Abstract: A self-contained, portable control device intended to relieve pilots of retrieving radio frequencies manually from maps, notes and directories eliminates the manual switching of frequencies on radios and other electronic devices replacing these procedures with a direct wireless link from a controlling device to the radio or other electronic device. The application of the invention is not limited to aviation but can be utilized in any utility scenario where operation calls for parameter changes, the object is conserving time and human effort, and raising standards of accuracy and system integrity. Remote control of onboard radio and other controllable electronics is achieved both by delivery of control codes and by use of a voice-to-text application. The configuration of a wireless-accessible database and a range of displays extends the application's utility to many forms of transportation, warehousing, farming, marine applications etc.

Abstract: A method for generating one or more images includes collecting data samples representative of a motion of an object, acquiring image data of at least a part of the object over a time interval, synchronizing the data samples and the image data to a common time base, and generating one or more images based on the synchronized image data. A method for generating one or more images includes acquiring image data of at least a part of an object over a time interval, associating the image data with one or more phases of a motion cycle, and constructing one or more images using the image data that are associated with the respective one or more phases.

Abstract: An optical lighting system for an aircraft includes an optical unit that can be configured according to the phases of flight or taxiing of the aircraft in order to emit a beam of light the spread and aim characteristics of which are dependent on the said phases of flight or of taxiing.

Abstract: A transceiver comprises local oscillator circuitry, phase noise determination circuitry, mixing circuitry, and digital signal processing circuitry. The local oscillator circuitry is operable to generate a local oscillator signal. The phase noise determination circuitry is operable to introduce a frequency-dependent phase shift to the local oscillator signal to generate a phase-shifted version of the local oscillator signal. The mixing circuitry is operable to mix the local oscillator signal and the phase-shifted version of the local oscillator to generate a baseband signal having an amplitude proportional to a phase difference between the local oscillator signal and the phase-shifted version of the local oscillator signal. The digital signal processing circuitry is operable to process the baseband signal to determine a phase error of the local oscillator signal, and perform signal compensation based on the determined phase error.

Abstract: A system comprises a microwave backhaul outdoor unit having a first resonant circuit, phase error determination circuitry, and phase error compensation circuitry. The first resonant circuit is operable to generate a first signal characterized by a first amount of phase noise and a first amount of temperature stability. The phase error determination circuitry is operable to generate a phase error signal indicative of phase error between the first signal and a second signal, wherein the second signal is characterized by a second amount of phase noise that is greater than the first amount of phase noise, and the second signal is characterized by a second amount of temperature instability that is less than the first amount of temperature instability. The phase error compensation circuitry is operable to adjust the phase of a data signal based on the phase error signal, the adjustment resulting in a phase compensated signal.

Abstract: A method of determining a position of a mobile electronic device with respect to a beacon is provided. The beacon transmits three or more radio signals having unique identifiers in different directions within a plane. The method includes receiving the radio signals and determining the received signal strength of each of the received radio signals. The method also includes calculating signal strength difference values for pairs of the received radio signals and determining an azimuth of the mobile electronic device relative to the beacon based on the calculated signal strength difference values for the pairs.

Abstract: Systems and methods for the selection of antennas in aircraft navigation systems are provided. In one embodiment, a navigation receiver system for an aircraft comprises: a first aircraft antenna that receives transmitter signals from fixed-location ground transmitters and a second aircraft antenna that receives transmitter signals from the fixed-location ground transmitters, wherein the first aircraft antenna has a first gain pattern that is different from a second gain pattern of the second aircraft antenna; a switch coupled to a first receiver and the first and second aircraft antenna; and a switch controller coupled to the switch. The switch controller operates the switch to electrically couple the first receiver to either the first or second aircraft antenna based on a determination of whether the first gain pattern or the second gain pattern provides higher gain in a direction of a first fixed-location ground transmitter of the fixed-location ground transmitters.

Abstract: A method and system for providing a bearing from a vehicle to a transmitting station are described. The method includes accessing a database to obtain transmitter position information for the transmitter, obtaining vehicle position information based on a GPS signal, and generating the bearing from the vehicle to the station utilizing the transmitter position information and the vehicle position information. The system includes a database storing transmitter position information identifying a position of the transmitter, a GPS receiver obtaining vehicle position information identifying a current position of the vehicle based on a GPS signal, and a controller generating a bearing from the vehicle to the transmitter utilizing the transmitter position information and the vehicle position information.

Abstract: A method and system for providing a bearing from a vehicle to a transmitting station are described. The method includes accessing a database to obtain transmitter position information for the transmitter, obtaining vehicle position information based on a GPS signal, and generating the bearing from the vehicle to the station utilizing the transmitter position information and the vehicle position information. The system includes a database storing transmitter position information identifying a position of the transmitter, a GPS receiver obtaining vehicle position information identifying a current position of the vehicle based on a GPS signal, and a controller generating a bearing from the vehicle to the transmitter utilizing the transmitter position information and the vehicle position information.

Abstract: To eliminate unwanted vibrations caused by synchronous disturbances, such as synchronous disturbances caused by an imbalance, for example, the invention proposes a compensation device for closed loop compensation of a synchronous disturbance in a rotating machine comprising a rotor (64) magnetically suspended by at least one radial magnetic bearing (63) comprising electromagnets (631, 632) driven by amplifiers (61, 62), a radial detector device (633, 634) for sensing the axial position of the rotor, and a closed loop servocontrol circuit connected to said detector device and to said electromagnets and comprising a control circuit (5) for controlling the energization of the electromagnets that supplies a control signal (u) to said amplifiers in response to signals supplied by the detector device to maintain the rotor in a predetermined axial position. The compensation device comprises means (100; 200; 300) for generating a signal for compensating the synchronous disturbance.

Abstract: A method to correct the drift in the phase shift between first and second signals, the first and second signals generated by a signal having frequency Fe, the drift in the phase shift resulting from a drift in the frequency Fe, according to a given relationship. In one embodiment, the method includes the steps of (1) determining a value of the phase shift from a phase of the first signal and a phase of the second signal, (2) estimating the value of the frequency Fe, and (3) adjusting the phase shift to a value within an interval of angular values containing the angular value obtained for a reference value, using the phase shift, the estimated value of the frequency, and the given relationship.

Abstract: An apparatus and method for inserting a waypoint into a preexisting flight plan which includes selecting a waypoint on a graphical display of a portion of the flight plan and automatically generating a proposed changed flight plan based upon inserting the waypoint into the nearest leg of the flight plan.

Abstract: The present invention relates to methods and systems for time-multiplexing a single VOR receiver to determine bearings from two or more VOR stations and thus determine a relative position of an object such as an aircraft. The invention employs a software-programmable digital signal processor (DSP) to process the VOR signals and control the amplifier stage. The gain control parameters that are used to process the VOR signals are stored for each processed carrier frequency so that the VOR signals may be quickly and reliably acquired; thus, enabling the time-multiplexing of the VOR receiver.

Abstract: The present invention relates to methods and systems for time-multiplexing a single VOR receiver to determine bearings from two or more VOR stations and thus determine a relative position of an object such as an aircraft. The invention employs a software-programmable digital signal processor (DSP) to process the VOR signals and control the amplifier stage. The gain control parameters that are used to process the VOR signals are stored for each processed carrier frequency so that the VOR signals may be quickly and reliably acquired; thus, enabling the time-multiplexing of the VOR receiver.

Abstract: A self contained electronic system for manual or automatic control and navigation of fixed winged aircraft using electronic position sensing such as GPS, DGPS, WAAS, and the like, as the primary sensor and making use of known flight characteristics of the aircraft to determine aircraft attitude without any interaction with the aircraft, its controls, or the outside environment and without any moving mechanical devices other than switches, dials and connectors. The automatic and visual interface between the system and the pilot provides for simplified flight controls, and a new solution to the hazard of disorientation, and will reduce the time needed for a pilot to become proficient in VFR and instrument flying. A single instrument replaces many of the conventional instruments used for flight. Navigation data is provided in an easy to understand graphical format. The pilot is told explicitly where to move aircraft controls.

Abstract: A navigation and control apparatus having a link to a GPS device for receiving positional and navigational data therefrom, a converter to convert the GPS signals into a VOR format, and a VOR signal generator to transmit the converted signals to a VOR receiver aboard the aircraft.

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: A Doppler position locator for determining the bearing of a signal source from a moving receiver. The signal source encodes a digital signal indicating its actual transmitting frequency on a transmitted carrier. The moving receiver such as an airplane receives a Doppler shifted carrier frequency and the digital information on what the actual transmitted frequency was. Comparison of the received frequency to the digital information on the transmitted frequency yields a Doppler frequency (the increase or decrease caused by the relative motion, i.e., the numerical difference between the transmitted and received frequencies). From the aircraft velocity and the two frequencies, the bearing can be determined using the formula .crclbar.=cos.sup.-1 (d*c)/(f*v) where .crclbar. is the bearing angle, f is the transmitted frequency, d is the Doppler shift or change in frequency, c is the speed of light and v is the magnitude of the receiver velocity.

Abstract: A very high frequency omni-range (VOR) receiver for use in aircraft radio-navigation, which provides an indication of course deviation that is substantially immune to effects such as reflections in transmitted VOR signals, transients occurring in an aircraft's electrical system and propeller and/or rotor modulations of an incoming VOR signal and the like which are all unrelated to actual course deviation, is disclosed. The receiver phase synchronizes a signal from a 1.08 MHz crystal oscillator to a 30 Hz reference signal and a 30 Hz variable signal; both the reference and variable signals are received from a VOR ground station. As a result of the phase synchronization, the receiver produces timing pulses which are accurately phase synchronized to a synchronized reference pulse stream derived from the 30 Hz reference signal. Additionally, the receiver produces a synchronized variable pulse stream that is derived from the 30 Hz variable signal.

Abstract: A VOR monitor employs a microprocessor-based system in which, after initial analog detection of a transmitted VOR signal, the critical parameters of the signal are extracted by digital signal processing to ensure that the transmitted signal in space remains within tolerance. Initial processing to isolate the 30 Hz AM (variable) modulation component and the 30 Hz reference component is conducted in the time domain. The 30 Hz reference is recovered by FM quadrature demodulation which, as a by-product, yields data from which an rms calculation is made of the amplitude of the 9960 Hz subcarrier. Further digital processing is then conducted in the frequency domain to yield spectra from which critical parameters of the VOR signal are extracted, e.g. the phases of the 30 Hz components (determining azimuth), the modulation percentages of the 30 Hz variable and the 9960 Hz subcarrier, and the 9960 Hz FM deviation ratio.

Abstract: A digital frequency discriminator designed to extract from a carrier at frequency f.sub.o a low frequency sinusoidal signal modulating the carrier. It receives digital samples x.sub.n from the carrier modulated at the frequency f.sub.e =4f.sub.o and includes:means of accumulation of N samples x.sub.nfirst means of storage of coefficients R.sub.01, R.sub.02, R.sub.11 and R.sub.12 defined by: ##EQU1## means for formatting the coefficients R.sub.ab, and first means of computing the quantity a.sub.1 defined by: ##EQU2## the quantity a.sub.1, similar to one point of the sought sinusoid, being then transferred into second means of storage, after which the next point of the sinusoid is determined from the next N samples.

Abstract: Aircraft navigational system and methods are disclosed for creating aircraft navigational guidepoints during in-flight operations. A digital computer and computer control displays provide dynamic and static display of the aircraft relative to the flight path and earth referenced data. In one embodiment, a new guidepoint is located and displayed at the intersection of a pilot selected radial and a track line, such as the aircraft projected flight path, defined by a series of guidepoints which are stored in the computer. The selected radial emanates from a selected geographical location defined by a known latitude/longitude, such as for example, preprogrammed NAVAIDS, geographical reference points and pilot entered geographical locations.

Abstract: A system and technique is disclosed which enables the production of in-phase and quadrature phase signals useful for deriving phase difference measurements. In an in-phase and quadrature phase difference measurement system, the phase shifter employed must receive an input signal and produce an output signal which is 90.degree. out of phase and equal in amplitude to the input signal over the full frequency range of the input signal. This is accomplished by using a phase locked loop which locks onto the input signal and uses the output of a voltage controlled oscillator located in the loop to derive the sine and cosine of the input signal. The resulting sine and cosine outputs are then 90.degree. out of phase and form in-phase and quadrature phase signals which have equal amplitudes. These two signals maintain lock over the frequency range of the input signal and may be used as inputs in the phase difference measurement system.

Abstract: A system for determining the closest navigation point to an aircraft utilizes a sphere of influence principle wherein the earth is subdivided into a plurality of geographic areas, for example, one quarter degree squares of latitude and longitude. An identifier such as an index number of the closest navigation point to each square is stored in a look up table. Position information from the navigation system of the aircraft is used to address the look up table to retrieve the appropriate index number which is then used to address a second look up table that contains information defining the closest navigation point.