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Active Flight Path Control for an Induced Spin Flight Termination System

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dc.contributor.authorShukla, Poorva Jahnukumaren
dc.contributor.committeechairWoolsey, Craig A.en
dc.contributor.committeememberAbaid, Nicoleen
dc.contributor.committeememberHajj, Muhammad R.en
dc.contributor.departmentEngineering Science and Mechanicsen
dc.date.accessioned2017-09-13T08:00:39Zen
dc.date.available2017-09-13T08:00:39Zen
dc.date.issued2017-09-12en
dc.description.abstractIn this thesis, we describe a method for controlling the cycle-averaged velocity direction of a fixed-wing aircraft in an unpowered, helical descent. While the aircraft propulsion system is disabled, either intentionally or due to a failure, the aerodynamic control surfaces (aileron, elevator, and rudder) are assumed to be functional. Our approach involves two steps: (i) establishing a stable, steady, helical motion for which the control surfaces are not fully deflected and (ii) modulating the aircraft control surfaces about their nominal positions to ``slant'' the helical flight path in a desired direction relative to the atmosphere, whether to attain a desired impact location, to counter a steady wind, or both. The effectiveness of the control law was evaluated in numerical simulations of a general transport model (GTM).en
dc.description.degreeMaster of Scienceen
dc.format.mediumETDen
dc.identifier.othervt_gsexam:12585en
dc.identifier.urihttp://hdl.handle.net/10919/78881en
dc.publisherVirginia Techen
dc.rightsIn Copyrighten
dc.rights.urihttp://rightsstatements.org/vocab/InC/1.0/en
dc.subjectLinear Control Theoryen
dc.subjectAerodynamic Flight Terminationen
dc.subjectActive Flight Path Controlen
dc.titleActive Flight Path Control for an Induced Spin Flight Termination Systemen
dc.typeThesisen
thesis.degree.disciplineEngineering Mechanicsen
thesis.degree.grantorVirginia Polytechnic Institute and State Universityen
thesis.degree.levelmastersen
thesis.degree.nameMaster of Scienceen

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