Biobjective mission planning for geosynchronous satellites on-orbit refueling

Yu, Jian; Yu, Yonggang; Dong, Hai‐Lin; Chen, Xiaoqian; Li, Hongyang

doi:10.1177/0954410017740383

Cited by 7 publications

(5 citation statements)

References 22 publications

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“…By converting the problem into a Location-Route Problem (LRP), a service plan is given in Ref. [17], same as in Ref [22][23][24][25][26]. While some others solved the problem by converti ng it into an Optimal Matching Problem (OMP) [18][19] or a mixed mode [20][21].…”

Section: Mtmmentioning

confidence: 99%

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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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Section: Mtmmentioning

confidence: 99%

“…In addition, according to formula (25), it can be obtained that the range of the semi-major axis for traverse is East Drift 150 75…”

Section: B Longitude Drift Ratementioning

confidence: 99%

A Traverse Inspection Constellation for GEO Quasi-Stationary Satellites

Chen,

Zhang,

Xue

2024

IEEE Access

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“…The refueling strategies can be divided into three main categories: one-to-many [15], many-to-many [31], and peer-to-peer [19]. For the one-to-many strategy, the number of fuel-deficient targets that could be refueled is quite small due to the limited fuel capacity of Ssc.…”

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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“…The on-orbit service (OOS) technology is mainly used for on-orbit maintenance of spacecraft, quickly solving the problems of spacecraft in space and extending the service life of spacecraft. 1,2 Since the concept of the OOS technology was put forward, 3,4 it has been applied to practical space missions for many times. For example, the damaged solar array of the Skylab was repaired by the OOS technology; many OOS technologies such as on-orbit spacecraft assembly and component replacement have also been applied in the on-orbit flight of spacecraft.…”

Section: Introductionmentioning

confidence: 99%

Fast cooperative angular trajectory planning for multiple on-orbit service spacecraft based on the Bezier shape-based method

Fan

Huo

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this article, a fast cooperative obstacle avoidance angular trajectory planning method is presented for multiple on-orbit service (OOS) spacecraft, which can obtain the spatial angular trajectories of multiple spacecraft in a considerably short time. For multiple OOS spacecraft equipped with the manipulator, under the constraints of the maximum control moment, multiple obstacles, dynamics, and geometry, the Bezier shape-based (SB) method is used to rapidly generate the cooperative obstacle avoidance attitude angular trajectories of all OOS spacecraft at the same time. The superiority of the proposed method is proved by comparing the results of Bezier SB method and the finite Fourier series (FFS) SB method under the same initial conditions. To further verify the effectiveness of the proposed method, the results of the Bezier method are substituted into the Gauss pseudospectral method (GPM) as the initial values to further optimize the angular trajectories in the simulation. Simulation results show that compared with the FFS SB method, the Bezier SB method can use shorter computation time to get the results of spacecraft attitude movement faster; compared with GPM, Bezier SB method only uses about 2% of computation time to get the results of movement time difference of only 2%. The method proposed in this article can be applied to complex space OOS missions, which requires multiple OOS spacecraft to rapidly realize the space obstacle avoidance attitude maneuver to complete cooperative operation missions.

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Biobjective mission planning for geosynchronous satellites on-orbit refueling

Cited by 7 publications

References 22 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

Fast cooperative angular trajectory planning for multiple on-orbit service spacecraft based on the Bezier shape-based method

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