Indirect optimization method for impulsive transfers

Colasurdo, Guido; Pastrone, Dario Giuseppe

doi:10.2514/6.1994-3762

Cited by 76 publications

(32 citation statements)

References 4 publications

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“…Chilan and Conway [9] also demonstrated the effectiveness of the algorithm by solving a minimum-fuel, time-fixed rendezvous between circular orbits originally posed by Prussing and Chui [11]. The algorithm proposed in [9] generated the optimal solution found by Colasurdo and Pastrone [12].…”

Section: Introductionmentioning

confidence: 88%

“…They applied this algorithm to the time-fixed rendezvous problem posed in [11] and found a low-thrust trajectory that was analogous to the best impulsive solution found in [12], but provided a lower cost. Chilan and Conway [10] applied the same bi-level HOC to find a minimum fuel, free final time trajectory from Earth to Mars.…”

Section: Introductionmentioning

confidence: 93%

“…(12) are rotated into vectors in the RSW frame, r c RSW ðt k enter Þ and r c RSW ðt k exit Þ, using Eq. (11).…”

Section: Cooperative Inspection Segmentmentioning

confidence: 99%

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Near-optimal geostationary transfer maneuvers with cooperative en-route inspection using hybrid optimal control

Showalter¹,

Black²

2014

Acta Astronautica

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Section: Introductionmentioning

confidence: 88%

Section: Introductionmentioning

confidence: 93%

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Near-optimal geostationary transfer maneuvers with cooperative en-route inspection using hybrid optimal control

Showalter¹,

Black²

2014

Acta Astronautica

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“…The problem of space trajectory optimization considered here is an impulsive time-fixed rendezvous transfer between two bodies with circular coplanar orbits (Prussing and Chiu 1986;Colasurdo and Pastrone 1994). Variables are made nondimensional by using the radius of the initial orbit and the corresponding circular velocity as reference values.…”

Section: Multiple-impulse Rendezvous Missionmentioning

confidence: 99%

Cooperative evolutionary algorithm for space trajectory optimization

Sentinella

Casalino

2009

Celest Mech Dyn Astr

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A hybrid evolutionary algorithm which synergistically exploits differential evolution, genetic algorithms and particle swarm optimization, has been developed and applied to spacecraft trajectory optimization. The cooperative procedure runs the three basic algorithms in parallel, while letting the best individuals migrate to the other populations at prescribed intervals. Rendezvous problems and round-trip Earth-Mars missions have been considered. The results show that the hybrid algorithm has better performance compared to the basic algorithms that are employed. In particular, for the rendezvous problem, a 100% efficiency can be obtained both by differential evolution and the genetic algorithm only when particular strategies and parameter settings are adopted. On the other hand, the hybrid algorithm always attains the global optimum, even though nonoptimal strategies and parameter settings are adopted. Also the number of function evaluations, which must be performed to attain the optimum, is reduced when the hybrid algorithm is used. In the case of Earth-Mars missions, the hybrid algorithm is successfully employed to determine mission opportunities in a large search space.

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“…The authors use a BVP solver that they developed 13 to match the analytical construction of the problem. The mission opportunities in the syzygistic period starting on June 20, 2000 (when Earth, Mars, and Venus are almost aligned with the sun), are analyzed.…”

mentioning

confidence: 99%

Optimization Procedure for Preliminary Design of Opposition-Class Mars Missions

Casalino

Colasurdo

Pastrone

1998

Journal of Guidance, Control, and Dynamics

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A numerical procedure, based on the theory of optimal control, is developed and used to nd the ight opportunities for a manned mission to Mars. High-thrust (impulsive) missions are considered; burns can occur either inside or outside the planets' spheres of in uence. Venus yby opportunities also are exploited, and time constraints are often present. The necessary conditions for optimality, derived to deal with such complex missions, constitute an extension of Lawden's primer vector theory. In particular, the optimal transfers that occur in a syzygistic period and that belong to the opposition class are analyzed, taking the eccentricity and inclination of the planetary orbits into account; adjustments produced by the addition of time constraints are discussed.

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Indirect optimization method for impulsive transfers

Cited by 76 publications

References 4 publications

Near-optimal geostationary transfer maneuvers with cooperative en-route inspection using hybrid optimal control

Near-optimal geostationary transfer maneuvers with cooperative en-route inspection using hybrid optimal control

Cooperative evolutionary algorithm for space trajectory optimization

Optimization Procedure for Preliminary Design of Opposition-Class Mars Missions

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