Advanced entry guidance systems could potentially enable future vehicles to generate feasible/optimal flight trajectories onboard for the latest mission requirements and track the new trajectories under uncertainties. To this end, an autonomous entry guidance algorithm is proposed for hypersonic vehicles using convex optimization methods. Based on previous sequential convex programming methods for entry trajectory optimization, a different successive procedure is developed for the online generation and tracking of reference trajectories from the current location to a desired target. In each guidance cycle, a new reference trajectory is generated by solving a second-order cone programming problem, and an optimal feedback guidance law is designed using a quadratically constrained quadratic programming method to track this reference trajectory. Because these two problems are convex, they are expected to be solved by state-of-the-art interior-point methods very efficiently. To demonstrate the effectiveness and performance of the proposed entry guidance algorithm, an offline convex entry guidance method is also designed for comparison based on a predetermined reference trajectory. Numerical simulations are presented for both offline and online approaches, which show that the proposed autonomous entry guidance algorithm is robust and efficient for potential future onboard guidance applications.
Autonomous Entry Guidance for Hypersonic Vehicles by Convex Optimization
Journal of Spacecraft and Rockets ; 55 , 4 ; 993-1006
01.07.2018
Aufsatz (Konferenz) , Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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