Our patented VORTEX® engine thrust chamber assembly confines propellant mixing and burning to the core region of a coaxial vortex flow field. Enabling dramatic cost savings through robust design margins also leads to extremely high durability, reliability, and reusability in engines that are inexpensive to manufacture and maintain.
The coaxial vortex flow field is also applicable to hybrid rocket engine systems to produce fuel regression rates significantly higher than conventional hybrid configurations. This increase in fuel regression rate enables the use of a simple circular grain port, conferring significant gains in performance, reliability, and durability of hybrid systems.
We provide economical testing services for rapid development of rocket engine components and systems. Our test facilities are designed to cost-effectively test liquid rocket engines, hybrid rocket engines at thrust levels from 1lbf up to 150,000lbf. In addition, testing can be conducted for cryogenic components and instrumentation.
Our test facilities are currently configured for:
Completed upgrades provide infrastructure for LH2 and LCH4 testing and increased thrust levels for all propellants.
Diverse activities in propellants and combustion include the synthesis of new, non-toxic propellants, the study of gelled propellant combustion, and the development of new diagnostics for combustion and two-phase flows.
Synthesis work involves the development of safe, energetic hypergols, new oxidizers, and energetic binders. Several non-toxic hypergols designed to replace MMH have been developed. Our work targets the atomization, vaporization, mixing, and ignition of propellant gels. Diagnostic work includes spray analysis, phosphor thermometry, and gamma densitometry measurements. Gamma is applied to measure void fraction in cryogenic and other two-phase flows relevant to many propulsion applications.
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