Journal of Projectiles, Rockets, Missiles and Guidance >
SINS/GPS Integrated Navigation System for Airborne Missile
Received date: 2011-10-03
Online published: 2025-05-29
In view of the characteristics of airborne missile, the SINS/GPS integrated navigation system for airborne missile was studied, fire control system arithmetic and integrated navigation system structure were designed; Local geographical coordinates was selected as integrated navigation coordinate frame. The error state and measurement equations under local geographical coordinates were derived. Finally, Monte Carlo simulation was adopted. The simulation results show that the integrated navigation arithmetic is feasible and can be applied, which indicates good prospect in aviation application.
CHENG Haibin , ZHANG Hongbo , LU Hao , XU Jianyun . SINS/GPS Integrated Navigation System for Airborne Missile[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2012 , 32(5) : 14 -16 . DOI: 10.15892/j.cnki.djzdxb.2012.05.024
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