An approach to seeker windows for aircraft comprises a window layer comprising an IR transparent material, the window layer comprising a first side and a second side substantially opposite the first side; and a heating layer on the first side or the second side of the window layer, the heating layer configured to apply a heating profile to the window layer to reduce thermal shock imparted to the window layer when the seeker window is exposed to hypersonic flight conditions.

A method for collaboration of a plurality of nodes includes determining at each node SLAM data for the node, the SLAM data including estimated position of features and/or targets observed and processed by the node using SLAM algorithms and covariance associated with the estimated positions, communicating at each node the node's SLAM data to the other nodes via each nodes' datalink communication system, receiving at each node SLAM data communicated from the other nodes via each node's datalink communication system, combining at each node the node's SLAM data and the SLAM data received from the other nodes based on features or targets included in SLAM data from the other nodes, refining at each node estimated positions of features and/or targets based on results of the combining, and navigating each node to a target at the target destination as a function of at least one of the refined estimated positions.

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 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 system and method to aid in guidance, navigation and control of a guided projectile including a precision guidance munition assembly is provided. The system and method obtain raw position data during flight of the guided projectile, the raw position data including a plurality of position data points from the guiding sensor for determining positions of the guided projectile, establish a window including a portion of the plurality of position data points, smooth the portion of the plurality of position data points in the window, and determine a reduced noise position estimate of the guided projectile, based, at least in part, on the smoothed portion of the plurality of position data points in the window. The system and method may determine a velocity estimate of the guided projectile and predict an impact point of the guided projectile relative to a target.

A method is provided to improve the impact point for at least one subsequent projectile fired towards a target, launched after an initial projectile, where the subsequent projectiles can alter their course, based on information on the previous projectiles' time of automatic detonation, to improve the ability to detect a target. A projectile and a fuse are also provided.

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.

Methods involve using a guided munition (e.g., a mortar round or a grenade) that utilizes deployable flow effectors, activatable flow effectors and/or active flow control devices to extend the range and enhance the precision of traditional unguided munitions without increasing the charge needed for launch. Sensors such as accelerometers, magnetometers, IR sensors, rate gyros, and motor controller sensors feed signals into a controller which then actuates or deploys the flow effectors/flow control devices to achieve the enhanced characteristics.

In certain embodiments, an imaging system includes an enclosure with an objective aperture opening into an interior space of the enclosure, an optical assembly optically coupling the objective aperture to an imaging sensor within the enclosure, a shutter mounted to the objective aperture for selectively blocking and admitting illumination through the objective aperture into the interior space, and an illuminator mounted to illuminate the interior space of the enclosure.

An optics system includes a convex catching mirror located within respect to the concave primary mirror to form an optical path for a field of view. A conical volume is formed with respect to the concave primary mirror and the convex catching mirror, the optical path not obstructed by the conical volume. A component within the conical volume.