A device for radar target feature recognition based on optical time-delay fast interference scanning. The device includes an antenna unit, an electro-optical converter, an optical time-delay numerical control scanning device, an optical combiner, a photoelectric detector and a power characteristic analysis device. The device quickly scans the delay amount of the two signals through the optical delay line, and calculates the power of the combined signal through photoelectric conversion and linear power detection. By observing the relationship between the combined power and the delay time, the rapid identification of the target radar signal characteristics is realized.

Techniques and architectures for managing radar sensor processing chains. A first high-frequency radio signal is received with a first RF receiver in the plurality of RF sensor suites on a host platform. The received high-frequency radio signal is converted to a lower second frequency range. A chirplet transform is performed on the signal in the second frequency range. Stored relative location information for a second RF receiver in the plurality of RF sensor suites is retrieved. Radar waveform information corresponding to the second RF receiver in a processing stream corresponding to the first RF receiver is extracted by utilizing the retrieved information and results from the chirplet transform. A point cloud is generated based on the converted signal in the second frequency range and the extracted radar waveform information.

A mode extractor for extracting TM01 mode from an electromagnetic signal, including a first and second turnstile junction, each of the turnstile junctions having first port, four second ports of rectangular waveguide which are mutually orthogonal and orthogonal to first port and matching section provided at least partially in center region of respective turnstile junction, center region being located at intersection of first port and four second ports wherein first and second turnstile junction are arranged so that longitudinal axes of their first ports are aligned with each other and their first ports are facing in opposite directions, each of the second ports of first turnstile junction is electromagnetically coupled to corresponding one of second ports of second turnstile junction, and a coaxial coupling device is inserted into matching section of first turnstile junction so that a portion of coaxial coupling device extends into first port of first turnstile junction.

High-performance 4-D Sparse MEMO Phased Array imaging and object detection radars with substantially reduced hardware and processing specifications are presented for automotive, ariel, and other application spaces. The radar antennas have 2-D angular sparse array and MIMO (Multiple Input and Multiple Output) features that can be implemented with a variety of subarrays or Antenna in Packages (AiPs) greatly simplifying the system manufacturing and feasibility. The significantly reduced data processing requirements also become feasible with the sparse subarray architectures. Advanced signal processing algorithms are presented, when coupled with the sparse and MIMO features, allow improved 2-D angular resolution of objects, improved imaging, and low sidelobes allowing the resolution of weaker targets in the presence of stronger target reflections.

Embodiments are directed to operating an analog signal processing circuit to emulate a Rotman lens. The analog signal processing circuit applies a plurality of time delays to a plurality of signals associated with a plurality of beam ports. The analog signal processing circuit forms a plurality of output beams for transmission by a plurality of array ports included in an array based on the time delayed signals by summing the time delayed signals. The time delays are based on a direction of transmission of the output beams.

The disclosure describes techniques to scan a radio frequency antenna beam along one or more axes. For example, for a wide transmit beam oriented such that the long axis is in azimuth, this disclosure describes techniques to scan the transmit beam in elevation, in the direction of a short axis of the transmit beam. The radar receive aperture may be synchronized with transmit beam to scan the radar receive aperture using RF beamforming such that the elevation scan of the field of view of the radar receive aperture follows the elevation scan of the transmit beam. The radar receiver circuitry may also down-convert the received radar signals to an intermediate frequency (IF). The radar receiver circuitry may digitally form monopulse receive beams at IF within the processing circuitry of the receiver electronics and digitally scan the monopulse receive beams along the long axis of the field of view.

A SIL monopulse radar includes a self-injection-locking oscillator (SILO), a transmit antenna, two receive antennas, a hybrid coupler, a first demodulator, a second demodulator and a processor. The transmit antenna transmits the oscillation signal of the SILO to object. The two receive antennas receive a reflected signal from the object as a first echo signal and a second echo signal. The hybrid coupler outputs a difference signal and a sum signal. The difference signal is injected into the SILO. The first demodulator frequency-demodulates the oscillation signal to produce a first demodulated signal. The second demodulator phase-demodulates the sum signal by using the oscillation signal as a reference signal to produce a second demodulated signal. The processor processes the first and second demodulated signals to produce a monopulse ratio signal. The SIL monopulse radar can identify the posture and motion of a human body by analyzing the monopulse ratio signal.

A method is provided for operating a monopulse active electronically scanned array (AESA) radar system on an aircraft. This system includes multiple emitter elements each with corresponding radio frequency (RF) channels including beamforming integrated circuits (BFICs). The method includes defining multiple modes, with each mode defining an effective aperture by specifying a different plurality of the emitter elements, and determining a preferred state of the AESA system based on a flight phase or environment of the aircraft. One of the plurality of modes is identified as corresponding to the preferred state, and beam steering is calibrated via a beam steering controller (BCM) to produce sum, azimuth difference, and elevation difference beams under the constraint of illuminating all of and only the plurality of the emitter elements corresponding to the selected one of the plurality of modes. BFICs of the emitter elements are then energized according to this calibrated beam steering.