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
Onboard Convex Optimization for Powered Descent Landing of EAGLE
Luleå University of Technology, Department of Computer Science, Electrical and Space Engineering, Space Technology.
2017 (English)Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
Abstract [en]

Future space exploration missions require new solutions in Guidance, Navigation and Control (GNC) for autonomous landing. The German Aerospace Centre, DLR, is developing the environment for autonomous GNC Landing experiments, EAGLE, acting as a demonstrator for vertical take-off and landing. The goal of this thesis is to develop a prototype real-time applicable guidance function based on convex optimal control theory for powered descent landing, which can be implemented and tested on the on-board computer of EAGLE. Applying loss less convexification, the powered descent landing fuel-optimal control problem is converted into a second order cone problem. A discretization and transcription method is designed in order to solve the resulting non-linear program by means of the embedded conic solver ECOS and the developed algorithm is verified by a comparison of simulation results for an example pinpoint landing on Mars.  In addition, a heuristic kinematic estimation for the fuel-optimal flight time is added, which defines a fixed flight time for the convex trajectory optimization problem. This enables to automatically generate trajectories optimized for the estimated flight time and given initial and final conditions. A processor-in-the-loop test proofs the potential to apply the developed guidance function on the onboard computer of EAGLE, while simulations with different sets of initial and final conditions reveal that the trajectories computed by the guidance function require more fuel than the actual fuel-optimal trajectory due to an inaccurate flight time estimation for several simulation sets. Therefore, the guidance function developed in this thesis provides a first step towards an optimal trajectory generation framework on-board of EAGLE.

Place, publisher, year, edition, pages
2017.
National Category
Other Engineering and Technologies Control Engineering
Identifiers
URN: urn:nbn:se:ltu:diva-66965OAI: oai:DiVA.org:ltu-66965DiVA, id: diva2:1165162
External cooperation
Institute of Space Systems, DLR
Educational program
Space Engineering, master's level (120 credits)
Supervisors
Examiners
Available from: 2017-12-13 Created: 2017-12-12 Last updated: 2017-12-13Bibliographically approved

Open Access in DiVA

No full text in DiVA

By organisation
Space Technology
Other Engineering and TechnologiesControl Engineering

Search outside of DiVA

GoogleGoogle Scholar

urn-nbn

Altmetric score

urn-nbn
Total: 112 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