An Integrated DGPS/INS Navigation System for a Ballistic Missile: Design and Flight Test Results

John Coffee, Prasad Maganty

Abstract:	The design and flight test results of a tightly cow pled, difTerentia1 GPS/INS navigation system are pre- sented. The integrated navigation system was de- signed and developed to provide low cost, precise tracking of medium range ballistic missiles on test ranges. A 27 state, extended Kalman filter blends data from a space stabilized, inertial platform with DGPS pseudorange and pseudorange rate measurements to produce real-time estimates of navigation and sensor errors. Low cost is achieved through the use of C/A- code GPS receivers and surplus Pershing I1 inertial hardware. The tightly coupled approach allows in- ertial sensor errors to be corrected during the boost and ballistic portions of the trajectory before reentry, where DGPS updates may be unavailable due to GPS jamming or loss of DGPS corrections. Navigation sys- tem performance sinidation results are presented, and the estimated degradation of reentry navigation accu- racy due to the loss of DGPS updates over the course of the trajectory are detailed. System performance was validated with a 130Iim test flight on a ballistic missilc with a Pershing I1 reentry vehicle, and results of the flight test are presented. When used with a giiidctl reentry vehicle, the navigation system has potential uses in precise targeting applications.
Published in:	Proceedings of the 1996 National Technical Meeting of The Institute of Navigation January 22 - 24, 1996 Loews Santa Monica Hotel Santa Monica, CA
Pages:	281 - 294
Cite this article:	Updated citation: Published in NAVIGATION: Journal of the Institute of Navigation
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