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Schafer Corporation 26709 Agoura Road Calabasas, CA 91302 818.880.0779 818.880.8978 FAX

Responsive Space Conference April 22, 04. The Schafer Family of Affordable, Responsive, and Multi-Mission Launch Vehicles. March 25, 2004. Schafer Corporation 26709 Agoura Road Calabasas, CA 91302 818.880.0779 818.880.8978 FAX http s ://www.schaferla.com.

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Schafer Corporation 26709 Agoura Road Calabasas, CA 91302 818.880.0779 818.880.8978 FAX

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  1. Responsive Space Conference April 22, 04 The Schafer Family of Affordable, Responsive, and Multi-Mission Launch Vehicles March 25, 2004 Schafer Corporation 26709 Agoura Road Calabasas, CA 91302 818.880.0779 818.880.8978 FAX https://www.schaferla.com The views, opinions, and/or findings contained in this article are those of the author and should not be interpreted as representing the official policies, either expressed or implied, of the Defense Advanced Research Projects Agency or the Department of Defense." Approved for Public Release, Distribution Unlimited

  2. SLV-DS Program Establishes OS Design # units Phase I/II Funding SLV-DS RE (AUC) LCC $5M/Launch DS Traceable 1000-lb to LEO to OS NRE OS Design is Bounded The End Goal is to Minimize SLV RE by DS NRE Cost and Development Risk 1. Identify & Execute Critical Low-Cost Enabling Technologies within Available NRE 2. Use Existing Technology Basis to Minimize SLV RE Cost

  3. Propulsion and Structures are Key Risk Drivers • Propulsion Development Risk Managed Through Conservative Operating Point • Ablative Chamber vs. Regen • Structures Leverages Simple Demonstrated Technologies SLV 1st Stage Engine Operating Point

  4. Configuration Synthesis Pathway Defined • Vehicle Family Architecture • Two Stage Vehicle For Satellite Launch and CAV Demo: SLV-2L • 1,000+ lb to LEO • Three Stage Growth Path for Stressing Missions: SLV-3L • 2,000+ lb to LEO • Modular Approach for SLV-2L and 3L Vehicles

  5. First Stage Engine Compartment Detailed Design Completed

  6. 1st Stage Injector Design is in Process

  7. TPA Characteristics Established • Schafer Established Preliminary Conceptual Design • Barber-Nichols Generated Detailed Conceptual Design

  8. Second Stage Detailed Design Completed

  9. Upper Stage Propulsion Development Underway • LOX/Jet-A Propellants • 5,000-lb TCA Flight Qualified • Al 2219 Option Available • Combustion Efficiency (hC*) = 92 - 94% + • 20,000-lb TCA Being Dev. • Combustion Efficiency (hC*) = 96% + • Ablative ~ Mid 04 • 50% Throttle

  10. Simplified CONOPS Enables Single Depot Assembly Satellite Hazardous Processing (HPF) Components Shipped to RISF Assemble Booster And Test RISF Integrate SAT to Booster Booster to TE Transport to Pad

  11. Responsive Launch Operations Using TE

  12. FALCON Launch Cost Goals Met • 73% of the Cost Database Based on Vendor Quotes and ROMs • 100% of Avionics is Quoted or ROMs Received • 94% of Propulsion is Quoted or ROMs Received • 82% of Structure is Quoted or ROMs Received • RFIs Released and Bids Received for All Cost Critical Components • Conservative Engineering Estimates Used for Un-Quoted Components • FALCON Cost per Launch Requirement Based on AUC 200 is Achieved

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