The primary goal of this project was to design, construct, and test a full scale, high pressure simulated propellant feed system test bed that could evaluate the ability of the Reciprocating Feed System (RFS) to provide essentially constant flow rates and pressures to a rocket engine. The two key issues addressed were the effects of the transition of the drain cycle from tank to tank and the benefits of other hardware such as accumulators to provide a constant pressure flow rate out of the RFS. The test bed provided 500 psi flow at rates of the order of those required for engines in the 20,000 lbf thrust class (e.g., 20 to 40 lb/sec). A control system was developed in conjunction with the test article and automated system operation was achieved. Pre-test planning and acceptance activities such as a documented procedure and hazard analysis were conducted and the operation of the test article was approved by, and conducted in coordination with, appropriate NASA Marshall Space Flight Center personnel under a Space Act Agreement. Tests demonstrated successful control of flow rates and pressures.
Experimental Assessment of the Reciprocating Feed System
42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit ; 2006 ; Sacramento, CA, United States
01.01.2006
Aufsatz (Konferenz)
Keine Angabe
Englisch
Experimental Assessment of the Reciprocating Feed System
British Library Conference Proceedings | 2006
|Experimental Assessment of the Reciprocating Feed System
AIAA | 2006
|Analytical Assessment of the Reciprocating Feed System
NTRS | 2006
|Analytical Assessment of the Reciprocating Feed System
AIAA | 2006
|Analytical Assessment of the Reciprocating Feed System
NTIS | 2006
|