Solar sail applications for mission design in sun-planet systems from the perspective of the circular restricted three-body problem

Rohan Sood, Purdue University

Abstract

As a consequence of the successful harnessing of solar radiation pressure demonstrated by JAXA's IKAROS mission, the interest and developments in the field of solar sails has gained a significant momentum. Sail-based spacecraft potentially offer indefinite maneuvering capability by exploiting photons from the Sun as a means of propulsion. Incorporating a solar sail model within the context of the circular restricted three-body problem extends trajectory design options. In the last few decades, the Lagrangian points, L i, as defined in the restricted problem, have increasingly become a focus for scientific spacecraft mission applications. In this investigation, a hybrid model that incorporates a solar sail force into the circular restricted three-body problem (SS-CR3BP) is developed. As a result of the additional force, the displaced locations of artificial collinear Lagrangian points are determined and exploited for trajectory design. In fact, various trajectories are constructed that employ only sail orientation angles to move through this dynamical regime. In particular, periodic orbits are computed in the vicinity of the displaced artificial L1 equilibrium point, located between the Sun and the Earth in this Sun-planet system. A sample offset periodic orbit is demonstrated that hovers over the displaced L1 point. Trajectory modifications are performed in the vicinity of the L1 equilibrium point using solar sail angles. Three-dimensional transfers between halos at three different sizes is also constructed to exhibit the capabilities of solar sails based on specific mission objectives. Thus, in this investigation, solar sail capabilities that widen the design space for mission design in the restricted three-body problem are explored.

Degree

M.S.A.A.

Advisors

Howell, Purdue University.

Subject Area

Aerospace engineering|Astrophysics

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