Air-Augmented Rocket Propellant Screening Facility.
Summary rept. 15 Feb 69-1 Jan 71,
AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CALIF
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The report summarizes the results of an Air Force Rocket Propulsion Laboratory engineering development effort to design, fabricate and activate a laboratory-scale, direct-connect test facility. The facility, composed of a clean air supply system, a primary solid rocket combustor and a ramburner, is designed to support air-augmented rocket propellant development efforts. The versatile facility design allows variation in hardware configuration and propellant flow parameters to simulate a broad range of flight conditions, i.e., Mach No. 2 to 3.5 and altitudes from sea level to 50,000 feet. The air delivery system is designed for maximum conditions of 7 lbsec, 1000F and 250 psia. The annular inlet manifold is adaptable to either a 2-inch-diameter, center-perforated or 6-inch-diameter, end burning primary combustor. A variable-length, 5-inch-diameter ramburner is used. The combustion processes occurring in the primary and secondary chambers are monitored by means of wall pressure and temperature measurements, thrust measurement, residue sampling and optical techniques. Facility performance capabilities, system calibration and preliminary evaluation of baseline direct-connect testing are presented. Author
- Test Facilities, Equipment and Methods
- Solid Propellant Rocket Engines