An Overview of the Role of Systems Analysis in NASA’s Hypersonics Project

1. An Overview of the Role of Systems Analysisin 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 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference

2. 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 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference

3. Fundamental Research Areas Subsonics: Rotary Wing Subsonics: Fixed Wing Supersonics Hypersonics Four Level Approach LevelPredictive Capabilities for: 4 Integrated Systems 3 Multi-Disciplinary Interactions and Sub-systems 2 Disciplines and Technologies 1 Natural Phenomena and Fundamental Physics 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 Fundamental Aero Projects Charter 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 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference

4. 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 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference

5. Hypersonic Systems and Missions • 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. 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference

6. 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 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference

7. 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 40-80 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. 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference

8. Reference Vehicle Development Technology Assessment Tool & Environment Development Systems Analysis Roles • Level 4 / Systems Analysis Team is a multi-center analysis organization • Systems Analysis primary roles within the Hypersonics Project is to: • 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. • Track technology and analytical tool development progress by analyzing technology benefits and exercising tools on reference vehicles. • Identify and help to fill gaps in analytical tool capability and design environments. 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference

9. Tool & Environment Development System Studies Technology Assessment 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 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference

10. 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 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference

11. HMMES System Studies Options for Hypersonic Decelerators Today’s Viking Baseline Options for Supersonic Decelerators Options for Subsonic Decelerators Options for Terminal Descent Systems 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference

12. Config & Geometry Aero/CFD Mass Props & Subsys Propulsion Vehicle Closure VehicleDesign Thermal & TPS Trajectory Structures Optimization Life Cycle Analysis Concept of Operations Tool & Environment Development Integrated Design Environments Individual Discipline Tools (primarily level 4 specific) Advanced Vehicle Integration & Synthesis Environment (AdVISE) 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference

13. 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 onaeroheating methodsin support of HMMES • New capability usesengineering methodsto extend a few highfidelity CFD solutionsover entire trajectory 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference

14. 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 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference

15. 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. 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference

16. 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. 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference

17. backup slides 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference

18. Entry Systems Ascent Systems Cruise Systems V∞ > 9 km/s V∞ < 9 km/s Ma/bmax > 15 Ma/bmax < 12 4 < Ma/b < 12 • 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 • 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 < 15+ • 500 < qbar < 2000+ 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 < 2000+ 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 (1000-2000+ psf) during accel to cruise Mach; reduced qbar (500-1000 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 *Ma/b=airbreathing Mach number Hypersonic Systems Taxonomy 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference