Abstract: A method is proposed for protecting a vehicle (2) from a threat (3), in which the threat (3) is recognized as such, preferably classified and a countermeasure (11) is implemented against the threat (3). For this purpose, a new overall situation resulting therefrom, consisting at least of a new wind direction and wind speed, as well as the direction of the threat and the threat distance, is calculated for every change of course and voyage. The calculated course and journey changes are displayed, in which a countermeasure to protect the vehicle can still be successfully implemented. The calculation takes into account at least wind data, threat type and threat direction. Furthermore, at least the vehicle's own data should be taken into account.

Abstract: The present disclosure primarily relates to interceptor unmanned aerial systems and methods for countering Unmanned Aerial Systems (UAS), although the inventions disclosed herein are useful for capture of any aerial object. The system utilizes a rigid effector frame, an effector attached directly to the frame, and at least two propulsion elements connected to the effector frame, and is configured to intercept and disable threat UAS. The disclosed systems can be oriented to any virtually any angle to maximize the chances of intercept.

Abstract: A system providing a physical-barrier defense against rocket-propelled grenades (RPGs) that is suitable for use on aircraft, ground vehicles and ships. The system includes a propulsion device (for example, a rocket) and a barrier that is attached to the propulsion device by one or more tethers. The barrier includes an inflatable frame. When the propulsion device is launched, an inflator inflates the frame to assume an open state, and the propulsion device pulls the tether and the barrier along a trajectory for intercepting an RPG.

Abstract: A system providing a physical-barrier defense against rocket-propelled grenades (RPGs). The system is suitable for use on aircraft, ground vehicles, and ships.

Abstract: The present invention relates to a method for antimissile protection of vehicles having a very short response time with practically no false alarms and not requiring the use of means such as decoys or conventional laser jammers, while providing the best possible protection. It is characterized in that at least one curtain of plasma filaments is created between these vehicles and the probable launch point of these missiles, this curtain being intended to blind the target-seeking device of the missiles.

Abstract: A protective device and protective measure for a radar system is provided that includes an active countermeasure by using passive emitter and/or decoys. Decoys are thereby utilized that function according to the reflection principle. These decoys are thereby radiated by the vehicle's radar. The radiation reflected by the decoys in the direction of the ARM has the same characteristic as the direct radiation from the radar itself. Thus, the ARM is unable to discriminate between decoys and the actual radar.

Abstract: A system of active protection system of objects has a central control panel, and at least one unit arrangeable on a protected object and including a target detection device, a protective ammunition connected with the target detection device, a device for moving the target detection device and the protective ammunition device, and a case accommodating the target detection device, the protective ammunition, and the moving out device, so that when the target detection device of the at least one unit detects a target, the ammunition of the at least one unit is moved out of the case and fired.

Abstract: An apparatus for protecting an object from an incoming munition includes a tracking apparatus mounted on the object, for tracking the incoming munition; a firing solution computer connected to the tracking apparatus; a plurality of launch tubes mounted on the object, the plurality of launch tubes pointing in different directions so as to maximize coverage of an area surrounding the object; a parachute container attached to each launch tube; an igniter disposed in a rear of each launch tube and connected to the firing solution computer; a propelling charge disposed in front of each igniter; a mass disposed in front of each propelling charge; a connecting ring attached to a front of each mass; a parachute disposed in the parachute container; and a cable connecting the connecting ring and the parachute.

Abstract: A system and apparatus for deployment of a decoy from a moving object, such as an aircraft, to protect the aircraft from an enemy missile. The decoy is stored in a housing mounted on the aircraft and is connected by a cable containing fiber optics and high voltage conductors. The cable is stored on a spool which is reciprocally moveable along a rotating shaft provided with a double helix and which is located coaxially within an outer rotatable de-bailer. The cable is drawn through a passage formed in an outer cylindrical side wall and end wall of the de-bailer as the decoy is deployed from the aircraft. The cable causes the de-bailer to rotate about the spool which reciprocates back and forth along the double helix shaft. The spool is connected to the helix of the shaft by a pawl and a brake mechanism controls the rotational speed of the shaft, and thus the payout speed of the cable.