Adaptive electronically steerable array (AESA) system for interceptor RF target engagement and communications

#Field of the Invention

#This invention relates to adaptive electronically steerable arrays (AESAs), and more particularly to an AESA system for a missile interceptor comprising multiple AESA arrays positioned on forward facing surfaces of the interceptor's aerodynamic control surfaces for radio frequency (RF) target tracking and communications. Deployment of the AESA arrays on the aerodynamic control surfaces frees up volume, thus increasing design options for an IR seeker.

#Description of the Related Art

#FIGS. 1a and 1b are perspective and side views of an embodiment a dual-mode missile seeker including an RF seeker having AESA arrays positioned on aerodynamic control surfaces and a strapdown IR seeker;

#FIGS. 2a and 2b are perspective and side views of another embodiment a dual-mode missile seeker including an RF seeker having AESA arrays positioned on aerodynamic control surfaces and a strapdown IR seeker;

#FIGS. 3a, 3b, 3c and 3d are diagrams of an embodiment of an AESA array geometry, the layout of the radiating elements in a single AESA array, the beam pattern for a single array and the beam pattern of the full array;

#The present invention describes an AESA system for RF target engagement and communications for interceptor. The AESA system comprises multiple arrays that are deployed on aerodynamic control surfaces of the interceptor. The arrays may be controlled independently or in concert for RF target engagement or communications. The AESA system may be paired with an IR system for dual-mode operation. Removal of the AESA system from the interceptor radome increases the design options for implementation of the IR system. For example, the dual-mode system may be able to eliminate the mechanical gimbal for the IR seeker and use an axisymmetric dome without sacrificing performance.

#The interceptor may be any airborne vehicle that includes aerodynamic control surfaces. These surfaces may provide lift or maneuverability, may be fixed or moveable. For example, the interceptor may be a self-propelled missile, a gun-launched projectile, a unmanned aerial vehicle (UAV), a manned aircraft or a planetary lander (provided the destination planet has an atmosphere). Without loss of generality, the AESA system will be shown in described in the context of a missile interceptor having four fixed dorsal fins positioned every 90 degrees about the circumference of the interceptor. The dorsal fins are modified to incorporate the AESA arrays and radome elements.

#Referring now to FIGS. 1a and 1b, an embodiment of an interceptor 10 includes an AESA system 12 for RF target engagement and communications and an IR system 14 for terminal target engagement. Interceptor 10 includes a missile body 16, generally a cylindrical metal tube symmetric about a longitudinal axis 18, a payload 20 including a forward hemispheric dome 22, and 4 fixed dorsal fins 24 positioned every 90 degrees about the circumference of the interceptor and running the length of the interceptor. The dorsal fins provide aerodynamic stability for the missile interceptor. Each dorsal fin has a forward-facing surface 26 that is generally perpendicular to longitudinal axis 18. This surface will have a shape, triangular or rectangular, dictated by the cross-section of the fin.