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Enhanced baseline determination for formation flying LEOs by relative corrections of phase center and code residual variations

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Chinese Journal of Aeronautics 2022年第2期35卷 185-194页

作者： Bin YI Defeng GU Bing JU Kai SHAO Houzhe ZHANG College of Liberal Arts and Sciences National University of Defense TechnologyChangsha 410073China TianQin Research Center for Gravitational Physics and School of Physics and Astronomy Sun Yat-sen University(Zhuhai Campus)Zhuhai 519082China National Key Laboratory of Science and Technology on Aerospace Flight Dynamics Beijing Aerospace Control CenterBeijing 100094China

formation flying Low Earth Orbiters(LEOs)are important for implementing new and advanced concepts in Earth observation *** Baseline Determination(PBD)is a prerequisite for LEOs to complete specified mission *** is usually performed based on space-borne GNSS data,the relative corrections of phase center and code residual variations play crucial roles in achieving the best relative orbit ***,the influences of antenna Relative Phase Centre Variations(RPCVs)and Single-Difference(SD)Melbourne-Wu¨bbena(MW)Combination Residuals Variations(SD MWVs)on PBD are *** methods were tested using flight data from Gravity Recovery And Climate Experiment(GRACE)and GRACE Follow-On(GRACE-FO).Results showed that the maximum values for RPCVs and SD MWVs were 14 mm and 0.32 cycles,***,the RPCVs correction significantly enhanced the baseline accuracy;the K-Band Ranging(KBR)measurement consistency improved by 30.1%and 37.5%for GRACE and GRACE-FO,*** application of SD MWVs further improved the accuracy and reliability of PBD *** GRACE,the ambiguities fixing success rate increased from 85.1%to 97.9%and a baseline consistency of 0.57 mm was achieved for the KBR *** was found that the correction of both RPCVs and SD MWVs reduced the carrier phase observation minus computation residuals from double-difference ionosphere-free *** addition,in-flight data processing demonstrated that RPCVs and SD MWVs estimations for the current period could be used for the previous and subsequent periods.

关键词： Ambiguity resolution formation flying Precise baseline determination(PBD) Relative phase centre variations(RPCVs)estimation SD MW combination residuals variations(SD MWVs)estimation

Nonlinear control of spacecraft formation flying with disturbance rejection and collision avoidance

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Chinese Physics B 2017年第1期26卷 250-259页

作者： Qing Ni Yi-Yong Huang Xiao-Qian Chen College of Aerospace Science and Engineering National University of Defense Technology Changsha 410073 China

A nonlinear controller for disturbances rejection and collision avoidance is proposed for spacecraft formation *** formation flying is described by a nonlinear model with the J2 perturbation and atmospheric drag. Based on the theory of the state-dependent Riccati equation（SDRE）, a finite time nonlinear control law is developed for the nonlinear dynamics involved in formation flying. Then, a compensative internal mode（IM） control law is added to eliminate *** two control laws compose a finite time nonlinear tracking controller with disturbances rejection. Moreover, taking safety requirements into account, the repulsive control law is incorporated in the composite controller to perform collision avoidance manoeuvres. A numerical simulation is presented to demonstrate the effectiveness of the proposed *** to the conventional control method, the proposed method provides better performance in the presence of the obstacles and external disturbances.

关键词： nonlinear control disturbances rejection collision avoidance formation flying

Discrete time multiple spacecraft formation flying attitude optimal control in presence of relative state constraints

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Chinese Journal of Aeronautics 2021年第4期34卷 293-305页

作者： Hossein MORADI PARI Hossein BOLANDI Department of Electrical Engineering Iran University of Science and TechnologyTehran 009821Iran

This paper addresses the challenge of synchronized multiple spacecraft attitude reorientation in presence of pointing and boundary constraints with limited inter-spacecraft communication *** attitude pointing constraint among the fleet of spacecraft has also been modeled and considered during the attitude maneuvers toward the desired *** fling control structure that consists of decentralized path planners based on virtual structure approach joint with discrete time optimal local controller is designed to achieve the mission's *** to digital computing of spacecraft's onboard computer,local optimal controller based on discrete time prediction and correction algorithm has been *** time step of local optimal algorithm execution is designed so that the spacecraft track their desired attitudes with appropriate error *** convergence of the proposed architecture and stability of local controller's tracking error within appropriate upper bound are ***,a numerical simulation of a stereo imaging scenario is presented to verify the performance of the proposed architecture and the effectiveness of the algorithm.

关键词： Decentralized Discrete time formation flying Optimal control Spacecraft Virtual structure approach

Finite-time coordination control for formation flying spacecraft

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Journal of Systems Engineering and Electronics 2014年第5期25卷 859-867页

作者： Yong Guo Shenmin Song Liwei Deng Center for Control Theory and Guidance Technology Harbin Institute of Technology

This paper investigates a distributed coordination control scheme using an adaptive terminal sliding mode for formation flying spacecraft with coupled attitude and translational dynamics. In order to overcome the singularity of the traditional fast terminal sliding manifold, a novel fast terminal sliding manifold is given. And then, based on the adaptive control method, a continuous robust coordinated controller is designed to compensate external disturbances and to alleviate the chattering phenomenon. The theoretical analysis shows that the coordinated controller can guarantee the finite-time stability of the overall closed-loop system through local information exchange, and numerical simulations also demonstrate its effectiveness.

关键词： formation flying coordinated control attitude and translational coupling finite-time stability adaptive control.

Solar radiation pressure used for formation flying control around the Sun-Earth libration point

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Applied Mathematics and Mechanics(English Edition) 2009年第8期30卷 1009-1016页

作者：龚胜平李俊峰宝音贺西 School of Aerospace Tsinghua University

Solar radiation pressure is used to control the formation flying around the L2 libration point in the Sun-Earth system. formation flying control around a halo orbit requires a very small thrust that cannot be satisfied by the latest thrusters. The key contribution of this paper is that the continuous low thrust is produced by solar radiation pressure to achieve the tight formation flying around the libration point. However, only certain families of formation types can be controlled by solar radiation pressure since the direction of solar radiation pressure is restricted to a certain range. Two types of feasible formations using solar radiation pressure control are designed. The conditions of feasible formations are given analytically. Simulations are presented for each case, and the results show that the formations are well controlled by solar radiation pressure.

关键词： solar sail solar radiation pressure halo orbit formation flying

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

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Applied Mathematics and Mechanics(English Edition) 2008年第2期29卷 185-198页

作者：袁长清李俊峰王天舒宝音贺西 School of Aerospace Tsinghua University

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.

关键词： attitude control formation flying multi-body spacecraft robust control,multi-target tracking

Energy-efficient control of nanosatellites during distributed region formation flying

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Control Theory and Technology 2016年第4期14卷 263-278页

作者： Reza HAGHIGHI Chee Khiang PANG Department of Electrical and Computer Engineering National Universily of Singapore Singapore 117583 Engineering Cluster Singapore Institute of Technology Singapore 138683

In this paper, we present an energy-efficient method for distributed region formation flying of nanosatellites. The proposed framework consists of two concurrent sub-schemes that include estimation and formation. In the estimation sub-scheme, unlike the existing methods on satellite formation flying, that assume the availability of the reference orbital elements to all followers, here, a distributed estimator is developed so that the follower nanosatellites estimate the position of the leader in its orbital slot. In the formation sub-scheme, we consider a region formation strategy which is an efficient method in dealing with the formation of a large number of nanosatellites. We propose an optimal region following formation method based on the receding horizon control （RHC） using the estimated reference orbital elements. Subsequently, an algorithm is presented to solve the proposed energy-efficient formation flying method. Finally, the simulation result is presented that illustrates the purposed method improves the power consumption for each nanosatellite with respect to the existing non-optimal region formation flying controllers.

关键词： formation flying distributed estimation region following formation

Nonlinear programming control using differential aerodynamic drag for CubeSat formation flying

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Frontiers of Information Technology & Electronic Engineering 2017年第7期18卷 867-881页

作者： Sheng-chao DENG Tao MENG Zhong-he JIN College of lnformation Science and Electronic Engineering Zhejiang University Hangzhou 310027 China School of Aeronautics and Astronautics Zhejiang University Hangzhou 310027 China

Because of their volume and power limitation, it is difficult for CubeSats to configure a traditional propulsion system. Atmospheric drag is one of the space environmental forces that low-orbit satellites can use to realize orbit adjustment. This paper presents an integrated control strategy to achieve the desired in-track formation through the atmospheric drag difference, which will be used on ZJUCubeSat, the next pico-satellite of Zhejiang University and one of the participants of the international QB50 project. The primary mission of the QB50 project is to explore the near-Earth thermosphere and ionosphere at the orbital height of 90-300 km. Atmospheric drag cannot be ignored and has a major impact on both attitude and orbit of the satellite at this low orbital height. We conduct aerodynamics analysis and design a multidimensional nonlinear constraint programming （MNLP） strategy to calculate different desired area-mass ratios and corresponding hold times for orbit adjustment, taking both the semimajor axis and eccentricity into account. In addition, area-mass ratio adjustment is achieved by pitch attitude maneuver without any deployable mechanism or corresponding control. Numerical simulation based on ZJUCubeSat verifies the feasibility and advantage of this design.

关键词： QB50 ZJUCubeSat Atmospheric drag formation flying

Attitude Coordination of Deep Space formation flying via Virtual Structure

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Attitude Coordination of Deep Space Formation Flying via Vir...