Evaluation and optimization of strapdown velocity numerical integration algorithms for SINS in spinning ballistic missiles

The error of the conventional velocity numerical integration algorithm was evaluated through the Taylor series expansion. It is revealed that neglecting the second- and higher-order terms of attitude increments will lead to the velocity numerical integration error, which is proportional to the tripl...

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Vydané v:Journal of Central South University Ročník 20; číslo 4; s. 942 - 949
Hlavní autori: Song, Min, Wu, Wen-qi
Médium: Journal Article
Jazyk:English
Vydavateľské údaje: Heidelberg Central South University 01.04.2013
Predmet:
Engineering
Metallic Materials
strapdown inertial navigation system (SINS)
spinning missile
velocity algorithm
error
ISSN:2095-2899, 2227-5223
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Shrnutí:The error of the conventional velocity numerical integration algorithm was evaluated through the Taylor series expansion. It is revealed that neglecting the second- and higher-order terms of attitude increments will lead to the velocity numerical integration error, which is proportional to the triple cross product of the angular rate and specific force. A selection criterion for the velocity numerical integration algorithm was established for strapdown inertial navigation system (SINS) in spinning missiles. The spin angular rate with large amplitude will cause the accuracy of the conventional velocity numerical integration algorithm in SINS to decrease dramatically when the ballistic missile is spinning fast. Therefore, with the second- and higher-order terms of attitude increments considered, based on the rotation vector and the velocity translation vector, the velocity numerical integration algorithm was optimized for SINS in spinning ballistic missiles. The superiority of the optimized algorithm over the conventional one was analytically derived and validated by the simulation. The optimized algorithm turns out to be a better choice for SINS in spinning ballistic missiles and other high-precision navigation systems and high-maneuver applications.
ISSN:2095-2899
2227-5223
DOI:10.1007/s11771-013-1569-9