An aircraft with an aircraft structure that comprises a radome cover opening kinematic and a radome cover shell that is adapted to enclose equipment in a nose region of the aircraft in a closed position. The radome cover opening kinematic may enable movements of the radome cover shell between the closed position and an opened position and vice versa. The radome cover opening kinematic may include a guiding rail that is attached to the radome cover shell, and at least three rollers that are attached to the aircraft structure, wherein a first and a second roller are arranged on opposing sides of the guiding rail, and wherein the second and a third roller are arranged on the same side of the guiding rail.

A sealant is provided for use on an aircraft or other vehicle. The sealant may be used with a gasket. The sealant is a perimeter seal that comprises a polyurea member. The polyurea member is a self-curing, two-component mix. It may cure to a hardness in the range of about 40 to 100 (Shore A). It may maintain an adequate peel strength to withstand multiple thermal and pressure cycling, and may have a working life, wherein it may be shaped, of less than about eleven minutes.

A sealant is provided for use on an aircraft or other vehicle. The sealant may be used with a gasket. The sealant is a perimeter seal that comprises a polyurea member. The polyurea member is a self-curing, two-component mix. It may cure to a hardness in the range of about 40 to 100 (Shore A). It may maintain an adequate peel strength to withstand multiple thermal and pressure cycling, and may have a working life, wherein it may be shaped, of less than about eleven minutes.

An unmanned aerial vehicle (UAV) navigation system includes a portable, ground-based landing pad comprising having a first antenna configured to transmit a data packet; a UAV comprising a second antenna configured to receive the data packet; and second processing circuitry configured to determine a signal strength between the first antenna and the second antenna; determine, based on the signal strength, an orientation of the vehicle relative to the landing pad; and determine, based on a time of flight of the data packet, a distance between the vehicle and the landing pad.

An unmanned aerial vehicle (UAV) navigation system includes a portable, ground-based landing pad comprising having a first antenna configured to transmit a data packet; a UAV comprising a second antenna configured to receive the data packet; and second processing circuitry configured to determine a signal strength between the first antenna and the second antenna; determine, based on the signal strength, an orientation of the vehicle relative to the landing pad; and determine, based on a time of flight of the data packet, a distance between the vehicle and the landing pad.

A platform-mounted radome which includes: a low-profile aerodynamic canopy made of a radio frequency (RF) transparent material, wherein the canopy has a leading edge and a trailing edge and is suitable to accommodate a flat panel satellite communication (SATCOM) antenna; an air-cooling duct connecting an inlet at the leading edge of the canopy and an outlet at the trailing edge of the canopy, wherein the air-cooling duct is designed to transfer naturally cool air collected by the inlet across the canopy when flying; means for transferring heat thermally coupled to heat-generating elements of the SATCOM antenna and the air-cooling duct; and one or more heat sinks located within the air-cooling duct and thermally coupled thereto.

An airfoil system is provided that includes an airfoil. This airfoil includes a first exterior surface, a second exterior surface, a first airfoil segment and a second airfoil segment. The airfoil extends widthwise between the first exterior surface and the second exterior surface. The first airfoil segment includes first composite material and a receptacle. A base of the receptacle is embedded within the first composite material. The second airfoil segment includes second composite material and a key. A base of the key is embedded within the second composite material. The key is mated with the receptacle thereby attaching the second airfoil segment to the first airfoil segment.

A method for conditioning to reduce lightning strike effects is provided herein. The method includes positioning a plurality of tabs on a component. The plurality of tabs are electrically conductive. The component includes at least one of a composite material and a metal material having at least one joint. The method includes positioning the component on a support that is electrically insulated, and connecting a plurality of wires between an initial set of the plurality of tabs and a pulse generator. The pulse generator is configured to generate a plurality of current pulses through the plurality of wires. The plurality of current pulses imitate a plurality of lightning strikes. The method further includes striking the component with the plurality of current pulses from the pulse generator, and reconnecting the plurality of wires to one or more different sets of the plurality of tabs between the plurality of current pulses.

A method for conditioning to reduce lightning strike effects is provided herein. The method includes positioning a plurality of tabs on a component. The plurality of tabs are electrically conductive. The component includes at least one of a composite material and a metal material having at least one joint. The method includes positioning the component on a support that is electrically insulated, and connecting a plurality of wires between an initial set of the plurality of tabs and a pulse generator. The pulse generator is configured to generate a plurality of current pulses through the plurality of wires. The plurality of current pulses imitate a plurality of lightning strikes. The method further includes striking the component with the plurality of current pulses from the pulse generator, and reconnecting the plurality of wires to one or more different sets of the plurality of tabs between the plurality of current pulses.

Aircraft antenna fairing assemblies include a fairing shell and connection components for positionally fixing the fairing shell to airframe structure of an aircraft. The connection components may comprise a guide assembly having a guide head and a receiver defining a guide channel for receiving the guide head therewithin, and a latch assembly for latching the fairing shell to the airframe structure of the aircraft. The receiver of the guide assembly may define a generally C-shaped or generally U-shaped channel for receiving the guide head therewithin.