Iterative Pseudostate Method for Transfer Trajectory Design of Interplanetary Orbiter Missions-Reference-Cited by-同舟云学术

Iterative Pseudostate Method for Transfer Trajectory Design of Interplanetary Orbiter Missions

Published:2016-12 Issue:12 Volume:39 Page:2799-2809
ISSN:0731-5090
Container-title:Journal of Guidance, Control, and Dynamics
language:en
Short-container-title:Journal of Guidance, Control, and Dynamics

Author:

Parvathi S. P.¹,Ramanan R. V.¹

Affiliation:

1. Indian Institute of Space Science and Technology, Trivandrum 695 547, Kerala, India

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Applied Mathematics,Electrical and Electronic Engineering,Space and Planetary Science,Aerospace Engineering,Control and Systems Engineering

Link

http://arc.aiaa.org/doi/pdf/10.2514/1.G002072

Reference16 articles.

1. HohmannW. “The Attainability of Heavenly Bodies,” NASA Technical Translation F-44, Washington, D.C. Nov. 1960.

2. A survey of impulsive trajectories.

3. Interplanetary Mission Design Using Differential Evolution

4. ClarkeV. C.Jr.BollmanW. E.FeitisP. H.RothR. Y. “Design Parameters for Ballistic Interplanetary Trajectories, Part II: One-Way Transfers to Mercury and Jupiter,” Jet Propulsion Lab., California Inst. of Technology, NASA TR 32-77, Pasadena, CA, Jan. 1966.

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