In one possible embodiment, a system capable of a self-propagating data link includes an unmanned vehicle having a data link transceiver and at least one deployable data link transceiver. The unmanned vehicle having a deployment means for deploying the at least one deployable data link transceiver.

Systems and methods for deploying smart munitions may provide targeting metadata generated by surveillance networks to munitions deployment and guidance systems for smart munitions. Targeting metadata may be received by a conduit system and automatically processed to generate guidance and deployment data actionable by a munitions deployment platform.

The fuse mode of a laser guided munition is remotely set and/or changed by encoding fuse mode information onto fuse mode designating light received by the light detector of the munition. Embodiments do not require hardware modification of existing munitions and/or control systems. The mode designating light can be the target designating laser light, and the fuse mode information can be encoded together with counter counter measure (CCM) information. Or the mode designating light source can be a separate laser or non-laser light source. Encoding of the fuse mode information can be by modulation and/or wavelength selection of the mode designating light. In embodiments, the fuse mode can be selected before and/or after launch of the munition.

The system and method of dynamic weapon to target assignment (DWTA) using a control based methodology to dynamically assign each projectile to a target in a multiple target engagement situation. In some cases, closest proximity is used in a real-time, to accomplish the DWTA functional requirement and performance criteria. In some cases, g pulling acceleration and projectile fin deflection motion are also used to assess the best matched pair for each projectile and each target with an end goal of intercepting the target or guiding the projectile to an acceptable error basket for target destruction via detonation. For the closest distance criterion for projectile/target pairing, a cutoff time is used to ensure the pairing is conducted within an acceptable duration while still being able to intercept the target or meet a required miss distance basket (e.g., <3 m).

The presently disclosed subject matter includes a computerized method and system for determining miss-distance between platforms. The proposed method and system make use of an electro optic sensor (e.g. camera) mounted on one of the platforms for obtaining additional data which is used for improving the accuracy of positioning data obtained from conventional positioning devices. A navigation error is calculated where the relative position of the two platforms is converted to the camera reference frame. Once the navigation error is available, it can be used to correct a measured miss-distance.

A hypersonic self-guided missile system is described. Particularly, embodiments describe missiles whose trajectories are controlled by an on-board control unit that decrease the effect of damaging heat to sensitive internal components by employing one or more annular windows, internal mirrors, lenses, and/or cameras. Embodiments may have an internal camera oriented substantially toward or away from the nose of the missile.

The system and method of dynamic weapon to target assignment (DWTA) using a control based methodology to dynamically assign each projectile to a target in a multiple target engagement situation. In some cases, closest proximity is used in a real-time, to accomplish the DWTA functional requirement and performance criteria. In some cases, g pulling acceleration and projectile fin deflection motion are also used to assess the best matched pair for each projectile and each target with an end goal of intercepting the target or guiding the projectile to an acceptable error basket for target destruction via detonation. For the closest distance criterion for projectile/target pairing, a cutoff time is used to ensure the pairing is conducted within an acceptable duration while still being able to intercept the target or meet a required miss distance basket (e.g., <3 m).

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 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.