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High-precision Mars Entry Integrated Navigation Under Large Uncertainties

Published online by Cambridge University Press:  20 November 2013

Shuang Li ,
Xiuqiang Jiang  and
Yufei Liu
Shuang Li*
Affiliation:
(College of Astronautics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China)
Xiuqiang Jiang
Affiliation:
(College of Astronautics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China)
Yufei Liu
Affiliation:
(P.O. Box 5142-228, China Academy of Space Technology, Beijing 100094, China)
*
(E-mail: [email protected])
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Abstract

In this paper, we present a high-precision Mars entry integrated navigation algorithm under large uncertainties via a desensitised extended Kalman filter (DEKF). Firstly, a new six degree-of-freedom Mars entry dynamics model is derived based on the angular velocity outputs of a gyro, which is free of modelling errors in the aerodynamic and control torques. Secondly, both the accelerometer outputs and radio measurements between orbiters and entry vehicle are used as the observations embedded in a navigation filter to perform state estimation and suppress the measurement noise. Finally, a desensitised extended Kalman filter, exhibiting the desirable property of efficiently reducing the sensitivity of state variables with respect to model and parameter uncertainties, is adopted in order to overcome the adverse effects of initial state errors and uncertainties during Mars atmospheric entry and further improve entry navigation accuracy. The numerical simulation results show that the DEKF-based integrated navigation algorithm developed in this paper can achieve a better navigation performance with higher accuracy when compared with the standard extended Kalman filter (EKF)-based integrated navigation algorithm in the presence of larger state errors and parameter uncertainties.

Keywords

Mars entryIntegrated navigationDesensitised extended Kalman filterAccelerometerRadio measurement
Type
Research Article
Information
The Journal of Navigation , Volume 67 , Issue 2 , March 2014 , pp. 327 - 342
Copyright
Copyright © The Royal Institute of Navigation 2013 

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References

REFERENCES

Boehmer, R.A., (1998). Navigation analysis and design for Mars entry. Master Thesis, Massachusetts Institute of Technology.Google Scholar
Brand, T., Fuhrman, L., Geller, D., Hattis, P., Paschall, S., and Tao, Y.C. (2004). GN&C Technology Needed to Achieve Pinpoint Landing Accuracy at Mars. AIAA/AAS Astrodynamics Specialist Conference and Exhibit, Providence, Rhode Island. AIAA 2004-4748.CrossRefGoogle Scholar
Braun, R.D. (2007). Mars exploration entry, descent, and landing challenges. Journal of Spacecraft and Rockets, 44(2), 310–323.Google Scholar
Burkhart, P. D., Ely, T., Duncan, C., Lightsey, E. G., Campbell, T., and Mogensen, A. (2005). Expected EDL navigation performance with spacecraft to spacecraft radiometric data. AIAA Guidance Navigation and Control Conference, 1060–1074.CrossRefGoogle Scholar
Chen, A., Beck, R., Brugarolas, P., Edquist, K., Mendeck, G., Schoenenberger, M., and Way, D. (2013). Entry system design and performance summary for the Mars science laboratory mission. AIAA/AAS Spaceflight Mechanics Meeting, Lihue, HI, AAS 13-422.Google Scholar
Chen, A., Vasavada, A., Cianciolo, A., Barnes, J., Tyler, D., Rafkin, S., Hinson, D., and Lewis, S. (2010). Atmospheric risk assessment for the Mars science laboratory entry, descent, and landing system. IEEE Aerospace Conference, Big Sky, MT.Google Scholar
Chu, C.C. (2006). Development of advanced entry, descent, and landing technologies for future Mars Missions. IEEE Proceedings of Aerospace Conference, Big Sky, Montana.Google Scholar
Ely, T.A., Bishop, R.H., and Dubois-Matra, O. (2001). Robust entry navigation using hierarchical filter architectures regulated with gating networks. 16th International Symposium on Spaceflight Dynamics Symposium, Pasadena, CA, United States.Google Scholar
Heyne, M.C. and Bishop, R.H. (2006). Spacecraft Entry Navigation using Sigma Point Kalman Filtering. 2006 IEEE/ION Position, Location, and Navigation Symposium, 71–79.Google Scholar
Karlgaard, C.D. and Shen, H.J. (2013). Desensitised kalman filtering. IET Radar, Sonar & Navigation, 7(1), 2–9.CrossRefGoogle Scholar
Karlgaard, C.D. and Shen, H.J. (2011). Desensitised optimal filtering. AIAA Guidance, Navigation and Control Conference, Portland, USA.Google Scholar
Lévesque, J.F. (2006). Advanced navigation and guidance for high precision planetary landing on Mars. PhD thesis, Sherbrooke University.Google Scholar
Lévesque, J.F., and Lafontaine, J.D. (2007). Innovative navigation schemes for state and parameter estimation during Mars entry. Journal of Guidance, Control and Dynamics, 30(1), 169–184.Google Scholar
Li, S. and Peng, Y.M. (2011). Radio beacons/IMU integrated navigation for Mars entry. Advances in Space Research, 47(1), 1265–1279.Google Scholar
Li, S., Peng, Y.M., Lu, Y.P., Zhang, L., and Liu, Y.F. (2010). MCAV/IMU integrated navigation for the powered descent phase of Mars EDL. Advances in Space Research, 46(5):557–570.Google Scholar
Li, S. and Zhang, L. (2009). Autonomous navigation and guidance scheme for precise and safe planetary landing. Aircraft Engineering and Aerospace Technology: An International Journal, 81(6), 516–521.Google Scholar
Li, S., Cui, P.Y. and Cui, H.T. (2007). Vision-aided inertial navigation for pinpoint planetary landing. Aerospace Science and Technology, 11(6), 499–506.CrossRefGoogle Scholar
Lockwood, M.K., Powell, R.W., Graves, C.A. and Carman, G.L. (2001). Entry system design considerations for Mars landers. Proceedings of the Annual AAS Rocky Mountain Conference, 31 Jan − 4 Feb, Breckenridge, CO.Google Scholar
Lu, Y.Y., Rong, W. and Wu, S.T. (2012). Introduction and New Technology of EDL System of MSL. Spacecraft Engineering, 21(5), 117–123.Google Scholar
Martin, A.M.S., Wong, E.C., and Lee, S.W. (2013). The development of the MSL guidance, navigation, and control system for entry, descent, and landing. AIAA/AAS Spaceflight Mechanics Meeting, Lihue, HI, AAS 13-238.Google Scholar
Martin-Mur., T.J., Kruizinga, G.L., Burkhart, P.D., Wong, M.C., and Abilleira, F. (2012). Mars Science Laboratory navigation results. 23rd international symposium on space flight dynamics, Pasadena, CA, United States.Google Scholar
Schoenenberger, M., Norman, J.V., Dyakonov, A., Karlgaard, C., Way, D., and Kutty, P. (2013). Assessment of the reconstructed aerodynamics of the Mars science laboratory entry vehicle. AIAA/AAS Spaceflight Mechanics Meeting, Lihue, HI, AAS 13-306.Google Scholar
Seywald, H. and Kumar, R. (1996). Desensitised Optimal Trajectories. Advances in the Astronautical Sciences, (93), 103–116.Google Scholar
Shen, H.J. and Karlgaard, C.D. (2012). Desensitised unscented Kalman filter about uncertain model parameters. Institute of Navigation International Technical Meeting, Newport Beach, California, USA.Google Scholar
Tolson, R.H. and Prince, J.L.H. (2011). Onboard atmospheric modeling and prediction for autonomous aerobraking missions. AAS/AIAA Astrodynamics Specialist Conference, Girdwood, AK.Google Scholar
Vinh, N.X., Busemann, A. and Culp, R.D. (1980). Hypersonic and planetary entry flight mechanics. University of Michigan press, Ann Arbor, MI.Google Scholar
Williams, J.L., Menon, P.R. and Demcak, S.W. (2012). Mars reconnaissance orbiter navigation strategy for mars science laboratory entry, descent and landing telecommunication relay support. AIAA/AAS Astrodynamics Specialists Conference Minneapolis, Minnesota, AIAA 2012-4747.Google Scholar
Wolf, A.A., Graves, C., Powell, R. and Johnson, W. (2005). Systems for pinpoint landing at Mars, Advances in the Astronautical Sciences, 119, 2677–2696.Google Scholar
Zanetti, R. and Bishop, R.H. (2007). Adaptive Entry Navigation Using Inertial Measurements. AAS/AIAA Space Flight Mechanics Meeting, Sedona, AZ, AAS-07-129.Google Scholar