Roll-pitch-yaw autopilot design for nonlinear time-varying missile using partial state observer based global fast terminal sliding mode control

Awad, Ahmed S. A.; Wang, Haoping

doi:10.1016/j.cja.2016.04.020

Cited by 20 publications

(10 citation statements)

References 33 publications

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Section: Pitch Control Model Considering Wind Disturbancementioning

confidence: 99%

“…The model of the missile in this paper has an axis-symmetric and cruciform shape, based on the general assumption [26], the model in the ascent phase that considers gust disturbances is shown in Figure 16. Assuming that the missile is not disturbed by the wind at the initial state, by this time, the flight state of the rocket is: the ground speed is V , the angle of attack is v  , the track angle is  , the pitch angle is  , and the roll angle is  .…”

Section: Pitch Control Model Considering Wind Disturbancementioning

confidence: 99%

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Attitude Control in Ascent Phase of Missile Considering Actuator Non-Linearity and Wind Disturbance

et al. 2019

Applied Sciences

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During the ascent phase of a missile, a challenging problem occurs that blocks the construction of a high-precision attitude control scheme, which directly affects accurate modeling including disturbances: non-linearities of an actuator, rapidly time-varying parameters, un-modeled dynamics, etc. In order to improve the control performance, an active disturbance rejection control (ADRC) scheme, considering non-linear dynamics of the actuator and wind disturbance during the ascent phase, is proposed in this paper. An expand state observer (ESO) is planned to estimate and compensate the actuator’s non-linear dynamics, flight model uncertainties, and wind disturbance. Therefore, the complex non-linear time-varying control problem is simplified into a linear time-invariant control problem. The pitch attitude control system is controlled by the cascade method and ADRC controllers are designed for actuator close loop and attitude control loop, respectively. The simulation results show that ADRC has strong robustness under different dead-zones and external disturbances of the actuator. On the other hand, ADRC can effectively suppress the external atmospheric disturbance. Compared with the traditional gain-scheduling control scheme, the ADRC scheme can significantly reduce the overloading of the system and shows remarkable performance for tracking as well as wind resistance.

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Section: Pitch Control Model Considering Wind Disturbancementioning

confidence: 99%

Section: Pitch Control Model Considering Wind Disturbancementioning

confidence: 99%

Attitude Control in Ascent Phase of Missile Considering Actuator Non-Linearity and Wind Disturbance

et al. 2019

Applied Sciences

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“…In recent years, terminal sliding mode control (TSMC) has been demonstrated to achieve finite time convergence and to against uncertainties with better robustness [15], [16]. TSMC method has been successfully applied in IGC design [17], [18]. However, TSMC has a singularity problem that may lead to negative results.…”

Section: Introductionmentioning

confidence: 99%

Impact Angle Constrained Three-Dimensional Integrated Guidance and Control Based on Fractional Integral Terminal Sliding Mode Control

et al. 2019

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In this paper, considering a class of skid-to-turn (STT) missile with impact angle constraint to intercept the maneuvering target, a three-dimensional integrated guidance and control law based on the fractional integral terminal sliding mode control (FITSMC) scheme is proposed. Firstly, a three-dimensional integrated guidance and control model is established for missile-target relative motion and nonlinear missile dynamics with multiple system uncertainties and unknown disturbances. Secondly, in order to achieve the desired impact angle in finite-time without singularity, a novel nonsingular FITSMC scheme is employed to construct the sliding surface, and a modified filter is applied to dynamic surface control design. Also, an extended state observer is introduced to estimate and compensate the system uncertainties and unknown disturbances. Then, a robust integrated guidance and control scheme with impact angle constraint is developed using aforementioned techniques. Furthermore, the finite-time stability of the closed-loop system is proven based on Lyapunov theory. Finally, the effectiveness and robustness of the proposed integrated guidance and control algorithm are verified through numerical simulations.INDEX TERMS Integrated guidance and control, impact angle constraint, fractional integral terminal sliding mode control, finite-time convergence, dynamic surface control.

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“…The discontinuous signum function induces the well-known chattering phenomenon as the switching gain need to be defined larger than the bound of uncertainties, which degrades system performance and prohibits implementation of the controller. Some works substituted the discontinuous item with saturation function or sigmoid function (29) , whereas control effectiveness is sacrificed to a certain degree. Refs.…”

Section: Introductionmentioning

confidence: 99%

“…To alleviate chattering effectively, an integrated roll-pitch-yaw autopilot based on global TSMC control was synthesised in Ref. (29) with a partial state nonlinear observer without using the signum function.…”

Section: Introductionmentioning

confidence: 99%

Smooth adaptive fixed time convergent controller design for BTT missiles with uncertainties

2019

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A smooth adaptive sliding-mode-based controller is developed for BTT missiles considering nonlinear couplings and aerodynamic uncertainties, wherein fixed-time stability theory is synthesised into sliding-mode control algorithm, such that control variables follow the desired command within fixed-bounded convergence time. Unlike other terminal sliding-mode-related works, the bound of settling time is independent of initial states, indicating that performance metrics, for instance the convergence rate, can be evaluated in advance. The control input is designed to be intrinsically smooth, based on adaptive estimations, and therefore the problem of singularity and chattering is effectively eliminated. Simulation results demonstrate the satisfactory performance and validate the effectiveness of the designed approach.

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Roll-pitch-yaw autopilot design for nonlinear time-varying missile using partial state observer based global fast terminal sliding mode control

Cited by 20 publications

References 33 publications

Attitude Control in Ascent Phase of Missile Considering Actuator Non-Linearity and Wind Disturbance

Attitude Control in Ascent Phase of Missile Considering Actuator Non-Linearity and Wind Disturbance

Impact Angle Constrained Three-Dimensional Integrated Guidance and Control Based on Fractional Integral Terminal Sliding Mode Control

Smooth adaptive fixed time convergent controller design for BTT missiles with uncertainties

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