Knobley Technical Associates Phase I Innovative Ignition System Technologies for Advanced Solid Rocket Motors proposed program will identify and evaluate emerging innovative technologies leading to the feasibility demonstration of the selected system in a prototype low-cost and reliable ignition system for use in multi-pulse, end-burning solid propellant rocket motors. The program consists of an ignition system concept design/trade study in which a matrix of types and configuration of primary igniter charges, initiator types, transmission lines and transmission line installations will be defined and evaluated as candidates for use in a MIL STD 2105C insensitive munitions and MIL STD 1901A compliant multi-pulse ignition system. Pyrotechnic, pyrogen and rapid deflagrating cord type primary ignition materials and charge configurations compatible with the starter and rate augmented end-burning grains of multi-pulse tactical rocket motors will be evaluated. Likewise, an array of applicable initiator technologies including: electrically activated bridge-wire and Low Energy Exploding Foil Deflagrating Initiators (LEEFI), laser activated initiators, shock tube tip initiators and the emerging MEMS based initiator-ignition safety device systems will be evaluated as candidates for the highly loaded grain pulse motor application. The study will evaluate candidate power transmission lines and packaging arrangements of various types: i.e. insulated wires, low-inductance strip lines, fiber optics and shock tubes that extend from the forward-end mounted multi-function ISD's or alternate power source to the initiator/igniter charge positions. Assessments of the technology readiness level, producibility, reliability, and projected development and production cost for each of the most promising ignition systems will be completed. KTA will design and demonstrate the functionality and feasibility of the most promising candidate innovative igniter system as part of the Phase I Option program
Benefit: The proposed program will serve to define and demonstrate and ignition system that is compatible with the operational and packaging constraints of the emerging technology highly-loaded grain solid propellant rocket motor system. The MEMS study of the program has the potential to define a breakthough approach to introduce a lightweight, packageable and low ignition safety device in envelope constrained tactical rocket motors.
Keywords: Pulse Motors, Pulse Motors, initiators, Igniters, MEMS Ignition System, Ignition Safety Device, Highly Loaded Grains, Shock Tube, Laser Diode Ignition
