A method of controlling a self-propelled flying device that seeks a target. A desired time to reach the target is obtained. The position of the target is acquired. A bias value is calculated, and the flight of the device towards the target is adjusted for a period of time using the bias value. The bias value is calculated so that the device reaches the target at the desired time.

A sensor waveguide system includes a sensor waveguide and a plurality of sensors. The sensor waveguide includes a main body defining a peak, a base, an axis of rotation, and a plurality of waveguide channels. The main body converges from the base to the peak to create a predetermined tapered profile. The plurality of waveguide channels are oriented parallel to the axis of rotation of the sensor waveguide and each waveguide channel defines an exit disposed at the base of the main body. A sensor is disposed at the exit of each of the plurality of waveguide channels.

Apparatus and associated methods relate to using a plurality of antennas radially distributed about a rotatable turret to sequentially scan a field of view. Each of the plurality of antennas directs an electromagnetic beam and senses its reflection along a principal direction defined by a roll position of the rotatable turret and an azimuthal beam angle. The principal directions of the antennas have a unique azimuthal beam angle relative to a boresight (i.e., axis of rotation). As the turret rotates, each of these antennas is sequentially turned on at a first roll position and off at a second roll position. This enables electromagnetic beams generated by the antennas to pan a scene both in azimuth and roll. An image processor then determines, based on the reflected signals received by the plurality of antennas, directions to and/or velocities of objects within the scanned field of view.

A wideband direction finding (WBDF) aperture employs a limited number of extreme wideband end-fire antenna elements capable of covering a wide frequency bandwidth. Arranging variable sized antenna elements in a specific pattern, the WBDF aperture enables direction finding capability covering an extreme wide frequency band. The pattern arrangement of variable sized elements offers the signal discernment to limit ambiguities in signal angle of arrival. This small form factor design enables the WBDF aperture to be mounted on the surface of a missile, munition, or small UAS wing or fuselage. The WBDF aperture offers a combination of differing sized antenna elements arranged in a specific pattern, combined with direction finding and signal tracking to provide an unambiguous relative azimuth and elevation angle of the target.

A radar antenna includes a plurality of horns in the annular space of a munition nose cone. The horns are disposed near the exterior surface of the nose cone. In a further aspect, the nose cone may be injection molded or additively manufactured so that the horns are embedded a known distance from the exterior surface. In a further aspect, the horns placed in either a transmit mode or a receive mode so as to maintain a minimum special separation between transmitting horns and receiving horns.

The present disclosure comprises an evaporative cooling assembly (200) for cooling an apparatus (220), and a method for cooling an apparatus (220). The evaporative cooling assembly comprises a refrigerant tank (202), the refrigerant tank (202) containing refrigerant (204). The apparatus also comprises a first evaporator (210) configured to be positioned proximal to the apparatus (220), and a second evaporator (216) positioned to cool the refrigerant tank (202). Each of the first evaporator (210) and the second evaporator (216) are in fluid communication with the refrigerant tank (202), and the second evaporator (216) is positioned downstream of the first evaporator (210). The method for cooling a heated apparatus (220) comprises passing a refrigerant (204) from a refrigerant tank (202) to a first evaporator (210), which is located proximal to the apparatus (220). At least part of the refrigerant is evaporated, and then passed to a second evaporator (216), which is positioned to cool the refrigerant tank (202).

A spatially-distributed architecture (SDA) of antennas transmits respective uniquely coded signals. A first receiver having a known position in a coordinate system defined by the SDA receives reflected versions of the uniquely coded signals. A first processor receives the reflected versions of the uniquely coded signals and identifies a position of a non-cooperative object in the coordinate system. A platform having a second receiver receives non-reflected versions of the uniquely coded signals. The platform determines a position of the platform in the coordinate system. In an example, the platform uses a self-determined position and a position of the non-cooperative object communicated from the SDA to navigate or guide the platform relative to the non-cooperative object. In another example, the platform uses a self-determined position and information from an alternative signal source in a second coordinate system to guide the platform. Guidance solutions may be generated in either coordinate system.

A flight guidance technique for guiding an aerial vehicle to track a target is provided. A flight guidance apparatus transmits a radio frequency (RF) signal encoded with transmission direction information to an antenna. A guided aerial vehicle receives RF signals transmitted through two antennas spaced apart from each other, measures a phase difference between the RF signals, and compares the measured phase difference with a result of decoding the transmission direction information to control a direction of flight.

Provided is an apparatus for detecting airborne objects comprising a kill vehicle bus having a radar sensor. The radar sensor may be an interferometric sensor comprising a plurality of transmit-receive arrays. Each of the transmit-receive arrays may be adapted to be stowed in a stowed position in or on the kill vehicle bus, and may be adapted to be expandable from the stowed position to an operable position.

An ordnance munition is included in an intelligent ordnance projectile delivery system and equipped with targeting and guidance systems that allow the ordnance munition to collaborate with other devices to intelligently select targets and/or to guide the ordnance munition to its selected target. The ordnance munition may be configured to generate first location information based on its determined approximate location, send the generated first location information to a wireless transceiver in proximity to the first ordnance munition, and receive location information from the wireless transceiver in response. The ordnance munition may determine its more precise location based on the received location information, and generating second location information based on the more precise location. The ordnance munition may change or adjust its flight path or trajectory based on the generated second location information.