An Integrated Ignition and Combustion System for Liquid Propellant Micro Propulsion
Abstract
Liquid monopropellant microthrusters utilizing electrolytic ignition were designed, fabricated, and analyzed. Low temperature co-fired ceramic tape technologies were used initially to fabricate microscale burners in order to evaluate the applicability of the technology to high temperature combustion systems. Microscale diffusion flames were stabilized in the burners, and optical spectroscopy measurements were performed to characterize the flame behavior. The low temperature co-fired ceramic tape technologies were then applied to the fabrication of microthrusters. The microthrusters had integrated silver electrodes to enable ignition of hydroxylammonium nitrate based liquid monopropellants by electrolytic decomposition. The volume of the thruster combustion chamber was 0.82 mm3. The microthruster was successfully ignited, and a thrust output of approximately 200 mN was measured with a voltage input of 45 V. Energy input as small as 1.9 J was achieved for ignition, and ignition delay as short as 224.5 ms was recorded.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 26, 2008
- Accession Number
- ADA483931
Entities
People
- I. A. Aksay
- Richard A. Yetter
- Vigor Yang
Organizations
- Pennsylvania State University