Abstract: A device includes a circuit board having thereon, a controlling component, a first radar chip and a second radar chip. The first radar chip includes a first radar transmission antenna, a second radar transmission antenna and a first radar receiver antenna array. The second radar chip includes a second radar receiver antenna array. The controlling component can control the first radar chip and the second radar chip. The first radar transmission antenna can transmit a first radar transmission signal. The second radar transmission antenna can transmit a second radar transmission signal. The second radar chip is spaced from the first radar chip so as to create a virtual receiver antenna array between the first radar receiver antenna array and the second radar receiver antenna array.

Abstract: Processes for determining imperfection offsets between an antenna and the platform to which the antenna is coupled, where the imperfection offsets are unknown offsets due to imperfections such as manufacturing imperfections. The platform can include an orientation mechanism that provides the orientation of the platform, and the imperfection offsets can be between the antenna and the orientation mechanism. The processes can include determining two different relative pointing vectors that correspond to a detected peak strength of a test signal transmitted between one or more targets and the antenna. The processes can further include utilizing an optimization process to determine the heading, pitch, and roll of the imperfection offsets from the two different relative pointing vectors.

Abstract: There is a calculation device for a radar apparatus which is configured to specify a direction of a target based on a reception signal of an antenna. A calculation unit is configured to calculate a relative displacement magnitude in a lateral direction of the target relative to a traveling direction of a moving object having the antenna mounted thereon, from data of the target position-measured by the reception signal while the moving object is moving, and evaluate a relative inclination between a reference axis of a scanning direction of the radar apparatus and a reference axis of the traveling direction of the moving object, based on the displacement magnitude.

Abstract: Examples of the present invention include calibration methods for phased array radar apparatus. The calibration methods include an electronic calibration of phase shifters, and compensation for mechanical misalignment. Approaches are particularly useful for automotive radar, and may be used for initial calibration after installation on a factory line, or at later times such as at a service station whenever recalibration becomes necessary.

Abstract: In an embodiment, a coordinate determiner is operable to identify at least first and second surfaces that each approximately intersect an object, and to determine at least two approximate coordinates of the object from the first and second surfaces, where at least one of the surfaces is nonplanar. For example, if the coordinate determiner is disposed on a fighter jet having at least two short-baseline-interferometers (SBIs), then two surfaces may be the surfaces of two cones having two of the SBIs as respective vertices, the object may be a close-in target, and the coordinate determiner may determine the azimuth and elevation of the target from the cone surfaces. Furthermore, the coordinate determiner or another computation unit onboard the jet may determine the slant range of the target from the elevation and the altitude of the jet.

Abstract: The disclosed approach provides a low-cost approach by employing a single channel receiver for a direction-finding missile, rather than a conventional four-channel system. It employs interferometry techniques. The proposed approach leverages orthogonal waveforms and pseudorandom noise (PN) codes. This is a low-cost approach for a single channel direction finding system by leveraging orthogonal waveforms and interferometric techniques.

Abstract: Provided is a vehicular radar device which is capable of reducing an operation resource quantity necessary for a process of estimating an axis deviation angle in a radar measurement coordinate system, to thereby reduce a device size. The vehicular radar device includes: a measurement unit that measures an azimuth angle and a relative Doppler velocity; an extraction/accumulation unit that extracts target information satisfying conditions related to the relative Doppler velocity, a travel speed and a turning velocity, and accumulates the azimuth angle and a velocity ratio obtained by dividing the relative Doppler velocity by the travel speed of the subject vehicle among the extracted target information; and an axis deviation angle estimate unit that reads the target information accumulated in the extraction/accumulation unit, and estimates an axis deviation angle of the measurement coordinate system of a radar based on a second-order polynomial expression of the azimuth angle of the target.

Abstract: An angle tracking radar system particularly for a missile with a steerable antenna and gyros strapped down to the missile body—a ‘partially strapdown’ system. The body rate signals, body acceleration signals where provided, and target position signals are converted into an electronic reference frame which is controlled to align with the target sightline, the above body and target signals being employed to produce estimates of target direction, sightline rate and sightline acceleration for use in controlling the missile.

Abstract: A detection system (1) having an optical sensor (3), a radar device (2) and a signal processor (4) communicatively connected with the optical sensor and the radar device. The signal processor comprises: a first detector (41, 410-413) for detecting a first object on the basis of a first signal coming from the optical sensor and determining at least one first property of the first object; a second detector (42, 420-421) for detecting a second object on the basis of a second signal coming from the radar device and determining at least one second property of that second object, and a signaling unit (43) for producing a signal if the at least one first property and the at least one second property satisfy a predetermined condition.

Abstract: The present invention is a method for obtaining a localizer deviation and a glide slope deviation for an aircraft. The method may include directing electromagnetic signals from a weather radar system of an aircraft towards a runway. The method may further include receiving return signals in response to the directed signals. The method may further include, based on the received return signals, determining an azimuth angle for the aircraft relative to the runway, determining an elevation angle for the aircraft relative to the runway, and determining a range for the aircraft relative to the runway. The method may further include based on the azimuth angle, the elevation angle, and the range, calculating the localizer deviation and the glide slope deviation for the aircraft.

Abstract: In a radar system, a monopulse calibration table is constructed from live targets of opportunity. A center of gravity or weighted average of normalized signals ?V received at SUM and DIFF channels from a live target are used to determine the target's actual azimuth. Off bore sight angles (OBA) of the target are then determined from the target's actual azimuth. Normalized received signal values of ?V are converted to nearest-valued integers. The OBA s that correspond to each integer-valued normalized received signal are averaged and can then be plotted as a function of normalized received signal value ?V. Different tables or plots can be constructed for elevation angles. An equation of a best-fit line the matches or at least closely approximates the plotted data is determined to smooth the actual data.

Abstract: A monopulse radar tracking method which analyzes boresight error information provided a monopulse radar to determine a location for two targets. The monopulse radar tracking method analyzes the boresight error information to determine an angle of arrival for a dominant target and a secondary target.

Abstract: A method for determining an angle for each of two RF signals at different frequencies and offset from each other. The average angle of a composite signal is obtained from the two RF signals over a frequency difference period by averaging the frequency difference period. The average angle of the composite signal is the dominant signal's angle. The smaller signal's angle is then calculated from the dominant signal's angle, an angle centroid, and the signal voltages for the two RF signals.

Abstract: A system for generating a pseudomonopulse tracking error includes an antenna system (401) that generates a sum antenna beam and a difference antenna beam. The sum antenna beam has a pattern with a peak gain on the boresight axis, and the difference antenna beam has a pattern that is circularly symmetric and forms a null about the boresight axis. The difference antenna beam has a relative phase that varies 360 degrees around the boresight axis. A differential phase dispersion is provided as between the sum and difference RF channels (405, 407) to providing a rotating scanning plane (702).

Abstract: A method for determining an angle for each of two RF signals at different frequencies and offset from each other. The average angle of a composite signal is obtained from the two RF signals over a frequency difference period by averaging the frequency difference period. The average angle of the composite signal is the dominant signal's angle. The smaller signal's angle is then calculated from the dominant signal's angle, an angle centroid, and the signal voltages for the two RF signals.

Abstract: System for dynamically tracking a position of a target with an antenna in a communication system. The system includes an antenna system (410) configured for generating a sum and difference antenna pattern (201-1, 201-2). A sum RF channel (401) is coupled to a sum channel output of the antenna system. A difference RF channel (402) is coupled to a difference channel output of the antenna system. An RF coupler (422-1) is provided that has a first input coupled to the sum RF channel and a second input coupled to the RF difference channel. One or more coupling control devices (418-1, 418-2) selectively vary an effective coupling value as between the difference channel and the sum channel. An antenna tracking error signal is generated at an output of the coupler.

Abstract: An on-vehicle radar and a method of determining an axial deviation of the radar using stationary objects free of erroneous determination are disclosed. The amount of axial deviation of the radar is determined from the calculated stationary object line based on the distribution of stationary objects. In the case where such a factor for determining the calculated stationary object line as to reduce the calculation accuracy of axial deviation is detected in the distribution of stationary objects, the calculation of the amount of the particular axial deviation is canceled.

Abstract: A method and apparatus for use in determining the range in a single time sample from a platform to a target are disclosed. The method includes receiving radiation emanating from the target at two points on the platform in a common time sample; detecting the received radiation and generating a signal representative thereof; and processing the signal. The signal is processed to determine a respective angle to target from two points on the platform by using a correlation between received signal amplitude and respective angle; and determine the range from the platform to the target from the respective angles and the separation distance between said two points in a single signal-to-noise sufficient sample. The apparatus includes a plurality of optical channels through which the apparatus can receive radiation emanating from the target, the optical channels and a plurality of electronics.

Abstract: Reducing antenna boresight error includes receiving radar pulses reflected from the ground, where pulses are emitted from the antenna of a radar system, reflected by the ground, and received by the antenna. The return pulses carry information about the ground. Measurement indices are established from radar and platform parameters, and a clutter spectrum is generated from the return pulse information. The amplitude of the clutter spectrum is measured at each of the measurement indices. Whether there is an amplitude imbalance is established in accordance with the measured amplitudes. An error estimate describing an antenna boresight error is determined if there is an amplitude imbalance.

Abstract: An invention is provided for determining the azimuth pointing angle of a moving monopulse antenna. Pulses of energy are broadcast at the surface of a planetary body. Reflected signals are received from the surface of the planetary body using a plurality of feeds. A monopulse ratio is then calculated based on a sum pattern and a difference pattern. The sum pattern is based on the sum of the reflected signals received using the feeds, and the difference pattern is based on a difference of the reflected signals received using the feeds. An azimuth pointing angle of a monopulse antenna is then calculated using the monopulse ratio.

Abstract: Reducing antenna boresight error includes receiving radar pulses reflected from the ground, where pulses are emitted from the antenna of a radar system, reflected by the ground, and received by the antenna. The return pulses carry information about the ground. Measurement indices are established from radar and platform parameters, and a clutter spectrum is generated from the return pulse information. The amplitude of the clutter spectrum is measured at each of the measurement indices. Whether there is an amplitude imbalance is established in accordance with the measured amplitudes. An error estimate describing an antenna boresight error is determined if there is an amplitude imbalance.

Abstract: A radar system mounted in a reference vehicle can detect a distance and orientation of a preceding vehicle to thereby compute a relative position of a width center of the preceding vehicle. A curving radius of the reference vehicle is then detected for computing a relative rotation angle between a direction from the reference vehicle and a longitudinal direction of the preceding vehicle. Relationship between a relative rotation angle and a lateral bias of the relative position of the width center is previously prepared in a map. The computed relative rotation angle is applied on the map, so that the corresponding lateral bias is obtained to correct the computed relative position of the width center of the preceding vehicle. Thus, the width center of the preceding vehicle moving in an adjacent lane can be accurately estimated.

Abstract: A monopulse radar system generates elevation and azimuth difference monopulse estimates of the location of targets in each range cell, where the target may be either a single or plural target, each of which is made up of multiple scattering sources. Each azimuth-elevation estimate is based on a transmitted pulse or burst at a given frequency, different from other frequencies in a set of pulses or bursts. A test statistic is generated for each set. The statistic relates to the shape in an azimuth-elevation plane of the cluster of estimates. The test statistic is compared with a threshold to decide whether a single target or plural targets exist in the range cell.

Abstract: An automobile radar which serves to provide data for cruise control or other systems in a host vehicle, comprising means for measuring radar boresight misalignment by detecting the presence of apparent variations in the spacing of stationary objects from the direction of motion of the host vehicle and utilising such detection to compensate for any misalignment.

Abstract: On an element-by-element basis, measure phases between signals at Port A to Port B of the antenna feed network to get a phase measurement angle that corresponds tp an angular difference between outgoing radar signals and target echo return signals; applying a least squares fit equation to the angular distance to get a correction phase slope across the array, &dgr;0, and applying a phase slope correction of &dgr; to the phases of the transmitted signal.

Abstract: A method is described in which the correction of the detection range of a distance sensor, which is installed with an eccentricity laterally offset with respect to the central axis of a motor vehicle. In order to correct the detection range, a correction angle (a) is used, with which the eccentricity (y) of the distance sensor (3) is corrected at the time of its installation. Thus the distance sensor (3) is not aligned parallel to the longitudinal axis of the vehicle, but to its central axis. Thus, the detection range is advantageously covered approximately symmetrically to the longitudinal axis of the vehicle. The correction angle (a) is determined either empirically, via appropriate test measurements, or mathematically.

Abstract: Disclosed is a method and apparatus for improving airborne vehicle tracking and guidance systems by reducing boresight error induced by polarization of the RF energy impinging on the vehicle radome. The radome wall is formed with a taper which gradually increases from the base near the vehicle antenna to the tip according to a disclosed formula which accounts for frequency, incidence angle, look angle, and the dielectric constant of the radome material. This taper of the radome minimizes the crossplane boresight error component magnitude which is polarization sensitive and produces a polarization insensitive inplane boresight error component. Also disclosed is a method of electronically compensating such radomes for boresight error where the radome boresight error data accumulated during testing is digitized and processed for compensating data in the vehicle electronic system to provide compensated tracking data for the vehicle guidance system.

Abstract: A radar apparatus is provided with signal converting means for FFT-transforming an output signal of reception means for detecting a reception electromagnetic wave; amplitude peak value detecting means for detecting a peak value of an amplitude level from a spectrum made by data converted by this signal converting means; beam scanning means for changing a beam direction of a transmission electromagnetic wave and also a beam direction of the reception electromagnetic wave; and measured-angle processing means operated in such a manner that when the same target object can be detected along a plurality of beam directions which are changed by the beam scanning means, an angle of the target object is calculated by employing the peak value of the amplitude levels along the respective directions, acquired by the amplitude detecting means, whereas when the target object is detectable only along a single beam direction, the angle of the target object is judged as preset angles D1, E1, F1.

Abstract: In a radar system, which is used particularly in motor vehicles, the angle at which a detected radar target is located are determined by providing that echo signals of the radar target are picked up via at least two reception channels, and their amplitudes are standardized and compared with standardized values, stored in memory, of a duplex antenna graph of the radar system.

Abstract: A method for calibrating the radar system includes the steps of: replacing stored statistically generated "average" error correction coefficients with error correction coefficients personal to a missile under test. More particularly, stored in the missile's memory are: (a) first personalized error correction coefficients generated in response to test signals produced internal to the missile and injected into a monopulse arithmetic unit for the missile's receiver/processor; and (b) a second set of personalized error coefficients generated in response to test signals external to the missile and injected through the missile's antenna to the receiver/processor. The missile includes a radio frequency (R.F.) energy test signal generator for performing a test during the missile's flight to determine "in-flight" personalized error correction coefficients. The test is performed in-flight by injecting the R.F.