Performance of an Air-to-Ground Missile Employing SAR-Retran Guidance.

摘要

The compatibility of a representative 500 pound weight boost-glide air-to-ground missile with the trajectory constraints imposed by a Synthetic Aperture Radar - Retransmission guidance system was investigated using a digital flight simulation. A demonstration flight profile was assumed, with a minimum of 20 seconds of tracking on the aircraft-to-target line of sight required. A guidance algorithm was developed which produced satisfactory trajectories. A first order gradient technique was employed in an unsuccessful attempt to optimize the trajectories for maximum range. A useable launch envelope for this missile was determined. The azimuthal extent of the envelope was limited by radar system constraints to 15 deg-90 deg from the aircraft velocity vector. A maximum slant range of 21 nautical miles was obtained from a launch altitude of 35,000 ft. Range deteriorated rapidly with decreasing launch altitude, with 5,000 ft being the lowest altitude at which a useable launch envelope was obtained. Maximum slant range at 5,000 ft launch altitude was 5.5 nautical miles. (Author)