Tactical Inertial Measurement Unit (IMU) integrated with missile borne Global Positioning System (GPS) antenna and ground-based receiver electronics.

摘要

Much of the recent developments involving the Global Positioning System (GPS) involves the integration of GPS and Inertial Navigation Systems (INS). These developments have been focused around manned platforms which have operator assisted capabilities such as aircraft and ground vehicles. The issues surrounding missile borne GPS/INS integrated systems differ in several important ways including time-of-flight, proximity and orientation to a jamming environment, flight dynamics, shadowing due to missile body/terrain/battlefield obstacles as well as system considerations such as size, weight, and power. The purpose of this research is to design, implement, and evaluate the sub-optimal integration filter formulated to accommodate a missile borne GPS antenna and ground based receiver electronics in a highly dynamic environment with tactical quality inertial instruments. Linear covariance simulation analysis will be utilized to predict system performance. The goal is to improve accuracy at the transition point between cruise and terminal homing and identify the trade-offs between sensor accuracy and loss of GPS.