Static Detonation Chamber M67 Rocket Motor Testing 25-27 May 2016 Presented to: The 19 th Annual International Chemical Weapons Demilitarisation Conference Presented by: Tim Garrett Anniston Site Project Manager APPROVED FOR PUBLIC RELEASE DISTRIBUTION UNLIMITED
Objective Determine Viability of Processing M67 Rocket Motors (RMs) in the Anniston Static Detonation Chamber (SDC) Support Permitting Actions to Increase Net Explosive Weight Limits: Resource Conservation and Recovery Act/Department of Defense Explosives Safety Board Collect SDC Emissions Data From M67 RM Testing 2
M67 Rocket Motor 3
Current Regulation Status Resource Conservation and Recovery Act Permit Limit <6.7 Pounds of Net Explosive Weight (NEW) Per Feed Department of Defense Explosives Safety Board <5.29 Pounds NEW Per Feed for Class 1.1 Explosives Dynasafe s Position - The Static Detonation Chamber is Capable of Safely Processing Higher NEW for Propellant 4
Modeling First Model M8 Propellant Second Model M67 Rocket Motors (RMs) (M28 Propellant) Used a Conservative Value to Predict Rupture Pressure of RM Casing (10 MegaPascal (MPa)) Concern About Overheating with Repeated Feed Added Atomizing Water Spray 5
Recommended Test Criteria Model Based Detonation Chamber 260 Pounds Per Square Inch Gauge (psig) Buffer Tank 87 psig Loading Chamber 2 180 psig 6
Study 3 Phases Phase 1 Process D541 M1 Propellant Gradually Increasing Net Explosive Weight (NEW) up to Approximately 23 Pounds 80% of 23 Pounds > NEW of an M67 Rocket Motor (RM) (18.13 Pounds NEW) Ramp-up Began 27 Aug 15 Approximate 1 Pound Increments from 7.30 Pounds to 23.13 Pounds Maximum Feed Events of 23.13 Pounds Conducted on 22 and 23 Oct 15 Process M28 Propellant Grains from an M67 RM at Approximately 23 Pounds Completed on 7 Jan 16 Feeds of 8.96 Pounds, 14.25 Pounds, and 23.12 Pounds Pressures Within Recommended Values 7
M28 Propellant Grain Pieces from an M67 Rocket Motor 8
Phase 1 Table of Results M28 Propellant Grain Pieces from an M67 Rocket Motor DC Detonation Chamber BT Buffer Tank LC2 Loading Chamber 2 9
Phase 2 Phase 2 Testing at Redstone Arsenal US Army Test and Evaluation Command High Temperature Test of M67 Rocket Motor (RM) to Determine How a RM Will Behave in the Static Detonation Chamber First Test Conducted 6 Jan 16» Diesel Fuel Temperature reached 1004 F when RM Ignited» Did Not Detonate» Casing Failed as Predicted at the Fore Cap 10
Video of M67 Rocket Motor High Temperature Test 6 Jan 16 11
Phase 2 (Continued) Phase 2 Testing at Redstone Arsenal US Army Test and Evaluation Command Second Test Conducted Week of 21 Mar 16» Heat Blankets» Pressure Sensors Temperature Reached 670 F When Rocket Motor Ignited Did Not Detonate Casing Failed as Predicted at the Fore Cap Burn Time was Approximately 1.6 Seconds 12
Video of M67 Rocket Motor High Temperature Test 23 Mar 16 13
Phase 2 (Continued) US Army Aviation and Missile Research, Development and Engineering Center Hydrostatic Test of M67 Rocket Motor Casing to Determine Failure Pressure and Failure Point Conducted Week of 11 Apr 16 14
Phase 3 Phase 3 Study Process 6 M67 Rocket Motors (RMs) and 3 M67 RM Grains in the Anniston Static Detonation Chamber Conduct Emissions Test for Information Purposes Scheduled for Week of 9 May 16 Concept of Feed - Dependent on Redstone Arsenal Results 15
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