Abstract
The Semi-Strapdown Inertial Navigation System (SSINS) provides a new solution to attitude measurement of a high-speed rotating missile. However, micro-electro-mechanical-systems (MEMS) inertial measurement unit (MIMU) outputs are corrupted by significant sensor errors. In order to improve the navigation precision, a rotation modulation technology method called Rotation Semi-Strapdown Inertial Navigation System (RSSINS) is introduced into SINS. In fact, the stability of the modulation angular rate is difficult to achieve in a high-speed rotation environment. The changing rotary angular rate has an impact on the inertial sensor error self-compensation. In this paper, the influence of modulation angular rate error, including acceleration-deceleration process, and instability of the angular rate on the navigation accuracy of RSSINS is deduced and the error characteristics of the reciprocating rotation scheme are analyzed. A new compensation method is proposed to remove or reduce sensor errors so as to make it possible to maintain high precision autonomous navigation performance by MIMU when there is no external aid. Experiments have been carried out to validate the performance of the method. In addition, the proposed method is applicable for modulation angular rate error compensation under various dynamic conditions.
Highlights
The independent high-precision measurement of a high-speed rotating missile’s attitude is the key technology of guidance and precision strikes, which is the main development trend of conventional high-speed rotating missile guidance [1]
The and attitudeThe accuracy increased by more than 65% by processes using theand method effect andposition navigation accuracy
Errors caused caused by acceleration-deceleration acceleration-deceleration the in effect and navigation accuracy
Summary
The independent high-precision measurement of a high-speed rotating missile’s attitude is the key technology of guidance and precision strikes, which is the main development trend of conventional high-speed rotating missile guidance [1]. The concept of the Gyroscope-free Strapdown Inertial Navigation System (GF-SINS) which uses a configuration of accelerometers only to measure the acceleration and rotational motion of a rigid body in 3D space has been proposed and extensively researched. In principle, it benefits from an effect known as lever-arm effect [3]. The complete AIV is used, but the focus is on the optimal design of the gyro-free inertial measurement unit (GF-IMU), avoiding the use of tri-axial accelerometers, and not on the fusion scheme [4]. In [5], Edwan et al presented an extended
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