An experimental investigation was conducted to further determine the operating characteristics of the dual chamber rocket motor. Axisymmetric and two-dimensional apparatuses were used with air flow to simulate the actual flow. Without special design considerations the sustainer exhaust was found to always shockdown within the booster cavity except for very short booster lengths. Thrust was found to be insensitive to booster cavity length. With nozzle throat area ratios and booster diameters sized properly supersonic flow could be maintained within the booster cavity. Practical designs for actual motors appear quite feasible, especially for a nozzleless booster. (Author)
Experimental Investigation of the Dual Chamber Rocket Motor
1980
56 pages
Report
No indication
English
Rocket Engines & Motors , Combustion & Ignition , Booster rocket engines , Nozzleless rocket engines , Integral rocket ramjets , Simulators , Dual mode , Exhaust gases , Sustainer engines , Supersonic flow , Cavities , Thrust , Experimental design , Length , Blast tubes , Combustors , Solid propellant rocket engines , Dual chamber rocket engines , Shockdown
An Experimental Investigation of the Dual Chamber Rocket
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