Abstract: A system and method for a multi-panel multi-function active electronically scanned array (AESA) radar operation receives radar commands from individual aircraft systems and segments a plurality of AESA panels fixed (at variable azimuth/elevation about the aircraft) into a plurality of subarrays to carry out each individual function commanded by the individual aircraft system. Dependent on aircraft status and phase of flight, the and individual AESA are designated for use and the subarrays are sized based on desired radar function at the specific phase of flight and specific threat associated with the phase. The system dynamically shifts the designated AESA, subarray size, beam characteristics, power settings, and function to enable multiple simultaneous function of the suite of AESA panels.

Abstract: A system and method for a multi-beam multi-function active electronically scanned array (AESA) radar operation receives radar commands from individual aircraft systems and segments a single AESA fixed panel into a plurality of subarrays to carry out each individual function commanded by the individual aircraft system. Dependent on aircraft status and phase of flight, the subarrays are sized based on desired radar function at the specific phase of flight and specific threat associated with the phase. The system dynamically shifts the subarray size, beam characteristics, power settings, and function to enable multiple function of a cost effective single AESA panel.

Abstract: A system of spiral antennas is incorporated into aircraft body panels. The spiral antennas may be slot or printed material antennas, cavity backed for unidirectional communication, or open for bi-directional communication. The spiral antennas are operated in concert as a steerable array. The spiral antennas are utilized for various signal functions including ultra-wideband communications and electronic support measures interferometry.

Abstract: The hazard warning system includes processing system for detecting an HVB condition. The aircraft warning system can use at least two types of radar returns and can measure decorrelation time to detect the HVB condition. Warnings of HVB conditions can allow an aircraft to avoid threats posed by such conditions including damage to aircraft equipment and engines.

Abstract: A system of high-frequency (HF) antennas is disposed on various aircraft body panels. The antennas are configured for orthogonal polarization such that NVIS may be operable no matter the state of the ionosphere. The antennas are disposed on substantially perpendicular body panels so that, when operated in concert, the resulting signals have opposite polarization and at least one signal will bounce off the ionosphere.

Abstract: A radio altimeter includes an electronically scanned array antenna. Orthogonal sweeps by the electronically scanned array antenna are used to identify a highest point in a region beneath the aircraft without the need for strong reflection. The electronically scanned array antenna may be reconfigured to scan a subregion including the highest point with a higher frequency beam and/or integrate multiple sweeps over time for a more accurate measurement.

Abstract: A system of spiral antennas is incorporated into aircraft body panels. The spiral antennas may be slot or printed material antennas, cavity backed for unidirectional communication, or open for bi-directional communication. The spiral antennas are operated in concert as a steerable array. The spiral antennas are utilized for various signal functions including ultra-wideband communications and electronic support measures interferometry.

Abstract: An antenna system and method includes or uses a set of M antenna structures and a cross bar beam former. The analog (or digital) cross bar beam former includes a set of M N to 1 (M(N×1)) interfaces, each of the M N to 1 interfaces having a first line coupled to a respective one of the set of the M antenna structures. The cross bar beam former also includes a set of N 1 to M (N(1×M)) interfaces, each of the N 1 to M interfaces having a set of M second lines, each of the M second lines being coupled to a respective one of the M N to 1 interfaces. Each of the N 1 to M interfaces includes a third line for a respective one of N independent beams.

Abstract: A system and method for ESA quadrant mechanical reconfiguration functions to shift some of the complexity from algorithmic manipulation of received radar data to mechanical transformation of a simple panel structure to achieve desired performance in a desired ESA boresight. The system receives a rotation trigger based on an external event such as altitude and mission and causes two or more simple ESA panels to rotate from a first azimuthal position to a second common azimuthal position without stopping at an intermediate azimuth. Once positioned, each individual rotational ESA panel is combined to function as a single aggregate ESA enabling desired performance in field of view, resolution, and range along a common boresight.

Abstract: A system of antennas, each having disparity operating frequencies, are incorporated into the same aircraft body panels. HF antennas define loops with large internal areas; additional higher frequency antennas are disposed within that large internal area. The higher frequency antennas are sufficiently different so as to prevent coupling. Antennas operating in the same frequency range, disposed on different parallel surfaces are operated in concert as a steerable array.

Abstract: A quadrature fed four-port radiating element is fed by an active quadrature combiner feed network. The active quadrature four-port combiner is ultra-wide band and includes RF signal amplification. The resulting feeder exhibits a size reduction over existing passive balanced/unbalanced technology on the order of five thousand to one. Such antennas may be incorporated into radio frequency integrated circuit transmit/receive modules. Such antennas may also be integrated with front end low noise amplifiers. Such feeder network enables practical implementation of two-port feeders compatible with AESA array lattice restrictions.

Abstract: Disclosed are embodiments of exterior aircraft assemblies integrating compatible elements. In one example, an integrated aircraft assembly includes an aerodynamic housing attachable to an aircraft, an antenna system including at least one antenna element housed within the aerodynamic housing, and a lighting system including at least one light fixture housed within the aerodynamic housing. The at least one antenna element and the at least one light fixture may be co-located within then housing or mounted separately on the housing.

Abstract: A system and method for cooperative aerial vehicle collision avoidance provides an ESA-based sensor network capable of high-resolution threat proximity measurements and cooperative and non-cooperative collision avoidance in the full spherical volume surrounding an aerial vehicle. The system incorporates a plurality of ESA panels onto the airframe where the conical scan volumes overlap leaving no gaps in spherical proximity coverage. The resulting received data is stitched together between the neighboring ESA panels and used to determine a position and vector for each threat aerial vehicle within range. The data is transmitted through a cooperative collision avoidance network to nearby aerial vehicles, and presented to the autopilot and flight crew to increase situational awareness. The system determines a maneuver for the aerial vehicle and a maneuver for the threat aerial vehicle based on relative maneuvering capabilities to maintain desired separation.

Abstract: A radio altimeter includes an electronically scanned array antenna. Orthogonal sweeps by the electronically scanned array antenna are used to identify a highest point in a region beneath the aircraft without the need for strong reflection. The electronically scanned array antenna may be reconfigured to scan a subregion including the highest point with a higher frequency beam and/or integrate multiple sweeps over time for a more accurate measurement.

Abstract: The system can include and the method can provide a first printed circuit board antenna tile. The first printed circuit board antenna tile comprises a repeating pattern of antenna element units. The antenna can also include and the method can also provide a second first printed circuit board antenna tile comprising the repeating pattern. The first printed circuit board antenna tile and the second first printed circuit board antenna tile can be attached such that the antenna elements maintain the same spacing in an X-Y plane associated with the repeating pattern across a boundary the first printed circuit board antenna tile and the second first printed circuit board antenna tile.

Abstract: Disclosed are embodiments of exterior aircraft assemblies integrating compatible elements. In one example, an integrated aircraft assembly includes an aerodynamic housing attachable to an aircraft, an antenna system including at least one antenna element housed within the aerodynamic housing, and a lighting system including at least one light fixture housed within the aerodynamic housing. The at least one antenna element and the at least one light fixture may be co-located within then housing or mounted separately on the housing.

Abstract: An antenna and manufacturing process for antennas produce radiating elements of desired size for certain frequency bands by bump mounting radiating elements to the printed circuit board substrate. Driving circuitry is stacked to save space. Also, the radiating elements are made using a different dielectric constant material as compared to the substrate. Tiling radiating elements or sub-arrays or radiating elements with bump mounting allows for spatial separation that eliminates surface waves. Bump mounted radiating elements also allow for multiple sizes of radiating elements in which smaller size provides lower directivity to cover broader beam scan performance.

Abstract: An ESA system includes first antennas, second antennas, a power supply, a transmit module and/or receive module, and a controller. The first antennas operate over a first frequency bandwidth from a first frequency to a second frequency greater than the first frequency. The second antennas operate over a second frequency bandwidth from the first frequency to a third frequency less than the second frequency. The transmit module receives DC power from the power supply and provides RF power corresponding to at least one first control point to the antennas. The controller adjusts the at least one first control point based on a predetermined ratio of a first RF signal strength associated with the first antennas to a second RF signal strength associated with the second antennas, a first passive antenna gain of the first antennas, and a second passive antenna gain of the second antennas.

Abstract: A radar system includes an electronically scanned array of dual orthogonal linearly polarized radiating elements. Each of the radiating elements is fed by a switch driven by a radar processing unit. The switch successively places each radiation element in a vertically polarized configuration and horizontally polarized configuration so that the antenna can transmit and receive both vertically and horizontally polarized images within the radar epoch/pulse timing sequence of the radar system. The vertically polarized image and horizontally polarized image are sufficiently close in time to be collated to form a multi-dimensional image. The switch may be driven at rates other than the radar system clock as dictated by algorithms for detecting weather related threats.

Abstract: A system and method for applying an adaptive adjustment or taper to an electronically scanned array (ESA) weather radar based on feedback from the weather radar. To minimize ground clutter and enable the ESA to display hazardous weather phenomena, the system adaptively adjusts amplitude and phase of ESA elements to adjust the far field pattern shape and sidelobes to maintain a desirable signal to clutter ratio. The system identifies ground clutter as a strong ground return over several azimuths depending on the radar beamwidth. Once the system IDs the ground clutter, it adaptively adjusts on receive for for the upcoming azimuths. The system selectively suppresses sidelobe echoes while maintaining the signal to noise (SNR) for weather targets. The system adaptively adjusts in real time as well as adjusting using precomputed historically accurate tapers stored in memory.