基于SO(3)的多四旋翼无人机编队协同控制

针对多四旋翼无人机系统的编队飞行问题,提出了基于特殊正交群SO(3)的协同控制设计方法.在给出编队空间队形和通信拓扑描述后,建立了多四旋翼无人机系统SO(3)控制模型.由于SO(3)与传统俯仰/偏航/滚转三通道模型具有不同的结构,文中进一步研究了SO(3)中无人机之间相对误差的表示方法,设计了适用于多飞行器的SO(3)控制器实现对编队和姿态的协同控制.推力控制器用于调节无人机的位置与速度,并在此基础上构造旋转矩阵形式的姿态协同指令.文中相应设计了SO(3)姿态控制器用于实现指令跟踪,最后从理论上对协同稳定性进行了分析.提出的控制方法能够使得多四旋翼无人机形成期望的队形,并且保持姿态一致进行稳定飞行.仿真结果验证了本文方法的有效性.     

基于单位四元数的Stewart 机构姿态工作空间研究

以单位四元数描述刚体的姿态,避免了欧拉角描述刚体姿态的奇异性问题,推导出Stewart 机构 处于给定位置时的姿态奇异表达式．提出了该机构处于给定位置时的非奇异姿态工作空间概念及其算法, 并 以非奇异姿态工作空间边界曲面的最小内切球作为实际姿态工作空间,以该球半径大小作为衡量机构处于给 定位置时的实际姿态能力的性能指标．给定该机构的具体结构参数,描述了该机构处于某给定位置时的非奇 异姿态工作空间,并进一步描述了在机构“初始姿态”的位置工作空间内实际姿态能力随位置不同而变化的 情况．     

多刚体动力学仿真的李群变分积分算法

刚体的构形可用其质心位置和姿态矩阵描述.刚体的位置可以在欧几里得空间中表示，但是其姿态矩阵是在李群上演化的.由于李群独特的非线性性质，基于欧氏空间的多体动力学建模与数值算法难以完全真实地描述系统的动力学特性，特别是长时间历程的动力学特性.本文基于几何力学理论，首先根据离散Hamilton变分原理与离散Legendre变换，建立了多刚体系统的Hamilton体系李群变分积分公式.其次，给出李群变分积分公式的两种离散格式：一般离散格式和RATTLie离散格式.最后，采用这两种不同离散格式构建的算法计算了重力作用下空间刚体双摆的动力学问题，对比研究了算法在保持系统群结构、系统能量等方面的性质.计算结果表明，RATTLie离散格式较一般格式精度更高，且能更好地保持系统群结构与能量.     

欠驱动刚体航天器姿态机动滑模控制研究

针对欠驱动刚体航天器的姿态机动控制问题,提出一种滑模变结构姿态控制器的设计方法.首先给出3轴稳定的欠驱动航天器姿态动力学和运动学模型,分析其模型特点;然后,设计了欠驱动刚体航天器的渐近稳定滑模控制律,并证明了其李雅普诺夫意义下的全局渐近稳定性.最后的仿真结果表明,该方法能够有效实现欠驱动航天器的姿态控制,且系统具有全局稳定性和鲁棒性.     

输入受限下的无人机编队控制方法研究

针对多旋翼飞行器在轨迹跟踪过程中控制输入受限的问题，设计了一种控制输入受限下的四旋翼无人机协同编队分布式控制算法。首先，对于外环位置子系统，基于线性矩阵不等式的方法，设计了输入受限下的多旋翼飞行器的编队控制律，使得所有无人机的位置收敛到所需的编队模式。其次，对于内环姿态子系统，采用基于双曲正切的方法设计控制输入受限的控制律，使多无人机的姿态趋于一致。最后，基于Lyapunov稳定性理论，证明了系统的稳定性，仿真结果表明，所设计的控制器能够达到良好的协同跟踪控制效果。     

基于虚拟样机技术的空间机器人系统的建模与仿真

首次采用虚拟样机技术对空间机器人系统进行建模和仿真,得出了反映机器人与卫星本体间运动学和动力学耦合情况的一些重要结果、为保持本体姿态稳定和驱动机器人按预定轨迹运动所需的控制力矩等．该方法可方便地用于验证固定基座、自由飞行、自由飘浮机器人的路径规划、控制算法、奇异空间等．与其它建模和仿真方法相比,该方法建模简单、可视化强、后处理功能极其强大,可实现多刚体系统闭环控制的仿真．     

非线性广义最小方差控制律综述

如何设计简单的控制策略对复杂非线性系统进行控制是控制界还未解决的难题．非线性广义最小方差控制律的提出使得非线性控制器的设计可以基于更为一般的非线性模型，并且控制器易于实现．整个系统包含时滞环节，稳定的非线性输入子系统和一个可以用多项式或者状态空间描述的子系统．通过最小化由误差加权项、状态加权项和输入加权项组成的信号的方差得到优化控制器．在系统为开环稳定的情况下，可用史密斯预估器进行控制．本文首先介绍了非线性广义最小方差控制的发展进程，然后综述了基于状态空间和多项式描述的系统的非线性广义最小方差控制器的设计以及其现状和今后的发展方向．     

基于滑模控制的3D刚体摆姿态稳定性

研究3D刚体摆姿态稳定性的滑模控制问题.3D刚体摆由一个刚体绕一固定且无摩擦的支点旋转,刚体受到恒重力作用且具有三个转动自由度.针对3D刚体摆平衡位置处的姿态稳定控制问题,设计了滑模控制器并分析了角速度和姿态的渐进稳定性.由Lyapunov直接法找出了各个滑模系数取值的充分条件,并通过数值仿真实验验证了滑模控制方法的有效性.     

多技术系统基于VHDL-AMS的统一建模与仿真技术研究

机电一体化系统设计要求跨领域的统一建模与仿真，多刚体动力学是其中的一个难点．通常的做法是采用动力学专用软件建模，求得DAEs形式的运动方程后再转化为集成环境中的统一建模语言．首先基于广义基尔霍夫网络理论，提出了基于端口的多技术系统集成组件，并采用VHDL—AMS混合系统建模语言进行描述．为了更有效的集成多刚体动力学，通过选取参考基作为端点，构造了计算多刚体系统动力学的广义基尔霍夫网络模型，具体阐述了基本组件的VHDL-AMS行为模型，从而将多刚体系统纳入基于VHDL—AMS的集成设计和仿真环境中．最后用一个实例进行了具体说明．     

欠驱动刚体航天器姿态运动规划的遗传算法

研究欠驱动刚体航天器姿态的非完整运动规划问题．航天器利用3个动量飞轮可以控制其姿态和任意定位,当其中一轮失效,航天器姿态通常表现为不可控．在系统角动量为零的情况下,系统的姿态控制问题可转化为无漂移系统的运动规划问题．基于优化控制理论,提出了求解欠驱动刚体航天器的姿态运动控制遗传算法,并且数值仿真表明：该方法对欠驱动航天器姿态运动的控制是有效的．     

The leader-following attitude control of multiple rigid spacecraft systems

In this paper, we consider the leader-following consensus problem for a multiple rigid spacecraft system whose attitude is represented by the unit quaternion. Most results on this problem rely on the assumption that every follower can access the state of the leader and are obtained via a decentralized control manner. By developing a nonlinear distributed observer for the leader system, we can solve this problem via a distributed control scheme under the mild assumptions that the state of the leader can reach every follower through a path and that the communication between followers is bidirectional. Moreover, our result can accommodate a class of desired angular velocities generated by a marginally stable linear autonomous system.     

Almost global finite‐time stabilization of rigid body attitude dynamics using rotation matrices

This work considers continuous finite‐time stabilization of rigid body attitude dynamics using a coordinate‐free representation of attitude on the Lie group of rigid body rotations in three dimensions, SO(3). Using a Hölder continuous Morse–Lyapunov function, a finite‐time feedback stabilization scheme for rigid body attitude motion to a desired attitude with continuous state feedback is obtained. Attitude feedback control with finite‐time convergence has been considered in the past using the unit quaternion representation. However, it is known that the unit quaternion representation of attitude is ambiguous, with two antipodal unit quaternions representing a single rigid body attitude. Continuous feedback control using unit quaternions may therefore lead to the unstable unwinding phenomenon if this ambiguity is not resolved in the control design, and this has adverse effects on actuators, settling time, and control effort expended. The feedback control law designed here leads to almost global finite‐time stabilization of the attitude motion of a rigid body with Hölder continuous feedback to the desired attitude. As a result, this control scheme avoids chattering in the presence of measurement noise, does not excite unmodeled high‐frequency structural dynamics, and can be implemented with actuators that can only provide continuous control inputs. Numerical simulation results for a spacecraft in low Earth orbit, obtained using a Lie group variational integrator, confirm the theoretically obtained stability and robustness properties of this attitude feedback stabilization scheme. Copyright © 2015 John Wiley & Sons, Ltd.     

Attitude control without angular velocity measurement: a passivityapproach

It is well known that the linear feedback of the quaternion of the attitude error and the angular velocity globally stabilizes the attitude of a rigid body. In this note, we show that the angular velocity feedback can be replaced by a nonlinear filter of the quaternion, thus removing the need for direct angular velocity measurement. In contrast to other approaches, this design exploits the inherent passivity of the system; a model-based observer reconstructing the velocity is not needed. An application of the proposed scheme is illustrated for the robot control problem. Simulation results are included to illustrate the theoretical results     

Finite‐time angular velocity observers for rigid‐body attitude tracking with bounded inputs

The attitude tracking of a rigid body without angular velocity measurements is addressed. A continuous angular velocity observer with fractional power functions is proposed to estimate the angular velocity via quaternion attitude information. The fractional power gains can be properly tuned according to a homogeneous method such that the estimation error system is uniformly almost globally finite‐time stable, irrespective of control inputs. To achieve output feedback attitude tracking control, a quaternion‐based nonlinear proportional‐derivative controller using full‐state feedback is designed first, yielding uniformly almost globally finite‐time stable of the attitude tracking system as well as bounded control torques a priori. It is then shown that the certainty equivalent combination of the observer and nonlinear proportional‐derivative controller ensures finite‐time convergence of the attitude tracking error for almost all initial conditions. The proposed methods not only avoid high‐gain injection, as opposed to the semi‐global results, but also overcome the unwinding problem associated with some quaternion‐based observers and/or controllers. Numerical simulations are presented to verify the effectiveness of the proposed methods. Copyright © 2016 John Wiley & Sons, Ltd.     

Distributed attitude and translation consensus for networked rigid bodies based on unit dual quaternion

This paper provides unified solutions for distributed attitude and translation consensus problems for networked fully actuated rigid bodies under the fixed and undirected communication topology with the tool of unit dual quaternion. We investigate two kinds of consensus, that is, leaderless consensus and leader‐following consensus with a static leader. Firstly, the dynamics of rigid bodies are presented by unit dual quaternion. The control inputs of rigid bodies are also obtained from unit dual quaternion. Secondly, we propose a distributed consensus law in the form of dual quaternion to guarantee that the attitudes and translations of all rigid bodies reach consensus, respectively, without a leader. Thirdly, the leader‐following consensus problem with a static leader is studied. With the proposed leader‐following consensus law, the states of all rigid bodies converge to the corresponding states of the static leader, including the attitude and the translation. Finally, numerical examples are provided to validate the effectiveness of the theoretical results. Copyright © 2017 John Wiley & Sons, Ltd.     

Time-varying formation control with attitude synchronization of multiple rigid body systems

In this article, we study the leader-following formation control problem for a group of rigid body systems whose followers' motions are described by dual quaternion equations. A few features are as follows. First, we introduce an exosystem to generate the leader's trajectory as well as the formation configuration, which can produce a large class of time-varying signals so that we can achieve a variety of time-varying formations. Second, to overcome the communication constraint described by a digraph, we extend the distributed observer to estimate not only the desired attitude and angular velocity but also the leader's position and linear velocity. Third, a novel distributed control law is synthesized to furnish a rigorous performance analysis of the closed-loop system. The effectiveness of our design is illustrated by a numerical example.     

Finite-time Attitude Control: A Finite-time Passivity Approach

This paper studies the finite-time attitude control problem for a rigid body. It is known that linear asymptotically stabilizing control laws can be derived from passivity properties for the system which describes the kinematic and dynamic motion of the attitude. Our approach expands this framework by defining finite-time passivity and exploring the corresponding properties. For a rigid body, the desired attitude can be tracked in finite time using the designed finite-time attitude control law. Some finitetime passivity properties for the feedback connection systems are also shown. Numerical simulations are provided to demonstrate the effectiveness of the proposed control law.      

Linearization of attitude-control error dynamics

Some useful properties of direction-cosine and quaternion attitude formulations that include specification of attitude error and the inversion of rigid-body rotational dynamics are reviewed. The inversion procedure is then applied to a measure of attitude error to realize a new model-follower control system that exhibits linear attitude-error dynamics. Error analyses and simulation results for spacecraft attitude-control systems are presented to demonstrate the more robust performance obtainable from an exact linear-error formulation over that obtained from either direction-cosine or quaternion formulations with simple linear feedback control laws     

The attitude control problem

A general framework for the analysis of the attitude tracking control problem for a rigid body is presented. A large family of globally stable control laws is obtained by using the globally nonsingular unit quaternion representation in a Lyapunov function candidate whose form is motivated by the consideration of the total energy of the rigid body. The controllers share the common structure of a proportional-derivative feedback plus some feedforward which can be zero (the model-independent case), the Coriolis torque compensation, or an adaptive compensation. These controller structures are compared in terms of the requirement on the a priori model information, guaranteed transient performance, and robustness. The global stability of the Luh-Walker-Paul robot end-effector controller is also analyzed in this framework