A DIGITAL COMPUTER PROGRAM FOR A GENERALIZED INERTIAL GUIDANCE SYSTEM ERROR ANALYSIS
TRW SPACE TECHNOLOGY LABS LOS ANGELES CA
Pagination or Media Count:
This paper considers the equations relating errors in inertial guidance system measurement instruments to errors in missile burnout position and velocity and consequently to target misses. The relationship is expressed in terms of three linear differential equations with trajectory-dependent coefficients and forcing functions which depend on the measurement instrument errors. The forcing functions are presented in forms sufficiently general to accommodate errors that might arise in widely different types of instruments, both accelerometers and gyroscopes. Furthermore, the forcing functions can be evaluated for arbitrary instrument orientations. Programmed on a digital computer, these equations allow swift computation of target misses for given component tolerances and component orientation and consequently facilitate the optimization of instrument orientation. Such a program has been used extensively by the authors for gyro orientation schemes and general error studies for a number of ballistic missile inertial guidance systems.
- Space Navigation and Guidance
- Guided Missile Trajectories, Accuracy and Ballistics