Minotaur V Space Launch Vehicle for Small, Cost-Effective Moon Exploration Missions Scott Schoneman 14 August 2007 21st Annual AIAA/USU Conference on Small Satellites Innovation You Can Count On™ Minotaur Family of Launch Vehicles 2 Minotaur Family Flight History and Firm Manifest 3 Minotaur IV Has an Extensive, Proven Heritage 4 Minotaur V Origins z Minotaur V is Five Stage Evolution of Minotaur IV ¾ Adds Upper Stage for High Energy Missions: MTO, GTO, TLI, and Beyond ¾ Retains Reuse of Reliable, Proven Solid Rocket Motors z Detailed Trade Study Resulted in Selection of Upper Stage Motors ¾ STAR 48BV for Stage 4 ¾ STAR 37 Options for Stage 5 – 37FM for Spin-Stabilized – 37FMV for 3-Axis Stabilized 5 Minotaur V - STAR 37FMV Stage 5 Configuration (3-axis Stabilized) z Extensive Minotaur-Family Heritage Composite Clamshell Fairing and Commonality z Flight Proven 92” Taurus Design ¾ Flight Proven OSP Avionics and Stage 5 Assembly Flight Software w/ Heritage of 10 z STAR 37FMV Solid Rocket Motor or more Flights ¾ Thrust Vector Controlled z OSP-Standard Avionics z Uses STAR 48 and STAR 37 Upper ¾ Only Subset Required to Fly Stage 5 Stage Motors z Cold Gas Attitude Control System (ACS) ¾ Extensive STAR Motor Flight z Composite Structure History Guidance Control Assembly (GCA)/Stage 4 ¾ Flight Qualified Flexseal and z GCA Design Shared with Minotaur III & IV Actuator System z OSP-Standard Flight Proven Avionics ¾ Split Between S4 and S5 z Performance: z Cold Gas ACS ¾ 721kg to GPS Transfer Orbit z Stage 4 STAR 48BV SRM (55 deg, Direct Ascent from ¾ Thrust Vector Control (TVC) WFF) GFE Peacekeeper Stages ¾ 594 kg to GEO Transfer Orbit z Stage 3 - SR120 (28.5 deg, Direct Ascent from z Stage 2 - SR119 Legend: Shared w/ M IV CCAFS) z Stage 1 -SR118 New for M V ¾ 402 kg to TLI (28.5 deg, Direct Ascent from CCAFS) 6 STAR Motors Provide Low Risk Upper Stages Propulsion z STAR 48 and STAR 37 Motors Have Extensive Flight History in Space Launch Applications ¾ GEO, Lunar, and Interplanetary Trajectory Insertion Stages ¾ STAR 37 on Delta, Atlas, Titan, Thor, N-2 (Japan) Launch Vehicles; GPS, FLTSATCOM, and Other Spacecraft ¾ STAR 48 on Delta (PAM-D), Shuttle (PAM-S), z STAR 48BV and STAR 37FMV Both Used the Same Flexseal Nozzle ¾ Flexseal Nozzle Qualified on STAR 48BV in Mid-90’s ¾ STAR 37FMV Flight Test Planned in Next 12 Months z TVC System Qualified by Static Fire on Orion 38HP (May 06) ¾ Component Heritage to GMD and THAAD Systems ¾ Same TVC Proposed for Use on STAR 48BV and STAR 37FMV 7 Minotaur V Stage 5 Layout Spacecraft Adapter Cylinder (Optional) • Adapted from composite avionics structure from Minotaur I/Pegasus •Avionics and ACS for 3-Axis ACS A nk CS Stablized Configuration CS Tank 92 in. Fairing Tank Ta ACS Ta nk AC A S nal) Ta Optio nk ank ( op S T t. AC Base Ring B a tt Batt MA C MACH H Thruster Thruster STAR 37FM or FMV B Solid Rocket Motor a t t AD A & S SIGI SIGI 38.8 in. Dia. Spacecraft Interface 48 in. to 37 in. Adapter Cone • Minotaur I/Pegasus standard • Bolted I/F to separation system Existing 48 in. Sep Standard STAR System (SAAB) 37 bolted 8 interface Minotaur V Payload Dynamic Envelope (STAR 37 FMV Configuration) z Flight Proven Taurus 92” Fairing ¾ Spacecraft Encapsulated with Stage 5 Assembly z Volume for Small Secondary Payloads or Experiment ¾ On Stage 5 Structure ¾ Negotiable z Standard 38.8” Spacecraft Interface Bolt Pattern Spacecraft Dynamic Motion Must Stay Within The Fairing ¾ Common With Pegasus, Taurus, and Minotaur I Dynamic Envelope ¾ Multiple Options for Separation Systems and/or Smaller Diameter PAFS 9 Minotaur V Benchmark Orbits & Performance Arg. 3-Axis Spin Peri- Inclin of C3 Launch Apogee Stabilized Stabilized Orbit Type gee -ation Peri- (km2/ Site (km) (km) (deg) gee s2) Kg Lbm Kg lbm (deg) LEO KSC 200 200 28.55 NA -60.59 2165 4774 2213 4879 MTO WFF 185 20367 37.83 NA -23.93 721 1590 766 1690 GTO KSC 185 37800 28.55 180 -15.71 594 1311 640 1411 Molniya VAFB 500 39965 63.40 90 -14.98 450 993 496 1094 WFF 200 408,556 37.83 180 -1.89 386 852 432 952 TLI KSC 200 408,556 28.55 180 -1.89 402 886 447 986 10 Minotaur V C3 Performance from Wallops Island 3-Axis Stabilized Stage 5 Configuration Mission Design Trade Space GTO: C3=-15.71 Between Curves TLI: C3 =-1.89 11 Minotaur V TLI Trajectory (Typical) Elliptical Parking Orbit 12 Summary z Minotaur Vehicles Build on Highly Successful Legacies ¾ Minotaur I & II: 13 Successful Launches ¾ Three Successful Taurus Launches Using PK Stage 1 ¾ Long Term Demonstrated Reliability of Minuteman and PK Boosters ¾ Extensive Flight Heritage of Avionics, FTS, RF, and ACS Components z First Several Minotaur IV Missions Are Under Contract and Progressing Toward Launch ¾ Avionics and Flight Software are Common Across All Minotaur Vehicles ¾ Identified Risks Methodically Retired During Early Development Effort ¾ Minotaur IV CDR Completed Fall 06 – On Track for 4Q08 Initial Launch z Minotaur V is a Natural Extension of Minotaur IV Using Mature Technologies ¾ STAR 48 and STAR 37 Motors Have Extensive Flight History ¾ Flexseal Nozzle and TVC Actuators Qualified via Static Fire and Planned Flight Test Well Before First Minotaur V Launch Minotaur Family Launch Vehicles Provide Existing, Reliable, and Cost Effective Launch Capability to Facilitate Low Cost High Energy Misisons 13.