Electrolytic Ignition System for Monopropellants
Abstract
It was the objective of this work to utilize the electrolytic decomposition of hydrazine toward the improvement of starting pressurization transients in monopropellant rockets. The electrochemistry and heat generation involved during the electrolytic decomposition of propellant grade hydrazine was examined by means of polarography and chromatographic examination of the decomposition gases. Critical voltages of decomposition and related data obtained were incorporated into a thermal ignition model to aid in the design of a flow system ignition cell. It was found that engine ignition times of 2 to 5 milliseconds and pulse start transients of less than 15 milliseconds could be obtained in a simulated one-half thrust configuration. The ignition data and chamber pressure traces included in this report demonstrate the reproducibility of electrolytic ignitions through the electrolytic decomposition of hydrazine. Although the primary concern of this work was engine start-up, variables necessary to optimize ignition delay and maintain sustained engine operation after start-up were investigated.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 12, 1970
- Accession Number
- AD0864185
Entities
People
- B. P. Breen
- M. A. Mclain
- M. Gerstein