Advanced Propulsion for Tactical Missiles
-
Upload
lazos-vretsidis -
Category
Documents
-
view
196 -
download
37
Transcript of Advanced Propulsion for Tactical Missiles
Advanced Propulsion
For
Tactical Missiles
NDIA Conference on
Armaments for the Army Transformation
June 2001Mike Lyon, Acting Director
Propulsion and Structures Directorate
AMCOM
User Requirements
• Low operating and support costs• Controllability• Advanced materials• Minimum signature• High energy• Insensitivity• Minimal toxicity• Long life• High reliability
Aviation
Propulsion Cycles
Liqu
id r
ocke
t
Gel
roc
ket
Hyb
rid
rock
et
Air
-aug
roc
ket
Sin
gle
puls
e so
lid
Boo
st/s
usta
in s
olid
Pul
se s
olid
Pin
tle
solid
Turb
ojet
Air
tur
boro
cket
Pul
seje
t
Duc
ted
rock
et
Liqu
id r
amje
t
Sol
id r
amje
t
High energyLow cost
Min signatureHigh impulse / weight
High volumetric loading Propulsion characteristicsLong service life
Insensitive
ControllableLong range
High Vbo Missile requirementsEndgame capability
Highly maneuverable
Best suitedPartially suited
Ill-suited
Advantages of Controlled ThrustPropulsion Systems
Short Range Long Range
Search
High g End Game
Terminal Boost
LOA L
Low Velocity Long TOF
High VelocityShort TOF
LOB L
Approach
Air Turbo Rockets
Throttleable Solids
Turbojets
Gels
Army
Propulsion
Variable-area Nozzles
• 20:1 turn down• Up to 12” diameter• Axial and off-axis actuation• CFD modeling of pintle shapes• Evaluation of pintle materials
Variable Thrust Motor Static FiringTest #1
0.0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
Pin
tle
Po
siti
on
(in
.)
0
200
400
600
800
1000
1200
1400
1600
Th
rust
(lb
f)
0 5 10 15 20 25 30
Time (sec)
Measured ThrustMeasured PositionCalculated ThrustCalculated Position
VTM Test # 2 ResultsThrust and Pintle Position
Turndown Ratio of 14:1
Boost
Sustain
Pintle Controlled Solid TechnologyPressure vs. Time
0
500
1000
1500
2000
0 5 10 15 20Time, sec
Pre
ssur
e,ps
i
Pintle Propellant Burn Rate
Pressure, psi
1000
Bu
rn R
ate,
in/s
ec
0.1
1
Mix 1-1 Mix1-2 Mix1A-1 Mix1A-2
Regression Linesn=0.75
l Controllable, variable thrust propulsionl Tactical boost/sustain/coast profile with high
thrust turndown ratiol Ability of pintle to control pressure and thrust
within 2% of desired valuel Motor response times acceptable for tactical
applicationsl AMCOM-developed AN minimum smoke
propellant Non-Axial Heavywall Hardware
6 Inch Diameter Motor
Axial Pintle Motor Performance
0
500
1000
1500
2000
0 5 10 15Time, seconds
Pre
ssu
re, p
si
0
1
2
3
4
Pin
tle P
osi
tion
Pressure
PredictedPosition
“Self-healing” Properties
Gel bi-propulsion systems
• have controlled thrust• Minimize time to target ; Maximize range• Provide a variety of thrust profiles to perform multiple missions; end-game
enhancements
• are rugged and reliable• Demonstrated ruggedness by withstanding two hard landings with no evidence of leaks
• are survivable– Have plumes with minimum signature exhaust– Meet Insensitive Munitions requirements– Have gel propellants that:
• Are immobilized at ambient conditions• Have greatly reduced vapor pressure
FMTI Gel Propulsion System
Gas generator,pressure control
Coaxial tank
Fore-aft conduit
Bipropellant engine
•Key Features
•Fits in TOW envelope w/greater than2X TOW range
•Retains short time-of-flight for close-intargets
•On-demand, unlimited duty cycle,multi-pulse motor for velocity control
•Central conduit for missile fore-aftcabling and wave guide
•Can easily be sized for other missilesystems (Common Missile, ModernizedHellfire, etc.)
The AMCOM Impinging StreamVortex Engine (ISVE)
The ISVE was developed in AMCOM. Theoriginal patent was awarded in 1968 while themodern concept (shown here) was patented in1997 by AMCOM and is currently undergoingtest/evaluation in the Propulsion/StructuresDirectorate at AMRDEC (Redstone).
Fuel and oxidizer are injected through pairs of injector holesplaced along the chamber wall. Within a pair, these holes areslanted toward each other (the fuel/oxidizer streams impinge)and azimuthally so that vortical mixing is induced along thechamber wall. Impingement angles are set such that thevertical component of the stream momentum vector is zero.The wall is transpiration cooled by the flow. This mixing hasbeen shown to be beneficial for liquid and gelled propellants.
Benefits: Simple design allows for low cost hardware. For length constrainedsystems, small L/D for the combustion chamber means more engine length for flowexpansion. Stream impingement enhances atomization of gel propellant.
COMB.CHAMBER
INJECTOR PAIR NOZZLE
PRESSURE TAPS
ATR General Description
• Utilizes a compressor and turbine, similar to a turbojet orturbofan
• Also utilizes a secondary combustor much like a ramjet orducted rocket
• The turbine and compressor are linked by a mechanicaldrive shaft– turbine power from the gas generator fuel effluent drives the
compressor
Typical ATR Scheme
• Turbine drive gas:– Independent of compressor airflow– May be generated by a hot gas source
• a liquid or solid propellant gas generator– Utilized as the primary fuel source
Air Breathing Turbo-Rocket
• Independent Drive for Turbine Gives Higher Speed and Altitude Capability
• Static Thrust Allows Low Speed Takeoff
• Deep Throttleability Allows Loiter Capability Combined With High Speed Intercept
Fits Directly Between TurbojetsAnd Rockets Without Extreme
Technology Challenges
ATR Cycle Advantages
• Maximum speed superior to either a turbojet or turbofan• Compressor inlet temperature is the limiting component
parameter in an ATR– The compressor inlet temperature determines the maximum flight speed
for any given altitude– No rotating hardware in the hot section
• The ATR does not require a separate booster– Easily operates at low flight speeds at which a ramjet or ducted rocket
cannot operate– Performs well at sea level static conditions– High thrust per frontal area– High turn down ratio --- >10:1
ATR Design Challenges
• Most existing solid propellant gas generators are not optimized for use in anATR
• A suitable gas generator effluent must be:– An effective secondary combustor fuel
• Should maximize residual heating value• Retain excellent combustion properties
– An efficient turbine drive gas should have low molecular weight
• ATR secondary combustion chamber design is critical
– To maximize the operational performance of the cycle requires:• Short residence time• Must combust a potentially fuel rich equivalence ratio• Operate at low combustion pressures
DARPA/AMCOM Key Sponsors OfSmall Engine Development
Year Engine Thrust Program Flight Test1985 TJ-20 40 - 70 lb US Army MICOM MIG-29 Target 4
1989 TJ-90 105 lb US Army MICOM FOG-M Risk Reduction
1990 TJ-50 50 lb DARPA SENGAP Four Inch Engine
1994 TJ-50-1 50 lb DARPA/Northrop MALD POC 4
1996 TJ-50-3 50 lb Teledyne Ryan MALD POC 4
1996 TJ-50-10 57 lb DARPA/Ryan MALD ACTD 4
1997 TJ-65 80 lb DARPA Advanced Material Partnership
1999 TJ-50-11 52 lb US Army AMCOM PKAT Missile
1999 TJ-50M-1 120 lb DARPA/Ryan MALI ATD 4
2000 TJ-30 30 lb DARPA NetFires 4
Technology Goals and Tasks
• Advantages of Airbreathing Propulsion– Propulsion flexibility and multi-mission capability– Supports AMCOM missile systems– Very low fuel consumption– Benefits from advanced sensor and system technologies
• Target goals• low cost• expendable ( <15 minutes operation)• minimum of parts and hardware• microprocessor based components
Expendable Turbojet/TurbofanPerformance Comparison
0
200
400
600
800
1000
1200
1400
10 100 1000
Thrust Fn (lbf)
Th
rust
/Fo
nta
l Are
a (l
bf/
ft^2
)
Turbojets
TurbofansTCAE 373
TREND
SWB-4SWB-3
WI F121
NPT 171WI WR24-8
TCAE 312
ALLISON 150
WI F107TCAE J402
MALD TJ-50
MALI TJ-50M
HS TJ180
Allison 150 Fore & Aft
Quad Exhaust View
View into Compressor
Small 4.0 Inch Turbojet
• Sunstrand TJ-50– Successfully flown in flight tests
• 50 lbs thrust, <10 lbs weight• Simple design, no exotic materials• Engine Speed: 135,000 RPM
Key Technologies ForSmall Turbojets/Turbofans
• Very Small Combustors– Much higher heat loading than larger engines– Altitude starting
• Small Diameter Compressors– High efficiency aerodynamics in small sizes– Mixed flow for small diameter
• High Speed Bearings– >130,000 RPM
Availability of these technologies has given great improvementin the major vehicle parameter -
THRUST PER UNIT FRONTAL AREA
Technology Path
0
200
400
600
800
1000
1200
1400
10 100 1000
Thrust Fn (lbf)
Th
rust
/Fo
nta
l Are
a (l
bf/
ft^2
)
Current
Future
OldTechnology
Summary
Army’s propulsion
program
Air Turbo Rockets
Throttleable Solids
Turbojets
Gels
• Smarter
• Smaller
• Lighter
• More Lethal
• More Autonomous
• AFFORDABLE
End products