elib
DLR-Header
DLR-Logo -> http://www.dlr.de
DLR Portal Home | Impressum | Datenschutz | Kontakt | English
Schriftgröße: [-] Text [+]

A Constrained Inverse Modeling Approach for Trajectory Optimization

Müller, Reiko und Looye, Gertjan (2013) A Constrained Inverse Modeling Approach for Trajectory Optimization. In: AIAA Guidance, Navigation, and Control Conference. American Institute of Aeronautics and Astronautics. AIAA Guidance, Navigation, and Control Conference, 2013-08-19 - 2013-08-22, Boston (MA), Vereinigte Staaten von Amerika. doi: 10.2514/6.2013-4762. ISBN 978 1 62410 224 0.

[img] PDF
1MB

Offizielle URL: http://dx.doi.org/10.2514/6.2013-4762

Kurzfassung

In aircraft trajectory optimization, modeling almost always relies on the usage of standard (forward) three- or more degrees of freedom equations of motion for the aircraft. The usual practice for simulating the trajectories is either to continuously trim the aircraft along the desired flight path and speed profile, and/or to use reduced point mass models that are defined in the vertical plane only. Alternative approaches became prominent in recent years, whereas in this paper the inverse modeling technique and an important extension to it is considered. First, inverse models have several advantages for trajectory optimization, the most important ones being the faster computation time and easy generation of start solutions, compared to standard forward models. In this work it is combined with speed- and flightpath- control loops to cancel the position error introduced during model integration. Still, an important problem remains: saturation limits and dynamics of the control systems used in the actual forward model are normally not considered when inverting the model equations, therefore losing the information of the limitations of the aircraft. In the presented case, the inversion becomes invalid, when the aircraft thrust is outside of the limits due to the commands of the inverse model inputs. This problem is addressed in the model by a pseudo-control-hedging (PCH) approach for altitude and velocity commands. By this means the inverse model inputs are automatically altered depending on the error between commanded and available thrust and the generated trajectory is rendered flyable.

elib-URL des Eintrags:https://elib.dlr.de/84083/
Dokumentart:Konferenzbeitrag (Vortrag)
Titel:A Constrained Inverse Modeling Approach for Trajectory Optimization
Autoren:
AutorenInstitution oder E-Mail-AdresseAutoren-ORCID-iDORCID Put Code
Müller, ReikoReiko.Mueller (at) DLR.deNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Looye, Gertjangertjan.looye (at) dlr.deNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Datum:19 August 2013
Erschienen in:AIAA Guidance, Navigation, and Control Conference
Referierte Publikation:Ja
Open Access:Ja
Gold Open Access:Nein
In SCOPUS:Nein
In ISI Web of Science:Ja
DOI:10.2514/6.2013-4762
Verlag:American Institute of Aeronautics and Astronautics
ISBN:978 1 62410 224 0
Status:veröffentlicht
Stichwörter:Trajectory optimization, Model inversion
Veranstaltungstitel:AIAA Guidance, Navigation, and Control Conference
Veranstaltungsort:Boston (MA), Vereinigte Staaten von Amerika
Veranstaltungsart:internationale Konferenz
Veranstaltungsbeginn:19 August 2013
Veranstaltungsende:22 August 2013
Veranstalter :American Institute of Aeronautics and Astronautics, Inc.
HGF - Forschungsbereich:Luftfahrt, Raumfahrt und Verkehr
HGF - Programm:Luftfahrt
HGF - Programmthema:Starrflügler (alt)
DLR - Schwerpunkt:Luftfahrt
DLR - Forschungsgebiet:L AR - Starrflüglerforschung
DLR - Teilgebiet (Projekt, Vorhaben):L - Systeme & Kabine (alt)
Standort: Oberpfaffenhofen
Institute & Einrichtungen:Institut für Systemdynamik und Regelungstechnik > Flugzeug-Systemdynamik
Hinterlegt von: Müller, Reiko
Hinterlegt am:30 Sep 2013 11:21
Letzte Änderung:24 Apr 2024 19:50

Nur für Mitarbeiter des Archivs: Kontrollseite des Eintrags

Blättern
Suchen
Hilfe & Kontakt
Informationen
electronic library verwendet EPrints 3.3.12
Gestaltung Webseite und Datenbank: Copyright © Deutsches Zentrum für Luft- und Raumfahrt (DLR). Alle Rechte vorbehalten.