Indirect Optimization of Three-Dimensional Finite-Burning Interplanetary Transfers Including Spiral Dynamics

Ranieri, Christopher L.; Ocampo, Cesar A.

doi:10.2514/1.38170

Cited by 29 publications

(13 citation statements)

References 11 publications

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“…Note that state differential equations (1) (2) and Hamiltonian (9) are all linear with respect to the magnitude of thrust u, whose admissible domain is closed, i.e., u∈[0,1]. Thus the optimal thrust magnitude u is derived as bangbang control in the following.…”

Section: Fuel Optimal Low Thrust Rendezvousmentioning

confidence: 99%

“…And what's worse, without an account of the physics underlying the optimal guidance problem, it's not reasonable to expect too much from the direct method with regard to the global optimality of its results, as GALLOP claims, i.e., gravity-assisted low-thrust local optimization program. Indirect method [6][7][8][9][10] in trajectory optimization, on the other hand, taking into account more intrinsic optimal structures, unveiled by the optimal control theory [11][12][13], especially PMP, is believed likely to provide one with more reliable global optimal results at much fewer computation costs. However, difficulties from the indirect method seem formidable when the fuel optimal low thrust trajectory is treated.…”

Section: Introductionmentioning

confidence: 99%

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Fuel optimal low thrust rendezvous with outer planets via gravity assist

Guo

Jiang

Baoyin

2011

Sci. China Phys. Mech. Astron.

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Section: Fuel Optimal Low Thrust Rendezvousmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Fuel optimal low thrust rendezvous with outer planets via gravity assist

Guo

Jiang

Baoyin

2011

Sci. China Phys. Mech. Astron.

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“…Many methods have been adopted to compute good initial guesses for low‐thrust trajectories or atmospheric flight applications, as shown, for example, in . In , the generic approach consists in solving a simpler problem with analytic results to approximate the optimal initial adjoints in the full problem.…”

Section: Introductionmentioning

confidence: 99%

“…More physical meaning can be given to the initial estimates of the unknowns with the use of an adjoint control transformation (ACT) . The velocity adjoints can be related to the velocity change, in particular, to the direction of the impulse vector.…”

Section: Introductionmentioning

confidence: 99%

Adjoints estimation methods for impulsive Moon-to-Earth trajectories in the restricted three-body problem

Shen

Casalino

2014

Optim. Control Appl. Meth.

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SUMMARYA study of optimal impulsive Moon-to-Earth trajectories is presented in a planar circular restricted threebody framework. Two-dimensional return trajectories from circular lunar orbits are considered, and the optimization criterion is the total velocity change. The optimal conditions are provided by the optimal control theory. The boundary value problem that arises from the application of the theory of optimal control is solved using a procedure based on Newton's method. Motivated by the difficulty of obtaining convergence, the search for the initial adjoints is carried out by means of two different techniques: homotopic approach and adjoint control transformation. Numerical results demonstrate that both initial adjoints estimation methods are effective and efficient to find the optimal solution and allow exploring the fundamental tradeoff between the time of flight and required ΔV.

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“…Proc IMechE Part G: J Aerospace Engineering 228(14) at UNIV OF VIRGINIA on December 13, 2014 pig.sagepub.com Downloaded from…”

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confidence: 99%

Optimal control for far-distance rapid cooperative rendezvous

Feng

Ren

Shi

2014

Proceedings of the Institution of Mechanical Engineers, Part G:

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This study investigated the far-distance cooperative rendezvous problem for two spacecrafts. The orbital dynamics equations were represented based on the orbital elements with an improved vernal equinox and were normalized. Pontryagin's extremum principle was introduced into the dynamics equations and the co-state equations were obtained. A performance evaluation function was created by particle swarm optimization algorithm based on simulated annealing. The convergent co-state initial vector was obtained using an improved particle swarm optimization algorithm. The initial vector was set as the initial value for optimization and a rapid small-population genetic algorithm was applied, before the approximate global optimum was obtained rapidly. The fine adjustment of the search process was performed based on sequential quadratic programming and the results were sufficiently precise. The process of optimization was simulated for problems that involved far-distance coplanar cooperative rendezvous and active-passive rendezvous, which showed that cooperative rendezvous had more advantages than active-passive rendezvous in terms of fuel saving and time.

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Indirect Optimization of Three-Dimensional Finite-Burning Interplanetary Transfers Including Spiral Dynamics

Cited by 29 publications

References 11 publications

Fuel optimal low thrust rendezvous with outer planets via gravity assist

Fuel optimal low thrust rendezvous with outer planets via gravity assist

Adjoints estimation methods for impulsive Moon-to-Earth trajectories in the restricted three-body problem

Optimal control for far-distance rapid cooperative rendezvous

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