The present invention relates to a computer-implemented method for targeting missiles, to a corresponding computer program, to a corresponding computer-readable medium and to a corresponding data processing device, as well as to a missile.

A target intercept system for guiding an interceptor to a target using passive ranging includes an EO/IR sensor that provides target azimuth and elevation angles, target irradiance, target area and target length. A dual Kalman Filter architecture is implemented where, prior to a target image becoming resolved, i.e., prior to endgame, a first Kalman Filter provides guidance as a function of target azimuth and elevation angles and target irradiance measurements. After the target image becomes resolved, i.e., at endgame, a second Kalman Filter provides guidance as a function of target azimuth and elevation angles, target area and, optionally, target length, instead. The dual Kalman Filter approach improves the estimates of time-to-go by optimizing the on-board EO/IR sensor measurements at the optimal times.

The invention presents a system optimizing control coefficients of flight object under complex environmental effects using hybrid Fuzzy Logic and PID variant controller. The proposed system includes: target module, seeker module, guidance module, control module, dynamics module. The fuzzy logic controller is applied to determine the parameters coefficients of a proportional integral derivative (PID) based on the effect of these coefficients on the system response. The control module is less affected by the accuracy of the mathematical model and can perform well in environments with impact noise.

A target intercept system for guiding an interceptor to a target using passive ranging includes an EO/IR sensor that provides target azimuth and elevation angles, target irradiance, target area and target length. A dual Kalman Filter architecture is implemented where, prior to a target image becoming resolved, i.e., prior to endgame, a first Kalman Filter provides guidance as a function of target azimuth and elevation angles and target irradiance measurements. After the target image becomes resolved, i.e., at endgame, a second Kalman Filter provides guidance as a function of target azimuth and elevation angles, target area and, optionally, target length, instead. The dual Kalman Filter approach improves the estimates of time-to-go by optimizing the on-board EO/IR sensor measurements at the optimal times.

A proximity sensor for a Laser Guided Bomb (LGB) is provided. A proximity sensor for a Laser Guided Bomb (LGB) includes: an electronics package unit (EPU) configured to be connected to a front end of a warhead; and at least one sensor separate from the EPU and configured to be connected to a forward adapter that is connected to the front end of the warhead. The at least one sensor is configured to obtain data that is used to determine a height above ground of the LGB. The EPU is configured to compare the determined height above ground to a predefined value. The EPU is configured to generate a detonation signal for the warhead based on the determined height above ground being equal to or less than the predefined value.

A method of targeting a missile. A plurality of images of a target, taken from a plurality of viewpoints, are received. Features in the images characteristic of the target are identified. Data representing the characteristic features are provided to the missile to enable the missile to identify, using the characteristic features, the target in images of the environment of the missile obtained from an imager included in the missile.

A target assignment system includes a sensor system which detects a position of a moving vehicle, an assigning section which determines the launcher system assigned with the moving vehicle in response to the position of the moving vehicle and generates a first display signal which shows the moving vehicle and a first launcher system, a display section which displays the moving vehicle and the assigned launcher system in real time in response to the display signal, and an input section which instructs a change of the assigned launcher system. The assigning section generates a second display signal in which the first launcher system is changed to a second launcher system, in response to an instruction of assignment change.

A waveguide based fused vision system includes a helmet mounted or head worn sensor module and a display assembly. The display assembly includes a frame including a pair of waveguide combiners and a pair of projectors associated with waveguide combiners. The display assembly also includes a sensor module. The pair of projectors is disposed on opposite sides of a frame. The sensor module is disposed substantially above the frame and includes a first sensor, a second sensor, a video processing circuit, and a symbol generator. The video processing circuit is configured to merge first sensor information from the first sensor and first symbols from the symbol generator and to merge second symbols and the second sensor information for displaying conformally the real world scene.

A proximity sensor for a Laser Guided Bomb (LGB) is provided. A proximity sensor for a Laser Guided Bomb (LGB) includes: an electronics package unit (EPU) configured to be connected to a front end of a warhead; and at least one sensor separate from the EPU and configured to be connected to a forward adapter that is connected to the front end of the warhead. The at least one sensor is configured to obtain data that is used to determine a height above ground of the LGB. The EPU is configured to compare the determined height above ground to a predefined value. The EPU is configured to generate a detonation signal for the warhead based on the determined height above ground being equal to or less than the predefined value.

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.