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 guidance system for deployment on-board a projectile includes a laser-seeking detector, an imaging device, and a control module. The laser-seeking detector is designed to detect the position of the projectile with reference to a laser spot on a target. The imaging device is designed to capture one or more images in front of the projectile. The control module is designed to control a flight direction of the projectile based on input received from the laser-seeking detector in a first mode, control the flight direction of the projectile based on input received from the imaging device in a second mode, and switch between the first mode and the second mode while the projectile is in flight towards the target. Both guidance technologies are leveraged to develop an improved guidance technique that provides highly accurate targeting and allows for a faster rate of fire to deal with multiple targets.

An MKV interceptor includes a carrier vehicle (CV) that supports the deployment of M kill vehicles (KVs) and provides centralized acquisition and discrimination pre-ejection. Pre-ejection each KV acquires and transmits IR imagery, and possibly visible imagery, via an internal communication bus to a central processor on the CV. The central processor spatially registers the IR images from the different KVs, either directly from the IR images themselves or using the visible imagery, and sums the IR (and visible) images to form a registered spatially averaged IR image. This image has the same resolution but higher SNR than any one of the KV IR images. The central processor uses this registered spatially averaged image during pre-ejection acquisition and discrimination modes. The key benefit is the elimination of independent CV sense capability, which is large, heavy and expensive, and was required by either the command guided or sharing concepts.

A launched flying object continues to transmit a signal to a launching device. The launching device continues to receive the signal from the flying object, continues to calculate a probability when the flying object intercepts a target from the distance, the relative velocity and the relative angle between the flying object and the target and the flying object, and outputs a final interception probability when the communication from the flying object is stopped.

An ultra-wide band (UWB) radio frequency (RF)/optical aperture includes a substrate having a plurality of regions. The plurality of regions may have varying characteristics and properties. In some embodiments, the plurality of regions includes a first region having a first relative dielectric constant and being transparent to signals having a frequency in a first frequency range, a second region contained in the first region and having a second relative dielectric constant and being transparent to signals having a frequency in a second frequency range, and a third region contained within the second region and having a third relative dielectric constant and being transparent to signals having a frequency in a third frequency range.

A seeker includes a detection array having at least 2500 sensing pixels arranged in rows by row request lines and in columns by column request lines. At least one pixel includes an electromagnetic radiation sensor to trigger the pixel in response to sensing a triggering quantity of electromagnetic radiation, a row request circuit to send a row request after the pixel triggers, and a column request circuit to send a column request after the pixel triggers. The seeker further includes a row receiver to receive the row requests, a column receiver to receive the column requests, and a sequencer to receive, for each triggering pixel, the row of the row request and the column of the column request, and to generate an event including the received row and column of the pixel. The seeker also includes a time stamper to generate a time stamp for the generated event.

A dual mode RF/IR seeker suitable for use in an anti-radiation missile is disclosed. The infrared sensor is responsive to radiation within the 4.0 to 4.8 micron band and the radio frequency sensor is responsive to radio frequency signals within a 6.5 to 16.5 GHz band. The infrared sensor comprises a folded Cassegrainian telescope arrangement, including a primary mirror which is transparent to radio frequency energy. The radio frequency sensor comprises an annular array of orthogonally disposed stripline flared notch radiating elements. A broadband microwave receiver, fabricated in a multilayered stripline package, is provided for forming radio frequency monopulse sum (E) and difference (A) signals and for converting such radio frequency monopulse signals to suitable intermediate frequency signals for processing in an I.F. receiver.

A method and system for constraining navigational drift in a munition caused by Inertial Measurement Unit (IMU) bias error during flight of the munition in a constellation of a plurality of munitions in a Global Positioning System (GPS) denied attack. Each munition is provided with a datalink communication system to communicate with other munitions in the constellation and a navigation system having an IMU for guiding the munition in flight. An estimated position and covariance of the estimated position is determined for each munition via each munitions' navigation system. A range of each munition relative to at least one other munition in the munition constellation is determined via each munitions' datalink communication system. The estimated position and range to at least one other munition in the munition constellation is shared by each munition via each munitions' datalink communication system. Navigational drift for each munition is determined utilizing the estimated position of at least one other munition and the range to that at least one other munition in the munition constellation. And navigational drift in each munition is constrained by compensating for IMU bias error in each munition utilizing the determined navigational drift for each respective munition in the munition constellation.

A closed, self-contained ballistic apogee detection module for use in a projectile, such as a rocket, mortar round, or artillery round, fuses data from multiple built-in sensors, such as an accelerometer, a magnetometer, and a gyroscope, and processes the data using a microprocessor through a custom quaternion extended Kalman filter to provide accurate state and orientation information about the projectile so as to accurately predict apogee. The module outputs a signal indicating apogee detection or prediction which they projectile uses to initiate fuze arming, targeting control, airbody transformation, maneuvering, flow effector deployment or activation, payload exposure or deployment, and/or other mission activity. Because the system and method of the invention does not rely on external environmental data to detect apogee, it need not use a pressure sensor and can be completely sealed in and closed without requiring access to air from outside the projectile for barometric readings.

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.