Ascent guidance for air-breathing hypersonic vehicles based on dynamic inversion

Liu, Xing; Liu, Lei; Wang, Yongji

doi:10.1177/1729881417703775

Cited by 2 publications

(3 citation statements)

References 27 publications

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“…As given in Equations ()–(), the terminal height is used to generate the trajectory. The procedure is like a dynamic inverse control, and the dynamic inverse convergence analysis is the same as Reference 21.…”

Section: Uncertain Parameters Estimation Based On the Extended Kalman...mentioning

confidence: 99%

“…In order to enable the MPSP to adapt to such uncertainties, online parameter estimation is employed to reduce the errors in model parameters to guarantee the accuracy of the terminal state of the vehicle. The commonly used parameter estimation methods are the least‐square estimation algorithm, 21 maximum likelihood estimate, 22 Kalman filtering, 23 and other neural‐based methods 24,25 . Due to the rapid changes in the flight environment, the estimation method needs to be reliable and capable to implement online.…”

Section: Introductionmentioning

confidence: 99%

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Ascent adaptive energy management method for solid rocket‐powered hypersonic vehicle under uncertainties

Liu

Wang

et al. 2023

Adaptive Control & Signal

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Summary The solid rocket booster is widely used in the launch mission for hypersonic vehicles nowadays, whose ascent energy management is still a challenging problem due to the inherent dynamic nonlinearity. This paper casts the problem into an equivalent ascent guidance one and proposes a model predictive static programming (MPSP) based solution. The MPSP‐based method is a computationally efficient solver that adapts to different energy demands while guaranteeing the satisfaction of terminal constraints. To further improve the performance of MPSP in this problem, a Bézier spline guidance method is proposed to generate high‐quality reference trajectories such that the MPSP can converge with high accuracy while satisfying the real‐time requirement. Additionally, an online parameter estimation based on the extended Kalman filter is employed to avoid large terminal state deviations incurred by parametric uncertainties during the Bézier curve computation and linearization in MPSP. Numerical simulations with different hard terminal constraints and uncertainties are conducted to demonstrate the effectiveness and robustness of the proposed algorithm. The simulation results show that our proposed algorithm can guide the hypersonic vehicle to a given terminal state under uncertainties and outperforms several existing ascent energy management methods.

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Section: Uncertain Parameters Estimation Based On the Extended Kalman...mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Ascent adaptive energy management method for solid rocket‐powered hypersonic vehicle under uncertainties

Liu

Wang

et al. 2023

Adaptive Control & Signal

Self Cite

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“…The GHV model used in this paper is called HL20 [34], [35]. The general configuration and mission of HL20 can be found in their works.…”

Section: A Mathematical Modelmentioning

confidence: 99%

Ascent Trajectory Optimization for Hypersonic Vehicle Based on Improved Chicken Swarm Optimization

Wang

et al. 2019

IEEE Access

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Trajectory optimization problem for hypersonic vehicles has received wide attention as its high speed and large flight range. The strong nonlinear characteristic of the ascent phase aerodynamics makes the trajectory optimization problem difficult to be solved by the optimal control theory. In this paper, an improved chicken swarm optimization (ICSO) algorithm is proposed to optimize the hypersonic vehicle ascent trajectory. To overcome the obstacle of premature convergence, three improvement strategies are put forward. To be specific, the updating laws of roosters are modified by the average position of roosters, and the difference of the optimal solution between two adjacent iterations is used to calculate the mutated particle instead of the gradient. Meanwhile, the uniform mutation operator is used to get rid of the local minimum. The convergence analysis of the proposed ICSO is provided subsequently. To handle constraints, an improved adaptive penalty method is put forward. The comparison results show that the proposed ICSO outperforms CSO and PSO on benchmark functions of CEC2014. Finally, the trajectory optimization results for a generic hypersonic vehicle, in compare with the open-source optimization software PSOPT, are put forward to demonstrate the feasibility and effectiveness of the proposed method. The results of 50 independent runs show that the improved adaptive penalty function method is effective in constraints handling.

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Ascent guidance for air-breathing hypersonic vehicles based on dynamic inversion

Cited by 2 publications

References 27 publications

Ascent adaptive energy management method for solid rocket‐powered hypersonic vehicle under uncertainties

Ascent adaptive energy management method for solid rocket‐powered hypersonic vehicle under uncertainties

Ascent Trajectory Optimization for Hypersonic Vehicle Based on Improved Chicken Swarm Optimization

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