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Estimation of small uav position and attitude with reliable in-flight initial alignment for MEMS inertial sensors

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Treść / Zawartość
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Warianty tytułu
Języki publikacji
EN
Abstrakty
EN
The advance of MEMS-based inertial sensors successfully expands their applications to small unmanned aerial vehicles (UAV), thus resulting in the challenge of reliable and accurate in-flight alignment for air-borne MEMS-based inertial navigation system (INS). In order to strengthen the rapid response capability for UAVs, this paper proposes a robust in-flight alignment scheme for airborne MEMS-INS aided by global navigation satellite system (GNSS). Aggravated by noisy MEMS sensors and complicated flight dynamics, a rotation-vector-based attitude determination method is devised to tackle the in-flight coarse alignment problem, and the technique of innovation-based robust Kalman filtering is used to handle the adverse impacts of measurement outliers in GNSS solutions. The results of flight test have indicated that the proposed alignment approach can accomplish accurate and reliable in-flight alignment in cases of measurement outliers, which has a significant performance improvement compared with its traditional counterparts.
Słowa kluczowe
Rocznik
Strony
603--616
Opis fizyczny
Bibliogr. 23 poz., fot., rys., tab., wykr., wzory
Twórcy
autor
  • National University of Defense Technology, College of Aerospace Science and Engineering, Changsha, China
autor
  • National University of Defense Technology, College of Aerospace Science and Engineering, Changsha, China
autor
  • National University of Defense Technology, College of Aerospace Science and Engineering, Changsha, China
autor
  • National University of Defense Technology, College of Aerospace Science and Engineering, Changsha, China
autor
  • 61206 PLA Troop, Beijing, China
Bibliografia
  • [1] Bento, M.F. (2008). Unmanned Aerial Vehicles: An Overview. InsideGNSS, 1, 54-61.
  • [2] Schmidt, G.T. (2015). Navigation sensors and systems in GNSS degraded and denied environments. Chinese Journal of Aeronautics, 28, 1-10.
  • [3] Wang, D.J., Chen, L., Wu, J. (2016). Novel In-flight coarse alignment of low-cost Strapdown Inertial Navigation System for Unmanned Aerial Vehicle Applications. Transactions of The Japan Society for Aeronautical and Space Sciences, 59(1), 10-17.
  • [4] Shin, E.H., Naser E.S. (2007). Unscented Kalman Filter and Attitude Errors of Low-Cost Inertial Navigation Systems. Navigation, Journal of the Institute of Navigation, 54(1), 1-9.
  • [5] Han, S.L., Wang, J.L. (2010). A novel initial alignment scheme for low-cost INS aided by GPS for land vehicle applications. The Journal of Navigation, 63(4), 663-680.
  • [6] Groves, P.D. (2008). Principles of GNSS, inertial and multisensor integrated navigation systems . London: Artech House, 407-418.
  • [7] Kong, X. (2004). INS algorithm using quaternion model for low cost IMU. Robotics and Autonomous Systems, 46(4), 221-246.
  • [8] Wang, D.J., Lv H.F., Wu, J. (2017). In-flight Alignment for small UAV MEMS-based navigation via adaptive unscented Kalman filtering approach. Aerospace Science and Technology, 61, 73-84.
  • [9] Wang, D.J., Lv, H.F., Wu, J. (2016). Augmented Cubature Kalman Filter for nonlinear RTK/MIMU Integrated Navigation with non-additive noise. Measurement, 97, 111-125.
  • [10] Rogers, R.M. (1997). IMU In-Motion Alignment without Benefit of Attitude Initialization. Navigation, Journal of the Institute of Navigation, 44(3), 301-311.
  • [11] Wu, M.P., Wu, Y.X., Hu, X.P., Hu, D.W. (2011). Optimization-based alignment for inertial navigation systems: Theory and algorithm. Aerospace Science and Technology, 15(1), 1-17.
  • [12] Wu, Y.X., Pan, X.F. (2013). Velocity/Position Integration Formula Part I: Application to In-Flight Coarse Alignment. IEEE Transactions on Aerospace and Electronic Systems, 49(2), 1006-1023.
  • [13] Ma, L., Wang, K., Shao, M. (2013). Initial alignment on moving base using GPS measurements to construct new vectors. Measurement, 46(8), 2405-2410.
  • [14] Richard, P.K., Hansman R.J., John, D. (1998). Single-antenna GPS-based aircraft attitude determination. Navigation, Journal of the Institute of Navigation, 45(1), 51-60.
  • [15] Wieser, A., Fritz, B.K. (2002). Short static GPS Sessions: robust estimation results. GPS Solution, 76(6), 353-358.
  • [16] Wang, J.L., Wang, J. (2007). Mitigating the effect of multiple outliers on GNSS navigation with M-estimation schemes. Proc. of International Global Navigation Satellite Systems Society Symposium 2007, Sydney, Australia, 1-9.
  • [17] Tong, H.B., Zhang, G.Z. (2014). Robust positioning algorithm with modified M-estimation for multiple outliers. Acta Geodaetica et Cartographica Sinica, 43(4), 366-371.
  • [18] Wu, F.M., Yang, Y.X. (2010). An extended adaptive Kalman filtering in tight coupled GPS/INS integration. Survey Review, 42(316), 146-154.
  • [19] Chang, G.B. (2014). Robust Kalman filtering based on Mahalanobis distance as outlier judging criterion. Journal of Geodesy, 88, 391-401.
  • [20] Li, Z.K., Wang, J., Gao, J.X. (2017). Application of improved robust Kalman filter in data fusion for PPP/INS tightly coupled positioning system. Metrol. Meas. Syst., 24(2), 289-301.
  • [21] Savage, P.G. (1998). Strapdown inertial navigation integration algorithm design Part 1: attitude algorithms. Journal of Guidance, Control, and Dynamics, 21(1), 19-28.
  • [22] Savage, P.G. (1998). Strapdown inertial navigation integration algorithm design Part 2: velocity and position algorithms. Journal of Guidance, Control, and Dynamics, 21(2), 208-221.
  • [23] Quinchia, A.G., Falco, G., Falletti, E., Dovis, F., Ferrer, C. (2013). A comparison between different error modeling of MEMS applied to GPS/INS integrated systems. Sensors, 13, 9549-9588.
Uwagi
PL
Opracowanie rekordu w ramach umowy 509/P-DUN/2018 ze środków MNiSW przeznaczonych na działalność upowszechniającą naukę (2018).
Typ dokumentu
Bibliografia
Identyfikator YADDA
bwmeta1.element.baztech-3ab93ef1-f57b-465f-ab00-7904bc179772
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