Accession Number : AD0875313
Title : Thrust Measurement for Lance Engine Testing, Extended Range Lance Tests Through Test No. 6922.
Descriptive Note : Test evaluation rept.,
Corporate Author : ARMY MISSILE RESEARCH DEVELOPMENT AND ENGINEERING LAB REDSTONE ARSENAL AL TES T AND EVALUATION DIRECTORATE
Personal Author(s) : Presson, A. W.
Report Date : 24 MAR 1970
Pagination or Media Count : 53
Abstract : The LANCE engine testing has been performed on test stands designed to measure the six components of thrust reaction. The basic problem inherent in such stands is that of restraining the engine with a measurement system that permits the engine 6 degrees of freedom without the introduction of unknown effects upon the engine. This is further compounded by the requirement to supply propellants through a high-pressure plumbing system that shunts the measurement system. This report provides details of the calibration procedures, data acquisition and analysis methods, and results that are relevant to the period of 'C' casting tests through engine test No. 6922. Because prior experience had indicated synergistic effects among the components, the program adopted was geared to an empirical approach. The premise of this scheme was that a practical number of the infinite number of possible combinations of components could be evaluated to derive equations relating the true input components to the observed output components. A step-wise multiple linear regression technique was used to define these relationships. Calibration hardware was devised to provide servo-controlled and cycled input loads to the measurement system while the complete data acquisition system was utilized to monitor the inputs and the outputs simultaneously. Propellant line pressurization and flow dynamics effects were also tested. This provided a complete through-the-system calibration. (Author)
Descriptors : *LIQUID PROPELLANT ROCKET ENGINES), *ARTILLERY ROCKETS), (*TEST EQUIPMENT, (*CAPTIVE TESTS, FORCE(MECHANICS), MEASUREMENT, LOADS(FORCES), THRUST, CALIBRATION, REGRESSION ANALYSIS.
Subject Categories : Test Facilities, Equipment and Methods
Liquid Propellant Rocket Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE