Research on constellation refueling based on formation flying

Xu, Bo; Qian, Feng

doi:10.1016/j.actaastro.2010.11.012

Cited by 19 publications

(4 citation statements)

References 13 publications

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“…[8][9]. Genetic algorithms (GA), Particle Swarm Optimization (PSO) and other optimization algorith ms are also used to solve the problem [10][11][12][13][14][15].…”

Section: Otmmentioning

confidence: 99%

A Traverse Inspection Constellation for GEO Quasi-Stationary Satellites

Chen,

Zhang,

Xue

2024

IEEE Access

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Space-based observation can achieve close range, long-term, and multi-angle tracking and observation of space targets. In the current situation, where the capabilities of ground-based optical and radar equipment are insufficient, space-based observation is the only means to obtain detailed information of space targets, especially GEO quasi-stationary satellites. GEO quasi-stationary satellites are those GEO satellites with an inclination angle below 0.1 °which majority of are important strategic satellites for communication, early warning, and other purposes. It is also an important prerequisite and guarantee for developing GEO on-orbit service and operational technologies, and conducting relevant technical verification experiments. Traverse inspection, which means to observe and image all targets on GEO at close range by using one or more satellite, is one of the most important technologies. This paper focuses on the traverse inspection of GEO quasi-stationary targets, proposes a set of traverse inspection strategies and orbit design methods based on multiple longitude drift rates by combining the analysis of GEO target optical observation constraints, which including four steps: (1) Dividing the targets into different zones by using dichotomy approach; (2) Calculate the longitude drift rates based on targets' sub-satellite points in each zone; (3) Determine the observation position and moment based on the local time of each zone, combined with constraints; (4) Determine the transfer trajectory for east-west turn around with a dual pulse orbit maneuver. On this basis, the proposed strategies and methods were analyzed and validated in detail. The results showed that the traverse inspection orbit can effectively achieve traverse inspection of GEO quasi-stationary targets, with a traverse period of no more than 62 days and an energy consumption of no more than 0.022km/s. And, the total energy consumption of a single traverse cycle in all zones shall not exceed 0.11km/s.

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“…[8][9]. Genetic algorithms (GA), Particle Swarm Optimization (PSO) and other optimization algorith ms are also used to solve the problem [10][11][12][13][14][15].…”

Section: Otmmentioning

confidence: 99%

A Traverse Inspection Constellation for GEO Quasi-Stationary Satellites

Chen,

Zhang,

Xue

2024

IEEE Access

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“…The second type uses multiple servicing spacecraft to service multiple targets. Bo and Feng [16] proposed a new scheme for refueling spacecraft constellation, and the new pattern is based on formation flying. Both single-supplier refueling and double-supplier refueling were studied.…”

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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“…1 is also known as C-W equation or Hill equation [5,6]. The analytical solution of this equation is:…”

Section: Hill Equation Of Satellite Formation Flyingmentioning

confidence: 99%

Research on the Calculation Method of the Collision Probability of Satellite Formation Flying

He¹,

Zhang²

2017

dtetr

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Abstract. For some reasons (such as the failure of a satellite or the formation of a satellite formation mission), it is necessary to reconstruct the formation. In this process, the research on satellite collision avoidance has received extensive attention. In this paper, by deriving the initial state covariance matrix of the satellite, the collision probability density function was integrated in a specific region of the satellite, then the collision probability of formation satellites was obtained. The simulation experiments show that the method has great significance for the collision between satellites.

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Research on constellation refueling based on formation flying

Cited by 19 publications

References 13 publications

A Traverse Inspection Constellation for GEO Quasi-Stationary Satellites

A Traverse Inspection Constellation for GEO Quasi-Stationary Satellites

Multiobjective Mission Planning for Multiple Geosynchronous Spacecraft Refueling

Research on the Calculation Method of the Collision Probability of Satellite Formation Flying

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