Prospects of Using a Pulsed Electrostatic Tractor With Nominal Geosynchronous Conditions

Hughes, Joseph; Schaub, Hanspeter

doi:10.1109/tps.2017.2684621

Cited by 15 publications

(2 citation statements)

References 17 publications

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“…Apart from the deorbit removal methods for spacecraft at the end of mission life, i.e., drag sail [23], inflate-sail [24], and electrodynamic tether [25], contactless active removal methods such as Coulomb thrusting [26], laser beam [27], artificial atmosphere [28], and expanding foam [29] have been proposed in the application of space debris mitigation. Coulomb thrusting removal is applicable only when the Debye shielding is weak [30,31]. Laser beam removal can only remove very small debris [32,33].…”

Section: Introductionmentioning

confidence: 99%

Multiple SSO Space Debris Flyby Trajectory Design Based on Cislunar Orbit

Zhang,

Wang

2024

Universe

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This paper investigates the trajectory design problem in the scenario of a multiple Sun-synchronous Orbit (SSO) space debris flyby mission from a DRO space station. At first, the characteristics of non-planar transfer from DRO to SSO in the Earth–Moon system are analyzed. The methods of large-scale ergodicity and pruning are utilized to investigate single-impulse and two-impulse DRO–Earth transfers. Using a powered lunar flyby, the two-impulse DRO–Earth transfer is able to fly by SSO debris while satisfying the requirements of the mission. After the local optimization, the optimal result of two-impulse DRO–Earth transfer and flyby is obtained. A multi-objective evolutionary algorithm is used to design the Pareto-optimal trajectories of multiple flybys. The semi-analytical optimization method is developed to provide the estimations of the transfer parameters in order to reduce the computations caused by the evolutionary algorithm. Simulations show that transferring from the 3:2 resonant DRO to a near-coplanar flyby of a SSO target debris using a powered lunar gravity assist needs a 0.47 km/s velocity increment. The mission’s total velocity increment is 1.39 km/s, and the total transfer time is 2.23 years.

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Section: Introductionmentioning

confidence: 99%

Multiple SSO Space Debris Flyby Trajectory Design Based on Cislunar Orbit

Zhang,

Wang

2024

Universe

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“…Close-proximity spacecraft formation has huge potential in telescope-occulter pairs, space-borne interferometry, and Earth imaging [1]. The fast throttle ability and avoidance of plume impingement issues of Coulomb control make it get attracted sustained attention in close-proximity formation mission design [2]. By actively charging spacecraft, repulsive and attractive forces can be generated to execute Coulomb control over a close formation.…”

Section: Introductionmentioning

confidence: 99%

High-order analytical solutions of bounded relative motions for Coulomb formation flying

Lin

Zhang

et al. 2023

Nonlinear Dyn

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Close-proximity Coulomb formation flying offers attractive prospects in multiple astronautical missions. An analytical method of constructing the series solution up to an arbitrary order for the relative motion near the equilibrium of Coulomb formation systems is proposed to facilitate the design of Coulomb formations based on a Lindstedt-Poincaré method. The details of the series expansion and coefficient solution for Lissajous orbits and arbitrary m : n-period orbits are discussed. To verify the effectiveness of the Lindstedt-Poincaré method in constructing series solutions, the practical convergence domain of series solutions for various bounded orbits is computed by comparison with the corresponding exact numerical solutions. Given the accuracy requirements of practical formation missions, the configuration design for the Coulomb formation can be carried out conveniently and quickly by employing the proposed series solutions.

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Application of Lagrangian coherent structures to Coulomb formation on elliptic orbit

Lin

Zheng

2020

Nonlinear Dyn

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Prospects of Using a Pulsed Electrostatic Tractor With Nominal Geosynchronous Conditions

Cited by 15 publications

References 17 publications

Multiple SSO Space Debris Flyby Trajectory Design Based on Cislunar Orbit

Multiple SSO Space Debris Flyby Trajectory Design Based on Cislunar Orbit

High-order analytical solutions of bounded relative motions for Coulomb formation flying

Application of Lagrangian coherent structures to Coulomb formation on elliptic orbit

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