ELECTRIC ARC DISCHARGE IN SUPERSONIC FLOW FOR THRUST VECTOR CONTROL
Abstract
The phenomenon of disturbances caused by electric arc discharge in a supersonic flow was studied both analytically and experimentally. The purpose was to study the feasibility of using this concept for attitude control of space vehicles. A possible application for rocket propelled vehicles was selected for the test condition of an experimental program. Fair agreement was obtained between the test results and the analytical solutions. It was found that: (1) A local static pressure rise can be created by the electric discharge in a supersonic stream; (2) The electric field to initiate discharge was about 2000 volts/in for nitrogen stream at Mach number 2.5 with static pressure of 2 psia and stagnation temperature of 4000 R; (3) The arc discharge, without a magnetic field, in a supersonic flow of Mach number 2.5 can be maintained and is stable; (4) The affected area is small which resulted in small side force; (5) The generated side force per unit electric power input is small in view of the available electric power supply. The use of an electric discharge for practical thrust vector control of rocket motors is only feasible if the power supply can be improved.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1967
- Accession Number
- AD0822593
Entities
People
- Jain-ming Wu
- Shen C. Lee
Organizations
- University of Tennessee Space Institute