A device may acquire an image of a target area located within the mission environment. A device may provide a first set of firing conditions to the munition, the first set of firing conditions corresponding at least to the target area. A device may provide authorization to the at least one mobile munition assembly for firing based at least on an airspace collision avoidance status dynamically determinable over a maximum future time of launch consideration (tmax). A device may be based on a provided authorization, firing the munition from the launcher according to the initial parameter set. A device may at the fired munition: measuring a second set of firing conditions, confirming an intended firing status of the munition by comparing the second set of firing conditions to the first set of firing conditions; and guiding the munition to the target area.

A system and method for enhanced aircraft-based targeting senses RF emissions or other signals associated with a target while navigating a trajectory through a GPS-challenged airspace. While the target is being observed, the aircraft targeting system tracks GPS-challenged state vectors (e.g., via an onboard inertial reference system) and pressure altitudes consistent with each observation. When the aircraft emerges from the GPS-challenged airspace, the targeting system determines multiple GPS-driven subsequent absolute positions of the aircraft. The targeting system determines a refined estimate of the target location via batch factor graph optimization of measurements taken while inside and outside of the GPS-challenged airspace.

Disclosed is a Global Positioning System (GPS) independent navigation system (GINS) for a self-guided aerial vehicle (SAV). The SAV has a housing, where the housing has an outer surface, a length, a front-end, and a longitudinal axis along the length of the housing. The GINS includes a first optical sensor, a second optical sensor, a storage unit, and a comparator.

A method for planning and launching two or more missiles, to be included in the same mission, and where this is done from one or more aircraft in such a way that the missiles arrive at same target approximately at the same time without interfering with each other on the way to the target. The planning of the mission is performed by sending a set of identical mission data to the missiles prior to launch; letting each missile be assigned a unique identity, letting each missile calculate identical trajectories and a unique offset to this, in one or more of four dimensions, where a resulting offset trajectory is unique for each missile and based on the identical mission data and unique identity, and launching the missiles included in the same mission.

Disclosed is A Global Positioning System (GPS) independent navigation system (GINS) for a self-guided aerial vehicle (SAV). The SAV has a housing, where the housing has an outer surface, a length, a front-end, and a longitudinal axis along the length of the housing. The GINS may include a first optical sensor, second optical sensor, storage unit, and comparator.

A method for ascertaining position information for an effector after launching from a launcher of a weapons system including the effector and at least one weapons system unit different from the effector, includes receiving a time synchronization signal at the effector in such a way that the effector and the at least one weapons system unit are temporally synchronized at the latest when the effector is launched. The effector furthermore receives position data of the at least one weapons system unit and a timestamp with unique assignment to the position data through a wireless communication connection after the effector has been launched. Position information is ascertained based on the timestamp, the effector's own time upon receipt of the timestamp, and the position data assigned uniquely to the timestamp. An effector, a computing unit and a weapons system are also provided.