Abstract
In this paper, considering the various terminal states constraints, and coupling of different states in the ascent phase of the hypersonic aircraft, a multi-constrained guidance method based on predictor–corrector policy is proposed. Firstly, the dynamic equations of ascent phase are given. And then, the dynamic amplification factors for the various flight states are calculated. Analyzing the dynamic equations of ascent phase, it can be found that only the attack angle is used to control various states and the guidance of ascent phase is an under-driven problem. The path angles are small values at the terminal flight phase, and it has little couple influence on the altitude. In order to solve the under-driven problem, the whole ascent phase has two parts. At the initial phase, eliminating the terminal height error is chosen as the guidance object. At the terminal phase, eliminating the path angle error at the end point is chosen as the guidance object. What’s more, the influence of choosing different segmentation altitude on the terminal states errors is analyzed. Moreover, the Monte Carlo simulation demonstrates the effectiveness of the proposed multi-constrained adaptive predictor–corrector guidance method.
Access this chapter
Tax calculation will be finalised at checkout
Purchases are for personal use only
Similar content being viewed by others
References
Betts, J.T.: Survey of numerical methods for trajectory optimization. J. Guidance Control Dyn. 21(1), 193–207 (1988)
Schleich, W.T.: The space shuttle ascent guidance and control. AIAA A82-38927 (1982)
Lu, P., Tsai, B.: Ascent, closed-loop Endo-atmospheric ascent guidance. AIAA 2002-4558 (2002)
Dukeman, G.A., Calise, A.J.: Enhancements to an atmospheric ascent guidance algorithm. AIAA 2003-5638 (2003)
Zhang, Z., Hu, J.: Prediction-based guidance algorithm for high-lift reentry vehicle. Sci. China (Inform. Sci.) 54(3), 498–510 (2011)
Zeng, L., Zhang, H.B., Zheng, W.: A three-dimensional predictor–corrector entry guidance based on reduced-order motion equations. Aerosp. Sci. Technol. 73, 223–231 (2018)
Li, M.M., Hu, J.: An approach and landing guidance design for reusable launch vehicle based on adaptive predictor-corrector technique. Aerosp. Sci. Technol. 75, 13–23 (2018)
Acknowledgments
Research supported by National key R&D Program of China under Grant 2018YFA0703800.
Author information
Authors and Affiliations
Corresponding author
Editor information
Editors and Affiliations
Rights and permissions
Copyright information
© 2022 The Editor(s) (if applicable) and The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd.
About this paper
Cite this paper
Maomao, L., Jun, H., Huang, H., Ruike, G. (2022). A Multi-constrained Adaptive Predictor–Corrector Guidance Method for Ascent Phase of Hypersonic Vehicle. In: Yan, L., Duan, H., Yu, X. (eds) Advances in Guidance, Navigation and Control . Lecture Notes in Electrical Engineering, vol 644. Springer, Singapore. https://doi.org/10.1007/978-981-15-8155-7_14
Download citation
DOI: https://doi.org/10.1007/978-981-15-8155-7_14
Published:
Publisher Name: Springer, Singapore
Print ISBN: 978-981-15-8154-0
Online ISBN: 978-981-15-8155-7
eBook Packages: Intelligent Technologies and RoboticsIntelligent Technologies and Robotics (R0)