Radome structures comprising a structural layer comprising a fiber reinforced thermoplastic composite including a fiber reinforcement and a thermoplastic resin. In addition, one or more RF matching layers may be disposed on at least one side of the structural layer. The RF matching layer comprising a first dielectric constant value that is lower than that a dielectric constant value of the structural layer. In this regard, the RF matching layer may provide smaller discrete changes in dielectric constant through a thickness of the radome to provide enhanced RF performance. In an example, a resin content of the thermoplastic resin of the fiber reinforced thermoplastic composite is not fewer than 25 weight percent and not more than about 60 weight percent, which provides enhanced RF performance relative to structural performance of the radome. In turn, manufacturing cost and complexity may be reduced by use of the thermoplastic materials as described herein.

A mounting system for an aircraft fuselage includes one or more fixed anchors attached to the fuselage. A plurality of vertically adjustable anchors are likewise attached to the fuselage, wherein each vertically adjustable anchor includes a spinwheel on a threaded shaft. An adapter plate is attached to the fixed anchors and the adjustable anchors, wherein a contact surface of the spinwheel directly engages with the adapter plate.

A stealth antenna includes an electromagnetic wave absorbing structure and an antenna patch embedded in the electromagnetic wave absorbing structure. The electromagnetic wave absorbing structure includes an upper dielectric layer, a lower dielectric layer and a spacer disposed between the upper dielectric layer and the lower dielectric layer. The upper dielectric layer includes a dielectric fabric and a conductive coating layer combined with at least a portion of the dielectric fabric. The lower dielectric layer includes a dielectric fabric and has a dielectric constant lower than that of the upper dielectric layer. The antenna patch is disposed between the spacer and the lower dielectric layer.

An antenna cladding is for fastening fuselage fittings protruding from an outer skin of the aircraft. The antenna cladding has a carrier for fastening antenna modules thereto; a radome fuselage cladding fastened to the carrier for contact on the outer skin; and a radome cover, which forms a continuous cover and lining for electromagnetic radiation in a predetermined wavelength range with the radome fuselage cladding. The carrier is a fiber composite adapter plate made of fiber having recesses with inserts, which have connection fittings for connection to the fuselage fittings. The connection fittings are arranged between upper and lower faces of the adapter plate and are designed such that the connection fittings do not protrude beyond the upper side of the adapter plate and the fuselage fittings do not protrude into the adapter plate when connected to the connection fittings, but do not project beyond the upper side thereof.

Antenna elements include a metallic square ring patch and a metallic square ring slot to transmit or receive radio frequency (RF) signals. The antenna elements use several dielectric layers that are separated by a low-dielectric foam layer upon which the square ring patch is positioned. The antenna elements may be arranged into an antenna array that is tunable to collectively generate or receive RF signals to and from airborne and mobile vehicles with an agile, electronically scanning antenna array beam, with no moving parts. The antenna array includes a top section to communicate RF signals; a bottom section to generate a desired RF signal; and a foam layer between the top and bottom sections to separate the ring patch from the ring slot. High isolation between the top section and the bottom section allows the antenna elements to be used in higher gain and high-power arrays without adverse feedback issues.

An antenna array has a plurality of square or rectangular antenna assemblies. Each assembly includes a first antenna assembly surface with a solar cell and a second antenna assembly with one or more antenna elements. The antenna assemblies are interconnected without gaps therebetween to form a first contiguous array surface comprised of the first antenna assembly surfaces and a second contiguous array surface comprised of the second antenna assembly surfaces. The antenna assemblies are connected together by mechanically stored-energy connectors, such as spring tape, that self-deploy the array in space without the use of electric energy.

An antenna system of an unmanned aerial vehicle, the antenna system including a first loop antenna system, a second loop antenna system, and a feed line. The second loop antenna system is spaced apart from the first loop antenna system. The feed line extends between and connects the first loop antenna system and the second loop antenna system.

An integrated imaging and passive directional finding (DF) system for a guided munition or weapons platform includes an electro-optical infrared (EOIR) imager within a nosecone of the weapons platform and configured for imaging of a detected target. The passive DF system includes an array of long periodic array (LPA) antenna elements, each element disposed on a face of a tapered conical ground chassis having a polygonal cross section, the LPA antenna elements self-shielded from the EOIR imager and other electronic components by the ground chassis. Each LPA antenna element scans for signals of interest (SoI) within the ultra-wide band (UWB) frequency range. Geolocation or passive direction finding (DF) based on detected signals of interest may be performed to guide the weapons platform into imaging range of one or more targets of interest, where EOIR imaging may take over for target discrimination and aimpoint refinement.

Examples disclosed herein describe an antenna architecture (e.g., a planar electronically steered antenna architecture) that enables operation at low elevation angles, down to zero degrees from the satellite. The proposed 3SA architecture may improve power consumption and array footprints. The proposed 3SA architecture can support aero terminal implementation on aircraft, enabling the use of GEO, MEO and LEO satellites even in regions having low elevation angles. The architecture may include a horizontal antenna array and vertical antenna array as well as a controller for switching between the antenna arrays.

Antenna elements include a metallic square ring patch and a metallic square ring slot to transmit or receive radio frequency (RF) signals. The antenna elements use several dielectric layers that are separated by a low-dielectric foam layer upon which the square ring patch is positioned. The antenna elements may be arranged into an antenna array that is tunable to collectively generate or receive RF signals to and from airborne and mobile vehicles with an agile, electronically scanning antenna array beam, with no moving parts. The antenna array includes a top section to communicate RF signals; a bottom section to generate a desired RF signal; and a foam layer between the top and bottom sections to separate the ring patch from the ring slot. High isolation between the top section and the bottom section allows the antenna elements to be used in higher gain and high-power arrays without adverse feedback issues.