An Improved Nonlinear Dynamic Inversion Method for Altitude and Attitude Control of Nano Quad-Rotors under Persistent Uncertainties

Nonlinear dynamic inversion(NDI)has been applied to the control law design of quad-rotors mainly thanks to its good robustness and simplicity of parameter tuning.However,the weakness of relying on accurate model greatly restrains its application on quad-rotors,especially nano quad-rotors(NQRs).NQRs are easy to be influenced by uncertainties such as model uncertainties(mainly from complicated aerodynamic interferences,strong coupling in roll-pitch-yaw channels and inaccurate aerodynamic prediction of rotors)and external uncertainties(mainly from winds or gusts),particularly persistent ones.Therefore,developing accurate model for altitude and attitude control of NQRs is difficult.To solve this problem,in this paper,an improved nonlinear dynamic inversion(INDI)method is developed,which can reject the above-mentioned uncertainties by estimating them and then counteracting in real time using linear extended state observer(LESO).Comparison with the traditional NDI(TNDI)method was carried out numerically,and the results show that,in coping with persistent uncertainties,the INDI-based method presents significant superiority.

Novel Logarithmic Non-Singular Terminal Sliding Mode and ItsApplication in Attitude Control of QTR

In this study we mainly focus on the attitude control problem of a quad tilt rotor aircraft with respect to unknown external disturbance. We propose a class of control methods based on a novel logarithmic fast non singular terminal sliding surface a new fast reaching law and extended state disturbance observer. A logarithmic non singular terminal sliding surface is used owing to its convergence in finite time and significant robustness. A fast reaching law with two order characteristics of the sliding mode is designed. This reaching law can be used reduce the convergence time of traditional reaching law. In addition the extended state disturbance observer is utilized for online estimation and to compensate for system disturbance. The simulation experiment results show that the control strategy proposed in this paper outperforms the traditional non singular fast sliding mode control.

Extended State Observer based Attitude Control of a Bird-like Flapping-wing Flying Robot

The attitude control system of a flapping-wing flying robot plays an important role in the precise orientation and tracking of the robot.In this paper,the modeling of a bird-like micro flapping-wing system is introduced,and the design of a sliding mode controller based on an Extended State Observer(ESO)is described.The main design difficulties are the control law and the adaptive law for the attitude control system.To address this problem,a sliding mode adaptive extended state observer algorithm is proposed.Firstly,a new extended state approximation method is used to estimate the final output as a disturbance state.Then,a sliding mode observer with good robustness to the model approximation error and external disturbance is used to estimate the system state.Compared with traditional algorithms,this method is not only suitable for more general cases,but also effectively reduces the influence of the approximation error and interference.Next,the simulation and experiment example is given to illustrate the implementation process.The results show that the algorithm can effectively estimate the state of the attitude control system of the flapping-wing flying robot,and further guarantee the robustness of the model regarding error and external disturbance.

基于主动悬架的整车车身姿态控制策略研究

针对车辆在行驶过程中产生的车身姿态失衡问题,提出了一种基于姿态补偿的主动悬架整车车身姿态控制策略。在建立整车七自由度动力学模型,并基于随机路面进行实车试验验证整车模型的准确性的基础上,构建了模型预测控制器,根据状态观测器估计的各信号求解各个悬架的垂向控制力以衰减车辆垂向振动;进而以模糊算法为基础设计车身姿态补偿控制策略,使电磁直线作动器产生反作用力以抑制车身姿态恶化。选取某型号直线电机作为主动悬架力源,将垂向控制力与姿态补偿力合并得到各悬架控制所需电磁作动力,以此计算电机所需目标电流,并通过MATLAB/Simulink平台对主动悬架系统进行仿真。仿真结果表明:所提出的基于主动悬架的整车车身姿态控制策略在不影响车辆垂向控制效果的基础上,能够大幅降低车辆质心侧倾角和俯仰角的均方根值,车身姿态得到有效控制。

基于NESO-LFDC的四旋翼无人机滑模姿态控制

针对四旋翼无人机姿态控制中存在空气动力学特性复杂,易受干扰的特性,提出一种基于非线性扩张状态观测器(nonlinear extended state observer,NESO)和低频干扰补偿器(low-frequency disturbance compensator,LFDC)的非奇异快速终端滑模控制方法。该方法内环设计了NESO和LFDC结合,以获得干扰补偿值并补偿总干扰的低频分量。在外环设计了跟踪微分器和可变切换增益的非奇异快速终端滑模控制器,用于补偿虚拟干扰估计值的误差和总干扰的高频分量。仿真结果表明,该控制方法可以更好地估计总干扰的低频和高频分量,减少虚拟干扰估计值的误差对四旋翼无人机姿态控制的影响,并提升响应速度。

基于ESO的仿蝙蝠扑翼飞行器姿态控制仿真

针对仿蝙蝠扑翼飞行器的纵向气动特性不稳定、易受扰动的问题,设计了一种基于扩张状态观测器(ESO)的姿态控制方法,实现了扑翼飞行器姿态的稳定与抗干扰控制。首先建立仿蝙蝠扑翼飞行器的动力学模型;进而在该模型基础上分析了扑翼飞行器的纵向稳定性;然后将系统的不确定部分与各种未知的外界扰动作为系统的总扰动,引入ESO模块对总扰动进行实时观测与跟踪;最后在原有的PID控制器中加入扰动补偿环节。数值仿真结果表明,基于ESO的控制算法对于仿蝙蝠扑翼飞行器的控制效果显著优于基于PID的控制方法,阶跃响应的调节时间加快41.27%,对系统输入的白噪声干扰波动峰值从6.02%降低到2.82%,正弦扰动的波动峰值从11.56%降低到3.22%。

Observer-Based Fuzzy Sliding Mode Attitude Control for Flexible Spacecraft

In this paper,the attitude stabilization of flexible spacecraft with umeasurable states and disturhances is adressed by an observer baced fuzay integal sliding modle control scheme.First,a Takagi-Sugeno fuxy modlel of flexible spacecraft is establisbed and an obeerver is propoeed based on this modeL The covengence conditions of the estimation errors are given by Lyapunow function and the gains of the observer are thus determinedl.Acoording to the obtained estimates,a novel fuxy slidling mode control strategy is designed to compensate the infuence of disturbance.F nally,an example of flexible spacecnaft is employed to venify the effectivenes of the propoeed obeerver and control law.

基于改进自抗扰的涵道无人机姿态控制

为解决涵道无人机在狭窄空间下易受紊乱气流影响,导致姿态控制系统鲁棒性能差、控制精度低等问题,以自主研发的共轴双旋翼涵道无人机为研究对象,进行运动学和动力学建模,在此基础上考虑建模的误差和飞行过程中存在的外部干扰,采用PID和自抗扰控制串联的方法设计涵道无人机的姿态控制系统,并通过搭建仿真模型,对涵道无人机在理想情况和有紊流风场扰动情况下进行仿真对比测试,最后在真机上进行飞行试验。结果表明,所设计的姿态控制系统具有良好的鲁棒性和抗干扰性能。

Solid Rocket Booster Thrust Asynchrony Identification Method for Solid Rocket Bundled Rockets With ESO

The role of the rocket attitude control system is to execute the required maneuvers for guidance and ensure the stability of the rocket's flight attitude. Attitude control technology has always been one of the key technologies for ensuring the success of rocket flights and has been a core topic in carrier rocket technology research. The Gravity-1 solid carrier rocket is the first solid rocket bundled rocket developed by China, adopting a configuration with four boosters and a core stage bundled together. During the actual flight process, the four booster engines are ignited first, and then, in the event of insufficient control force from the boosters, the core stage engine is ignited to participate in control. To address thrust asynchrony during the descent of the four boosters, an Extended State Observer(ESO) is employed in the control scheme for this flight segment. This involves real-time estimation and compensation of attitude parameters during flight, identification of thrust asynchrony among the boosters, and simultaneous determination of whether the core stage engine is ignited to participate in control.Through six degrees of freedom simulation analysis and Y1 flight test validation, this method has been proven to be correct and feasible.

基于ESO的车载并联稳定平台快速非奇异终端滑模控制

针对车载并联稳定平台受到多源干扰影响姿态稳定问题,提出了一种线性扩张状态观测器复合快速非奇异终端滑模控制方案。首先,建立并联稳定平台系统模型;然后,设计姿态环扩张状态观测器对系统多源干扰进行扰动估计,基于干扰估计值设计姿态环复合快速非奇异终端滑模控制器;接着,基于李雅普诺夫定理证明快速非奇异终端滑模控制器的稳定性;最后,在车载并联稳定平台上完成所设计控制器的仿真和实验验证。结果表明:所设计的控制器提升了车载并联稳定平台姿态控制的响应速度和抗干扰性能。

Fully Actuated System Approach for 6DOF Spacecraft Control Based on Extended State Observer

This paper deals with the problem of position and attitude tracking control for a rigid spacecraft.A fully actuated system(FAS)model for the six degree-of-freedom(6DOF)spacecraft motion is derived first from the state-space model by variable elimination.Considering the uncertainties from external disturbance,unknown motion information,and uncertain inertia properties,an extended state observer(ESO)is designed to estimate the total disturbance.Then,a tracking controller based on FAS approach is designed,and this makes the closed-loop system a constant linear one with an arbitrarily assignable eigenstructure.The solution to the parameter matrices of the observer and controller is given subsequently.It is proved via the Lyapunov stability theory that the observer errors and tracking errors both converge into the neighborhood of the origin.Finally,numerical simulation demonstrates the effectiveness of the proposed controller.

基于改进ADRC的四旋翼姿态控制器设计

针对四旋翼无人机姿态自抗扰控制(ADRC)系统应对复杂干扰时,基于传统fal函数设计的扩张状态观测器(ESO)抗扰动能力不足、易产生抖振的问题,提出一种改进型ADRC并用于四旋翼姿态控制。基于正弦函数构建一种新型光滑非线性xfal函数以改进ESO,利用Lyapunov函数对改进ESO的稳定性进行证明。通过仿真平台,与其他ADRC进行比较。实验结果表明:改进型ADRC和标准ADRC相比,当四旋翼无人机不受干扰时,在其抖振区间内,俯仰角均方误差降低了约38.7%;当四旋翼无人机分别受到连续干扰、突发干扰、复杂干扰时,在各自计算区间内,俯仰角均方误差分别降低了约78.4%、80.2%、83.3%。因此,改进型ADRC在有效减小抖振的同时,还具备优良的抗干扰能力。

基于相位校正LESO的飞行器姿态控制

高速飞行器主动段飞行过程中由于质心、压心、动压、舵效等高动态变化带来飞行器气动参数不确定性大、通道耦合严重及外干扰强非线性等特点,从而使得飞行器主动段的高精度稳定控制成为一项难题。研究了一种基于相位校正的扩张状态观测器的高精度强鲁棒姿态控制方法解决了上述难题,并重点针对扩张状态观测器参数配置难、依赖大增益的问题进行研究。首先,通过干扰估计量的传递函数分析了线性扩张状态观测器的干扰补偿原理,并从频域角度上的分析指出其干扰估计误差来源于相角滞后。接着通过降阶和安排相位校正网络对线性扩张观测器进行改进,保证在较小的增益系数下估计能力得到提升。仿真结果表明了上述方法的有效性。

基于单位四元数的锚杆钻车铺网单元控制方法

针对现有铺网过程仍需人工手动操作、人工成本高、危险系数高、作业效率低等问题,提出了一种基于单位四元数的锚杆钻车铺网单元控制方法,通过对铺网单元机械手爪进行基于单位四元数的姿态建模,设计了扩张状态观测器完成自抗扰控制,并对所设计的控制系统进行了仿真验证。结果表明,该方法使网片运输和安装到目标位置的过程实现了自动化,并在遭受扰动时能很快回归稳态,为实现井下锚护过程自动化打下坚实的基础。

Data-driven model-free adaptive attitude control of partially constrained combined spacecraft with external disturbances and input saturation

This study presents an improved data-driven Model-Free Adaptive Control(MFAC)strategy for attitude stabilization of a partially constrained combined spacecraft with external disturbances and input saturation. First, a novel dynamic linearization data model for the partially constrained combined spacecraft with external disturbances is established. The generalized disturbances composed of external disturbances and dynamic linearization errors are then reconstructed by a Discrete Extended State Observer(DESO). With the dynamic linearization data model and reconstructed information, a DESO-MFAC strategy for the combined spacecraft is proposed based only on input and output data. Next, the input saturation is overcome by introducing an antiwindup compensator. Finally, numerical simulations are carried out to demonstrate the effectiveness and feasibility of the proposed controller when the dynamic properties of the partially constrained combined spacecraft are completely unknown.

基于改进型自抗扰控制的四旋翼无人机姿态控制系统研究

针对四旋翼无人机姿态控制系统在外界干扰下,跟踪精度和抗扰动性能易受到影响的问题,提出一种改进型自抗扰控制(ADRC)算法。首先,基于原点平滑性和连续性考虑设计了改进型非线性函数。其次,基于线性扩张状态观测器(LESO)和非线性扩张状态观测器(NLESO)各自的优点,设计了线性/非线性可切换的改进型扩张状态观测器(IESO)。最后,基于IESO设计了改进型ADRC,将其应用于四旋翼无人机姿态控制系统,并从响应速度、跟踪精度、抗干扰能力三方面对其进行仿真实验验证。实验结果显示,IESO具有更好的观测效果,改进型ADRC的控制性能比传统的线性ADRC和非线性ADRC更优。

基于改进ESO的反馈线性化四旋翼无人机姿态控制

针对四旋翼飞行器非线性、强耦合的特性以及存在建模误差和未知扰动下姿态控制问题,提出了一种改进自抗扰控制方案。利用反馈线性化方法将无人机姿态动力学模型转化为线性模型,减少了小扰动假设带来的系统误差;改进了扩张状态观测器(ESO)的结构,使其能同时利用角度和角速度的测量信息,提高了其对时变扰动的估计精度;基于改进ESO完成了自抗扰控制器的设计并证明了该控制系统的稳定性。仿真实验结果表明,基于改进ESO的自抗扰控制器具有更强的抗干扰性和鲁棒性。

离散型自抗扰控制器在四旋翼飞行姿态控制中的应用

本文首先介绍了自抗扰控制器的结构组成,包括跟踪微分器、扩张状态观测器以及非线性状态误差反馈律,及各部分的典型算法.针对四旋翼盘旋系统的姿态控制问题,设计了3种离散型自抗扰控制器,搭建了仿真结构图,并进行了参数整定,得到了优良的仿真结果.进而在实际装置上进行试验,调试出了令人满意的姿态实时控制结果.实时控制结果表明,文中所设计的自抗扰控制器可以满足控制精度及快速性的要求,并且具有抗干扰性能、稳定控制能力以及对非线性强耦合系统的解耦能力.最后,总结并分析了3种自抗扰控制器的优缺点及适用范围.

串级自抗扰控制器在纵列式双旋翼直升机飞行姿态控制中的应用

本文将自抗扰控制应用于直升机飞行姿态控制中,针对纵列式双旋翼直升机的飞行姿态控制问题,设计串级自抗扰控制器,并进行了参数整定,得到了优良的仿真结果.进而在实际装置上,调试出了令人满意的飞行姿态实时控制结果.对比于线性二次型调节器(linear quadratic regulator,LQR)控制算法,文中所设计的串级自抗扰控制器显然具有更加精准的控制精度,能更加满足快速性的要求,并且更具有鲁棒性、抗干扰性能以及对非线性强耦合系统的解耦能力.

含扩张状态观测器的高超声速飞行器动态面姿态控制

针对高超声速飞行器复杂非线性、高不确定性和强通道耦合等特点,提出了一种飞行器姿态控制的非线性设计方法。根据高超声速飞行器无动力飞行的姿态运动方程组,给出一个可面向姿态控制的非线性设计模型。针对一类非线性系统,提出了一种基于扩张状态观测器(ESO)的动态逆设计方法,并通过动态面控制理论,将其应用于高超声速飞行器的三通道姿态控制中。仿真结果表明,相比基于传统动态逆的动态面控制方案,本文所提出的控制方案可以保证飞行器快速、精确地跟踪角位置指令,并且具备针对系统不确定性的强鲁棒性能。