Change search
CiteExportLink to record
Permanent link

Direct link
Cite
Citation style
  • apa
  • harvard1
  • ieee
  • modern-language-association-8th-edition
  • vancouver
  • Other style
More styles
Language
  • de-DE
  • en-GB
  • en-US
  • fi-FI
  • nn-NO
  • nn-NB
  • sv-SE
  • Other locale
More languages
Output format
  • html
  • text
  • asciidoc
  • rtf
Airspace constraints in aircraft emission trajectory optimization
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics. (Flight Dynamics)
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics. (Flight Dynamics)ORCID iD: 0000-0003-2391-641X
(English)Manuscript (preprint) (Other academic)
Abstract [en]

This paper describes a method for handling restricted airspace in trajectory optimization problems while maintaining the full dynamics of the aircraft model. The discussion is limited to the local solution of the optimization problem. The topological problem of determining which side of the restricted regions the aircraft trajectory should take can be seen as more of a preprocessing stage determining, for example, the shortest path. The trajectory optimization is performed with environmental objective functions describing the emissions from the aircraft engine. Results from two cases are presented. The first case is flying in the vicinity of an airport during the approach and avoiding flying directly above urban areas. The second case involves a long distance flight with a large region of restricted airspace in the way. Both cases are performed with a model of the Swedish Air Force trainer SK60. The results show that the solution, and the solution time, depend significantly on the initial starting guess. With a feasible starting guess, the efficiency of the optimization algorithm is not too degraded due to the nonconvex airspace constraints.

 

Keyword [en]
Tractory optimization, nonconvex airspace constraints, emissions
National Category
Vehicle Engineering
Identifiers
URN: urn:nbn:se:kth:diva-10956OAI: oai:DiVA.org:kth-10956DiVA: diva2:233074
Note
QC 20100720Available from: 2009-08-27 Created: 2009-08-27 Last updated: 2010-07-20Bibliographically approved
In thesis
1. On improving efficiency of flight using optimization
Open this publication in new window or tab >>On improving efficiency of flight using optimization
2009 (English)Doctoral thesis, comprehensive summary (Other academic)
Abstract [en]

In this thesis, optimization is used to improve the performance of aircraft. The focus is on operating current generation aircraft more efficiently rather than designing new aircraft. Drag minimization and aircraft trajectory optimization is used to increase efficiency. Optimization methods are implemented and evaluated on different problem formulations.

The first part of the thesis presents a drag minimization strategy using multiple control surfaces distributed across the span of an elastic wing. Aeroelasticity is exploited to reduce drag for a wide range of flight conditions. A method to minimize drag during a long distance flight is developed and tested in a wind tunnel environment. The method is based on continuously changing the control surface deflections to obtain a more beneficial load distribution from a drag point of view for the current flight condition. In a second study, the method is extended to include the angle of attack as a variable together with the control surface deflections in the drag minimization algorithm. Extensive wind tunnel testing demonstrates the possibility to reduce drag significantly with the presented method for a wide range of flight conditions.

The second topic in the thesis is optimizing the aircraft trajectory. The emissions from the aircraft engine are modeled as smooth functions suitable for optimization using published certification data. These emissions are combined in different environmental indices and used as objective functions in the aircraft trajectory optimization problem. The optimization problem is formulated by discretizing the trajectory in time. The resulting large scale nonlinear optimization problem is solved using a sequential quadratic programming method. The trajectory optimization problem is first studied using a model of the Boeing 737 and the results show that the optimal trajectory depends significantly on the definition of the environmental objective function. A method to treat restricted airspace is also presented and evaluated using a model of the Swedish Air Force trainer SK60. The results show that the method for imposing airspace constraints on the flight path works well, especially when the initial point for the optimization is feasible.

 

Place, publisher, year, edition, pages
Stockholm: KTH, 2009. 37 p.
Series
Trita-AVE, ISSN 1651-7660 ; 2009:45
National Category
Vehicle Engineering
Identifiers
urn:nbn:se:kth:diva-10958 (URN)
Public defence
2009-09-22, F3, KTH, Lindstedtsvägen 26, Stockholm, 10:15 (English)
Opponent
Supervisors
Note
QC 20100720Available from: 2009-09-04 Created: 2009-08-27 Last updated: 2010-07-20Bibliographically approved

Open Access in DiVA

No full text

Authority records BETA

Ringertz, Ulf

Search in DiVA

By author/editor
Jacobsen, MarianneRingertz, Ulf
By organisation
Flight Dynamics
Vehicle Engineering

Search outside of DiVA

GoogleGoogle Scholar

urn-nbn

Altmetric score

urn-nbn
Total: 118 hits
CiteExportLink to record
Permanent link

Direct link
Cite
Citation style
  • apa
  • harvard1
  • ieee
  • modern-language-association-8th-edition
  • vancouver
  • Other style
More styles
Language
  • de-DE
  • en-GB
  • en-US
  • fi-FI
  • nn-NO
  • nn-NB
  • sv-SE
  • Other locale
More languages
Output format
  • html
  • text
  • asciidoc
  • rtf