TY - JOUR
T1 - Hypersonic boost–glide vehicle strapdown inertial navigation system / global positioning system algorithm in a launch-centered earth-fixed frame
AU - Chen, Kai
AU - Zhou, Jun
AU - Shen, Fu Qiang
AU - Sun, Han Yan
AU - Fan, Hao
N1 - Publisher Copyright:
© 2020 Elsevier Masson SAS
PY - 2020/3
Y1 - 2020/3
N2 - To suit the features of hypersonic vehicles and meet the requirement of their flight control system, we propose an integrated navigation algorithm in the launch-centered earth-fixed (LCEF) frame. First, we introduce a system mechanization for the strapdown inertial navigation algorithm in the LCEF frame and derive discrete update algorithms of strapdown inertial navigation attitude, velocity, and position in the LCEF frame. A coning effect compensation algorithm is deduced in the update algorithm of attitude, and a sculling effect compensation algorithm is deduced in the update algorithm of velocity. Then, we derive the attitude, velocity, and position error equations in the LCEF frame; we further derive a strapdown inertial navigation system (SINS) / global positioning system (GPS) integrated navigation filter state equation and measurement equation of the LCEF frame as well as introduce a simultaneous method of SINS/GPS integrated navigation. Finally, considering the typical hypersonic boost–glide vehicle as the object, the SINS/GPS algorithm is applied in a semi-physical simulation environment; verification results yield a position error less than 10 m, a velocity error less than 0.2 m/s, and an attitude error less than 0.05°.
AB - To suit the features of hypersonic vehicles and meet the requirement of their flight control system, we propose an integrated navigation algorithm in the launch-centered earth-fixed (LCEF) frame. First, we introduce a system mechanization for the strapdown inertial navigation algorithm in the LCEF frame and derive discrete update algorithms of strapdown inertial navigation attitude, velocity, and position in the LCEF frame. A coning effect compensation algorithm is deduced in the update algorithm of attitude, and a sculling effect compensation algorithm is deduced in the update algorithm of velocity. Then, we derive the attitude, velocity, and position error equations in the LCEF frame; we further derive a strapdown inertial navigation system (SINS) / global positioning system (GPS) integrated navigation filter state equation and measurement equation of the LCEF frame as well as introduce a simultaneous method of SINS/GPS integrated navigation. Finally, considering the typical hypersonic boost–glide vehicle as the object, the SINS/GPS algorithm is applied in a semi-physical simulation environment; verification results yield a position error less than 10 m, a velocity error less than 0.2 m/s, and an attitude error less than 0.05°.
KW - Hypersonic vehicle
KW - Integrated navigation system
KW - Launch-centered earth-fixed frame
KW - Near space
KW - Strapdown inertial navigation algorithm
UR - http://www.scopus.com/inward/record.url?scp=85078569160&partnerID=8YFLogxK
U2 - 10.1016/j.ast.2020.105679
DO - 10.1016/j.ast.2020.105679
M3 - 文章
AN - SCOPUS:85078569160
SN - 1270-9638
VL - 98
JO - Aerospace Science and Technology
JF - Aerospace Science and Technology
M1 - 105679
ER -