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Fast cooperative trajectory optimization and test verification for close-range satellite formation using Finite Fourier Series method

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Chinese Journal of Aeronautics 2020年第8期33卷 2224-2229页

作者： mingying huo Zichen FAN Naiming QI Zhiguo SONG Xin SHI School of Astronautics Harbin Institute of TechnologyHarbin 150001China China Academy of Launch Vehicle Technology Beijing 100076China

The process of formation reconfiguration for close-range satellite formation should take into account the risk of collisions between *** this end,this paper presents a method to rapidly generate low-thrust collision-avoidance trajectories in the formation reconfiguration using Finite Fourier Series(FFS).The FFS method can rapidly generate the collision-avoidance threedimensional *** results obtained by the FFS method are used as an initial guess in the Gauss Pseudospectral Method(GPM)solver to verify the applicability of the *** with the GPM method,the FFS method needs very little computing time to obtain the results with very little difference in performance *** verify the effectiveness,the proposed method is tested and validated by a formation control *** satellite simulators in the testbed are used to simulate two-dimensional satellite formation *** simulation and experimental results show that the FFS method can rapidly generate trajectories and effectively reduce the risk of collision between *** fast trajectory generation method has great significance for on-line,constantly satellite formation reconfiguration.

关键词： Collision-avoidance Finite Fourier Series(FFS) Satellite formation reconfiguration Satellite simulators Shape-Based(SB)method

Jupiter system exploration trajectory design: Summary of the winning solution at CTOC10

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Astrodynamics 2021年第1期5卷 13-26页

作者： Haiyang Zhang Yabo Hu Zichen Fan Jie Lv Huidong Ma Ze Yu mingying huo Gang Zhang Harbin Institute of Technology Harbin 150080China

This paper presents the methods and results submitted by the winning team from Harbin Institute of Technology of the 10th China Trajectory Optimization Competition(CTOC10).The problem posed by CTOC10 requires exploring the Jupiter system using a combined *** exploration mission consists of the detection of Jupiter’s magnetic field and an exploration of the Galilean *** mission is completed through three steps:problem analysis,orbital design process,and data *** orbital design process is mainly divided into four parts,namely,repeating groundtrack orbit design,gravity-assisted orbit design,initial orbit parameter selection,and local optimization *** designed orbit is then evaluated using a heuristic optimization algorithm applied during the data ***,six full-coverage observations of Jupiter’s magnetic field are realized under the constraints of fuel and *** final index of the submitted result is 357.8067.

关键词： China Trajectory Optimization Competition Jupiter exploration repeating ground-track orbit gravity assist

Coupled attitude-vibration analysis of an E-sail using absolute nodal coordinate formulation

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Astrodynamics 2020年第3期4卷 249-263页

作者： Ce Zhao mingying huo Ji Qi Shilei Cao Dongfang Zhu Lujun Sun Hongli Sun Naiming Qi School of Astronautics Harbin Institute of TechnologyHarbin 150001China Ming Hsieh Department of Electrical and Computer Engineering University of Southern CaliforniaLos AngelesCA 9007USA Shanghai Academy of Spaceflight Technology Shanghai 201109China

In this study,the effects of solar wind on an electric sail(E-sail)are modeled and analyzed using an absolute nodal coordinate formulation(ANCF).First,the thrust of the charged metal tether that makes up the E-sail was analyzed and a model was *** simulations of a single metal tether were ***,an overall E-sail model was established using the connection matrix,and E-sails subjected to different angular velocities were *** results of the ANCF model and a dumbbell model were compared at different angular *** results confirm that with a relatively high angular velocity,the flexible metal chain can be approximately regarded as a rigid ***,with a small angular velocity,the flexibility of the metal chain cannot be ignored.

关键词： E-sail absolute nodal coordinate formulation dynamic model

A Distributed Parameter Saturated Capacitor Model for Hysteresis in Piezoelectric Actuators

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A Distributed Parameter Saturated Capacitor Model for Hyster...

Research on Conversion Measurement Method of Hidden Features in Automatic Docking System

第37届中国控制会议

作者： Yanfang Liu Desong Du Jun Zhao mingying huo Harbin Institute of Technology

Hysteresis is a very important nonlinearity in piezoelectric actuators（PEA）.This paper proposes a distributed parameter saturated capacitor（DPSC） approach to model and compensate for *** DPSC model is extended from saturated capacitor（SC） hysteresis *** multiple SCs is replaced by a DPSC,the elastance and saturated charge of which have distributed parameter properties and governed by continuous ***,compared with the SC model,the DPSC model requires much less *** a exponential function to describe the elastance,only three parameters are *** show that it achieves a satisfactory *** normalized root mean square error of the DPSC model is as less as 0.63%.The hysteresis is compensated for by connecting the DPSC in serial with a *** compensation reduces the hysteresis nonlinearity from 13.8%to 1.69%by 87.8%.

关键词： Hysteresis Distributed Parameter Saturated Capacitor Modeling and Compensation Piezoelectric Actuators

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Research on Conversion Measurement Method of Hidden Features...

大挠性机动飞行器改进型正向位置反馈振动控制

第32届中国控制与决策会议

作者： Wenyu Feng Naiming Qi Naihan Yang Fuyou Zhao Tong Lin mingying huo School of Astronautics Harbin Institute of Technology

In response to the demand for non-contact measurement in the automatic docking system,this paper proposes a conversion measurement method for hidden features based on visual measurement system,and designs a hidden feature conversion measurement *** using this device,the position and attitude parameters of the hidden features that are not easy to directly measure are converted to a position on the outer shell of cabin,where the measurement is *** hidden feature conversion measurement algorithm of the automatic docking process is derived,and the feasibility and accuracy of the method are verified by mathematical simulation calculation and docking test *** the conversion measurement method designed in this paper,the measurement during automatic docking process can be more convenient and accurate,and the cabins docking quality can be greatly improved.

关键词： Automatic docking system Non-contact measurement Hidden features Conversion measurement

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北京航空航天大学学报 2018年第2期44卷 375-382页

作者：袁秋帆霍明英齐乃明曹世磊肖余之哈尔滨工业大学航天学院哈尔滨150001 上海航天技术研究院上海201109

针对一类大挠性机动飞行器,同时进行的姿态和轨道机动将激发挠性结构与中心刚体之间的平移耦合模态和转动耦合模态。为了提高姿态和轨道控制稳定度,提出了一种整合的改进型正向位置反馈(MPPF)控制方法抑制挠性结构的振动。首先建立了包... 详细信息

针对一类大挠性机动飞行器,同时进行的姿态和轨道机动将激发挠性结构与中心刚体之间的平移耦合模态和转动耦合模态。为了提高姿态和轨道控制稳定度,提出了一种整合的改进型正向位置反馈(MPPF)控制方法抑制挠性结构的振动。首先建立了包含转动耦合和平移耦合模态的动力学模型,推导了耦合模态参数,然后基于MPPF控制律,设计了对转动耦合模态和平移耦合模态同时进行抑制的主动振动控制器,并采用M范数方法进行了参数优化,采用压电智能材料构建了主动振动控制系统。仿真结果表明所设计的控制器能够对机动飞行器的挠性结构振动起到很好的抑制效果,并且提高了姿态和轨道的控制稳定度。

关键词：挠性飞行器机动振动控制耦合动力学改进型正向位置反馈(MPPF)

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小推力航天器逃离太阳系的引力辅助轨迹设计

宇航学报 2024年第7期45卷 1032-1039页

作者：范子琛成飞李文龙霍明英齐乃明哈尔滨工业大学航天学院哈尔滨150001 上海卫星工程研究所上海201109

针对太阳系边界探测,利用形函数轨迹优化算法快速生成连续小推力航天器引力辅助逃离太阳系的三维轨迹,实现在有限燃料条件下的超远距离探测。通过对比有无引力辅助设计的仿真结果,证明了引力辅助技术在逃离太阳系过程中的有效性。仿真... 详细信息

针对太阳系边界探测,利用形函数轨迹优化算法快速生成连续小推力航天器引力辅助逃离太阳系的三维轨迹,实现在有限燃料条件下的超远距离探测。通过对比有无引力辅助设计的仿真结果,证明了引力辅助技术在逃离太阳系过程中的有效性。仿真结果表明,基于贝塞尔形函数方法的连续小推力轨迹优化算法可以高效地设计出引力辅助逃离太阳系的合理三维初始轨迹,对于初始探测任务的快速设计和分析具有重要意义。

关键词：引力辅助小推力轨迹设计逃离太阳系贝塞尔形函数法

基于贝塞尔形函数的电动帆逃离太阳系初始轨迹设计

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深空探测学报（中英文） 2021年第6期8卷 625-631页

作者：范子琛霍明英任辉齐乃明哈尔滨工业大学航天学院哈尔滨150001

探测太阳系边际需要寻找高效的推进系统和设计合理逃离太阳系的轨迹。提出了利用贝塞尔形函数方法快速生成电动帆逃离太阳系的三维轨迹,为更精确的轨迹优化算法提供合适的初始解。通过将贝塞尔形函数方法获得的结果作为高斯伪谱法(Gauss... 详细信息

探测太阳系边际需要寻找高效的推进系统和设计合理逃离太阳系的轨迹。提出了利用贝塞尔形函数方法快速生成电动帆逃离太阳系的三维轨迹,为更精确的轨迹优化算法提供合适的初始解。通过将贝塞尔形函数方法获得的结果作为高斯伪谱法(Gauss Pseudospectral method,GPM)的初始解进行计算,并对贝塞尔形函数方法获得的结果对直接解算器初始解的适用性进行了评估。仿真结果表明,贝塞尔形函数方法可以在短时间内为直接优化求解器设计出合理的电动帆逃离太阳系的三维初始轨迹。对于在太阳系边际探测初步任务设计阶段快速评估大量电动帆飞行场景具有参考意义。

关键词：电动帆轨迹设计逃离太阳系贝塞尔形状法初步任务分析

弱引力环境四足机器人的强化学习姿态机动控制

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宇航学报 2024年第10期45卷 1676-1684页

作者：高海波齐骥苏桓立霍明英于海涛邓宗全哈尔滨工业大学机器人技术与系统国家重点实验室哈尔滨150080 哈尔滨工业大学航天学院哈尔滨150001

针对四足机器人在小天体表面跳跃巡游探测过程中的空中姿态控制问题,提出了一种基于强化学习的无模型控制方案。在小天体的弱引力环境下,机器人单次跳跃的滞空时间很长,机器人需要利用这段时间修正起跳带来的姿态偏差以实现安全着陆,或... 详细信息

针对四足机器人在小天体表面跳跃巡游探测过程中的空中姿态控制问题,提出了一种基于强化学习的无模型控制方案。在小天体的弱引力环境下,机器人单次跳跃的滞空时间很长,机器人需要利用这段时间修正起跳带来的姿态偏差以实现安全着陆,或改变偏航角以改变未来行进方向。提出的基于近端策略优化(PPO)算法训练的控制器以猫落反射为启发,无需引入额外的姿态控制执行器。仿真结果表明,训练得到的控制器可通过控制四足机器人摆动腿部关节实现三轴姿态机动。设计并搭建了四足机器人气浮微重力模拟试验平台,通过样机试验,控制策略模型的有效性得到了验证。

关键词：星球探测机器人小天体探测强化学习微低重力模拟