Countermeasure simulating structures may include (a) a base and (b) one or more separated combustible tracks fixed to the base's surface. The combustible tracks may include thermite and/or other combustible material. The combustible tracks may be shaped to simulate countermeasure flares deployed by a vehicle (e.g., a jet). The countermeasure simulating structure may be incorporated into a countermeasure simulating system that includes (a) an infrared and/or optical sensing system (e.g., like those included in missiles) and (b) a simulator mount holding the countermeasure simulating structure. Countermeasures may be tested in such systems by: (a) arranging an infrared and/or optical sensing system to receive infrared energy and/or visible light emitted by the countermeasure simulating structure; (b) igniting the combustible material of the combustible track such that combustion of the combustible material moves along the combustible track; and (c) determining whether the infrared and/or optical sensing system tracks infrared energy and/or visible emitted by the combustion.

A method is provided for calculating the bursting point of at least one projectile fired at a target object, involving measuring the position of the projectile, estimating the position of the projectile, estimating the speed of the projectile, measuring the position of the target object, estimating the position of the target object, estimating the speed of the target object, calculating optimal bursting points for the projectile based on the estimated position of the projectile, the estimated speed of the projectile, the estimated position of the target object and the estimated speed of the target object, and communicating the bursting points for the projectile to the projectile. A computer program, a computer system, and a weapons system are also provided.

An inflatable dummy target comprising a chassis of inflatable ducts wrapped with a sheet.

A Vehicle Based Independent Range System (VBIRS) (10) comprised of individual stacked chambered modules that function as a single integrated system that provides a self-contained space based range capability, and is comprised of a power module (12), an artificial intelligence/autonomous engagement/flight termination system module (20), a satellite data modem module system (30) and a navigation, communications and control module system (40), all of which interface with a VBIRS test and checkout system (52) and a weather data system (116). The artificial intelligence/autonomous engagement/flight termination system module (20) is comprised of an inherent artificial intelligence capability that envelopes and interchanges data with an autonomous engagement controller (22) that contains all missile/rocket autonomous cooperative engagement, destruct decision software and range safety algorithm parameters required for optimum mission planning. VBIRS employed aboard an aircraft or between any combination of launching systems allows that aircraft to launch a missile/rocket from any location on earth, whether the missile/rocket is singularly launched by itself or as a larger group of missiles/rockets launched in a salvo arrangement, while providing collaborative real-time targeting to occur directly between missiles/rockets in conjunction with other missile/rocket launch platforms or stand-alone mission control centers.

A simulator for simulating a use of a missile of an attacking system is proposed. The simulator comprises: a storage device for storing of a terrain model of a battle terrain and target object models of target objects; a sensing unit for sensing and tracking a defined target object of the target objects in the battle terrain; a transmitting unit for transmitting a coded laser signal to the defined target object; a receiving unit for receiving a response signal transmitted by the defined target object; a providing unit for providing a target object model for the defined target object in dependence on at least type information of the received response signal; and a visual means associated with the missile for outputting a current visual representation of the battle terrain by means of the terrain model, the provided target object model and the location information.

Disclosed is a decision assistance system (8) for firing a projectile at a target (4) mounted on a mobile carrier (1), the system comprising: a first simulator (10) for applying a process repeatedly to simulated data that represent a configuration of the carrier and a trajectory of the carrier between a first (T1) and a second (T2) instant, to develop a precision of a navigation solution of the associated carrier at the second instant (T2); a second simulator (12) for: a) being initialized with said precision, b) applying a process repeatedly to simulated data that represent a trajectory of the projectile between the second and a third instant (T3), in order to develop a precision of a navigation solution of the projectile (4) associated with the third instant (T3), and a selector (14) for either selecting the projectile or not (4) in order to fire on the target, according to the precision developed in step b).

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 ground imaging system for use on a guided aerobody includes one or more lenses designed to receive EM radiation from a ground level, a filter substrate having a plurality of filters, a sensor array designed to receive the EM radiation from the filter substrate, and a processing device coupled to the sensor array. The filter substrate is located at a focal plane of the one or more lenses such that the filter substrate receives the EM radiation from the one or more lenses. The plurality of filters includes at least polarization filters and multispectral filters. The processing device is designed to analyze multispectral and polarization signatures of the electromagnetic radiation from identified objects at the ground level and determine that one or more of the objects is not a desired target based at least on the hyperspectral and polarization signatures of the one or more objects.

The present invention relates to a training system for training of a forward controller. The training system utilises a pod housing that can be attached to a hardpoint under an aircraft wing. The pod is configured to receive communications from the forward controller on the ground (or in another aircraft) and communicate wirelessly with an HMD and/or electronic device in the cockpit of the aircraft. This allows cheaper, less expensive aircraft to be used for training purposes.

A course correction system for a projectile can include a pre-steering trajectory determination module. The pre-steering trajectory determination module can be configured to receive a series of possible trajectories from an estimation module including a physical model defining trajectory as a function of gravitational pull and one or more launch variables, and receive a sensor data from one or more on-board sensors of the projectile. The pre-steering trajectory determination module can also be configured to reduce the possible trajectories from the estimation module to one or more refined trajectories using the sensor data, and output the one or more refined trajectories.