Multi-objective Optimization for Time-Open Lambert Rendezvous Between Non-coplanar Orbits

Wu, Guan-qun; Tan, Li; Li, Xin; Song, Shenmin

doi:10.1007/s42405-019-00231-z

Cited by 6 publications

(4 citation statements)

References 23 publications

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“…Wu et al proposed an adaptive evolutionary strategy to improve the NSGA2 algorithm. For the multi-impulse Lambert problem, the burnup and flight time are used as the optimization objectives for global optimization [16]. However, this kind of multi-objective optimization algorithm based on the Pareto concept increases the complexity of individual sorting and makes the calculation longer.…”

Section: Introductionmentioning

confidence: 99%

A time-fuel hybrid optimal guidance for micro/nano satellite’s glideslope approach

Zeng,

Xu,

Chen

et al. 2024

J. Phys.: Conf. Ser.

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Aimed at the trajectory planning problem of micro/nano satellites’ approaching missions under multiple constraints, this paper proposes a V-bar glideslope maneuver optimization method considering both time and fuel consumption. A dual-objective trajectory optimization model is established based on the CW motion equation, considering the constraints of trajectory and impulse. The optimal solution set of the glideslope point position and maneuvering time is obtained by employing the NSGA2 algorithm. In order to reduce computational complexity, a method for simplifying trajectory optimization is proposed. By solving a constrained dual-impulse optimization problem, the feasible range of distance and transfer time between adjacent glideslope points are obtained, which transforms the constraint equations of the glideslope maneuver optimization into the search space of optimization variables. The problem is simplified to an unconstrained optimization problem. Finally, a simulation is conducted with the approaching mission of a typical micro/nano satellite. The results demonstrate that the proposed method can provide an optimal solution set considering both fuel and time consumption, offering a flexible maneuver planning strategy for on-orbit application.

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Section: Introductionmentioning

confidence: 99%

A time-fuel hybrid optimal guidance for micro/nano satellite’s glideslope approach

Zeng,

Xu,

Chen

et al. 2024

J. Phys.: Conf. Ser.

View full text Add to dashboard Cite

show abstract

“…Wu improved the NSGA2 algorithm with an adaptive evolutionary strategy. It enhanced the diversity and convergence of time-fuel consumption optimization for multi-pulse lambert problem [15] .…”

Section: Introductionmentioning

confidence: 99%

A multi-segment multi-pulse maneuver control method for micro satellite

Zeng

Chen

2023

J. Phys.: Conf. Ser.

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Aiming at the constraint due to micro satellite orbital maneuverability and relative navigation, a multi-segment multi-pulse maneuver control method is proposed for approaching a target satellite. Convert the along-track approaching trajectory into an impulsive control problem with fixed time and fixed distance. With time and distance from origin to destination as the optimization objectives, the time-distance optimal solution set is generated under the delta-v constraint and trajectory constraint. The planning function is obtained by fitting a segmented polynomial to the optimal solution set. In the approach mission, the maneuver time to reach the expected terminal is determined based on the planning function, and the approaching to the terminal is accomplished using fixed-time multi-pulse control. Based on the simulation scenario, a multi-segment maneuvering strategy is obtained according to the optimization result, and the mission simulation is completed using the three-pulse control. The results show that the proposed multi-segment multi-pulse maneuver control method can reliably complete the approach mission under the constraints.

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“…This algorithm is used to solve an optimal flight-path design for a constrained multi-objective aero-assisted vehicle trajectory optimization problem. An improved NSGA-II algorithm is developed in [5] for solving non-coplanar orbits transfers in multi-impulse Lambert rendezvous problems. The proposed algorithm benefits from a self-adaptive differential evolution technique to increase the efficiency of the algorithm.…”

Section: Introductionmentioning

confidence: 99%

Time-Varying Lyapunov Control Laws with Enhanced Estimation of Distribution Algorithm for Low-Thrust Trajectory Design

Shirazi

Holt

Armellín

et al. 2023

Springer Optimization and Its Applications

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Enhancements in evolutionary optimization techniques are rapidly growing in many aspects of engineering, specifically in astrodynamics and space trajectory optimization and design. In this chapter, the problem of optimal design of space trajectories is tackled via an enhanced optimization algorithm within the framework of Estimation of Distribution Algorithms (EDAs), incorporated with Lyapunov and Q-law feedback control methods. First, both a simple Lyapunov function and a Q-law are formulated in Classical Orbital Elements (COEs) to provide a closed-loop low-thrust trajectory profile. The weighting coefficients of these controllers are approximated with various degrees of Hermite interpolation splines. Following this model, the unknown time series of weighting coefficients are converted to unknown interpolation points. Considering the interpolation points as the decision variables, a black-box optimization problem is formed with transfer time and fuel mass as the objective functions. An enhanced EDA is proposed and utilized to find the optimal variation of weighting coefficients for minimum-time and minimum-fuel transfer trajectories. The proposed approach is applied in some trajectory optimization problems of Earth-orbiting satellites. Results show the efficiency and the effectiveness of the proposed approach in finding optimal transfer trajectories. A comparison between the Q-law and simple Lyapunov controller is done to show the potential of the potential of the EEDA in enabling the simple Lyapunov controller to recover the finer nuances explicitly given within the analytical expressions in the Q-law.

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Multi-objective Optimization for Time-Open Lambert Rendezvous Between Non-coplanar Orbits

Cited by 6 publications

References 23 publications

A time-fuel hybrid optimal guidance for micro/nano satellite’s glideslope approach

A time-fuel hybrid optimal guidance for micro/nano satellite’s glideslope approach

A multi-segment multi-pulse maneuver control method for micro satellite

Time-Varying Lyapunov Control Laws with Enhanced Estimation of Distribution Algorithm for Low-Thrust Trajectory Design

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