Marcus J. Holzinger

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— Recent on-orbit mission performance illustrates a pressing need to develop passively safe formation flight trajecto-ries and controllers for multiple satellite proximity operations. A Receding Horizon Control (RHC) approach is formulated that directly relates navigation uncertainty and process noise to non-convex quadratic constraints, which enforce(More)
, The paper describes two approaches to improving on-board robustness of spacecraft relative motion guidance and control. The first approach is based on Model Predictive Control (MPC), and this paper demonstrates its capability for robust trajectory execution by changing the environment with a sudden obstacle appearing along its path. The second, novel(More)
Recent advances in robotics and computer vision have enabled the implementation of sophisticated vision-based relative navigation algorithms for robotic spacecraft using a single calibrated monocular camera. These techniques, initially developed for ground robots, show great promise for robotic spacecraft applications. However, several challenges still(More)
—Sufficient stability conditions are derived for simultaneous uncoordinated impulsive maneuvers in distributed mean orbit element spacecraft formations. Lyapunov stability formalisms are used in conjunction with distributed mean orbit element spacecraft formation definitions. Special cases of the sufficient stability conditions are examined. Simulated(More)
—Computational savings in reachability set sub-space computation are realized by carefully applying transversality conditions to trajectory samplings of the full reachability set. Differential constraints on the initial state and initial constraint Lagrange multiplier are developed that enforce the necessary conditions of optimality as total trajectory(More)
The track assignment problem in applications with large gaps in tracking measurements and uncertain boundary conditions is addressed as a Two Point Boundary Value Problem (TPBVP) using Hamiltonian formalisms. An L2-norm analog Linear Quadratic Regulator (LQR) performance function metric is used to measure the trajectory cost, which may be interpreted as a(More)
This paper investigates controlling spacecraft formations, as opposed to individual spacecraft in formation, with the intent to determine whether Leader-Follower formations are error-or fuel-optimal. An formation optimal control problem is developed wherein formation slots and spacecraft barycenter weights are the formation control variables. Restricted(More)
Magnetometer-based detection and characterization of space objects is motivated and challenges are discussed. Observable constants of motion with and without charge screening are derived in detail. Batch filtering methods are proposed to estimate the observable space object states. A novel application of orbit and detection constraints is used to generate(More)