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

A threat degree of each of targets is numerized based on data obtained by observing the targets after launching of the flying objects. Also, the firepower of flying object is numerized based on the state of flying object after the launching. The optimal assignment of firepower is calculated based on the numerized threat degrees and firepower, and is shared by the flying objects. Each flying object intercepts the target specified based on the optimal assignment.

A method for facilitating real time tracking of an airborne asset via downlink of GPS signals that are usable for determining asset location information from the asset to a ground station may include receiving a first GPS signal and a second GPS signal at a device disposed on the airborne asset and combining the first and second GPS signals to form combined signal responsive to filtration and amplification of the first and second GPS signals. The method may further include employing an overlay analog translation to convert the combined signal into a composite signal at a different frequency than the combined signal, generating a pilot carrier frequency for association with the composite signal, and amplifying the composite signal prior to transmission via the downlink from the airborne asset to the ground station. The pilot carrier frequency and amplitude may be adjustable.

A system for finding up in a projectile flight relative to earth. The system having a transmitter which transmits polarized reference signals to a guidance sub-system on the projectile. The guidance sub-system includes a magnetometer and polarized and non-polarized receivers. Measurements from the magnetometer are used to determine a general up direction. The polarized and non-polarized receivers are arranged such that, during rotation of the projectile, reference signals received by the polarized receiver modulate whereas reference signals received by the non-polarized receivers are unaffected. A ratio of the strengths of the signals received by the polarized and non-polarized receivers determines alignment of a vertical axis. From the general up direction and alignment of the vertical axis, a precise up direction of the projectile in flight relative to the earth can be determined.

The system and method for accurately determining range-to-go for a time-delayed command detonation of a projectile. Using dual laser and/or radio frequency detectors on the tail and on the nose of a spinning projectile to determine the range-to-go, time-to-go, and/or lateral offset from the projectile to the target. A time to detonation clock is used to determine when a projectile transitions from an exterior to an interior of a structure such that the projectile can more accurately detonate within a fixed structure.

A navigation system for a swarm of guided projectiles, such as cruise missiles, having three or more projectiles launched at a target is provided. The projectiles can be in secure communication with one another and can operate as a single swarm using a fusion of angle of arrival and time difference of arrival of a detected signal to direct the projectiles to a point of impact on a target that is offset from an emitter generating the detected signal. The projectiles can further use knowledge of their relative position to maintain and/or adjust their flight path and/or speed to maintain their course to the point of impact in areas of GPS denial or unavailability.

A navigation system for a swarm of guided projectiles, such as cruise missiles, having three or more projectiles launched at a target is provided. The projectiles can be in secure communication with one another and can operate as a single swarm using a fusion of angle of arrival and time difference of arrival of a detected signal to direct the projectiles to a point of impact on a target that is offset from an emitter generating the detected signal. The projectiles can further use knowledge of their relative position to maintain and/or adjust their flight path and/or speed to maintain their course to the point of impact in areas of GPS denial or unavailability.

A projectile is disclosed, having: a longitudinal axis, a steering assembly, a shell body, an attitude control system, a despin module, an electromagnetic receiver and/or emitter system, and a controller. The attitude control system includes a ram air inlet in selective open fluid communication with an exhaust assembly, which includes a plurality of exhaust outlets to selectively generate each of a plurality of thrust jets from a ram air inflow provided by the ram air inlet, each thrust jet being selectively controllable via the controller. The despin module is configured for selectively de-spinning the steering assembly with respect to the shell body about the longitudinal axis. The electromagnetic receiver and/or emitter system is configured for receiving and/or emitting electromagnetic energy, and for cooperating with the controller for operating the exhaust assembly to thereby selectively provide steering control moments. Systems and methods for steering the projectile are also disclosed.

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 target assignment system includes a sensor system which detects a position of a moving vehicle, an assigning section which determines the launcher system assigned with the moving vehicle in response to the position of the moving vehicle and generates a first display signal which shows the moving vehicle and a first launcher system, a display section which displays the moving vehicle and the assigned launcher system in real time in response to the display signal, and an input section which instructs a change of the assigned launcher system. The assigning section generates a second display signal in which the first launcher system is changed to a second launcher system, in response to an instruction of assignment change.