SBIR-STTR Award

Hybrid rocket motors based on gaseous and liquid oxidizers have been successfully demonstrated in the past. The offeror's proposed design consists of the consolidation of high performance solid or semi-solid oxidizers into individual high density sealed packages. These packets would be stored in the oxidizer section of the rocket and could be delivered at a controlled rate to the hybrid combustion chamber. Throttling and start/stop capabilities which are inherent characteristics of hybrid propulsion systems would be realized in this design. Delivery of these packets could be accomplished by a number of means such as pyrotechnics and gas charge or either method in combination with acceleration forces. Geometry of the packages can be tailored to optimize packaging, structural efficiency, delivery systems and storage (pressurization). Storage, stability, safety and munition sensitivity could be improved while realizing the benefits of these high performance oxidizers. Hybrid propulsion systems offer a number of advantages over conventional solid motors when used in conjunction with high performance oxidizers. Because the oxidizer is stored separately from the fuel component until use, the need to compound the oxidizer with the appropriate fuel/binder system is eliminated. This is a definite advantage because high performance oxidizers such as HNF have been shown to react with a number of common curative agents used in solid propellant binder systems. Hermetically sealed oxidizer packets minimize environmental exposure of the oxidizer compound and offer the potential for improved storage, deployment and long term stability. A successful packetized hybrid motor design has the potential of improving bulk loading limitations found in conventional hybrids. Hybrid rocket motors utilizing high performance storable oxidizers have commercial applications in military tactical missiles, ballistic targets and non-military aerospace propulsion systems.

Keywords:
Hybrid Missile Expulsion System Polymer Rocket Oxidizer Packet Regenerator Peroxide

The offeror's proposed development consists of the consolidation of a high performance oxidizer (defined as oxidizers having higher performance in some way than Ammonium Perchlorate) into solid or semi-solid high density packages. These packets would be stored in the oxidizer section of the rocket and could be delivered at a controlled rate to the hybrid combustion chamber. Efforts will be made in evaluating and down selecting several potential candidate high performance oxidizers. Potential materials include but are not limited to ADN, HNF, NP, HNE or CL20. This effort will involve numerous thermo-chemical computer simulations, a sophisticated analysis of actual and potential commercial availability and cost/performance trade offs. After the trade study is complete materials will be procured and/or formulated. In most cases advanced oxidizers are not suitable for use in standard solid propellant rocket motors due to short or long term stability problems caused by the interaction between the oxidizers and the fuel binder. Delivery of these oxidizer packets could be accomplished by a number of means such as pyrotechnics and gas charge or either method in combination with acceleration forces. The geometry of the packets could be tailored to optimize packaging, structural efficiency, delivery systems and storage. Storage, stability, safety and munitions sensitivity could be improved while realizing the benefits of these high performance oxidizers. As a follow on to the Phase I effort, Phase II will attempt to demonstrate improved performance of an advanced solid oxidizer hybrid motor in a full-sized tactical missile system. Full-scale testing will be conducted statically and will conclude with a full-up full scale firing. The objective of this project is to develop mufti-packet advanced solid oxidizer/solid fuel hybrid motor system suitable for use in tactical missiles.

Keywords:
Hybrid Missile; Expulsion System; Oxidizer Packet; Expulsion System; Advanced Solid Oxidizers