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COMPARISON OF TWO METHODS IN satellite formation flying

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Applied Mathematics and Mechanics(English Edition) 2003年第8期24卷 902-908页

作者：高云峰宝音贺西李俊峰 Department of Engineering Mechanics Tsinghua UniversityBeijing 100084 P.R.China Department of Engineering Mechanics Tsinghua UniversityBeijing 100084 P.R.Chinaecently the research of dynamics and control of the satellite formation flying has been attracting a great deal of attentions of the researchers. The theory of the research was mainly based on Clohessy-Wiltshire' s (C-W's) equations which describe the relative motion between two satellites. But according to some special examples and qualitative analysis neither the initial parameters nor the period of the solution of C-W' s equations accord with the actual situation and the conservation of energy is no longer held. A new method developed from orbital element description of single satellite named relative orbital element method ( ROEM) was introduced. This new method with clear physics conception and wide application range overcomes the limitation of C-W s equation and the periodic solution is a natural conclusion. The simplified equation of the relative motion is obtained when the eccentricity of the main satellite is small. Finally the results of the two methods (C-W' s equation and ROEM) are compared and the limitations of C-W s equations are pointed out and explained.

Recently, the research of dynamics and control of the satellite formation flying has been attracting a great deal of attentions of the researchers. The theory of the research was mainly based on Clohessy-Wiltshire' s (C-W's) equations, which describe the relative motion between two satellites. But according to some special examples and qualitative analysis , neither the initial parameters nor the period of the solution of C-W' s equations accord with the actual situation, and the conservation of energy is no longer held. A new method developed from orbital element description of single satellite , named relative orbital element method ( ROEM) , was introduced. This new method, with clear physics conception and wide application range, overcomes the limitation of C-W s equation , and the periodic solution is a natural conclusion. The simplified equation of the relative motion is obtained when the eccentricity of the main satellite is small. Finally, the results of the two methods (C-W' s equation and ROEM) are compared and the limitations of C-W s equations are pointed out and explained.

关键词： satellite formation flying relative motion C-W' s equation relative orbital element method periodic solution

Adaptive repetitive learning control for trajectory-keeping of satellite formation flying

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Journal of Control and Decision 2014年第4期1卷 317-331页

作者： Yunan Hu Jianming Wei Meimei Sun Department of Control Engineering Naval Aeronautical Engineering InstituteYantaiP.R.China

An adaptive repetitive control scheme is proposed for trajectory-keeping of satellite formation flying in the leader–follower mode which is described by Lawden *** system is parameterised by power series approximation and the unknown timevarying parameters are estimated by adaptive repetitive learning *** rigorous analysis by constructing a Lyapunov-like composite energy function(CEF),the stability of the closed-loop system is ***,a simulation example is provided to illustrate the effectiveness of the control algorithms proposed in this paper.

关键词： satellite formation flying trajectory-keeping adaptive repetitive learning control

Inter-satellite Radio Links and Spread-spectrum Ranging for satellite formation flying

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Inter-satellite Radio Links and Spread-spectrum Ranging for ...

2002 3rd International Conference on Microwave and Millimeter Wave Technology

作者： Wang.shilian Zhang.eryang School of Electronic Science and Engineering National University of Defence Technology

ISBN: (纸本)078037486X

＜正＞To maintain and control a satellite cluster effectively,an on-board executive controller is necessary. Both information exchange among satellites and relative position determination with high accuracy in real time are of prime importance in satellites formation flying. This article firstly makes an overview of research programs of formation flying satellites cluster with inter-satellite link（ISL） at *** proposals for the development of ISL low layer protocols are presented in the following.A novel satellite-to-satellite ranging model based on direct spread spectrum in inter-satellite radio links are brought forward,the corresponding expected system performance of ranging accuracy is analyzed theoretically in the end.

关键词： satellite links space communication links transport protocols spread spectrum communication distance measurement channel coding radiofrequency interference inter-satellite radio link intersatellite links satellite-to-satellite ranging model spread-spectrum ranging satellite formation flying formation flying satellite cluster satellite constellations on-board executive controller multi-path interference satellite cluster control low layer protocols distance measurement on-board guidance/navigation/control RFI

USEFUL RELATIVE MOTION DESCRIPTION METHOD FOR PERTURBATIONS ANALYSIS IN satelliteformation flying

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Applied Mathematics and Mechanics(English Edition) 2005年第11期26卷 1464-1474页

作者：孟鑫李俊峰高云峰 MA Xing-rui School of AeroSpace Tsinghua University Beijing 100084 P. R. China 不详

A set of parameters called relative orbital elements were defined to describe the relative motion of the satellites in the formation flying. With the help of these parameters, the effect of the perturbations on the relative orbit trajectory and geometric properties of satellite formation can be easily analyzed. First, the relative orbital elements are derived, and pointed out： if the eccentricity of the leading satellite is a small value, the relative orbit trajectory is determined by the intersection between an elliptic cylinder and a plane in the leading satellite orbit frame reference; and the parameters that describe the elliptic cylinder and the plane can be used to obtain the relative orbit trajectory and the relative orbital elements. Second, by analyzing the effects of gravitational perturbations on the relative orbit using the relative orbital elements,it is found that the propagation of a relative orbit consists of two parts ： one is the drift of the elliptic cylinder; and the other is the rotation of the plane resulted from the rotation of the normal of the plane. Meanwhile, the analytic formulae for the drift and rotation rates of a relative trajectory under gravitational perturbations are presented. Finally, the relative orbit trajectory and the corresponding changes were analyzed with respect to the J2 perturbation.

关键词： satellite formation flying relative orbital element gravitational perturbation drift rate rotation rate

6DOF Quasi-Optimal Integral Sliding Mode Control for satellite formation Flving Using Dual Ouaternion

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6DOF Quasi-Optimal Integral Sliding Mode Control for Satelli...

第25届中国控制与决策会议

作者： Jinjie Wu Kun Liu Yudong Gao Binbin Zhang College of Aerospace Science and Engineering National University of Defense Technology

ISBN: (纸本)9781467355339

This paper addresses the tracking control problem of six-degree-of-freedom （6DOF） leader-follower satellite formation flying. First, using dual quaternion, 6DOF relative motion model of formation satellite is introduced. Then, a 6DOF quasi-optimal integral sliding mode controller is proposed to guarantee the globally asymptotic convergence of translational and rotational tracking errors despite the presence of parametric uncertainties and external disturbances. In the presented controller, control Lyapunov function is used to construct an optimal controller to minimize two predefined performance indices. A detailed stability analysis of the resulting closed-loop system using a Lyapunov fiarnework is also included. Finally, numerical simulations are presented to illustrate the validity and effectiveness of the proposed controller.

关键词： Integral sliding mode control Control Lyapunov function Tracking control Dual quaternion satellite formation flying

Orbit and attitude control of spacecraft formation flying

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Applied Mathematics and Mechanics(English Edition) 2008年第1期29卷 43-50页

作者：张治国李俊峰 School of Aerospace Tsinghua University

formation flying is a novel concept of distributing the functionality of large spacecraft among several smaller, less expensive, cooperative satellites. Some applications require that a controllable satellite keeps relative position and attitude to observe a specific surface of another satellite among the cluster. Specially, the target space vehicle is malfunctioning. The present paper focuses on the problem that how to control a chaser satellite to fly around an out-of-work target satellite closely in earth orbit and to track a specific surface. Relative attitude and first approximate relative orbital dynamics equations are presented. Control strategy is derived based on feedback linearization and Lyapunov theory of stability. Further, considering the uncertainty of inertia, an adaptive control method is developed to obtain the correct inertial ratio. The numerical simulation is given to verify the validity of proposed control scheme.

关键词： satellite formation flying orbit attitude dynamics and control

satellite Relative Dynamic in Terms of Mean Motion on a Zone Harmonic Perturbed Elliptical Orbit

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Satellite Relative Dynamic in Terms of Mean Motion on a Zone...

第25届中国控制与决策会议

作者： Guangyan Xu Feng Xiang School of Automation Shenyang Aerospace University

ISBN: (纸本)9781467355339

The equations of satellite relative dynamics described by mean orbital elements are derived under LVLH coordinates. The primary gravitational perturbation that results from the equatorial bulge term J2 is considered. In this paper, the short and long-periodic variations of J2 perturbation are neglected, only show the effect of a secular term . The first-order Taylor series expansion is employed to linearize the equations. Finally, the accurate description of satellite relative motion under the eccentric orbit is obtained.

关键词： J2 perturbation satellite formation flying Mean orbit elements

Exact Dynamic of satellite Relative Motion under Arbitrary Zonal Harmonic Perturbations

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Exact Dynamic of Satellite Relative Motion under Arbitrary Z...

第24届中国控制与决策会议

作者： Guangyan Xu 1 , Feng Xiang 1 , Ying Chen 2 1. School of Automation, Shenyang Aerospace University, Shenyang, China 1101362. Beijing Institute of Control Engineering, Beijing, China 100048

To expand the exact dynamic model of satellite relative motion under J 2 perturbation, a new model is established which is exactly up to arbitrary zonal harmonic perturbations. Moreover, a set of differential equations in terms of Reference satellite Variables （RSV） are obtained to describe the satellite motion around the Earth accurately under arbitrary zonal harmonic perturbations. Since no simplification is applied during the derivation, the result is valid for arbitrary eccentric orbits.

关键词： satellite relative motion satellite formation flying Zonal harmonic perturbations

线性多智能体系统一致性的一个统一框架(英文)

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线性多智能体系统一致性的一个统一框架(英文)

第五届全国复杂网络学术会议

作者：李忠奎 Peiking University

This paper addresses the consensus problem of multi-agent systems with a time-invariant communication topology consisting of general linear node dynamics.A distributed observer-type consensus protocol based on relative output measurements is proposed.A new framework is introduced to address in a unified way the consensus of multi-agent systems and the synchronization of complex *** this framework,the consensus of multi-agent systems with a communication topology having a spanning tree can be cast into the stability of a set of matrices of the same low *** notion of consensus region is then introduced and *** is shown that there exists an observer-type protocol solving the consensus problem and meanwhile yielding an unbounded consensus region if and only if each agent is stabilizable and detectable.A multi-step consensus protocol design procedure is further *** consensus with any prescribed convergence rate is also *** effectiveness of the theoretical results is demonstrated through numerical simulations,with an application to the lowearth-orbit satellite formation flying.

关键词： Multi-agent system complex networks consensus synchronization satellite formation flying