Accession Number : AD0430863


Title :   Dormant Missile Inertial Guidance and Control System. Phase I Study Program


Corporate Author : SPERRY GYROSCOPE CO GREAT NECK NY


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/430863.pdf


Report Date : JUL 1963


Pagination or Media Count : 33


Abstract : The results of a test program on a Rotating Pendulum Accelerometer (RPA) to determine its applicability to the Dormant Missile Inertial Guidance and Control System are presented. Test were performed primarily to determine stability and quick starting characteristics. The feasibility model originally fabricated was modified to attain the degree of quality expected of future models. The tests demonstrated feasibility, and performed in the manner predicted, showing the following characteristics: low noise, stability required by dormant system, ability to start quickly, and capability of perfect temperature compensation. (Author)


Descriptors :   *GUIDED MISSILES , *ACCELEROMETERS , *INERTIAL GUIDANCE , TEMPERATURE , STABILITY , CONTROL SYSTEMS , ACCELERATION , ELASTIC PROPERTIES , FEASIBILITY STUDIES , ROTATION.


Subject Categories : GUIDED MISSILES
      NAVIGATION AND GUIDANCE


Distribution Statement : APPROVED FOR PUBLIC RELEASE