Optimal short-range rendezvous using on–off constant thrust

Zhang, Gang; Ye, Dong

doi:10.1016/j.ast.2017.06.029

Cited by 12 publications

(5 citation statements)

References 26 publications

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“…In references [ 22 , 25 ], a tangential maneuvering strategy is used to obtain the minimum fuel consumption, which is an optimal strategy for the case where the eccentricity dominates the conformational divergence. In contrast to the studies described,

is the main divergence element in the study, which is caused by the geometrical differences of the orbits; for this reason, in-plane control simultaneously in the radial and tangential directions is a more efficient option.…”

Section: Continuous Low-thrust Maneuver Planning Via Improved Particl...mentioning

confidence: 99%

“…Di Mauro [ 22 , 23 , 24 ] presents a solution to the minimum-fuel spacecraft formation reconfiguration maneuver in J 2 perturbed near-circular orbits and subsequently investigates several flight scenarios by analytical and numerical methods. Zhang [ 25 ] proposes a control parameter direct optimization method for the optimal short-range elliptic orbit rendezvous problem using on–off constant thrust; during the study, the optimal control problem is transformed into a nonlinear programming problem with bound constraints on the optimization variables and terminal equality constraints. The aforementioned continuous control strategies can provide a reference for the reconfiguration control of a gravitational wave formation, but the current research mostly concentrates on near-ground scenarios; therefore, related research still needs to be refined and improved in order to be adaptable to the high Earth orbit environment while meeting the limitations of poor maneuverability, a long mission period, and high accuracy requirements in gravitational wave missions.…”

Section: Introductionmentioning

confidence: 99%

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Continuous Low-Thrust Maneuver Planning for Space Gravitational Wave Formation Reconfiguration Based on Improved Particle Swarm Optimization Algorithm

Wang

Lian

et al. 2023

Sensors

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This study proposes a three-spacecraft formation reconfiguration strategy of minimum fuel for space gravitational wave detection missions in the high Earth orbit (105 km). For solving the limitations of measurement and communication in long baseline formations, a control strategy of a virtual formation is applied. The virtual reference spacecraft provides a desired relative state between the satellites, which is then used to control the motion of the physical spacecraft to maintain the desired formation. A linear dynamics model based on relative orbit elements’ parameterization is used to describe the relative motion in the virtual formation, which facilitates the inclusion of J2, SRP, and lunisolar third-body gravity effects and provides a direct insight into the relative motion geometry. Considering the actual flight scenarios of gravitational wave formations, a formation reconfiguration strategy based on continuous low thrust is investigated to achieve the desired state at a given time while minimizing interference to the satellite platform. The reconfiguration problem is considered a constrained nonlinear programming problem, and an improved particle swarm algorithm is developed to solve this problem. Finally, the simulation results demonstrate the performance of the proposed method in improving the maneuver sequence distribution and optimizing maneuver consumption.

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Section: Continuous Low-thrust Maneuver Planning Via Improved Particl...mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Continuous Low-Thrust Maneuver Planning for Space Gravitational Wave Formation Reconfiguration Based on Improved Particle Swarm Optimization Algorithm

Wang

Lian

et al. 2023

Sensors

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show abstract

“…A suitable optimization method is used to determine the optimal set of control variables that minimize the total velocity variation required by the inspection maneuver. Since the objective function in this class of problems is usually characterized by a high number of local minima [11,12], global optimization algorithms are used to estimate the optimal relative trajectory of the IS. The results are then further refined with the aid of local optimization algorithms.…”

Section: Introductionmentioning

confidence: 99%

Optimal On-Orbit Inspection of Satellite Formation

et al. 2022

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In a formation-flying mission where multiple spacecraft must cooperate and maintain a prescribed relative separation, the early detection of possible anomalies is a primary requirement. This is possible, for example, by employing an inspector spacecraft whose aim is to monitor the condition of the formation members with an on-orbit inspection. This paper analyzes a rest-to-rest multiple-impulse transfer that the inspector spacecraft must accomplish to visit all of the formation members. The problem is studied using the linearized Hill–Clohessy–Wiltshire equations and is solved in an optimal framework by minimizing the total velocity variation along the transfer trajectory. The solution algorithm implements a two-step procedure that combines differential evolution algorithms and Nelder–Mead simplex method-based routines. A case study is thoroughly investigated where a formation of six satellites covers a circular orbit of altitude 300km over Earth. The proposed algorithm could efficiently find a solution and with reduced computational times.

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“…However, the method proposed in this study is only valid for circular orbits. Zhang and Ye 22 introduced a control parameter direct optimization method for the optimal short-range elliptic orbital rendezvous problem using on–off constant thrust. In their paper, the along-track thrust and the non-radial (i.e.…”

Section: Introductionmentioning

confidence: 99%

Optimal control of rapid cooperative spacecraft rendezvous with multiple specific-direction thrusts

Feng

Yang

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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Focusing on the long-distance rapid cooperative rendezvous of two spacecraft under finite continuous thrust, this paper proposes a practical strategy for space operation using multiple specific-direction thrusts. Based on the orbital dynamic theory and Pontryagin’s maximum principle, the dynamic equations and optimal control equations for radial, circumferential, and normal thrust are determined. The optimization method is a hybrid algorithm. The initial costate variables for the fuel-optimal rapid cooperative rendezvous problem are obtained using quantum particle swarm optimization and subsequently set as the initial values in the sequence quadratic programming to search for the exact convergent solution. The elliptical and near-circular mission orbital rendezvous for spacecraft with multiple specific-direction thrusts are simulated and optimized. Numerical examples verifying the proposed method are provided. The results facilitate easier realization of rapid spacecraft maneuvering under continuous thrust conditions.

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Optimal short-range rendezvous using on–off constant thrust

Cited by 12 publications

References 26 publications

Continuous Low-Thrust Maneuver Planning for Space Gravitational Wave Formation Reconfiguration Based on Improved Particle Swarm Optimization Algorithm

Continuous Low-Thrust Maneuver Planning for Space Gravitational Wave Formation Reconfiguration Based on Improved Particle Swarm Optimization Algorithm

Optimal On-Orbit Inspection of Satellite Formation

Optimal control of rapid cooperative spacecraft rendezvous with multiple specific-direction thrusts

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