Multisatellite Flyby Inspection Trajectory Optimization Based on Constraint Repairing

Peng, Chenyuan; Jin, Zhang; Yan, Bing; Luo, Yuling

doi:10.3390/aerospace8090274

Cited by 10 publications

(5 citation statements)

References 25 publications

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“…(3) The initial locations of FDs are not fixed, and they are instead design variables (4) The GEO targets are moving, while, of course, the customers are stationary (5) There are infinite possible trajectories to transfer from one GEO target to another (6) The objective is to minimize the fuel cost and mission duration simultaneously…”

Section: Mission Scenariomentioning

confidence: 99%

“…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%

See 1 more Smart Citation

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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Section: Mission Scenariomentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Multiobjective Mission Planning for Multiple Geosynchronous Spacecraft Refueling

Kong,

Zhou

2023

International Journal of Aerospace Engineering

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“…With the ever-lasting development and utilization of the space science and technology (Chen et al, 2023a(Chen et al, , 2023bChen et al, 2023aChen et al, , 2023b, the demand for space on-orbit service, such as on-orbit fuel filling, space debris cleaning and decommissioning of obsolete satellites, is enlarging (Chiu, 2019;Peng et al, 2021;Li et al, 2023). With the development of space on-orbit service technology, the demands on service satellite capabilities are becoming higher and higher.…”

Section: Introductionmentioning

confidence: 99%

“…, 2023a, 2023b; Chen et al. , 2023a, 2023b), the demand for space on-orbit service, such as on-orbit fuel filling, space debris cleaning and decommissioning of obsolete satellites, is enlarging (Chiu, 2019; Peng et al. , 2021; Li et al.…”

Section: Introductionmentioning

confidence: 99%

Research on relative reachable domain in target orbit for maneuvering spacecraft

Li,

Zhang

2024

AEAT

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Purpose Lots of successful space missions require that the maneuvering spacecraft can reach the target spacecraft. Therefore, research on relative reachable domain (RRD) in target orbit for maneuvering spacecraft is particularly important and is currently a hot-debated topic in the field of aerospace. This paper aims at analyzing and simulating the RRD in target orbit for maneuvering spacecrafts with a single fixed-magnitude impulse and continuous thrust, respectively, to provide a basis for analyzing the feasibility of spacecraft maneuvering missions and improving the design efficiency of spacecraft maneuvering missions. Design/methodology/approach Based on the kinematics model of relative motion, RRD in target orbit for maneuvering spacecraft with a single fixed-magnitude impulse can be calculated via analyzing the relationship between orbital elements, position vector and velocity vector of spacecrafts, and relevant studies are introduced to compare simulation results for the same case and validate the method proposed in the paper. With analysis of the dynamic model of relative motion, the calculation of RRD in target orbit for maneuvering spacecraft with continuous thrust can be transformed as the solution of the optimal control problem, and example emulations are carried out to validate the method. Findings For the case with a single fixed-magnitude impulse, simulation results show preliminarily that the method is in agreement with the method in Ref. (Wen et al., 2016), which treats the same case and thus is plausibly correct and feasible. For the case with continuous thrust, analysis and simulation results confirm the validity of the proposed method. The methods based on relative motion in this paper can efficiently determining the RRD in target orbit for maneuvering spacecraft. Originality/value Both theoretical analyses and simulation results indicate that the method proposed in this paper is comparatively simple but efficient for determine the RRD in target orbit for maneuvering spacecraft swiftly and precisely.

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“…Therefore, detecting or maintaining the satellites in these constellations has emerged as an essential research topic. The flyby multi-target problem [7,8], particularly the flyby non-coplanar multi-target problem [9,10], was investigated to some extent, but most solutions require numerous orbit maneuvers and are incredibly dependent on the ground station [11]. Minimizing the number of orbital maneuvers can effectively decrease the mission constraint, and thus, enhance the efficacy of each orbital maneuver; therefore, it is crucial to study the single-impulse flyby co-orbital multi-target problem.…”

Section: Introductionmentioning

confidence: 99%

Numerical Solution for the Single-Impulse Flyby Co-Orbital Spacecraft Problem

Su¹,

Dong²,

Liu³

et al. 2022

Aerospace

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The traversal inspection of satellites in satellite constellations or geosynchronous orbits has been a focus of research. A large number of variable orbit requirements in the “single-to-single” mode severely affects the efficiency of inspections. To address this problem, this study investigated the problem of a single-impulse flyby co-orbiting two spacecraft and proposed a derivative-free numerical solution method that used the geometric relationship between the two intersections of the target and transfer orbits of the flyby problem in order to transform them into a nonlinear equation in a single variable for a given impulse time. The validity of the proposed method was verified using numerical examples. While the Lambert problem is one of the bases for solving the variable orbit problem, on-star intelligent control also raises the requirements for speed. To address this problem, this study also investigated the Lambert problem in a single-impulse flyby co-orbiting two spacecraft and determined the iterative initial value by constructing a quadratic interpolation equation between the inverse of the transfer time and the vertical component of the eccentric vector, the derivative-free quadratic interpolation cut-off method was proposed. Using 100,000 random tests showed that computational efficiency was improved by more than one order of magnitude compared with commonly used methods, with a calculation error of less than 10−6.

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Multisatellite Flyby Inspection Trajectory Optimization Based on Constraint Repairing

Cited by 10 publications

References 25 publications

Multiobjective Mission Planning for Multiple Geosynchronous Spacecraft Refueling

Multiobjective Mission Planning for Multiple Geosynchronous Spacecraft Refueling

Research on relative reachable domain in target orbit for maneuvering spacecraft

Numerical Solution for the Single-Impulse Flyby Co-Orbital Spacecraft Problem

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