
Accession Number : AD0812945
Title : PRINCIPAL ERROR AXES AND OPTIMIZATION OF ACCELEROMETER MOUNTING ANGLES IN INERTIAL GUIDANCE SYSTEMS.
Descriptive Note : Technical rept.,
Corporate Author : AIR FORCE MISSILE DEVELOPMENT CENTER HOLLOMAN AFB NM
Personal Author(s) : Nichols, Julian S.
Report Date : APR 1967
Pagination or Media Count : 97
Abstract : This is a study of the physical significance and the guidance implications of the two accelerometer mounting angles. It is shown that the mounting angle of the singly integrating accelerometer defines a line in the pitch plane; velocity deviations along this line at engine cutoff result in maximum impact error. Similarly, the mounting angle of the doubly integrating accelerometer defines a line in the pitch plane; position deviations along this line at engine cutoff result in maximum impact error. The mounting direction of the singly integrating accelerometer is defined to be the principal error axis for velocity (PEAV). The mounting direction of the doubly integrating accelerometer is defined to be the principal error axis for position (PEAP). For typical cases, the range error is much more sensitive to acceleration errors in the direction of the PEAV than to acceleration errors in the direction of the PEAP.
Descriptors : *ACCELEROMETERS, *INERTIAL GUIDANCE, BIBLIOGRAPHIES, EQUATIONS OF MOTION, PARTIAL DIFFERENTIAL EQUATIONS, MISS DISTANCE, ROCKET ENGINES, THRUST TERMINATION SYSTEMS, GUIDED MISSILES.
Subject Categories : Navigation and Guidance
Distribution Statement : APPROVED FOR PUBLIC RELEASE