Test Firing of a Supersonic Split-Line Nozzle
Abstract
A supersonic split-line (SSSL) nozzle test was conducted on the Air Force Rocket Propulsion Laboratory (AFRPL) 84-inch Char motor, utilizing a Gilmore six-component thrust stand. The side force amplification factor was determined to be about 1.07, with an estimated maximum error of plus or minus 5 percent. The torque required to actuate the nozzle was determined to be about 670 in-lb per degree with a maximum vector angle of 5.2 degrees. The maximum thrust was 21,200 pounds and the nozzle produced a maximum side force of about 1920 pounds at a deflection of 5.1 degrees. Burning and average chamber pressure were 36 seconds and 640 psi, respectively. The thrust stand exhibited much dynamic ringing in one of the axes, with very little in the other. The side- force-versus-time curves were essentially parallel to the nozzle duty-cycle curves. The test was a complete success, demonstrating the supersonic split-line concept by the measurement of a side force amplification factor greater than 1. 0.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1969
- Accession Number
- AD0865977
Entities
People
- Richard K. Strome
Organizations
- Air Force Research Laboratory