A lightweight (i.e., less than 50 kg) optical jammer system for use with a satellite in earth orbit. The jammer system is mounted on the satellite and produces an obfuscating programmable signature of concentrated sunlight which is modulated and directed to earth. A potential enemy observer on earth is thereby prevented from ascertaining the general mission of the satellite, because the known reflected sunlight signature of the satellite is masked.
One or more decoys (22) are towed by an aircraft (18) to confuse hostile radar. The tow lines (20) to the decoys (22) include fiber optic components which optically transmit to the decoys (22) both radio frequency signals for retransmission to hostile radar (24), and direct current power. The fiber optic components absorb strain forces imposed by towing the decoys (22). Multiple decoys (22) are deployed at varying distances from the aircraft (18) to increase the overall range of frequencies covered by the system, simulate a plurality of false targets, or accomplish angle gate deception. The deception may be accomplished by transmitting signals from the decoys in sequence and can be enhanced by dynamically varying the power levels of the decoy transmitting antennas. The fiber optic components may be separate optical fibers deployed separately or joined together for simultaneous deployment. The preferred configuration is a single optical fiber with coaxial inner and outer cores. The decoy preferably has a transmitting antenna in the form of a simulated biconical dipole. In one embodiment, both halves of the dipole are simulated by a set of fins. In another embodiment, the forward half is simulated by a truncated cone.
One or more decoys (22) are towed by an aircraft (18) to confuse hostile radar. The tow lines (20) to the decoys (22) include fiber optic components which optically transmit to the decoys (22) both radio frequency signals for retransmission to hostile radar (24), and direct current power. The fiber optic components absorb strain forces imposed by towing the decoys (22). Multiple decoys (22) are deployed at varying distances from the aircraft (18) to increase the overall range of frequencies covered by the system, simulate a plurality of false targets, or accomplish angle gate deception. The deception may be accomplished by transmitting signals from the decoys in sequence and can be enhanced by dynamically varying the power levels of the decoy transmitting antennas. The fiber optic components may be separate optical fibers deployed separately or joined together for simultaneous deployment. The preferred configuration is a single optical fiber with coaxial inner and outer cores. The decoy preferably has a transmitting antenna in the form of a simulated biconical dipole. In one embodiment, both halves of the dipole are simulated by a set of fins. In another embodiment, the forward half is simulated by a truncated cone.
A light weight decoy for deceiving radar and forward looking infrared tracking systems. The decoy provides the same radar cross-section as that of an intercontinental ballistic missile (ICBM) and is thermally massive across the entire black body spectrum. Thermal massiveness is accomplished by measuring the temperature of the decoy outer surface and the temperature of the space surrounding the decoy, obtaining the differential temperature, and radiating heat within the decoy to maintain the surface thereof at a temperature similar to that of an ICBM.
A device for the directional transmission and the directional reception of modulated light waves between geostationary satellites, or respectively geostationary satellites still close to earth, which have been constructed in a particularly weight-saving manner.
A countermeasure system, adapted for use on board an aircraft, for confus an incoming missile as to the location and heading of the aircraft. The countermeasure system generates for each side of the aircraft at least two infrared energy images which are projected onto the aircraft's fuselage and then swept across the aircraft's fuselage to confuse the incoming missile's infrared seeker. Each infrared energy image is generated by at least two lasers operating at different frequencies within the infrared region of the electromagnetic spectrum. A beam combiner combines the beams of infrared energy from each laser forming a single collimated beam of infrared energy having multiple frequencies which is then directed to a beam former. The beam former spreads the collimated beam of infrared energy which it then directs to a scanner. The scanner, which is mounted in a wing tip pod on the aircraft, directs the collimated beam to the fuselage of the aircraft sweeping the beam of infrared energy over the fuselage of the aircraft to confuse the infrared seeker of the incoming missile as to the flight path of the aircraft.
