Accession Number:

AD0870696

Title:

Test Firing of a Supersonic Probe Thrust Vector Control Concept

Descriptive Note:

Technical rept

Corporate Author:

AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA

Personal Author(s):

Report Date:

1970-06-01

Pagination or Media Count:

38.0

Abstract:

The test firing of a rocket nozzle equipped with two fixed exit cone probes was conducted at the Air Force Rocket Propulsion Laboratory on a 36-inch inside diameter incuredpropellant solid rocket motor. The exit cone probes were designed to act as shock inducing members, thereby generating side forces for thrust vector control. The probes were of two different configurations, a thin shell of silver infiltrated tungsten, and a thick block of the same material. The thin shell probe was ejected early in the firing, while the thick block verison survived satisfactorily. The motor performed as desired, with a 740 psig maximum pressure, 15 second duration firing. LPC 614-A, a 16 percent Aluminum, PBAN binder propellant was utilized.

Subject Categories:

  • Metallurgy and Metallography
  • Guided Missiles
  • Combustion and Ignition
  • Solid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE