Cruise Range Optimization of a Propeller-Driven Light Aircraft Using a Direct Transcription Method with a Regularization Term

[EN] The problem of maximizing the range of a propeller-driven aircraft in a level flight cruise is analyzed within the framework of optimal control. The specific fuel consumption and propeller efficiency of its propulsive system are characterized by functions of the velocity and engine power (full...

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Autores: Delgado Marcos, Adrián, Rubio Sierra, Carlos, Domínguez Fernández, Diego, Escapa García, Luis Alberto
Tipo de recurso: artículo
Estado:Versión publicada
Fecha de publicación:2024
País:España
Institución:Ajuntament de Barcelona
Repositorio:BULERIA. Repositorio Institucional de la Universidad de León
OAI Identifier:oai:buleria.unileon.es:10612/22846
Acceso en línea:https://www.mdpi.com/2226-4310/11/10/794
https://hdl.handle.net/10612/22846
Access Level:acceso abierto
Palabra clave:Ingeniería aeroespacial
Propeller-driven aircraft
Maximun range
Flight optimization
Optimal control
Direct transcription method
Regularization
3301.15 Sistemas de Propulsión
3319.10 Hélices
3301.06 Estructuras de Aeronaves
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spelling Cruise Range Optimization of a Propeller-Driven Light Aircraft Using a Direct Transcription Method with a Regularization TermDelgado Marcos, AdriánRubio Sierra, CarlosDomínguez Fernández, DiegoEscapa García, Luis AlbertoIngeniería aeroespacialPropeller-driven aircraftMaximun rangeFlight optimizationOptimal controlDirect transcription methodRegularization3301.15 Sistemas de Propulsión3319.10 Hélices3301.06 Estructuras de Aeronaves[EN] The problem of maximizing the range of a propeller-driven aircraft in a level flight cruise is analyzed within the framework of optimal control. The specific fuel consumption and propeller efficiency of its propulsive system are characterized by functions of the velocity and engine power (full model), in contrast to previous works, where they were considered to be constant. To conduct the study, a notional Piper Cherokee PA-28 is selected as representative of light aircraft, defining both the airplane and mission features. Two simplified models are also derived: the Von Mises model, with constant specific fuel consumption and propeller efficiency, and the Parget and Ardema model, defined by constant specific fuel consumption and propeller efficiency depending on the velocity. The problem is solved numerically by means of a direct transcription method. Since the optimal problems of the Von Mises and Parget and Ardema models are singular, it is necessary to incorporate a regularization term. Such a numerical algorithm is validated against the analytical solution given by the Breguet formulation. In this context, the velocity and mass (state variables), the power throttle (control), and the best range are determined. The full model provides a maximum range of 1492 km. The differences between the Von Mises and Parget and Ardema models are about 24 km and 1 km, respectively. A non-optimal steady cruise is also analyzed, providing a significant reduction in the flight time, with a decrease of about 2% of the range. The evolution of the state variables and control in the steady cruise, however, separates from the full model. On the other hand, the Parget and Ardema model almost reproduces the full model results, leading to a clear image of the physics involved: the best range comes from maximizing the product of the propeller and aerodynamic efficiencies with respect to the velocity, which determines the optimal arc.SIMDPIIngenieria AeroespacialEscuela de Ingenierias Industrial, Informática y Aeroespacial2024info:eu-repo/semantics/articleinfo:eu-repo/semantics/publishedVersionhttps://www.mdpi.com/2226-4310/11/10/794https://hdl.handle.net/10612/22846reponame:BULERIA. Repositorio Institucional de la Universidad de Leóninstname:Ajuntament de BarcelonaIngléshttp://creativecommons.org/licenses/by-nc-nd/4.0/info:eu-repo/semantics/openAccessoai:buleria.unileon.es:10612/228462026-06-24T12:43:27Z
dc.title.none.fl_str_mv Cruise Range Optimization of a Propeller-Driven Light Aircraft Using a Direct Transcription Method with a Regularization Term
title Cruise Range Optimization of a Propeller-Driven Light Aircraft Using a Direct Transcription Method with a Regularization Term
spellingShingle Cruise Range Optimization of a Propeller-Driven Light Aircraft Using a Direct Transcription Method with a Regularization Term
Delgado Marcos, Adrián
Ingeniería aeroespacial
Propeller-driven aircraft
Maximun range
Flight optimization
Optimal control
Direct transcription method
Regularization
3301.15 Sistemas de Propulsión
3319.10 Hélices
3301.06 Estructuras de Aeronaves
title_short Cruise Range Optimization of a Propeller-Driven Light Aircraft Using a Direct Transcription Method with a Regularization Term
title_full Cruise Range Optimization of a Propeller-Driven Light Aircraft Using a Direct Transcription Method with a Regularization Term
title_fullStr Cruise Range Optimization of a Propeller-Driven Light Aircraft Using a Direct Transcription Method with a Regularization Term
title_full_unstemmed Cruise Range Optimization of a Propeller-Driven Light Aircraft Using a Direct Transcription Method with a Regularization Term
title_sort Cruise Range Optimization of a Propeller-Driven Light Aircraft Using a Direct Transcription Method with a Regularization Term
dc.creator.none.fl_str_mv Delgado Marcos, Adrián
Rubio Sierra, Carlos
Domínguez Fernández, Diego
Escapa García, Luis Alberto
author Delgado Marcos, Adrián
author_facet Delgado Marcos, Adrián
Rubio Sierra, Carlos
Domínguez Fernández, Diego
Escapa García, Luis Alberto
author_role author
author2 Rubio Sierra, Carlos
Domínguez Fernández, Diego
Escapa García, Luis Alberto
author2_role author
author
author
dc.contributor.none.fl_str_mv Ingenieria Aeroespacial
Escuela de Ingenierias Industrial, Informática y Aeroespacial
dc.subject.none.fl_str_mv Ingeniería aeroespacial
Propeller-driven aircraft
Maximun range
Flight optimization
Optimal control
Direct transcription method
Regularization
3301.15 Sistemas de Propulsión
3319.10 Hélices
3301.06 Estructuras de Aeronaves
topic Ingeniería aeroespacial
Propeller-driven aircraft
Maximun range
Flight optimization
Optimal control
Direct transcription method
Regularization
3301.15 Sistemas de Propulsión
3319.10 Hélices
3301.06 Estructuras de Aeronaves
description [EN] The problem of maximizing the range of a propeller-driven aircraft in a level flight cruise is analyzed within the framework of optimal control. The specific fuel consumption and propeller efficiency of its propulsive system are characterized by functions of the velocity and engine power (full model), in contrast to previous works, where they were considered to be constant. To conduct the study, a notional Piper Cherokee PA-28 is selected as representative of light aircraft, defining both the airplane and mission features. Two simplified models are also derived: the Von Mises model, with constant specific fuel consumption and propeller efficiency, and the Parget and Ardema model, defined by constant specific fuel consumption and propeller efficiency depending on the velocity. The problem is solved numerically by means of a direct transcription method. Since the optimal problems of the Von Mises and Parget and Ardema models are singular, it is necessary to incorporate a regularization term. Such a numerical algorithm is validated against the analytical solution given by the Breguet formulation. In this context, the velocity and mass (state variables), the power throttle (control), and the best range are determined. The full model provides a maximum range of 1492 km. The differences between the Von Mises and Parget and Ardema models are about 24 km and 1 km, respectively. A non-optimal steady cruise is also analyzed, providing a significant reduction in the flight time, with a decrease of about 2% of the range. The evolution of the state variables and control in the steady cruise, however, separates from the full model. On the other hand, the Parget and Ardema model almost reproduces the full model results, leading to a clear image of the physics involved: the best range comes from maximizing the product of the propeller and aerodynamic efficiencies with respect to the velocity, which determines the optimal arc.
publishDate 2024
dc.date.none.fl_str_mv 2024
dc.type.none.fl_str_mv info:eu-repo/semantics/article
info:eu-repo/semantics/publishedVersion
format article
status_str publishedVersion
dc.identifier.none.fl_str_mv https://www.mdpi.com/2226-4310/11/10/794
https://hdl.handle.net/10612/22846
url https://www.mdpi.com/2226-4310/11/10/794
https://hdl.handle.net/10612/22846
dc.language.none.fl_str_mv Inglés
language_invalid_str_mv Inglés
dc.rights.none.fl_str_mv http://creativecommons.org/licenses/by-nc-nd/4.0/
info:eu-repo/semantics/openAccess
rights_invalid_str_mv http://creativecommons.org/licenses/by-nc-nd/4.0/
eu_rights_str_mv openAccess
dc.publisher.none.fl_str_mv MDPI
publisher.none.fl_str_mv MDPI
dc.source.none.fl_str_mv reponame:BULERIA. Repositorio Institucional de la Universidad de León
instname:Ajuntament de Barcelona
instname_str Ajuntament de Barcelona
reponame_str BULERIA. Repositorio Institucional de la Universidad de León
collection BULERIA. Repositorio Institucional de la Universidad de León
repository.name.fl_str_mv
repository.mail.fl_str_mv
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