DocumentCode
2201762
Title
On SINS for Rocket Bomb Trajectory Correction Based on MEMS
Author
Ren, Bo ; Li, Huan
Author_Institution
Sch. of Equip. Eng., Shenyang Ligong Univ., Shenyang, China
fYear
2010
fDate
1-3 Nov. 2010
Firstpage
296
Lastpage
299
Abstract
Taken guided rocket bomb as the research object and aimed at trajectory correction, the kinematics model of guided rocket bomb is established and a strap down inertial navigation system(SINS) is designed using MEMS inertial sensors. According to the output data of guidance system, a differential geometry algorithm is proposed to calculate the curvature of the actual trajectory. Compared it with the which of the designed trajectory, deviate error is obtained to control rudder leaning angle to achieve trajectory correction. The simulation analysis shows that the method can greatly improve the accuracy of long-range rocket bomb.
Keywords
differential geometry; inertial navigation; missile guidance; rockets; sensors; MEMS inertial sensor; SINS; differential geometry algorithm; guided rocket bomb; kinematics model; rocket bomb trajectory correction; strapdown inertial navigation system; trajectory correction; MEMS; SINS; differential geometry; rocket bomb; trajectory;
fLanguage
English
Publisher
ieee
Conference_Titel
Intelligent Networks and Intelligent Systems (ICINIS), 2010 3rd International Conference on
Conference_Location
Shenyang
Print_ISBN
978-1-4244-8548-2
Electronic_ISBN
978-0-7695-4249-2
Type
conf
DOI
10.1109/ICINIS.2010.31
Filename
5693738
Link To Document