Accession Number:

ADA002245

Title:

Rocket Chamber Temperature Measurements by Microwave Techniques

Descriptive Note:

Final rept. 1 Oct 1970-31 Mar 1974

Corporate Author:

UTAH UNIV SALT LAKE CITY MICROWAVE DEVICE AND PHYSICAL ELECTRONICS LAB

Personal Author(s):

Report Date:

1974-07-01

Pagination or Media Count:

157.0

Abstract:

Microwave attenuation techniques are used to find the combustion chamber temperature of a solid rocket motor, and the predicted value calculated by a theoretical specific impulse computer program and the value calculated with the microwave measurements agree within three percent. The propellants used in this investigation were seeded with five percent potassium perchlorate by weight to furnish enough electrons in the plasma to cause measurable attenuation. The propellants were also seeded with 5 to 10 percent aluminum to produce suspended metallic particles in the plasma. The temperature profile inside the combustion chamber is determined for a distance of two inches away from the burning surface by scanning the focused microwave signal transverse to the combustion chamber and by using the motion of the burning surface with respect to the antennas.

Subject Categories:

  • Plasma Physics and Magnetohydrodynamics
  • Combustion and Ignition
  • Solid Propellant Rocket Engines
  • Solid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE