Embodiments include engagement management systems and methods for managing engagement with aerial threats. Such systems include radar modules and detect aerial threats within a threat range of a base location. The systems also track intercept vehicles and control flight paths and detonation capabilities of the intercept vehicles. The systems are capable of communication between multiple engagement management systems and coordinated control of multiple intercept vehicles.

A system for providing integrated detection and deterrence against an unmanned vehicle including but not limited to aerial technology unmanned systems using a detection element, a tracking element, an identification element and an interdiction or deterrent element. Elements contain sensors that observe real time quantifiable data regarding the object of interest to create an assessment of risk or threat to a protected area of interest. This assessment may be based e.g., on data mining of internal and external data sources. The deterrent element selects from a variable menu of possible deterrent actions. Though designed for autonomous action, a Human in the Loop may override the automated system solutions.

A method steers a missile towards a flying target. In order to permit precise flight to the target even under poor visibility conditions owing to the weather, a radar which is remote from the missile detects the target and transmits data relating to a first location area of the target to the missile. The missile determines, from the data of its own missile radar, a second location area of the target, processes both location areas to form a target area and flies to the target area.

A method for launching a round from an airborne platform, receiving a plurality of RF signals at the round, determining an amount of time between a first and second received RF signal, where the second signal is a multi-path signal and the first signal is a direct path signal. An altitude of the round is determined based on the delay between the first and second received signal and aligning the round's flight path with an initial velocity vector of the aircraft platform to reduce dispersion. The round can include a plurality of sensors for detecting the RF signals. The second received RF signal may be a multi-path signal having been reflected off of the earth's surface or another object on the earth's surface. The altitude of the round can be determined using the known altitude of the airborne platform, the delay of time between the first and second received signals, and the speed of light.

A narrow band antenna is configured to guide a munition toward a target location during a flight of the munition from a launch location toward the target location. The antenna has a first mode of operation operable during a first portion of the flight at a first bandwidth, and a second mode of operation operable during a second portion of the flight at a second bandwidth, the second bandwidth being a harmonic of the first bandwidth, and may be a third harmonic of the first bandwidth. The method includes transmitting a target location information to the munition in the first bandwidth during the first portion of the flight and then transmitting the target location information to the munition in the second bandwidth during the second portion of the flight. The first band may be X-band and the second band may be Ka-band.

A spatially-distributed architecture (SDA) of antennas transmits respective uniquely coded signals. A first receiver having a known position in a coordinate system defined by the SDA receives reflected versions of the uniquely coded signals. A first processor receives the reflected versions of the uniquely coded signals and identifies a position of a non-cooperative object in the coordinate system. A platform with a platform receiver receives non-reflected versions of the uniquely coded signals. The platform determines a position of the platform in the coordinate system. In an example, the platform uses a self-determined position and a position of the non-cooperative object communicated from the SDA to navigate or guide the platform relative to the non-cooperative object. In another example, the platform uses a self-determined position and information from an alternative signal source in a second coordinate system to guide the platform. Guidance solutions may be generated in either coordinate system.

A precision guided munition (PGM) system is disclosed. The PGM system comprises a body including a nose portion. The nose portion includes an aperture. A window is attached, secured, or adhered to the body at the nose portion. One or more antenna substrates is attached, secured, or adhered to the window. A plurality of radiating elements is attached, secured, or adhered to the one or more antenna substrates. An image sensor configured to capture an image in front of the body. The image sensor is behind the aperture and is configured to focus at an infinity focus in front of the body. The one or more antenna substrates include unpopulated areas configured to let photons pass through the antenna substrates from the window to the image sensor. The photons are parallel or collimated and the captured image does not include features of the antenna substrates.

A command control system includes an interception predicting section and an assigning section. The interception predicting section calculates a predicted intercept point of a target to be shot down and a guided missile to shoot down the target. The assigning section acquires first weather data of the predicted intercept point, and generates a launching instruction based on the first weather data so as to launch one of a first guided missile and a second guided missile as the guided missile. A method by which the first guided missile detects the target and a method by which the second guided missile detects the target are different.

The disclosure discloses a channel combining and time-division processing circuit of a dual-plane pulse Doppler radar seeker. The circuit includes a time-division control circuit configured to receive a time-division control signal, control input of an elevation difference channel signal and an azimuth difference channel signal, combine the elevation difference channel signal and the azimuth difference channel signal and output a combined difference channel signal, and a hybrid bridge circuit configured to receive a sum channel signal, combine channels for the sum channel signal and the combined difference channel signal and output signals on a combined channel. With the circuit of the disclosure, signals received from a sum channel, an azimuth difference channel and an elevation difference channel can be combined into received signals from two channels for processing with one received signal processing channel hardware omitted.

Embodiments include engagement management systems and methods for managing engagement with aerial threats. Such systems include radar modules and detect aerial threats within a threat range of a base location. The systems also track intercept vehicles and control flight paths and detonation capabilities of the intercept vehicles. The systems are capable of communication between multiple engagement management systems and coordinated control of multiple intercept vehicles.