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The Indian Head Division, Naval Surface Warfare Center (IHDIV, NSWC) has been involved with the laser initiation of energetic materials over the past 18 years. Specifically, the IHDIV, NSWC has been leading efforts in the basic research into laser ignitability of various energetic materials, developing cartridges and Cartridge Actuated Devices (CADs) incorporating this research, and ultimately implementing these new devices into a variety of aircrew escape system and weapon system applications. This paper presents an overview of one of these on-going programs: the effort to determine the laser ignitability characteristics of the MTV (Magnesium Teflon Viton) initiation material used in Mk 117 Mod 0 Jet Assisted Take-Off device. This example highlights one of the current efforts being conducted at the IHDIV, NSWC and supplements the previously presented technical papers offered at various the AIAA Conferences and other related symposia. The laser ignition capability is currently supporting several Department of Defense CAD/PAD programs. This paper will highlight the efforts underway to support an effort to determine the laser ignitability characteristics of the MTV (Magnesium Teflon Viton) and NOSIH-AA6 double base propellant used in the Mk 117 Mod 0 Jet Assisted Task-Off (JATO) device. This investigation is one phase of a larger investigation into several anomalies associated with this JATO and the BQM-74E Aerial Target system. FIELDED SYSTEM AND INVESTIGATION: BACKGROUND: This paper presents the IHDIV, NSWC current capability to study the laser ignition characteristics of various energetic materials used in various CAD/PAD (Cartridge Actuated Device/Propellant Actuated Device) applications. Determining the laser ignition characteristics of an energetic material greatly enhances the overall understanding of how this material reacts to a stimulus and supplements the standard mechanical, chemical, and ignition test parameters generated when an energetic material is studied. The IHDIV, NSWC approach to evaluating the laser ignition characteristics of energetic materials utilizes a 400 Watt Coherent, Inc. carbon dioxide (CO2) laser (10.6 micrometer wavelength) with a developed test methodology to generate two critical energetic material characteristics: a 50% ignition threshold level and identifying the time to first light (or ignition delay). The details of the test approach will follow. Photo 1: BQM-74E Aerial Target Launch The U.S. Navy has utilized the BQM-74E Aerial Target (Photo (1)) extensively for various training and weapon system tests over the past several years. The BQM-74E Target utilizes an on-board jet engine to provide over 200 pounds of thrust to sustain flight. The dual Mk 117 Mod 0 JATOs provide a combined thrust of approximately 7,000 pounds to launch the target both from land-based and from shipboard platforms. 1 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 10 13 July 2005, Tucson, Arizona AIAA 2005-3517 This material is declared a work of the U.S. Government and is not subject to copyright protection in the United States. Recently, the Navy has experienced several anomalies in which the JATO devices have either failed to ignite or have not provided continuous sustained thrust shortly after ignition. In these cases, the asymmetric thrust resulting from only one successful JATO have resulted in the complete loss of the aerial target (Photos (2), (3), and (4)). These photos were taken during a 3 May 2004 incident at the Naval Air Warfare Center – Weapons Division, Point Mugu, CA. e r Photo 5: JATO Initiator Configuration LASER IGNITABILITY TEST METHODOLOGY: In general, the test methodology adopted for all of the IHDIV, NSWC laser ignitability programs is very similar. Utilizing the carbon dioxide laser previously described, a mask with a 0.10-inch diameter hole in the center is used to limit the generated laser beam (normally the beam is 1.0-centimeters in diameter at the 1/e points). This 0.10inch beam delivers a controlled thermal input to the energetic material samples. For the NOSIH-AA-6 propellant, a series of 0.25-inch cube propellant samples were used. For the MTV ignition material, a series of short, extruded cylinders were used. All of these samples are centered in the test chamber in brass holders. These samples were prepared specifically for this investigation.

This paper presents the current U. S. Navy program to characterize energetic materials for unlimited use in varied applications and offers two examples of new materials that have undergone or are undergoing test and analysis required to complete this program. CP (Pentaammine (5-cyano-2H- tetrazolato-N2) cobalt (111) perchlorate) and BNCP (Tetraammine-cis-bis (5-nitro-2H-tetrazolato-N 2 ) cobalt (111) perchlorate) are two chemically related explosive materials developed and used in various Department of Energy (DOE) applications. In recent years, the use of CP and BNCP has been expanded to include detonators for some U. S. Navy missile and aircrew escape applications. Certification of CP has been granted based primarily on DOE-supplied performance and safety test data and analysis. A program to complete the characterization testing and analysis of BNCP between IHDIV, NSWC and Pacific Scientific (the primary manufacturer) is scheduled for completion in early 2002. The characterization program and the testing and analysis curlcluc~ccl ij, bdli tlx CP aid BNCP cncrgctic materials are detailed in this paper.

The Cartridge Actuated Device (CAD) Research and Development Branch was tasked by the Naval Air Warfare Center Aircraft Division, In-Flight Escape Systems Branch to continue to investigate, develop, test, and evaluate the potential to implement a laser energy based Signal Transmission System (STS) for the Advanced Technology Ejection Seat (ATES) Program. ATES is a team program and previous results have been presented by The Boeing Defense and Space Group in April 1998 and by the U. S. Navy at the Safety and Flight Equipment (SAFE) National Symposium in October 2000. The primary objective of the STS phase of the program is to determine the potential for utilizing an electronic sequencer containing laser diodes capable of generating sufficient power to initiate escape system cartridges and CADs. The fiber optic lines selected to transmit the laser signal, the specialized fiber optic connectors, and the energetic devices, which accept the signal and perform required functions, were also evaluated under this effort. This paper presents the design approach, fabrication process, and the test results generated when investigating laser-diode sequencers capable of meeting all ATES requirements. The test results and analysis used to evaluate the capability of the fiber optic lines, specialized fiber optic connectors, and laser ordnance devices are also presented. In conclusion, an approach to conducting ATES system-level sled tests is offered. BACKGROUND The Advanced Technology Ejection Seat (ATES) program is a demonstration effort being managed by the In-Flight Escape Systems Branch at the Naval Air Warfare Center Aircraft Division at Patuxent River, MD. All cartridge, Cartridge Actuated Device (CAD) and Signal Transmission System (STS) efforts are the responsibility of the IHDIV, NSWC CAD Research and Development Branch. The Boeing Company, Defense and Space Group in Seattle, WA, is the prime contractor for this effort. An Integrated Product Team approach has been implemented for this program to ensure an efficient evaluation and implementation of all concepts. The primary objective of this program is to integrate the controllable propulsion system developed as the Fourth Generation Escape System onto a modified AV-8B aircraft SIIIS Goodrich Universal Propulsion Company ejection seat. In addition, this program will demonstrate emerging Signal Transmission System (STS) technologies not previously evaluated under the Fourth Generation Escape System effort. The technical approach adopted by the team is to minimize development costs by adapting proven technology from other industries and programs where applicable, and then supplementing the technology gaps with small-scale development programs. To this end, the following ATES design has been selected by the team (See Conceptual Design (Figure (1)): Modified SIIIS (AV-8/B) seat platform with SIIIS baseline catapult Flight controller based on Boeing CREST and ACES II technology (new) Electronic laser sequencer (new) Laser/fiber optic signal transmission system (new) Laser Ordnance devices to accept input signal and generate ballistic pressure output (new) H-motor controllable propulsion system based on ACES II and NACES pintle nozzle technology (new) ACES II drogue and main parachutes (current) This paper is declared a work of the U.S. Government and is not subject to copyright protection in the United States. 1 American Institute of Aeronautics and Astronautics c)2001 American Institute of Aeronautics & Astronautics or Published with Permission of Author(s) and/or Author(s)' Sponsoring Organization. CATAPULT H MOTOR 9/1/98 ACTUATOR DRIVER SEAT BACK STRUCTUR

The Indian Head Division, Naval Surface Warfare Center (IHDIV, NSWC) is the lead service activity for cartridges, Cartridge Actuated Devices (CADs), and Aircrew Escape Propulsion Systems (AEPS) for the Department of Defense. In this role, the CAD Research and Development/Product Improvement Program'Branch has been actively investigating newly developed energetic materials for use in aircrew escape applications. Pacific Scientific, Energy Dynamics Division, has been active in the design, development, and production of detonators, cartridges, and CADs for these systems since 1968. Currently, Pacific Scientific is optimizing the production process for a new energetic material, BNCP, for use in these components. BNCP (Tetraamminebis (5-nitro-2H-tetrazolateo-N) cobalt (III) perchlorate) accepts an input stimulus and produces a detonation output. This paper presents a series of preliminary screening test results for a Government-owned electrical detonator design where BNCP has replaced the current ignition material. These test results supplement the prior findings which evaluated BNCP in an optical detonator configuration and were presented at the Joint Propulsion Conference in 1996 (AIAA Paper #96-2619)'.