A Vehicle Based Independent Range System (VBIRS) (10) comprised of individual stacked chambered modules that function as a single integrated system that provides a self-contained space based range capability, and is comprised of a power module (12), an artificial intelligence/autonomous engagement/flight termination system module (20), a satellite data modem module system (30) and a navigation, communications and control module system (40), all of which interface with a VBIRS test and checkout system (52) and a weather data system (116). The artificial intelligence/autonomous engagement/flight termination system module (20) is comprised of an inherent artificial intelligence capability that envelopes and interchanges data with an autonomous engagement controller (22) that contains all missile/rocket autonomous cooperative engagement, destruct decision software and range safety algorithm parameters required for optimum mission planning. VBIRS employed aboard an aircraft or between any combination of launching systems allows that aircraft to launch a missile/rocket from any location on earth, whether the missile/rocket is singularly launched by itself or as a larger group of missiles/rockets launched in a salvo arrangement, while providing collaborative real-time targeting to occur directly between missiles/rockets in conjunction with other missile/rocket launch platforms or stand-alone mission control centers.

A method for aligning a missile with a target in a laser beam riding missile guidance system, the system including a laser transmitter for generating and projecting a laser information field towards the target and an optical sight for aiming the laser beam towards the target, the method comprising: determining a point in the laser information field with which the missile is currently aligned; determining a distance of the target from the missile; determining an angular displacement between the missile's current direction of travel and the direction in which the target lies from the missile; determining, based on said distance and angular displacement, a new point in the laser information field with which the missile should be aligned to reach the target; and controlling missile guidance systems on board the missile to bring the missile into alignment with the new point in the laser information field.

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 spherically constrained optical seeker assembly includes a spherical lens having an outer surface, an optical sensor assembly associated with the spherical lens, and a gimbal assembly. The optical sensor assembly is coupled to the gimbal assembly. The gimbal assembly is configured to move the optical sensor assembly to at least one desired position on the outer surface of the spherical lens. A method of manipulating the optical sensor assembly includes positioning the optical sensor assembly with respect to the spherical lens and moving the optical sensor assembly to at least one desired position with respect to the outer surface of the spherical lens by the gimbal assembly.

A method includes receiving a plurality of laser pulses as a pulse train on a plurality of imaging sensor pixels in an array of pixels. For each pixel in the array of pixels, the method includes receiving a respective one of the laser pulse trains, and scanning the pixels response across a range of frequencies with a bandpass filter to determine pulse shape characteristics of the respective one of the laser pulse trains. The method includes filtering out all of the laser pulse trains that do not fit a predetermined pulse shape characteristic for a true target designation pulse train, and physically adjusting trajectory of a physical resource toward a target based on location on the imaging sensor of one or more pixels receiving a laser pulse train that fits the predetermined pulse shape characteristic for the true target designation pulse train.

Apparatus and associated methods relate to a dual-mode seeker for a guided missile equipped with seeker/designation handoff capabilities. The dual-mode seeker has Semi-Active Laser (SAL) and Image InfraRed (IIR) modes of operation. SAL-mode operation includes detecting laser pulses reflected by a target designated by a remote Laser Target Designator (LTD) and determining target direction using the detected laser pulses. SAL-mode operation also includes determining the Pulse Repetition Interval (PRI) of the detected laser pulses, and predicting timing of future pulses generated by the LTD. IIR-mode operation includes capturing Short-Wavelength InfraRed (SWIR) images of a scene containing the designated target and determining target location using one or more image features associated with the designated target. After the target direction can be determined using the IIR-mode of operation, an illuminator projects a signal onto the designated target so as to communicate to a remote operator that LTD target designation can be suspended.

An adaptive navigation system for airborne, ground and dismount applications. The system performs adaptive fusion of all sensed signals, information sources, and databases that may be available on a single or multiple cooperative platforms to provide optimal Positioning, Navigation, and Timing (PNT) state. To reduce error building over time, the system incorporates the concept of geo-registration fusion into the ANAGDA filter. The architecture of the ANAGDA filter consists of user/application configurable functionalities in hierarchical layers. The sensing layer senses the environment and contains the required databases such as surveyed landmarks, and Digital Terrain Elevation Data/Digital Elevation Model (DTED/DEM). The processing layer has a Smart Sensor Resource Manager which is a performance-based sensor/feature selection module. The measurement abstraction layer isolates the filter from hardware specifics. The fusion layer performs the Inertial Measurement Unit (IMU) data integration with sensor measurements, and feature fusion.

A rescue system includes a wearable article, such as a wristband, which includes a radio frequency identification (RFID) tag, a radio frequency (RF) beacon, and a power supply. One or more RFID readers (collectively, an RF network) are located on a vessel, the RFID readers being configured to communicate with the RFID tag. Should the RF network detect a passenger overboard event, a modular rocket system is deployed. The modular rocket system comprises a guidance module, the guidance module including a guidance system for guiding the modular rocket system toward a target. A flight control module is removably attached to the guidance module, said flight control module including a plurality of airfoils. A flotation module is removably attached to the flight control module, said flotation module including a flotation device. A rocket motor module removably attached to the flotation module, said rocket motor module including a rocket motor configured to propel the modular rocket system.

A method of conducting a strike against a target using a designator and a missile. The following steps are conducted: (i) the designator designates the target using a first signal, such as a laser; (ii) the missile detects the laser reflected off the target; (iii) after detecting the reflected laser, the missile emits a second signal, such as a LADAR signal, to designate the target; (iv) the missile tracks the so-designated target; (v) the designator detects the LADAR signal reflected off the target; and (vi) in response to detecting the reflected LADAR signal, the designator stops the designation of the target. This may enable the designator to perform other tasks, while the missile tracks and engages the target.

The present invention relates to electro-optic guided missile systems and, in particular, it concerns systems and methods providing enhanced navigation capabilities based on ego-motion processing of seeker images. The missile system comprising: a missile; a seeker located at a nose portion of said missile, said seeker comprising an electro-optic imaging sensor; and a control arrangement for steering the missile along a flight path to a target, characterized in that the missile system further comprises: a navigation subsystem receiving images from said imaging sensor, said navigation subsystem being configured to: co-process a plurality of said images from said imaging sensor to derive ego-motion of said missile relative to a region viewed by said imaging sensor; derive from said ego-motion a calculated target direction from said missile to a target.