System Design of Propulsion Systems for Moon or Planetary Descent Vehicles
- Paper number
IAC-06-C4.1.10
- Author
Mr. Markus Peukert, EADS Astrium, Germany
- Coauthor
Mr. Martin Riehle, EADS Astrium GmbH, Germany
- Year
2006
- Abstract
Currently several studies of descent modules for moon or planetary landing with similar objectives are under investigation in Europe. For most of them EADS Space Transportation GmbH in Lampoldshausen, Germany will contribute to the study by taking the responsibility for concept of the chemical propulsion subsystem. All these lander studies pursue the concept of soft landing. There thrust phases change with free-falling phases subsequently decreasing in duration. Each time the breaking burns are stopped, the relative velocity increases. During free-falling the GNC subsystems determine the parameters for the following breaking burn. Based on the system requirements and mission profiles, various propulsion system concepts that have been investigated and evaluated will be presented. The final choice and recommendation will then be made, based on the selected subsystem concept and components analysis. Major component would be, of course, the main engine. The system study and assessment will be made between a wide portfolio of mono- and bipropellant engines, mainly used for satellite apogee burns and a new developed engine with extreme high chamber pressures. For redundancy reasons several engines of lower thrust might be prefered over one single high thrust engine. This decision making process will be outlined, the advantages and dis-advantages of the selected configuration analysed and described in detail. Further on this paper will also present the applied trade-offs and detailed component hydraulics and performance analyses. Herewith the operational conditions as well as performance constraints of the used components are outlined.
- Abstract document
- Manuscript document
IAC-06-C4.1.10.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.