Analytical Solution for Nonlinear Three-Dimensional Guidance With Impact Angle and Field-of-View Constraints

Hu, Qinglei; Han, Tuo; Xin, Ming

doi:10.1109/tie.2020.2982114

Cited by 33 publications

(8 citation statements)

References 26 publications

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“…Note that these terminal angle constrained guidance laws are developed in a planar case, which assumes decoupled three-dimensional (3D) engagement dynamics. However, a real 3D interception is more practical for guidance law design, which attracts the recent study on the design of 3D guidance laws [20][21][22][23][24][25][26][27][28][29][30]. Thus, it is of practical significance to investigate the terminal angle constrained guidance law in the 3D space.…”

Section: Introductionmentioning

confidence: 99%

“…There have been several 3D guidance laws considering the terminal angle constraint. In [23], a trajectory shaping 3D guidance law with impact angle constraint was proposed via developing reference line-of-sight (LOS) profiles. Then, adaptive multivariable twisting and super-twisting controls were employed to handle the impact angle constrained 3D guidance problems in [24,25].…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Sensor-Based Robust Incremental Three-Dimensional Guidance Law with Terminal Angle Constraint

Han¹,

Hu²,

Shin³

et al. 2021

Journal of Guidance, Control, and Dynamics

Self Cite

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In this work, a robust incremental three-dimensional (3D) guidance law is proposed considering terminal angle constraint against maneuvering targets. As a stepping stone, the line-of-sight (LOS) tracking error dynamics is employed for the 3D guidance law design. A sliding variable is constructed such that its first-order derivative excludes the relative range in the perturbation, which avoids the unboundedness of system perturbation induced by target maneuvers near collision. A time-varying version of the sliding variable is designed to accelerate convergence of the LOS tracking errors and avoid large initial sliding variables. Then, two guidance laws are derived as a benchmark via the nonlinear dynamic inversion (NDI)-based sliding mode control (NDI-SMC) and NDI-based time-varying sliding mode control (NDI-TVSMC), respectively. To further improve guidance robustness with reduced system perturbation, the sensor-based incremental nonlinear dynamic inversion (INDI) control is used to design the INDI-SMC-based and INDI-TVSMC-based guidance laws. The sensor-based guidance laws exploit the LOS angular acceleration and guidance command output at the latest step, which result in smaller guidance gains to reject the perturbation than the NDI guidance laws. Numerical simulations in various cases and comparison studies are conducted to verify the effectiveness and robustness of the proposed method.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Sensor-Based Robust Incremental Three-Dimensional Guidance Law with Terminal Angle Constraint

Han¹,

Hu²,

Shin³

et al. 2021

Journal of Guidance, Control, and Dynamics

Self Cite

View full text Add to dashboard Cite

show abstract

“…In [12], a twisting control-based guidance law considering nonlinear/coupled dynamics and terminal angle constraints was proposed in a three-dimensional space. In [13] [14], an analytical threedimensional guidance law, considering nonlinear coupled dynamics and the constraints of impact angle and field-ofview, was proposed. Morphing aircrafts with different morphing modes were proposed and studied in [15].…”

Section: Introductionmentioning

confidence: 99%

Longitudinal Tracking Control for a Morphing Waverider Using Adaptive Super Twisting Control

et al. 2021

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The morphing aircraft is a promising solution to achieve an optimal flight performance according to various mission scenarios. To apply the morphing technology in hypersonic vehicles, a variable-sweep-wing morphing waverider was proposed in previous studies, and its aerodynamic performance and dynamic model were presented. In this paper, this morphing waverider is assumed to perform a long-range unpowered glide mission over a wide speed range from hypersonic to subsonic speed. First, the accurate longitudinal dynamic model for the morphing waverider is presented, with all the additional forces and moments that stem from morphing. And a control-oriented longitudinal dynamic model is proposed and it separates the additional morphing forces and moments from derivatives of state variables. Then, an adaptive super twisting sliding mode controller is applied for this morphing waverider to track the optimized trajectory during the entire morphing process. Finally, the overall performance of this controller is examined by nominal condition simulations and Monte Carlo runs. Under the nominal condition simulations, the adaptive super twisting algorithm based sliding mode controller reduces mean tracking error of the pitch angle by 25% compared with the traditional sliding mode controller. In the 500 Monte Carlo runs, the ASTA controller reduces maximum tracking error of the pitch angle by 47% compared with the SMC controller.INDEX TERMS Variable-sweep-wing, morphing waverider, sliding mode control, adaptive super twisting algorithm

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“…In order to tackle this problem, the concept of finite-time control (FTC) was put forward in the middle of the last century [34][35][36]. Given a limit condition of the system initial value, if the system states never exceed a certain threshold within a finite-time interval, the system is described as finitetime stable.…”

Section: Introductionmentioning

confidence: 99%

BLSTM-Based Adaptive Finite-Time Output-Constrained Control for a Class of AUSs with Dynamic Disturbances and Actuator Faults

Huang

Rong

Chang

et al. 2021

Mathematical Problems in Engineering

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In this paper, a BLSTM-based adaptive finite-time control structure has been constructed for a class of aerospace unmanned systems (AUSs). Firstly, a novel neural network structure possessing both the time memory characteristics and high learning speed, broad long short-term memory (BLSTM) network, has been constructed. Secondly, several nonlinear functions are utilized to transform the tracking errors into a novel state vector to guarantee the output constraints of the AUSs. Thirdly, the fractional-order control law and the corresponding adaptive laws are designed, and as a result, the adaptive finite-time control scheme has been formed. Moreover, to handle the uncertainties and the faulty elevator outputs, an inequality of the multivariable systems is utilized. Consequently, by fusing the output of the BLSTM, the transformation of the tracking errors, and the adaptive finite-time control law, a novel BLSTM-based intelligent adaptive finite-time control structure has been established for the AUSs under output constraints. The simulation results show that the proposed BLSTM-based adaptive control algorithm can achieve favorable control results for the AUSs with multiple uncertainties.

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Analytical Solution for Nonlinear Three-Dimensional Guidance With Impact Angle and Field-of-View Constraints

Cited by 33 publications

References 26 publications

Sensor-Based Robust Incremental Three-Dimensional Guidance Law with Terminal Angle Constraint

Sensor-Based Robust Incremental Three-Dimensional Guidance Law with Terminal Angle Constraint

Longitudinal Tracking Control for a Morphing Waverider Using Adaptive Super Twisting Control

BLSTM-Based Adaptive Finite-Time Output-Constrained Control for a Class of AUSs with Dynamic Disturbances and Actuator Faults

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