%0 Journal Article
%T Method of large acceleration change for in
%A Xin-hua Zhu
%A Yan Su
%A Yun Xu
%A Zhen Hong
%J Transactions of the Institute of Measurement and Control
%@ 1477-0369
%D 2019
%R 10.1177/0142331218811468
%X Aiming at the problem that the purposive maneuver of the guided projectile is difficult to be realized during its short flight time, a method based on large acceleration change using double-vector observations for the in-flight alignment was proposed. First, according to the navigation velocity rate equation, double-vector observations were derived, and the Request algorithm was introduced for the initial attitude estimation. Then, error analysis was discussed, which puts forward a large acceleration change for the in-flight alignment. Simulation experiment analyzed and discussed the effectiveness of the proposed large acceleration change for the in-flight alignment. The simulation result indicated that the in-flight alignment can be achieved quickly, and the heading misalignment error is about 0.3กใ, the pitch and rolling misalignment errors are less than 0.2กใ
%K Micro Inertial Navigation System (MINS)
%K large acceleration change
%K guided projectile
%K in-flight alignment
%K attitude determination
%U https://journals.sagepub.com/doi/full/10.1177/0142331218811468