A study was conducted to compare ballistic performance data obtained during testing at pressure altitudes of approximately 100,000 ft with performance data obtained during actual flights. The systems investigated included the Applications Technology Satellite Apogee Motor (JPL-SR-28-3), Communications Satellite Corporation Intelsat II Apogee Motor (AGC SVM-1), Anchored Interplanetary Monitoring Platform Spacecraft Retrograde Motor (TE-M-458), Scout Launch Vehicle third-stage Propulsion Unit (Hercules X-259), Scout Launch Vehicle fourth-stage Propulsion Unit and the Delta Launch Vehicle third-stage Propulsion Unit (UTC XSR 57-UT-1), Scout Launch Vehicle fourth-stage Propulsion Unit and the Delta Launch Vehicle third-stage Propulsion Unit (Hercules X-258), and the Apollo Service Module Primary Propulsion System (AGC AJ10-137). The performance data used for comparison were vacuum specific impulse data. The results of this study indicate that no significant difference between the true arithmetic means of AEDC simulated altitude test and flight specific impulse can be established for any of the propulsion systems investigated. (Author)
Comparison of Specific Impulse from AEDC Simulated Altitude and Flight Tests for Several Rocket Propulsion Systems
1969
54 pages
Report
Keine Angabe
Englisch
Rocket Engines & Motors , Liquid propellant rocket engines , Solid propellant rocket engines , Specific impulse , Analysis of variance , Liquid rocket propellants , Solid rocket propellants , Captive tests , Altitude chambers , Doppler radar , Telemetering data , Performance(Engineering) , Third stage engines , Fourth stage engines , Apollo , Apollo service module , Delta launch vehicles , Intelsat satellites , Scout
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