Optimal feedback control of the deployment of a tethered subsatellite subject to perturbations

This paper presents the nonlinear optimal feedback control for the deployment process of a tethered subsatellite model, which involves not only the usually addressed in-plane motion, but also the out-of-plane motion. The model also takes the uncertainties in the mass parameter, the perturbations in initial states, and the external disturbance forces into consideration from an engineering point of view. The proposed controller is on the basis of a shrinking horizon and online grid adaptation scheme. Even though the proposed feedback law is not analytically explicit, it is easy to determine it by using a rapid recomputation of the open-loop optimal control, which generates the initial guesses for controls by interpolating the results from the previous computation. The case studies in the paper well demonstrate the effectiveness, robustness, and dominant real-time merits of the proposed controller.     

Review of deployment technology for tethered satellite systems

Tethered satellite systems (TSSs) have attracted significant attention due to their potential and valuable applications for scientific research. With the development of various launched on-orbit missions, the deployment of tethers is considered a crucial technology for operation of a TSS. Both past orbiting experiments and numerical results have shown that oscillations of the deployed tether due to the Coriolis force and environmental perturbations are inevitable and that the impact between the space tether and end-body at the end of the deployment process leads to complicated nonlinear phenomena. Hence, a set of suitable control methods plays a fundamental role in tether deployment. This review article summarizes previous work on aspects of the dynamics, control, and ground-based experiments of tether deployment. The relevant basic principles, analytical expressions, simulation cases, and experimental results are presented as well.     

Optimal deployment of spin-stabilized tethered formations with continuous thrusters

Nonlinear Dynamics - This paper addresses issues relevant to thruster-aided deployment of spin-stabilized tethered formations in a circular orbit. The dynamics of the tethered formation are first...     

Advances in dynamics and control of tethered satellite systems

The concept of tethered satellite system （TSS） promises to revolutionize many aspects of space exploration and exploitation. It provides not only numerous possible and valuable applications, but also challenging and interesting problems related to their dynamics, control, and physical implementation. Over the past decades, this exciting topic has attracted significant attention from many researchers and gained a vast number of analytical, numerical and experimental achievements with a focus on the two essential aspects of both dynamics and control. This review article presents the historic background and recent hot topics for the space tethers, and introduces the dynamics and control of TSSs in a progressive manner, from basic operating principles to the state-of-the-art achievements.     

On the dynamics of a tethered satellite system

The Hamiltonian structure for a fundamental model of a tethered satellite system is constructed. The model is composed of two point masses connected by a string with no restrictions on the motions of the two masses. A certain symmetry with respect to the special orthogonal group SO(3) for such a system is observed. The classical station-keeping mode for the tethered system is found to be nothing more than the relative equilibrium corresponding to the reduction of the system by the symmetry. The microgravity forces on the two point masses are responsible for the possible configurations of the string at the so-called radial relative equilibrium. A stability analysis is performed on the basis of the reduced energy-momentum method. Criteria for stability are derived, which could find potential applications in space technology.     

Periodic solutions and stability of a tethered satellite system

In this paper, several criteria on the existence of periodic solutions for a tethered satellite system (TSS) in an elliptical orbit, as well as the uniqueness of periodic solutions for the TSS in a circular orbit are presented on the basis of coincidence degree theory. In addition, the conditions on the global asymptotic stability of the equilibrium states for the TSS are also addressed in accordance with the Lyapunov stability theory and Barbashin–Krasovski theory.     

Stability and control of tethered satellite with chemical propulsion in orbital plane

The tethered satellite with chemical propulsion has broad application prospects in the disposal of abandoned satellites, the orbital rescue of spacecrafts, and the transportation of space supplies, which is completely different from the traditional applications of tethered satellites. Therefore, new research on its dynamics, stability, and control becomes useful and interesting. In this article, based on a dumbbell model of tethered satellite, the dynamics equations of tethered system in orbital maneuvering are established. Furthermore, according to the definitions of transversal and radial propulsive coefficients, analytical solutions of the equilibrium position for librational angle are derived during maneuvering in orbital plane; meanwhile, the effects of propulsive coefficients on librational stability are analyzed, which provides a basis for a selection of expected attitude trajectory. Then, a method of hierarchical sliding-mode tension control is presented to track the expected in-plane angle. This method can address the underactuated problem of tethered systems without either complex coordinate transformation for the system state model or constraint equation restrictions. During orbital flight, in-plane and out-of-plane angles are decoupled, so the tether tension control cannot be conducted to inhibit the out-of-plane angle. To solve this problem, the binormal component of thrust acceleration normal to the orbital plane is adopted as a control variable, and a feedback linearization-based thrust controller is designed to damp out the out-of-plane angle. Afterwards, orbital transfer cases between two circular orbits are studied to demonstrate the effectiveness of the tethered satellite with chemical propulsion. Numerical simulation results indicate that the stability of librational angles has a close relation to propulsive coefficients, and distributions of stable centers and unstable saddle points are totally different on both sides of bifurcation point. In addition, tracking control requirements for tethered satellite are guaranteed by designed controllers, which ensure flight safety in orbital maneuvering.     

An analytical control law of length rate for tethered satellite system

Based on the nonlinear dynamic equations of a tethered satellite system with three-dimensional attitude motion, an analytical tether length rate control law for deployment is derived from the equilibrium positions of the system and the scheme of the value range of the expected in-plane pitch angle. The proposed control law can guarantee that the tensional force acting on the end of the tether remains positive. The oscillation of the out-of-plane roll motion in conjunction with the in-plane pitch motion is effectively suppressed during deployment control. The analytical control law is still applicable, even if the system runs on a Keplerian elliptical orbit with a large eccentricity. The local stability of the non-autonomous system during deployment control is analyzed using the Floquet theory, and the global behavior is numerically verified using simple cell mapping. The numerical simulations in the paper demonstrate the proposed analytical control law.     

Attitude stability of a tethered satellite in locked rotation

Summary The linear stability of the attitude of a tethered satellite system, consisting of an asymmetric satellite with two equal tethered masses arranged vertically, is studied. The differential equations of motion are established, the attitude stability conditions are found, and then entered into a Magnus triangle. It is concluded that a tether parameter has a significant effect on the satellite's attitude stability. By increasing the value of , the stable regions in the Magnus triangle grow, until they cover more than half of its area, and then decline to exactly one half.

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Richtungstabilität eines gravitationsstabilisierten Satelliten mit Pendelmassen

Übersicht Die lineare Stabilität der Orientierung, d. h. der Winkellage, eines Systems aus einem starren Hauptsatelliten mit zwei im Schwerefeld vertikal an Seilen befestigten Punktmassen wird untersucht. Die Bewegungsgleichungen werden hergeleitet, deren Stabilitätsgrenzen berechnet und ins Magnussche Formdreieck eingetragen. Es wird gezeigt, daß der Seilparameter einen entscheidenden Einfluß auf das Stabilitätsverhalten hat. Je größer der Seilparameter ist, desto grïoßer werden die Stabilitätsgebiete, bis sie mehr als die Hälfte des Magnusschen Formdreiecks ausmachen, um bei weiterem Ansteigen dann auf genau die Hälfte zurückgehen.

     

Dynamic analysis of a tethered satellite system with a moving mass

This paper presents a dynamic analysis of a tethered satellite system with a moving mass. A dynamic model with four degrees of freedom, i.e., a two-piece dumbbell model, is established for tethered satellites conveying a mass between them along the tether length. This model includes two satellites and a moving mass, treated as particles in a single orbital plane, which are connected by massless, straight tethers. The equations of motion are derived by using Lagrange’s equations. From the equations of motion, the dynamic response of the system when the moving mass travels along the tether connecting the two satellites is computed and analyzed. We investigate the global tendencies of the libration angle difference (between the two sections of tether) with respect to the changes in the system parameters, such as the initial libration angle, size (i.e. mass) of the moving mass, velocity of the moving mass, and tether length. We also present an elliptic orbit case and show that the libration angles and their difference increase as orbital eccentricity increases. Finally, our results show that a one-piece dumbbell model is qualitatively valid for studying the system under certain conditions, such as when the initial libration angles, moving mass velocity, and moving mass size are small, the tether length is large, and the mass ratio of the two satellites is large.     

Dynamic analysis of a tethered satellite system for space debris capture

Herein we analyze the dynamic behavior of a tethered satellite system for space debris capture, considering the large deformation of a tether. The tethered satellite system is modeled as two point masses and a string, and the equations of motion of the tethered satellite system are derived by using the absolute nodal coordinate formulation. To calculate the net velocity after debris capture, equations are established describing the momentum exchange between the net and the space debris. By using this model, the dynamic responses of the tethered satellite system after debris capture are calculated for the variations of the capture angles and capture velocities of the debris. This allows analysis of the orbital response of the tethered satellite system and the large tensions arising from tether tumbling. Finally, we analyze the effects of varying system parameters of the tethered satellite system and the space debris upon the dynamic responses.     

旋转三角形绳系卫星编队系统动态稳定性分析

本文研究了平动点附近的旋转三角形绳系卫星编队系统的动态稳定性问题.为了便于分析,假设系绳始终保持张紧状态,且不计系绳的质量.为了建立更加符合实际的数学模型,考虑了姿态运动和轨道运动的相互影响,即姿轨耦合,并在此基础上推导出了考虑姿轨耦合的非线性动力学方程.最后用数值方法模拟了在不同的旋转速度情况下系统的动态稳定性,模拟结果表明旋转速率越大系统稳定性越好.     

Attitude control for part actuator failure of agile small satellite

The stability and singularity problem of agile small satellite （ASS） with actuator failure is discussed in this paper. Firstly, the three-axis stabilized controller of an ASS is designed, where micro control moment gyros （MCMG＇s） in pyramid configuration （PC） is used as the actuator. By using the same controller and steering law, the control results before and after one gyro fails are compared by simulation. The variation of singular momentum envelope before and after one gyro fails is also compared. The simulation results show that the failure intensively decreases the capacity of output torque, which leads to the emergence of more singular points and the rapid saturation of MCMG＇s. Finally, the parameters of system controller are changed to compare the control effect.     

Optimal control and analysis of stabilometric tests with step disturbances of human sensory systems

Several optimal control problems are considered for a human motion model in the case of stabilometric tests when the posture of a person changes under a step disturbance. Such a situation is observed in the case of a galvanic vestibular stimulation or a vibration stimulation of the proprioceptors of shin muscles. Stabilometric tests with visual step disturbance are widespread in Russia. A characteristic feature of center of pressure (COP) trajectories for these tests is the presence of swings and overshoots. The test results are compared with the solutions of optimal control problems devoted to the repositioning of an inverted pendulum by a coupling torque. A speed-of-response problem and an optimal stabilization problem with a quadratic quality criterion are considered. The solutions to these optimum problems are compared with the results of stabilometric tests, which allows one to state a hypothesis on the sources of the above effects.