is determined. Processing includes generation of baseband signals including in-phase signals and quadrature signals, AM demodulation, filtering, decimating, demultiplexing, discrete fourier transformation, and function processing according to a selected function. The selected functions may include Localizer, Marker Beacon and Glideslope.

Abstract: A comparator circuit compares two temporally separated input bursts of signals which occur at two different frequencies. The first burst is an interrogation pulse and the second burst is a reply pulse in a DME system. The comparator circuit includes a first frequency converter (CO1) for receiving at an input thereof the two input bursts, and a comparing device (DC) connected to receive an output of the first frequency converter (CO1). In order to reduce the measurement errors, the first frequency converter (CO1) receives at the input thereof the two input bursts and converts them into two new bursts of signals that have a common frequency so that the comparing device (DC) can carry out the comparison at the common frequency.

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: An aircraft landing system employs an array of antennas aligned across the runway, and equipment on board the aircraft employs radio interferometry to measure path length differences between the aircraft and selected pairs of the antennas. The antennas each include circuitry for sideband modulation of a basic FM signal so that each antenna radiates a pair of sidebands displaced above and below the basic signal by a respective number of increments. The FM signal can be carried on an X-band carrier of nominally ten GHz, with a frequency deviation of .+-.250 MHz and a modulating frequency of 20 Hz. Further antennas provide taxiing guidance. Data can be communicated on the system.

Abstract: A GPS precision approach and landing system for aircraft employs a fixed ground facility and a single satellite navigation receiver on board the aircraft. The fixed ground facility includes a reference receiver that measures differential corrections to the satellite code and carrier measurements and a pseudolite that is employed to transmit these corrections to a broadband GPS receiver on board the aircraft and to provide an additional code and carrier measurement to assist in the navigation solution. The pseudolite signal is broadcast at a frequency offset from the L1 GPS frequency in order to prevent interference with the satellite navigation system. The broadband GPS receiver on board the aircraft is capable of making phase coherent measurements from the GPS satellites, the pseudolite signal, and the GLONASS satellites.

Abstract: A passive aircraft monitoring system (20) receives signals transmitted by an instrument landing system (14, 16) and reflected from aircraft (18). The Doppler shift in the reflected signals is used to calculate the position or velocity of the aircraft. Using the ILS 90 and 150 Hz signals reflected from the aircraft and comparing their magnitude, the altitude and lateral position of the aircraft can also be determined.

Abstract: It describes a Microwave Landing System wherein.The means for surveillance of the transmissions from the various MLS stations are centralized in a single central station which then commands the various MLS stations. The connection between the central station and the MLS stations is assured by a network of optical fibers.

Abstract: The system comprises a central station assuring the generation of the microwave signals which must be transmitted by the different stations of an MLS. The signals thus generated in a centralized way are distributed to the different stations via an optical fiber network, the stations then assuring only the amplification and transmission of the signals.

Abstract: A portable siting system particularly useful for siting a portable localizer for a collocated approach guidance system for aircraft utilizes a laser range finder in conjunction with a shaft encoder to determine the distance between the localizer and two arbitrary points along a runway center line as well as the azimuth offset between the two points. A microprocessor is used to compute the number of degrees the antenna of the localizer must be rotated so that its beam intersects the extended runway center line at a predetermined point based on trigonometric computations performed on the two measured distances and the measured angle.

Abstract: A precision aircraft landing system comprising at least four receivers which are located at different predetermined positions. Each receiver includes a precision timer for measuring the timer interval between the receiver's detection of an interrogation signal and a reply signal from a transponder onboard the aircraft. The system also includes a central processing unit (computer) at a base station which collects the time measurements from the receivers, and calculates the location of the aircraft. Because more than three independent measurements are used, the base station can compute not only the three-dimensional coordinates of the aircraft, but also the transponder reply time. Preferably estimation filtering calculations, such as Kalman filtering, are used to improve the accuracy. The aircraft's position is compared with a mathematical description of a desired approach path, and the position error is then communicated to the aircraft.

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: A system for landing aircraft during low visibility includes a number of millimeter wave sources in or near the runway light housings radiating millimeter wave beams along the runway. An airborne millimeter wave camera includes a millimeter wave lens that focuses the image of the millimeter wave sources upon a hemispherical detector array that provides signals processed to create an image of the millimeter wave sources corresponding substantially to the visible image perceived by a landing pilot when observing the runway light pattern during good visibility conditions.

Abstract: A method and apparatus for detecting amplitude compression in a guidance system utilizes a transmitting system that transmits two pulses having a predetermined amplitude differential therebetween on each of a plurality of directional beams. The amplitudes of the pulses received from an individual one of the beams are compared, and if the amplitude differential between the received pulses is different than the predetermined amplitude differential of the transmitted pulses, a signal indicative of receiver compression is generated.

Abstract: There is disclosed a microwave landing system wherein there are provided at least two means which are spaced by a predetermined distance and from two of which beams radiate alternately to scan a predetermined region vertically and horizontally. In the microwave landing system, multipath propagating beams due to the scanning beams or side-lobes thereof are of out of phase or in non-correlation with each other in a receiving means in an aircraft to suppress multipath errors.

Abstract: A system for landing an aircraft is described, using a ground installation and an airborne installation which are synchronized together using GPS system time. Specifically, the ground installation includes a ground transmitter which radiates the sequence of signals which provide precision guidance information to the aircraft, an aircraft installation which includes a radio receiver and a processor to receive and process the transmitted guidance signals and to provide indications to aid the pilot in landing the aircraft, a GPS receiver in the air and on the ground for producing signals representative of GPS system time, and a channel selector in the aircraft for actuating the processor to synchronize its operation with the ground installation transmitter. Range information is provided by measuring the time interval between the transmission of a reference at the ground and its receipt in the air.

Abstract: A method for the radioelectric synchronization of slave stations by a master station, especially for a MLS type landing control system. The method consists in transmitting by the azimuth station a synchronization data coded in the form of a series of short duration pulses, prior to each MLS cycle, a cycle being constituted by a plurality of successive transmission of MLS functions.

Abstract: A microwave landing system incorporates a set of antennas for the sequential transmission of guidance signals through a sequence of directions to enable the reception and decoding of the signals by an airborne receiver. Circuitry is included for the retransmission of a frame of the signals by a procedure wherein the directions of transmissions is altered so as to increase the guidance sector over which the receiver is effective.

Abstract: An active, electro-optical display system for use on fixed-wing, land-based airport runways, is disclosed for remotely guiding a pilot during visual approach and landing of an aircraft. Conventional Microwave Landing System (MLS) ground-transmitted data is air-derived on board the aircraft and data-linked to a ground receiver to produce a continuous digital data signal indicative of aircraft slant range, elevation and azimuth relative to the desired landing position. The resulting data signal is electrically coupled to a signal processor governed in accordance with control guidance laws to produce three discrete signals indicative of the magnitude and direction of the descent rate error, the flight path acceleration, and the lateral drift rate of the aircraft relative to the intended landing area.