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Jianwei Zhao, Weimin Jia, Rong Wang, Zhixiang Yan, "Attitude Estimation Based on the Spherical Simplex Transformation Modified Unscented Kalman Filter", Mathematical Problems in Engineering, vol. 2014, Article ID 925914, 9 pages, 2014. https://doi.org/10.1155/2014/925914
Attitude Estimation Based on the Spherical Simplex Transformation Modified Unscented Kalman Filter
Abstract
An antenna attitude estimation algorithm is proposed to improve the antenna pointing accuracy for the satellite communication onthemove. The extrapolated angular acceleration is adopted to improve the performance of the time response. The states of the system are modified according to the modification rules. The spherical simplex transformation unscented Kalman filter is used to improve the precision of the estimated attitude and decrease the calculation of the unscented Kalman filter. The experiment results show that the proposed algorithm can improve the instantaneity of the estimated attitude and the precision of the antenna pointing, which meets the requirement of the antenna pointing.
1. Introduction
The great demand for the broadband mobile communication has inspired the development of the satcom onthemove (SOTM) in recent years. SOTM is a mobile communication system based on the fixedsatellite service. SOTM can provide realtime battlefield information. It enables the commander to execute the command effectively, while the soldiers are far from the command post [1]. Except for the military applications, SOTM is also widely used in the security emergency communications and communication support for major events. SOTM has become a hot field all over the world. Measurement and control system is the core aspect of the system to ensure the normal communication and set up a successful satellite link. When the carrier of the mobile satellite communication is affected by the outside interference factors, measurement and control system guarantees that the beam of the satellite antenna points to the satellite [2]. The length of the control time determines the performance of the SOTM. However, adequate time is necessary for the acquisition and the transmission of the signal from the sensors and extra time is needed to correct the pointing error of the antenna. What is worse is that the outside factors such as the environment of the driven route and the great mobility of the carrier do great harm to the attitude estimation, which also causes time lag for the control. As a result, commands cannot be transmitted in time, and the error cannot be compensated for highly dynamic perturbations at the right time.
The attitude estimation is related to the motion state of the carrier and the estimated angles are easily affected by the outside factors. In [3], an adaptive filter is proposed to improve the precision of the estimation. The maneuvering acceleration of the carrier is estimated and corrected to improve the performance of the attitude estimation. However, the adaptive filter based on the covariance matching is a crude method for precise attitude estimation in nature. Therefore, the performance is poor in situation of highly dynamic perturbations for the reason that the windowed innovation sequences cannot catch the carrier dynamics exactly. In [4], an adaptive switch method is adopted to deal with the external acceleration. The attitudes are got by integrating the output of the gyros. The vehicle acceleration is detected by the switch rules. However, it is not sufficient to be suitable for the various dynamics of the carrier and the accuracy of the estimation is restricted. Reference [5] presents a lowcost attitude estimation algorithm based on the GPS/INS integration; the precision of the attitude is improved by the assistance of the GPSmeasured course angle and the cascaded Kalman filter. But the cascaded Kalman filter increases the calculation of the system. The instantaneity of the algorithm is worse under the condition of strong maneuvering. Many previous works have been done to improve the precision of the attitude [6–8]. Reference [8] proposes a novel degradation to predict the drift errors of the inertial navigation system. The degrading trend of the drift errors can be predicted in realtime, which improves the precision of the estimated states. However, they all ignored the instantaneity and antijamming capability under strong maneuvering situation.
An attitude estimation based on the spherical simplex transformation modified UKF was presented to improve the performance of the SOTM to ensure the antenna pointing to the satellite precisely. The realtime character of the system had been improved by adding the extrapolated angle accelerator to the states of the system. The angle rates of gyroscope could be evaluated precisely. In addition, the rules for the judgment of the motion state increased the antijamming capacity of the system. Strong maneuvering situation could be detected by the setting rules. The predicted covariance was corrected by the weighting function automatically. It overcomes the shortcoming of the traditional Kalman filter, whose covariance cannot be synchronized with the change of target state [9]. What is more, the spherical simplex transformation UKF not only improved the precision of the attitude estimation, but also decreased the calculation of the system [10]. As a result, the proposed attitude estimation system was validated through field tests.
The paper is organized as follows. In Section 2, we present some preliminaries of the antenna attitude estimation system for SOTM. In Section 3, we elaborate the proposed algorithm in detail. The effectiveness of the proposed attitude estimation system is validated through field tests in Section 4. Finally, the paper is concluded in Section 5.
2. Preliminaries
This section offers basic knowledge for the attitude estimation, such as the definition of the reference frames, attitude representation methods, and the algorithms used in this paper.
2.1. Reference Frames and System Configuration
Reference frames are the foundation of the attitude measurement system (Figure 1). The frames related to attitude estimation are defined as follows.
The local geodetic coordinate frame: it is called the northeastdown frame, denoted by the frame. The vector expressed in the frame is expressed by the superscript . For instance, in this frame is denoted by .
The vehiclefixed coordinate frame: it is also called the body coordinate frame (frame), which is associated with the vehicle and aligned with its forward, right, and upward axes. The vector expressed in the frame is expressed by the superscript . For instance, in this frame is denoted by .
The beam coordinate frame: its axis points to the target satellite. is defined as a vector expressed in frame.
Given the longitude and latitude of the local earth station and the longitude of the synchronous orbiting satellite, we can get the azimuth (), elevation (), and polarization () angles, which are used to give a reference for the antenna beam pointing to the satellite. The formulas are as follows: where is the radius of the earth and is the elevation of the local area.
2.2. Attitude Representation
Several attitude representations can be used for vehicle kinematics, such as quaternion, Euler angles, and modified Rodrigues [11]. The representation of Euler angles is the minimal representation that has no redundancy. Therefore, Euler angles are adopted to parameterize the representation of the threedimensional attitude . The transformation from one frame to another can be realized through three continuous rotations [12]. Each rotation can be represented by one direction cosine matrix. The transformation from the local geodetic coordinate frame to the vehiclefixed coordinate frame can be represented by the following three matrixes:
The transformation matrix can be derived by the product of the anterior matrix We can get the transformation matrix as follows: where the notations and represent cosine and sine, respectively.
The relationship between the euler angles rates and the measurements of the gyroscope is described as follows [13]: where , , and are the outputs of three gyros.
2.2.1. Unscented Kalman Filter
For the reason that trigonometric functions are involved in the Euler angle attitude representation, the extended Kalman filter (EKF) is not in point for its big lineation error. Whereas the unscented Kalman filter is a nonlinear filter that can obtain the estimation to at least second order [14], the expected error is much lower than the EKF. In addition, UKF needs not to calculate the Jacobian matrix used in the EKF, even though the calculation is still larger than the EKF. Now many researches are done to reduce the calculation of the UKF.
The nonlinear system model can be given by [15] where is the state vector of the nonlinear system and is the measurement vector. is the state propagation equation and is the measurement propagation equation. The process noise and the measurement noise are zeromean Gaussian noise processes with covariances and , respectively. UKF is briefly presented here. The UKF is performed as follows.(1)Initialization of the states vector and the convenience (2)Choosing of the sampling sigma points (3)Time update where and is the corresponding weight calculated by the unscented transformation (UT) theory.(4)Measurement update where
Because SOTM is a realtime system, the calculation is one of the keys to ensure the normal operation. Measures must be taken to ensure the precision and the realtime of the system.
3. The Proposed Attitude Estimation Algorithm
Methods to improve the performance of the attitude estimation are presented in this section: model built based on the addition of the angle acceleration; the states modification and its realization; the proposed UKF algorithm.
3.1. Modeling of the Attitude Estimation System
The traditional attitude estimation uses inertial measurement units with high precision as the sensors. As the angle acceleration has no direct observation, only angle and angle rates are chosen as the states of the system. The estimated errors cannot be ignored for lacking the observation of the angular acceleration. The estimation of the system states may suffer from impact and the response is likely with step response, as is shown in Figure 2.
Ignoring the impact of the time lag caused by the signal transmission and processing, the main limiters to the attitude estimation are the sampling rate. In the interval, the disturbance cannot be sensed in time and the caused error cannot be corrected at the same time. The antijamming ability of the system is weak so the error cannot meet the requirements of beam pointing in the situation of strong maneuvering. Therefore, the extrapolated angle acceleration is proposed to be added to the system states.
The system states become ; , , and are the angles, angle rates, and the angle accelerations, respectively.
The observations of the extrapolated angle acceleration can be obtained by the difference between the adjacent measurements of the angle rates, as follows: where is the sampling time interval.
The system equation is where is the coefficient matrix, with the following form:
It is obvious that the system equation is nonlinear. As the measurements are the attitude, angle rates, and angle accelerations, the measurement equation is
The advantage of using extrapolated angular acceleration is that it is immune to the estimated states at the previous time. Additionally, it can also reflect the real states of the carrier.
3.2. The States Modification Rules
An algorithm based on the states modification is suggested to improve the antijamming ability of the SOTM in this section.
3.2.1. The States Modification Rules
In order to sense the attitude changes in time, the following three rules are set. They determine whether the estimated value of the attitude angle is to be compensated or not.
(a) The gyro outputs of the yaw axis, pitch axis, and roll axis are used to determine whether there is sudden disturbance. The disturbance judgment rule is as follows: where , , and are the biases drift of the outputs of the angle rates. , , and are the thresholds used to detect the disturbance.
The first rule means that when any angle rate of the threeaxis gyro output exceeds the threshold value, it is necessary to compensate for the predicted value of the state.
(b) The adjacent yaw angle changes are adopted to determine whether there is a sudden turn. The rule can be expressed by the following style: where means the error of the adjacent yaw angles. is the threshold used for the turn detection.
The second rule means that the states modification can be determined by the adjacent yaw angle. When the error between the adjacent yaw angles is larger than the threshold, measures should be taken to modify the estimated states.
(c) The location information of the carrier is used to detect the sudden disturbance. The rule is given as follows: where means measurement yaw angle; it can be obtained by the location information of the carrier. It is different from rule (b) that may still suffer from time lag in fact, as the estimated angle is still slower than the practical value in response. In order to overcome the time lag, the location information can be used to detect the sudden disturbance. is the threshold used for the turn detection which can be got from the empirical value of the dynamic carrier test and the product manual. The principle is shown in Figure 3.
The aiming yaw angle is derived from the error between the estimated location in time and the measurement location of the GPS in time . The known yaw angle is derived from the location in time and in time . When the error between the two yaw angles is small which can be ignored, it means there is no disturbance. On the other hand, a large error means there is a large disturbance. Therefore, the choice of plays an important role in the attitude estimation. If is larger than the practical one, the turn detection may be inefficient. If is smaller than the practical one, the turn detection may be too sensitive which causes the wrong justification.
3.2.2. The States Modification
Based on the proposed rules, the weighting factor can be chosen to realize the algorithm based on the prediction filter.
The can be determined by
The can be determined by
The can be determined by where is uniformly distributed in the interval .
When mutation of the carrier occurs, increases at the same time. Therefore, can be considered as input variables. The Gaussian function with the centers 0 and can be used as the weighting function of the algorithm. The weights of the previous yaw angle and the realtime measured yaw angle could be determined adaptively according to the changes of .
The expression of the weighting function is where and are the center value and the standard deviation of the Gaussian function, respectively. When the center value of the Gaussian function is zero, it means the carrier has no sudden disturbance. When the central value of the Gaussian function is , itmeans that the carrier has strong maneuvering.
The extrapolated angular acceleration can be expressed by where is the extrapolated angular acceleration, is the measured value of the threedimensional attitude angle, is the estimated values for the last time, and is sampling interval of the sensor.
As the angular acceleration is based on the measurement dates, it is easily affected by the measurement noise. Under conditions of weak maneuver, the algorithm has good stability and the accuracy meets the actual communication needs. In order to ensure the predicted value of the angular acceleration to have both good stability and realtime ability during the strong maneuver, the predicted angular acceleration is modified by the extrapolation angular acceleration according to the carrier’s Kinematics equation. The expression is given by where is the predicted value of the angular acceleration.
The predicted value of the angular rates can be obtained by the previous predicted value and the predicted angular acceleration:
By improving the model and algorithm, the onestep prediction states value can be modified according to the states modification roles automatically. The onestep states can be obtained by where is the onestep prediction state from Kalman filter and is the measurement prediction state value.
In conclusion, when the carrier moves normally, we can get , . In fact, it is similar to the traditional algorithm. When the carrier moves with strong maneuver, and . In this situation, the precision of the attitude estimation is improved by the modification. The final estimated value of the attitude is
3.3. The Spherical Simplex Transformation Prediction UKF
The calculation of UKF is related to the number of sigma points. More sigma points mean more computation. For the dimensional state vector, the standard UKF adopts symmetric sampling strategy; sigma points are needed to approximate the states’ probability distribution [16]. In order to decrease the computation of the UKF, symmetric sampling is replaced by super spherical sampling. The distance between the sigma points and the center point is the same, and the weight is also the same. sampling points are needed to describe its mean and variance. Adding the mean value of the states, the total number of the super spherical sampling UKF is , and the computation decreases obviously. The algorithm is as follows:(1)choose ,(2)making sure of the weight of (3)scale correction where is the scaling factor that can control the distance between the sampling points and the mean value of the sigma points,(4)initialization of the vector sequence (5)for the dimension of the input , the iteration formula is where is the dimension of the vector and is the sequence of the sampling points,(6)for any of the means and covariance, sigma can be obtained by the following formula: where is the square root of the covariance matrix by Cholesky decomposition.
The process of the proposed algorithm is shown in Figure 4. MEMS sensor such as gyro and accelerometer and GPS are integrated to give the initial output of the attitude and the angle rates, and then the modification rules are used for the justification on the states of the carrier. The symmetric sampling transformation prediction UKF is adopted eventually to improve the performance of the estimation.
4. Experimental Validation and Discussions
In order to verify the performance of the proposed algorithm, the experimental platform was constructed. It consists of outdoor and indoor parts. The outdoor part is composed of a high precision attitude and heading reference system XWADU7612, a lowcost miniature inertial measurement unit XWIMU5220, and a single baseline GPS XWADU3601. Attitude can be acquired by fusing the output of the XWIMU5220 and XWADU3601. The reference system XWADU7612 can provide the attitude to an accuracy of 0.1° (in dynamic and baseline >2 m) for comparison. The algorithm is running in a DSP processor with the frequency 400 MHz in realtime in the indoor parts. The experimental carrier and equipment are shown in Figure 5.
The experiment was conducted in a country road. The route of the mobile satellite communication earth station carrier can be seen from Figure 6. It is suitable for validating the performance of the algorithm for some strong maneuvers intervals. The thresholds , , and in the disturbance judgment rule from gyros are all set to be 0.01 rad/s. The adjacent yaw angle change is set to be 1.5 rad. The parameter to detect the sudden disturbance in the location information of the carrier is set to be 1.5 rad.
The attitude estimated by the integration of XWIMU5220 and XWADU3601 using EKF could be seen from Figures 7 and 8. Accurate estimation of the attitude could be got when the carrier moved in a straight line uniformly. The errors of the estimated attitude were all with 0.5° that met the requirement for the mobile satellite communication. However, the errors were increasing when the carrier made a sharp turn, such as in the intervals 14.3 s–27.6 s, 50 s–65 s, and 80 s–110 s. The estimated attitudes value had large error due to the strong maneuvering. The maximum error of the yaw angle was beyond 300° in short time. The error of the pitch angle and the roll angle was within 3° that could not meet the basic requirement of the satellite communication. In order to improve the precision of the attitude estimation, modification must be taken to decrease the effect of the sudden disturbance.
In order to overcome the problem, the extrapolated angular acceleration was adopted to improve the performance of the time response. The states of the system were modified according to the modification rules. The results of the algorithm are shown from Figures 9, 10, and 11.
After the modification, it was obvious that the precision of the attitude estimation had been improved; the error of the pitch angle and the roll angle was within 0.5°, which met the requirement of the antenna pointing. However the error of the yaw angle was still beyond 0.5° in time interval 80 s–110 s. So UKF was proposed to improve the precision. However, the execution time was so long that it could not meet the realtime character of the SOTM. Spherical simplex transformation UKF was adopted to improve the precision of the attitude and to decrease the calculation of the realization of the SOTM. As can be seen from Figure 12, the errors of attitude are within 0.5° that meets the requirement of the antenna pointing.
In order to verify the efficiency of the algorithm, the RMSE and the execution time were listed in Table 1. It is obvious that the RMSE of the suggested MUKF was better than other algorithms. Besides, the execution time was 3.34, which was comparable with MEKF. So the suggested algorithm has a desirable precision and moderate execution time which is suitable for the application of SOTM.

5. Conclusion
An attitude estimation algorithm based on the spherical simplex transformation modified UKF is proposed to estimate the attitudes of the vehicle and keep the antenna pointing to the satellite precisely. The extrapolated angle accelerator improves the realtime character of the system. Besides, the antijamming capacity of the system has been increased for the rules for the judgment of the motion state.
The test results demonstrate that the performance of attitude estimation was improved by the state modification and spherical simplex transformation UKF. The errors of the estimated attitudes were within 0.5° and the least RMSE were all less than 0.47. Besides, the execution time of the suggested algorithm was comparable with EKF. Compared with UKF, the spherical simplex transformation had greatly decreased the executing time. The proposed attitude estimation system is validated through field test that meets the requirement of the antenna pointing. The algorithm has a good application prospect which will greatly accelerate the development of the SOTM.
Conflict of Interests
The authors declare that there is no conflict of interests regarding the publication of this paper.
Acknowledgments
The authors would like to show thanks to their colleagues in the SOTM Laboratory for their help in conducting these tests. The authors acknowledge the anonymous reviewers for their valuable suggestions and comments.
References
 C. Ozbay, W. Teter, D. He, M. J. Sherman, G. L. Schneider, and J. A. Benjamin, “Design and implementation challenges in KA/KU dualband satcomonthemove terminals for military applications,” in Proceedings of the Military Communications Conference (MILCOM '06), Washington, DC,USA, October 2006. View at: Publisher Site  Google Scholar
 D. M. Bevly, J. Ryu, and J. C. Gerdes, “Integrating INS sensors with GPS measurements for continuous estimation of vehicle sideslip, roll, and tire cornering stiffness,” IEEE Transactions on Intelligent Transportation Systems, vol. 7, no. 4, pp. 483–493, 2006. View at: Publisher Site  Google Scholar
 Y. S. Suh, “Orientation estimation using a quaternionbased indirect Kalman filter with adaptive estimation of external acceleration,” IEEE Transactions on Instrumentation and Measurement, vol. 59, no. 12, pp. 3296–3305, 2010. View at: Publisher Site  Google Scholar
 J. Zhao, W. Jia, M. Yao et al., “Integrated attitude estimation algorithm for mobile satellite communication system,” Journal of Xi’an Jiaotong University, vol. 48, no. 8, pp. 36–41, 2014. View at: Google Scholar
 Z. Wu, M. Yao, H. Ma, and W. Jia, “Improving accuracy of the vehicle attitude estimation for lowcost INS/GPS integration aided by the GPSmeasured course angle,” IEEE Transactions on Intelligent Transportation Systems, vol. 14, no. 2, pp. 553–564, 2013. View at: Publisher Site  Google Scholar
 A. Noureldin, T. B. Karamat, M. D. Eberts, and A. ElShafie, “Performance enhancement of MEMSbased INS/GPS integration for lowcost navigation applications,” IEEE Transactions on Vehicular Technology, vol. 58, no. 3, pp. 1077–1096, 2009. View at: Publisher Site  Google Scholar
 U. Maeder and M. Morari, “Attitude estimation for vehicles with partial inertial measurement,” IEEE Transactions on Vehicular Technology, vol. 60, no. 4, pp. 1496–1504, 2011. View at: Publisher Site  Google Scholar
 W. Zhaoqiang, “A realtime prognostic method for the drift errors in the inertial navigation system by a nonlinear randomcoefficient regression model,” Acta Astronautica, vol. 103, pp. 45–54, 2014. View at: Google Scholar
 S. J. Julier and J. K. Uhlmann, “Unscented filtering and nonlinear estimation,” Proceedings of the IEEE, vol. 92, no. 3, pp. 401–422, 2004. View at: Publisher Site  Google Scholar
 J. L. Crassidis and F. L. Markley, “Unscented filtering for spacecraft attitude estimation,” Journal of Guidance, Control, and Dynamics, vol. 26, no. 4, pp. 536–542, 2003. View at: Publisher Site  Google Scholar
 P. Li, T. Zhang, and B. Ma, “Unscented Kalman filter for visual curve tracking,” Image and Vision Computing, vol. 22, no. 2, pp. 157–164, 2004. View at: Publisher Site  Google Scholar
 E. A. Wan and R. van der Merwe, “The unscented Kalman filter for nonlinear estimation,” in Proceedings of the IEEE Adaptive Systems for Signal Processing, Communications, and Control Symposium (ASSPCC '00), pp. 153–158, Alberta, Canada, October 2000. View at: Publisher Site  Google Scholar
 P. Sándor, “Applying the extended and unscented kalman filters for nonlinear state estimation,” in Proceedings of the InterEng Conference, pp. 233–239, TîrguMureş, Romanian, 2012. View at: Google Scholar
 R. Kandepu, B. Foss, and L. Imsland, “Applying the unscented Kalman filter for nonlinear state estimation,” Journal of Process Control, vol. 18, no. 78, pp. 753–768, 2008. View at: Publisher Site  Google Scholar
 J. L. Crassidis, F. Landis Markley, and Y. Cheng, “Survey of nonlinear attitude estimation methods,” Journal of Guidance, Control, and Dynamics, vol. 30, no. 1, pp. 12–28, 2007. View at: Publisher Site  Google Scholar
 S. J. Julier, “The spherical simplex unscented transformation,” in Proceedings of the American Control Conference, vol. 3, pp. 2430–2434, June 2003. View at: Google Scholar
Copyright
Copyright © 2014 Jianwei Zhao et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.