A system for monitoring a user of a firearm generally includes an inertial measurement unit configured to be disposed inside a grip of the firearm for measuring motion of the firearm. The system also includes an event detection system for detecting a detected event that includes at least one of gripping of the firearm, raising of the firearm, aiming of the firearm, and discharging of the firearm based on the motion of the firearm measured by the inertial measurement unit. The system further includes a communication system for wirelessly communicating the detected event.

In a display apparatus of an interception area, a first detection device scans a first area containing at least a part of a firing range of a first weapon to detect an obstacle. A first terminal calculates the first interception area in which the first weapon is possible to intercept, based on data of the detected obstacle and data of the first weapon; calculates a first display area showing the first interception area on a screen based on the first interception area; receives second area data generated by a second terminal, and calculates a second display area based on the second area data. The second display area shows on the screen an area in which a second weapon is possible to intercept. The first terminal displays the first display area and the second display area.

An area denial system may be operationally placed with communication latency compensation. The area denial system may include a plurality of munitions, one or more sensor devices, and a command and control unit, networked together and having a command and control latency for communication between the command and control unit and the remainder of the area denial system. Latency compensation may include determining a first target position, determining a first predicted position area for the target using the command and control latency and the first target position, receiving an authorization to arm one or more of the munitions, determining a second target position, and determining that the second target position is outside a threshold distance from a first authorized munition of the one or more authorized munitions, and in response, de-authorizing the first authorized munition.

An area denial system may be operationally placed with communication latency compensation. The area denial system may include a plurality of munitions, one or more sensor devices, and a command and control unit, networked together and having a command and control latency for communication between the command and control unit and the remainder of the area denial system. Latency compensation may include determining a first target position, determining a first predicted position area for the target using the command and control latency and the first target position, receiving an authorization to arm one or more of the munitions, determining a second target position, and determining that the second target position is outside a threshold distance from a first authorized munition of the one or more authorized munitions, and in response, de-authorizing the first authorized munition.

An aircraft control device calculates trajectories of multiple aircraft that is member of a flight by use of a method such as Direct Collocation with Nonlinear Programming (DCNLP), in which an optimal solution is obtained by discretizing continuous variables. Nodes indicating the trajectory are calculated and set by substituting a discretized control variable of the aircraft into an aircraft equation of motion, or by use of other methods. Instead of calculating the trajectory of the aircraft as a continuous problem, discretisation reduces the calculation amount and time required for the trajectory calculation. The aircraft control device then determines, from among trajectories satisfying constraints corresponding to the role of the aircraft, an optimal trajectory based on an evaluation value obtained by an objective function corresponding to the role. Accordingly, the aircraft control device can calculate a more optimal trajectory corresponding to the role of the aircraft in a shorter time.

A firearm monitoring and remote support system monitors firearms and other assets within a deployment location to detect threats to users of the firearms and to perform actions in response to the threats. Measurements recorded using sensors of the firearms and/or of the other assets are used to determine changes in motion, position, orientation, and/or operation of the firearms and/or of the other assets. The measurements are processed to determine the nature of a threat and the particular actions to perform in response thereto. Graphical user interfaces visualizing the users within the deployment location are updated using the measurements to show, in real-time, positions and orientations of cones of fire for the users within the deployment location. In some cases, the cones of fire may be used to detect threats within the deployment location. In some cases, the actions to perform in response to a detected threat may be automated.

Techniques are provided for determination of a guided-munition orientation during flight based on lateral acceleration, velocity, and turn rate of the guided-munition. A methodology implementing the techniques, according to an embodiment, includes obtaining a lateral acceleration vector measurement and a velocity of the guided-munition, and calculating a ratio of the two, to generate an estimated lateral turn vector of the guided-munition. The method also includes integrating the estimated lateral turn vector, over a period of time associated with flight of the guided-munition, to generate a first type of predicted attitude change. The method further includes obtaining and integrating a lateral turn rate vector measurement of the guided-munition, over the period of time associated with flight of the guided-munition, to generate a second type of predicted attitude change. The method further includes calculating a gravity direction vector based on a difference between the first and second types of predicted attitude change.

Techniques are provided for determination of a guided-munition orientation during flight based on lateral acceleration, velocity, and turn rate of the guided-munition. A methodology implementing the techniques, according to an embodiment, includes obtaining a lateral acceleration vector measurement and a velocity of the guided-munition, and calculating a ratio of the two, to generate an estimated lateral turn vector of the guided-munition. The method also includes integrating the estimated lateral turn vector, over a period of time associated with flight of the guided-munition, to generate a first type of predicted attitude change. The method further includes obtaining and integrating a lateral turn rate vector measurement of the guided-munition, over the period of time associated with flight of the guided-munition, to generate a second type of predicted attitude change. The method further includes calculating a gravity direction vector based on a difference between the first and second types of predicted attitude change.

An aerial vehicle is described that is capable of interacting within a TES environment, and capable of acting as a Ground Based Air Defense (GBAD) platform to represent virtually any type of aircraft in the simulation. The aerial vehicle may include sensors for determining its own location and/or orientation, and may further carry a payload of components that can be assembled modularly to equipped the aerial vehicle with different types of functionality. Such functionality can include enabling the aerial vehicle to gather information regarding its surroundings, engage with other military entities within the TES environment, and/or enable other military entities within the TES environment to engage with it.

Systems are disclosed for navigating a missile to a target using a fixed sensor onboard the missile. In an embodiment, a system includes a launch platform traveling a pre-programmed route to deliver the missile within an area. The missile travels a first flight path through the area in effort to detect targets. If no targets are detected along the first flight path, the missile transitions to a second flight path, different from the first flight path, to locate targets off-axis relative to the first flight path. While the missile travels the second flight path, the sensor receives signal identifying a target located at a position off-axis relative to the first flight path. The missile then adjusts the second flight path to direct the missile to the target. In an example embodiment, the first flight path is straight or arced, while the second flight path is u-shaped, corkscrew-shaped, or spiral-shaped.