Optimal turning maneuvers for six-degree-of-freedom high angle-of-attack aircraft models

dc.contributor.advisor Bion L. Pierson
dc.contributor.author Chou, Jen-nai
dc.contributor.department Aerospace Engineering
dc.date 2018-08-23T02:32:42.000
dc.date.accessioned 2020-06-30T07:08:30Z
dc.date.available 2020-06-30T07:08:30Z
dc.date.copyright Sun Jan 01 00:00:00 UTC 1995
dc.date.issued 1995
dc.description.abstract <p>Various Minimum-Time Turning Maneuvers for two high angle-of-attack, six-degree-of-freedom, aircraft models have been investigated. The primary aircraft model is for a nonlinear 6-DOF F-16 fighter aircraft with high angle-of-attack maneuverability. The other model is for a linearized 6-DOF F-18 fighter which also can be flown in the high angle-of-attack range. Standard 6-DOF equations are employed except that the Quaternion attitude representation system is used instead of Euler Angles to avoid the pitch angle singularity of Euler Angles;These Optimal Control problems have been transformed into Nonlinear Programming problems via Parameter Optimization techniques. Different parameterization techniques were tested on the Van der Pol Problem and Soliman's Problem and their variations before applying them on the main turning problems. These techniques include Control Parameterization and State Parameterization (Inverse Dynamics Approach). Also, a novel Control-Integration Method is proposed to find the discontinuous control history of the possible Singular Arc Problems. Different ways to deal with various types of constraints are also discussed. In particular, when dealing with path constraints of the original optimal control problems, an Extreme-Bounds-on-Intervals method was created. However, it has not been actually developed and tested. The resulting sparse Hessian matrix from this method can speed up the calculations if a specially arranged NLP code is used;The Sequential Quadratic Programming method is primarily relied on to search for the optimum. Several different performance indices are utilized, including 3-D minimum-time-to-turn and 3-D minimum-time-to-half-loop. Several new solutions for these maneuvers are obtained. Moreover, since multiple local minima are present, several global optimization schemes have been studied. A Genetic Algorithm, Adaptive Simulated Annealing, and a Hybrid method which combines the merits of both genetic algorithms and sequential quadratic programming have been used to find the global optimum.</p>
dc.format.mimetype application/pdf
dc.identifier archive/lib.dr.iastate.edu/rtd/10891/
dc.identifier.articleid 11890
dc.identifier.contextkey 6423310
dc.identifier.doi https://doi.org/10.31274/rtd-180813-10072
dc.identifier.s3bucket isulib-bepress-aws-west
dc.identifier.submissionpath rtd/10891
dc.identifier.uri https://dr.lib.iastate.edu/handle/20.500.12876/64087
dc.language.iso en
dc.source.bitstream archive/lib.dr.iastate.edu/rtd/10891/r_9531727.pdf|||Fri Jan 14 18:30:02 UTC 2022
dc.subject.disciplines Aerospace Engineering
dc.subject.keywords Aerospace engineering and engineering mechanics
dc.subject.keywords Aerospace engineering
dc.title Optimal turning maneuvers for six-degree-of-freedom high angle-of-attack aircraft models
dc.type article
dc.type.genre dissertation
dspace.entity.type Publication
relation.isOrgUnitOfPublication 047b23ca-7bd7-4194-b084-c4181d33d95d
thesis.degree.level dissertation
thesis.degree.name Doctor of Philosophy
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