Accession Number : ADA483931


Title :   An Integrated Ignition and Combustion System for Liquid Propellant Micro Propulsion


Descriptive Note : Technical rept. 1 Sep 2006-31 Dec 2007


Corporate Author : PENNSYLVANIA STATE UNIV UNIVERSITY PARK DEPT OF MECHANICAL AND NUCLEAR ENGINEERING


Personal Author(s) : Yetter, Richard A ; Yang, Vigor ; Aksay, I A


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a483931.pdf


Report Date : 26 Jun 2008


Pagination or Media Count : 19


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.


Descriptors :   *MINIATURIZATION , *THRUSTERS , *LIQUID PROPELLANTS , FABRICATION , COMBUSTION , MONOPROPELLANTS , IGNITION , DIFFUSION , HIGH TEMPERATURE , SPECTROSCOPY , INTEGRATED SYSTEMS , PROPULSION SYSTEMS


Subject Categories : Combustion and Ignition
      Jet and Gas Turbine Engines


Distribution Statement : APPROVED FOR PUBLIC RELEASE