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

Fu, Bangsheng; Qi, Hui; Xu, Jiangtao; Yong, Yang; Wang, Shaobo; Gao, Quanxi

doi:10.3390/app9235113

Cited by 7 publications

(4 citation statements)

References 24 publications

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“…Where𝐽 𝐽 / is the moment of inertia further converted to the motor. When the inductance parameters are further ignored, the form is the simplified rigid model adopted in [12][13][14].…”

Section: Modeling and Analysis Of Ema Considering Elasticity 211 Mode...mentioning

confidence: 99%

Vibration Suppression of Electromechanical Actuator Considering Backlash Nonlinearity

Qian²,

Xu³

et al. 2022

J. Phys.: Conf. Ser.

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As an electromechanical drive system, nonlinear factors are unavoidable in electromechanical actuator (EMA). In this paper, elasticity of shaft and backlash nonlinearity are considered in the model, the effects of elasticity and backlash on EMA are analyzed. In order to suppress the vibration caused by nonlinearity and elasticity, A nonlinear control method based on backstepping method is proposed. The simulation results show that this method can eliminate the limit cycle oscillation (LCO) caused by backlash, and effectively suppress the vibration.

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Section: Modeling and Analysis Of Ema Considering Elasticity 211 Mode...mentioning

confidence: 99%

Vibration Suppression of Electromechanical Actuator Considering Backlash Nonlinearity

Qian²,

Xu³

et al. 2022

J. Phys.: Conf. Ser.

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“…Пошук C W , що задовольняє (9), здійснюється за допомогою алгоритму, що використовує 2-Ріккаті підхід [18]. Для об'єкта з передатними функціями (8), отримаємо вираз коригуючого пристрою у просторі станів: С и с т е м и т а п р о ц е с и к е р у в а н н (11) При цьому критерій якості (9) досяг значення 0,97. Запас стійкості за амплітудою становив 14,9 дБ, за фазою -74°.…”

Section: синтез динамічного робастного регулятораunclassified

Development and study of a supersonic aircraft flight control laws in a turbulent atmosphere

Gladychkevych,

Burnashev

2022

MGS

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A dynamic robust regulator as well as proportional regulators of the motion parameters of a supersonic unmanned aerial vehicle for operation in strong wind conditions has been developed. At that, we obtained a robust regulator based on the minimization of the four-block quality criterion using the 2-Rikkati approach. For the synthesis of proportional regulators the Kalman-Letov functional was used. We calculated the parameters of the dynamic robust regulator at one point of the trajectory. They are unchanged from the start to the touchdown of the aircraft. The coefficients of the proportional regulator for the entire flight are changed four times. In the article we compare the transient processes quality and the control accuracy in all sections of the flight trajectory. The accuracy of the flight end point position is also considered. For this purpose we presented simulation modelling results of the control system operation. They show that both types of regulator provide stable motion of the aircraft in stormy wind conditions. However, the robust regulator using lead to a higher quality of the control system dynamic properties, and the proportional regulator provides higher accuracy at the final flight stage due to the astatic properties.

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“…To improve the performance of the missile in the ascent phase, Ref. [21] utilized the ADRC to simplify the complex nonlinear time-varying process, including nonlinear dynamics of the actuator and wind disturbance into a linear time-invariant one, which can be compensated directly.…”

Section: Introductionmentioning

confidence: 99%

A Camera Stabilized Platform Based on the Feedforward Strap-Down Control with Approximate Dead-Zone Model and a Compensator with LESO

Gao

Guan

et al. 2023

Machines

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A feedforward strap-down control with a compensator base on the linear extended state observer (LESO) is proposed for a miniaturized camera stabilized platform, which reduces the influence of the dead zone in speed regulation and uncertainties in parameters to reduce the level of angular bias to the field of vision (FOV) in a low-cost stabilized platform. Firstly, the feedforward control is inspired by an approximate linear model proposed for the dead zone to improve the response velocity of the system when tracking the varying reference. Then, the compensator, combining the LESO and proportional differential (PD) law, is designed to eliminate the disturbances including the model bias in the dead zone, inaccuracy in the plant model, and external disturbance. Moreover, the observation performance of the LESO is improved by a preprocessor based on a tracking differentiator (TD) to deal with the time delay and nonlinearities in sampling the state variables. Meanwhile, the complex and uncertain control plant is also simplified by an approximate model combining a disturbance compensator for practical application. Finally, the feasibility of the proposed controller is verified and analyzed by the simulation, and its effectiveness is simultaneously validated by the 2-DOF camera stabilized platform.

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

Cited by 7 publications

References 24 publications

Vibration Suppression of Electromechanical Actuator Considering Backlash Nonlinearity

Vibration Suppression of Electromechanical Actuator Considering Backlash Nonlinearity

Development and study of a supersonic aircraft flight control laws in a turbulent atmosphere

A Camera Stabilized Platform Based on the Feedforward Strap-Down Control with Approximate Dead-Zone Model and a Compensator with LESO

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