A method for repairing a damaged area of a stealth composite structure having a stealth function using a scarf patch includes the steps of diagnosing the damaged area; deriving a repair area including the diagnosed damaged area; processing the scarf patch according to the derived repair area; machining a patch hole according to the derived repair area to remove the damaged area; and coupling the scarf patch to the patch hole so that an inner wall of the patch hole and a side surface of the scarf patch face.

A vehicle (2) comprising a vehicle part (4), the vehicle part (4) comprising: an electrically conductive core (6); a non-electrically conductive outer skin (8) made of a radar-absorbent material which surrounds, at least to some extent, the core (6) such that the core (6) is not visible from outside the vehicle (2); and one or more electrically conductive members (10) electrically connected to the core (6); each of the one or more members (10) is a tapered member having a relatively large cross sectional area where that member (10) is electrically connected to the core (6), and tapers from its end that is connected to the core (6) to a point; and the point of each member (10) is located at an outer surface of the external skin (8) such that the point of each of the members (10) is exposed.

A vehicle (2) comprising a vehicle part (4), the vehicle part (4) comprising: an electrically conductive core (6); a non-electrically conductive outer skin (8) made of a radar-absorbent material which surrounds, at least to some extent, the core (6) such that the core (6) is not visible from outside the vehicle (2); and one or more electrically conductive members (10) electrically connected to the core (6); each of the one or more members (10) is a tapered member having a relatively large cross sectional area where that member (10) is electrically connected to the core (6), and tapers from its end that is connected to the core (6) to a point; and the point of each member (10) is located at an outer surface of the external skin (8) such that the point of each of the members (10) is exposed.

A system for bistatic radar target detection employs an unmanned aerial vehicle (UAV) having a ramjet providing supersonic cruise of the UAV. Deployable antenna arms support a passive radar receiver for bistatic reception of reflected radar pulses. The UAV operates with a UAV flight profile in airspace beyond a radar range limit. The deployable antenna arms have a first retracted position for supersonic cruise and are adapted for deployment to a second extended position acting as an airbrake and providing boresight alignment of the radar receiver. A mothership aircraft has a radar transmitter for transmitting radar pulses and operates with an aircraft flight profile outside the radar range limit. A communications data link operably interconnects the UAV and the tactical mothership aircraft, transmitting data produced by the bistatic reception of reflected radar pulses in the UAV radar antenna to the mothership aircraft.

A system includes a matrix material to remove heat from an object. The matrix material includes a plurality of vascular structures. Each of the vascular structures are filled with a fluid. At least one transducer generates field-induced forces into the fluid within the vascular structures of the matrix material. At least one controller pulses the transducer to generate the field-induced forces into the fluid within the vascular structures. The field-induced forces generate fluid flow within the vascular structures to remove the heat from the object.

An aircraft weapons control system including a weapons stores processor panel for receiving input signals from a weapons input; a weapons interface for receiving fire signals from the weapons stores processor panel to control firing of aircraft weapons; and a flight management system in communication with the weapons stores processor panel and the weapons interface, the flight management system providing control signals to the weapons interface; wherein the weapons stores processor panel implements safety interlocks to prevent or enable firing of the aircraft weapons.

An aircraft weapons control system including a weapons stores processor panel for receiving input signals from a weapons input; a weapons interface for receiving fire signals from the weapons stores processor panel to control firing of aircraft weapons; and a flight management system in communication with the weapons stores processor panel and the weapons interface, the flight management system providing control signals to the weapons interface; wherein the weapons stores processor panel implements safety interlocks to prevent or enable firing of the aircraft weapons.

Particular embodiments include a mission payload mounting apparatus. The mission payload apparatus includes a pressurized door plug assembly on a side of an aircraft fuselage and a strut having a first end and a second end. The strut extends from an interior of the aircraft fuselage through the pressurized door plug assembly to an exterior of the aircraft fuselage. The first end of the strut is connected to the interior of the aircraft fuselage. One or more payloads are attached to the strut.

Particular embodiments include a mission payload mounting apparatus. The mission payload apparatus includes a pressurized door plug assembly on a side of an aircraft fuselage and a strut having a first end and a second end. The strut extends from an interior of the aircraft fuselage through the pressurized door plug assembly to an exterior of the aircraft fuselage. The first end of the strut is connected to the interior of the aircraft fuselage. One or more payloads are attached to the strut.

A drive device includes a screw-and-nut system comprising a threaded rod and a first nut that is connected to the threaded rod by means of a screw connection; a gearset, allowing a rotational movement to be transmitted to the threaded rod, a first toothed wheel and a second toothed wheel engaged with the first toothed wheel; a set of stops comprising a first stop connected to the first wheel rotating about an axis of rotation of the first wheel and a second stop connected to the second toothed wheel rotating about an axis of rotation of the second wheel, the first stop and the second stop being configured and arranged to butt against one another so as to limit an angular travel of the threaded rod at a first angular position in a first direction.