Journal Of Guidance, Control, Dynamics（杂志的指导,控制,动态）.pdfVIP

BLAZING GYROS - THE EVOLUTION OF STRAPDOWN INERTIAL NAVIGATION TECHNOLOGY FOR AIRCRAFT Paul G. Savage Strapdown Associates, Inc. (SAI) WBN-14009 May 29, 2015 Originally published in the AIAA Journal Of Guidance, Control, Dynamics Volume 36, Number 3, May - June, 2013, Pages 637-655 INTRODUCTION Inertial navigation is the process of autonomously calculating the position and velocity of a moving vehicle from measurements of angular rotation and linear acceleration provided by vehicle mounted inertial sensors (gyros and accelerometers). The first inertial navigation system (INS) was developed at the MIT Instrumentation Lab (eventually becoming the Charles Stark Draper Laboratory) for ballistic missile guidance [1]. Soon thereafter, the technology was applied to aircraft navigation, with four companies eventually dominating the US aircraft inertial navigation (INS) industry in the 1960s; Honeywell Aerospace and Defense Group with gyro design/manufacturing in Minneapolis, MN and INS design/development/manufacturing in Clearwater, FL; Kearfott in Wayne, NJ; Litton Guidance Control Division in Woodland Hills, CA, and Delco Electronics Division of General Motors in Milwaukee, WI. Honeywell specialized in high accuracy systems and introduced a new electrostatically suspended gyro (ESG) technology for precision applications. Delco concentrated on transoceanic commercial and military cargo/tanker aircraft applications using the Carousel IV system (a variation of the Titan II ballistic missile inertial guidance set). Litton and Kearfott focused on medium accuracy military tactical aircraft and airborne missile applic