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Re-entry guidance method based on decoupling control variables and waypoint

Published online by Cambridge University Press:  05 April 2019

Z. Li Open the ORCID record for Z. Li [Opens in a new window] ,
T. Yang  and
Z. Feng
Z. Li*
Affiliation:
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha, China
T. Yang
Affiliation:
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha, China
Z. Feng
Affiliation:
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha, China
*
[email protected]
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Abstract

Generally, earth rotating and non-spherical perturbation of the earth in re-entry motion model are simplified using the standard trajectory guidance method. The re-entry motion is also simplified to horizontal motion and vertical motion and controlled, respectively. The simplification of re-entry motion model will lead to loss of motion accuracy and location accuracy. The direct decomposition will lead to the reduction of control accuracy because the horizontal motion and the vertical motion are coupled in re-entry. To improve the standard trajectory guidance method, the standard trajectory guidance method based on decoupling control variables and waypoint is proposed in this paper. The proposed guidance method will not simplify earth rotating and non-spherical perturbation of the earth in motion equation or decompose the re-entry motion to horizontal motion and vertical motion. Trajectory waypoint is adopted to reduce the change frequency of tracking states, because tracking states change frequently if the entire standard trajectory is tracked in real time.

Keywords

WaypointGuidance methodSliding mode control methodAircraft re-entry
Type
Research Article
Information
The Aeronautical Journal , Volume 123 , Issue 1262 , April 2019 , pp. 523 - 535
Copyright
© Royal Aeronautical Society 2019 

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References

1. Phillips, T.H A common aero vehicle (CAV) model, description, and employment guide, 2003.Google Scholar
2. Lu, P. Entry guidance: a unified method, J. Guidance, Control, and Dynamics, 2014, 37, (3), pp 713–728.Google Scholar
3. Yu, W. and Chen, W. Entry guidance with real-time planning of reference based on analytical solutions, Advances in Space Research, 2015, 55, (9), pp 2325–2345.Google Scholar
4. Youssef, H., Chowdhry, R.S., Lee, H., et al. Predictor–corrector entry guidance for reusable launch vehicles. AIAA Guidance, Navigation, and Control Conference. Montreal, 2001. AIAA-2001-4043, pp 1–8.Google Scholar
5. Joshi, A. and Sivan, K Reentry guidance for generic rlv using optimal perturbations and error weights. AIAA Guidance, Navigation, and Control Conference and Exhibit, 2005. San Francisco: AIAA-2005-6438, pp 1–14.Google Scholar
6. Xu, M.L., Chen, K.J., Liu, L.H., et al. Quasi-equilibrium glide adaptive guidance for hypersonic vehicles, Science China, 2012, 55, (3), pp 856–866.Google Scholar
7. Shen, Z.J. and Lu, P. Onboard generation of three-dimensional constrained entry trajectories, J. Guidance, Control, and Dynamics, 2003. 26, pp 111–121.Google Scholar
8. Hanson, J.M. and Jones, R.E Test results for entry guidance methods for reusable launch vehicles. 42nd AIAA Aerospace Sciences Meeting and Exhibit, 2004. Reno: AIAA-2004-701, pp 1–10.Google Scholar
9. Li, Z., Yang, T. and Feng, Z. The multiobjective trajectory optimization for hypersonic glide vehicle based on normal boundary intersection method. Mathematical Problems in Engineering, 2016. vol. 2016, Article ID 9407238, pp 8. https://doi.org/10.1155/2016/9407238.Google Scholar
10. Samira, E. and Renuganth, V. Singularity-free integral-augmented sliding mode control for combined energy and attitude control system, Advances in Space Research,, 2017, 59, (2), pp 631–644.Google Scholar
11. He, S. and Lin, D. Sliding mode-based continuous guidance law with terminal angle constraint, Aeronautical Journal – New Series, 2016, 1, (1229), pp 1–21.Google Scholar
12. Xiong, J.H., Tang, S.J., Guo, J., et al. Improved sliding mode guidance law based on fuzzy variable coefficients strategy, Aeronautical J, 2014, 118, (1202), pp 435–451.Google Scholar