A mission planning method for use with a weapon is disclosed. The method comprises: obtaining a first training data set describing the performance of the weapon; using the first training data set and a Gaussian Process (GP) or Neural Network to obtain a first surrogate model giving a functional approximation of the performance of the weapon; and providing the first surrogate model to a weapons system for use in calculating a performance characteristic of the weapon during combat operations.

A Launch Acceptability Region [LAR] display system and method for a payload-releasing platform, the system being configured to be communicably coupled to a LAR computing module (104) configured to compute LAR data representative of a Launch Acceptability Region in respect of said platform based on a set of input parameters and predefined payload performance parameters, the system comprising: an input module (100) configured to obtain or receive a first input parameter value in respect of a first of said input parameters, generate a set of second input parameter values in respect of said first of said input parameters, said second input parameter values being different to and at respective intervals from, said first input parameter value, and input said first input parameter value and said second input parameter values to said LAR computing module so as to cause said LAR computing module to compute, based on each of said first and second input parameter values, a respective LAR and output a set of LAR data, each data item of said set of LAR data being representative of a respective LAR and the input parameter value on which it is based; an image data generation module (106) configured to receive said set of LAR data and generate therefrom a set of LAR image data, each data item of said set of LAR image data being representative of a respective data item of said set of LAR data; anda display module (108) configured to receive said set of LAR image data and display, simultaneously, a visual representation of each LAR, wherein the relative positions in said display of said visual representations is based on their respective associated input parameter value.

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 winged external guidance frame placed on the muzzle that can couple with a projectile while exiting the barrel utilizing the kinetic energy of the projectile to travel to the target while the accuracy is provided by on board electronics and corrected using the wings. Alternately a reusable unmanned aerial system that travels in the speed and direction of the projectile and couples with the projectile as it exits the barrel.

A method and apparatus for generating, in an aircraft in flight, a feasibility display indicative of the feasibility of a weapon, the method comprising: providing a performance envelope for the weapon; determining, using the performance envelope, configuration data for configuring a generic algorithm; uploading the configuration data to the aircraft; generating feasibility data indicative of the feasibility of a weapon carried on the aircraft successfully engaging a target and/or the feasibility of a weapon carried on the target successfully engaging the aircraft; determining, on board the aircraft, using the same generic algorithm and the uploaded configuration data, one or more test criteria; performing, on board the aircraft, an assessment process including determining whether or not the feasibility data satisfies the one or more test criteria; and, based the assessment, using the feasibility data, generating the feasibility display.

An unmanned flying grenade launcher system is provided. The unmanned flying grenade launcher can include a portable unmanned aerial vehicle with an attachment apparatus configured to receive a standardized grenade launcher, and a servo coupled to adjust the angle of the grenade launcher relative to the portable unmanned aerial vehicle downward relative to the unmanned aerial vehicle. One or more telemetry systems can provide a visual indication of the unmanned aerial vehicle's surroundings to an operator, and can receive flight commands and firing commands from the operator such that a firing mechanism fires the standardized grenade launcher in response to the firing command.

A system comprising an unmanned aerial vehicle (UAV) configured to transition from a terminal homing mode to a target search mode, responsive to an uplink signal and/or an autonomous determination of scene change.

An unmanned aerial system (UAS) includes a body and a lift and propulsion system coupled to the body. The UAS includes a weapon coupled to the body. The weapon has an aiming axis oriented in a fixed direction relative to the body. The UAS includes a control system operatively coupled to the lift and propulsion system and the weapon. The control system is configured to determine a roll angle and a flight path such that the aiming axis is directed at a target when the UAS moves according to at least a portion of the flight path at the roll angle. The control system is further configured to control the lift and propulsion system such that the UAS moves according to the at least the portion of the flight path at the roll angle.

A terrain-referenced navigation system for an aircraft comprises: a stored digital terrain map; a position calculation unit arranged to calculate aircraft position relative to the stored digital terrain map to determine a terrain-referenced aircraft position; a fall line calculation unit arranged to calculate a fall line for a projectile starting from the terrain-referenced aircraft position as a launch point; and an impact point calculation unit arranged to directly compare the fall line with the digital terrain map, by incrementally comparing a height of the projectile along the fall line with a height of the terrain according to the stored digital terrain map in order to find an expected impact point on the terrain.

A system for mitigating a threat in a facility according to the present disclosure includes a threat identification module and at least one group of drones. The threat identification module is configured to generate a threat identification signal indicating that the threat has been identified in the facility and transmit the threat identification signal to a central command center. The at least one group of drones is configured to move toward the threat in response to at least one of the threat identification signal and a command from the central command center.