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- W2602420152 abstract "This paper describes a new method for rapid initializationof a strapdown initial navigation system (SINS) which ishosted on a missile intended for vertical launch from aland vehicle. The SINS initialization aims to determineinitial values of the system, including position, velocity,and attitude. For a fixed host platform, the attitude is themost critical aspect of the initialization. There are twoalignment procedures. The first is the analyticalalignment, in which the attitude matrix is computeddirectly utilizing the output of an inertial measurementunit (IMU) in combination with known earth rotation andgravity. The second procedure, usually referred to as theprecise alignment, utilizes rough-wrought output from theanalytical alignment to estimate precise initial attitudeusing a Kalman filter. Commonly used methods forprecise alignment include the single-position alignment,the two-position alignment and the multi-positionalignment. The latter two methods are widely used onfixed platforms because of good observability of thesystem. The two-position alignment introduces the secondposition alignment by rotating the yaw angle by180o . Themulti-position alignment is implemented by furtherrotating yaw or pitch based on the rotation of the twopositionalignment. For a missile which is verticallylaunchedfrom a land vehicle, either the multi-position ortwo-position alignment reduces the effectiveness andflexibility of operations as both alignments require amachine to implement the yaw rotation.This paper presents a new two-position self-alignmentmethod, which introduces a rotation of pitch by 90o , tonaturally reflect the raising to an upright position of thewhile on a fixed land vehicle. Distinguishing itself fromthe commonly-used two-position alignment or multipositionalignment, the new method requires the rotationto the second position after the missile remains at the firstposition for 30s until the horizontal misalignment anglesbecome stable. In computer simulations, the effect of wind disturbance is considered. The results confirm thatthe proposed method can reduce the alignment period andachieve a higher precision of solution than those ofcommonly used methods." @default.
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- W2602420152 date "2008-09-19" @default.
- W2602420152 modified "2023-09-27" @default.
- W2602420152 title "Rapid Initialization of SINS for Land Vehicle-based Vertically-launched Missiles" @default.
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