Methods and apparatus for molding and joining composite parts are disclosed herein. An example method includes positioning a base mandrel over a tool base, laying up plies of material over the base mandrel and the tool base to form a support structure base layup, curing the support structure base layup to form a support structure base, removing the support structure base from the tool base and the base mandrel, and configuring the support structure base to be a first support structure for use with a first radar assembly or a second support structure for use with a second radar assembly.

A multi-functional, multi-layer film or skin which may be used as a covering for a structure or platform incorporates an integrated photovoltaic element and an integrated RF antenna element. The film or skin is suitable for use in various applications, including those involving autonomous, self-powered, mobile communication systems and especially for use as a skin or covering for solar powered aircraft and UAVs. Planar PV cells and planar RF antenna are used to facilitate their integration into the film or skin. The PV cells and RF antenna are configured to face operate outward from opposite faces of the skin. The film or skin addresses potential problems arising from conflicting directional requirements for PV orientation and antenna pointing on mobile platforms. This is accomplished by employing wide angle AR coatings on the PV elements and electrical controls to steer the RF antenna.

An adaptive electronically steerable array (AESA) system comprises a plurality of arrays, each comprising a plurality of radiating elements, each array configured for placement on a forward-facing surface of a different one of a plurality of aerodynamic control surfaces on an interceptor. A plurality of radio frequency (RF) transmissive radome elements, each having an aerodynamic shape complementary to the aerodynamic control surface, are placed over one of the arrays. Control circuitry configures the arrays, independently or in concert, for RF target engagement and communication. Additional arrays may be positioned on side or aft-facing surfaces of the aerodynamic control surfaces for RF communication. The AESA system may be paired with an IR system for dual-mode operation.

According to some aspects, an antenna is provided comprising a substrate, a first conductive region disposed on a first side of the substrate, a second conductive region disposed on a second side of the substrate, and a coaxial transmission line, an inner conductor of the coaxial transmission line electrically coupled to the first conductive region and an outer conductor of the coaxial transmission line electrically coupled to the second conductive region, wherein the second conductive region includes at least one structural feature that functions as a choke when the first and second conductive regions are operated together as an antenna. According to some aspects, an aerial vehicle comprising a conformal antenna is provided.

A system includes a septum sleeve, an aperture fitting, and a removable aperture. The septum sleeve is substantially hollow and is configured to be positioned at least partially within a core of an assembly of an aircraft. The aperture fitting is configured to provide an interface to mechanically fasten the removable aperture. The removable aperture is configured to contain one or more electronic components and to be removably positioned at least partially within the septum sleeve.

Composite antennas and methods of forming the composite antennas are described. In one example, a composite antenna includes a plurality of strips of carbon fiber material, and a metal shim strip. A portion of the metal shim strip is positioned and embedded between two of the strips of carbon fiber material in a layup stack of the strips of carbon fiber material and the metal shim strip. In another example, a method of forming a composite antenna includes cutting carbon fiber material into a plurality of strips of carbon fiber material, cutting metal shim stock into a metal shim strip, arranging the strips of carbon fiber material, the metal shim strip, and an uncured resin into a layup stack of material, and curing the layup stack of material to form a laminate stack.