Abstract: A power demand anticipation system for a rotorcraft includes an engine subsystem having an engine with a power output. The power demand anticipation system also includes one or more sensors including a cyclic control sensor. The one or more sensors are operable to detect one or more flight parameters of the rotorcraft to form sensor data including a cyclic control position. A power demand anticipation module is in data communication with the engine subsystem and the one or more sensors. The power demand anticipation module is operable to anticipate a power demand of the engine using the sensor data to form a power demand anticipation signal. The engine subsystem is operable to adjust the power output of the engine based on the power demand anticipation signal received from the power demand anticipation module.

Abstract: In some embodiments, a technique for logging an item encountered by a mobile device comprises automatically detecting an item in an uncontrolled environment, extracting an identity associated with the item, logging an encounter, wherein the encounter includes the identity, and deleting the encounter after a predetermined period of time has elapsed, wherein the encounter is not marked as relevant.

Abstract: Methods and compositions for preventing opposing ILS systems on a single runway from becoming active at the same time. A physical interlock system employs a physical switch element that may activate a first ILS system or an opposing second ILS system, but is not capable of permitting, and may prevent, opposing ILS systems from being active simultaneously. Also included are methods for preventing opposing ILS systems on a single runway from becoming active, comprising the use of a physical switch preventing activating signals from being sent to opposing ILS systems at the same time.

Abstract: A present novel and non-trivial system and methods for generating and presenting glide path information are disclosed. A symbology generator may be configured to receive first data representative of a desired glide path (“DGP”); receive second data representative of first glide path deviation or third data representative of at least aircraft position; determine second glide path deviation as a function of the DGP and the aircraft position if the second data is not received; and generate symbology data as a function of the DGP and the first glide path deviation or second glide path deviation, where the symbology data is representative of a glide path angle reference cue comprised of a desired glide path deviation indicator. The desired glide path deviation indicator may be comprised of a single geometric symbol or a pattern of a plurality of geometric symbols.

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 method of geolocating a stationary transmitter observed by a fixed receiver device and at least two receiver devices, at least one of the receiver devices moving includes obtaining wavelength-scaled phase difference measurements between pairs of receiver devices, and obtaining a result lattice of possible locations of the transmitter, one location more probable than the remainder. A method of geolocating a moving transmitter observed by a plurality of fixed or nearly fixed receiver devices, and a moving receiver device, includes obtaining wavelength-scaled phase difference measurements from the plurality of fixed or nearly fixed receiver devices to obtain a shape of the transmitter trajectory, measuring the phase difference between the moving receiver device and at least one of the plurality of fixed or nearly fixed receiver devices to obtain a phase error residual, and moving an estimated starting point of the transmitter to obtain a best-fit residual.

Abstract: An exclusion zone compliance circuit comprises a terrestrial radio signal reception component for receiving a terrestrial radio signal comprising a unique identification of a transmission source. A non-volatile memory component of the circuit stores an encrypted data set describing boundaries of an exclusion zone. A navigation data deriving component of the circuit accesses a data set and compares the unique identification with a station identification of the transmission source and the geographic position of the transmission source. The navigation data deriving component derives a geographic position of the exclusion zone compliance circuit and determines whether the exclusion zone compliance circuit is located within an exclusion zone. A data blocking component of the circuit accesses the encrypted data set. A data control component of the exclusion zone compliance circuit blocks output of a signal in response to an indication that the circuit is located within an exclusion zone.

Abstract: A circuit for exclusion zone compliance is recited. In one embodiment, the circuit comprises a satellite navigation signal reception component configured for receiving at least one signal from at least one Global Navigation Satellite System satellite and a navigation data deriving component configured for deriving position data and a clock time from the at least one signal. The circuit further comprises a non-volatile memory component configured for storing an encrypted data set describing the boundaries of an exclusion zone and a data blocking component configured for controlling the accessing of the encrypted data set. The circuit further comprises a data control component configured for blocking the output of a signal from the circuit in response an indication selected from the group consisting of: an indication that the circuit is located within an exclusion zone and an indication that output of said signal is not permitted based upon said clock time.

Abstract: Systems and methods for a high-precision time of arrival ultra-wideband positioning system are provided. In one embodiment, a method for generating precision localizer messages for an ultra-wideband time-of-arrival positioning system is provided. The method comprises receiving a signal from an atomically accurate reference, generating a timing signal based on the atomically accurate reference signal, correcting a system time based on the timing signal when an error is detected, and transmitting an ultra-wideband signal having a localization message based on the system time.

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 Localizer cable fault analyzer that memorizes which antenna in a Localizer antenna array caused a fault. The Localizer equipment monitors the antenna transmit and monitor cables for continuity using a DC voltage. The present invention senses the voltage drop on the antenna circuit when a fault occurs and causes an indicator device to signal the presence of the fault in that particular antenna circuit. The indicator device continues to signal the presence of a fault until a reset switch is activated.

Abstract: A Localizer cable fault analyzer that memorizes which antenna in a Localizer antenna array caused a fault. The Localizer equipment monitors the antenna transmit and monitor cables for continuity using a DC voltage. The present invention senses the voltage drop on the antenna circuit when a fault occurs and causes an indicator device to signal the presence of the fault in that particular antenna circuit. The indicator device continues to signal the presence of a fault until a reset switch is activated.

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 digital camera for providing a short burst of global navigation satellite system (GNSS) signal samples in a picture data file with an approximate time for reading by a computer apparatus some time later for determining the geographical location and an accurate time of the picture. An apparatus and method for determining a GNSS position of an event where an event capture device writes a short burst of GNSS signal samples with an approximate time into an event data file and a GNSS sample processor reads the event data file some time later for determining the geographical location and an accurate time of the event.

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: A method for monitoring a localizer course facility in an instrument landing system, including modulating a course signal at a first signal frequency and at a second signal frequency, and transmitting the modulated course and clearance signals. The method also includes detecting by sensors the modulated course and clearance signals, demodulating the modulated course and clearance signals, monitoring variables obtained from the demodulated course and clearance signals to ensure that the variables are within limit values, and subjecting the demodulated course and clearance signals to Fourier transformation. Also included is determining a first phase difference for a first modulation frequency between the course and clearance signals detected by the sensors and a second phase difference for a second modulation frequency in the course and clearance signals, betweem the course and clearance signals detected by the sensors.

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: A beacon transmission signal comprises at least one carrier (C+SB) including sidebands (SB) and one sideband only signal (SBO), said carrier and said signal being in any mutual phase relationship. The method of the invention includes the steps of demodulating the sum of the carrier (C+SB) and of the signal (SBO), on one hand by multiplying it by a frequency (F), and on the other hand by multiplying it by the same frequency in phase quadrature, extracting from the products continuous components representative of the carrier portion (C) of said carrier (C+SB) and the low frequency components of the beacon transmission signal representative of the sideband portions (SB) of the carrier (C+SB) and of the signal (SBO), calculating the module and phase of portion (C) of the carrier (C+SB) and deriving from the low frequency components the amplitudes of the sidebands (SB) and the amplitude and phase of the signal (SBO).

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: The location of a subscriber device in a wireless cellular communications system is established by transmitting digital data signals to a cellular digital data receiver of the subscriber device from at least three different cellular cell site transmitters at known locations. Each data signal has a time-synchronized synchronization signal, preferably synchronized through the time signals of the global positioning system. The time of arrival of each of the time-synchronized synchronization signals is determined with respect to an internal clock of the receiver. The location of the subscriber device is established from the locations of the cell sites and the times of arrival of the synchronization signals relative to the internal clock.

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: A video processor system has separate and independent video processors for performing a variety of video processor functions required for encoding and decoding video signals. Each of the separate video processors performs its own individual set of video processor functions. During the encode process the first video processor performs motion estimation to provide motion estimation information which it applies to the second video processor. The second video processor receives the motion estimation information and performs forward and inverse discrete cosine transforms, quantization and dequantization, frame addition and frame differencing, as well as run length encoding. The run length encoding operation produces run/value pairs which are then applied to the first video processor. The first video processor performs variable length encoding upon the run/value pairs.

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: Two-frequency transmitting apparatus (S1, S2, LA) for instrument-landing systems is insensitive to so-called difference in depth of modulation (DDM) distortions caused by reflections of a clearance signal from obstacles (H) located near the runway (RW). This insensitivity is achieved by providing different phase shifts to the equal modulation frequencies (90 Hz and 150 Hz) used for the course and clearance signals. The different phase shifts correspond to a phase shift of a common fundamental frequency (30 Hz). The two-frequency transmitting apparatus can be used to specify a localizer course or a glide path.

Abstract: Data from long range aids such as the global positioning system (GPS) and an inertial navigation system (INS) and short range aids such as a microwave landing system (MLS) are used to smoothly and automatically transition an aircraft from the long range aids to the short range aids. During cruise a Kalman filter combines data from the global positioning system and the inertial navigation system to provide accurate enroute information. When the aircraft arrives in the vicinity of the airport and begins to acquire valid data from the microwave landing system, the Kalman filter is calibrated with the MLS data to permit Precision landing with GPS/INS data alone in case the MLS system subsequently fails. In addition, navigation information begins to be derived from a weighted sum of the GPS/INS and MLS data, the weighting being determined by distance from the airport. In a first region farthest from the airport, the GPS/INS data is given a 1.

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: Disclosed is an improvement to Integral Monitoring of two-frequency Instrument Landing System Localizer transmitting antenna arrays, by means of which the Clearance signal can be precisely separated from the combined Course and Clearance output of an Integral Monitor recombiner and monitored as if it existed alone. A first detector detects a composite Clearance and Course signal input, and sends an output to a separation filter which does not pass frequencies of 0, 90 or 150 hertz, but does pass frequencies of the difference between Course and Clearance frequencies (.DELTA.f), .DELTA.f.+-.90 hertz, and .DELTA.f.+-.150 hertz. The output of the filter is input to a second detector which measures the difference between the percentages of 90 and 150 hertz amplitude modulations of an amplitude modulated carrier having a frequency .DELTA.f.

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: An azimuthal scanning antenna for an aircraft landing system is formed of a set of vertically disposed columnar radiators arranged side-by-side in a horizontal array. The columnar radiators are tilted back in pitch 7.5.degree.. Individual ones of the radiators are formed of waveguide sections terminated by reflecting end walls. The terminating walls provide for a standing wave of electromagnetic field in response to microwave electromagnetic energy applied to the waveguide section by a feed disposed at or near the bottom of the waveguide section. Slot apertures are disposed along a front wall of each waveguide section, and are oriented at a selected angle relative to a perpendicular relationship to the sidewalls. The orientation of the slots introduces a variation in coupling for illumination of the radiation aperture of the radiator wherein the phase center is offset from a central point towards an upper end of each of the waveguide sections.

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: Disclosed is a radiofrequency distributor for a two frequency Instrument Landing System Localizer transmitting antenna array, for the purpose of driving each antenna with predetermined modulated radiofrequency currents of four different types, the distributor consisting of a combination of quarter wavelength power dividers and bidirectional couplers.

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.