This paper presents a segment-by-segment approach for designing transfer trajectories from the low-Earth parking orbit to a target orbit around an asteroid. With three-dimensional high-fidelity model incorporating n-body dynamics and planetary ephemeris, we design an optimal Earth-asteroid transfer trajectory that minimizes initial and final velocity increments. To alleviate numerical sensitivity which is often caused by stringently satisfying the departure and arrival conditions, the design process is divided into several segments. Then, parametric studies based on numerical optimizations are performed by changing orbital elements of departure orbit. In this way, the tendency/correlation of design variables/parameters is analyzed and their optimum values are determined.
|Title of host publication||Space Flight Mechanics Meeting|
|Publisher||American Institute of Aeronautics and Astronautics Inc, AIAA|
|Publication status||Published - 2018|
|Event||Space Flight Mechanics Meeting, 2018 - Kissimmee, United States|
Duration: 2018 Jan 8 → 2018 Jan 12
|Name||Space Flight Mechanics Meeting, 2018|
|Other||Space Flight Mechanics Meeting, 2018|
|Period||18/1/8 → 18/1/12|
Bibliographical noteFunding Information:
This work was mainly supported by the Basic Science Research Program through the National Research Foundation of Korea (NRF) funded by the Ministry of Science, ICT and Future Planning (NRF-2015R1A1A1A05001063) and in part by the Yonsei University Future-leading Research Initiative of 2014 (2016-22-0100)
© 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
All Science Journal Classification (ASJC) codes
- Aerospace Engineering