Presentation on theme: "I n t e g r i t y - S e r v i c e - E x c e l l e n c e 1 Reusable Space Systems 21 st Century Technology Challlenges Disclaimer “The views, opinions,"— Presentation transcript:

1 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 1 Reusable Space Systems 21 st Century Technology Challlenges Disclaimer “The views, opinions, and/or findings contained in this presentation are those of the author/presenter and should not be interpreted as representing the official views or policies, either expressed or implied, of the Defense Advanced Research Projects Agency or the Department of Defense.” Jess Sponable Defense Advanced Research Projects Agency 17 June 2009 DISTRIBUTION STATEMENT A Approved for Public Release, Distribution Unlimited



2 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 2 The Question? Is “aircraft-like” access to and through space possible or just a 20 th century dream?  No answer yet, but this brief addresses the technology – Spaceplanes – Reusable Transfer Vehicles Earth is the cradle of humanity, but one cannot remain in the cradle forever …Konstantin Tsiolkovsky, 1857-1935 Cleared for Public Release DISTAR Case 13717



3 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 3 A Common Spaceplane Vision VISION… A 21 st century of diverse, routine, reliable & affordable space access! Cleared for Public Release DISTAR Case 12541



4 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 4 The Ghost of Spaceplanes Past WWII V-DAY The Greatest Generation Built and Flew X-Planes Opening the Skies To the Brink of Space Cleared for Public Release DISTAR Case 12541



5 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 5 NASA Programs … A Long Spaceplane History 80 82 84 86 88 90 92 94 96 98 00 02 03 04 05 WWII era German Sanger Concept X-15 Rocket Plane Program (Plus other rocket planes) USAF Aerospace Plane Program, early 1960’s Dynasoar Program, 1960’s Science Dawn, Science Realm, TAV, MAV, Copper Canyon Have Region National Aero-Space Plane $70M SAC SON 7-79 AFSPC MNS 6-84 $35M SSTO Studies $3,000M AFSPC MNS 1-01 & 2-01 AFSPC CONOPS DOD DC-X Program Air Force Technoloy/Programs AFSPC LFT ICD Cleared for Public Release DISTAR Case 12541



6 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 6 Sänger Amerika Orbital Bomber The final test facilities for full- scale rocket engine tests were being built when Russia was invaded in June 1941 Resources transferred to nearer term needs Wind Tunnel Model Cleared for Public Release WPAFB-08-0651



7 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 7 USAF HAVE REGION Program 1970’s/1980’s BOEING Cleared for Public Release DISTAR Case 12541



8 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 8 HAVE REGION Technology Demos Weights within 3% of budget Weights within 3% of budget Loads validated by FEM Loads validated by FEM All articles tested to destruction All articles tested to destruction All program managers identified Fixes...Vehicles deemed feasible...Durability Still An Issue All program managers identified Fixes...Vehicles deemed feasible...Durability Still An Issue 1989 Results Cleared for Public Release DISTAR Case 12541



9 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 9 National Aero-Space Plane 1980/1990’s Revolutionary Technology Key Program Goals  Single Stage to Orbit (SSTO)  Horizontal Take-Off and Land  Aircraft-Like Operations  Variable geometry Low Speed/RAM/ SCRAM/Rocket combined cycle Many Design Challenges Complex Airframe/ Propulsion Integration Active cooling using H 2 over 40% of acreage Heavy flight controls supporting 2,700 PSF Dynamic Pressures Must overcome ~45,000 fps Ideal Delta-Vee to Orbit (includes drag) Low Propellant Density (LH 2 is 4.4 lbs/ft 3 ) Grows Airframe High Isp, but Low T/W Cleared for Public Release DISTAR Case 12541



10 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 10 Single Stage Rocket Technology Concepts Circa ~ 1991 Base Entry GENERAL DYNAMICS Nose Entry McDONNELL DOUGLAS Horizontal Landing BOEING Horizontal Take-Off ROCKWELL INT’L Vertical Take-Off Vertical Takeoff & Land Cleared for Public Release DISTAR Case 12541



11 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 11 Comparing Key Characteristics  V = I SP * g * ln M I M F Actively Cooled TPS Ascent Heating 200-500 btu/ft 2 /s Conformal Airframe Built Around Engine Flight Controls Ascent Q 1,500-3,000 psf Engine T/W Total Avg ~ 5-15 Engine T/W Total Avg ~ 60-150 Cylindrical or Conical Airframe Flight Controls Ascent Q 400-600 psf Internal Payload Bay External Payload Bay Passively Cooled TPS Decent Heating 40-80 btu/ft 2 /s Complex Airframe System Trades Drag/Gravity Losses Rocket: 5,000 - 6,000 fps Airbreather: 15,000 - 20,000 fps Specific Impulse Rocket: One Cycle, Trajectory Avg Isp 330 – 440 s Airbreather: Multiple Cycles, Avg Isp 500-1,000 s Propellant Bulk Density Drives Airframe Size LH 2 ~ 4.4 lbs/ft 3 JP or RP ~ 53 lbs/ft 3 LOX ~ 72 lbs/ft 3 LOX/JP ~ 65 lbs/ft 3 LOX/LH 2 ~ 23 lbs/ft 3 Cleared for Public Release DISTAR Case 12541



12 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 12 DC-X “Ops Lab” Procured on 2 yr Schedule, $70M Contract Award Aug 91 First Flight 18 Aug 93 DC-X/XA Demonstrated  Streamlined Management  “Aircraft-like” O&M – 26 hr turnaround time – 2-3 hr call up/alert – Small crews: 6 to 12 – Minimal facilities < $600K  “Aircraft-Like” Flight Ops – Flight abort/engine out – Incremental flight test – All weather  Selected Technologies Cleared for Public Release DISTAR Case 12541



13 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 13 In 1990’s U.S. Invested in X-Planes …Then Quit Conical Body Lifting Body VTHL Most New Technology VTHL Most Conventional Approach VTOL Focus on Operability Cylindrical Body Air Launch – Horizontal Land Least New Technology Cleared for Public Release DISTAR Case 12541



14 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 14 90 60 120 Single Stage To Orbit (LOX/LH 2 Propellants) 30 VentureStar TM Original Delta Clipper TM COST Two Stage To Orbit (LOX/JP Propellants) Some Lessons Learned Two Stage or Not to Stage? feet It Depends, But … … Two Stages & High Density Propellants Make Vehicles Smaller Cleared for Public Release DISTAR Case 12541



15 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 15 Some Lessons Learned Streamlined Management Essential YEAR CUMMULATIVE COST % 100 80 60 40 20 0 1/4 th COST TO FIRST FLIGHT 0123456689 BAU OPERATIONAL SYSTEM “SKUNKWORK STYLE” MANAGEMENT FIRST FLIGHT (BASB) FIRST FLIGHT (BAU) “Business as Should Be” Key to X-Vehicle Success Many Successes Many Companies Cleared for Public Release DISTAR Case 12541



16 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 16 Some Lessons Learned Stay Focused: Stop the Start/Stop Cycle Build X-Planes, Not Systems Take Incremental Steps Build on Successes People/Teams are Key Mach 8 Aircraft Operability Integral load bearing Conformal composite tanks Composite intertank & structure Composite aeroshell & TPS Upgraded avionics Follow-On Proposed as Mach 8 X-Plane for ~$100M BUT NOT SELECTED Stop/Start Wastes Years & Millions!!! Cleared for Public Release DISTAR Case 12541



17 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 17 The Ghost of Spaceplanes Present Lot’s of Paper Not Enough Hardware Cleared for Public Release DISTAR Case 12541



18 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 18 DARPA-AF Falcon Program The Flagship …  Demonstrates and validates technologies through flight testing via the joint Air Force-DARPA Falcon effort that will: Demonstrate affordable, responsive spacelift… Small Launch Vehicle (SLV) develops responsive capability for putting small payloads (TacSats) in Low Earth Orbit …while enabling a prompt global reach capability Hypersonic Technology Vehicle (HTV) explores common hypersonic technologies via multiple demo vehicles HTV-2 Design and Fab Matured More Parts, Less Charts Fly 2009 2006 & 2007 Flights Cleared for Public Release DISTAR Case 13717



19 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 19 Program Goals and Objectives Demonstrate key Hypersonic Cruise Vehicle Technologies in-flight through a series of Hypersonic Technology Vehicles (HTVs) Technical Approach Aero-Thermal Dynamics High-Temperature Materials & Structures Navigation Guidance and Control Communications through Plasma Combined Cycle Propulsion Military Utility Prompt Global Reach from CONUS –Reconnaissance –Anti-access capability Reusable Space Access –Aircraft-like operations HTV-1 HCV Ground Demonstrations First Flight 2009 Notional Flight Demonstrator Vision Vehicle Demonstrating Long-Duration Hypersonic Flight HTV-3X HTV-2 DARPA-AF Falcon Program Cleared for Public Release DISTAR Case 12541



20 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 20 Wake B A First Mission Pierce Point Conditions - V = 19,700 fps -  = -5.03 deg Endo flight time = 1,363 sec Endo range = 3,180 nm Impact 1,798s Second Mission Pierce Point Conditions - V = 23,500 fps -  = -3 deg Endo flight time = 1,409 sec Endo range = 3,079 nm Endo cross-range = 1250 nm HTV-2 Focus Long Duration Flight Tests in 2009 Enables Hypersonic Flight Systems Downrange: 9,000 nm Endoatmospheric Flight Crossrange: 3,000 nm Flight Global Reach: < 2 hrs Cleared for Public Release DISTAR Case 12541



21 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 21 Inward Turning Inlet System Inlet Starting (Turbojet through DMRJ Transition) Inlet Performance / Operability Dual Mode Ramjet Combustor (DMRJ) Combustion Performance Combustor Operability (Low Q Flight) Structural Concept Flt Weight, Efficient Structural Concept Common Nozzle Turbojet Effluent Integration Technology 1 Technology 2 Technology 3 Technology 4 Mach 4 Turbine Engine Thrust per unit frontal area (lbf/ft2) High Turbine Entrance Temp High Temperature Bearings High Mach Thermal Mgmt Installation Effects Scaling; Reusability & Life Hot Shutdown / Cocooning / Restart HCV/HTV-3X Focus Propulsion Technology Challenges Cleared for Public Release DISTAR Case 12541



22 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 22  Emerging entrepreneurial space access industry …suborbital then orbital market: $Billions  Aircraft-like space access technology will feed …to emerging orbital industry (and military) …growing interest in P2P as well  Military/civil capabilities may build on space commerce …analog to Admiral Mahan’s maritime power theories  Naval power stems from maritime commerce, circa 1900 Carmack ~$0.1B The Good News US Entrepreneurs Starting to Engage! Bezos ~$7.5B Musk ~$0.5B Bigelow ~$0.6B Futron & ISU “Very Elastic” Market Studies Branson ~$2B Allen ~$20B + MANY OTHERS Alfred T. Mahan Cleared for Public Release DISTAR Case 12541



23 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 23 AFRL Also Maturing Technology Airframe & SHM Reusable Boost System Flyback & Boostback Boosters Weight Optimize d TSTO Modular TSTO High Speed Aircraft Space Maneuver Vehicles Ground Operability Ops Control Center Aircraft-Like Operability TPS ISHM/AG&C Propulsion Flight Experiment(s) Essential for Any Future System! Cleared for Public Release DISTAR Case 12541



24 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 24 But The Future of Spaceplanes is Largely Unexplored Medium Lift Payloads Mach 7 Mach 12 Boeing 747 (Ref) Small, affordable X-Planes are 1 st step Lots of growth room! Cleared for Public Release DISTAR Case 12541



25 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 25 The Ghost of Spaceplanes Future  A dangerous time  A time of opportunity  A TIME OF CRISIS! Cleared for Public Release DISTAR Case 12541



26 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 26 Predicting the Future Disclaimer “What can be more palpably absurd than the prospect held out of locomotives traveling twice as fast as stagecoaches?”  The Quarterly Review, England, March 1825 “Man will not fly for fifty years.”  Wilbur Wright, 1901 “ Even considering the improvements possible…the gas turbine could hardly be considered a feasible application to airplanes…”  U.S. National Academy of Sciences, 1940 “I think there is a world market for maybe five computers. ”  Thomas Watson, Chairman of IBM, 1943 “Man will never reach the Moon regardless of all future scientific advances.”  Dr. Lee DeForest, 1957 “640K ought to be enough for anybody.”  Bill Gates, 1981 Cleared for Public Release DISTAR Case 12541



27 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 27 Physics Establishes the Potential…  Orbital Kinetic Energy = ½ mv 2  For a 1 lb mass to LEO, Energy = 13,800,000 Joules  Converting Joules to KWhrs  Energy = 3.8 KWhrs  Cost of placing 1 lb in orbit at 10¢ per KWhr (1996 US Avg)  Approximate cost = 38¢ per pound Assuming we can work out a few details …Ticket price to orbit $76.00 ! Cleared for Public Release DISTAR Case 12541



28 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 28 Art of the Possible Set by Engineering for Operability Ground Ops Design for Existing Equipment FOCC Flight Stand Easy Maintenance Access Simplified Facilities Rapid Turnaround Key to Operability AUTONOMOUS VEHICLE, NO SOLID BOOSTERS, UPPER STAGES, PAYLOAD FAIRING, etc. DC-X Demonstrated Turn 26 Hrs SPECIAL GSE OPS FLOW MGMT AUTOMATED CHECKOUT ON BOARD SELF TEST ON BOARD HEALTH MONITORING PAYLOAD STANDARD INTERFACES INCREMENTAL FLIGHT TEST 480 Delta Baseline Data Turnaround (hours) Cleared for Public Release DISTAR Case 13717



29 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 29 Art of the Possible Set by Engineering for Low Cost Best Case: Uses Long-Life Rockets and TPS using F-15 O&S Cost Factors Baseline Case: Spaceplane Data using C-5A O&M Cost Factors Typical Flight Rates Today Commercial Spaceplane Flight Rates Analysis uses aircraft CORE O&M costing model, modified for four two stage spaceplanes Note: ~15,000 lb payload Still 100X more than equivalent cost of electricity There is Room for Improvement! Cleared for Public Release DISTAR Case 12541



30 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 30 AFRL Incrementally Maturing S&T Focus is “Aircraft-Like” Operability Far Term Near Term Mid Term Rapid turn 4 hrs 100X lower ops cost Vehicle reliability 0.9998 All Wx availability 98% 1,000 Sortie Airframe 500 Sortie Propulsion & Systems Rapid turn 24 hrs 10X lower ops cost Vehicle reliability 0.999 All Wx availability 95% 500 Sortie Airframe 250 Sortie Propulsion & Systems Rapid turn 48 hrs 3X lower ops cost Vehicle reliability 0.995 All Wx availability 90% 250 Sortie Airframe 100 Sortie Propulsion & Systems Performance Gains Traded for Operability Enhancements BASELINE EELV, Shuttle, Aircraft Ops Cleared for Public Release DISTAR Case 12541



31 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 31 Potential Demonstration Reusable Booster Mach 3.5+ Separation Reusable Booster System + Expendable Upper Stage Boost or Glide Back Deploy Satellite 66x100nm orbit Minimal reentry heating Low ascent heating Cleared for Public Release DISTAR Case 12541



32 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 32 Incremental Steps Key to Affordability Build a Little, Test a Little Step 1 – X-Plane Step 2 Step 3 Falcon Stage 50% Larger 1 st Stage Near Term Options Small to Medium Lift Far Term Options Medium to Heavy Lift F-15 (Size Ref) Demo F9, NK-33 or HC Boost Propulsion Pack Mach 3-7 Flight Test S-1 S-2 Bare Base CONOPS 4 Merlin 1C Engines Falcon 1 components as Upper Stage Test Build Cleared for Public Release DISTAR Case 13717



33 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 33 Enabling Technology Investments Ground Operability Ops Control Center Aircraft-Like Operability Integral Load Bearing Composite Tank & Structure Demos ongoing Merlin 1C, Block II Propulsion Minor mods Many other options Integration Readiness Mature, ready for next step Thermal Protection & Leading Edges Many Options Work Ongoing Upper Stage 1 st Stage of Falcon I Many other options Cleared for Public Release DISTAR Case 12541



34 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 34 Technologies Also Complement & Feed Hypersonic Cruise Demonstrator Single Fuel (JP-7) for All Propulsion CG / Fuel Control out to Mach 6 Stored Energy APU for Power After TJ Shutdown Over-Under Combined Cycle Propulsion Engines Regen Cooled Flight Weight DMRJ, TJ & Airframe Nozzle Integrated Dual Turbo- Ramjet SERN Nozzle Waverider Integrated Inward Turning Turbo- Ramjet Inlet Flight Demo Firsts “Hot/Warm” Metallic Primary Structure Low Transonic Drag – High Hypersonic L/D Hot Metallic Leading Edges Hot Metallic Control Surfaces Size Comparisons Have Blue HTV-3X D-21 (60% F-117) Cleared for Public Release DISTAR Case 12541



35 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 35 Other Applications of Technology Boost Glide Point to Point (P2P) Transport  Key technologies – High PMF structures – High temperatures/TPS – Efficient boost/propellants – Explore L/D enhancement  Evaluate alternative shapes – High energy stage High PMF – Single stage stretch goal 200 Range (nm) 100 3,000 6,000 Altitude (K ft) Single Stage Flight Requires PMF ~85 to 89% 1 hr flight time Many Concepts Planetspace Rocketplane Whittinghill Gov’t Concept HTV-2 Cleared for Public Release DISTAR Case 12541



36 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 36 P2P Has Ready Made Market Commercial International Fast Freight n Freight tons between U.S. & World –Europe: 2,024,909 tons –Far East: 1,572,512 tons –Above two represent 68% of U.S.-World traffic n Above excludes foreign-foreign traffic n Part of Global Freight Market (all transports): ~$1 trillion/yr n Boeing Study Projects Emerging International Express Market –18% Annual Growth –31% of Int’l Cargo Market by 2014 –Market viable at 5,500 lb cargo - $300/lb Top Five U.S. International Freight Markets Top Five U.S. International Freight Gateways Freight (M Tons/yr) Data from 1990’s Is there a corresponding military requirement ! Cleared for Public Release DISTAR Case 12541



37 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 37 Many Commercial Opportunities …A Few Below Rocketplane Blue Origin XCOR Spaceship Two EADS Can We Demo Technology on Commercial Vehicles? Cleared for Public Release DISTAR Case 12541



38 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 38 If the Past Portends the Future… … Spaceplanes are Coming!  There is a 20 th Century historical parallel – Emerging 21 st century spaceplane industry – Akin to 20 th century aviation industry  Gov’t investment in S&T and X-Planes created: – Waves of new jobs, companies, and export markets, – New services such as rapid mail and freight delivery – Incalculable social value to daily lives of all Americans  As air travel became safer and more affordable …And enabled the world’s best military aircraft Cleared for Public Release DISTAR Case 12541



39 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 39 … But Spaceplanes are Not Enough  Robert Heinlein observed … … Low Earth Orbit is halfway to anywhere!  Reusable transfer vehicles – Ultimately required for robust space access – DARPA investing in several key technologies High power, low mass solar electric arrays Electric propulsion Space robotics Cleared for Public Release DISTAR Case 13717



40 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 40 Fabricate a high power and light weight solar electric array that can support a wide range of space applications, and ground test it in a relevant space environment GOALS >20 kWe electrical power >130 W/kg specific power Scaleable to 80 to 1,000 kWe Demo design mature, CDR in Aug 09 Multifunctional Concentrator Assembly (MCA) 171 MCA’s make up solar array wing Wing tension enables precise pointing Concentration of 12.5:1 reduces acreage ~92% Power generation of 29.3 kWe Beginning of life power in LEO Specific power of 136 W/Kg 216 kg for entire power system, except batteries MCA Solar Performance Characteristics Sunlight Thermal Conduction Radiative Emission Mechanical / Electrical Link Mirror Radiator Solar Cells - 12.5:1 Concentration 23.1m Bow Spring End Beam Tether Beam Valance Solar Module Solar Wing 2.25m Fast Access Spacecraft Testbed FAST Overview Cleared for Public Release DISTAR Case 13717



41 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 41 Key FAST Advantages Inherent scalability Design is modular, one array yields ~30 kWe Modular approach scales up Up to six wings can be flown in tandem for 175 kWe Scaling up dimensions by 2X yields ~720 kWe Future technology further scales up power/reduces mass Flexible launch vehicle packaging & interface 6X better packaging efficiency SLV  30 kWe packages in Falcon 1E or Minotaur IV EELV  Scaled-up 175 kWe system fits in 5m fairing Inherently survivable/hardened configuration Laser survivability due to MCA geometry Radiation hard due to shielding of surrounding structure (MCA’s) 30 kWe Array in Falcon 1E 175 kWe or 720 kWe Concept Big when scaled up…but not too big Equivalent Acreage 175 kWe 720 kWe Laser Off Axis > 15 o Reflects Harmlessly Incoming Sunlight at 0 o Cleared for Public Release DISTAR Case 13717



42 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 42 Why FAST? SPECIFIC POWER (W/kg) 20X greater than ISS 3X greater than today’s satellites KEY ADVANTAGES Enhance current space systems 3X less power system mass 6X greater volumetric efficiency Potential for improved survivability Enable new high power capabilities Expendable/Reusable Transfer Vehicle Radar, LIDAR, high BW comm, etc. Planetary Flight / Exploration 33.5 m 11.6 m 42 Equivalent Active Solar Cell Area FAST with IMM – 10.5 m 2 IMM Only – 130 m 2 ISS with Si – 390 m 2 42 Cleared for Public Release DISTAR Case 13717



43 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 43 Q4 FY 2008 Q1 FY 2009 Q2 FY 2009 Q3 FY 2009 Q4 FY 2009 Q1 FY 2010 Q2FY 2010 Q3 FY 2010 Q4 FY 2010 JulAugSepOctNovDecJanFebMarAprMayJunJulAugSepOctNovDecJanFebMarAprMayJunJulAugSep Phase 1 Interim Design Final Design Phase 2 Detailed Design System Applications Studies Prototype Fabrication Hardware Integration Ground Testing of Prototype IDR FDR CDR TRR Testing Complete Go/ No Go Phase 2 Phase 1 ATP Planned Schedule & Testing FAST Wing Deployment Zero-g Simulation Demo Thermo-Vac Testing Key System Tests Component Tests MCA’s Valence H/W Cleared for Public Release DISTAR Case 13717



44 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 44 DARPA FREND Program Goal DARPA FREND Program Goal Develop a robotic arm able to autonomously rendezvous & grapple legacy space assets –Requires no modification of customer spacecraft –Include sensor suite, controls and end effectors –Deliver flight qualifiable prototype Key Accomplishments 10 of 10 successful marman clamp band grapples Also demonstrated eyebolt hole end effectors Environmental testing of prototype complete Potential military and commercial users identified Military Utility Space based “tug” capable of on-orbit servicing –Disposal or retirement– Salvage / Repair –Orbital repositioning– Refueling –Technology refresh– Debris Removal Future Robotic Enhancements 6DOF Testing in NRL’s Proximity Operations Testbed Environmental Testing Complete Reusable Transfer Vehicle Enables “First Responder” Servicing Cleared for Public Release DISTAR Case 13717



45 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 45 FAST + Electric Propulsion  Reusable Transfer Vehicle FAST power & weights BPT-4000 HET performance Conceptual design of RTV bus New capabilities Enables LEO to GEO transfer (or MEO) ~30 days on Falcon 1 or Minotaur IV (small payload) ~60 days on EELV (10,000 lb payload) Enables use of FREND robotic arm for on-orbit servicing Potential commercial financing via loan guarantees with SECDEF signature Potential NASA/Civil Applications Rapid interplanetary flight (Electric + Chemical RTV architecture?) Non-nuclear, faster missions, more power for planetary probes Commercial servicing/refueling extends life Reusable Transfer Vehicle Commercial Reusable In-Space Transportation Act of 2002 Provides Loan Guarantees up to $1.5B (Public Law 107-248) Cleared for Public Release DISTAR Case 13717



46 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 46 RTV-R (Reusable) RTV-D (Disposable) Payloads (multiple options) Tanks with Xenon (up and back) Chemical propellant for RTV-R Electric Propulsion thrusters Docking targets / Attach HW Structure & Thermal Solar Arrays / Power System (PPU, etc.) Potential for modular deployment of arrays growing power over time Reaction/Attitude Control System Station Keeping / Maintenance Maneuvering / Docking Docking Suite (Active H/W, Sensors) Satellite Avionics, Comm, etc. Reusable Transfer Vehicle Functionality Breakdown Conceptual Design – One of Many Options Payload Options Modular Solar Array Deployment? Cleared for Public Release DISTAR Case 13717



47 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 47 1. RTV-R Launched in to LEO (loiters) 4. EP Transfer to mission orbit 2. RTV-D Launched in to LEO 3. RTV-R and RTV-D Rendezvous & Dock 5. Payload Delivered to GEO 6. RTV-R and RTV-D Return to LEO (EP Transfer) Reusable Transfer Vehicle Concept of Operations 7. RTV-D deorbited in LEO (RTV-R loiters for next payload) OR Cleared for Public Release DISTAR Case 13717



48 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 48 Reusable Transfer Vehicle Technology Challenges and Issues  Light weight solar electric arrays (FAST)  Light weight power processing unit (FAST)  Light weight, long life RTV bus  Extended operation in LEO due to eclipse  Radiation resistant solar cells for Van Allen Belts  Improved EP (bismuth, life, etc.) – Higher T/P @ I SP  Chemical/EP mixed mode propulsion  Cannot ignore alternative technologies – Thin film photovoltaic solar arrays – Solar thermal reusable transfer vehicle – Chemical transfer for crewed & time critical missions Cleared for Public Release DISTAR Case 13717



49 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 49 Future Performance Enhancements Next generation space solar cells – Many options – Historical efficiency growing ~1%/yr – Challenges – meeting unique space needs such as radiation & thermal resistance Evolution toward 50% cell helps – a lot! – From 130 W/Kg to ~200 W/Kg – Reduces weight & transfer time ~30% – Enables higher power & faster transfer InGaN Cells Inverted Metamorphic Multi-junction (IMM) Cells Bismuth Hall Effect Thruster One next generation electric thrusterOne next generation electric thruster 30-40% higher thrust/power vs xenon Hall Effect Thruster Bismuth is readily available 100X lower cost than xenon Challenges - high temperature operation & bismuth contamination Advanced EP / Bi HET helps – a lot!Advanced EP / Bi HET helps – a lot! Reduces transfer time 30% or more Or enables use of smaller power system Relative T/P vs Xenon (%) Isp (sec) Threshold Objective Combined  Reduces system mass ~30% AND cuts transfer times in half Step One is a Successful FAST Demonstration Superior Solar Cells Improved Electric Propulsion Excellent Match to Solar Spectra Cleared for Public Release DISTAR Case 13717



50 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 50  Need vision of affordable, reliable, routine space access … grow space industry and economy, benefit everyone … explore to enable industrial growth & settlement … everyone goes or benefits from tech base  Push enabling technology – Not a Shuttle II system investment … technology only, but fly technology & X-Planes often … NACA like cooperation with commercial industry – Consider NASA Advanced Research Projects Agency … per recommendation of 2001 Space Commission  Don’t overlook on-orbit infrastructure technology … RTV increases effective exploration payload 2 to 4X … Energy investments where they intersect space needs Final Observations Cleared for Public Release DISTAR Case 13717



51 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 51 Steps to the Future … 1.Continue maturing space access technology 2.Flight test technology on commercial vehicles 4.Mature orbit transfer/energy technologies for access 3.Periodic integration & flight of larger X-Planes Build the Industry – Not Just a Gov’t Program Cleared for Public Release DISTAR Case 13717



52 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 52 Reality Check…  Between 1750 - 1900 Knowledge Doubled – Every 150 years  Between 1900 - 1950 Knowledge Doubled – Every 50 years  Between 1950 - 1960 Knowledge Doubled – Every 10 years  Between 1960 - 1992 Knowledge Doubled – At least once every 5 years  By 2020 – Knowledge will double every 73 days Note: As reported at the June 1992 Conference Teach America: Teacher Preparation for the New American School Reusable Space is coming – “time is on my side!” Cleared for Public Release DISTAR Case 12541



53 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 53 Final Thought: Just Do It From the October 9th, 1903 edition of the New York Times: “[A] flying machine which will really fly might be evolved by the combined and continuous efforts of mathematicians and mechanicians in from one million to ten million years.” From Orville Wright’s diary October 9th, 1903: “We started assembly today.” Cleared for Public Release DISTAR Case 12541



54 I n t e g r i t y - S e r v i c e - E x c e l l e n c e 54 Wrap-Up... Cleared for Public Release DISTAR Case 13717

