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.

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.

The subject disclosure relates to a simulation system having an aircraft, a local wireless transceiver, and a simulation computer. The aircraft may include an onboard wireless transceiver and a flight controller operatively coupled with an onboard sensor payload to perceive a physical environment and to generate position and pose data. The simulation computer may be configured to communicate wirelessly with the aircraft via the local wireless transceiver. In operation, the simulation computer may be configured to generate one or more virtual reality sensor inputs and to receive the position and pose data from the aircraft. The simulation computer can be configured to transmit the one or more virtual reality sensor inputs to the flight controller of the aircraft.

The presently disclosed subject matter includes an active protection system and a method, dedicated for detecting, locating, and incapacitating beam-riding missiles and in that way protecting an asset from being targeted by the missile. According to some examples following receipt of a threat-indication, the active protection system estimates a location of a beam used for directing a threat (e.g., ATGM) to the target and launches an aerial platform that flies in the opposite direction along the beam until it meets and incapacitates the incoming threat.

A system includes a high energy laser (HEL) configured to transmit a HEL beam and a beacon illumination laser (BIL) configured to transmit a BIL beam. The system also includes at least one fast steering mirror (FSM) configured to steer the BIL beam to be offset from the HEL beam. The system further includes at least one Coud? path FSM configured to correct for atmospheric jitter of the HEL beam and the BIL beam while maintaining the offset of the BIL beam from the HEL beam.

A laser source (340) that generates an output beam (354) that is directed along a beam axis (354A) that is coaxial with a first axis and orthogonal to a second axis comprises a first frame (356), a laser (358), and a first mounting assembly (360). The laser (358) generates the output beam (354) that is directed along the beam axis (354A). The first mounting assembly (360) couples the laser (358) to the first frame (356). The first mounting assembly (360) allows the laser (358) to expand and contract relative to the first frame (356) along the first axis and along the second axis, while maintaining alignment of the output beam (354) so the beam axis (354A) is substantially coaxial with the first axis. The first mounting assembly (360) can include a first fastener assembly (366) that couples the laser (358) to the first frame (356), and a first alignment assembly (368) that maintains alignment of the laser (358) along a first alignment axis (370) that is substantially parallel to the first axis.

Systems, devices, and methods for identifying a target aerial vehicle, deploying an interceptor aerial vehicle comprising at least one effector, maneuvering the interceptor aerial vehicle to a position to engage a target aerial vehicle, deploying the at least one effector to intercept the target aerial vehicle, and confirming that the target aerial vehicle has been intercepted.

An apparatus for combining electro-optical infrared threat warning, and proactive and reactive countermeasures includes a laser which generates a laser beam. A tracking module is included in the apparatus which scans a field of regard with the laser beam and collects threat signals generated from objects of interest. A passive warning module observes the threat signals in the field of regard and generates passive warning operational signals. A proactive module also observes the threat signals in the field of regard with the laser beam and generates proactive operational signals. A reactive module directs the laser beam at the objects of interest in said field of regard, and generates reactive operational signals. The modules exchange the operational signals therebetween and with the laser and the tracking module to at least monitor the objects of interest.

A system for inhibiting the electronic system of a target object is provided. The system comprises an Electronic Counter Measure (ECM) unit, and a projectile for carrying the ECM unit towards the target object.

A method and device for determining the distance between an airborne receiver and a stationary ground transmitter are disclosed. A digital terrain model is implemented to determine a range of distance values containing the transmitter. A receiver distance is found and, with the range of values, a plurality of theoretical distances is calculated, to each of which a corresponding azimuth angle and elevation angle are associated. The thus calculated azimuth and elevation angles are compared to the measured azimuth and elevation angles of the line of sight under which the receiver observes the transmitter.