Accession Number : AD0831546
Title : INERTIAL GUIDANCE-FLIGHT CONTROL INTEGRATED TEST DESCRIPTION AND TEST PLAN,
Corporate Author : GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
Personal Author(s) : Baker, C. L.
Report Date : 08 APR 1959
Pagination or Media Count : 11
Abstract : The integrated procedure described in the document is to be used during the early phases of the D series R and D missile production for determining compatibility between the Flight Control and Inertial Guidance systems subsequent to the separate System Tests and prior to the Composite Test. It is not intended that this test be a mandatory requirement for all D AIG missiles. Instead, this test will be eliminated when the frequency of problems arising from the mating of the two systems decreases to a level that will not warrant the time and energy required to perform and evaluate the test. (Author)
Descriptors : *CHECKOUT PROCEDURES), (*ALL INERTIAL GUIDANCE, (*FLIGHT CONTROL SYSTEMS, CHECKOUT PROCEDURES), SURFACE TO SURFACE MISSILES, CHECKOUT EQUIPMENT, INTEGRATED SYSTEMS, TEST METHODS, AUTOMATIC PILOTS, NAVIGATION COMPUTERS, ATTITUDE CONTROL SYSTEMS, COMPATIBILITY.
Subject Categories : Surface-launched Guided Missiles
Distribution Statement : APPROVED FOR PUBLIC RELEASE