Abstract
The trajectory design and optimization problem for single stage rocket launched supersonic powered vehicle subject to multiple process and terminal constraints is discussed. The whole trajectory is divided into a boost phase and two scramjet powered ascent phases. For boost phase trajectory, the angle of attack is expressed as a function of time, and determined by design optimization parameters. The trajectory state variables are obtained by numerical integration, and by optimizing of design parameters, all the process and terminal constraints are satisfied, and the nominal profiles are generated. A nominal profile tracking and feedback control guidance is proposed. For a scramjet powered flight test vehicle, the constant speed ascent phase and constant dynamic pressure ascent phase trajectory profile is designed, equivalence ratio and angle of attack controls are generated by solving nonlinear equations. Numerical simulation for an example test vehicle has been done and results are given, verifying that these methods are correct and effective.
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Liu, J., Wang, L., Zhang, M., Ge, Y. (2022). Trajectory Design Optimization and Guidance for Supersonic Vehicle Subject to Multiple Constraints. 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_401
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DOI: https://doi.org/10.1007/978-981-15-8155-7_401
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Publisher Name: Springer, Singapore
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Online ISBN: 978-981-15-8155-7
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