Parameter Identification Method for SINS Initial Alignment under Inertial Frame
The performance of a strapdown inertial navigation system (SINS) largely depends on the accuracy and rapidness of the initial alignment. The conventional alignment method with parameter identification has been already applied widely, but it needs to calculate the gyroscope drifts through two-position method; then the time of initial alignment is greatly prolonged. For this issue, a novel self-alignment algorithm by parameter identification method under inertial frame for SINS is proposed in this paper. Firstly, this coarse alignment method using the gravity in the inertial frame as a reference is discussed to overcome the limit of dynamic disturbance on a rocking base and fulfill the requirement for the fine alignment. Secondly, the fine alignment method by parameter identification under inertial frame is formulated. The theoretical analysis results show that the fine alignment model is fully self-aligned with no external reference information and the gyrodrifts can be estimated in real time. The simulation results demonstrate that the proposed method can achieve rapid and highly accurate initial alignment for SINS.
Strapdown inertial navigation system (SINS) has been widely used in aviation, marine, and land vehicle navigation and positioning because of its special advantages, and it necessitates an alignment stage to determine the initial conditions prior to navigation operation . Compared with the initial attitude, initial velocity and position can be easily acquired with reference navigation system, such as Global Position System (GPS) . Thus, the accuracy and stability of initial alignment are critical for high performance SINS [3, 4], and the purpose of initial alignment is to obtain an initial attitude matrix from body frame to navigation frame and set the misalignments to zero. The traditional initial alignment is often divided into two procedures: coarse alignment and fine alignment [5–7]. The coarse alignment is used to resolve large misalignment angle rapidly, and then the fine alignment is used to compensate and correct the misalignment angle further .
A lot of literature has been devoted to coarse alignment methods. The conventional coarse alignment is based on analytical method which generally uses two feature vectors of the earth: the acceleration of gravity and the angular rate of the earth’s rotation, and it asks for the base in a static case [9, 10]. However, in many cases, the process of the alignment is affected by various interference factors of the base, such as engine vibration, crew motion, and strong flurry. Because the intensity of the interference signal is obviously larger than the angular rate of the earth’s rotation, the earth rotation rate is completely submerged in measurement noise. So the conventional coarse alignment method cannot be utilized. In order to solve the alignment problem on a rocking base, the method is to use the inertial frame as a transitional coordinate to realize the initial alignment by using the gravity acceleration information [11–14].
In the fine alignment procedure, gyrocompass alignment, Kalman filter, and parameter identification method are the mostly used techniques to deal with alignment problems in SINS [15–17]. Gyrocompass alignment based on compass effect is an important fine alignment method with the properties of interference suppression and lower computational complexity [18, 19], but it needs to set longer damping time constant and always costs much more time to finish the alignment process [20, 21]. Kalman filter is an optimal linear estimator when measurement noise has a Gaussian distribution with known measurement and process noise variance values [8, 22–25]. However, it is impractical that measurement noise has a Gaussian distribution with known measurement and process noise variance values, and it is very sensitive to the rocking interference and has the disadvantage of large amount of calculation . Parameter identification method based on recursive least square method (RLS) is a very useful fine alignment method, which does not need to know the distribution of measurement noise and has the characteristics of small computational amount [17, 20, 26]. However, all of them need to calculate the gyroscope drifts through two-position method; then the time of initial alignment is greatly prolonged.
Inspired by the idea in , a novel self-alignment algorithm by parameter identification method under inertial frame for SINS is proposed in this paper, and simulation test verifies the effectiveness of the proposed method. Firstly, similar to [8, 27], utilizing the gravity in the inertial frame as a reference, the coarse alignment method is discussed to overcome the limit of dynamic disturbance on a rocking base. Secondly, the fine alignment model by parameter identification method in the inertial frame is developed, and the theoretical analysis results show that the proposed fine alignment model is fully self-aligned with no external reference information and the gyrodrifts can be estimated in real time.
The rest of this paper is organized as follows. Section 2 introduces the fundamental principles of coarse alignment method using the gravity information in the inertial frame. The fine alignment method by parameter identification under inertial frame is formulated in Section 3. In Section 4, the validity of the proposed method is further verified by simulation. Finally, some conclusions are made in Section 5.
2. Coarse Alignment Method by Using the Gravity Information in the Inertial Frame
2.1. Coordinate Frame Definitions
In order to better understand SINS initial alignment, it is necessary to explain the navigation coordinate system, that is, the earth frame ( frame), the inertial frame ( frame), the computed inertial frame ( frame), the navigation frame ( frame), and the body frame ( frame), together with the body inertial frame ( frame), which will be introduced in the sequel, and the relationship among the various frames is denoted in Figure 1, where is the angular rate of the earth’s rotation, is the local gravity acceleration, and is the time for alignment. And the various frames are defined in detail as follows.
(i) Frame. The earth’s core is the origin and axis points to the intersection of the prime meridian and the equator. axis goes upward along earth polar axis. , , and form a right-hand coordinate frame. frame moves with the earth in angular rate .
(ii) Frame. It is the ideal inertial coordinate frame; at the starting time for the initial alignment, frame coincides with frame and is fixed in the inertial space.
(iii) Frame. It is the computed inertial coordinate frame where there is some error between frame and frame owing to the alignment error and the sensor error.
(iv) Frame. The origin is the centroid of the carrier. axis goes upward along the local geodetic vertical and axis north (and horizontal) with axis east (and horizontal).
(v) Frame. The origin is the centroid of the carrier. axis shifts rightward along the carrier’s transverse axis, forward along the longitudinal axis, and upward along the vertical axis.
(vi) Frame. At the starting time for the initial alignment, frame coincides with frame and is fixed in the inertial space.
2.2. The Coarse Alignment Algorithm in the Inertial Frame
The basic idea using the gravity acceleration information in the inertial frame for the initial alignment is to decompose into several attitude matrices, whose references are all based on the inertial frame [8, 12, 27]. The decomposition method in this paper is as follows:
It shows that time-varying matrix is composed of three parts. One part is , which is the transformation matrix between frame (geographic coordinate frame) and frame. And it is produced by the earth rotation rate:where is the starting time for the alignment, is the time for alignment, and is the latitude.
Another part is , which is the transformation matrix between frame and frame. It can be obtained by the output signal of the gyroscopes at any time:where and denotes the skew-symmetric matrix of which is measured by the gyroscopes in frame.
Therefore, the mission of the coarse alignment is transformed into the estimation problem of which is the transformation matrix between frame and frame, and it is a constant value. Owning towhere denotes the specific force measured by accelerometers in frame, is the gravity vector in frame.
Ignoring the influence of the installation error, accelerometer drift, and the disturbing acceleration, the relationship of and is
Selecting different times and , can be presented aswhere hat “” denotes the calculated value. To improve the measurement accuracy on a rocking base, it can be integrated from (5) thatwhere and are already expressed in  aswhere and are the first and second samples of the accelerometer-measured incremental velocity and and are the first and second samples of the gyroscope-measured incremental angle, respectively, so thatThis is the practical equation for the coarse alignment.
3. Fine Alignment by Parameter Identification under Inertial frame
The coarse initial attitude angle can be obtained by the coarse alignment method in Section 2. The carrier heading angle error is estimated to be within a few degrees and pitch/roll angle to be within a few tenths of a degree. In this section, the fine alignment by parameter identification in inertial frame is developed.
3.1. Analysis of the Attitude Misalignment Angles in the Inertial Frame
Note that there is a big calculation error between estimation value and true value , and calculated by the outputs of gyroscopes also exists error. Therefore, we havewhere , and which is the transformation matrix from ideal inertial coordinate frame ( frame) to erroneously computed inertial coordinate frame ( frame) can be formulated aswhere is the misalignment angle vector in frame. The subscripts , , are the three axes of frame, respectively. And the task of fine alignment is to estimate misalignment angle .
In ideal conditions, the differential equation of iswhere is the transformation matrix between frame and frame. denotes the angular rate of frame with respect to frame, expressed in frame.
In practice, the differential equation of iswhere is the transformation matrix between frame and frame. measured by gyroscopes in frame is the computed value of . And can be formulated aswhere is the gyroscope error vector in frame.
Differentiating on both sides yields
Owing to and , substituting them into (5) and multiplying from right on each part yield
Ignoring the influence of the installation error and scale factor error, (20) can be rewritten aswhere is the bias of gyroscope in frame, and it can be approximately regarded as a random constant vector in the process of alignment. And this is the attitude error equation in frame.
When the carrier shakes modestly, can be nearly a constant matrix, so can be approximately regarded as a random constant vector named as gyroscope’s equivalent constant drift in frame; that is,where subscripts , , are the three axes of frame, respectively.
The alignment process is usually performed in a few minutes (not more than ten minutes), so is a very small amount. Then, and can be approximately rewritten as
To this respect, (23) can be rewritten as
Integrating both sides of (24), the misalignment angles changing with the time can be formulated as follows:where is the initial value vector of misalignment angle in frame.
It is easy to see that and are the constant valves; based on them, we can calculate the misalignment angles in real time. In this respect, the fine alignment problem has been transformed into the parameter identification problem for and .
3.2. Estimation of Attitude Misalignment Angles by Parameter Identification Method
On a rocking base, the measured specific force projected from accelerometer in frame can be written as
Ignoring the second-order small amount yieldswhere is the accelerometer bias vector in frame. is uncertainty measurement disturbance caused by the carrier’s rocking and swaying in frame. , , are the three components of the gravity vector in frame, respectively. , , are the three components of the accelerometer bias in frame, respectively. According to the time for alignment, and can be calculated, respectively, as follows:where , , are the three components of the accelerometer equivalent bias in frame, respectively. Because is a small amount, substituting (22) into (28) and (29) yields
In order to eliminate the alternating specific force interference caused by shaking and improve the measurement accuracy on a rocking base, integrating (32) on both sides yields
From (33), it can be observed that initial misalignment angle can be directly estimated according to the first-order terms of and , and and can be obtained by the quadratic terms of and , respectively, so the convergence speed of is faster than the convergence speed of and . , , and can be estimated according to the third-order terms of , , and ; because cubic curve only exhibits a linear characteristic in a short time, the convergence speed of the three initial misalignment angles is faster than the convergence speed of the three gyroscope’s equivalent constant drifts. Therefore, the alignment time with drift measurement and alignment accuracy cannot be taken into account, and alignment time cannot be shortened infinitely.
The discrete form of (33) can be formulated aswhere is the interval of the SINS update which is rather small and denotes th time-step and
Because the time of alignment is very short, can be nearly a constant value and (34) is the measurement equation, so can be derived from the measured values (i.e., , , and ) by using parameter identification method. DefineThen, the state equation models of , , and can be, respectively, expressed as follows:where .
Given initial guess of state and associate covariance , an adaptive recursive weighted least squares algorithm computes a posteriori estimate , gain matrix , and a posteriori covariance as follows :where is called innovation vector. In general, , , and is a large scalar.
We can find that the measurement noise is not used directly in the above algorithm but merged into . The advantage is that we do not have to know the statistical properties caused by speed disturbance and the gain can be adaptively weighted calculated by the innovation vector. So it will speed up the convergence of the algorithm.
After gaining the estimate value of , substituting them into (35), we have
If the gyroscope’s equivalent east constant drift (i.e., ) is not measured, , , and can be, respectively, expressed as follows:And the calculation errors of misalignment angles are formulated as follows:
After gaining initial misalignment angles , , and , substituting them into (25), we can obtain the misalignment angles in real time. Then, complete the initial alignment according to (11), and the gyrodrifts can be calculated as follows:where is transformation matrix from frame to frame and .
4. Simulation and Analysis
The parameters of the simulation are set as follows.
The carrier is rocked by the wind. Pitch , roll , and heading resulting from the carrier rocking are changed periodically and can be described as follows:
The velocity caused by surge, sway, and heave is as follows:where subscript , , are the three axes of frame, respectively. m, m, and m. s, s, and s. obeys the uniform distribution on interval .
The inertial measurement unit (IMU) is composed of medium precision sensors and the errors are set as follows: the gyroconstant drift is 0.01°/h; the gyrorandom noise is 0.01°/h; the accelerator bias is 1 × 10−4 g; and the accelerator measurement noise is 1 × 10−4 g. SINS location is as follows: north latitude is 40° and east longitude is 118°.
Simulation 1. The coarse alignment lasts 120 s. The values of and in (10) are set to 60 s and 120 s, respectively. The simulation for the coarse alignment runs 50 times. The pitch, roll, and heading errors at the end of the coarse alignments are shown in Figure 2 and the statistics for coarse alignment simulation result are shown in Table 1.
From Figure 2 and Table 1, it is obvious that the level attitude errors of the coarse alignment are less than 0.4 degrees and the heading attitude error is less than 1.5 degrees. The attitude errors calculated by the proposed coarse alignment algorithm can fulfill the requirement for the fine alignment. Next, the maximum of misalignment angles in Table 1 is used as input for fine alignment to validate the proposed parameter identification under inertial frame in Simulation 2.
Simulation 2. The simulation for fine alignment by parameter identification under inertial frame lasts 600 s and runs 6 times. The statistics for fine alignment simulation result are shown in Table 2 and the estimate errors of misalignment angles (one of them) are shown in Figure 3.
According to Figure 3 and Table 2, it is clear that converges almost instantaneously with a high-precision (better than 0.5 arcmin). Specifically, and take longer time than to converge; they stabilize at 2 arcmin in 200 seconds and the results confirm the former analysis in Section 3.2.
Simulation 3. In this simulation, the gyrodrifts are estimated in real time and the simulation lasts for 1500 s. The simulation results are shown in Figure 4. The simulation results demonstrate that all the three gyrodrifts are observable and they converge with good results at the time of 300 s.
The accuracy and applicability of SINS largely depended on the precision and swiftness of the alignment. This paper proposed a novel self-alignment algorithm by parameter identification under inertial frame for SINS. Firstly, the coarse alignment method by using the gravity information in the inertial frame is introduced. Secondly, the fine alignment method by parameter identification under inertial frame is formulated. The theoretical analysis results show that the fine alignment model is fully self-aligned with no external reference information and the gyrodrifts can be estimated in real time. Simulation results proved the accuracy and validity of the proposed method for SINS self-alignment, and the estimation results of the misalignment angles and gyrodrifts can approach the theoretical analysis results.
The authors declare that there are no competing interests regarding the publication of this paper.
This work was supported by the National Natural Science Foundation of China under Grant 41174162.
X. X. Liu, Y. Zhao, X. J. Liu, Y. Yang, Q. Song, and Z. P. Liu, “An improved self-alignment method for strapdown inertial navigation system based on gravitational apparent motion and dual-vector,” Review of Scientific Instruments, vol. 85, no. 12, Article ID 125108, 2014.View at: Publisher Site | Google Scholar
F. Sun, Q. Sun, Y. Y. Ben, Y. Zhang, and G. Wei, “A new method of initial alignment and self-calibration based on dual-axis rotating strapdown inertial navigation system,” IEEE Transactions on Aerospace and Electronic Systems, vol. 48, no. 29, pp. 1323–1328, 2012.View at: Google Scholar
L. Schimelevich and R. Naor, “New approach to coarse alignment,” in Proceedings of the IEEE Position Location and Navigation Symposium (PLANS '96), pp. 324–327, Atlanta, Ga, USA, April 1996.View at: Google Scholar
S. V. Vidya, S. Brajnish, and B. R. Kumar, “Novel method for coarse alignment of strapdown INS on oscillatory base,” Journal of Aerospace Science & Technologies, vol. 61, no. 1, pp. 194–200, 2009.View at: Google Scholar
Y. Y. Qin, “Parameters identification method of the alignment of a Strapdown Inertial Navigation System,” Journal of Chinese Inertial Technology, vol. 2, pp. 1–16, 1990.View at: Google Scholar
G.-M. Yan, J. Weng, C.-S. Zhao, and Y.-Y. Qin, “Improved parameter identification method for SINS initial alignment,” Journal of Chinese Inertial Technology, vol. 18, no. 5, pp. 523–584, 2010.View at: Google Scholar
C. S. Zhao, Y. Y. Qin, and Q. Zhou, “Modified two-position parameters identification alignment method,” Journal of Chinese Inertial Technology, vol. 17, no. 6, pp. 631–635, 2009.View at: Google Scholar