The six degree of freedom trajectory equations fused with interference factors for the reentry maneuvering warhead at the reentry phase were designed. A method for parameter estimation based on partial derivative matrixes and deflection of trajectory parameters was studied. The reentry error for each node before the work of aided navigation system was calculated by this method. Theoretical analysis and simulation indicate that the proposed method of reentry error analysis for reentry maneuver warhead is reasonable, and the analysis result is in the range of estimated results. The aerodynamic disturbance is the primary factor affecting reentry error.
Key words
reentry maneuver /
reentry error /
aided navigation system /
error analysis /
error conversion
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