Optimal Multiple Finite Burn Strategies for Trans-lunar and Trans-planetary Manoeuvres
Optimal Multiple Finite Burn Strategies for Trans-lunar and Trans-planetary Manoeuvres
- Neue Suche nach: Aggarwal, Garima
- Neue Suche nach: Ramanan, R. V.
- Neue Suche nach: Sastry, PSR Srinivasa
- Neue Suche nach: CV, Jiji
- Neue Suche nach: Raghavamurthy, D.V.A.
- Neue Suche nach: Rao, Samba Siva
- Neue Suche nach: Aggarwal, Garima
- Neue Suche nach: Ramanan, R. V.
In Chandrayaan I Mission and Mars Orbiter Mission, ISRO put the spacecraft from Earth Parking Orbit to the trans-lunar/trans-planetary injection point through a series of orbit-raising manoeuvres around Earth. The start time and duration of each burn, along with the size of the intermediate orbits and the burn sequence, must be designed, such that at the end of manoeuvres, the trans-lunar/trans-planetary injection epoch is achieved. This study aims to design the optimal multiple finite burn orbit-raising manoeuvres for trans-lunar and trans-planetary manoeuvres, using differential evolution as the optimization technique. The reduction in the computational time is achieved through multi-threading.
Dokumentinformationen
Optimal Multiple Finite Burn Strategies for Trans-lunar and Trans-planetary Manoeuvres
Lect.Notes Mechanical Engineering
2020-05-05
15 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
Orbit-raising manoeuvers , Finite burn loss , Differential evolution , Chandrayaan I Mission , Mars orbiter mission , Multi-threading Engineering , Aerospace Technology and Astronautics , Control, Robotics, Mechatronics , Multiagent Systems , Space Sciences (including Extraterrestrial Physics, Space Exploration and Astronautics)
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