Optimal transfer schemes between space debris objects in geostationary orbit

Баранов, А. А.; Гришко, Д. А.; Khukhrina, О.I.; Chen, Danhe

doi:10.1016/j.actaastro.2020.01.001

Cited by 15 publications

(3 citation statements)

References 16 publications

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“…The resulting velocity pulse values from (12) and (13), gained over one enabling cycle, and the number of times ERPS is enabled fully characterize the energy costs of the de-orbiting process and do not depend on the characteristics of a particular propulsion system.…”

Section: Devising a Methodology For Determining The Parameters Of Thementioning

confidence: 99%

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Development of the combined method to de-orbit space objects using an electric rocket propulsion system

Golubek

Dron

Dubovik

et al. 2020

EEJET

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A method has been developed for the combined de-orbiting of large-size objects of space debris from low-Earth orbits using an electro-rocket propulsion system as an active de-orbiting means. A principal de-orbiting technique has been devised, which takes into consideration the patterns of using an electric rocket propulsion system in comparison with the sustainer rocket propulsion system. A procedure for determining the parameters of the de-orbiting scheme has been worked out, such as the minimum total speed and the time of the start of the de-orbiting process, which ensures its achievement. The proposed procedure takes into consideration the impact exerted on the process of the de-orbiting by the ballistic factor of the object, the height of the initial orbit, and the phase of solar activity at the time of the de-orbiting onset. The actual time constraints on battery discharge have been accounted for, as well as on battery charge duration, and active operation of the control system. The process of de-orbiting a large-size object of space debris has been simulated by using the combined method involving an electro-rocket propulsion system. The impact of the initial orbital altitude, ballistic coefficient, and the phase of solar activity on the energy costs of the de-orbiting process have been investigated. The dependences have been determined of the optimal values of a solar activity phase, in terms of energy costs, at the moment of the de-orbiting onset, and the total velocity, required to ensure the de-orbiting, on the altitude of the initial orbit and ballistic factor. These dependences are of practical interest in the tasks of designing the means of the combined de-orbiting involving an electric rocket propulsion system. The dependences of particular derivatives from the increment of a velocity pulse to the gain in the ballistic factor on the altitude of the initial orbit have been established. The use of these derivatives is also of practical interest to assess the effect of unfolding an aerodynamic sailing unit

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Section: Devising a Methodology For Determining The Parameters Of Thementioning

confidence: 99%

“…Their task is to ensure the de-orbiting of passive objects. Thus, to clean geostationary orbits, paper [13] proposed using a special active dispenser. The authors developed two schemes of de-orbiting objects from geostationary orbits.…”

Section: Literature Review and Problem Statementmentioning

confidence: 99%

Development of the combined method to de-orbit space objects using an electric rocket propulsion system

Golubek

Dron

Dubovik

et al. 2020

EEJET

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“…In the past few years, on-orbit servicing compromising refueling, repairs, and upgrades has acquired significant attention because it would enhance the operational life and capability of space systems [1][2][3][4][5][6][7][8]. Long et al [9] summarized five broad categories of benefits of servicing: (1) reduce risk of mission failure, (2) reduce mission cost, (3) increase mission performance, (4) improve mission flexibility, and (5) enable new missions.…”

Section: Introductionmentioning

confidence: 99%

Multiobjective Mission Planning for Multiple Geosynchronous Spacecraft Refueling

Kong,

Zhou

2023

International Journal of Aerospace Engineering

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This paper studies the multiple geosynchronous spacecraft refueling problem (MGSRP) with multiple servicing spacecraft (Ssc) and fuel depots (FDs). In the mission scenario, multiple Ssc and FDs are parked in the geosynchronous Earth orbit (GEO) initially. Ssc start from FDs and maneuver to visit and refuel multiple GEO targets with known demands. These capacitated Ssc are expected to rendezvous with fuel-deficient GEO targets and FDs for the purpose of delivering the fuel stored in FDs to GEO targets. The objective is to find a set of Pareto-optimal solutions with minimum fuel cost and mission duration. The MGSRP is a much more complex variant of multidepot vehicle routing problems mixing discrete and continuous variables. A two-nested optimization model is built. We propose a new multiobjective hybrid particle swarm optimization to solve the outer-loop problem, and the design variables are the refueling sequence, task assignment, time distribution, and locations of FDs. In the inner-loop problem, branch and bound method is used to find the optimal decision variable for a given outer-loop solution. Finally, numerical simulations are presented to illustrate the effectiveness and validity of the proposed approach.

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Low-thrust Lambert transfer based on two-stage constant-vector thrust control method

Sun

Bai²

2022

Nonlinear Dyn

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Optimal transfer schemes between space debris objects in geostationary orbit

Cited by 15 publications

References 16 publications

Development of the combined method to de-orbit space objects using an electric rocket propulsion system

Development of the combined method to de-orbit space objects using an electric rocket propulsion system

Multiobjective Mission Planning for Multiple Geosynchronous Spacecraft Refueling

Low-thrust Lambert transfer based on two-stage constant-vector thrust control method

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