National Aeronautics and Space Administration 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference 1 November 6-9, 2006 An Overview of the Role of Systems Analysis in NASA’s Hypersonics Project Jeffrey S. Robinson and John G. Martin NASA Langley Research Center, Hampton, VA Jeffrey V. Bowles and Unmeel B. Mehta NASA Ames Research Center, Moffett Field, CA and Christopher A. Snyder NASA Glenn Research Center, Cleveland, OH

National Aeronautics and Space Administration 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference 2 November 6-9, 2006 Background & Introduction NASA’s Aeronautics Research Mission Directorate recently restructured its technology programs. The newly formed Fundamental Aeronautics Program (FAP) was chartered and focused towards increased understanding of the fundamental physics that govern flight in all speed regimes. This presentation will provide a brief overview of the Hypersonics Project, one of four new projects under FAP The project organization and the role that systems analysis plays within the project is given, as well as the plans and current status of the systems analysis discipline

National Aeronautics and Space Administration 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference 3 November 6-9, 2006 Fundamental Aero Projects Charter Hypersonics Subsonics: Rotary Wing Supersonics Subsonics: Fixed Wing Fundamental Research Areas Objective: Expand science & engineering base knowledge of aeronautics challenges Results: Validated physics-based multidisciplinary analyses and optimization tool suite with the predictive capability to design for any mission and fly as designed LevelPredictive Capabilities for: 4Integrated Systems 3Multi-Disciplinary Interactions and Sub-systems 2Disciplines and Technologies 1Natural Phenomena and Fundamental Physics Four Level Approach Expected Outcomes Developed Capabilities Prediction of technology influence on mission performance, cost, risk Computational and experimental validation of simulations and models Acquired Knowledge Technical peer-reviewed documentation and papers of research progress Technical presentations at professional conferences

National Aeronautics and Space Administration 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference 4 November 6-9, 2006 Technical Project Structure Four levels from foundational physics up to system design Guided by “push – pull” technology development philosophy; technologies & capabilities flow up, requirements flow down Example: L1: New boundary layer transition model developed L2: Incorporated into CFD code w/ increased heat transfer prediction capability L3: CFD analysis coupled with TPS sizing to determine material distribution and thicknesses L4: Reduced uncertainty in prediction translates to lower required margins, yielding either a lighter or more capable overall system

National Aeronautics and Space Administration 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference 5 November 6-9, 2006 The project’s original plan was to tackle, one at a time, each of the columns and develop reference vehicles for each Following a NASA HQ review, the project decided to focus in on one or two missions The project has selected Highly Reliable Reusable Launch Systems (HRRLS) and High Mass Mars Entry Systems (HMMES) as the two focus mission classes. Hypersonic Systems and Missions

National Aeronautics and Space Administration 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference 6 November 6-9, 2006 Why Highly Reliable Reusable Launch Systems? Recent studies (NGLT) have indicated the potential for order of magnitude increases in system reliability for airbreathing horizontal takeoff launch vehicles Builds on previous investments in turbine and scramjet technology DoD is currently investing in operationally responsive and low cost systems; having NASA work high reliability is highly complementary The HRRLS covers many of the other challenges for the cruise systems and Earth entry from orbit

National Aeronautics and Space Administration 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference 7 November 6-9, 2006 Mars surface above -1.0km MOLA in black Why High Mass Mars Entry Systems? Only five successful U.S. landings on Mars: –Vikings I and II (1976) –Mars Pathfinder (1997) –Mars Exploration Rovers, Spirit and Opportunity (2004) All five of these successful systems: –Had landed masses of less than 0.6 MT –Landed at low elevation sites (below –1 km MOLA) –Had large uncertainty in landing location (uncertainty in targeting landing site of 100s km) All of the current Mars missions have relied on large technology investments made in the late 1960s and early 1970’s as part of the Viking Program –Aerodynamic characterization of 70-deg sphere cone forebody heatshield –SLA-561V TPS –Supersonic disk-gap-band parachute –Autonomous terminal descent propulsion –MSL relying on modified Viking engines Studies show requirements for landing large robotic or human missions on Mars include landing MT payloads with a precision of tens of meters, possibly at high altitude. Studies also indicate that these requirements can not be met with Viking era technology.

National Aeronautics and Space Administration 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference 8 November 6-9, 2006 Systems Analysis Roles Level 4 / Systems Analysis Team is a multi-center analysis organization Systems Analysis primary roles within the Hypersonics Project is to: 1.Develop and analyze reference vehicle concepts in support of HRRLS and HMMES in order to determine potential system capabilities and to provide technology goals and requirements to lower levels. 2.Track technology and analytical tool development progress by analyzing technology benefits and exercising tools on reference vehicles. 3.Identify and help to fill gaps in analytical tool capability and design environments. Reference Vehicle Development Tool & Environment Development Technology Assessment

National Aeronautics and Space Administration 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference 9 November 6-9, 2006 Systems Analysis Work Plan Our plan is to try and keep a balanced approach between developing / analyzing reference vehicles, performing technology assessments, and developing and improving our design & analysis tools Tool improvements will be a continuous process running throughout each FY and will ideally consume 1/3 of our time The other 2/3 of our time will be spent serially working system studies (for about 6- 8 months), followed by technology assessment (for 4-6 months) Annual reviews of tool and technology development status will be conducted Tool & Environment Development System Studies Technology Assessment

National Aeronautics and Space Administration 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference 10 November 6-9, 2006 HRRLS System Studies Work has begun on an updated TSTO concept for HRRLS. The system has a TBCC first stage and rocket powered second stage (both expendable and reusable options will be examined). Currently working on keel line design for first stage. Beginning initial sizing of reusable upper stage. TSTO concept provides flight loads to materials & structures discipline for design. Integrated environment being worked concurrently. Hypersonic Vehicle Design Environment

National Aeronautics and Space Administration 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference 11 November 6-9, 2006 Options for Hypersonic Decelerators Options for Supersonic Decelerators Options for Subsonic Decelerators Options for Terminal Descent Systems Today’s Viking Baseline HMMES System Studies

National Aeronautics and Space Administration 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference 12 November 6-9, 2006 Tool & Environment Development Vehicle Design Structures Life Cycle Analysis Optimization Trajectory Vehicle Closure Mass Props & Subsys Config & Geometry Aero/CFD Thermal & TPS Propulsion Advanced Vehicle Integration & Synthesis Environment (AdVISE) Integrated Design EnvironmentsIndividual Discipline Tools (primarily level 4 specific) Concept of Operations

National Aeronautics and Space Administration 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference 13 November 6-9, 2006 Other Tool Development Efforts Underway Finishing POST2 interface / integration into design environment –Completing debug, adding hooks for other codes and for trade study and Monte Carlo run management Starting contracted efforts for upgrades to safety tool for hypersonic systems and for scramjet weights modeling. Work continuing on aeroheating methods in support of HMMES –New capability uses engineering methods to extend a few high fidelity CFD solutions over entire trajectory

National Aeronautics and Space Administration 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference 14 November 6-9, 2006 Special Project Support Level 4 has been supporting Fresh-FX with aerodynamic database development (Missile Datcom, APAS, and USM3D) and trajectory analysis At the same time, L4 is working to improve design and analysis tools –Developed rapid missile geometry generation –Automated execution of Missile Datcom –Automated generation of panels for APAS, structured grids for CFD (.stl format), and IGES surfaces USM3D solution Missile Design Environment

National Aeronautics and Space Administration 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference 15 November 6-9, 2006 Next Steps Near term plan is to finish TSTO system study, including sensitivity and uncertainty analysis, followed by tech assessment. System study should finish by early spring, tech assessment by late spring. While higher fidelity analysis will continue on the TSTO, work will begin in summer ’07 on the HMMES system study in cooperation with ESMD. The project’s next NRA call is scheduled for February 07 and should contain several systems analysis topic areas. Work will continue on the integrated design and analysis environment, finishing the trajectory, sizing & closure, subsystems, and optimization modules. We will hold our first tools & methods workshop in the fall of ’07. The goal is to have all performance related disciplines included within three years while work continues on improved reliability and cost models. Once those models are complete, they will be integrated and the full environment completed.

National Aeronautics and Space Administration 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference 16 November 6-9, 2006 Summary NASA has formally established the Hypersonics Project as part of its new Fundamental Aeronautics Program. Technology development within the Hypersonics Project will be guided by the classic “push-pull” philosophy, with the highest level goal of providing improved predictive design capability at the system level. The systems analysis team supports the project by providing reference concepts and technology assessment guidance. The team will also work to improve their tools & processes, including individual discipline tools as well as integrated design and analysis environments. All tasks undertaken by the team will support the project’s two primary mission classes, HRRLS and HMMES.

National Aeronautics and Space Administration 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference 17 November 6-9, 2006 backup slides

National Aeronautics and Space Administration 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference 18 November 6-9, 2006 Hypersonic Systems Taxonomy V ∞ > 9 km/sV ∞ < 9 km/sM a/b max > 15 M a/b max < 124 < M a/b < 12 Entry SystemsAscent Systems Cruise Systems Radiation becomes significant / dominant Single use heat shield; expendable/reusable other Ablative materials Blunt bodies / edges Sphere-cones, biconics, blunt bodies; very low hypersonic L/D (0<L/D<0.5) Ex: Apollo, CEV, Galileo, Stardust Convection dominant (radiation potential for non-air) Multi-use / reusable for manned; single use for robotic Blunt and sharp bodies / edges Capsules, lifting bodies, winged bodies; moderate to high hypersonic L/D (0.3<L/D<5) Ex: STS, HL-20, MER Hydrogen fueled highspeed Reusable Airbreathing flight envelope: 0 < Mach < < qbar < psf Efficient / lightweight structure crucial Packing efficiency critical Sharp leading edges, actively cooled RCS and aero control surf. Significant fuel cooling Lifting & winged bodies; high L/D (3<L/D<5) Ex: NASP, GTX Hydrogen and/or HC Reusable Airbreathing max Mach: M5-6 (no or metallic TPS?), ramjet/turboram M7-8 (max for HC) M8-12 (H2 only) 500 < qbar < psf Sharp leading edges Stage separation Aero control surfaces (RCS possible) Lifting & winged bodies; high L/D (3/L/D/5) Ex: ATS-Opt 3 Hydrogen and/or HC Reusable aircraft; expendable missiles Higher qbar ( psf) during accel to cruise Mach; reduced qbar ( psf) for extended cruise Reduced throttle operation Sharp leading edges Aero control surfaces Lifting & winged bodies; high L/D (3<L/D<5) Ex: DF-9, X-51 Lowspeed (0<M<3-4) systems include turbines, rockets, pdes, lace, etc. Highspeed (3-4<M<6-15+) systems include ramjets, scramjets, DMSJ Powered transonic and takeoff performance critical; external burning Flow control / manipulation; MHD / plasma dynamics Propulsion systems integrated/combined in multiple ways and on both stages Deployable decelerating devices RCS and/or aero control surface Hazard detection & avoidance; pinpoint autonomous landing Direct entry for human; aerocapture, aerobraking for robotic Air/ non-air atmospheres *M a/b =airbreathing Mach number