Explicit Parameterized Energy Management for Scramjet Transition

This paper presents a guidance law for a booster to meet the requirements of scramjet transition. The straightforward open-loop and closed-loop guidance laws are combined together through a smooth switch. In the closed-loop guidance law, the worst case with a minimal lift-drag ratio is selected to o...

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Bibliographic Details
Published in:IEEE transactions on aerospace and electronic systems 2019-04, Vol.55 (2), p.798-809
Main Authors: Sun, Mingwei, Zhang, Youan, Liu, Jingmao, Huang, Jian, Wang, Zenghui, Chen, Zengqiang
Format: Article
Language:English
Subjects:
Aerodynamics
Ascent phase
Computer simulation
Elevation angle
Energy management
guidance
Guidance (motion)
hypersonic vehicle
Robustness (mathematics)
Rockets
scramjet
Supersonic combustion ramjet engines
Trajectory optimization
transition
Uncertainty
Vehicle dynamics
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Summary:This paper presents a guidance law for a booster to meet the requirements of scramjet transition. The straightforward open-loop and closed-loop guidance laws are combined together through a smooth switch. In the closed-loop guidance law, the worst case with a minimal lift-drag ratio is selected to obtain a nominal elevation angle. The excessive energy due to various uncertainties could be dissipated around this nominal trajectory adaptively. Numerical simulations are conducted to validate the effectiveness and robustness of the proposed method.
ISSN:0018-9251
1557-9603
DOI:10.1109/TAES.2018.2864810