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dc.contributor.advisorHutchins, Robert G.
dc.contributor.advisorDobrokhodov, Vladimir
dc.contributor.advisorKitsios, Ioannis.
dc.contributor.authorMiranda, Ricardo E.
dc.date.accessioned2012-03-14T17:42:22Z
dc.date.available2012-03-14T17:42:22Z
dc.date.issued2009-09
dc.identifier.urihttp://hdl.handle.net/10945/4586
dc.descriptionApproved for public release, distribution unlimiteden_US
dc.description.abstractThis paper describes the development of a 6-degree of freedom (6-DOF), nonlinear, miniature rotary-wing unmanned aerial vehicle (RW UAV) simulation environment using MathWorks Simulink simulation software. In addition to the modeling process, this research also conducts flight-path controller design using Proportional-Derivative (PD) control techniques. This model's development is motivated by the desire to enable a rapid prototyping platform for design and implementation of various flight control techniques with further seamless transition to the hardware in the loop (HIL) and flight-testing. The T-Rex Align 600 remote controlled helicopter with COTS autopilot was chosen as a prototype rotary UAV platform. The development of the nonlinear simulation model is implemented starting with extensive literature review of helicopter aerodynamics and flight dynamics theory and applying the mathematical models of the helicopter components to generate helicopter inertial frame motion simulations from operator commands. The primary helicopter components modeled in this thesis include the helicopter main rotor inflow, thrust, flapping dynamics, as well as the tail rotor inflow and thrust responses. The inertial frame motions are animated using the Flight Gear Version 0.9.8 software. After obtaining simulations with verifiable results, the nonlinear model is linearized about the hovering flight condition and a linear model is extracted. Lastly, the PD controller is designed and flight path software in the loop (SIL) test results are presented and explained. The SIL tests are conducted for autonomous flight along specified rectangular and figure-8 flight paths.en_US
dc.description.urihttp://archive.org/details/developmentofnon109454586
dc.format.extentxx, 113 p. : ill. ;en_US
dc.publisherMonterey, California: Naval Postgraduate Schoolen_US
dc.subject.lcshElectrical engineeringen_US
dc.subject.lcshVehicles, Remotely piloteden_US
dc.titleDevelopment of a nonlinear 6-degree of freedom miniature rotary-wing unmanned aerial vehicle software model and PID flight path controller using Mathworks Simulink simulation environmenten_US
dc.typeThesisen_US
dc.contributor.corporateNaval Postgraduate School (U.S.)
dc.description.serviceUS Marine Corps (USMC) author.en_US
dc.identifier.oclc463643495
etd.thesisdegree.nameM.S.en_US
etd.thesisdegree.levelMastersen_US
etd.thesisdegree.disciplineElectrical Engineeringen_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US
etd.verifiednoen_US


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