Analysis and design of aerobraking tethers
Abstract
The aerobraking tether is proposed as a means to achieve a capture orbit about a planet from hyperbolic approach velocities without the expenditure of propellant. The concept involves two vehicles connected by a long, thin tether. One of the vehicles passes through the atmosphere of a planet to achieve the desired velocity change, while the other vehicle remains above the sensible atmosphere. In this thesis, the optimal aerobraking maneuver is analytically characterized. A nondimensional parameterization of the theory leads to some useful design concepts. Optimization of the maneuver using nonlinear programming provides an argument that previously found maneuvers are global minima. The graphical nature of the algorithm is useful in gaining insight into the dynamics of the system. A sensitivity analysis is performed to determine how the aerobraking maneuver is affected by parameter uncertainties. A maneuver is designed to accommodate the large stochastic errors associated with an atmospheric flythrough. This research demonstrates the feasibility of the aerobraking tether as a new, cost-effective vehicle with exciting applications in the future of space exploration.
Degree
Ph.D.
Advisors
Longuski, Purdue University.
Subject Area
Aerospace materials|Mechanical engineering
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