Accession Number : AD0475564


Title :   THRUST VECTOR DETERMINATION FOR THE APOLLO SERVICE PROPULSION ENGINE USING A SIX-COMPONENT FORCE BALANCE


Descriptive Note : Technical rept. 1 Sep 1964-11 Jul 1965


Corporate Author : ARO INC ARNOLD AFS TN


Personal Author(s) : Robinson, C E ; Runyan, R B


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/475564.pdf


Report Date : Dec 1965


Pagination or Media Count : 50


Abstract : A multicomponent force system was developed to determine the line of action of the forces generated by the Apollo Service Module engine. This force system was a force balance based on the principles of linear and repeatable installation tare effects. The basic concepts of the force balance and the statistical accuracies which were achieved are presented along with a detailed discussion of the calibration procedure and data reduction methods. Thrust vector excursion for two ablative combustion chambers during nongimbaling engine operation and limited thrust vector data during gimbaling operation are also presented. The precision of the thrust vector data was determined to be 0.033 deg for angular measurement and 0.026 in. for position determination.


Descriptors :   *LIQUID PROPELLANT ROCKET ENGINES , *LUNAR CRAFT , ABLATION , ALIGNMENT , ALTITUDE CHAMBERS , BALANCES , CALIBRATION , CAPTIVE TESTS , COMBUSTION CHAMBERS , ERRORS , EXPERIMENTAL DATA , FORCE(MECHANICS) , INSTALLATION , INSTRUMENTATION , MANNED SPACECRAFT , MISALIGNMENT , MOVABLE ROCKET ENGINES , PERFORMANCE(ENGINEERING) , SPACE CAPSULES , THRUST


Subject Categories : Liquid Propellant Rocket Engines


Distribution Statement : APPROVED FOR PUBLIC RELEASE