航天器有限时间自适应容错姿态控制

针对存在执行器故障、转动惯量偏差以及外部扰动等系统不确定性的航天器姿态跟踪问题,提出一种有限时间自适应容错姿态控制方法。建立基于四元数的航天器姿态动力学模型、执行器故障模型和系统不确定性模型,并将执行器故障分为乘性故障和加性故障两大类;利用滑模控制和有限时间控制理论设计有限时间姿态控制器,并通过设计自适应变量及更新方法对执行器故障以及系统不确定性引起的控制偏差上界进行估计和补偿,使姿态控制器对故障和扰动具有良好的适应性和鲁棒性。得到的新型有限时间自适应容错姿态控制器能够保证航天器在执行器故障以及系统不确定性条件下在有限时间内精确收敛到期望值。利用Lyapunov稳定性理论证明了系统的渐进稳定性和有限时间稳定性,数值仿真验证了所提出方法的可行性和有效性。     

基于输入成型的挠性航天器自适应姿态控制（英文）

针对快速调姿挠性航天器的姿态控制问题,提出一种基于输入成型的自适应姿态控制方法,解决俯仰、偏航、滚转三通道的控制耦合问题,抑制航天器挠性振动、提高姿态控制精度。首先,建立了考虑弹性振动、执行器故障及惯量不确定性的挠性航天器姿态动力学模型。基于欧拉轴角提出一种姿态机动参考轨迹设计方法,避免了俯仰、偏航、滚转三通道的耦合问题。通过多模输入成型方法对姿态机动参考轨迹进行修正,以抑制航天器弹性振动。采用自适应容错控制方法对修正后的参考轨迹进行跟踪,以实现挠性航天器快速姿态机动任务。数值仿真结果表明,与传统PD姿态控制方法相比,所提出的基于输入成型的挠性航天器自适应姿态控制方法可将残余弹性振动幅值和姿态控制偏差降低两个数量级,验证了该方法的有效性。     

基于Rodrigues参数的陀螺体受控运动

经典刚体动力学中表示刚体姿态的参数中，Euler角、Cardan角和Euler参数在工程技术中使用最为普遍．近期在航天器姿态控制问题中使用Rodrigues参数的报道也引起注意，Rodrigues参数以其表达形式简明和代数运算特点而具有独特优点．航天器姿态控制系统必须具有自适应性以适应参数的变化，建立用Rodrigues参数表达的无力矩陀螺体受控运动方程，提出基于Rodrigues参数的自适应姿态控制方案，并应用Lyapunov定理证明受控运动的渐近稳定性。     

刚弹性耦合的高超声速飞行器自适应有限时间控制

针对高超声速飞行器刚性-弹性耦合动力学特性诱发的再入姿态稳定控制难题,提出了一种具有有限时间收敛功能的自适应积分Lyapunov控制方法。建立了刚性-弹性耦合动力学模型,将弹性模态与外部不确定性视为归一化扰动,构造辅助误差补偿子系统。设计自适应律跟踪归一化扰动,可使姿态跟踪误差在有限时间内收敛,同时增强积分Lyapunov控制方法的鲁棒性。此外,为解决传统反步法控制的“微分爆炸”问题,引入一阶线性滤波器,避免了直接求导,得到了平滑且可执行的控制指令。仿真结果表明：所提控制方法在气动参数摄动±20%的条件下,实现速度跟踪误差不大于0.1 m/s,高度跟踪误差不大于0.5 m,可有效抑制弹性模态和外部扰动对姿态控制的不利影响。     

控制一类磁性刚体航天器的混沌姿态运动

本文研究一类磁性航天器的混沌姿态运动及其控制,建立了在近地球赤道面圆轨道上运动受万有引力矩、磁力矩作用磁性刚体航天器姿态运动的动力学方程。采用时间历程、Poincare截面、Lyapunov指数和功率谱对系统的动力学行为进行数值识别,结果表明随着磁场参数的增大系统动力学行为由准周期环面破裂而出现混沌。利用输入－输出反馈精确线性化的方法将航天器的混沌姿态控制运动控制为姿态静止和按给定的周期规律运动,数值结果表明该控制方法的有效性。     

航天器编队系统相对位置自适应分布式控制

针对具有参数不确定性以及外部扰动的航天器编队飞行队形跟踪控制问题,基于反步控制策略提出了一种能够实现控制有界的自适应编队控制方法。首先建立航天器相对运动的非线性动力学方程,在不考虑外部干扰情况下,利用饱和函数设计了输入有界的自适应协同控制器;之后进一步考虑存在外部干扰的情况,通过估计扰动上界设计了鲁棒自适应协同控制器,并且采用Lyapunov稳定性分析方法证明了控制系统的稳定性。数值仿真结果表明,提出的控制方法能够满足控制受限并实现航天器队形的协同控制,同时在大约100 s误差收敛到0附近,队形跟踪和队形保持的稳态误差分别小于0.002 m和0.005 m。     

一种新型稳定平台伺服控制系统

深入研究了三自由度并串联混合机构稳定平台,设计了一个非线性自适应控制器。考虑到实际系统工作中存在摩擦、负载扰动和动力学参数误差,分离出动力学模型中的未建模动力学参数、摩擦力参数和负载扰动,建立了关于待辨识参数的线性动力学模型。运用Lyapunov方法设计了一个非线性自适应控制器。构建了并串联光电稳定平台伺服系统实验平台。分别将所设计的控制器与计算力矩控制器分别在高速和低速扰动情况进行了实验,实验表明所提出非线性自适应控制器在低速0.006(°)/s时,跟踪精度分别为滚转轴0.071°、俯仰轴0.064°、偏转轴0.038°,在20(°)/s高速状态下,跟踪精度分别为滚转轴0.045°、俯仰轴0.042°、偏转轴0.029°,其控制效果明显好于传统控制。     

空间机械臂关节轨迹跟踪的自适应反演滑模控制

讨论了载体位置、姿态均不受控制情况下,具有外部扰动与参数不确定的自由漂浮空间机械臂系统关节空间轨迹跟踪的控制问题.结合系统动量、动量矩守恒关系及拉格朗日方法,建立了自由漂浮空间机械臂的系统动力学方程.针对外部扰动与参数不确定的情况,提出一种自适应反演滑模控制方案.此控制方案无需要求系统动力学方程关于惯性参数呈线性函数关系;同时,它可保证系统具有全局意义下的渐近稳定性.数值仿真结果证实了该控制方案可有效地消除外部扰动与参数不确定对系统的影响,控制空间机械臂系统各关节按关节空间内的期望轨迹进行运动.     

柔性全充液航天器大角度姿态机动混沌动力学

研究了受液体燃料黏性阻尼及柔性附件扭振影响的全充液航天器由最小惯量轴向最大惯量作大角度姿态机动过程中的混沌姿态动力学, 尤其是液体燃料和柔性附件振动的耦合效应对航天器姿态动力学的影响. 推导了耦合系统的动力学方程并利用尺度化方法将其转化为扰动系统的标准形式以便应用Melnikov方法对系统进行混沌姿态预测.推导了以系统参数形式表达的混沌姿态预测的解析准则. 将利用数值方法所得到的对系统的数值仿真结果与Melnikov解析准则进行了比较和评述. 研究了诸如航天器构型、液体燃料惯量及阻尼、柔性附件固有频率等系统特征量对混沌姿态的影响.      

基于MSCMG大型遥感卫星高精度姿态控制方法

针对大力矩飞轮前馈和闭环反馈补偿复杂、对精度影响敏感性大的问题,提出了基于磁浮控制力矩陀螺闭环补偿的大型遥感卫星高精度姿态控制方法。该方法采用磁悬浮力矩陀螺为控制执行机构,通过变结构反馈补偿控制律设计,建立新的运动补偿控制系统,减小相机和卫星本体耦合效应。基于磁浮力矩陀螺力矩大、反向激励扰动小、精度高的特性,将其应用于对地遥感成像相机运动补偿控制系统中,仿真结果表明,与飞轮前馈补偿相比,姿态稳定度提高了一个数量级,有效提高空间大惯量卫星姿态控制的稳定度,提升相机对地成像质量;研究结果可为甚高精度卫星姿态控制与载荷运动补偿提供参考。     

Attitude tracking control of flexible spacecraft with large amplitude slosh

This paper is focused on attitude tracking control of a spacecraft that is equipped with flexible appendage and partially filled liquid propellant tank. The large amplitude liquid slosh is included by using a moving pulsating ball model that is further improved to estimate the settling location of liquid in microgravity or a zero-g environment. The flexible appendage is modelled as a three-dimensional Bernoulli–Euler beam, and the assumed modal method is employed.A hybrid controller that combines sliding mode control with an adaptive algorithm is designed for spacecraft to perform attitude tracking. The proposed controller has proved to be asymptotically stable. A nonlinear model for the overall coupled system including spacecraft attitude dynamics,liquid slosh, structural vibration and control action is established. Numerical simulation results are presented to show the dynamic behaviors of the coupled system and to verify the effectiveness of the control approach when the spacecraft undergoes the disturbance produced by large amplitude slosh and appendage vibration. Lastly, the designed adaptive algorithm is found to be effective to improve the precision of attitude tracking.     

Combined control of fast attitude maneuver and stabilization for large complex spacecraft

In remote sensing or laser communication space missions, spacecraft need fast maneuver and fast stabilization in order to accomplish agile imaging and attitude tracking tasks. However, fast attitude maneuvers can easily cause elastic deformations and vibrations in flexible appendages of the spacecraft. This paper focuses on this problem and deals with the combined control of fast attitude maneuver and sta- bilization for large complex spacecraft. The mathematical model of complex spacecraft with flexible appendages and momentum bias actuators on board is presented. Based on the plant model and combined with the feedback controller, modal parameters of the closed-loop system are calculated, and a multiple mode input shaper utilizing the modal information is designed to suppress vibrations. Aiming at reducing vibrations excited by attitude maneuver, a quintic polynomial form rotation path planning is proposed with constraints on the actuators and the angular velocity taken into account. Attitude maneuver simulation results of the control systems with input shaper or path planning in loop are sepa- rately analyzed, and based on the analysis, a combined control strategy is presented with both path planning and input shaper in loop. Simulation results show that the combined control strategy satisfies the complex spacecraft＇s require- ment of fast maneuver and stabilization with the actuators＇ torque limitation satisfied at the same time.     

单框架控制力矩陀螺输出特性分析

广泛用于航天领域的单框架控制力矩陀螺,具有力矩放大效应的优点,其理论基础为有假设条件的力矩放大原理.本文不局限于这些假设,不限定工况,解析单框架控制力矩陀螺的输出特性.考虑安装基座的运动,得到具有两维输入三维输出的单框架控制力矩陀螺力矩输出模型,提出将输出力矩分解为可调控与不可调控两部分.为分析单框架控制力矩陀螺的输出...     

航天器有限时间饱和姿态跟踪控制

针对刚体航天器系统,对存在模型不确定性、外界干扰力矩和控制器饱和等条件下的姿态跟踪控制问题进行了研究。首先,考虑未知模型不确定性和外界干扰,且总干扰上界为未知常数,结合快速非奇异终端滑模、快速终端滑模趋近律以及辅助系统构造了基本的鲁棒有限时间饱和控制器,并通过辅助系统直接补偿了控制器饱和;其次,针对系统总干扰具有多项式上界的情形,进一步结合自适应控制算法,对其上界函数中的未知参数进行在线估计,并设计了自适应有限时间饱和控制器。同时,基于Lyapunov稳定性理论证明了所提出控制算法的有限时间收敛特性。最后,通过数值仿真验证所提出控制算法的控制效果,在两种控制器作用下姿态的跟踪精度分别为5×10-5和1×10-5,证明了所提出控制算法的有效性。     

Robust attitude control for rapid multi-target tracking in spacecraft formation flying

A robust attitude tracking control scheme for spacecraft formation flying is presented. The leader spacecraft with a rapid mobile antenna and a camera is modeled. While the camera is tracking the ground target, the antenna is tracking the follower spacecraft. By an angular velocity constraint and an angular constraint, two methods are proposed to compute the reference attitude profiles of the camera and antenna, respectively. To simplify the control design problem, this paper first derives the desired inverse system （DIS）, which can convert the attitude tracking problem of 3D space into the regulator problem. Based on DIS and sliding mode control （SMC）, a robust attitude tracking controller is developed in the presence of mass parameter uncertainties and external disturbance. By Lyapunov stability theory, the closed loop system stability can be achieved. The numerical simulations show that the proposed robust control scheme exhibits significant advantages for the multi-target attitude tracking of a two-spacecraft formation.     

Robust adaptive sliding mode attitude maneuvering and vibration damping of three-axis-stabilized flexible spacecraft with actuator saturation limits

This paper presents a dual-stage control system design method for flexible spacecraft attitude maneuvering control by use of on-off thrusters and active vibration suppression by embedded smart material as actuator. As a stepping stone, an adaptive sliding mode controller with the assumption of knowing the upper bounds of the lumped perturbation is designed that ensures exponential convergence or uniform ultimate boundedness (UUB) of the attitude control system in the presence of bounded parameter variation/disturbances and control input saturation as well. Then this adaptive controller is redesigned such that the need for knowing the upper bound in advance is eliminated. Lyapunov analysis shows that this modified adaptive controller can also guarantee the exponential convergence or UUB of the system. For actively suppressing the induced vibration, linear quadratic regulator (LQR) based positive position feedback control method is presented. Numerical simulations are performed to show that rotational maneuver and vibration suppression are accomplished in spite of the presence of disturbance torque/parameter uncertainty and saturation input.     

Sliding mode maneuvering control and active vibration damping of three-axis stabilized flexible spacecraft with actuator dynamics

This paper presents a dual-stage control system design method for the three-axis-rotational maneuver control and vibration stabilization of a spacecraft with flexible appendages embedded with piezoceramics as sensor and actuator. In this design approach, the attitude control system and vibration suppression were designed separately using a lower order model. Based on the sliding mode control (SMC) theory, a discontinuous attitude control law in the form of the input voltage of the reaction wheel is derived to control the orientation of the spacecraft actuated by the reaction wheel, in which the reaction wheel dynamics is also considered from the real applications point of view. The asymptotic stability is shown using Lyapunov analysis. Furthermore, an adaptive version of the proposed attitude control law is also designed for adapting the unknown upper bounds of the lumped disturbance so that the limitation of knowing the bound of the disturbance in advance is released. In addition, the concept of varying the width of boundary layer instead of a fixed one is also employed to eliminate the chattering and improve the pointing precision as well. For actively suppressing the induced vibration, modal velocity feedback and strain rate feedback control methods are presented and compared by using piezoelectric materials as additional sensors and actuators bonded on the surface of the flexible appendages. Numerical simulations are performed to show that rotational maneuver and vibration suppression are accomplished in spite of the presence of disturbance torque and parameter uncertainty.     

Control of Chaotic Motion in a Spinning Spacecraft with a Circumferential Nutational Damper

Control of chaotic vibrations in a simplified model of a spinning spacecraft with a circumferential nutational damper is achieved using two techniques. The control methods are implemented on a realistic spacecraft parameter configuration which has been found to exhibit chaotic instability when a sinusoidally varying torque is applied to the spacecraft for a range of forcing amplitude and frequency. Such a torque, in practice, may arise in the platform of a dual-spin spacecraft under malfunction of the control system or from an unbalanced rotor or from vibrations in appendages. Chaotic instabilities arising from these torques could introduce uncertainties and irregularities into a spacecraft's attitude and consequently could have disastrous affects on its operation. The two control methods, recursive proportional feedback (RPF) and continuous delayed feedback, are recently developed techniques for control of chaotic motion in dynamical systems. Each technique is outlined and the effectiveness of the two strategies in controlling chaotic motion exhibited by the present system is compared and contrasted. Numerical simulations are performed and the results are studied by means of time history, phase space, Poincaré map, Lyapunov characteristic exponents and bifurcation diagrams.