Upload
trinhdang
View
223
Download
0
Embed Size (px)
Citation preview
Ronald Veraar and Eelko v. Meerten (TNO)Guido Giusti (RWMS)
Flight and Terminal Ballistic Performance Demonstration of a Gun-Launched Medium Caliber Ramjet Propelled Air Defense Projectile
GMS conference, March 27-30, 2006Ramjet Projectile Performance Demonstration2
Contents
• Solid Fuel Ramjet Projectile Concept
• Ramjet Projectile Technology Development
• Ramjet Projectile Technology Demonstration Program• Programme definition• Design requirements and strategy• Projectile design• Free jet test facility and test results• Flight demonstration tests• Terminal ballistic firings• Conclusions
GMS conference, March 27-30, 2006Ramjet Projectile Performance Demonstration3
Solid Fuel RamJet (SFRJ) Projectile Concept
• No on-board oxidizer ⇒ superior propulsive performance• Applications
• Naval Fire Support, artillery (extended range & reduced time-to-target)
• Direct-hit ammunition (reduced time-to-target & increased kinetic energy)
• Technology development at TNO since 1980
GMS conference, March 27-30, 2006Ramjet Projectile Performance Demonstration4
Ramjet Projectile Technology DevelopmentCooperative TNO/FOI research program (1995-2000)
Demonstration SFRJ propulsion for generic projectile through
• design
• manufacturing
• development
• flight testing
Thrust equal to drag capability demonstrated in flight tests
GMS conference, March 27-30, 2006Ramjet Projectile Performance Demonstration5
Ramjet Projectile Technology Demonstration ProgramProgram definition
Joint effort by TNO and RWMS
Goal• Demonstrate SFRJ technology for a specific application
Application • Medium calibre spin-stabilised air defence projectile• Fired from a standard gun
Approach• Design• Manufacturing• Flight testing of a technology demonstrator• Firings to obtain indication of terminal ballistic performance
GMS conference, March 27-30, 2006Ramjet Projectile Performance Demonstration6
Ramjet Projectile Technology Demonstration ProgramProjectile design requirements & strategy• Requirements
• Total projectile length ≤ 179 mm• Projectile launch mass ≤ 0.375 kg• Acceleration load ~70000 g• Spin rate at launch ~80000 rpm• Propelled flight range ~3 km (~constant flight velocity)
• Design strategy• Geometric projectile design based on aero-thermodynamics• Mechanical design using geometric design as input• Perform experiments to verify different aspects of projectile
design• Iterate projectile design until requirements are satisfied
• Challenges• Extreme interaction between aerodynamic & mechanical design• Aero-heating of intake and gas dynamic heating of nozzle
GMS conference, March 27-30, 2006Ramjet Projectile Performance Demonstration7
Ramjet Projectile Technology Demonstration ProgramAero-thermodynamic projectile design
• Air intake design based on engineering design rules
• CFD calculations by CFS Engineering SA using NSMB code• Calculation of complete internal flow field of projectile
• Projectile flight performance prediction• RP5 = Engineering code modelling subsystem performance
and their interaction• Optimize projectile configuration
GMS conference, March 27-30, 2006Ramjet Projectile Performance Demonstration8
Ramjet Projectile Technology Demonstration ProgramMechanical projectile design
• Mechanical design based on engineering design rules
• Verification of structural integrity• Projectile structure by gun
firings• Fuel by tensile tests and
bonding tests• Fuel grain by gun firings
GMS conference, March 27-30, 2006Ramjet Projectile Performance Demonstration9
Ramjet Projectile Technology Demonstration ProgramFree jet test facility
• Following ignition problems encountered in TNO/FOI flight tests• To enable on-ground verification of intake performance and
projectile functioning• Free jet Mach numbers: 3.25 and 4.0• Fixed projectile as well as spinning set-up available
GSS Air heater Free jet nozzle Projectile set-up -
GMS conference, March 27-30, 2006Ramjet Projectile Performance Demonstration10
Ramjet Projectile Technology Demonstration Program Free jet aerodynamic heating tests• Aluminium nose cone• Schlieren video
• Projectile intake• Thermo-graphic image (top)• Schlieren image (bottom)
Material other than Aluminium is required for Mach 4 SL flight
GMS conference, March 27-30, 2006Ramjet Projectile Performance Demonstration11
Ramjet Projectile Technology Demonstration Program Free jet intake performance verification tests (1/2)• Fixed nozzle throat areas• Pressure measured at 4 locations
along combustor wall• CFD predictions performed by
CFS Engineering SA
0.00
0.05
0.10
0.15
0.20
0.25
0.00 0.02 0.04 0.06 0.08 0.10 0.12 0.14x-coordinate along combustor wall [m]
Free
str
eam
tota
l to
com
bust
or w
all p
ress
ure
ratio
[-]
CFD Dt=13.0mmExp. Dt=13.0mmCFD Dt=13.5mmExp. Dt=13.5mmCFD Dt=14.0mmExp. Dt=14.0mm Good agreement
with CFD predictions
GMS conference, March 27-30, 2006Ramjet Projectile Performance Demonstration12
Ramjet Projectile Technology Demonstration Program Free jet intake performance verification tests (2/2)
• Variable nozzle throat area• Good agreement with fixed nozzle
results
0.00
0.05
0.10
0.15
0.20
0.25
10 11 12 13 14
Equivalent throat diameter [mm]
Free
str
eam
tota
l to
com
bust
or w
all p
ress
ure
ratio
[-]
F020128-02Dt=13.0 mmDt=13.5 mmDt=14.0 mm
critical
sub-critical super-critical
Intake performance verification in one experiment
GMS conference, March 27-30, 2006Ramjet Projectile Performance Demonstration13
Ramjet Projectile Technology Demonstration Program Free jet projectile performance verification tests
• Pressure measured at 1 location• Fast auto-ignition• Stable and efficient combustion
until fuel burn-out
Proper functioning complete projectile demonstrated0.15
0.25
0.35
0.45
0.55
0.65
0.75
0.85
0.95
1.05
1.15
1.25
1.35
23.00 23.50 24.00 24.50 25.00 25.50 26.00 26.50 27.00 27.50 28.00 28.50 29.00
Time (s)
Pres
sure
(MPa
)
F 021031-03Ch39
air heater ignition
full ramjet ignition
ramjet burn-outair heater termination
GMS conference, March 27-30, 2006Ramjet Projectile Performance Demonstration14
Ramjet Projectile Technology Demonstration Program Flight demonstration tests
• Fast ignition• Constant flight velocity• Good reproducibility of flight
performance
-0.2
-0.1
0
0.1
0.2
0.3
0.4
0 0.1 0.2 0.3
Time of flight [s]D
rag
coef
ficie
nt [-
]T = D @ 1400 m/s = world record !
GMS conference, March 27-30, 2006Ramjet Projectile Performance Demonstration15
Ramjet Projectile Technology Demonstration Program Terminal ballistic firings (1/2)• Firings on range targets representing
the structure of a fighter aircraft
• Damage on target platesAll plates perforated
11 Aluminium plates with 2 mm thicknessSpacing between the plates 300 mmFirst plate 70 degrees NATO
GMS conference, March 27-30, 2006Ramjet Projectile Performance Demonstration16
Ramjet Projectile Technology Demonstration Program Terminal ballistic firings (2/2)• Firings on range targets representing
the structure of an armored helicopter
• Damage on target platesAll plates perforated
Spacing between the plates 700 mmFirst plate 10 mm RHA, 60 degrees NATOSecond plate 2mm Steel, 30 degrees NATOPlates 3-6: Aluminium plates with 2 mm thickness
GMS conference, March 27-30, 2006Ramjet Projectile Performance Demonstration17
Ramjet Projectile Technology Demonstration Program Conclusions• Projectile design satisfies mass & length requirements
• Structural integrity verified successfully in gun firings
• On-ground free jet tests verified• Aerodynamic heating• Intake performance• Projectile functioning
• Flight demonstration tests demonstrated• Very short ignition delay• Clear capability to maintain initial flight speed of 1400 m/s
• Firings on range targets demonstrated• Excellent terminal ballistic performance
SFRJ projectile technology = ready for application