The design for this research project requires a small MKV design about the size of a small baseball and weighing a mere one kilogram. The final rocket design for the MKV will serve as an interception device for ballistic missile and will help to bring missile defense technologies to a new level. Combustion systems that are currently in use do not adhere to the small size requirements that this design entrails. Therefore, a new system must be design and tested for use in these micro rocket propulsion systems to be used in the MKVs.; Testing for the propulsion system began with cold flow testing and moved to the current hot fire testing. Hot fire testing was performed on all three injectors currently under study, the one, four and eight orifice injectors. Preliminary testing was performed with gaseous methane and oxygen.; These tests show qualities present at these conditions yet further testing is required to truly compare these results to those of the cold flow tests. Therefore, a new testing facility should be constructed and testing should be performed for the same conditions as the cold flow tests. (Abstract shortened by UMI.)
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