An electronically scanned array is comprised of a plurality of radiating horns embedded in a nose cone. The radiating horns are configured as an electronically scanned array. The nose cone comprises a dielectric material with a known thickness in front of the radiating horn opening. Each radiating horn is driven by a phase shifter. The phase shifters are configured to produce a radiation pattern with attenuated side lobes.

The present invention provides a structure at least partially transparent to radio frequency signals, the structure being formed of a tessellated polyhedral material comprising a plurality of polyhedral cells. The present invention also provides a method of manufacturing the same.

An antenna device is presented comprising: a conformal antenna body which has a desired geometry corresponding to a front portion of a platform on which the antenna device is to be mounted, and an antenna unit carried by the antenna body. The antenna unit comprises at least one phased array of antenna elements, the antenna elements of each of the at least one array being arranged in a spaced-apart relationship in a closed loop path along a circumference of the antenna body having a desired geometry corresponding to the front portion of the platform on which the antenna unit is to be mounted. Each of the antenna elements is configured as an end-fire antenna element capable of emitting linearly polarized radiation. The array of the antenna elements is operable as a forward looking end-fire antenna array, enabling electronic steering of an antenna beam by controllably modifying phases of the antenna elements of each array.

Systems, devices, and methods for a vertical take-off and landing (VTOL) aerial vehicle having a first GPS antenna and a second GPS antenna, where the second GPS antenna is disposed distal from the first GPS antenna; and an aerial vehicle flight controller, where the flight controller is configured to: utilize a GPS antenna signal via the GPS antenna switch from the first GPS antenna or the second GPS antenna; receive a pitch level of the aerial vehicle from the one or more aerial vehicle sensors in vertical flight or horizontal flight; determine if the received pitch level is at a set rotation from vertical or horizontal; and utilize the GPS signal not being utilized via the GPS antenna switch if the determined pitch level is at or above the set rotation.

A lightning protection system of an aircraft includes a wall defining an inner surface and an outer surface. The outer surface is configured to come into contact with a mass of air located around the aircraft. The lighting protection system also includes at least two electrically conductive lighting traps received in holes traversing the wall and at least one strip with pellets having an electrically insulating substrate and electrically conductive pellets spaced apart from one another on the electrically insulating substrate. The strip with pellets is fastened on the wall by the two lightning traps. The strip with pellets is attached on the inner surface of the wall.

An aircraft radar assembly (200) comprising: a radome (202); a radar antenna (100) housed within the radome (202), the radar antenna (100) having a surface for transmitting and/or receiving radar waves; and rotation means (204) configured to rotate the radar antenna (100) within the radome (202) about an axis of rotation (206); wherein the surface is oblique to the axis of rotation (206).

An aerial vehicle includes a body and an antenna assembly mounted to the body. The antenna assembly includes a fairing component comprising a hollow body, a conductive coating formed on at least an inner surface of the fairing component, a plurality of antenna elements formed in the conductive coating, each antenna element including a first slot line defining a first transmission line and a second slot line defining a second transmission line, an insulator sleeve disposed within the fairing component, wherein an outer surface of the insulator sleeve at least substantially matches an inner surface of the fairing component, and a plurality of cable assemblies operably coupled to the plurality of antenna elements, wherein each cable assembly is coupled to a respective antenna element.

A missile, in particular a guided missile, has a missile body and a radar sensor unit for acquiring a target object. The radar sensor unit contains at least one radar antenna, strip-shaped in the longitudinal direction, that is mounted or integrated on a circumferential surface of the missile body such that the longitudinal direction of the at least one strip-shaped radar antenna is aligned in the direction of the missile longitudinal axis.

Disclosed is a calibration device of an imaging system for a moving carrier, the imaging system including: a support panel; an antenna array comprising radiating elements positioned on the support panel; and optical sensors capable of providing images and positioned on the support panel. The calibration device includes at least one optical pattern generator, each generator being secured to the support panel.

An aircraft nose radome has a first portion that is transparent to X band microwave energy, and a second portion that is transparent to W band microwave energy. The second portion may be an insert that is secured to the radome at an opening formed therein. The insert may have a multi-layer structure with first, second and third layers, a fourth layer of foam between the first and second layers, and a fifth layer of foam between the second and third layers. The insert may include a plurality of spaced-apart, elongated reinforcing members or ribs between the first and second layers and between the second and third layers that extend along a longitudinal direction defined by the insert. The insert may have a serrated cross-sectional configuration.