Abstract: Disclosed is a self-surveying relative GPS (Global Positioning System) weapon guidance system (10). This guidance system (10) includes multiple GPS satellites (12-18) which transmit GPS data to a ground sensor (20). The ground sensor (20) includes a GPS receiver (24), a self-surveying computer (28), a data formatter (30) and a transmitter (32). The GPS receiver (24) receives the GPS data and determines a second location of the ground sensor (20) based on the GPS data. The self-surveying computer (28) determines a first location of the ground sensor (20) based on the GPS data gathered over time, which is more accurate than the second location. The data formatter (30) determines a GPS error between the first and second locations which is transmitted by the transmitter (32). The GPS error is used by guided weapons in the vicinity of the ground sensor (20) to substantially increase the delivery accuracy of the guided weapons (40).

Abstract: An autonomous bomb damage assessment system that is piggybacked to a bomb to provide imagery of a bombed area immediately after bomb delivery. The bomb damage assessment system comprises a housing that is releasably secured to the bomb. An imaging system is disposed at one end of the housing and a folded inflatable balloon is disposed at the other end of the housing. An inflation device is provided for inflating the balloon with a lighter-than-air gas such as helium. A proximity fuze is used to sense the location of the ground, for causing the system to be ejected away from the bomb shortly before bomb impact, and for causing the inflation device to inflate the balloon. A data link is disposed in the housing for transmitting images derived from the imaging system to a remote location. The present invention provides imagery of a bombed area immediately after bomb delivery. The lighter than air characteristic of the system allows a dwell time over the bombed area so debris and dust can settle.

Abstract: A bomb damage assessment system that is carried by a weapon and released to provide imagery of a bombed area before and after bomb delivery. The system comprises a glider that is releasably secured to the weapon that includes tracking and guidance electronics for programmably controlling the flight thereof. An imaging system is disposed in the front end of the glider and a deployable ballute is disposed at the rear end thereof. A data link is provided for transmitting images to a command center for review. The system provides imagery of a target area before, during and after weapon impact. Television or infrared cameras may be used for day or night missions. As a target area is approached, the glider is released, is decelerated by the ballute, wings are unfolded, and the ballute is released, resulting in an aerodynamic vehicle that flies much slower than the weapon. The imaging system tracks the weapon to impact. The explosion of the weapon produces a hot spot that is tracked by the imaging system.

Abstract: An improved imaging system. The inventive imaging system (10) is adapted to transmit a plurality of first radar signals at millimeter wave frequencies at an area including an object along with background clutter. The return signals are processed to provide a three dimensional image for applications demanding visibility through fog, haze, smoke and other obscurants. Such applications include enhanced vision for helicopters, ships, buses, trucks, traffic observation stations for an intelligent highway or security cameras for plants and military installations. In a guidance system application, for example, the inventive system would include an electronically scanning antenna (12) to provide range and amplitude signals representative of a target area. The range and amplitude signals (18, 20) are compared to stored signals (26, 30) to create the three dimensional image. The stored signals are selected for comparison based on the dive angle of the missile (28, 32).

Abstract: A method that provides precise target location measurement using a synthetic aperture radar (SAR) system jointly with a global positioning inertial navigation system (GPS/INS) located on a moving aircraft. The SAR system provides a precise measurement of the round trip elapsed radar wave propagation time from the aircraft location to a selected pixel in a ground map that includes a portion of the target. The velocity of radar wave propagation is measured at the same time that the range time lapse to the designated SAR map pixel is measured. When combined with position and velocity information derived from the GPS/INS inertial navigation system, the radar wave propagation time is used to calculate the position of the target pixel in GPS/INS coordinates, thereby improving measurement accuracy. The method comprises flying an aircraft containing GPS/INS and SAR systems along a predetermined flight path.