Combustion Processes in Space Storable Liquid Rocket Engines

Period of Performance: 10/01/1993 - 09/30/1995


Phase 2 SBIR

Recipient Firm

Software & Engineering Assoc., Inc.
1802 N. Carson Street, Suite 200
Carson City, NV 89701
Principal Investigator


Computer software is to be developed that will provide a capability for studying the over-all performance of liquid fueled rocket engines. A generalized method will be used so that all engine cycles or current and projected usage can be evaluated, and compared on a consistent basis. The emphasis is to be placed on cryogenic propellants; specifically LOX/LH2. Other propellant combinations to be included are NTO/MMH, NTO/A5O, and LOX.RP-1. Engine components to be modelled include tanks, lines, valves, turbines, pumps heat exchangers, combustion chambers, etc. The effects of heat transfer on the performance of these devices are to be calculated. Pump fed engines are of particular interest. Steady state engine performance is to be derived after first calculating transient performance. The code is to be validated using transient data from existing engines, such as the RL-10. Extensive documentation will be provided so that the users can understand the basis for the analysis. An innovative feature of the project is the application of a "Fourth Generation" language to construct a Graphics User Interface (GUI). The GUI is to be designed so that the user is effectively guided in setting up the engines that are to be analyzed.