SINS in-Flight Alignment Using Quaternion Error Models
摘要
The widely used conventional linearized error models or perturbation models are not effective to represent the nonlinear characteristics of SINS error propagation with large attitude errors. Error equations in terms of quaternion error are derived, and extended Kalman filter techniques are used to solve the in flight alignment problems. In the case of small attitude errors, the nonlinear models can be reduced to conventional phi angle models. The simulation results show that the proposed error models may improve the performance of alignment.
引用本文（GB/T 7714）
Wei Chun. SINS in-Flight Alignment Using Quaternion Error Models[J]. 未知来源, 2001.
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