GT16Low Freejet Summary

1
HyFly OverviewSeptember 2007
2
HyFly Dual Combustion Ramjet (DCR)
Boeing/Aerojet HyFly DCR
JHU/APL AWADM DCR

• Originally developed by JHU/APL for the Navy
  during 1970s-1980s
• Further maturation occurred under HWT and ARRMD
  Programs
• Operates from Mach 3-6 using conventional liquid
  hydrocarbon fuels
• Operates on fuel at ambient temperature (no
  heating reqd)
• Compatible with air- and surface-launch platforms
• Incorporates two inlet systems and unique
  dual-combustor concept

3
HyFly Program and Objectives

• Five Year ONR/DARPA Program 2002 Through 2007
• Develop and Demonstrate Advanced Technologies for
  Hypersonic Flight
• Flight Demonstration
• Emphasis on a Missile Application
• Build Up Complexity Through Progressive Flight
  Testing
• Demonstrate a Minimum 400 nm Range Capability
  (With an Objective of 600 nm) With a Block Speed
  Above 4400 ft/sec
• Demonstrate a Sustainable Cruise Speed of Mach 6
  or Greater
• Four Flights (First Two Already Completed)
• Separation Test Flight
• Boosted Test Flight
• Two Air-Breathing Propulsion Flights

4
HyFly Engine Utilizes the JHU/APL Dual Combustion
Ramjet (DCR)
DCR Combines the Best Features of a Ramjet and
Scramjet
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DCR Engine Concept

• Two Ram Inlets Provide Air to the Gas Generator
  (GG)
• All JP-10 Fuels the GG (Burns Rich)
• GG Fuels the Core of the Round Scram Combustor
• Four Scram Inlets Merge Together to Provide Air
  to the Outer Annulus of the Scram Combustor
• Flow in Supersonic Combustor Either Remains
  Supersonic or Becomes Subsonic with a Thermal
  Throat Downstream
• Dual Mode Combustor
• Mode is a Function of Mach and Fueling Level

6
HyFly Air Frame Assembly
Fuel Tank Shown During Weld Process
Titanium Casting
Airframe Ships To Aerojet for Engine Install
Fuel Tank Prepared for Heat Treat
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Engine Hardware Fabrication
8
HyFly Ground Test Vehicle
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HyFly Ground Test Strategy

• One-Third Scale Inlet Testing at Boeing PolySonic
  WT (PSWT)
• Full Scale Direct-Connect Testing at JHU/APL
• Full Scale Freejet Testing at NASA 8-FT HTT and
  AEDC APTU Facilities (4 Test Entries 2002
  2005)
• Test of the Complete Engine Flowpath (and Missile
  w/o Fins/Pods)
• Testing at Mach 3.3, 4.1, 4.8, and 6.5 0º, 2.5º,
  and 5º AOA 1º AOS

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Flight Engine vs. Freejet Engine Design
Flight Engine

• Since HyFly is a Missile, Reusability is Not
  Required
• Some Level of Material Degradation is Permissible
• An Un-cooled Design is Feasible
• Wetted Flow Path is Constructed Entirely from
  High Temperature Composite Materials

Freejet Engine

• Freejet Test Article Must Withstand Many
  Exposures
• Run Duration of 15-20 seconds or Longer 100
  Runs
• Freejet Engine is of Entirely Metallic
  Construction
• Thick Walls are Used to Provide a Heat Sink
  Design
• Water Cooling and Exotic Materials are Used in
  Some Areas

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Freejet Model Installation Differences at
the8-Ft. HTT and APTU Facilities

• Model was Installed Upright at the HTT and
  Inverted at APTU Due to Space Constraints
• Suspended From Large Frame Mounted to FMS at APTU
• Elevator Injects Model at the HTT No Elevator at
  APTU
• Model Position Changed at HTT to Set AOA Nozzle
  Moved at APTU

APTU Installation (Prior to Diffuser)
HTT Installation
Non-Metric Floor
Big Blue Frame
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A Pedestal Windscreen Was Designed for the 2nd
Entry of Freejet Testing in the 8-Ft. HTT

• Windscreen Shields the Forward Wedge of the
  Pedestal
• Windscreen is Bolted to the Non-Metric False
  Floor in the 8-Ft. HTT
• Windscreen Significantly Reduced the Support
  Structure Drag
• Still Higher Than Flight Due to Saddle and
  Remaining Pedestal Drag
• Implemented to Reduce the Uncertainty in Net
  Thrust Due to Potential Separation of the HTT
  Nozzle
• Separation Observed During a Portion of the 1st
  8-Ft. HTT Test Series
• Windscreen Resulted in the Direct Demonstration
  of Net Positive Force

False Floor
Windscreen
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Net Thrust Determination

• Net Thrust Calculation Requires 3 Runs
• Calibration, Mass Capture, and Performance Run
• Approach Requires Good Run-to-Run Repeatability
• Calibration Run
• Provides Freestream Properties
• Mass Capture Run
• Yields Air Mass Capture
• Yields External Drag
• Performance Run
• Yields Net Thrust

Dext
Fram
Fnoz
Faxial
DEXT (FMS Axial Force) (Ram Drag) (MC
Nozzle Gross Thrust)
Internal Drag
Dext
Fnet
FNET DEXT - (FMS Axial Force)
Faxial
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Performance Run Video

• Mach 4.8, NASA 8-Ft. HTT

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Flight Performance Prediction Approach

• Engine Performance Predicted Using the HFP Engine
  Code
• HyFly Flowpath Performance (HFP) Code
• Developed at Aerojet Under the Numerical
  Propulsion System Simulation (NPSS) Framework
  (NASA Glenn)
• CEA Equilibrium Thermochemistry, RJPA Logic, TDK
  Nozzle Analysis
• Inlet Testing, Direct-Connect Testing, CFD, and
  Other Analyses Provide Data to Develop Engine
  Component Models
• Components Assembled to Calculate Integrated
  Engine Perf.
• Freejet Tests Validate HFP Integrated Performance
  Results
• HFP Predicts Engine Performance Over the Flight
  Envelope

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HFP Validation Results

• HFP Code Prediction Compares Favorably With
  Freejet Results

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HyFly Flight Demonstrator is Air-Launched by a
Boeing F-15

• Flight Testing at Point Mugu (Western Test Range)
• Carried by F-15 to 40,000 ft Released at High
  Subsonic Mach
• Boosted to Air-Breathing Takeover Conditions by a
  Modified SLAT Booster (Government Furnished
  Surplus Booster)
• Booster Separates at End of Boost Inlet Shroud
  Deploys
• Air-Breathing Takeover Near Mach 3.5 Accelerates
  Up to Mach 6

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HyFly Flight Program Overview
Separation Test
Boost Test
Flight 1
Flight 2
Non-propulsive
Booster only
Booster FS1 DCR
Booster FS2 DCR

• Safe separation
• Rate capture
• Stabilize for boost
• Cntrl during boost
• EOB conditions
• Inlet Cover sep
• Booster sep

• Safe separation
• Rate capture
• Stabilize for boost

• Safe separation
• Rate capture
• Stabilize for boost
• Cntrl during boost
• EOB conditions
• Inlet Cover sep
• Booster sep
• DCR takeover
• Demo fuel cntrl
• Climb/accel to M5
• Invest un-start
• Invest re-light

• Safe separation
• Rate capture
• Stabilize for boost
• Cntrl during boost
• EOB conditions
• Inlet Cover sep
• Booster sep
• DCR takeover
• Demo fuel cntrl
• Climb/accel to M5
• Climb/accel to M6
• Flight Perf Data
• Terminal Accuracy

Completed 27 Jan 05
Completed 26 Aug 05
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Whats Next?

• Flight Testing

Photo HyFly Boost Test Vehicle
2 Flights Will Be Conducted in Fall 2007
Demonstrating Sustained DCR Engine Operation Up
To Mach 6
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Summary

• HyFly on track for first flight in September 2007
• HyFly will demonstrate that strike weapons with
  cruise speeds up to Mach 6 are feasible
• High-speed strike weapons are a cost-effective
  solution to counter time-critical targets