Dynamics of a tethered satellite formation for space exploration modeled via ANCF

Cheng-xin, Luo; Sun, Jialiang; Wen, Hao; Jin, Dongping

doi:10.1016/j.actaastro.2019.11.028

Cited by 31 publications

(12 citation statements)

References 15 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Differing from the conventional ANCF elements that adopt vectors of the positions and the slopes as the node coordinates, additional material coordinates are introduced as the generalized coordinates in the ANCF-ALE elements [27,28] . As shown in Fig.…”

Section: A Dynamic Equations Of Variable-length Tethermentioning

confidence: 99%

“…Also, a thin variable length plate element of ANCF-ALE description was developed in [27] that was applied to a topology optimization of the flexible multibody systems. Luo et al [28] investigated the dynamics of a tethered satellite formation under combination of a linear piecewise deployment and an applied jet force. In this paper, a variable-length element that combines arbitrary Lagrangian and Eulerian description in the framework of ANCF is adopted to take the length variation and large deformation of the tether into account.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Effects of Orbital Perturbations on Deployment Dynamics of Tethered Satellite System Using Variable-Length Element

Bai

Jiang

2021

IEEE Access

View full text Add to dashboard Cite

Orbital perturbations caused by the space environment will induce deviations compared with the prescribed motion trajectory or dynamic performance of the tethered satellite system (TSS). To comprehensively investigate the effects of the orbital perturbations on the TSS, a precise variable-length element that can describe the large deformation and flexibility of the tether is adopted in this paper to predict the deployment dynamics considering orbital perturbations, including atmospheric drag, solar pressure, lunisolar gravitation, and J2 perturbation. To this end, the variable-length element using arbitrary Lagrangian-Eulerian (ALE) description in the frame work of absolute nodal coordinate formulation (ANCF) is developed firstly. Subsequently, the dynamic governing equations for the TSS are established in the context of ANCF with the employment of ANCF reference node (ANCF-RN). Effects of orbital perturbations including atmospheric drag, solar pressure, lunisolar gravity and J2 perturbation on the dynamics of an optimal deployment are analyzed numerically. It is shown that the orbital perturbations except the J2 perturbation will induce the out-of-plane motion of the TSS. Additionally, the tether tension is less affected by the orbital perturbations. By contrast, the lunisolar gravitation will induce a deviation on the motion path of satellite, which should be considered in the design phase of the TSS.

show abstract

Section: A Dynamic Equations Of Variable-length Tethermentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Effects of Orbital Perturbations on Deployment Dynamics of Tethered Satellite System Using Variable-Length Element

Bai

Jiang

2021

IEEE Access

View full text Add to dashboard Cite

show abstract

“…The sliding joint on flexible beam [1][2][3][4] is widely used in dynamic modeling of practical engineering systems, such as pantograph/catenary system [5,6], tethered satellite system [7,8] and arresting system [9]. The variable-length ALE-ANCF finite element [10,11] which can be used to efficiently and effectively implement the sliding joint dynamic model, has been established based on ANCF [12][13][14][15][16] in the framework of ALE description.…”

Section: Introductionmentioning

confidence: 99%

A Variable-length Rational Finite Element Based On The Absolute Nodal Coordinate Formulation

Ding¹,

Ouyang²

2022

Preprint

View full text Add to dashboard Cite

The variable-length arbitrary Lagrange-Euler (ALE)-ANCF finite element, which employ nonrational interpolating polynomials, cannot exactly describe the rational cubic Bezier curves such as conic and circular curves. The rational absolute nodal coordinate formulation (RANCF) finite element, whose reference length (undeformed length) is constant, can exactly represent the rational cubic Bezier curves. A new variable-length finite element called the ALE-RANCF finite element, which is capable of accurately describe the rational cubic Bezier curves, is proposed by combining the desirable features of the ALE-ANCF and RANCF finite element. In order to control the reference length of ALE-RANCF element within a suitable range, element segmentation and merging schemes are proposed. It is demonstrated that exact geometry and mechanic is maintained after the ALE-RANCF element is divided into two shorter ones, and compared with the ALE-ANCF elements, there are smaller deviations and oscillations after two ALE-RANCF elements are merged into a longer one. Numerical examples are presented and the feasibility and advantages of the ALE-RANCF finite element are demonstrated.

show abstract

“…One feasible approach is to employ thrusters in the deployment control strategy. In [17], apart from the constant tether length law, thrust forces, acting on the subsatellites of a TSF system at the L2 point, are applied to keep the flexible tethers taut and enhance the control of libration motions during tether deployment.…”

Section: Introductionmentioning

confidence: 99%

“…min   denote the largest and smallest eigenvalues of a matrix, respectively.It can be seen that Eq. (19) guarantees the globally uniformly ultimate boundness of the system shown in Eq (17)…”

mentioning

confidence: 99%

Deployment of Hub-Spoke Tethered Satellite Formation with Adaptive Sliding Mode Tension Control

Liu

Wang

Kang

et al. 2021

Preprint

View full text Add to dashboard Cite

This paper studies the deployment control of a spinning hub-spoke tethered satellite formation, which is a challenging issue due to the strong nonlinear coupling between the hub and sub-satellites, and the underactuated nature of the system if no thrust is used for control. The mathematical model of the formation system is established based on the assumption of rigid body of the hub, inextensible tether, and lumped masses of the sub-satellites. Two novel formation deployment controllers are proposed based on tension control and hybrid tension-thrust control strategies, where underactuated sliding mode control and nonsingular terminal sliding mode control method are used, respectively. The adaptive control theory is adopted to estimate the unknown upper bound of the gravitational perturbation caused by the rotation of the system around the hub. It can be proven by the Lyapunov theory that the close-loop systems have bounded and asymptotic stability under these two deployment controllers, respectively. Finally, numerical simulations are conducted to validate the effectiveness and robustness of the proposed controllers.

show abstract

Dynamics of a tethered satellite formation for space exploration modeled via ANCF

Cited by 31 publications

References 15 publications

Effects of Orbital Perturbations on Deployment Dynamics of Tethered Satellite System Using Variable-Length Element

Effects of Orbital Perturbations on Deployment Dynamics of Tethered Satellite System Using Variable-Length Element

A Variable-length Rational Finite Element Based On The Absolute Nodal Coordinate Formulation

Deployment of Hub-Spoke Tethered Satellite Formation with Adaptive Sliding Mode Tension Control

Contact Info

Product

Resources

About