LOGIN TO YOUR ACCOUNT

Username
Password
Remember Me
Or use your Academic/Social account:

CREATE AN ACCOUNT

Or use your Academic/Social account:

Congratulations!

You have just completed your registration at OpenAire.

Before you can login to the site, you will need to activate your account. An e-mail will be sent to you with the proper instructions.

Important!

Please note that this site is currently undergoing Beta testing.
Any new content you create is not guaranteed to be present to the final version of the site upon release.

Thank you for your patience,
OpenAire Dev Team.

Close This Message

CREATE AN ACCOUNT

Name:
Username:
Password:
Verify Password:
E-mail:
Verify E-mail:
*All Fields Are Required.
Please Verify You Are Human:
fbtwitterlinkedinvimeoflicker grey 14rssslideshare1
Sullo, Nicola; De Sousa Silva, Priscilla A.; Terra, Maisa O.; Ceriotti, Matteo (2016)
Languages: English
Types: Other
Subjects:

Classified by OpenAIRE into

arxiv: Physics::Space Physics, Astrophysics::Earth and Planetary Astrophysics
This paper presents an optimization procedure to generate fast and low-∆v Earth-Moon transfer trajectories, by exploiting the multi-body dynamics of the Sun-Earth-Moon system. Ideal (first-guess) trajectories are generated at first, using two coupled planar circular restricted three-body problems, one representing the Earth-Moon system, and one representing the Sun-Earth. The trajectories consist of a first ballistic arc in the Sun-Earth system, and a second ballistic arc in the Earth-Moon system. The two are connected at a patching point at one end (with an instantaneous ∆v), and they are bounded at Earth and Moon respectively at the other end. Families of these trajectories are found by means of an evolutionary optimization method. Subsequently, they are used as first-guess for solving an optimal control problem, in which the full three-dimensional 4-body problem is introduced and the patching point is set free. The objective of the optimisation is to reduce the total ∆v, and the time of flight, together with introducing the constraints on the transfer boundary conditions and of the considered propulsion technology. Sets of different optimal trajectories are presented, which represents trade-off options between ∆v and time of flight. These optimal transfers include conventional solar-electric low-thrust and hybrid chemical/solar-electric high/low-thrust, envisaging future spacecraft that can carry both systems. A final comparison is made between the optimal transfers found and only chemical high-thrust optimal solutions retrieved from literature.
  • The results below are discovered through our pilot algorithms. Let us know how we are doing!

    • 1 Crawford, I. A., “Lunar resources: A review,” Progress in Physical Geography, vol. 39, 2015, pp. 137-167.
    • 2 Hubbard, S., “What Do We Do with the Moon?,” New Space, vol. 4, 2016, pp. 1-1.
    • 3 Price, H., Baker, J., and Naderi, F., “A Minimal Architecture for Human Journeys to Mars,” New Space, vol. 3, 2015, pp. 73-81.
    • 4 Sousa-Silva, P. A., O. Terra, M., and Ceriotti, M., “Novel fast low-cost Earth-Moon transfers with patched three-body systems,” Celestial Mechanics and Dynamical Astronomy (under revision).
    • 5 Sousa-Silva, P. A., O. Terra, M., McInnes, C. R., and Ceriotti, M., “A heuristic strategy to compute ensembles of trajectories for 3D low-cost EarthMoon transfers,” 67th International Astronautical Congress, 2016.
    • 6 Curtis, H. D., Orbital Mechanics for Engineering Students (Third Edition), 2014.
    • 7 Koon, W. S., Lo, M. W., Marsden, J. E., and Ross, S. D., Dynamical systems, the three-body problem and space mission design, 2008.
    • 8 Patterson, M. A., and Rao, A. V., “GPOPS-II: A MATLAB Software for Solving Multiple-Phase Optimal Control Problems Using hp-Adaptive Gaussian Quadrature Collocation Methods and Sparse Nonlinear Programming,” ACM Transactions on Mathematical Software, 2013.
    • 9 Gill, P. E., Murray, W., and Saunders, M. A., “SNOPT: An SQP Algorithm for Large-Scale Constrained Optimization,” SIAM Journal on Optimization, vol. 12, 2002, pp. 979-1006.
    • 10 Weinstein, M. J., and Rao, A. V., “A Source Transformation via Operator Overloading Method for the Automatic Differentiation of Mathematical Functions in MATLAB,” ACM Transactions on Mathematical Software, 2014.
    • 11 Gao, Y., “Near-Optimal Very Low-Thrust EarthOrbit Transfers and Guidance Schemes,” Journal of Guidance, Control, and Dynamics, vol. 30, 2007, pp. 529-539.
    • 12 Heiligers, J., Ceriotti, M., Mcinnes, C. R., and Biggs, J. D., “Design of optimal Earth pole-sitter transfers using low-thrust propulsion,” Acta Astronautica, vol. 79, 2012, pp. 253-268.
    • 13 Topputo, F., “On optimal two-impulse Earth-Moon transfers in a four-body model,” Celestial Mechanics and Dynamical Astronomy, vol. 117, 2013, pp. 279- 313.
  • No related research data.
  • No similar publications.

Share - Bookmark

Download from

Cite this article