In this thesis, an overall framework is established for the redirection of near-Earth asteroids using spacecraft formation strategies in order to access and utilize asteroid resources. The framework is parsed into three critical areas of research, namely, redirection methods, trajectory transfer, and formation design and control. Additionally, research into the application of asteroid redirection methods to the related area of space debris removal is discussed.

In the area of redirection methods, in-depth analyses and systematic comparisons are conducted. The performance of each method is evaluated through several multicriteria assessment techniques and Monte Carlo analysis is used to quantify the uncertainty intrinsic to the asteroid population. The redirection methods are evaluated with respect to their suitability for spacecraft formation.

The trajectory transfer research focuses on the study of Arjuna-type asteroids, which are considered excellent targets for redirection missions. The research can be divided into two main studies using low-thrust methods:​ i) an assessment of the Arjuna domain, and ii) an approach to optimal three-dimensional transfer trajectory design. The first study investigates the feasibility of transferring an Arjuna-type asteroid using a minimized form of Gauss’s variational equations, spacecraft sizing metrics, and mission cost analysis formulae. The second study outlines the design of a stochastic optimization approach to three-dimensional asteroid transfer from its initial orbit to an orbit in the Earth-Moon system. The research employs pseudo-equinoctial exponential shaping to design the transfer trajectory and quantifies the uncertainty in asteroid parameters through Monte Carlo analysis.

In the area of formation design and control, the thesis develops an optimal approach to asteroid redirection using landed thruster formations. First, the mission design for a landed formation of spacecraft is analysed and optimized from the perspective of resource utilization. Secondly, a method for determining the landing locations and thruster orientations for time-optimal detumbling of an asteroid using a landed formation of spacecraft is formulated. The method models the asteroid as a high resolution convex polyhedra, determines feasible landing locations and thrust directions, and optimizes a spacecraft formation to minimize detumbling time while ensuring full control.

Through systematically presenting work in these three areas, this research helps set the groundwork for future researchers, corporations, and government agencies to seize the opportunities provided by asteroid resources.