High-accuracy Moon to Earth escape trajectory optimization

Hui Yan, Qi Gong, Chandeok Park, I. Michael Ross, Christopher N. D'Souza

Research output: Chapter in Book/Report/Conference proceedingConference contribution

2 Citations (Scopus)

Abstract

The trajectory optimization of a spacecraft is considered in the gravitational effects of the Moon, Earth, and Sun in the paper. Imposing practical constraints of maximum thrust, fuel budget, and flight time generates a constrained, non-autonomous, nonlinear optimal control problem. Severe constraints on the fuel budget combined with high accuracy demands on the endpoint conditions necessitates a high-accuracy solution to the trajectory optimization problem. The problem is first solved using the standard Legendre pseudospectral method. The optimality of the solution is verified by an application of the Covector Mapping Principle. It is shown that the thrust structure consists of three finite burns with nearly linear steering-angle time histories. A singular arc is detected and is interpreted as a singular plane-change maneuver. The Bellman pseudospectral method is then employed to improve the accuracy of the solution.

Original languageEnglish
Title of host publicationAIAA Guidance, Navigation, and Control Conference
DOIs
Publication statusPublished - 2010 Dec 1
EventAIAA Guidance, Navigation, and Control Conference - Toronto, ON, Canada
Duration: 2010 Aug 22010 Aug 5

Publication series

NameAIAA Guidance, Navigation, and Control Conference

Other

OtherAIAA Guidance, Navigation, and Control Conference
CountryCanada
CityToronto, ON
Period10/8/210/8/5

Fingerprint

Moon
Earth (planet)
Trajectories
Gravitational effects
Sun
Spacecraft

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Control and Systems Engineering

Cite this

Yan, H., Gong, Q., Park, C., Ross, I. M., & D'Souza, C. N. (2010). High-accuracy Moon to Earth escape trajectory optimization. In AIAA Guidance, Navigation, and Control Conference [AIAA 2010-7726] (AIAA Guidance, Navigation, and Control Conference). https://doi.org/10.2514/6.2010-7726
Yan, Hui ; Gong, Qi ; Park, Chandeok ; Ross, I. Michael ; D'Souza, Christopher N. / High-accuracy Moon to Earth escape trajectory optimization. AIAA Guidance, Navigation, and Control Conference. 2010. (AIAA Guidance, Navigation, and Control Conference).
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Yan, H, Gong, Q, Park, C, Ross, IM & D'Souza, CN 2010, High-accuracy Moon to Earth escape trajectory optimization. in AIAA Guidance, Navigation, and Control Conference., AIAA 2010-7726, AIAA Guidance, Navigation, and Control Conference, AIAA Guidance, Navigation, and Control Conference, Toronto, ON, Canada, 10/8/2. https://doi.org/10.2514/6.2010-7726

High-accuracy Moon to Earth escape trajectory optimization. / Yan, Hui; Gong, Qi; Park, Chandeok; Ross, I. Michael; D'Souza, Christopher N.

AIAA Guidance, Navigation, and Control Conference. 2010. AIAA 2010-7726 (AIAA Guidance, Navigation, and Control Conference).

Research output: Chapter in Book/Report/Conference proceedingConference contribution

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N2 - The trajectory optimization of a spacecraft is considered in the gravitational effects of the Moon, Earth, and Sun in the paper. Imposing practical constraints of maximum thrust, fuel budget, and flight time generates a constrained, non-autonomous, nonlinear optimal control problem. Severe constraints on the fuel budget combined with high accuracy demands on the endpoint conditions necessitates a high-accuracy solution to the trajectory optimization problem. The problem is first solved using the standard Legendre pseudospectral method. The optimality of the solution is verified by an application of the Covector Mapping Principle. It is shown that the thrust structure consists of three finite burns with nearly linear steering-angle time histories. A singular arc is detected and is interpreted as a singular plane-change maneuver. The Bellman pseudospectral method is then employed to improve the accuracy of the solution.

AB - The trajectory optimization of a spacecraft is considered in the gravitational effects of the Moon, Earth, and Sun in the paper. Imposing practical constraints of maximum thrust, fuel budget, and flight time generates a constrained, non-autonomous, nonlinear optimal control problem. Severe constraints on the fuel budget combined with high accuracy demands on the endpoint conditions necessitates a high-accuracy solution to the trajectory optimization problem. The problem is first solved using the standard Legendre pseudospectral method. The optimality of the solution is verified by an application of the Covector Mapping Principle. It is shown that the thrust structure consists of three finite burns with nearly linear steering-angle time histories. A singular arc is detected and is interpreted as a singular plane-change maneuver. The Bellman pseudospectral method is then employed to improve the accuracy of the solution.

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Yan H, Gong Q, Park C, Ross IM, D'Souza CN. High-accuracy Moon to Earth escape trajectory optimization. In AIAA Guidance, Navigation, and Control Conference. 2010. AIAA 2010-7726. (AIAA Guidance, Navigation, and Control Conference). https://doi.org/10.2514/6.2010-7726