MaCH – SR1: Increasing T/W Ratio of Engine 5 APR 2005

MaCH-SR1 Multi-disciplinary University of Colorado High-altitude Student Rocket 2 Overview Project Objectives Project Overview Thrust – Weight Ratio Reduction ◦Chamber Design ◦Interfaces ◦Injector Plate ◦Nozzle ◦Mass Analysis Fuel Combustion Characteristics Testing ◦Component Test ◦Thrust Test

5 APR 2005 MaCH-SR1 Multi-disciplinary University of Colorado High-altitude Student Rocket 3 Project Objectives Increase T/W Ratio of Proven Engine Design  Decrease Overall Mass of Engine  Demonstrate Composite Technologies for Future Mass Reduction  Characterize Fuel Combustion Process for Future Mass Reduction

5 APR 2005 MaCH-SR1 Multi-disciplinary University of Colorado High-altitude Student Rocket 4 Project Overview Feasibility of Hybrid Rocket Technology Sept 2000 – Jul 2001 Demonstration of Hybrid Rocket Technology Jul 2001 – May 2003 Demonstration of High-Power Hybrid Rocket Technology May 2003 – May 2004 Hybrid Rocket Flight Testing High-Power Hybrid Rocket Flight Testing Sub-Orbital Launch Vehicle (110km)2010 Current Year DescriptionDates Phase 0 Phase Phase I Phase II Phase III Phase IV

5 APR 2005 MaCH-SR1 Multi-disciplinary University of Colorado High-altitude Student Rocket 5 T/W Reduction: Chamber Design Oxidizer Interface Pre-Combustor Post Combustor Flanges Nozzle Oxidizer Adapter Injector Fitting Phenolic Nozzle Thread Rings Composite Aluminum Baseline

5 APR 2005 MaCH-SR1 Multi-disciplinary University of Colorado High-altitude Student Rocket 6 T/W Reduction: Interface Design O-ring Glands

5 APR 2005 MaCH-SR1 Multi-disciplinary University of Colorado High-altitude Student Rocket 7 T/W Reduction: Injector Plate Design

5 APR 2005 MaCH-SR1 Multi-disciplinary University of Colorado High-altitude Student Rocket 8 T/W Reduction: Nozzle Design Baseline New Camber Graphite Ceramic

5 APR 2005 MaCH-SR1 Multi-disciplinary University of Colorado High-altitude Student Rocket 9 T/W Reduction: Nozzle Design

5 APR 2005 MaCH-SR1 Multi-disciplinary University of Colorado High-altitude Student Rocket 10 T/W Reduction: Mass Analysis Overall Mass Reduction:  Aluminum Engine – 49.8%  Composite Engine – 61.1% Chamber Mass Reduction:  Aluminum Chamber – 52.9%  Composite Chamber – 77.5%

5 APR 2005 MaCH-SR1 Multi-disciplinary University of Colorado High-altitude Student Rocket 11 Fuel Combustion Characteristics ‘CG’ Engine ‘CGC’ Engine

5 APR 2005 MaCH-SR1 Multi-disciplinary University of Colorado High-altitude Student Rocket 12 Testing: Components Injector Cap – 1500psi Flow Rate – 0.45 lb/s Chamber – 750 psi Phenolic – 6300ºF Nozzle – 6300ºF Cerafiber – 6300ºF

5 APR 2005 MaCH-SR1 Multi-disciplinary University of Colorado High-altitude Student Rocket 13 Testing: Thrust Performance Test Objectives: Baseline Engines 1&2 (April 1, 2005)  Establish Baseline Engine Performance Data  Obtain Fuel Regression Data New Engines (April 5, 2005)  Verify T/W Objectives Met

5 APR 2005 MaCH-SR1 Multi-disciplinary University of Colorado High-altitude Student Rocket 14 Acknowledgements MaCH-SR1 Team Nicole Ortmann, Nick Patzer, Chris Madsen, Laurren Kanner Josh Stamps, Joel Wecker, Kevin Corcoran, Andrew Campbell Former MaCH-SR1 Team Members Heather Chluda, Kevin McWilliams, Ervin Krause, Otto Krause CU Advisors Dr. Donna Gerren, Dr. Brian Argrow, Dr. Jean Koster Dr. Jeffrey Thayer, Dr. Kurt Maute, Matt Rhode

Questions?

5 APR 2005 MaCH-SR1 Multi-disciplinary University of Colorado High-altitude Student Rocket 16 References 1)MaCH-SR Fall Report 2)MaCH-SR Final Report 3)MaCH-SR Final Report 4)Anderson, Campbell, and Kanner “Investigation of a Castable Ceramic Nozzle in a Mid-Powered Rocket Application”, AIAA )Humble, Henry, and Larson, Space Propulsion Analysis and Design. Space McGraw Hill Publishing, )Moss, Dennis, Pressure Vessel Design Manual. Gulf Professional Publishing 7)Ortmann, “Advanced Processing of Hybrid Rocket Solid Propellant” AIAA )Vable, Madhukar, Mechanics of Materials Book. Oxford University Press ©2002 New York