A system for transferring power and/or data between a host and a store over a single-wire umbilical cable is herein described. The system comprises a host-store interface configured to allow the transfer of both power and data between the host and a store in operative communication therewith. The store comprises a microcontroller and memory operatively coupled thereto, allowing the microcontroller to be powered on and to receive and store data sent by the host in its memory through a single-wire without requiring additional electronic systems that the store may comprise to also be powered on. This data may later be incorporated into pre-programmed systems onboard the store at full power-on, thereby enabling the reprogramming of the store without powering it on prior to launch.

An improved emitter tracking system. In aspects of the present teachings, the presence of a desired emitter may be established by a relatively low-power emitter detection module, before images of the emitter and/or its surroundings are captured with a relatively high-power imaging module. Capturing images of the emitter may be synchronized with flashes of the emitter, to increase the signal-to-noise ratio of the captured images.

An improved emitter tracking system. In aspects of the present teachings, the presence of a desired emitter may be established by a relatively low-power emitter detection module, before images of the emitter and/or its surroundings are captured with a relatively high-power imaging module. Capturing images of the emitter may be synchronized with flashes of the emitter, to increase the signal-to-noise ratio of the captured images.

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.

A cover assembly is provided, for use with an instrument package having a common aperture. The cover assembly includes an inner cover member and an outer radome member. The inner cover member is substantially transparent to electromagnetic (EM) radiation of at least a first wavelength range. The radome member is configured for selectively and reversibly covering the inner cover member and transparent to EM radiation of at least a second wavelength range different from the first wavelength range. The second wavelength range includes a radio frequency wavelength range. The outer radome member is configured for being mounted in overlying relationship with respect to the common aperture of the instrument package. The radome member is configured for being initially in overlying relationship with respect to the inner cover member and for being selectively removed from the overlying relationship with respect to the inner cover member at least during flight conditions.

A method for planning and launching two or more missiles, to be included in the same mission, and where this is done from one or more aircraft in such a way that the missiles arrive at same target approximately at the same time without interfering with each other on the way to the target. The planning of the mission is performed by sending a set of identical mission data to the missiles prior to launch; letting each missile be assigned a unique identity, letting each missile calculate identical trajectories and a unique offset to this, in one or more of four dimensions, where a resulting offset trajectory is unique for each missile and based on the identical mission data and unique identity, and launching the missiles included in the same mission.

A system and method is provided for detecting the trajectory of multiple fragments through a conic or cylindrical section, such as the body of a missile. Three or more sensors are placed on the on the body of the object. Each of the sensors is constructed and arranged to measure signals to the sensor at from impacts on one or more locations on the body. The sensor then transmits a signal commiserate with the impact of a fragment thereon. A computer system is also provided to perform necessary calculations and, potentially, record the impact times and locations. When the body of the object is hit by fragments or shrapnel, a signal from one or more of the sensors is sent to the computer system. This operation is performed and constantly updated for all locations where a fragment is detected by one or more of the sensors. Waveforms of the impacts are recorded, but because multiple hits can occur, there can be superposition (or destruction) of the resulting waveform sent to the computer system. The computer system can interpret which superposition or destruction is indicative of another fragment strike, and filter out those additions or subtractions to the waveforms that could not possibly be from another fragment.

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.

Disclosed is a method for delivering a load on-board an aircraft to a target. The method comprises: acquiring a position of the target; acquiring parameter values relating to aircraft maneuverability; acquiring load properties; acquiring parameter values relating to environmental conditions; using the acquired information, determining a position and a velocity value; performing, by the aircraft, the procedure; and, at a point in the procedure that the aircraft has the determined position and its travelling at a velocity equal to the determined velocity value, releasing the load. The determined position and velocity value are such that, were the aircraft to release the load while having the determined position and velocity, the load would travel to be within a predetermined distance of the target. The procedure is such that the aircraft would have the determined position and velocity at some time-step.

Disclosed herein is a system and method for simulating real-time visualizable electronic warfare. The system includes a location calculation unit for calculating location coordinates of the aircraft and the missile for each frame according to a display frame rate, a display unit for visualizing, for each frame, movement of the aircraft and the missile depending on the location coordinates thereof, a precise tracking unit for, when a relative distance between the aircraft and the missile is less than a dangerous distance, dividing an interval between a current frame and a subsequent frame into sub-intervals based on the display frame rate, and sampling locations of the aircraft and the missile, and a proximity fuse control unit for processing the missile to explode when a relative distance between sampled locations of the aircraft and the missile, is less than or equal to a maximum explosible distance of a proximity fuse of the missile.