Input to the Steering Group of the Planetary Society Decadal Survey. Medium Lift Launch Vehicle Solution 22 February 2010

Transcription

1 Input to the Steering Group of the Planetary Society Decadal Survey Medium Lift Launch Vehicle Solution 22 February 2010 Warren Frick Advanced Programs, Orbital Sciences Corporation

2 Orbital Overview Leading Developer and Manufacturer of Smallto- Medium Class Satellites and Launch Vehicles Focused on Customer Needs, Emerging Market Areas and Innovative Solutions Wide Spectrum of Products and Experience in Government and Commercial Markets Provide High Performance/Reliable Systems, on Short Schedules, at Affordable Prices Some 835 Satellites and Launch Vehicles Built or On Contract for Customers 730 Systems Developed, Built and Delivered From 1982 to Systems Under Contract for Deliveries From 2010 to 2013 Over $4.8 Billion Total Contract Backlog With Premier Customers Revenues of $1.17 Billion in 2008, Aiming for!10% Annual Long-Term Growth Conservative Balance Sheet, Strong Cash Flow and Liquidity Full Development, Production, Test and Operations Capabilities 3,500 Employees, State-of-the-Art Facilities Chandler, Arizona Launch Vehicle Engineering, Manufacturing and Test Dulles, Virginia Satellite Engineering, Manufacturing, Test and Operations Page 2

3 Orbital Sciences Product Lines Launch Vehicles and Missile Systems Satellites and Other Space Systems Space Launch Vehicles Interceptor Launch Vehicles Target Vehicles/Missiles Communications Satellites Scientific Satellites Other Space Systems 656 Launch Vehicles Developed, Built or Under Contract 97% Mission Success Achieved Over Last 10 Years (99 Vehicles) 179 Satellites/Space Systems Developed, Built or Under Contract 97% Mission Success Achieved Over Last 10 Years (70 Space Systems) Advanced Space Programs Advanced Launch Vehicles Human Space Systems Military Satellites 8 Major Advanced Space Systems Conceived, Prototyped or Under Contract to Develop Innovative Solutions Across All Sectors Involve Customer- and Company-Funded R&D and Limited-Quantity Production Programs to Demonstrate New Technologies Page 3

4 Taurus II Medium Class Launch Vehicle Designed to provide reliability, flexibility and cost-effective access to space for medium-class payloads

5 Two Decades 10 Space and Strategic Launch Vehicles BUILDING ON A HERITAGE OF SUCCESS Orbital has Successfully Developed More Launch Vehicles During the Last 20 Years Than Any Other Organization The Taurus II Launch System Leverages Orbital s Heritage of our Highly Successful Pegasus, Taurus, and Minotaur Space Launch Vehicles, As Well As Launch Vehicles Developed for the Nation s Missile Defense Systems Taurus II is Being Developed, Manufactured and Launched Using Proven Management Approaches, Engineering Standards, and Manufacturing and Test Processes Common to Orbital s Other Major Launch Vehicles Page 5

6 Taurus II Justification Orbital had a need for a mediumcapacity launch vehicle to perform space lift for the Cygnus ISS resupply space vehicle. 8 Missions to deliver 20,000 kg cargo to the International Space Station Delta II Launch Vehicle was not affordable and increasingly unavailable Business case justified development of reliable mediumclass replacement vehicle for space access ISS resupply LEO access High energy science access Large performance gap between small and Intermediate class launch vehicles To 600 km/sun Sync orbit 1200 kg maximum performance for Minotaur IV and Taurus XL Vehicles (Small) 7000 kg minimum performance for Atlas V 401 and Delta IV M Vehicles (Intermediate) Delta 7300 to 7900 replacement Page 6

7 Taurus II vs. Delta II Comparisons Height Taurus II 40 m Taurus II E 44 m Delta II Fairing 38.2 m Delta II L Fairing 38.9 m Gross Lift-Off Weight 285,000 kg 300,000 kg 162,000 kg 230,000 kg Performance to 200km Sun Synch. Inclination Performance to 200 km 28.5" Inclination High Energy Performance C3 = 0 km 2 /sec 2 Payload Envelope Width X Length Payload Volume 3,800 kg 5,000 kg 1,100 kg (Castor 30A/ Star 48) 3. 5 m x 7.7 m 50 m 3 5,300 kg 1905 kg 3,470 kg 6,900 kg 1,300 kg (HEUS/ Star 48) 60 m 3 2,800 kg 775 kg (7425) 26 m 3 5,530 kg 1,155 kg (7925) 3. 5 m x 8.7 m 2.5 m x 6.8 m 2.7 m x 7.4 m 38 m 3 Page 7

8 Taurus II Schedule and Manifest Page 8

9 Key Access Dates Taurus II Risk Category 1 No successful flights, ISO 9001 Certification, NASA Audit, Range Safety Compliance, Comprehensive Acceptance Test Results, etc. Payload Class D Risk Tolerance (Low significance payloads) Risk Category 2 1 st H, Successful launch, NASA Audit, Range Safety Compliance, Comprehensive Acceptance Test Results, etc. Payload Class C & D Risk Tolerance (Low to medium significance payloads) Risk Category 3 1 st H, Successful launches, NASA Audit, Range Safety Compliance, Comprehensive Acceptance Test Results, etc. Payload Class A, B, C & D Risk Tolerance (Medium to high significance payloads) Taurus II Enhanced Category 3 Certification 2 nd H, Successful launches of evolved vehicle family, NASA Audit, Range Safety Compliance, Comprehensive Acceptance Test Results, etc. Payload Class A, B, C & D Risk Tolerance Page 9

10 Taurus II Launch Vehicle Overview Payload Fairing 3.9 meter diameter by 9.9 meters high Composite Honeycomb core structure with Graphite-Epoxy Composite Face Non-contaminating Frangible Rail and Ring Separation System Cold-gas actuator/hinge fairing jettison system Baseline Stage 2 Overall stage development and integration by Orbital ATK CASTOR 30 Solid Motor with Active Thrust Vectoring Orbital MACH avionics module Cold-gas 3-axis Attitude Control System VEHICLE PARAMETERS Gross Liftoff Mass: 290,000 kg Vehicle Length: 40 m Vehicle Diameter: 3.9 m Stage 1 Overall stage development and integration by Orbital Main engine design and production by Aerojet and Orbital Two AJ26-62 engines with independent thrust vectoring Liquid Oxygen/RP-1 fueled Core design and verification by Yuznoye (Zenitderived heritage) and Orbital Core production by Yuzhmash Taurus II Core Utilizes Heritage Vendors with Large Manufacturing Capacity Page 10

11 Taurus II Heritage To control risk and maximize reliability, Orbital chose experienced partners and subcontractors for Taurus II development ATK CASTOR 30, STAR-48 Unparalleled in Solid Motor Development Aerojet/SNTK AJ-26 Nearly 100,000 seconds of test time of heritage NK-33 engines 200,000 including derivative NK-15 and 43 engines Yuzhnoye/Yuzhmash Stage 1 Core Zenit (Sea Launch), Dnepr, Cyclone Major subcontractors all have extensive experience Moog AACS Etc. Page 11

12 Taurus II Main Systems and Suppliers Fairing and Primary Composite Structures Applied Aerospace Structure Corp. - California Payload Separation Systems RUAG Space AB - Sweden Frangible Joint Separation Systems Ensign Bickford Corp. - Connecticut Attitude Control System Tanks Ardé New Jersey Attitude Control System Thrusters & TVC System Moog New York Stage 2 Castor 30 Solid Motor Alliant Techsystems - Utah Avionics & Guidance Control Systems Orbital Science Corp. - Arizona Stage 1 Core Structures and Fueling Systems N.P.O. Yuzhnoye / Yuzhmash - Ukraine Main Engine Feed Lines FMH Inc. - California AJ Main Engines Aerojet General Corp. - California Main Engine Thrust Vector Control System Moog Aerospace Corp. New York Main Engine Thrust Frame Process Fab Inc. - California Aft Thermal Blanket Hi Temp Corp - Texas Page 12

13 Taurus II Enhanced Independent Team Was Created in Sep 2009 to Identify a Path to Taurus II Enhanced Performance for Jan 2013 ILC Replaced Castor 30 With New 2 nd Stage Top Requirements: Injection Orbit 200 Km Circular, 51.6 Deg from WFF Increase payload volume by 1m, linearly Ready for ILC Of 1/31/2013 Utilize Existing Stage 1 and Ground Infrastructure Top Goals Requirement 6500 Kg, Goal 6700 Kg Payload Performance Improve Injection Accuracy from Baseline Vehicle Utilize Current Upper Stack Design as Much as Possible Schedule Milestones Kickoff Development Meeting January 2010 to Meet 2013 ILC Standard 2-Stage Drawings are conceptual and not based on specific solution. 3 Stage Option 2 Stage Option Page 13

14 Taurus II High Energy Third Stage STAR-48 Based third stage supplements CASTOR 30 and Enhanced Taurus second stage for high energy space access 3-axis stabilized (non-spinning) stage baselined Orbital developing similar STAR 48BV and STAR 37 stages for Minotaur IV+ and Minotaur V Decades of experience developing solid-motor based stages Recent experience with small (STAR 27) stage for NASA s successful IBEX mission STAR 48 has long heritage of high energy missions Propelled fastest object mankind has ever launched Less than two years to develop stage Page 14

15 Launch Vehicle High Energy Performance Capabilities Launch Vehicle Performance to C3 = 0 Performance (kg) !!"#$%&'()%*! +#$'&%,#! -#.#*("'), /()0*')#1')1213$ Minotaur V Delta II 7425 Taurus II w/ STAR 48 Delta II 7925 Taurus II E w/ STAR 48 Delta IV M Atlas V 401 Minotaur V and Taurus II With STAR 48 Upper Stage have Heritage Medium-Class Vehicle Performance Page 15

16 Taurus II High Energy Performance 1,600 1,500 1,400 1,300 Taurus II Earth-Escape Energy Performance from CCAFS With STAR 48 3rd Stage Castor 30A + STAR 48 Enhanced TII + STAR 48 1,200 1,100 1, Earth Escape Energy (km 2 /s 2 ) Page 16

17 Taurus II Payload Accommodations Taurus II Bi-conic Payload Fairing Volume Exceeds the Medium Class Payload Envelope Simplifying Design of Payloads with Large Deployables Spacecraft Handling Operations Maximize Payload Integration Effectiveness Processing Scheme Minimizes Contamination Risk by Allowing Late Access for Removal of Covers Launch Vehicle Processing Flow Minimizes Pad Time and Significantly Reduces Payload Risk due to Exposure to Elements 2430 (95.7) All Anticipated Level of Services Provided Contamination Control Available for Sensitive Payloads Flexible Mechanical and Electrical Interfaces and Door Locations Accommodates Wide Range of Payload Requirements Volume Greatly Exceeds Existing Medium-Class Payload Volume Page 17

18 Taurus II High Energy Payload Volume 2430 mm (95.7 in) FWD -R mm (17.3 in) Enhanced Taurus II Fairing 1m (39 ) Longer than Baseline Taurus II Estimated Volume Impact of STAR 48 Stage 2 m (79 ) 2430 (95.7) 2430 mm (95.7 in) FWD -R mm (17.3 in) Payload Fairing Payload Fairing 5614 mm (221.0 in) 6614 mm (260.4 in) 3948 mm (155.4 in) 2036 mm (80.2 in) Baseline Taurus II With STAR 48 Payload Volume 3454 mm (136.0 in) Payload Static Envelope 4948 mm (194.8 in) 3036 mm (119.5 in) Enhanced Taurus II With STAR 48 Payload Volume 3454 mm (136.0 in) Payload Static Envelope Payload Separation Plane AFT RUAG 1666 Sep System Payload Adapter Payload Separation Plane AFT RUAG 1666 Sep System Payload Adapter Page 18

19 Taurus II Environments Acoustics Quasi-Static Acceleration Sine Vibe Shock Taurus II Environments Similar to Comparable Vehicles Enhanced Taurus II Will Have Comparable Environments Page 19

20 Taurus II Static Test Article #1 Production at Yuzhmash Page 20

21 Taurus II Flight Stage 1 Manufacturing Page 21

22 Existing Main Engine Inventory NDK Inventory In Samara = 30 NK-33s Aerojet Inventory In Sacramento = 38 NK-33s Page 22

23 Stennis E-1 Test Stand for AJ26 Engine Hot Fires Flame Duct Construction on Schedule to Support Main Engine Testing in Early 2010 Page 23

24 Castor 30 Static Fire Successful Stage 2 Motor Hot Fire Test Successfully Completed December 2009 Page 24

25 Taurus II Fairing Manufacturing Tools Complete First Fairing Unit Currently Under Construction First Fairing Delivery to Chandler Scheduled for Early 2010 Page 25

26 Taurus II Stage 2 Mockups and Qual Hardware In-Work Fairing Mock-Up 153 dia x 32ft long Avionics Cylinder (92 dia) Motor Cone (153 to 92 dia) Fairing Adapter (153 dia) Page 26

27 WFF Launch Pad 0A Construction Progressing Launch Site Construction Has Begun at WFF Page 27

28 Taurus II Contact Information Mark Pieczynski Vice President, Southern California Engineering Center, Launch Systems Group (714) Warren Frick Taurus II and Cygnus Advanced Programs, Advanced Programs Group (703) Orbital Sciences Corporation Atlantic Blvd Dulles VA, Page 28

29 Backup Information

30 Minotaur V Minotaur IV is a Launch Vehicle Developed to Utilize Peacekeeper Assets to Support Government Small/Medium Space Launch Uses 3 Stages from Peacekeeper, and a Taurus XL-derived upper stage and fairing. Minotaur V was Developed to Increase the Minotaur IV s High Energy Capability, Allowing Small Payload Access to GTO/GEO NASA is Launching Lunar Atmospheric and Dust Environment Exporer (LADEE) to the Moon From Wallops Flight Facility on a Minotaur V in 2012 LADEE Lunar Insertion Mass 130 kg (NASA Web Site) Page 30

31 Minotaur V Space Launch Vehicle Minotaur V is Five Stage Evolution of Minotaur IV Adds Upper Stage for High Energy Missions: MTO, GTO, TLI, and Beyond Detailed Trade Study Resulted in Selection of Upper Stage Motors STAR 48BV for Stage 4 Same as M-IV+ (TacSat-4 Mission) STAR 37 Options for Stage 5 37FM for Spin-Stabilized 37FMV for 3-Axis Stabilized Page 31

32 Minotaur V Payload Envelope Page 32

33 Minotaur V High Energy Performance Page 33