National Aeronautics and Space Administration 14th AIAA/AHI Space Planes and Hypersonic Systems and...

National Aeronautics and Space Administration

14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference 1November 6-9, 2006 www.nasa.gov

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



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



Fundamental Aero Projects Charter

HypersonicsSubsonics: Rotary Wing

SupersonicsSubsonics: 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

Level Predictive Capabilities for:4 Integrated Systems3 Multi-Disciplinary Interactions and Sub-systems2 Disciplines and Technologies1 Natural 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



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 developedL2: 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



• 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



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

Reliability

(1 in odds of Loss of Vehicle)

Overall Loss Of Vehicle

(Longer Bar = Higher Reliability)

0

20000

40000

60000

80000

100000

120000

140000

1 2 3 4

TSTO AllRocketVTHL

TSTOTBCC

TSTORBCC

SSTO

TBCC

AIAA 2003-5265

Low

High

Aero-Propulsion Integration• Mode Transition • Aero-Propulsive Performance

Propulsion• Advanced Turbojets• Ramjet• Dual-Mode Scramjet• RBCC

Integrated Systems• Staging• Thermal Management• Health Management• Power and Actuators• Intelligent/autonomous

controls

Airframe Structures and Materials• Long life, high temperature

structures & materials• TPS• Leading Edges• Control Surfaces • High-Temperature Seals

• Reusable Cryo Tanks

Aero-Propulsion Integration• Mode Transition • Aero-Propulsive Performance

Propulsion• Advanced Turbojets• Ramjet• Dual-Mode Scramjet• RBCC

Integrated Systems• Staging• Thermal Management• Health Management• Power and Actuators• Intelligent/autonomous

controls

Airframe Structures and Materials• Long life, high temperature

structures & materials• TPS• Leading Edges• Control Surfaces • High-Temperature Seals

• Reusable Cryo Tanks



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.



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



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


SystemStudies

Technology Assessment

ID Task Name

1 '06 Tools Review2 '07 Technology Assessment Review (supports POP)3 '07 Tools Review4 '08 Technology Assessment Review (supports POP)5 '08 Tools Review6 Tool Development7 '07 Technology Assessment8 '07 Reference Vehicle Development9 '08 Technology Assessment10 '08 Reference Vehicle Development

3rd Quarter 4th Quarter 1st Quarter 2nd Quarter 3rd Quarter 4th Quarter 1st Quarter 2nd Quarter 3rd Quarter 4th Quarter 1st Quarter



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



Options for HypersonicDecelerators

Options for SupersonicDecelerators

Options for SubsonicDecelerators

Options for Terminal Descent Systems

Today’sViking Baseline

HMMES System Studies




VehicleDesign

StructuresLife CycleAnalysis

Optimization

Trajectory

VehicleClosure

Mass Props& Subsys

Config & Geometry

Aero/CFD

Thermal& TPS

Propulsion

Advanced Vehicle Integration & Synthesis Environment (AdVISE)

Integrated Design Environments Individual Discipline Tools(primarily level 4 specific)

Concept of Operations



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 uses

engineering methodsto extend a few highfidelity CFD solutionsover entire trajectory



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



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.



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.



backup slides



Hypersonic Systems Taxonomy

V∞ > 9 km/s V∞ < 9 km/s Ma/bmax > 15 Ma/bmax < 12 4 < Ma/b < 12

Entry Systems Ascent 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 < 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

• 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

*Ma/b=airbreathing Mach number

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