usa applied hypersonics t. jackson

USA Applied Hypersonics

Thomas A. Jackson, Ph.D.

Aerospace Propulsion Division

Propulsion Directorate

Air Force Research Laboratory

16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference

19-22 Oct 2009

Approved for Public Release88ABW-2009-4321

9 Oct 2009

2

Outline

• Introduction – USAF development approach for hypersonic, air-breathing propulsion

• US national efforts in air-launch free-flight• US national efforts in ground-launch hypersonic R&D• USAF/DARPA X-51 Scramjet Engine Flight Experiment• USAF/AUS DSTO HIFiRE Flight 2• US DARPA FaCET• US TES&T HyV• USAF Robust Scramjet S&T Program• Conclusion

Approved for Public Release 88ABW-2009-4321, 9 Oct 2009

3

AFRL’s Scramjet Technology Development Approach

Hypersonic Missiles/

Small Launch Systems

Stair-step approach builds

upon prior successes

Large Hypersonic Missiles

Small Launch Systems

Operationally Responsive Spacelift

(Robust, Responsive)

Small Scramjets

Medium Scramjets

Large Scramjets and CCEs

LRC

LRC

LRC

Ramjets

Hypersonic Missiles

(Time-Critical Targets)

198

0 ~

20

10

20

15

202

02

030

X-51 Program

Cleared for Public Release: #88ABW-2009-3878

National Hypersonic Flight Demo Landscape

Program Speed Significance First Flight

X-43A M 7,10 Airframe-Integ Mar 04

HyFly DCR M 6 Missile ATD Oct 07

X-51A M 6+ H/C Fuel Dec 09Cooled Engine

Blackswift M 6 Reusable 2012+Comb Cycle Engine


National Hypersonic Ground-Launch Flight Experiments

Program Speed Significance First Flight

FASTT M 6 accel free-flt Mar 04

HyShot M 8-10 low cost R&D Oct01-Jun07

(AUS)

HyCAUSE M 10 strm-trace IML Jun 07

(AUS/DARPA)

HIFiRE Flt2 M 6-8 Depressed Traj Nov 10

(AF/DSTO)

HyV M 5 Vitiation effects Mar 11Cleared for Public Release: #88ABW-2009-3878

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IntroductionScramjet Overview and Challenges

• Liquid Hydrocarbon (endothermic JP7) Fuelled• Fixed Geometry, Self-Starting Inlet• Nominal 10 lbm/sec airflow• Planar Cross-Section• Accelerate over 2 Mach numbers• Dual-Fuel Combustor Ignition System• Un-Cooled Engine Leading Edges, Inlet Ramp, Nozzle• Cooled Internal Inlet, Isolator, Combustor with Thermal

Balance at Cruise

Advanced endotherm-no depositsVariable internal contraction and BL bleed

Times 10 for large weapon application (10X)Shape transitions, axisymmetric, streamline-traced IML

Accelerate over 3+ Mach numbersRapid ignition on liquid fuel – Cold Start

Higher T materials and increased fuel endotherm

Endothermic Fuel Process:

~ 1000 BTU/lbm

Distribution A: 88ABW-2009-2489, 5 June 2009

• Acquire ground and flight data on an actively cooled, self-controlled operating scramjet engine (rules and tools development)

• Demonstrate viability of an endothermically fueled scramjet in flight

• Prove viability of a free-flying, scramjet powered, vehicle (Thrust > Drag)

X-51A Program Objective

Flight test the USAF Hypersonic Technology (HyTech) scramjet engine, using endothermic hydrocarbon fuel, by accelerating a vehicle from boost (~M=4.5) to Mach 6+

Cleared for Public Release: 88ABW-2008-0845

X-51A Propulsion Heritage

Ground Demo Engine 1 (June ’03)•Flight weight•Fuel cooled, but open loop fuel system

Performance Test Engine (Jan ’01)•Copper heat sink construction•Partial width flowpath

Ground Demo Engine 2 (Mar ’06)•Center engine for X-43C•Fuel cooled, closed loop fuel system

HyTech Flowpath

Development

X-51A Dev. Engine, SJX61-1 (Jul ’07)•Full X-51A forebody and nozzle•Fuel cooled, closed loop fuel system

X-51A FCE SJX61-2 (Oct 08)•Flight Clearance Engine•Flight fuel pump & instr.

X-51A propulsion system has strong foundation in past component & freejet tests

X-51A Flight Test


FTS, FTI and Control Systems• Antennas• Sensors• Control Actuators

JP-7 Fuel • Integral Tanks• 271 lb

Subsystems Bay • GCU/IMU/GPS• FADEC• Flight Test Instrumentation (FTI)

Engine Subsystems (Packaged Wet in JP-7)• Engine Fuel Pump

• Ethylene (Engine Start)• Nitrogen (Fuel Pressurization)

Fuel System• Fuel Pump

Batteries• Engine Systems• Actuators• Avionics and FTI• Flight Termination System (Separate)

(Li-ion Pack)

X-51A Subsystems Packaging


F119 FADEC Fuel Pump

Flowpath & Heat Exchanger

Vehicle Nozzle

Integral forebody / inlet

X-51A Propulsion Configuration

JP-7 Fuel Tank


Fuel Coolant Collection Manifold

Fuel Dist. Valves

Body Inlet Manifold

Fuel Coolant Inlets

Body Exit Manifold

Fuel-Cooled Scramjet OverviewClosed Loop Fuel System & Cold Start

SJX61-1 Ground Test Engine Configuration

Heat Exchanger Panel

Cold coolant fuel into HEX

Coolant fuel flo

w through Heat

Exchanger (HEX)

Hot coolant fuel out of HEX

Hot fuel into flowpath


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Four Vehicles in Assembly(Boeing Palmdale Facility)


13

Ground Test Operations

X-51 to B-52 Carriage Integration

X-51/B-52 on Aircraft System Integration

Electromagnetic Compatibility / Safety of Flight Test (EMC/SOF)


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HIFiREHypersonic International Flight Research Experimentation

• Joint program: U.S. AFRL and AUS DSTO … AFRL/RB Lead

• Up to 10 flights exploring fundamental hypersonic technologies

• AFRL/RZA prime for Flights 2 & 6 and Experiment Contributor in Flight 1

Pervasive Opportunities:• Experimental Approach – seconds of clean, high-speed flight• Core flow measurements with high spatial and temporal resolution

Flight 1: •Optically–based, engine air mass capture

HF2 Conceptual Payload LayoutHF2 Conceptual Payload Layout

Flight 1

Flight 2: •Ram-Scram mode transition•Scram performance•Scram stability (LBO)•Combustion progress

Distribution A: 88ABW-2009-2489, 5 June 2009

45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference Denver, Colorado August 2 - 5 2009

15

0

20000

40000

60000

80000

100000

120000

4 5 6 7 8 9 10

Mach Number

Alti

tude

(ft)

Nom. Flight Path

q=1000 psf

q=3000 psf

ShroudDeployment

Dual-mode to Scramjet-mode

Transition Experiment

~ 6 seconds

143.6-kPa (3000-psf)

47.9-kPa (1000-psf)

InletStart

Scramjet PerformanceExperiment

Nominal Flight Path

q=47.9 kPa (1000 psf)

q=143.6 kPa (3000 psf)

Nominal Trajectory / Test Window

• Flight Trajectory Objectives

• Constant Q0 trajectory of 86.2-kPa (1800-psf)

• 2 sigma Q0 range of 47.9 – 143.6-kPa (1000 – 3000-psf)

• Accelerating from Mach 5.5 – 8.5

• Test time ≥ 8 seconds in the test window

• Maintain ≤ ± 2° and ≤ ± 2°

• Flight Trajectory Objectives

• Constant Q0 trajectory of 86.2-kPa (1800-psf)

• 2 sigma Q0 range of 47.9 – 143.6-kPa (1000 – 3000-psf)

• Accelerating from Mach 5.5 – 8.5

• Test time ≥ 8 seconds in the test window

• Maintain ≤ ± 2° and ≤ ± 2°


45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference Denver, Colorado August 2 - 5 2009

16

TDLAS

Goal: Develop first generation compact diode laser systems Predecessor of system to measure combustion efficiency and thrust

System components Two independent flight electronic systems each with one distributed

feedback laser (DFB) scanned at 50,000 Hz Four detector channels per DFB Processed by custom-built electronics (Zolo Technologies, Inc.)

System specifications 2kg mass, 14W max power consumption Processed data telemetered at up to 1 kHz 8 simultaneous line-of-sight measurements

Isolator / Combustor

Nozzle


Notional Mach 6 prompt global ISR/strike aircraft

Turbine-Based Combined Cycle (TBCC)DARPA’s Falcon Combined-Cycle Engine Technology (FaCET)

FaCET freejet engine installed in AEDC APTU (Tullahoma, TN)

Reproduced with DARPA permission from4 Aug2009 AIAA JPC presentation of paper AIAA-2009-5537

Short Duration Propulsion Test and Evaluation (Hy-V) Program

• SDPTE Program established and combined with Hy-V Program• Goal is to resolve effects of duration and vitiation of ground test

media on DMSJ performance• Culminates with Mach 5 sounding rocket flight of two DMSJ

flowpaths

ATK Freejet TestsUVa Direct-Connect

TestsFlight at

NASA WFF

Prediction of Flight Performance- Thrust- Combustor pressure- Isolator pressure- Inlet operability- Heat flux

Cleared for public release AEDC PA 2009-292

Robust Scramjet 10X Program

• Narrowed scope to 10x (from 100x)

• Focus limited resources

• 1x to 10x is significant leap as a design challenge

• 10x is still compatible with national T&E infrastructure at least in direct-connect mode

• AFRL/RZA-led exercise with industry to identify technology gaps

Heavy Hypersonic Cruise Missile

• 10X Design Concept– Operation over range of 3 Mach

numbers within Mach 3.5 to 8.0– Operating dynamic pressure

range from at least 1000 to more than 2000 lbf/sq ft

– On-design captured air mass flow rate of 100 lbm/s

– Resultant off-design capture between 50 and 200 lbm/s

• Ops Concept– Air-launch from B-52H– Rocket boost

Primary Technology Gaps

•Ignition/Engine Start Sequence

•Flameholding Scaling and Flow Coupling

•Inlet Starting/Operability Limits

•Seals, Gaps, and Tolerances

•Shape Stable High Temperature Materials

•Thermal Management

•Fuel Modeling, Characterization , Stability19Distribution A: 88ABW-2009-2489, 5 June 2009

AFRL Hypersonic Propulsion Technology Programs

20

LRC

Combined Cycle Engine Components• Merge scramjet with turbine and

rocket engines for wide range of flight speeds

• Key to air breathing access to space

Robust Scramjet• 10X – 100X scale• Increased durability• Improved operability

X-51A Scramjet Engine Demonstration• Demo HyTech scramjet in flight• First flight FY09

Cleared for Public Release: # DOD 06-S-2154

LRC 10 X SED

LRC

100 X SED

usa applied hypersonics t. jackson

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