Abstract
The purpose of this paper is to present an in-flight initial alignment method for the guided projectiles, obtained after launching, and utilizing the characteristic of the inertial device of a strapdown inertial navigation system. This method uses an Elman neural network algorithm, optimized by genetic algorithm in the initial alignment calculation. The algorithm is discussed in details and applied to the initial alignment process of the proposed guided projectile. Simulation results show the advantages of the optimized Elman neural network algorithm for the initial alignment problem of the strapdown inertial navigation system. It can not only obtain the same high-precision alignment as the traditional Kalman filter but also improve the real-time performance of the system.
Highlights
The initial alignment of the strapdown inertial navigation system (SINS) provides initial values in order to complete the navigation calculations task, including initial position, initial velocity, and initial attitude
The purpose of this paper is to present an in-flight initial alignment method for the guided projectiles, obtained after launching, and utilizing the characteristic of the inertial device of a strapdown inertial navigation system
Since the attitude matrix is corrected by the estimation of the misalignment angle in initial alignment, the simulation results of the three misalignment angles under the Unscented Kalman Filter (UKF) filter and the Elman neural network are compared
Summary
The initial alignment of the strapdown inertial navigation system (SINS) provides initial values in order to complete the navigation calculations task, including initial position, initial velocity, and initial attitude. Due to the accumulation of initial errors in navigation calculations, it is necessary to control the initial alignment errors within a certain range, especially the initial attitude error. The main task of the initial alignment is to determine the initial direction cosine matrix, namely, the attitude matrix Cbn, which is transferred from the body coordinate (b-coordinate) to the navigation coordinate (n-coordinate). Many researches on static base alignment technology are discussed and studied [1,2,3,4], but for the guided projectile studied in this paper, the velocity and attitude dynamically change, so it is necessary to complete the alignment under the condition of the movement base. The gravitation acceleration and the gyro-measured value of the earth’s rotation cannot be used to calculate the attitude matrix Cbn [5]
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