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A review on DFACS(I):System design and dynamics modeling

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Chinese Journal of Aeronautics 2024年第5期37卷 92-119页

作者： Bohan JIAO Qifan LIU Zhaohui DANG xiaokui yue Yonghe ZHANG Yuanqing XIA Li DUAN Qinglei HU Chenglei yue Pengcheng WANG Ming GUO Zhansheng DUAN Bing CUI Chu ZHANG Xiaodong SHAO School of Astronautics Northwestern Polytechnical UniversityXi’an 710072China Innovation Academy for Microsatellites Chinese Academy of SciencesShanghai 710699China School of Automation Beijing Institute of TechnologyBeijing 100081China Institute of Mechanics Chinese Academy of SciencesBeijing 710043China School of Automation Science and Electrical Engineering Beihang UniversityBeijing 100191China School of Automation Science and Engineering Xi’an Jiaotong UniversityXi’an 710049China

The Drag-Free and Attitude Control System(DFACS)is a critical platform for various space missions,including high precision satellite navigation,geoscience and gravity field measurement,and space scientific *** paper presents a comprehensive review of over sixty years of research on the design and dynamics model of ***,we examine the open literature on DFACS and its applications in Drag-Free missions,providing readers with necessary background information on the ***,we analyze the system configurations and main characteristics of different DFACSs,paying particular attention to the coupling mechanism between the system configuration and dynamics ***,we summarize the dynamics modeling methods and main dynamics models of DFACS from multiple perspectives,including common fundamentals and specific ***,we identify current challenges and technological difficulties in the system design and dynamics modeling of DFACS,while suggesting potential avenues for future *** paper aims to provide readers with a comprehensive understanding of the state-of-the-art in DFACS research,as well as the future prospects and challenges in this field.

关键词： Drag-Free DFACS System Design Dynamics Modeling Control design

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重构谐波平衡法及其求解复杂非线性问题应用

力学学报 2024年第1期56卷 212-224页

作者：代洪华王其偲严子朴岳晓奎西北工业大学航天学院西安710072 航天飞行动力学技术国家级重点实验室西安710072

谐波平衡法是求解非线性动力学系统周期解的最常用方法,但对非线性项进行高阶近似需要庞杂的公式推导,限制了该方法的超高精度解算.通过对频域非线性量的时域等价重构,提出了重构谐波平衡法(RHB法),解决了经典谐波平衡法超高阶次计算难... 详细信息

谐波平衡法是求解非线性动力学系统周期解的最常用方法,但对非线性项进行高阶近似需要庞杂的公式推导,限制了该方法的超高精度解算.通过对频域非线性量的时域等价重构,提出了重构谐波平衡法(RHB法),解决了经典谐波平衡法超高阶次计算难题.然而,上述两种方法均要求动力学系统为多项式型非线性,且无法直接用来求解非线性系统的拟周期解.针对上述问题,文章提出一种将RHB法和复杂非线性系统等价重铸法相结合的计算方法,首先将一般非线性问题无损重铸为多项式型非线性系统,然后用RHB法进行高精度求解;针对拟周期响应求解问题,提出基于“补频”思想的RHB方法,通过基频的优化筛选,实现拟周期响应的快速精准捕捉.选取非线性单摆、相对论谐振子和非线性耦合非对称摆等典型系统进行仿真计算,仿真结果表明,所提出的RHB-重铸法在解非多项式型非线性系统的稳态响应时精度保持为10^(-12)量级,达计算机精度,远超现有方法水平.补频RHB法则实现了对拟周期问题的高效解算,拓宽了方法对真实物理响应的求解范围.

关键词：非多项式型非线性系统重构谐波平衡法微分方程重铸非线性单摆拟周期响应

Full-State-Constrained Non-Certainty-Equivalent Adaptive Control for Satellite Swarm Subject to Input Fault

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IEEE/CAA Journal of Automatica Sinica 2022年第3期9卷 482-495页

作者： Zhiwei Hao xiaokui yue Haowei Wen Chuang Liu National Key Laboratory of Aerospace Flight Dynamics School of AstronauticsNorthwestern Polytechnical UniversityXi’an 710072China IEEE

Satellite swarm coordinated flight(SSCF)technology has promising applications,but its complex nature poses significant challenges for control *** response,this paper proposes an easily solvable adaptive control scheme to achieve high-performance trajectory tracking of the SSCF system subject to actuator efficiency losses and external *** existing adaptive controllers based on the certaintyequivalent(CE)principle show unpredictability and nonconvergence in their online parameter *** overcome the above vulnerabilities and the difficulties caused by input failures of SSCF,this paper proposes an adaptive estimator based on scaling immersion and invariance(I&I),which reduces the computational complexity while improving the performance of the parameter ***,a barrier Lyapunov function(BLF)is applied to satisfy both the boundedness of the system states and the singularity avoidance of the *** is proved that the estimator error becomes sufficiently small to converge to a specified attractive invariant manifold and the closed-loop SSCF system can obtain asymptotic stability under full-state ***,numerical simulations are performed for comparison and analysis to verify the effectiveness and superiority of the proposed method.

关键词： Dynamic scaling full-state constraints input faulttolerance non-CE adaptive control satellite swarm

Preface:Nonlinear Computational and Control Methods in Aerospace Engineering

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Computer Modeling in Engineering & Sciences 2020年第1期122卷 1-4页

作者： Honghua Dai xiaokui yue College of Astronautics Northwestern Polytechnical UniversityXi’an710072China

In practice,almost all real engineering systems are essentially *** systems are just idealized models that approximate the nonlinear systems in a prescribed situation subject to a certain *** nonlinearity is included,analytical solutions are rarely available for almost all real ***,nonlinear computational methods are becoming *** most aerospace problems,however,a relatively high-fidelity nonlinear model has to be established,especially when the system is immersing in a complicated environment and nonlinearity is not negligible *** complex phenomena,i.e.,bifurcation,limit cycle oscillation,chaos,turbulence,may occur in a variety of aerospace systems,which may be described by nonlinear Ordinary Differential Equations(ODEs)for rigid body problems or Partial Differential Equations(PDEs)for flexible solids or fluid mechanics *** general,nonlinearity in aerospace systems is often regarded as unwanted and troublemaker,due to the fact that considering nonlinearity makes the solution methods as well as the control methods more ***,there has been a general tendency to circumvent,design around them,control them,or simply ignore them.

关键词： nonlinearity nonlinear negligible

Review of control and guidance technology on hypersonic vehicle

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Chinese Journal of Aeronautics 2022年第7期35卷 1-18页

作者： Yibo DING xiaokui yue Guangshan CHEN Jiashun SI School of Astronautics Northwestern Polytechnical UniversityXi’an 710072China Shanghai Aerospace Control Technology Institute Shanghai 201109China Beijing Reserarch Institute of Automation for Machinery Industry Co. LTD.Beijing 100124China

Air-breathing hypersonic vehicle has great military and potential economic value due to its characteristics:high velocity,long range,quick ***,the development of hypersonic vehicle and its guidance and control technology are reviewed in this ***,the development and classification of hypersonic vehicles around the world are summarized,and the geometric configuration and mission profile of typical air-breathing hypersonic vehicle are ***,the control difficulties of air-breathing hypersonic vehicle are introduced,including integrated design of engine and fuselage,static instability,strong nonlinearity,uncertain aerodynamic parameters,*** to its control requirements,the control methods considering external disturbance,fault-tolerant control methods,anti-saturation methods,and prescribed performance control methods considering transient performance constraints are summarized *** classification and comparison of various control methods are given,and the frontiers of theoretical development are ***,considering the effects of composite disturbances,the design of terminal guidance law under multiple constraints is overviewed,including guidance law with angle constraint,velocity constraint,acceleration constraint and time ***,the classification of guidance law design methods under different constraints,their advantages as well as the future development trend and requirements are introduced.

关键词： Classification of hypersonic vehicles Control equipmentaerospace applications Flight profiles Guidance strategy Hypersonic vehicles

Adaptive control for attitude coordination of leader-following rigid spacecraft systems with inertia parameter uncertainties

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Chinese Journal of Aeronautics 2019年第3期32卷 688-700页

作者： xiaokui yue Xianghong XUE Haowei WEN Jianping YUAN National Key Laboratory of Aerospace Flight Dynamics Northwestern Polytechnical University School of Astronautics Northwestern Polytechnical University

This paper studies the leader-following attitude coordination problems of multiple spacecraft in the presence of inertia parameter uncertainties. To achieve attitude coordination in the situation that even the leader's attitude is only applicable to a part of the following spacecraft, a nonlinear attitude observer is proposed to obtain an accurate estimation of the leader's attitude and angular velocity for all the followers. In addition, a distributed control scheme based on noncertainty equivalence principle is presented for multiple spacecraft' attitude synchronization. With a dynamic scaling, attitude consensus can be achieved asymptotically without any information of the bounds of the uncertain inertia parameters. Furthermore, once the estimations of inertia parameters reach their ideal values, the estimation process will stop and the ideal value of inertia parameter will be held. This is a special advantage of parameter estimation method based on non-certainty equivalence. Numerical simulations are presented to demonstrate that the proposed non-certainty equivalence-based method requires smaller control toque and converges faster compared with the certainty equivalence-based method.

关键词： Adaptive control Attitude coordination Leader-following consensus Non-certainty equivalence Spacecraft formation flying

Hybrid Passive/Active Vibration Control of a Loosely Connected Spacecraft System

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Computer Modeling in Engineering & Sciences 2020年第1期122卷 61-87页

作者： Xin Wang xiaokui yue Haowei Wen Jianping Yuan National Key Laboratory of Aerospace Flight Dynamics Northwestern Polytechnical UniversityXi’an710072China School of Astronautics Northwestern Polytechnical UniversityXi’an710072China

In this paper,a hybrid passive/active vibration(HPAV)controller of a loosely connected spacecraft consisting of a servicing satellite,a target and an X-shape structure isolator is first proposed to suppress vibrations of the system when subjected to the impulsive external excitations during the on-orbit *** passive dynamic response of the combined system can be adjusted appropriately to achieve the desired vibration isolation performance by tuning the structural parameters of the bio-inspired X-shape ***,the adaptive control design through dynamic scaling technique is selected as the active component to maintain high vibration isolation performance in the presence of parameter uncertainties such as mass of the satellite platform,the damping and rotation friction coefficients of the X-shape *** with the pure passive system and the traditional spring-mass-damper(SMD)isolator,the HPAV strategy witnesses lower transmissibility,smaller vibration amplitude and higher convergence rate when subjected to the post-capture *** simulations demonstrate the feasibility and validity of the proposed hybrid control scheme in suppressing vibrations of the free-floating spacecraft.

关键词： Hybrid passive/active vibration control X-shape structure adaptive control on-orbit capture

Postcapture stabilization of space robots considering actuator failures with bounded torques

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Chinese Journal of Aeronautics 2018年第10期31卷 2034-2048页

作者： xiaokui yue Teng ZHANG Honghua DAI Xin NING Jianping YUAN National Key Laboratory of Aerospace Flight Dynamics (AFDL) Northwestern Polytechnical University School of Astronautics Northwestern Polytechnical University Department of Mechanical Engineering University of Alberta

Space robotics is regarded as one of the most impressing approaches for space debris removal missions. Due to the residual momentum of debris, it is essential to stabilize the base rapidly after capture. This paper presents a novel control strategy for stabilization of a space robot in postcapture considering actuator failures and bounded torques. In the control strategy, the motion of the manipulator is not regarded as a disturbance to the base; in contrast, it is utilized to compensate for the limitation of the control torques by means of an inverse dynamical model of the system. Different scenarios where actuators are external mechanisms or momentum exchange devices have been carried out, and for actuator failures, both single-and two-actuator failures have been considered. Regarding to the performance of actuators, control torques are bounded. In cases that either single or two actuators have failed, the base can be stabilized kinematically when actuators are external mechanisms, but can only be stabilized dynamically when only momentum exchange devices are used. Finally, a space robot with a seven-degree-of-freedom manipulator in postcapture is studied to verify the validity and feasibility of the proposed control scheme. Simulation results show that the whole system can be stabilized rapidly.

关键词： Actuator failure Attitude control Bounded torque Postcapture Space robot

Fast and accurate adaptive collocation iteration method for orbit dynamic problems

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中国航空学报:英文版 2023年第9期36卷 231-242页

作者： Honghua DAI Zhe ZHANG Xuechuan WANG Haoyang FENG Changtao WANG xiaokui yue National Key Laboratory of Aerospace Flight Dynamics(AFDL) Northwestern Polytechnical UniversityXi’an 710072China School of Astronautics Northwestern Polytechnical UniversityXi’an 710072China

For over half a century,numerical integration methods based on finite difference,such as the Runge-Kutta method and the Euler method,have been popular and widely used for solving orbit dynamic *** general,a small integration step size is always required to suppress the increase of the accumulated computation error,which leads to a relatively slow computation ***,a collocation iteration method,approximating the solutions of orbit dynamic problems iteratively,has been *** method achieves high computation accuracy with extremely large step *** efficient,the collocation iteration method suffers from two limitations:(A)the computational error limit of the approximate solution is not clear;(B)extensive trials and errors are always required in tuning *** overcome these problems,the influence mechanism of how the dynamic problems and parameters affect the error limit of the collocation iteration method is *** this basis,a parameter adjustment method known as the“polishing method”is proposed to improve the computation *** method proposed is demonstrated in three typical orbit dynamic problems in aerospace engineering:a low Earth orbit propagation problem,a Molniya orbit propagation problem,and a geostationary orbit propagation *** simulations show that the proposed polishing method is faster and more accurate than the finite-difference-based method and the most advanced collocation iteration method.

关键词： Collocation iteration method Numerical integration method Orbit dynamics Parameter adjustment method Polishing method