Various publications:

• Safety of Nitrous oxide N₂O in rocketry. Presentation given in the frame of the 4th AMRAS symposium. PDF english, PDF german, also have a look at Rick Newlands great paper about hybrid safety (mainly nitrous related stuff)
• Ignition!: : An informal history of liquid rocket propellants, by John D. Clark. Probably one of the most important book for people involved in liquid rocket propulsion. Very informative but also very entertaining. Out of print, but it can still be ordered as a reprint from UMI. We scanned and edited it because we wanted it in an electronical form, so we can search in it. Since it's still copyright protected we only grant access to this dokument for our internal members. PDF (2.8 MB), Word (1.6 MB) HTML (1.6 MB)
• Project Enterprise. In the frame of the recently started project ENTERPRISE with our partner Talis-Institut (sorry, you will see nothing if Javascript is disabled) we wrote a german overview of our work. Just go to the Talis webpage and choose the link to the Project Enterprise (sorry, no permalink on the site) and our report in the september edition of the Talis online magazine T.I.M. (A local copy of our article: as a HTML or PDF document)
• Reusable Rocket Propulsion for Space Tourism Vehicles, Doug Jones from XCOR mentions our 2.5 kN LOX/Ethanol engine in the frame of the 40th AIAA Joint Propulsion Conference, PDF-File, 500 kByte, English
• Preliminary design for a sound suppressing system for the SPL rocket engine test facility, Gianni Ermini about rocket noise and how to avoid problems with our neighbourhood PDF-File, 306 kByte, German
• SPL-Flyer, as presented on the Spaceforum 2001 held by the Swiss Astronautics Association (a bit outdated) PDF-File, 580 kByte, German
• SPL, an Introduction (powerpoint 7 MByte, PDF 2.5 MByte), updated version 3.2007

Student projects:

• Development of a water-cooled rocket nozzle (Mark Vujicic and Justin Mercier at HEPIA 2016). The job includes designing the nozzle, its cooling jacket as well as the outer shell which houses all the components. The whole construction will have to fit in to the combustion chamber, which already exists and was developed by SPL. To help with choosing the most optimized cooling settings, different simulations of the nozzle were run using mainly three software's (PTC Creo Parametrics, Rocket Propulsion Analysis and ANSYS Fluent 14.5).. The full report as PDF 8 MByte (including workshop drawings) . Designing and building of a stage separation mechanism (Thesis of Mr. M. Vögelin and Mr. P. Frey at FHNW (former FHBB) 2007). The students worked out several variants for a stage separation mechanism which can be used on rockets with a diameter of 300 mm like X-Bow I or AUSROC 2.5. It can also be used to deploy recovery equipment. Thsi is the final desgn. The full report as PDF 5 MByte, german (without workshop drawings) . Handout as presented at the exhibition. See the news entry from 21. February 2007
• Construction of a Curtis impulse turbine to drive turbo pumps (Thesis of Mr. L. Lehmann and Mr. M. Kneier at FHBB, 2006). The full report will be available soon.
• Designing and building of a stage separation mechanism (Thesis of Mr. C. Schulthess at FHBB, 2006). This is a continuation of the last years work. The full report will be available soon.
• Designing and building of a stage separation mechanism (Thesis of Mr. R. Buser and Mr. A. Maritz at FHBB, 2005). The students worked out several variants for a stage separation mechanism which can be used on rockets with a diameter of 300 mm like X-Bow I or AUSROC 2.5. It can also be used to deploy recovery equipment. The full report as PDF 10 MByte, german (without workshop drawings) . Handout as presented at the exhibition.
• Construction of a test bench for small turbines (Thesis of Mr. A. Hostettler and Mr. F. Jacot at FHBB, 2005). The goal of this student project at FHBB was the design, building and testing of a test bench where modified turbines of automotive turbo chargers can be tested as a power plant for turbo pumps. Our long term intention is a small low cost turbo pump for small rocket engines. Interim report: PDF-File, 1.3 MByte, German, Final report (2 MByte, German, without workshop drawings), Handout as presented at the exhibition.
• Designing, building and testing of a regenerative cooled combustion chamber with 2.5 kN/560 lbs thrust (Thesis of Mr. G. Ermini and Mr. F. Kaiser at FHBB, 2002). The students have analysed the heat flux through the chamber walls and the heat transfer into the coolant (water, kerosene and pure ethanol) . They have also developed a code to optimise the size and shape of the cooling channels. PDF-File, 2.3 MByte, German Addendum: There are some miscalculations in the heat flux calculations!
• Analysis of the behavior of various injection systems in a high-pressure environment (cold spray test into a chamber). Investigation of the size, speed and distribution of droplets injected into a test chamber (Thesis of  Mr. Martin Lüthi and Mr. Christian Muser at FHBB, 2000) PDF-File, 1.4 MByte, German