This report describes the results of TRW injector development tests. This project, a task under the overall Minimum Cost Design Space Launch Vehicle (MCD/SLV) Program, has as a goal the development of low-cost injectors capable of performing at 90% theoretical Isp (shifting), 250,000-lb thrust using N2O4/UDMH propellants, and will evaluate their scalability up to the multimillion-lb-thrust class. A total of seven injector and three chamber configurations were tested. Maximum performance obtained was approximately 88% of test site theoretical shifting Isp (90% vacuum Isp). Dynamic combustion characteristics of this concept were evaluated by artificially inducing chamber pressure overpressures of 100% or greater. In all tests, chamber pressure recovered to within 10% of the original value within 30 to 40 milliseconds, and the engine is considered dynamically stable.


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    Title :

    Injector/Chamber Scaling Evaluation-TRW Injector Development


    Contributors:

    Publication date :

    1969


    Size :

    78 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English