The objective of this test program was to evaluate the feasibility of using a water-cooled nozzle on large solid propellant motors. The support requirement for this second nozzle test was 1100 gal/min coolant water flow with an inlet coolant pressure of 850 psi. The nozzle was successfully tested with no indication of burn-through or film boiling occurring. Test duration was 62 seconds at an average chamber pressure of 380 psi. Results of this test indicated the entire system operated satisfactorily at maximum operating conditions. (Author)
Demonstration Test Firing of a Water-Cooled Nozzle on a Solid Propellant Motor
1969
72 pages
Report
No indication
English
Rocket Engines & Motors , Missile Technology , Solid propellant rocket engines , Rocket nozzles , Cooling , Second-stage motors , Water , Pressurization , Captive tests , Erosive burning , Ablation , Alumina , Deposition , Film boiling , Nozzle closures , Nozzle gas flow , Cold flow , Checkout procedures , Minuteman , Minuteman 2 missiles , Titan 2 missiles
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