Preliminary trajectory design for a solar polar observatory using SEP and multiple gravity assists

Preliminary trajectory design for a solar polar observatory using SEP and multiple gravity assists

Corpaccioli, L.
Noomen, R.
De Smet, S.
Parker, J.S.
Herman, J.F.C.

Aerospace Engineering

Space Engineering

2015-10-22

Satellite solar observatories have always been of central importance to heliophysics; while there have been numerous such missions, the solar poles have been extremely under-observed. This paper proposes to use low-thrust as well as multiple gravity assists to reach the enormous energies required obtain high heliocentric inclinations. Two novel methods are used to provide initial guesses to a low-thrust trajectory optimizer. Results show that the complete trajectory would take between 3-4 years, although scientific observations can start already after 2 years. This assumes starting masses of 1000-2000 kg, and payload masses of 500-1300 kg. The best inclinations reached are 55-65 degrees to the ecliptic, while maintaining a perihelion and aphelion of 0.5 and 1 AU respectively. More research still needs to be performed to attempt to reach a global optimum. Further investigation is suggested to extend the mission for further objectives, such as lowering perihelion, or further cranking inclination.

solar observatory
multiple gravity assists
low-thrust
ecliptic inclination
Solar Electric Propulsion (SEP)
trajectory optimization
GASP

http://resolver.tudelft.nl/uuid:fc4db167-f591-49cf-9474-d05577da5644

DLR

ISSFD 2015: Proceedings of the 25th International Symposium on Space Flight Dynamics, Munich, Germany, 19-23 October 2015

Institutional Repository

conference paper

(c) 2015 DLR