Review of control and guidance technology on hypersonic vehicle

Ding, Yibo; Yue, Xiaokui; Chen, Guangshan; Si, Jiashun

doi:10.1016/j.cja.2021.10.037

Cited by 125 publications

(15 citation statements)

References 101 publications

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“…Note that ë V , ë h and e (3) h appear in Equations ( 13) and (14). In order to obtain the j-th order derivatives of error e (j)…”

Section: Exact Robust Differentiatormentioning

confidence: 99%

“…Thus, how to guarantee the robustness of closed‐loop system before the NDO error convergence is an interesting topic. SMC is a conventional robust control method to handle the nonlinear and perturbed system, 11,12 but it generally requires the bound of uncertainties to design the switching gains 13,14 . Furthermore, the implementation of sliding mode control is often irritated by high frequency oscillations known as “chattering” 15,16 .…”

Section: Introductionmentioning

confidence: 99%

“…SMC is a conventional robust control method to handle the nonlinear and perturbed system, 11,12 but it generally requires the bound of uncertainties to design the switching gains. 13,14 Furthermore, the implementation of sliding mode control is often irritated by high frequency oscillations known as "chattering". 15,16 Some novel high-order sliding model (HOSM) methods can obtain a continuous control law and guarantee the finite-time convergence of tracking error.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Robust approximate optimal control for air‐breathing hypersonic vehicle

Xiao

Liu

Fan

et al. 2023

Intl J Robust & Nonlinear

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This paper investigates the robust approximate optimal control problem for air-breathing hypersonic vehicle (AHV). By input-output linearzation and introducing auxiliary variables, the high-order nonlinear AHV dynamics are transformed to a second-order feedback decoupling model. Then a virtual command is designed by back-stepping strategy to guarantee the practical finite-time convergence of tracking error. In order to drive the AHV with uncertainties to follow the virtual command, a robust approximate optimal controller based on adaptive dynamic programming (ADP) is proposed. Different from the conventional robust method, both the robustness and the input cost are taken into consideration in the proposed controller, which can optimize the control actions and hence avoid the chattering. Besides, the proposed controller adopts a single critic network design instead of actor-critic structure, which ensures the stability of the system autonomously and simplifies the implementation procedure. The simulation results show the effectiveness of the proposed scheme.

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“…Note that ë V , ë h and e (3) h appear in Equations ( 13) and (14). In order to obtain the j-th order derivatives of error e (j)…”

Section: Exact Robust Differentiatormentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Robust approximate optimal control for air‐breathing hypersonic vehicle

Xiao

Liu

Fan

et al. 2023

Intl J Robust & Nonlinear

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show abstract

“…From the last few decades until now, hypersonic glide vehicles (HGV) have attracted the attention of researchers [1][2][3][4][5] due to their high velocity and wide flight airspace. Usually, cooperative guidance has been widely studied as an effective threat to valuable targets represented by hypersonic vehicles [6][7][8][9][10].…”

Section: Introductionmentioning

confidence: 99%

Intelligent Online Multiconstrained Reentry Guidance Based on Hindsight Experience Replay

Jiang

Wang

Bai

et al. 2023

International Journal of Aerospace Engineering

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Traditional guidance algorithms for hypersonic glide vehicles face the challenge of real-time requirements and robustness to multiple deviations or tasks. In this paper, an intelligent online multiconstrained reentry guidance is proposed to strikingly reduce computational burden and enhance the effectiveness with multiple constraints. First, the simulation environment of reentry including dynamics, multiconstraints, and control variables is built. Different from traditional decoupling methods, the bank angle command including its magnitude and sign is designed as the sole guidance variable. Secondly, a policy neural network is designed to output end-to-end guidance commands. By transforming the reentry process into a Markov Decision Process (MDP), the policy network can be trained by deep reinforcement learning (DRL). To address the sparse reward issue caused by multiconstraints, the improved Hindsight Experience Replay (HER) method is adaptively combined with Deep Deterministic Policy Gradient (DDPG) algorithm by transforming multiconstraints into multigoals. As a result, the novel training algorithm can realize higher utilization of failed data and improve the rate of convergence. Finally, simulations for typical scenes show that the policy network in the proposed guidance can output effective commands in much less time than the traditional method. The guidance is robust to initial bias, different targets, and online aerodynamic deviation.

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“…Hypersonic flight vehicle (HFV) has high flight speed, strong penetration capability, and good concealment performance, which has become a research hotspot in the current aerospace field (Ding et al, 2022; Xu and Shi, 2015). As one of the key technologies, the attitude control system of HFV is of vital importance.…”

Section: Introductionmentioning

confidence: 99%

Attitude optimization control of hypersonic flight vehicle considering partially unknown control direction

Guo

Wang

Guo

et al. 2022

Transactions of the Institute of Measurement and Control

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In this paper, a control method based on periodic sliding mode technology and adaptive dynamic programming algorithm is proposed for the attitude dynamics of hypersonic flight vehicle. The method takes into account a case that there is unknown control direction in a single channel. First, under the premise that the disturbance observers estimate the coupling and other disturbances, the attitude dynamics are decomposed into mathematical models of pitch channel and yaw-roll channel, respectively. Then, a periodic sliding mode control law with both stability and rapidity is designed for the unknown control direction in pitch channel. In the yaw-roll channel, an optimal attitude control law satisfying cost function is designed based on adaptive dynamic programming algorithm. What’s more, the closed-loop system is proved to be stable by Lyapunov stability theorem. Finally, the simulation results show that the attitude angle can track the command stably, which proves the effectiveness of the control scheme. Compared with the backstepping control scheme, the simulation results show that the proposed scheme can effectively avoid the divergence of the system because of the control direction switch, and the system have better dynamic performance and robustness.

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Review of control and guidance technology on hypersonic vehicle

Cited by 125 publications

References 101 publications

Robust approximate optimal control for air‐breathing hypersonic vehicle

Robust approximate optimal control for air‐breathing hypersonic vehicle

Intelligent Online Multiconstrained Reentry Guidance Based on Hindsight Experience Replay

Attitude optimization control of hypersonic flight vehicle considering partially unknown control direction

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