Deployment and retrieval of tethered satellite system under J2 perturbation and heating effect

Yu, B.S.; Jin, Dongping

doi:10.1016/j.actaastro.2010.05.013

Cited by 31 publications

(8 citation statements)

References 14 publications

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“…Moreover, a similar impact behavior was witnessed in a multiapplication survivable tether (MAST) experiment [3]. Furthermore, numerical simulations have indicated that vibroimpacts occurred at the end of the free deployment of a flexible tethered satellite system, as shown in Figure 1 [4]. Matunaga et al [5] pointed out that the impact phenomena in a tethered satellite system are caused by a sudden tensioning force in the tether.…”

Section: Introductionmentioning

confidence: 81%

Vibroimpact Dynamics of a Tethered Satellite System

Wen

2017

Shock and Vibration

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This paper presents the vibroimpact dynamics of an in-plane tethered subsatellite caused by sudden braking during deployment or retrieval. The full dynamics of the subsatellite are composed of its free-flight and the instantaneous impacts. At the moment of impact, the reflective angle of the subsatellite is envisioned to be equal to its incident angle such that the impact law is obtained. Then, the stability of the periodic vibroimpacts is analyzed using the composite Poincaré map. Further, the vibroimpact responses that do not exceed a specified region are numerically determined via the cell mapping method.

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Section: Introductionmentioning

confidence: 81%

Vibroimpact Dynamics of a Tethered Satellite System

Wen

2017

Shock and Vibration

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“…Since the thermal flux due the tether conduction flow Q CON is less significant, it can be safely ignored in Eq. (21) [20].The detailed expressions of each thermal flux and correspondence coefficients can be founded in [20,21]. Then, the Article in Advance / LI ET AL.…”

Section: Thermal Flux Effectmentioning

confidence: 99%

“…Williams et al showed that the variation of temperature along the tether strongly influenced the dynamics of capture maneuvers [20]. Yu and Jin found that the thermal effect had a quite different dynamic effect during the retrieval of tethered satellites [21]. For EDT systems, the temperature variation of tethers between day and night affects the internal stress, conductivity/resistance, and thermal properties, which leads to the variation of electrodynamic force and tether longitudinal oscillation.…”

Section: Introductionmentioning

confidence: 99%

Libration Control of Bare Electrodynamic Tethers Considering Elastic–Thermal–Electrical Coupling

Zhu

Cain

et al. 2016

Journal of Guidance, Control, and Dynamics

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The paper investigates the elastic, thermal, and electrical coupling effects on the dynamics and libration stability of flexible bare electrodynamic tethers in the end-of-mission satellite deorbit. A high-fidelity model is developed by considering transverse and longitudinal dynamics and libration dynamics of the tether and environmental effects with the latest models for atmospheric and plasma density, as well as Earth gravity and magnetic fields. The long-term orbital and libration dynamics of the tether are analyzed by a nodal position finite element method and symplectic time integration. Orbital motion limited theory is used to model the electron collection by bare electrodynamic tethers, whereas a Fowler-Nordheim equation is used for a Spindt array cathode. The thermal effect and its coupling with the dynamics of electrodynamic tethers are investigated parametrically. It is found that the thermal effect significantly affects the stability of electrodynamic tethers, which must be considered in the stability control. Two practical and effective electrical current on/off control strategies are developed based on the libration energy and libration angles. Although the libration energy control is found to be more stable and efficient than the libration angle control, the latter is more appealing for practical applications due to its simplicity and low computational effort. NomenclatureA t , A s = cross section or stress area of tether and projected drag area of satellite, m 2 B g = vector of Earth magnetic field strength in the global frame, T c m = specific heat of tether material, J · kg · K −1 d = tether diameter, m e E = eccentricity of electrodynamic tether orbital plane H 0 = Hamiltonian of tethered system in equilibrium configuration, J I t = electrical current at electron emitter device, A L, L = total and characteristic length of tether, m L e0 L e = unstretched length (instant length) of tether element, m M yaw , M in , M out = components of electrodynamic torque in system orbital frame, N · m n orb = orbital mean motion, rad · s −1 Q = thermal flux, W · m 2 R e = electrical resistance in tether, Ω R, S, W = unit vector of orbital frame of tethered system T, T 0 = instant and initial temperature, K t = time t, n, b = unit vectors of the local frame of tether element V cc = potential bias at the cathodic end C with respect to the ambient plasma, V X, Y, Z = components of position vector in global geocentric inertial frame, m Z T = impedance of emitter device, Ω α, _ α = pitch angle and pitch angular velocity of virtual tether, rad α p , _ α p = periodic solution of pitch angle, rad; and angular velocity of virtual tether, rad · s −1 α s ∕ε = ratio of absorptivity to emissivity of the tether β, _ β = roll angle, rad; and angular velocity of virtual tether, rad · s −1 θ, θ 0 = north latitude and colatitude, rad λ = east longitude, rad μ g = gravitational constant of Earth, m 3 s −2 ρ a ,ρ t = atmospheric density and material density of tether, kg · m −3 σ = electrical conductivity of tether material, Ω −1...

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“…Based on the rod model, Wu et al [20] developed a linearized relative motion model of the TSS considering the J2 perturbation, and the dynamics of a fuel-optimal deployment was discussed. On the basis of the lumped mass model, Yu et al [21] investigated the effect of J2 perturbation and thermal effect, which indicated that the effect of J2 perturbation depends on the magnitude of sliding friction. Further, considering the space environment including the J2 perturbation, the atmospheric drag, and solar pressure, an analytical control low of the tether was presented [22].…”

Section: Introductionmentioning

confidence: 99%

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

Bai

Jiang

2021

IEEE Access

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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.

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Deployment and retrieval of tethered satellite system under J2 perturbation and heating effect

Cited by 31 publications

References 14 publications

Vibroimpact Dynamics of a Tethered Satellite System

Vibroimpact Dynamics of a Tethered Satellite System

Libration Control of Bare Electrodynamic Tethers Considering Elastic–Thermal–Electrical Coupling

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

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