An optical scanning system includes one or more Micro-Electro-Mechanical System (MEMS) Micro-Mirror Arrays (MMAs) used to scan a field-of-view (FOV) over a field-of-regard (FOR). The MEMS MMA is configured such that optical radiation from each point in the FOV does not land on or originate from out-of-phase mirror segments and a diffraction limited resolution of the optical system is limited by the size of the entrance pupil and not by the size of individual mirrors.

A method and system for coordinating munitions in a salvo to form a constellation in a Global Positioning System (GPS) denied attack of a plurality of targets. Each munition is provided with a datalink communication system to communicate with other munitions and a navigation system for guiding the munition in flight. An estimated position of each munition is determined relative to the other munitions in the salvo via each munitions' datalink communication system. Two-Way Timing and Ranging (TRTW) techniques are utilized to determine positioning of each munition relative to one another. A distance range of each munition relative to the other munitions in the salvo is determined via each munitions' datalink communication system. A constellation formation of the plurality of munitions in the salvo is determined based upon the determined relative position and distance range of each munition relative to one another. A target seeker basket coordinate respectively for each munition in the constellation formation is determined relative to an array of targets. Each munition in the constellation is then navigated in flight to its respective target seeker basket coordinate via its navigation system, wherein navigating to a respective target seeker basket includes coordinating a flight path of each munition in the constellation relative to one another to its respective determined target seeker basket. And coordinating the flight path of each munition includes determining an Estimated Time of Arrival (ETA) for each munition relative to its determined target seeker basket.

A system comprising an unmanned aerial vehicle (UAV) configured to transition from a terminal homing mode to a target search mode, responsive to an uplink signal and/or an autonomous determination of scene change.

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 method includes removably coupling a projectile interface of a dongle to a dongle interface of a projectile. The method also includes loading a dongle code from the dongle onto the projectile. The dongle code identifies a pulse repetition frequency (PRF) code to be recognized by the projectile. The dongle code may be unique to an operator of the projectile. The method may further include, prior to loading the dongle code onto the projectile, loading an operator code onto the projectile, where the dongle code is loaded onto the projectile in response to the projectile authorizing the operator code. There may be a limited number of uses of the dongle code with different projectiles, and/or there may be a limited amount of time for using the dongle code. A companion electronic device may be used to authenticate the dongle.

A system and method for measurement and correction of aero-optical and aero-thermal effects to an EO/IR sensor's window/dome on a supersonic flight-vehicle. Range-gating of laser pulses measures and separates aerodynamic and atmospheric effects. Separate control algorithms and control loops at different update rates both simplifies the control algorithms and improves overall performance. The use of a MEMS MMA having tip/tilt/piston capabilities as the deformable mirror to provide wavefront correction enhances overall performance. The corrected laser pulses may also be used to actively illuminate a target to provide both active and passive detection.

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.

The present invention relates to a glide bomb and methods of use thereof for use with an unmanned or manned aerial vehicle or for operative deployment. In one form, the glide bomb is configured to be carried and released by an unmanned aerial vehicle (“UAV”) for flight towards a selected target. The glide bomb includes an elongate body having a nose and an opposed tail aligned along a longitudinal axis; a payload; a pair of wings extendable from opposed sides of the body for producing lift, said wings configured to be selectively moveable between a retracted position and an extended position; and two or more tail control surfaces operatively associated with the tail of the body for at least pitch and yaw control.