Notice of RetractionAttitude algorithm of MEMS IMU for advanced rocket ammunitions with Swing Markov IMM

Notice of Retraction

After careful and considered review of the content of this paper by a duly constituted expert committee, this paper has been found to be in violation of IEEE´s Publication Principles.

We hereby retract the content of this paper. Reasonable effort should be made to remove all past references to this paper.

The presenting author of this paper has the option to appeal this decision by contacting TPII@ieee.org.

The error correction of MEMS Inertial Measurement Unit (IMU) is often implemented by the model filtering as well as the compensation of instrument error, which effectiveness of filtering is determined by the coherence between the models of filter and the maneuver modes of weapons. As the maneuverability of advanced rocket ammunitions with the lateral thrust greatly increased, the traditional filter models such as Constant Velocity (CV) are hardly matched against the rocket attitude oscillations with high frequency. Fortunately the attitude oscillations after the lateral thrust boost are similar to the damped oscillations with natural frequency, which natural frequency and damp ratio could be obtained from the aerodynamic analysis for rocket body. This paper introduced Swing Markov model into describing the attitude oscillations and proposed Swing Markov Interacting Multiple Model (IMM) with two models to establish the combinational filter, which corresponded with the attitude motion of advanced rocket ammunitions. The results and analysis of digital simulation for advanced rocket ammunitions demonstrated the satisfied accuracy of Swing Markov IMM filtering for attitude angle and angular ratio.