Application of GPS for Missile Post Flight Guidance Accuracy Analysis

Abstract

The high quality of a GPS-based trajectory reference makes it useful for evaluating the performance of a missile's Inertial Navigation System (INS) during a missile flight test. The complexity of the design of the GPS user segment depends on flight test objectives and factors such as the expected satellite/vehicle geometry. Design curves are developed which illustrate the relationship between flight test objectives, the GPS user segment design, and such factors as antenna performance.