Interactive optimization approach for optimal impulsive rendezvous using primer vector and evolutionary algorithms

Luo, Yuling; Jin, Zhang; Li, Haiyang; Tang, Guojian

doi:10.1016/j.actaastro.2010.02.014

Cited by 40 publications

(18 citation statements)

References 8 publications

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“…Many numerical optimization methods are available to solve the linear impulsive trajectory optimization problem

{scriptP}_{0}

(see for the details). This paper does not intended to propose a new numerical optimization method for

{scriptP}_{0}

.…”

Section: Primer Vector Analysis and Problem Simplificationmentioning

confidence: 99%

Analytical fuel‐optimal impulsive reconfiguration of formation‐flying satellites

2016

Optim Control Appl Methods

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Summary This paper investigates fuel‐optimal impulsive reconfiguration of formation‐flying satellites near circular reference orbit. First, the general reconfiguration is transformed into reconfiguration that should be accomplished during multiple orbital periods of the chief. Then, based on the primer vector analysis, multiple‐impulse fuel‐optimal analytical solutions for the transformed reconfiguration are derived. It is shown that multiple‐impulse fuel‐optimal analytical solutions appear conjugated and the corresponding reconfiguration trajectories are symmetric about the chief. Furthermore, for fuel‐optimal analytical solution with three or more impulses, the associated impulse magnitudes may have many combinations, which would yield different reconfiguration trajectories but with the same fuel cost. Finally, numerical examples for three typical formation reconfiguration maneuvers, including resizing, reorientation, and reassignment, are given to illustrate and validate the obtained results. Copyright © 2016 John Wiley & Sons, Ltd.

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“…Many numerical optimization methods are available to solve the linear impulsive trajectory optimization problem

{scriptP}_{0}

(see for the details). This paper does not intended to propose a new numerical optimization method for

{scriptP}_{0}

.…”

Section: Primer Vector Analysis and Problem Simplificationmentioning

confidence: 99%

Analytical fuel‐optimal impulsive reconfiguration of formation‐flying satellites

2016

Optim Control Appl Methods

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“…To obtain global fuel‐optimal impulsive reconfiguration trajectories, a hybrid optimization method was proposed in the aforementioned work, in which the genetic algorithm performs a global search to find 2‐impulse trajectories, and then, with the 2‐impulse trajectories as initial guesses, primer vector analysis is utilized to find multiple‐impulse local optimal trajectories. An interactive optimization approach, which combines primer vector theory and evolutionary algorithms, is proposed in the work of Luo et al for fuel‐optimal impulsive rendezvous. A closed‐loop brain storm optimization method was proposed in the work of Sun et al for multiple‐satellite GCO reconfiguration using 2‐impulse control.…”

Section: Introductionmentioning

confidence: 99%

Analytical fuel‐optimal impulsive reconfiguration of formation‐flying satellites: A revisit and new results

2018

Optim Control Appl Methods

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Summary This paper investigates fuel‐optimal impulsive reconfiguration of formation‐ flying satellites near circular reference orbit. The author's previous work is extended to the in‐plane reconfiguration, as well as reconfigurations between different formation configurations. Analytical solutions are derived and their optimality is problem dependent. A novel kind of fuel‐optimal solutions, whose associated primer vector magnitude is identically equal to 1, has been obtained for reconfigurations with nonoptimal analytical solutions. Numerical examples are given to illustrate and validate the obtained results.

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“…This is by no means a new problem and it has been investi gated by numerous authors in the past. However, the previous methods suffer from one or more of the following drawbacks: l. They involve the computationally expensive and sensitive solution of sets of nonlinear equations [1][2][3][4][5][6][7][8][9][10][11][12][13]. 2.…”

mentioning

confidence: 99%

“…2. They assume a circular or near-circular reference orbit [1][2][3][4]6,9,10,[13][14][15][16] 3. They assume a set of impulse times and do not solve for the optimal ones [15][16][17][18][19][20][21].…”

mentioning

confidence: 99%

Formation establishment and reconfiguration using differential elements in J2-perturbed orbits

Roscoe

Westphal

Griesbach

et al. 2014

2014 IEEE Aerospace Conference

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A practical algorithm is developed for on-board plan ning ofn-impulse fuel-optimal maneuvers for establishment and reconfiguration of spacecraft formations. The method is valid in circular and elliptic orbits and includes first-order secular h effects. The dynamics are expressed in terms of differential mean orbital elements, and relations are provided to allow the formation designer to transform these into intuitive geometric quantities for visualization and analysis. The maneuver target ing problem is formulated as an optimal control problem in both continuous and discrete time. The continuous-time formulation cannot be solved directly in an efficient manner, and the discrete time formulation, which has an analytical solution, does not directly yield the optimal thrust times. Therefore, a practi cal algorithm is designed by iteratively solving the discrete time formulation while using the continuous-time necessary conditions to refine the thrust times until they converge to the optimal values.Simulation results are shown for a variety of reconfiguration maneuvers and reference orbits, including simulations with and without navigation errors for the NASA CubeSat Proximity Operations Demonstration mission.

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Interactive optimization approach for optimal impulsive rendezvous using primer vector and evolutionary algorithms

Cited by 40 publications

References 8 publications

Analytical fuel‐optimal impulsive reconfiguration of formation‐flying satellites

Analytical fuel‐optimal impulsive reconfiguration of formation‐flying satellites

Analytical fuel‐optimal impulsive reconfiguration of formation‐flying satellites: A revisit and new results

Formation establishment and reconfiguration using differential elements in J2-perturbed orbits

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