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 time domain detection system to measure and report on hypervelocity impacts HVI between an interceptor vehicle and a target vehicle. Wherein, said time domain detection system comprises a target vehicle components installed on said target vehicle, a one or more panels arranged on a portion of said target vehicle at a potential HVI locations, and a hit detection system wired into said one or more panels. Said target vehicle components comprise at least said hit detection system, and a lines. Said one or more panels are wired into said hit detection system with said lines. Said hit detection system is configured to communicate with said one or more panels over said lines. Said one or more panels can each comprise a one or more detector panel layers, and a two or more insulator layers.

A device for detecting and/or tracking a projectile has a receiving antenna, for receiving at least an electromagnetic signal emitted by at least one radar, at least one amplifier configured to amplify the electromagnetic signal received by the receiving antenna, and at least one emitting antenna. The emitting antenna is configured to return, at an output of the device, an amplified electromagnetic signal for calculating data indicative of the trajectory of the projectile based at least on the amplified electromagnetic signal. A system for detecting a projectile has a transmitting device mounted on the projectile, a radar configured to sense an electromagnetic signal produced and sent by the transmitting device. The signals emitted from the projectile are limited to the electromagnetic signal sent by the transmitting device, and a processing unit, configured to calculate data indicative of the trajectory of the projectile, based on the sensing of the electromagnetic signal.

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 system and method for improved detection of lasers for use in laser guidance systems. By providing background illumination via one or more radiation sources the accuracy of the laser detection system can be improved. A closed loop system detects the background current on the detector and provides additional illumination when the back ground level is below a threshold current value thus providing for a faster detector response.

A weapon and weapon system, and methods of manufacturing and operating the same. In one embodiment, the weapon includes a warhead including destructive elements and a guidance section with a seeker configured to guide the weapon to a target. The seeker includes a detector configured to receive a distorted signal impinging on an objective lens from the target, memory configured to store target criteria and a correction map, and a processor configured to provide a correction signal based on the distorted signal, the target criteria and the correction map to guide the weapon to the target.

A system and method for improved detection of lasers for use in laser guidance systems. By providing background illumination via one or more radiation sources the accuracy of the laser detection system can be improved. A closed loop system detects the background current on the detector and provides additional illumination when the back ground level is below a threshold current value thus providing for a faster detector response.

The invention relates to a method for determining characteristic-curve correction factors a matrix detector that images in the infrared spectral range. A good image correction can be obtained by virtue of an area of homogeneous temperature being recorded at two different temperatures by the matrix detector, there being two images with different integration times for each temperature. A signal gradient over the integration time is established for each of the pixels from the four pixel values at the two temperatures in each case and the gain being established from the difference of the signal gradients and characteristic-curve correction factors for the gain being stored.

Techniques are provided for automated determination of a rocket configuration based on acceleration during rocket motor burn-out and temperature. The rocket configuration is associated with a class of warhead affixed to the rocket. A methodology implementing the techniques according to an embodiment includes measuring the acceleration of the rocket over a period of time associated with the flight of the rocket. The method also includes calculating an acceleration difference between the measured acceleration associated with the start of rocket motor burn-out and the measured acceleration associated with the end of rocket motor burn-out. The method further includes measuring an internal temperature of the rocket and selecting a delta acceleration threshold based on the measured temperature. The method further includes comparing the calculated acceleration difference to the selected delta acceleration threshold, to estimate the rocket configuration. The estimated rocket configuration is used by guidance and control circuitry to select autopilot parameters.

An autonomous flight termination system for terminating vehicle flight after the vehicle is launched from an aircraft includes a global positioning system (GPS) receiver; a termination unit selected from a cut-off switch connected to terminate vehicle flight when actuated, and a switch connected to detonate an explosive on the vehicle; a system controller for receiving a first signal indicating separation of the vehicle from the aircraft and a second signal from the GPS receiver to calculate an actual vehicle trajectory, and for sending a third signal to actuate the termination unit to terminate the flight of the vehicle when the actual vehicle trajectory is determined to be outside the safety bounds of a mission-planned flight trajectory; and a failsafe controller connected to receive operational data of the system controller, and to actuate the termination unit when the operational data indicates that the system is in an error state.