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Sequential dynamic resource allocation in multi-beam satellite systems:A learning-based optimization method

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Chinese Journal of Aeronautics 2023年第6期36卷 288-301页

作者： Yixin HUANG shufan wu Zhankui ZENG Zeyu KANG Zhongcheng MU Hai HUANG School of Aeronautics and Astronautics Shanghai Jiao Tong UniversityShanghai 200240China Shanghai Academy of Spaceflight Technology Shanghai 200240China School of Astronautics Beihang UniversityBeijing 100191China

Multi-beam antenna and beam hopping technologies are an effective solution for scarce satellite frequency *** of the primary challenges accompanying with Multi-Beam Satellites(MBS)is an efficient Dynamic Resource Allocation(DRA)*** paper presents a learning-based Hybrid-Action Deep Q-Network(HADQN)algorithm to address the sequential decision-making optimization problem in *** using a parameterized hybrid action space,HADQN makes it possible to schedule the beam pattern and allocate transmitter power more *** pursue multiple long-term QoS requirements,HADQN adopts a multi-objective optimization method to decrease system transmission delay,loss ratio of data packets and power consumption load *** results demonstrate that the proposed HADQN algorithm is feasible and greatly reduces in-orbit energy consumption without compromising QoS performance.

关键词： Beam hopping Deep reinforcement learning Dynamic resource allocation Mixed-integer programming Multi-beam satellite systems Multi-objective optimization

Attitude control of multi-spacecraft systems on SO(3)with stochastic links failure

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Chinese Journal of Aeronautics 2024年第3期37卷 320-331页

作者： KANG Zeyu SHEN Qiang wu shufan Chris J.DAMAREN MU Zhongcheng School of Aeronautics and Astronautics Shanghai Jiao Tong UniversityShanghai 200240China Institute for Aerospace Studies University of TorontoTorontoOntario M3H 5T6Canada

In this paper,for Multi-Spacecraft System(MSS)with a directed communication topology link and a static virtual leader,a controller is proposed to realize attitude consensus and attitude stabilization with stochastic links failure and actuator ***,an MSS attitude error model suitable for a directed topology link and with a static virtual leader based on SO(3)is derived,which considers that the attitude error on SO(3)cannot be defined based on algebraic ***,we design a controller to realize the MSS on SO(3)with attitude consensus and attitude stabilization under stochastic links failure and actuator ***,the simulation results of a multi-spacecraft system with stochastic links failure and a static virtual leader spacecraft are demonstrated to illustrate the efficiency of the attitude controller.

关键词： Multi-spacecraft systems Attitude consensus Attitude stabilization Stochastic links failure Super-martingale convergence

Reinforcement learning based dynamic distributed routing scheme for mega LEO satellite networks

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Chinese Journal of Aeronautics 2023年第2期36卷 284-291页

作者： Yixin HUANG shufan wu Zeyu KANG Zhongcheng MU Hai HUANG Xiaofeng wu Andrew Jack TANG Xuebin CHENG School of Aeronautics and Astronautics Shanghai Jiao Tong UniversityShanghai 200240China School of Astronautics Beihang UniversityBeijing 100191China School of Aerospace Mechanical and Mechatronic EngineeringThe University of SydneyCamperdown 2006Australia X-Laboratory The Second Academy of China Aerospace Science and Industry CorporationBeijing 100854China

Recently,mega Low Earth Orbit(LEO)Satellite Network(LSN)systems have gained more and more attention due to low latency,broadband communications and global coverage for ground *** of the primary challenges for LSN systems with inter-satellite links is the routing strategy calculation and maintenance,due to LSN constellation scale and dynamic network topology *** order to seek an efficient routing strategy,a Q-learning-based dynamic distributed Routing scheme for LSNs(QRLSN)is proposed in this *** achieve low end-toend delay and low network traffic overhead load in LSNs,QRLSN adopts a multi-objective optimization method to find the optimal next hop for forwarding data *** results demonstrate that the proposed scheme can effectively discover the initial routing strategy and provide long-term Quality of Service(QoS)optimization during the routing maintenance *** addition,comparison results demonstrate that QRLSN is superior to the virtual-topology-based shortest path routing algorithm.

关键词： LEO satellite networks Mega constellation Multi-objective optimization Routing algorithm Reinforcement learning

Attitude Guidance Algorithms for Agile Satellite Dynamic Imaging

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Guidance, Navigation and Control 2022年第4期2卷 41-56页

作者： Ning Du shufan wu Zhansheng Chen Kaihua Zhang Gang Liu School of Aeronautics and Astronautics Shanghai Jiao Tong University Shanghai 200240 P.R.China Institute of Satellite Engineering Shanghai Academy of Spaceflight Technology Shanghai 201109 P.R.China Department of Research and Development Shanghai Academy of Spaceflight Technology Shanghai 201109 P.R.China Institute of Spaceflight Control Technology Shanghai Academy of Spaceflight Technology Shanghai 201109 P.R.China

Dynamic imaging modes are increasingly crucial for agile satellites to perform complicated Earth observation *** this study,a direct guidance algorithm is developed to calculate the reference attitude and velocity for dynamic imaging mode from target geolocation information while considering the constraints on both the satellite camera boresight axis and the image motion *** two slew angles are determined directly,and no rotation around the boresight or reference vector is *** proposed approach employs a direct solution instead of the iterative process to obtain the reference attitude,which releases the onboard control system from the intensive computational *** illustrate the performance of the proposed guidance algorithms,numerical simulation results are presented.

关键词： Attitude guidance dynamic imaging drift angle attitude maneuver image motion

STUDIES ON THE FLIGHT PERFORMANCE OPTIMIZATION OF COMMERCIAL AIRCRAFTS

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STUDIES ON THE FLIGHT PERFORMANCE OPTIMIZATION OF COMMERCIAL...

Adaptive Terminal Sliding Mode Attitude Control of Hypersonic Vehicles During Re-entry

计算机，通信，控制与电力工程国际会议

作者： shufan wu Yongzhang Shen Department.of Automatic Control Nanjing University of Aeronautics & Astronautics

ISBN: (纸本)0780312333

A thorough research on the flight trajectory optimization techniques with energy-state approach is conducted in this *** pointmass energy-state approximation model and the trajectory optimization principle and algorithms based on this model are first *** fixed-time 4D trajectory optimization is then discussed,and the associated iteration algorithm is *** step-climb mode optimization principle and method are considered and discussed. An algorithm simplification approach based on modelling the optimized results for specific aircraft model is presented and discussed,aimed to reduce the computation requirement amount so as to enhance its on-board real-time implementation *** simulations and some specific modelling results for a Boeing-707 transport aircraft model are presented and discussed.

关键词： STUDIES ON THE FLIGHT PERFORMANCE OPTIMIZATION OF COMMERCIAL AIRCRAFTS

来源： cnki会议评论

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cnki会议

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上海航天（中英文） 2020年第S1期37卷 20-24,33页

作者： WANG Xiaoliang GONG Deren wu Yuedong wu shufan School of Aeronautics and Astronautics Shanghai Jiao Tong UniversityShanghai 200240China

Based on the principles of the non-singular terminal sliding mode control(NTSMC),a new control method along with the adaptive filter technology,which can tolerate external disturbances and noises with unknown statistics,is proposed for the attitude control of hypersonic vehicles during re-entry. First,a disturbance compensated module is used as a discontinuous control part of the NTSMC to enhance the performance of the controller due to chattering. Second,a new methodology is proposed based on a real-time estimate of system states by the nonlinear filter and the measurement and process noise covariances. To compare this evolutionary method with classical methods,an optimal filter algorithm is introduced. The results show that,compared with many existing works on the terminal sliding mode control(TSMC),the proposed method exhibits three attractive features:(i) it can avoid singularity problems without any constraints,and provide faster responses by tuning the parameters in the algorithm;(ii)for constant or eventually constant disturbances,zero steady-state error can be achieved when a boundary layer is used to alleviate chattering;(iii)the switching gain is only required to be designed to be greater than the bound of the disturbance. Finally,the effectiveness of the proposed control method is verified by the simulation results of both the numerical and application examples.

关键词： Attitude method eventually

STUDIES ON AIRCRAFT TOTAL ENERGY FLIGHT CONTROL SYSTEM：NONLINEAR SYSTEM INTEGRATION AND SIMULATION

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Chinese Journal of Aeronautics 1995年第1期8卷 36-44页

作者： wu shufan Shen Yongzhang Guo Suofeng( Dept of Automatic Control, Nanjing University of Aeronauticsand Asironautics, Nanjing, China, 210016)

ＳＴＵＤＩＥＳＯＮＡＩＲＣＲＡＦＴＴＯＴＡＬＥＮＥＲＧＹＦＬＩＧＨＴＣＯＮＴＲＯＬＳＹＳＴＥＭ：ＮＯＮＬＩＮＥＡＲＳＹＳＴＥＭＩＮＴＥＧＲＡＴＩＯＮＡＮＤＳＩＭＵＬＡＴＩＯＮＷｕＳｈｕｆａｎ；ＳｈｅｎＹｏｎｇｚｈａｎ... 详细信息

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关键词： flight control. thrust control. nonlinearity simulation

基于改进Kinky Inference的输出调节自适应无拖曳控制

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北京航空航天大学学报 2024年第5期50卷 1604-1613页

作者：孙笑云沈强吴树范上海市引力波探测前沿科学研究基地上海200240 上海交通大学航空航天学院上海200240

在空间引力波探测任务中,航天器内部检验质量因存在载荷硬件噪声、环境噪声及微推力器耦合噪声等复杂干扰,影响其无拖曳控制精度,难以实现超净、超稳控制需求。提出一种基于惰性适配Lipschitz常数Kinky Inference (LACKI)的航天器自适... 详细信息

在空间引力波探测任务中,航天器内部检验质量因存在载荷硬件噪声、环境噪声及微推力器耦合噪声等复杂干扰,影响其无拖曳控制精度,难以实现超净、超稳控制需求。提出一种基于惰性适配Lipschitz常数Kinky Inference (LACKI)的航天器自适应无拖曳控制方法,运用监督学习规则实现先验知识不足、样本数据存在损坏时外界干扰的逼近和抑制,及基于输出调节的模型参考自适应控制(MRAC)方法实现检验质量精确的无拖曳控制。数值仿真验证了无拖曳控制中敏感轴平动和转动自由度的状态响应性能及LACKI规则针对外界干扰的估计效果,通过与常规线性控制方法的对比,验证了所提方法对于提高无拖曳控制精度的有效性。

关键词：监督学习 Lipschitz估计模型参考自适应控制无拖曳控制输出调节 Kinky Inference

包含有界切换增益的空间惯性传感器输出调节积分模型参考自适应控制

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中国科学：技术科学 2024年第3期54卷 490-500页

作者：孙笑云吴树范沈强上海交通大学航空航天学院上海200240 上海市引力波探测前沿科学研究基地上海200240

基于输出调节的多变量模型参考自适应控制(model reference adaptive control,MRAC)用于解决系统状态不可直接获取时,多变量系统向参考系统的稳定输出跟踪问题.在空间引力波探测航天器内部惯性传感器静电悬浮控制中,考虑到其作为航天器... 详细信息

基于输出调节的多变量模型参考自适应控制(model reference adaptive control,MRAC)用于解决系统状态不可直接获取时,多变量系统向参考系统的稳定输出跟踪问题.在空间引力波探测航天器内部惯性传感器静电悬浮控制中,考虑到其作为航天器平台惯性基准的稳定需求,双质量块动力学中存在的不连续干扰影响,以及应对不同工作模式的瞬态切换,提出一种基于积分输出调节MRAC的静电悬浮控制方案,引入有界的切换自适应校正增益及自适应积分修正项,用于系统不连续情况下的抗输入饱和、瞬态抑制及惯性传感器非敏感轴各自由度向参考状态的稳定逼近.基于Filippov集与广义梯度的Lyapunov分析验证该方案下,不连续系统中各闭环信号的收敛性,数值仿真验证样例空间引力波探测航天器中,作为关键载荷的双质量块空间惯性传感器各非敏感轴自由度针对位移噪声及残余加速度及切换瞬态的良好抑制效果.

关键词：静电悬浮控制空间引力波探测惯性传感器模型参考自适应控制不连续系统有界切换增益