Parameter identification for SINS coarse alignment based on apparent velocity

MENG Xiang-fei, LI Xin

(School of Electrical and Automation Engineering, Changshu Institute of Technology, Changshu 215500, China)

Parameter identification for SINS coarse alignment based on apparent velocity

MENG Xiang-fei, LI Xin

(School of Electrical and Automation Engineering, Changshu Institute of Technology, Changshu 215500, China)

Traditional dual-vector coarse alignment with apparent velocity has the problems of poor alignment precision and slow convergence rate due to the influence of random noises on inertial sensors. To solve this problem, a new dual-vector coarse alignment method is designed, which uses a new adaptive Kalman filter to estimate the parameters in an apparent velocity model without using the accurate covariance of the measurement noises. Meanwhile, a reconstructed algorithm with recognized parameters is adopted for the dual-vector, which can avoid the collinearity of the dual-vector. Analysis and simulation indicate that, by using this method, the random noises in the measured apparent velocity can be effectively eliminated compared with the traditional dual-vector coarse alignment. Simulation and turntable experiments show that, compared with traditional methods, the proposed method for the coarse alignment can acquire more accurate alignment results with the same alignment time, and can improve the convergence rate with the same alignment accuracy. The turntable tests by the new method show that the yaw error is -0.1391° and the standard deviation is 0.012°.

strapdown inertial navigation system; coarse alignment; adaptive Kalman filter; parameter identification; dual-vector attitude determination

The initial alignment is a critical technique for the strapdown inertial navigation system (SINS)[1]. The precision of the initial alignment determines the positioning precision of the pure inertial navigation. The traditional initial alignment procedure often consists of two consecutive stages: coarse alignment and fine alignment[2]. The current fine alignment methods based on Kalman filter rely heavily on the coarse alignment stage to provide a roughly known initial attitude, otherwise they cannot guarantee a rapid and accurate alignment result[3-4].

There are some coarse alignment methods such as analytical method, inertial frame method, gravitational apparent motion method and so on[5-7]. Among these methods, the dual-vector method based on the apparent velocity is an effective method for initial coarse alignment. However, because of the random noises in the apparent velocity, the performance of the coarse alignment precision was reduced, and it needs prolong alignment time to avoid the collinearity of the dual-vector.

To overcome the flaws of the traditional dual-vector coarse alignment, some methods based on low-pass filter technique are proposed[8], nevertheless, it is difficult to find an available low-pass filter for all environments with complex noise. Then, a method based on recursive least square (RLS) was proposed[9-10], the method analyzed the composition of the truth apparent velocity. With the identified parameters, the new accurate apparent velocity vector was constructed. This method can solve some existent problems in dual-vector coarse alignment. However, it needs the accurate statistical information of the sensor measurements, which can not be obtained easily from the actual system, and the error in the covariance of the measurements noises will reduce the performance of the coarse alignment.

To solve the aforementioned problems, this paper intends to adopt the new Kalman filter to estimate the parameters in the apparent velocity model[11-12]. It is based on the adaptive filter theory, so it does not need to analyze the measurement noises. And the reconstructed algorithm was used to avoid the collinearity of the dual-vector in this paper. The rest of the paper is organized as follows. The reference frame is presented in Section 1. Mechanism of the alignment method based on dual-vector is described in Section 2. Section 3 gives the adaptive Kalman filter for parameter identification and reconstruction algorithm. At last, the test results and conclusion are discussed in Section 4 and Section 5, respectively.

1 Reference frame

The coordinate frames in this paper are defined as:

1) The local level navigation frame (n): an orthogonal reference frame aligned with east-north-up (ENU) geodetic axes.

2) The SINS body frame (b): an orthogonal reference frame aligned within the IMU axes.

3) The earth frame (e): an Earth-centred Earth- fixed (ECEF) orthogonal reference frame.

4) The initial inertial frame (i0): an orthogonal reference frame non-rotating relative to the inertial frame, which is formed by the earth frame at the start-up in the inertial space.

5) The initial body frame (b0): an orthogonal reference frame non-rotating relative to the inertial frame, which is formed by the SINS body frame at the start-up in the inertial space.

2 Mechanism of the alignment method based on dual-vector attitude determination

Based on the chain-decomposition of the direction cosine matrix (DCM), the initial alignment matrix can be described as:

where, ωiedenotes the angular rate of the earth, L denotes the latitude of the IMU, and t is the alignment time.

The rate equation of IMU body frame respect to the initial IMU body frame is:

Therefore, the initial alignment can be completed with equation (1) to (9). However, there are still two problems in the aforementioned method. One is that the random noises in the apparent velocity, and the other is the collinearity of the dual-vector with the short time intervals, these contaminate the alignment results. To avoid the two problems, the adaptive Kalman filter technique was proposed in the next section.

3 Adaptive Kalman filter for parameter identifycation and reconstruction algorithm

To acquire more accurate alignment results compared with the existing methods, a novel method based on the parameter identification is proposed in the next subsection. With the estimated parameters, the new dual-vector can be reconstructed, and the two aforementioned problems can be eliminated effectively.

3.1 Parameter identification model

From the dual-vector coarse alignment, the critical step is how to calculate the apparent velocityb0, which can be obtained by integrating the apparent gravity gb0, it is calculated as:

where, B is the parameter matrix which used to construct the apparent velocity, and it is more accurately over the alignment time.

3.2 Adaptive Kalman filter

The RLS method can be used to estimate the parameter matrix, however, it needs the accurate measurement covariance, which cannot be attained easily from the actual system. In this paper, a new Kalman filter is used to estimate the parameters, which is an adaptive filter, so it does not need the accurate statistics of the noises of the measurements. To develop the adaptive Kalman filter, the filter model is constructed, firstly.

1) Filter model

The filter model on the z-axis is given as:

where, Bzdenotes the third line of the parameter matrix,denotes the z-axis element of thewhich can be obtained by equation (5), and σzis the random noise.

2) Adaptive Kalman filter

Adopting to the filter model, the adaptive Kalman filter for parameter identification can be described as:

where, i=x,y,z, ei,kdenotes the i-axis residual error, and Λi,k+1is the i-axis adaptive parameter.

3.3 Reconstruction algorithm

With the adaptive Kalman filter, the parameter matrix B can be obtained accurately over the alignment time, then the new apparent velocity can be obtained by equation (11). To avoid the collinearity ofthe dual-vector, the traditional method needs to prolong the alignment time, because the interval of t1and t2is the decisive factor. To overcome the flaws of the traditional method, with the equation (11), the reconstructed dualvector can be obtained as:

where, t1is always the initial time, so compared with the traditional method where t1is equal to t2/2, the new method has longer interval, and it can avoid the collinear problems effectively.

4 Test results

In order to validate the effectiveness of the coarse alignment method presented in this paper. The simulation and the turntable tests were carried out, and the comparative results with the existing method are given in the next subsection.

4.1 Simulation test

In order to analyze the real alignment results, we design the swaying alignment test to simulate the static ship. The swaying parameters are listed in Tab.1, the inertial sensors parameters are shown in Tab.2, and the initial values of the adaptive Kalman filter are listed in Tab.3.

In the simulation test, the update frequency for sensor outputs and alignment solution are both set as 200 Hz, while the statistic frequency for the alignment errors is 2 Hz. After the simulation of 600 s, the apparent velocity errors and the alignment errors are shown in Fig.1 and Fig.2, respectively, and the statistic results are listed in Tab.4.

Tab.1 Setting of swinging parameters

Tab.2 Setting of sensor errors

Tab.3 Initial value of adaptive Kalman filter

In Fig.1, the random noises of the apparent velocity are smoothed, with the advantages of the adaptive Kalman filter, the apparent velocity can be obtained accurately, which determines the alignment precision by equation (9). In Fig.2, the alignment errors show that the proposed method obtains the more smoothed results, and the random noises still influence the results of the traditional dual-vector coarse alignment, it also can be founded that the RLS method gives the sub-optimal alignment results. As can be seen in Tab.4, the errors of pitch and roll are close by comparing with the three methods. However, the yaw alignment errors are smaller than the existing method, and with the standard deviations, the proposed method is smaller than the others in the same instant time of the whole alignment. This means the proposed method has more effective performance in yaw alignment errors, and the convergence rate is faster.

Fig.1 Errors of apparent velocities

Fig.2 Curves of alignment errors

Tab.4 Statistics of alignment errors (°)

4.2 Turntable test

The turntable test is carried out to confirm the proposed methods in the real-time initial alignment. The swaying parameters is set the same as the simulation test (see Tab.1), and the IMU is installed as Fig.3

Fig.3 Turntable and IMU

The alignment results and the statistical information of the alignment errors are shown in Fig.4 and Tab.5, respectively.

In Fig.4, we can find out that there is oscillation in the alignment errors, which matches the real results, and the alignment precision in pitch and roll is close. However, the proposed method has higher performance in yaw.

As amplified figure in Fig.4 and the statistics in Tab.5, the improved Kalman filter method has more smooth results in alignment errors. During the whole alignment process, the means of pitch and roll errors are very close, while the standard deviations of the improved Kalman filter method are slightly smaller than the traditional dual-vector and RLS method. In addition, the means of yaw of the improved Kalman filter method are approximately close to the RLS method, but the deviations of the proposed method are greatly smaller than the other two methods.

Fig.4 Alignment errors in turntable test

Thus, the conclusion can be obtained: the proposed alignment method with parameter identification and reconstruction can increase alignment accuracy without adding alignment time.

Tab.5 Statistic of alignment errors in turntable test (°)

5 Conclusion

In this paper, a new dual-vector coarse alignment method based on the apparent velocity has been proposed, which adopts the adaptive Kalman filter for parameter identification, and use the effective reconstructed dual-vector to eliminate the two problems in the traditional dual-vector coarse alignment.

Simulation and turntable tests are designed in this thesis, the results indicates that compared with the existing method, the adaptive Kalman filter method has higher performance of the coarse alignment, it mainly shows in alignment accuracy and convergence rate.

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基于參數識別視速度的雙矢量粗對準方法

孟翔飛，李 鑫
（常熟理工學院 電氣與自動化工程學院，常熟 215500）

針對傳統基于視速度雙矢量粗對準中，由于傳感器隨機噪聲的影響，存在對準精度差，收斂速度慢的缺點，提出了一種新型自適應 Kalman濾波的參數識別粗對準方法。該方法通過對視速度運動進行建模，設計采用自適應Kalman濾波對模型參數進行參數識別，從而有效地消除視運動中的隨機噪聲，提高粗對準的精度和收斂速度。由于自適應濾波的特點，新方法不需要對傳感器誤差進行統計，使其在實際系統中具有更加廣泛的應用價值。針對雙矢量粗對準的計算特點，設計了一種矢量重構算法，從而盡可能地規避雙矢量共線性問題，加快了粗對準的收斂過程。仿真與轉臺實驗表明，與傳統方法對比，新方法在相同的對準時間內具有更高的對準精度，在相同的對準精度下，具有更高的收斂速度。轉臺實驗的最終對準精度為-0.1391°，標準差為0.012°。

捷聯慣導系統；粗對準；改良Kalman濾波；參數辨識；雙矢量姿態確定

U666.1

：A

2016-09-02；

：2016-11-20

江蘇省產學研聯合創新資金（BY2014075）；江蘇高校品牌專業建設工程資助項目（PPZY2015C215）

孟翔飛（1977—），男，副教授，博士，從事導航定位研究。E-mail: mxf0316@163.com

1005-6734(2016)06-0730-06

10.13695/j.cnki.12-1222/o3.2016.06.006