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

A multiple target tracking, data association, and track file management system (MTT, DA, and TFM) specifically developed for a ground based EO/IR camera proposed in this present disclosure is intended for three main purposes: (1) providing a ground-based combat vehicle with multiple mission capability by adding a new low cost EO/IR sensor with MTT, DA, and TFM functionalities built-in to interact with the ground-based fire control and command guidance for both surface-to-surface and surface-to-air defense missions; (2) serving as a plug-and-play integrated sensor with built-in MTT functionalities easily adaptable to be used for other missions; (3) part of the weapon GN&C subsystem to function in a smart fashion allowing projectiles to work in a collaborative engagement fashion.

A flying vehicle is disclosed with a projectile module or component that contains a projectile for projecting at another flying device. The flying vehicle receives an identification of a target flying device and applies a projectile model which generates a determination that indicates whether a projectile, if fired from the projectile component, the projectile will hit the target flying device. The projectile model taking into account one or more of a wind modeling in an area around the flying vehicle based on an inference of wind due to a tilt of the flying vehicle, a projected path of the target device based on its identification and a drag on the projectile as it deploys from the projectile component. When the determination indicates that the projectile will hit the targeted device according to a threshold value, the flying vehicle fires the projectile at the targeted flying device.

A launch control system relates to a method and apparatus for launch control packet processing that is provided in the launch control system and configured to allow interworking between a plurality of firing control systems and the launch control system. The launch control system comprises a plurality of operation equipments, a system control device, and control the plurality of operation equipments, a launch control packet processing unit, a control signal distribution device, and a status display device.

A munitions rack includes a munitions rack structure that houses multiple compact ejectors. The structure includes a pair of internal longitudinal ribs, inboard of a pair of external longitudinal ribs. A spine of the munitions rack structure links all the ribs, and the munitions rack structure may be formed out of a single piece of material. The ribs define a pair of side recesses on the port and starboard sides of the bomb, which each may be further subdivided into a forward pocket and an aft pocket. Removable ejectors are located in the pockets. The ejectors may receive pressurized gas from pressurized gas source(s) located outside of the ejectors. The ejectors may each have multiple forward pistons and multiple aft pistons. The ejectors may include pitch control valving to control the relative amounts of pressurized gas sent to the forward piston(s) and aft piston(s).

The invention provides an aiming system comprising a display control unit connected to a screen having a surface that is covered at least in part by a touch interface, the display control unit being arranged to inlay an aiming frame in the images displayed on the screen. According to the invention, the display control unit is arranged to: inlay a control zone in a portion of the touch interface; and to move the aiming frame on the screen as a function of a contact exerted on the touch interface in the control zone. The invention also provides an aiming method implemented with such a system.

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.

A torpedo apparatus comprises a propulsion module operable to propel the torpedo apparatus through water and a steering module operatively coupled to the propulsion module. The steering module including a plurality of fins which are controllable for controlling a direction of travel of the torpedo apparatus through water. A plurality of head modules are removably and interchangeably attachable to the torpedo apparatus, wherein each of the head modules houses at least one guidance assembly and at least one utility assembly. A power supply module is configured to provide power to the propulsion module, the steering module, and an attached one of the head modules.

Automated systems and methods for collecting environmental data along a ballistic trajectory are disclosed. The systems and methods may comprise automatically estimating the ballistic trajectory of a projectile. The systems and methods may comprise automatically converting the ballistic trajectory into a ballistic flight path comprising a plurality of coordinates. The systems and methods may comprise electronically communicating the ballistic flight path to a guidance system of an Unmanned Aerial Vehicle (UAV). The guidance system may be configured to cause the UAV to navigate along the ballistic flight path. The systems and methods may comprise automatically collecting environmental data along the ballistic flight path.

A target designator for a guided weapon is disclosed. The designator has a sight arranged to display, in operation, a reticule superimposed upon a field of view. The reticule is moveable within the field of view. The designator further comprises an eye tracker operable to track the gaze of the operator whilst the operator uses the sight. The eye tracker communicates with the sight such that the reticule moves so as to be aligned with the direction of the gaze of the operator.