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1 Agenda WPML Background / Overview Program Highlights 2.75-inch Rocket Tests in Tank Subscale Tests in Va Tech Water Tunnel 5-inch Rocket Tests at NSWC Crane Lake Glendora Restrained Flyout Future Plans
2 Concentric Canister Launcher (CCL) Self-Contained Gas Management + Distributed Electronic Architecture Canister is an All-Up Launcher WCS WCS WCS CCL 1 CCL 2 CCL X CCL is is a Plug-n-Play Launch System, Electronically & Mechanically
3 CFD Computer Result for Flow of Rocket Exhaust through a CCL
4 CCL Surface Launch
5 Water Piercing Missile Launcher Concept
6 Benefits of WPML Concept Precludes need to pressurize missile for underwater launch Any existing service missile can be used without modification ATACMS ESSM AIM-9X Sidewinder PAM
7 Agenda WPML Background / Overview Program Highlights 2.75-inch Rocket Tests in Tank Subscale Tests in Va Tech Water Tunnel 5-inch Rocket Tests at NSWC Crane Lake Glendora Restrained Flyout Future Plans
8 2.75-inch Rocket Motor Tests CCLs with 7, 8, and 9 outer diameter MK66 (2.75 ) rocket motor as the gas source
9 2.75-inch Restrained Rocket Motor Test
10 2.75-inch Fly-out Experiment Modified 5 Navy Hi- Frag Projectile Mk66 Provides Thrust
11 2.75-inch Rocket Motor Flyout Test
12 Empirical Model for Predicting Jet Tip Trajectory Jet Tip Trajectory Data from 8 Tests with Three Launchers and Three Depths Distance Along Trajectory (Nondimensionalized by L m ) y = x R 2 = Time (Nondimensionalized using LM/V) Formula for trajectory from graph: y = x Let Z be a coordinate along the axis of the launcher starting at the exit plane and ending at the surface of the water, y (on the graphs above) = Z /Lm Let t be the time in seconds x (on the graphs above) = t/(lm/v) Substitute this into the equation for the trajectory on the graphs: Z/L m = x = (tV/Lm).5146 Solve for Z: Z=.01597L m (tv/lm).5146
13 Final Formula for a Jet Tip Trajectory Z Z = Jet tip height above the CCL exit L m = (Specific momentum flux) 3/4 / (Specific buoyancy flux) 1/2, where Specific momentum flux = Exhaust Area of CCL x Velocity 2, and Specific buoyancy flux = g (Volume Flux) (Density of Water-Density of Exhaust)/ Volume Flux = Velocity x Exhaust Area t = Time in Seconds V = Exit Velocity = L m (Density of Water), and tv L m.5146
14 Agenda WPML Background / Overview Program Highlights 2.75-inch Rocket Tests in Tank Subscale Tests in Va Tech Water Tunnel 5-inch Rocket Tests at NSWC Crane Lake Glendora Restrained Flyout Future Plans
15 Va Tech Water Tunnel Cross Flow Setup WPML is flush mounted onto flat plate Control of key variables Launcher exit velocity Launch depth Cross flow speed Shadowgraph images to record interface position U
16 Va Tech Water Tunnel Tests Mach # Cross Flow - 0 knots Time to Pierce -43ms Average Jet Velocity 31 fps
17 Va Tech Water Tunnel Tests Mach # Cross Flow knots Time to Pierce -48ms Average Jet Velocity 28 fps
18 Agenda WPML Background / Overview Program Highlights 2.75-inch Rocket Tests in Tank Subscale Tests in Va Tech Water Tunnel 5-inch Rocket Tests at NSWC Crane Lake Glendora Restrained Flyout Future Plans
19 Restrained Rocket Motor Test Series Objective Objective: Determine the water piercing capability of two different 5-inch diameter rocket motors through restrained firing tests at depths from feet Results will be used to update CFD models and scaling laws
20 5-Inch Rocket Motors Rocket Motor Average Thrust (lbf) Average Pressure (psi) Burn Time (Seconds) Nozzle Throat Area (square in) Avg. Mass Flow Rate (lbm/s) JATO ZUNI
21 Typical Test Setup
22 5-Inch Rocket Motor Launchers
23 Test Hardware Readiness Supporting Test Fixtures Launcher Cage Platform
24 5-inch Rocket Tests Conducted Test # Rocket Motor Depth (ft) Pierce? (Y/N) 1 JATO 10 Y 2 JATO 20 Y 3 Zuni 20 Y 4 JATO 27 Y 5 Zuni 32 Y 6 JATO 42 N 7 Zuni 40 Y? 8 JATO w/ Plug Nozzle 40 N 9 Zuni 40 Y 10 Zuni w/ Plug Nozzle 40 Y
25 Test Results Zuni at 32 feet Above Water Camera High Speed
26 Test Results Zuni at 32 feet DIDSON Acoustic Camera T= T=0.333 T=0.500 T=0.667 T= T=1.000 T=1.167 T=1.333 T=1.500 T=1.667
27 Test Results JATO at 42 feet Above Water Camera High Speed
28 Static Flyout Test 9/25/07 20 foot depth JATO Motor
29 Static Flyout Test 9/25/07 20 foot depth JATO Motor
30 Future Program Plan FY08 Translator Tests at NSWC Crane FY09, FY10 Open Ocean Fly Out Tests w/target FY11 Data Analysis, Decision on Submarine Integration FY12,13 Submarine Test with Prototype System FY14 Data Analysis, Transition to Acquisition Program FY08 FY09 FY10 FY11 FY12 FY13 FY14 TRL: 5 TRL: 6 TRL: 7 Translator tests at Lake Glendora (both flyout and restrained) Open Ocean Test (Proof-of- Concept Launcher) Open Ocean Test (Prototype Launcher) Analyze test results and make decision on Submarine Integration Submarine Integration in preparation for at sea demo on submarine Conduct submarine test with prototype system Data Analysis, final report and transition to acquisition program
31 Summary Tests and analysis have shown that the WPML concept is valid Continuing to Execute Program Plan FY08 Translator Tests at Lake Glendora FY10 Relevant Environment Test (Underwater Rail at San Clemente Island)
32 Questions?
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