Nonlinear fractional order proportion-integral-derivative active disturbance rejection control method design for hypersonic vehicle attitude control

Song, Jia; Wang, Lun; Cai, Guobiao; Qi, Xiaoqiang

doi:10.1016/j.actaastro.2015.02.026

Cited by 70 publications

(36 citation statements)

References 11 publications

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“…Give the positive function V 2 ðXÞ as a candidate Lyapunov function of the closed-loop system (10) and conditions (28), (29), and (30) are satisfied. The derivative of V 2 ðXÞ is satisfied with …”

Section: Stability Analysis Of Closed-loop Systemmentioning

confidence: 99%

“…For the nonlinear HRV system, different forms of ESO have also been applied to estimate uncertainties in attitude and angular rate loop. 26,27 Moreover, nonlinear tracking differentiator (TD) as other component of ADRC has been used for fewer control consumption and smooth transient performances in the studies by Shao et al 27,28 Note that actuator saturation exists commonly in systems. To deal with the problem of actuator saturation in HRV systems, filters with magnitude limit constraints have been used.…”

Section: Introductionmentioning

confidence: 99%

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Active disturbance rejection attitude control for a hypersonic reentry vehicle with actuator saturation

Yang¹,

Yu²,

Wang³

et al. 2017

International Journal of Advanced Robotic Systems

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In this article, nonlinear uncertainty has been investigated for a hypersonic reentry vehicle subject to actuator saturation via active disturbance rejection control technology. A nonlinear extended state observer is designed to estimate "total disturbances," which is compensated with a linear controller. Both convergence of the nonlinear extended state observer and stabilization of the closed-loop system are studied in this article. Some simulation results are given to illustrate the effectiveness of the proposed method.

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Section: Stability Analysis Of Closed-loop Systemmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Active disturbance rejection attitude control for a hypersonic reentry vehicle with actuator saturation

Yang¹,

Yu²,

Wang³

et al. 2017

International Journal of Advanced Robotic Systems

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“…1 and the notations related to GHV are shown in Fig. 2, according to [24]. ox y z denote the inertia coordinate system, the speed coordinate system and the body axes coordinate system, respectively, m, R and P denote the mass of vehicle, aerodynamic force and propulsion, respectively, , and V represent the attack angle, sideslip angle and velocity, respectively, , and denote the pitch angle, yaw angle and roll angle, respectively.…”

Section: Hypersonic Vehicle Vertical Modelmentioning

confidence: 99%

Comparison of linear and nonlinear active disturbance rejection control method for hypersonic vehicle

Gao

Wang

Yang

2016

2016 35th Chinese Control Conference (CCC)

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This version is available at https://strathprints.strath.ac.uk/56894/ Strathprints is designed to allow users to access the research output of the University of Strathclyde. Unless otherwise explicitly stated on the manuscript, Copyright © and Moral Rights for the papers on this site are retained by the individual authors and/or other copyright owners. Please check the manuscript for details of any other licences that may have been applied. You may not engage in further distribution of the material for any profitmaking activities or any commercial gain. You may freely distribute both the url (https://strathprints.strath.ac.uk/) and the content of this paper for research or private study, educational, or not-for-profit purposes without prior permission or charge.Any correspondence concerning this service should be sent to the Strathprints administrator: strathprints@strath.ac.ukThe Strathprints institutional repository (https://strathprints.strath.ac.uk) is a digital archive of University of Strathclyde research outputs. It has been developed to disseminate open access research outputs, expose data about those outputs, and enable the management and persistent access to Strathclyde's intellectual output. Comparison of linear and nonlinear active disturbance rejection control method for hypersonic vehicle

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“…The memory function and stability characteristic make the fractional order PID controller widely apply in the field of aircraft guidance and control 15,16 , such as pitch loop control of a vertical takeoff and landing Unmanned aerial vehicle (UAV) 17 , roll control of a small fixed-wing uAv 18 , perturbed UAV roll control 19 , hypersonic vehicle attitude control 20 , aircraft pitch control 21 , deployment control of a space tether system 22 , position control of a one-DoF flight motion table 23 , and vibration attenuation to airplane wings 24 . The viscosity of the atmosphere interacting with air vehicles has endued aircrafts the aerodynamics similar to the fractional order systems, thus the fractional order PID control theory is appropriate to design the aircraft guidance and control system.…”

Section: Introductionmentioning

confidence: 99%

Fractional Calculus Guidance Algorithm in a Hypersonic Pursuit-Evasion Game

et al. 2017

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<p class="p1">Aiming at intercepting a hypersonic weapon in a hypersonic pursuit-evasion game, this paper presents a fractional calculus guidance algorithm based on a nonlinear proportional and differential guidance law. First, under the premise of without increasing the complexity degree of the guidance system against a hypersonic manoeuvering target, the principle that the differential signal of the line-of-sight rate is more sensitive to the target manoeuver than the line-of-sight rate is employed as the guidelines to design the guidance law. A nonlinear proportional and differential guidance law (NPDG) is designed by using the differential derivative of the line-of-sight rate from a nonlinear tracking differentiator. By using the differential definition of fractional calculus, on the basis of the NPDG, a fractional calculus guidance law (FCG) is proposed. According to relative motions between the interceptor and target, the guidance system stability condition with the FCG is given and quantitative values are also proposed for the parameters of the FCG. Under different target manoeuver conditions and noisy conditions, the interception accuracy and robustness of these two guidance laws are analysed. Numerical experimental results demonstrate that the proposed guidance algorithms effectively reduce the miss distance against target manoeuvers. Compared with the NPDG, a stronger robustness of the FCG is shown under noisy condition.</p>

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Nonlinear fractional order proportion-integral-derivative active disturbance rejection control method design for hypersonic vehicle attitude control

Cited by 70 publications

References 11 publications

Active disturbance rejection attitude control for a hypersonic reentry vehicle with actuator saturation

Active disturbance rejection attitude control for a hypersonic reentry vehicle with actuator saturation

Comparison of linear and nonlinear active disturbance rejection control method for hypersonic vehicle

Fractional Calculus Guidance Algorithm in a Hypersonic Pursuit-Evasion Game

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