Leap trajectory tracking control based on sliding mode theory for hypersonic gliding vehicle

An, Kai Nan; Guo, Zhen-yun; Huang, Wei; Xu, Xiaoping

doi:10.1631/jzus.a2100362

Cited by 18 publications

(5 citation statements)

References 31 publications

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“…For the longitudinal maneuver strategy, Tan et al [22] used the adaptive pseudospectral method to obtain the optimal dive trajectory considering the path constraints. An et al [23] applied predictive correction guidance methods to longitudinal trajectory design and obtained the gliding phase ballistic trajectory form through offline calculations. Zhu et al [24] obtained the optimal maneuver form for the dive section based on the optimal control method with minimum energy consumption and line-of-sight angular velocity as the performance index in the dive stage.…”

Section: Introductionmentioning

confidence: 99%

“…To improve the robustness of the guidance law, the sliding mode control method has been introduced into the design of the gliding tracking guidance law. An et al [23] designed a finite-time convergent sliding mode guidance law according to the tracking error, and Li et al [33] designed a sliding mode guidance law combining the global integral sliding mode surface and the exponential form reaching law. The above method can achieve good state tracking ability through reasonable parameter design under standard conditions, but there are some shortcomings, such as repeated formulation of guidance parameters and the inability to constrain dynamic performance.…”

Section: Introductionmentioning

confidence: 99%

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Multiple Leap Maneuver Trajectory Design and Tracking Method Based on Prescribed Performance Control during the Gliding Phase of Vehicles

Zhang,

Shen

et al. 2024

International Journal of Aerospace Engineering

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A novel standard trajectory design and tracking guidance used in the multiple active leap maneuver mode for hypersonic glide vehicles (HGVs) is proposed in this paper. First, the dynamic equation and multiconstraint model are first established in the flight path coordinate system. Second, the reference drag acceleration-normalized energy (D-e) profile of the multiple active leap maneuver mode is quickly determined by the Newton iterative algorithm with a single design parameter. The range to go error is corrected by the drag acceleration profile update algorithm, and the drag acceleration error of the gliding terminal is corrected by the aerodynamic parameter estimation algorithm. Then, the reference drag acceleration tracking guidance law is designed based on the prescribed performance control method. Finally, the CAV-L vehicle model is used for numerical simulation. The results show that the proposed method can satisfy the design requirements of drag acceleration under multiple active leap maneuver modes, and the reference drag acceleration can be tracked precisely. The adaptability and robustness of the proposed method are verified by the Monte Carlo simulations under various combined deviation conditions.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Multiple Leap Maneuver Trajectory Design and Tracking Method Based on Prescribed Performance Control during the Gliding Phase of Vehicles

Zhang,

Shen

et al. 2024

International Journal of Aerospace Engineering

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“…Many papers have been devoted to solving nonlinear control problems for hypersonic velocities, and many new controllers have been designed based on fault-tolerant control [5], robust control [6], adaptive control [7], predictive control [8], sliding mode control [9], and other control methods. The dynamic inverse controller is designed to actively compensate elastic disturbance and solve the system uncertainty problem [1,4].…”

Section: Introductionmentioning

confidence: 99%

“…Sliding mode control is a kind of nonlinear variable structure control, which has the advantages of fast response, strong antidisturbance ability, and strong robustness, and has been widely used in the control of hypersonic vehicle. [9] proposed a supertorsional sliding mode controller, which can approximate the global fast terminal sliding mode in finite time and is robust to uncertain parameters and other disturbances. In [12], a quasicontinuous sliding mode controller is designed based on the high-order sliding mode theory, which reduced the speed and height step response time and suppresses sliding mode chattering.…”

Section: Introductionmentioning

confidence: 99%

Nonlinear Predictive Control with Sliding Mode for Hypersonic Vehicle

Bai

Xie

et al. 2023

International Journal of Aerospace Engineering

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Hypersonic vehicles are difficult to control due to their rapid time variation, dynamic nonlinearity, strong coupling, and model uncertainty. This paper proposes a new nonlinear predictive controller to solve the problem. An improved model predictive controller is used to improve the dynamic control performance of hypersonic vehicles by converting nonlinear dynamics into a state-dependent linear model. The sliding surface can significantly increase the speed of convergence. The radial basis function is used to reduce the influence of system uncertainty. The stability of the proposed controller is analyzed based on the Lyapunov approach. The comparison of simulation results verifies the excellent control performance of the proposed method both in convergence speed and antidisturbance ability.

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“…Hypersonic vehicles, one of the outstanding breakthrough of the 21st-century aviation and aerospace industries, enable to reach the speed of over Mach 5, featured by fast flight speed, long flight distance and strong lateral maneuverability [1]- [5]. The development of hypersonic vehicles poses a great challenge to the existing defence systems, making it difficult to intercept accurately by traditional guidance laws.…”

Section: Introductionmentioning

confidence: 99%

Research on differential game guidance law for intercepting hypersonic vehicles

Chen¹,

Cheng²,

Bao³

et al. 2022

6th International Workshop on Advanced Algorithms and Control Engineering (IWAACE 2022)

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Hypersonic vehicles pose a serious challenge to the existing defence systems due to the fast flight velocity, long flight distance, strong lateral maneuverability. Concerning the problem of accurately intercepting hypersonic vehicles, the present study investigates the hypersonic vehicle interception problem under a small velocity ratio of the missile and the target based on the nonlinear differential game theory. In this case, the interception problem is transformed into the solution of the state-dependent coefficient (SDC) and the algebraic Riccati equation. Moreover, it also provides the analytical form of the differential game guidance law by adopting the State-dependent Riccati Equation (SDRE) method, which does not need to calculate the remaining flying time of the missile. Based on the simulation results, the interception performance of the recommended differential game guidance law can be better than that of the proportional navigation guidance (PNG) together with the adaptive sliding mode guidance (ASMG) laws.

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Leap trajectory tracking control based on sliding mode theory for hypersonic gliding vehicle

Cited by 18 publications

References 31 publications

Multiple Leap Maneuver Trajectory Design and Tracking Method Based on Prescribed Performance Control during the Gliding Phase of Vehicles

Multiple Leap Maneuver Trajectory Design and Tracking Method Based on Prescribed Performance Control during the Gliding Phase of Vehicles

Nonlinear Predictive Control with Sliding Mode for Hypersonic Vehicle

Research on differential game guidance law for intercepting hypersonic vehicles

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