Design and optimization of low-thrust orbital phasing maneuver

Shang, Haibin; Shuai, Wang; Wu, Wenqi

doi:10.1016/j.ast.2015.02.003

Cited by 13 publications

(7 citation statements)

References 12 publications

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“…In cislunar setting, the design of this maneuver requires the non-negligible gravitational effects of Earth and Moon. Examples can be found in Bucchioni and Innocenti (2021b), Bucci et al (2017), Shang et al (2015), Blazquez et al (2018b), Blazquez et al (2018a), andGomez et al (2001). For the present analysis, the boundary conditions for the phasing trajectory were taken as follows:…”

Section: Phasingmentioning

confidence: 99%

Dynamics and control analysis during rendezvous in non-Keplerian Earth—Moon orbits

Innocenti

Bucchioni

Franzini³

et al. 2022

Front. Space Technol.

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The paper describes the development of a framework capable of addressing some fundamental issues in the analysis of proximity operations between two spacecraft that are operating within a three-body model defined by two primaries and the spacecraft themselves. The main objective is to enable the capability of analysing dynamic and control issues during an automated rendezvous between a vehicle and a passive space station orbiting around the Earth - Moon L2 Lagrangian point on a near rectilinear halo orbit. The paper presents first a restricted three body model dynamics and a nominal approach trajectory, followed by an analysis of the influence of assumed actuators and sensors. Critical aspects such as selected failures are investigated, in order to ensure passive safety of the mission using impulsive maneuvers. An example of closed loop guidance in the near range is also presented and the overall performance are validated with an Ephemeris model available in the literature.

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Section: Phasingmentioning

confidence: 99%

Dynamics and control analysis during rendezvous in non-Keplerian Earth—Moon orbits

Innocenti

Bucchioni

Franzini³

et al. 2022

Front. Space Technol.

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“…By using the normalization of the initial costate vector [32], the upper and lower bounds of the costate variables can be normalized to be [−1,1]. As to the terminal time variable t f , the upper and lower bound can be estimated from the analytical phasing maneuver time ∆t 1 [19] and the plane change time ∆t 2 [24], and is obtained as follows:…”

Section: Trajectory Optimization With the Averaged Orbital Dynamicsmentioning

confidence: 99%

“…Hall et al [18] solved the time-optimal coplanar LORP using indirect optimization method. Shang et al [19] extended the phasing problem on circular orbits to that on general elliptical orbits using the direct optimization method. Zhao et al [20] proposed an analytical costate approximate method for the minimum-time station-change problem in GEOs.…”

Section: Introductionmentioning

confidence: 99%

Practical Optimization of Low-Thrust Minimum-Time Orbital Rendezvous in Sun-Synchronous Orbits

Ma¹,

Wen²,

Zhang³

2021

Computer Modeling in Engineering &Amp; Sciences

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High-speci c-impulse electric propulsion technology is promising for future space robotic debris removal in sun-synchronous orbits. Such a prospect involves solving a class of challenging problems of low-thrust orbital rendezvous between an active spacecra and a free-ying debris. This study focuses on computing optimal lowthrust minimum-time many-revolution trajectories, considering the e ects of the Earth oblateness perturbations and null thrust in Earth shadow. Firstly, a set of mean-element orbital dynamic equations of a chaser (spacecra ) and a target (debris) are derived by using the orbital averaging technique, and speci cally a slow-changing state of the mean longitude di erence is proposed to accommodate to the rendezvous problem. Subsequently, the corresponding optimal control problem is formulated based on the mean elements and their associated costate variables in terms of Pontryagin's maximum principle, and a practical optimization procedure is adopted to nd the speci c initial costate variables, wherein the necessary conditions of the optimal solutions are all satis ed. A erwards, the optimal control pro le obtained in mean elements is then mapped into the counterpart that is employed by the osculating orbital dynamics. A simple correction strategy about the initialization of the mean elements, speci cally the di erential mean true longitude, is suggested, which is capable of minimizing the terminal orbital rendezvous errors for propagating orbital dynamics expressed by both mean and osculating elements. Finally, numerical examples are presented, and speci cally, the terminal orbital rendezvous accuracy is veri ed by solving hundreds of rendezvous problems, demonstrating the e ectiveness of the optimization method proposed in this article.

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“…Direct methods, on the other hand, discretize the control and state variables, transforming the continuous optimal control problem into a constrained finite-dimensional parameter optimization problem. Nonlinear programming methods are then used to solve it [6][7][8]. Direct methods have some advantages such as not requiring an initial guess for the co-state variable, having simple operations, wide convergence domains, and the ability to handle complex constraints.…”

Section: Introductionmentioning

confidence: 99%

Low-thrust trajectory optimization of deep space exploration based on discrete pulse method

Qin,

Shang,

Dong

et al. 2024

J. Phys.: Conf. Ser.

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Deep space exploration is gradually becoming the hot mission of human space activities, and this kind of mission has the characteristics of a long mission cycle, complex space environment, high fuel demand, and difficult telemetry track and command, etc. It is the future trend to carry out deep space exploration activities using low-thrust propulsion systems, and the trajectory optimization of interplanetary missions is one of the significant difficulties. Considering the characteristics and difficulties of interplanetary missions, a method of transfer orbit preliminary design in the multi-body system is proposed in this paper. The simulation results illustrate that the transfer orbit obtained by the method in this paper can provide a reliable initial guess for the optimization of high-precision orbit and decrease convergence sensitivity. The research results can provide a significant reference for the implementation of deep space exploration missions in China in the future.

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Design and optimization of low-thrust orbital phasing maneuver

Cited by 13 publications

References 12 publications

Dynamics and control analysis during rendezvous in non-Keplerian Earth—Moon orbits

Dynamics and control analysis during rendezvous in non-Keplerian Earth—Moon orbits

Practical Optimization of Low-Thrust Minimum-Time Orbital Rendezvous in Sun-Synchronous Orbits

Low-thrust trajectory optimization of deep space exploration based on discrete pulse method

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